RS-25 - Knowledge

1227: 710:). The discharge flow from the turbopump is routed to, and through, the main valve and is then split into three flow paths. One path is through the jacket of the main combustion chamber, where the hydrogen is used to cool the chamber walls. It is then routed from the main combustion chamber to the LPFTP, where it is used to drive the LPFTP turbine. A small portion of the flow from the LPFTP is then directed to a common manifold from all three engines to form a single path to the liquid hydrogen tank to maintain pressurization. The remaining hydrogen passes between the inner and outer walls of the hot-gas manifold to cool it and is then discharged into the main combustion chamber. A second hydrogen flow path from the main fuel valve is through the engine nozzle (to cool the nozzle). It then joins the third flow path from the chamber coolant valve. This combined flow is then directed to the fuel and oxidizer pre-burners. The HPFTP is approximately 550 by 1,100 mm (22 by 43 in) in size and is attached to the hot-gas manifold by flanges. 1753: 36: 865: 494: 1584:

could operate safely at levels above 100%, these higher levels became standard. Maintaining the original relationship of power level to physical thrust helped reduce confusion, as it created an unvarying fixed relationship so that test data (or operational data from past or future missions) can be easily compared. If the power level was increased, and that new value was said to be 100%, then all previous data and documentation would either require changing or cross-checking against what physical thrust corresponded to 100% power level on that date. Engine power level affects engine reliability, with studies indicating the probability of an engine failure increasing rapidly with power levels over 104.5%, which was why power levels above 104.5% were retained for contingency use only.

815: 806:(CMCs). These materials possess significantly lower thermal conductivities than metallic alloys, thus allowing more efficient combustion and reducing the cooling requirements. TBCs are thin ceramic oxide layers deposited on metallic components, acting as a thermal barrier between hot gaseous combustion products and the metallic shell. A TBC applied to the Inconel 718 shell during production could extend engine life and reduce cooling costs. Further, CMCs have been studied as a replacement for Ni-based superalloys and are composed of high-strength fibers (BN, C) continuously dispersed in a SiC matrix. An MCC composed of a CMC, though less studied and farther from fruition than the application of a TBC, could offer unprecedented levels of engine efficiency. 851:(about 69:1) for the chamber pressure. At sea level, a nozzle of this ratio would normally undergo flow separation of the jet from the nozzle, which would cause control difficulties and could even mechanically damage the vehicle. However, to aid the engine's operation Rocketdyne engineers varied the angle of the nozzle walls from the theoretical optimum for thrust, reducing it near the exit. This raises the pressure just around the rim to an absolute pressure between 4.6 and 5.7 psi (32 and 39 kPa), and prevents flow separation. The inner part of the flow is at much lower pressure, around 2 psi (14 kPa) or less. The inner surface of each nozzle is cooled by liquid hydrogen flowing through 992: 1853:, with different versions of the rocket being equipped with between three and five engines. The initial flights of the new launch vehicle are making use of previously flown Block II RS-25D engines, with NASA keeping such engines in a "purged safe" environment at Stennis Space Center, "along with all of the ground systems required to maintain them." For Artemis I, the RS-25D units with serial numbers E2045, E2056, E2058, and E2060 from all three orbiters were used. They were installed on the core stage by November 6, 2019. For Artemis II, the units with serial numbers E2047, E2059, E2062, and E2063 will be used. They were installed on the core stage by September 25, 2023. 1602: 719: 480: 1951:

limits. Tests of the engine continued in 2023; on February 8, 2023, it was fired for 500 seconds at 111% power, fitted with a new-production nozzle. Subsequent tests included a 600-second test at 111% power on February 22, a 520-second test at 113% power on March 8, a 600-second test at 113% power on March 21, a 500-second, 113% power level test on April 5, a 720-second fire that tested the engine's thrust vectoring gimbal system on April 26, a 630-second test on May 10, and five more 500-second, 113% power level tests without gimbaling on May 23, June 1, June 8, June 15, and June 22.

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launch vehicle, the gimbal bearing allows the engine to be pivoted (or "gimballed") around two axes of freedom with a range of ±10.5°. This motion allows the engine's thrust vector to be altered, thus steering the vehicle into the correct orientation. The comparatively large gimbal range is necessary to correct for the pitch momentum that occurs due to the constantly shifting center of mass as the vehicle burns fuel in flight and after booster separation. The bearing assembly is approximately 290 by 360 mm (11 by 14 in), has a mass of 105 lb (48 kg), and is made of

1313: 522: 1418:, as the RS-25D stock is intentionally being used up. Unlike previous versions, this engine is designed to be expendable. The powerhead is almost completely redesigned (as of September 2023 the specific design changes from the -25D have not been announced), and intended to incorporate various cost-saving measures and innovations in manufacturing. The first testing engine, E10001, passed all its qualifications and tests at NASA's Stennis Space Center, and demonstrated both a 113% FPL and a 30% increase in thrust. 1186:

Shuttle's components, including the engines, was conducted in 1979. The design reviews operated in parallel with several test milestones, initial tests consisting of individual engine components which identified shortcomings with various areas of the design, including the HPFTP, HPOTP, valves, nozzle, and fuel pre-burners. The individual engine component tests were followed by the first test of a complete engine (0002) on March 16, 1977, after its final assembly line was established in the main Rocketdyne factory in

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Engine 2's (serial number E2056) Core Stage Auxiliary Power Unit (CAPU) during the thrust vector control (TVC) system test. Engine 2's CAPU was shut down automatically, although if this issue had occurred during flight, it would not have caused an abort, as the remaining CAPUs are capable of powering the TVC systems of all four engines. The engine also suffered a different "Major Component Failure", in the engine control system, that was caused by instrumentation failure. This

2063: 2051: 2039: 2027: 2015: 980: 676:. The liquid oxygen flows through an anti-flood valve that prevents it from entering the heat exchanger until sufficient heat is present for the heat exchanger to utilize the heat contained in the gases discharged from the HPOTP turbine, converting the liquid oxygen to gas. The gas is sent to a manifold and then routed to pressurize the liquid oxygen tank. Another path enters the HPOTP second-stage pre-burner pump to boost the liquid oxygen's pressure from 30 to 51 MPa (4,300 1160:, de Laval-type engine. The request was based on the then-current design of the Space Shuttle which featured two reusable stages, the orbiter and a crewed fly-back booster, and required one engine which would be able to power both vehicles via two different nozzles (12 booster engines with 550,000 lbf (2,400 kN) sea level thrust each and 3 orbiter engines with 632,000 lbf (2,810 kN) vacuum thrust each). Rocketdyne, P&W and 745:

oxidizer and fuel pre-burner oxidizer valves increase or decrease the liquid oxygen flow, thus increasing or decreasing pre-burner chamber pressure, HPOTP and HPFTP turbine speed, and liquid oxygen and gaseous hydrogen flow into the main combustion chamber, which increases or decreases engine thrust. The oxidizer and fuel pre-burner valves operate together to throttle the engine and maintain a constant 6.03:1 propellant mixture ratio.

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cooling and chamber coolant valve systems is then sent via pre-burners into the HPFTP turbine and HPOTP before being reunited again in the hot gas manifold, from where it passes into the MCC injectors. Once in the injectors, the propellants are mixed and injected into the main combustion chamber where they are ignited. The ejection of the burning propellant mixture through the throat and bell of the engine's nozzle creates the thrust.

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three seconds because the combustion process is then self-sustaining. The pre-burners produce the fuel-rich hot gases that pass through the turbines to generate the power needed to operate the high-pressure turbopumps. The oxidizer pre-burner's outflow drives a turbine that is connected to the HPOTP and to the oxidizer pre-burner pump. The fuel pre-burner's outflow drives a turbine that is connected to the HPFTP.

508: 1362:, the Block I engines offered improved turbopumps featuring ceramic bearings, half as many rotating parts, and a new casting process reducing the number of welds. Block I improvements also included a new, two-duct powerhead (rather than the original design, which featured three ducts connected to the HPFTP and two to the HPOTP), which helped improve hot gas flow, and an improved engine heat exchanger. 1281:(SRBs), which committed the shuttle to the launch. At launch, the engines would be operating at 100% RPL, throttling up to 104.5% immediately following liftoff. The engines would maintain this power level until around T+40 seconds, where they would be throttled back to around 70% to reduce aerodynamic loads on the shuttle stack as it passed through the region of maximum dynamic pressure, or 3924: 2097: 1249: 1376:, the Block IIA engine was an interim model used whilst certain components of the Block II engine completed development. Changes included a new large throat main combustion chamber (which had originally been recommended by Rocketdyne in 1980), improved low-pressure turbopumps, and certification for 104.5% RPL to compensate for a 2 seconds (0.020 km/s) reduction in 902:, thereby enabling each system to detect failures by comparing the signal levels on the buses of the two M68000 processors within that system. If differences are encountered between the two buses, then an interrupt is generated and control turned over to the other system. Because of subtle differences between M68000s from Motorola and the second source manufacturer 1955:

tested to 113% power levels for 500 seconds on November 15, and to 113% for 650 seconds with gimbaling on November 29, 2023, to 113% for 500 seconds on January 17, 2024, January 23, and January 29, to 113% for 550 seconds on February 23, to 111% for 615 seconds on February 29, and to 113% for 600 seconds on March 6 and 500 seconds on March 22 and 27, and April 3.

1212:, before being removed in 1980 for further testing and reinstalled on the orbiter. The engines, which were of the first manned orbital flight (FMOF) configuration and certified for operation at 100% rated power level (RPL), were operated in a twenty-second flight readiness firing on February 20, 1981, and, after inspection, declared ready for flight. 1928:

the four-engine configuration and its position in-plane with the SLS booster exhaust nozzles. New ablative heat-shield insulation was to be tested as well. Tests occurred on January 9 (500 seconds), May 28 (450 seconds), June 11 (500 seconds), June 25 (650 seconds), July 17 (535 seconds), August 13 (535 seconds) and August 27 (535 seconds).

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104.5%. Existing engines used on the Space Launch System are throttled to 109% power during normal flight, while new RS-25 engines produced for the Space Launch System are to be run at 111% throttle, with 113% power being tested. These increases in throttle level made a significant difference to the thrust produced by the engine:

890:(M68000) processors (for a total of four M68000s per controller). Having the controller installed on the engine itself greatly simplifies the wiring between the engine and the launch vehicle, because all the sensors and actuators are connected directly to only the controller, each MEC then being connected to the orbiter's 575:(SLS), fuel and oxidizer from the rocket's core stage flow directly into the MPS lines. Once in the MPS lines, the fuel and oxidizer each branch out into separate paths to each engine (three on the Space Shuttle, four on the SLS). In each branch, pre-valves then allow the propellants to enter the engine. 1583:

Specifying power levels over 100% may seem nonsensical, but there was a logic behind it. The 100% level does not mean the maximum physical power level attainable, rather it was a specification decided on during engine development—the expected rated power level. When later studies indicated the engine

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The most obvious effects of the upgrades the RS-25 received through the Space Shuttle program were the improvements in engine throttle. Whilst the FMOF engine had a maximum output of 100% RPL, Block II engines could throttle as high as 109% or 111% in an emergency, with usual flight performance being

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To control the engine's output, the MEC operates five hydraulically actuated propellant valves on each engine; the oxidizer pre-burner oxidizer, fuel pre-burner oxidizer, main oxidizer, main fuel, and chamber coolant valves. In an emergency, the valves can be fully closed by using the engine's helium

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the two MECs (from engines 2020 and 2021), recovered from the seafloor, were delivered to Honeywell Aerospace for examination and analysis. One controller was broken open on one side, and both were severely corroded and damaged by marine life. Both units were disassembled and the memory units flushed

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and MCC, or through the chamber coolant valve. The fuel passing through the MCC cooling system then passes back through the LPFTP turbine before being routed either to the fuel tank pressurization system or to the hot gas manifold cooling system (from where it passes into the MCC). Fuel in the nozzle

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The RS-25E developmental unit E0525, with significant inclusion of new components including a redesigned nozzle, hydraulic actuators, flex ducts and turbopumps, was hot fire tested to 111% power levels for 550 seconds in the first in a series of certification tests beginning October 17, 2023. It was

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In 2015, a test campaign was conducted to determine RS-25 engine performance with a new engine controller unit, under lower liquid-oxygen temperatures, with greater inlet pressure due to the taller SLS core-stage liquid-oxygen tank and higher vehicle acceleration; and with more nozzle heating due to

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and to the engine by its lower flange. It represents the thrust interface between the engine and the launch vehicle, supporting 7,480 lb (3,390 kg) of engine weight and withstanding over 500,000 lbf (2,200,000 N) of thrust. As well as providing a means to attach the engine to the

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called NARloy-Z, developed specifically for the RS-25 in the 1970s. Around 390 channels are machined into the liner wall to carry liquid hydrogen through the liner to provide MCC cooling, as the temperature in the combustion chamber reaches 3300 °C (6000 °F) during flight – higher than the

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Four RS-25 engines are installed on each Space Launch System, housed in the engine section at the base of the core stage, and expended after use. The first four Space Launch System flights use modernized and refurbished engines built for the Space Shuttle program. Subsequent flights will make use of

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On December 14, 2022, a single development RS-25E, serial number E10001, attempted a 500-second hot-fire test. The test aborted at T+209.5 due to test systems subsequently interpreting signals from a group of improperly configured accelerometers during the hot fire as exceeding acceptable vibration

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Once the remaining RS-25Ds are exhausted, they are to be replaced with a cheaper, expendable version designated the RS-25E. In 2023, Aerojet Rocketdyne reported reductions in manufacturing time and labour requirements during manufacturing of new-production RS-25 engines, such as a 15% reduction in

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engines (which was based on both the SSME and Apollo-era J-2 engine) on the Ares V core stage; this meant that the RS-25 would be retired along with the Shuttle fleet. In 2010, however, NASA was directed to halt the Constellation program, and with it development of the Ares I and Ares V, instead of

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During the course of the Space Shuttle program, a total of 46 RS-25 engines were used (with one extra RS-25D being built but never used). During the 135 missions, for a total of 405 individual engine-missions, Pratt & Whitney Rocketdyne reports a 99.95% reliability rate, with the only in-flight

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After each flight the engines would be removed from the orbiter and transferred to the Space Shuttle Main Engine Processing Facility (SSMEPF), where they would be inspected and refurbished in preparation for reuse on a subsequent flight. A total of 46 reusable RS-25 engines, each costing around US$

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The low-pressure oxygen and low-pressure fuel turbopumps were mounted 180° apart on the orbiter's aft fuselage thrust structure. The lines from the low-pressure turbopumps to the high-pressure turbopumps contain flexible bellows that enable the low-pressure turbopumps to remain stationary while the

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suppression systems; to the low-pressure oxidizer turbopump (LPOTP); to the high-pressure oxidizer pre-burner, from which it is split into the HPFTP turbine and HPOTP before being reunited in the hot gas manifold and sent on to the main combustion chamber (MCC); or directly into the main combustion

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By the time the contract was awarded, budgetary pressures meant that the shuttle's design had changed to its final orbiter, external tank, and two boosters configuration, and so the engine was only required to power the orbiter during ascent. During the year-long 'Phase B' study period, Rocketdyne

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Two independent dual-CPU computers, A and B, form the controller; giving redundancy to the system. The failure of controller system A automatically leads to a switch-over to controller system B without impeding operational capabilities; the subsequent failure of controller system B would provide a

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igniter is a small combination chamber located in the center of the injector of each pre-burner. Two dual-redundant spark igniters are activated by the engine controller and are used during the engine start sequence to initiate combustion in each pre-burner. They are turned off after approximately

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The large silver pipe across the top carries fuel from the low-pressure fuel turbopump (not visible) to the high-pressure fuel turbopump (HPFTP, silver drum at lower left). The top of the HPFTP is bolted to part of the hot gas manifold (black, with brown diagonal pipe), and above that is the fuel

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3B controllers but required no engine shut down. In addition, a 0.1-inch diameter, 1-inch long gold-plated pin, used to plug an oxidizer post orifice (an inappropriate SSME corrective action eliminated from the fleet by redesign) came loose inside an engine's main injector and impacted the engine

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alloy (called NARloy-Z) and was tested on February 12, 1971, producing a chamber pressure of 3,172 psi (21,870 kPa). The three participating companies submitted their engine development bids in April 1971, with Rocketdyne being awarded the contract on July 13, 1971—although work did not

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In addition to fuel and oxidizer systems, the launch vehicle's main propulsion system is also equipped with a helium system consisting of ten storage tanks in addition to various regulators, check valves, distribution lines, and control valves. The system is used in-flight to purge the engine and

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control valve is mounted on the combustion chamber coolant bypass duct of each engine. The engine controller regulates the amount of gaseous hydrogen allowed to bypass the nozzle coolant loop, thus controlling its temperature. The chamber coolant valve is 100% open before the engine start. During

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The speed of the HPOTP and HPFTP turbines depends on the position of the corresponding oxidizer and fuel pre-burner oxidizer valves. These valves are positioned by the engine controller, which uses them to throttle the flow of liquid oxygen to the pre-burners and, thus, control engine thrust. The

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to 7,400 psia). It passes through the oxidizer pre-burner oxidizer valve into the oxidizer pre-burner and through the fuel pre-burner oxidizer valve into the fuel pre-burner. The HPOTP measures approximately 600 by 900 mm (24 by 35 in). It is attached by flanges to the hot-gas manifold.

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Following the awarding of the contract, a preliminary design review was carried out in September 1972, followed by a critical design review in September 1976 after which the engine's design was set and construction of the first set of flight-capable engines began. A final review of all the Space

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in every way they decided to select a much more advanced design in order to "force an advancement of rocket engine technology". They called for a new design based on a high-pressure combustion chamber running around 3,000 psi (21,000 kPa), which increases the performance of the engine.

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In the Space Shuttle, the main oxidizer and fuel bleed valves were used after shutdown to dump any residual propellant, with residual liquid oxygen venting through the engine and residual liquid hydrogen venting through the liquid hydrogen fill and drain valves. After the dump was completed, the

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The HPOTP turbine and HPOTP pumps are mounted on a common shaft. Mixing of the fuel-rich hot gases in the turbine section and the liquid oxygen in the main pump can create a hazard and, to prevent this, the two sections are separated by a cavity that is continuously purged by the engine's helium

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On January 16, 2021, the RS-25 engines were fired again, during a hot-fire test as part of the Artemis program. The test was originally scheduled as an 8-minute test but was terminated at the 67th second due to intentionally conservative test parameters being breached in the hydraulic system of

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Over the course of the Space Shuttle program, the RS-25 went through a series of upgrades, including combustion chamber changes, improved welds and turbopump changes in an effort to improve the engine's performance and reliability and so reduce the amount of maintenance required after use. As a

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powered by high-pressure liquid oxygen from the high-pressure oxidizer turbopump (HPOTP). It boosts the liquid oxygen's pressure from 0.7 to 2.9 MPa (100 to 420 psi), with the flow from the LPOTP then being supplied to the HPOTP. During engine operation, the pressure boost permits the

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stainless steel tube wall coolant passages. On the Space Shuttle, a support ring welded to the forward end of the nozzle is the engine attach point to the orbiter-supplied heat shield. Thermal protection is necessary because of the exposure portions of the nozzles experience during the launch,

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crew-launch vehicle rockets, which had been planned to use the RS-25 in their first and second stages respectively. While these configurations had initially seemed worthwhile, as they would use then-current technology following the shuttle's retirement in 2010, the plan had several drawbacks:

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The low-pressure fuel turbopump (LPFTP) is an axial-flow pump driven by a two-stage turbine powered by gaseous hydrogen. It boosts the pressure of the liquid hydrogen from 30 to 276 psia (0.2 to 1.9 MPa) and supplies it to the high-pressure fuel turbopump (HPFTP). During engine operation, the

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from the heat exchanger, and, not having any membrane, it operates by continuously recirculating the charge gas. A number of baffles of various types are present inside the accumulator to control sloshing and turbulence, which is useful of itself and also to prevent the escape of gas into the

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The level of throttle was initially set to 65%, but, following review of early flight performance, this was increased to a minimum of 67% to reduce fatigue on the MPS. The throttle lever was dynamically calculated based on initial launch performance, generally being reduced to a level around

664:(the main pump and a pre-burner pump) mounted on a common shaft and driven by a two-stage, hot-gas turbine. The main pump boosts the liquid oxygen's pressure from 2.9 to 30 MPa (420 to 4,350 psi) while operating at approximately 28,120 rpm, giving a power output of 23,260 1775:, various plans for the remaining engines were proposed, ranging from them all being kept by NASA, to them all being given away (or sold for US$ 400,000–800,000 each) to various institutions such as museums and universities. This policy followed changes to the planned configurations of the 1143:

In January 1969 NASA awarded contracts to General Dynamics, Lockheed, McDonnell Douglas, and North American Rockwell to initiate the early development of the Space Shuttle. As part of these 'Phase A' studies, the involved companies selected an upgraded version of the XLR-129, developing

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In addition to the RS-25Ds, the SLS program makes use of the Main Propulsion Systems (MPS, the "plumbing" feeding the engines) from the three remaining shuttle orbiters for testing purposes (having been removed as part of the orbiters' decommissioning), with the first two launches

4955:"Today's test is the 12th (and final) test in the current series using a certification engine with dozens of improvements to make production more efficient and affordable while maintaining high performance and reliability. Another certification engine will be tested this fall" 757:

The engine's main combustion chamber (MCC) receives fuel-rich hot gas from a hot-gas manifold cooling circuit. The gaseous hydrogen and liquid oxygen enter the chamber at the injector, which mixes the propellants. The mixture is ignited by the "Augmented Spark Igniter", an

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supply during engine operation. Two seals minimize leakage into the cavity; one seal is located between the turbine section and the cavity, while the other is between the pump section and cavity. Loss of helium pressure in this cavity results in automatic engine shutdown.

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were selected to receive funding although, given P&W's already-advanced development (demonstrating a working 350,000 lbf (1,600 kN) concept engine during the year) and Aerojet General's prior experience in developing the 1,500,000 lbf (6,700 kN)

1273:. If necessary the engines could be changed on the pad. The engines, drawing propellant from the Space Shuttle external tank (ET) via the orbiter's main propulsion system (MPS), were ignited at T−6.6 seconds prior to liftoff (with each ignition staggered by 120 1252: 1981:

AR-22 engine. The AR-22 was a version of the RS-25, with parts sourced from Aerojet Rocketdyne and NASA inventories from early versions of the engine. In July 2018 Aerojet Rocketdyne successfully completed ten 100-second firings of the AR-22 in ten days.

672:). The HPOTP discharge flow splits into several paths, one of which drives the LPOTP turbine. Another path is to, and through, the main oxidizer valve and enters the main combustion chamber. Another small flow path is tapped off and sent to the oxidizer 1190:. NASA specified that, prior to the Shuttle's first flight, the engines must have undergone at least 65,000 seconds of testing, a milestone that was reached on March 23, 1980, with the engine having undergone 110,253 seconds of testing by the time of 1048: 4834:"Operators are aiming for a test duration of more than 10 minutes (630 seconds), which is longer than the 500 seconds the engines must fire to help launch the @NASA_SLS (Space Launch System) to orbit and helps provide a margin of operational safety" 1053: 1051: 1047: 3814: 1032:

provides pressure for actuating engine valves within the propellant management system and during emergency shutdowns. During entry, on the Space Shuttle, any remaining helium was used to purge the engines during reentry and for repressurization.

4883:"On June 8, @NASA conducted the 10th certification test of an RS-25 engine at @NASAStennis, continuing a critical hot fire series to facilitate the production of new engines for future SLS (Space Launch System) flights. Watch the engine ignite!" 1052: 1253: 3307:"Today's RS-25 engine test on the Fred Haise Test Stand is targeted between 1:30-3:30 p.m. CDT on Facebook Live and YouTube! We will go live 15 minutes early, so tune in to learn more about RS-25 engine testing for future Artemis missions" 1023:

rest of the engine is gimbaled for thrust vector control, and also to prevent damage to the pumps when loads were applied to them. The liquid-hydrogen line from the LPFTP to the HPFTP is insulated to prevent the formation of liquid air.

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On March 18, 2021, the four RS-25 core-stage engines were once again fired as part of the second SLS core stage hot-fire test, which lasted the full duration of 500 seconds, successfully certifying the Artemis I core stage for flight.

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is 121 in (3.1 m) long with a diameter of 10.3 inches (0.26 m) at its throat and 90.7 inches (2.30 m) at its exit. The nozzle is a bell-shaped extension bolted to the main combustion chamber, referred to as a

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On February 28, 2019, NASA conducted a 510-second test burn of a developmental RS-25 at 113 percent of its originally designed thrust for more than 430 seconds, about four times longer than any prior test at this thrust level.

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The HPFTP is a three-stage centrifugal pump driven by a two-stage hot-gas turbine. It boosts the pressure of the liquid hydrogen from 1.9 to 45 MPa (276 to 6,515 psia), and operates at approximately 35,360 rpm with a power of

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415,000 lbf (1,850 kN), as the baseline engine for their designs. This design can be found on many of the planned Shuttle versions right up to the final decision. However, since NASA was interested in pushing the

582:(LPFTP and LPOTP), and from there into high-pressure turbopumps (HPFTP and HPOTP). From these HPTPs the propellants take different routes through the engine. The oxidizer is split into four separate paths: to the oxidizer 5053:"Today, NASA conducted the 2nd hot fire in a final 12-test certification series paving the way for production of new RS-25 engines to help power the @NASA_SLS rocket on future Artemis missions to the Moon and beyond" 4240: 2264: 1050: 748:

The main oxidizer and main fuel valves control the flow of liquid oxygen and liquid hydrogen into the engine and are controlled by each engine controller. When an engine is operating, the main valves are fully open.

633:. The LPOTP, which measures approximately 450 by 450 mm (18 by 18 in), is connected to the vehicle propellant ducting and supported in a fixed position by being mounted on the launch vehicle's structure. 436:) of 452 seconds (4.43 kN-sec/kg) in vacuum, or 366 seconds (3.59 kN-sec/kg) at sea level, has a mass of approximately 3.5 tonnes (7,700 pounds), and is capable of throttling between 67% and 109% of its 1877:

in their core stages. The SLS's propellants are supplied to the engines from the rocket's core stage, which consists of a modified Space Shuttle external tank with the MPS plumbing and engines at its aft, and an

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This Shuttle control panel is set to select the abort to orbit (ATO) option, as used in the STS-51-F mission. After orbit was achieved, the mission continued normally and the orbiter returned to Earth with the

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flame at the center of the injector head. The main injector and dome assembly are welded to the hot-gas manifold, and the MCC is also bolted to the hot-gas manifold. The MCC comprises a structural shell made of

4634: 698:, and is approximately 450 by 600 mm (18 by 24 in) in size. It is connected to the vehicle propellant ducting and is supported in a fixed position by being mounted to the launch vehicle's structure. 906:, each system uses M68000s from the same manufacturer (for instance system A would have two Motorola CPUs while system B would have two CPUs manufactured by TRW). Memory for block I controllers was of the 4727: 3411: 1904:

On 1 May 2020, NASA awarded a contract extension to manufacture 18 additional RS-25 engines, with associated services, for $ 1.79 billion, bringing the total SLS contract value to almost $ 3.5 billion.

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On 29 August 2022, Artemis I was delayed by a problem with engineering sensors on RS-25D #3 (serial number E2058) erroneously reporting that it hadn't chilled down to its ideal operating temperature.

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sensors flashed dry resulting in low-level cutoff of the main engines and a slightly early main engine cut-off with a 16 ft/s (4.9 m/s) underspeed, and an 8 nautical mile lower altitude.

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Each engine is equipped with a main engine controller (MEC), an integrated computer which controls all of the engine's functions (through the use of valves) and monitors its performance. Built by

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of acceleration as it became progressively lighter due to propellant consumption. The engines were then shut down, a procedure known as main engine cutoff (MECO), at around T+8.5 minutes.

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was able to make use of their experience developing the HG-3 engine to design their SSME proposal, producing a prototype by January 1971. The engine made use of a new Rocketdyne-developed

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Following these tests, four more engines were scheduled to enter a new test cycle. A new series of tests designed to evaluate performance in SLS-use cases was initiated in 2017.

1049: 1288:. The engines would then be throttled back up until around T+8 minutes, at which point they would be gradually throttled back down to 67% to prevent the stack exceeding 3 3288: 2954: 4228: 4202: 3856: 1739:

nozzle inner surface, rupturing three hydrogen cooling lines. The resulting three breaches caused a leak resulting in a premature engine shutdown, when four external tank LO

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mission. The engines, however, did suffer from a number of pad failures (redundant set launch sequencer aborts, or RSLSs) and other issues during the course of the program:

1097:. The studies were conducted under a program to upgrade the Saturn V engines, which produced a design for a 350,000 lbf (1,600 kN) upper-stage engine known as the 4688: 4428: 4002: 3791: 1395:, the Block II upgrade included all of the Block IIA improvements plus a new high-pressure fuel turbopump. This model was ground-tested to 111% FPL in the event of a 7921: 4626: 894:(GPCs) or the SLS's avionics suite via its own engine interface unit (EIU). Using a dedicated system also simplifies the software and thus improves its reliability. 5256: 2277: 7705: 5894: 4568: 4332: 2693: 925:

The controllers were designed to be tough enough to survive the forces of launch and proved to be extremely resilient to damage. During the investigation of the

3757: 7901: 4807: 4750: 4719: 3403: 2410: 2318: 422:, on April 12, 1981. The RS-25 has undergone upgrades over its operational history to improve the engine's thrust, reliability, safety, and maintenance load. 4856: 3905: 3343: 5490: 4301: 3377: 3088: 4905: 2388: 962:

engine operation, it is 100% open for throttle settings of 100 to 109%. For throttle settings between 65 and 100%, its position ranged from 66.4 to 100%.

5002: 4657: 4525: 3228: 1355:, the Phase II engine offered a number of safety upgrades and was certified for 104% RPL & 109% full power level (FPL) in the event of a contingency. 4389: 3942: 1650:– No. 3 engine caused an RSLS shutdown at T−4 seconds due to loss of redundant control on main engine valve, stack rolled back and engine replaced. 4468: 3172: 2727: 1798:

It would be expensive, time-consuming, and weight-intensive to convert the ground-started RS-25D to an air-started version for the Ares I second stage.

856:

ascent, on-orbit and entry phases of a mission. The insulation consists of four layers of metallic batting covered with a metallic foil and screening.

5646: 4591: 3591: 3529: 2787: 7916: 7700: 5413: 5074: 3560: 2608: 5308: 5577: 5554: 4976: 2452: 4494: 3722: 3470: 3054: 4159: 4024: 5126: 2855: 462:

engines. Following each flight, the RS-25 engines were removed from the orbiter, inspected, refurbished, and then reused on another mission.

4358: 2105: 4262: 3126: 2667: 1169:, Rocketdyne was forced to put a large amount of private money into the design process to allow the company to catch up to its competitors. 7906: 4128: 3968: 2526: 4776: 3202: 736:

to the hot-gas manifold. The fuel and oxidizer enter the pre-burners and are mixed so that efficient combustion can occur. The augmented

694:

pressure boost provided by the LPFTP permits the HPFTP to operate at high speeds without cavitating. The LPFTP operates at around 16,185

6007: 440:

in one-percent increments. Components of the RS-25 operate at temperatures ranging from −253 to 3,300 °C (−400 to 6,000 °F).

6251: 5651:

Space Transportation System, Space Shuttle Main Engine, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

4102: 3700: 3254: 883: 3647: 2193: 1296:

40 million, were flown during the Space Shuttle program, with each new or overhauled engine entering the flight inventory requiring

798:

An alternative for the construction of RS-25 engines to be used in SLS missions is the use of advanced structural ceramics, such as

7695: 7690: 7685: 7309: 6523: 6103: 3280: 2961: 2354: 459: 3848: 418:

at liftoff. Although RS-25 heritage traces back to the 1960s, its concerted development began in the 1970s with the first flight,

6093: 5887: 5882: 5754: 5678: 4194: 1912: 1795:

Each engine would have to undergo a test firing prior to installation and launch, with refurbishment required following the test.

1730:– An Orbiter Project AC1 Phase A electrical wiring short occurred at T+5 seconds causing an under voltage which disqualified SSME 5030:"Today's test of RS-25 Engine 0525 on the Fred Haise Test Stand has a planned duration of 500 sec. with a max. 113% power level" 2986: 6447: 6362: 5877: 4420: 3994: 4696: 6489: 6051: 5909: 4051: 3630: 3512: 3453: 2907: 2580: 6078: 3677: 6554: 3783: 2928: 2642: 1384:

payloads, but this was not required and would have reduced engine service life). A slightly modified version first flew on

5524: 2764: 1325:

FMOF (first manned orbital flight): Certified for 100% rated power level (RPL). Used for the orbital flight test missions

6468: 5899: 5230: 2814: 1714:– No. 3 engine (2032) caused an RSLS shutdown at T−1.9 seconds when a temperature sensor in its HPOTP exceeded its 1400: 1396: 7820: 5946: 5729: 1278: 452: 4560: 2697: 6031: 4324: 3749: 2568: 1901:

fabrication time for the powerhead and a 22-month reduction in the time needed to produce a main combustion chamber.

1890: 926: 1690:– No. 3 engine caused an RSLS shutdown at T−3 seconds due to a leak in its liquid-oxygen preburner check valve. 5607: 5205: 2418: 2310: 1344:, the Phase I engine offered increased service life and was certified for 104% RPL. Replaced by Phase II after the 1157: 4293: 3328: 568: 7219: 6213: 6044: 5951: 5934: 5153: 3369: 3077: 2134: 4561:"Before shortened NASA SLS rocket engine test, officials predicted only a 50 percent chance of complete success" 4077: 3879: 2162: 7911: 5929: 5861: 5703: 2380: 1221: 6501: 5635: 1802:

Following several design changes to the Ares I and Ares V rockets, the RS-25 was to be replaced with a single

991: 493: 6340: 6208: 2534: 2200: 595: 391: 96: 7850: 4451: 3159: 2720: 451:. The engines were used for propulsion throughout the spacecraft ascent, with total thrust increased by two 7896: 6516: 6434: 6335: 6177: 6172: 4464: 4232: 3339: 3232: 1885:

For the first two Artemis missions, the engines are installed on the SLS core stage in Building 103 of the

1301: 1195: 1070: 1058: 3599: 3568: 3537: 2791: 2612: 1985:

On January 22, 2020, Boeing announced its departure from the XS-1 program, leaving no role for the AR-22.

7891: 6357: 6141: 6088: 5941: 5734: 5708: 5671: 5387: 1381: 1266: 560: 448: 5641:

Lawrence J. Thomson Collection, The University of Alabama in Huntsville Archives and Special Collections

2444: 7840: 7174: 6893: 6855: 6475: 6317: 6015: 5744: 3726: 3445: 1601: 1133: 5547:"Aerojet Rocketdyne Selected As Main Propulsion Provider for Boeing and DARPA Experimental Spaceplane" 3478: 3050: 1879: 1752: 7139: 7134: 6410: 6187: 6110: 5987: 5971: 5966: 5961: 5956: 5846: 1886: 1834: 1270: 4450:

Vetcha, Naveen; Strickland, Matthew B.; Philippart, Kenneth D.; Giel, Thomas V. Jr. (July 9, 2018).

2859: 1850: 571:

and from there flowed through the orbiter's main propulsion system (MPS) feed lines; whereas in the

7235: 6564: 6367: 6218: 6146: 6098: 6038: 5997: 5904: 5791: 5777: 5759: 5636:

Spherical panoramas of RS-25D in SSME Processing Facility prior to shipping to Stennis Space Center

3652: 1842: 1772: 1669: 1657: 1628: 1187: 1128:-type engines. At the conclusion of the study, P&W put forward a proposal for a 250,000 lb 877: 803: 799: 155: 7129: 466:

a simplified RS-25E engine called the Production Restart, which is under testing and development.

7576: 6802: 6795: 6655: 6509: 6426: 6256: 6233: 6151: 5812: 5798: 5749: 2671: 1872: 1792:

The engines would not be reusable, as they would be permanently attached to the discarded stages.

1709: 1702:– No. 2 engine caused an RSLS shut down at T−3 seconds due to a faulty hydrogen fuel sensor. 1697: 1645: 848: 368: 192: 7660: 7529: 7299: 7289: 6980: 6962: 6394: 5805: 5784: 5664: 5640: 2538: 1977:

to complete design work on the XS-1 program. The technology demonstrator was planned to use an

1866: 1725: 1685: 1674:– No. 1 engine (2023) shutdown at T+5:43 due to faulty temperature sensors, leading to an 1236: 1207: 825: 695: 677: 621: 539:

The RS-25 engine consists of pumps, valves, and other components working in concert to produce

249: 7201: 4103:"To The Moon And Back, Aerojet Wants To Power Future Cislunar Economy | Aviation Week Network" 1849:(SLS), to replace the shuttle fleet. The design for the SLS features the RS-25 as part of its 1662:– No. 2 engine caused an RSLS shutdown at T−3 seconds due to a coolant valve malfunction. 1105:

already being tested. It was the design for the HG-3 that would form the basis for the RS-25.

7845: 7795: 7715: 7675: 7670: 7665: 7539: 7314: 7264: 7202: 6650: 6454: 6441: 6352: 5769: 5724: 5687: 2260: 1807: 1776: 1262: 564: 444: 20: 7720: 4784: 1077:

were conducting a series of studies on high-pressure engines, developed from the successful

934: 891: 7815: 7810: 7805: 7800: 7790: 7224: 6536: 6461: 6378: 6347: 6223: 5056: 5033: 4958: 4935: 4886: 4837: 4229:"We have Ignition: NASA Space Launch System RS-25 Engine Fires Up for Third Test in Series" 3310: 2483: 1765: 1203: 1153: 1098: 1003: 919: 911: 899: 839: 599: 140: 6869: 6862: 3708: 3258: 898:

graceful shutdown of the engine. Within each system (A and B), the two M68000s operate in

8: 7825: 7345: 7215: 6900: 6540: 6481: 6296: 6203: 6068: 3657: 3108: 3027: 2474:

Padture, Nitin P. (August 2016). "Advanced structural ceramics in aerospace propulsion".

2204: 1846: 1830: 1820: 1803: 1407: 1345: 1182:

begin on engine development until March 31, 1972, due to a legal challenge from P&W.

1166: 1102: 1101:. As funding levels for Apollo wound down the HG-3 was cancelled as well as the upgraded 1078: 873: 572: 380: 127: 5851: 4193:

Potter, Sean; Hambleton, Kathryn; Fairley, Tiffany; Cheshier, Leah (November 16, 2022).

2487: 2347: 914:

and retains data even after power is turned off. Block II controllers used conventional

7640: 6386: 6156: 6083: 6073: 5550: 5052: 5029: 4954: 4931: 4833: 4453:

1 Overview of RS-25 Adaptation Hot-Fire Test Series for SLS, Status and Lessons Learned

3438: 3306: 2841: 2138: 1978: 1974: 1121: 907: 395: 365: 102: 6182: 3626: 3508: 3449: 2903: 2576: 2507: 2499: 1964: 1113: 544: 5414:"Stennis Space Center updates RS-25 engine program, new missile production facility" 4882: 2101: 1915:, the first time the RS-25 engine had flown since the Space Shuttle's final flight, 1156:

for 'Phase B' main engine concept studies, requiring development of a throttleable,

443:

The Space Shuttle used a cluster of three RS-25 engines mounted at the stern of the

7770: 7750: 6402: 6291: 5388:"Artemis 2 moon astronauts celebrate engine test for future lunar missions (video)" 4460: 2491: 1377: 1145: 1137: 1117: 834:. The bright spot in engine 3's nozzle is from damage that occurred during liftoff. 661: 637: 587: 426: 281: 270: 4932:"RS-25 engine testing on the Fred Haise Test Stand at NASA's Stennis Space Center" 1261:

Each Space Shuttle had three RS-25 engines, installed in the aft structure of the

864: 35: 7169: 6587: 6266: 6246: 6136: 1943:

have triggered an abort of the launch countdown during an actual launch attempt.

1411: 1125: 844: 718: 617: 552: 548: 403: 170: 4977:"Start Your Engines: NASA to Begin Critical Testing for Future Artemis Missions" 2924: 2634: 1865:) originally predicted to make use of the MPS hardware from Space Shuttles 1845:, NASA announced that it would be developing a new launch vehicle, known as the 1226: 578:

Once in the engine, the propellants flow through low-pressure fuel and oxidizer

7144: 7124: 7119: 7114: 6738: 6575: 6543: 6531: 6241: 5516: 5154:"Fire! NASA kicks off Artemis moon program's 2024 with big engine test (video)" 4495:"RS-25 Engine Fired At Highest Power Level, Four Times Longer Than Prior Tests" 4160:"NASA Targets Sept. 3 for Next Artemis I Moon Mission Launch Attempt – Artemis" 2752: 1675: 1297: 1094: 887: 673: 583: 399: 292: 5464: 5438: 5360: 5334: 5282: 5257:"NASA Marks Halfway Point for Artemis Moon Rocket Engine Certification Series" 5178: 4526:"Green Run Update: Data and Inspections Indicate Core Stage in Good Condition" 2987:"Rocketdyne plant that built world's most powerful rocket engines being razed" 2757:

Report of the Presidential Commission on the Space Shuttle Challenger Accident

2066: 2054: 2042: 2030: 2018: 983: 7885: 7149: 6933: 6849: 6775: 6594: 6532: 6418: 6372: 5698: 5100: 3928: 2818: 2503: 1678:(although the mission objectives and length were not compromised by the ATO). 1623: 1231: 820: 788: 556: 407: 376: 225: 221: 122: 41: 4627:"NASA Conducts RS-25 Engine Hot Fire at Stennis for Future Artemis Missions" 4592:"Green Run Update: Full Duration Hot Fire Successfully Completed on Mar. 18" 1592: 5643:

Files of Lawrence J. Thomson, chief engineer for the SSME from 1971 to 1986

5127:"NASA Continues Artemis Moon Rocket Engine Tests with 1st Hot Fire of 2024" 4419:

Hambleton, Kathryn; Buckingham, Valerie; Northon, Karen (August 27, 2015).

3906:"All Four Engines Are Attached to the SLS Core Stage for Artemis I Mission" 3433: 2511: 1109: 737: 479: 2586: 2573:

History of Liquid Rocket Engine Development in the United States 1955–1980

1277:), which allowed their performance to be checked prior to ignition of the 7239: 7206: 3969:"All Engines Added to NASA's Artemis II Moon Rocket Core Stage – Artemis" 2166: 1894: 1274: 640:

suppression system accumulator. For use, it is pre-and post-charged with

7865:* Different versions of the engine use different propellant combinations 7655: 5656: 5650: 1380:(original plans called for the engine to be certified to 106% for heavy 1202:(MPTA). The first set of engines (2005, 2006 and 2007) was delivered to 7294: 5653:", 20 photos, 2 measured drawings, 8 photo caption pages 5206:"NASA fires up powerful Artemis moon rocket engine in key test (video)" 4808:"NASA Tests Critical In-Flight Capability During RS-25 Engine Hot Fire" 4720:"NASA Continues Test Series for Redesigned Artemis Moon Rocket Engines" 3943:"Space Launch System Engines: Launching Artemis Astronauts to the Moon" 3784:"SSME family prepare for SLS core stage role following Shuttle success" 3023: 2575:. AAS History Series. American Astronautical Society. pp. 69–122. 1862: 1074: 1007: 886:

computers, later upgraded to a system composed of two doubly redundant

703: 665: 630: 387: 80: 5491:"NASA Achieves Milestone for Engines to Power Future Artemis Missions" 4689:"NASA TV VIDEOFILE RUNDOWN – for Thursday February 23, 2023 – Evening" 4129:"NASA Commits to Future Artemis Missions with More SLS Rocket Engines" 1312: 1112:

funded a study into advanced rocket propulsion systems for use during

521: 410:

propellants, with each engine producing 1,859 kN (418,000 lb

7630: 7625: 7274: 6261: 3849:"Engineers begin removing orbiter MPS components for donation to SLS" 3370:"RS-25 hot fire pushes SLS engine to record 113 percent thrust level" 2495: 2142: 1994: 1858: 1415: 1178: 880: 780: 579: 40:

RS-25 test firing. The bright area at the bottom of the picture is a

4751:"NASA Conducts Long Duration Hot Fire of RS-25 Certification Engine" 4263:"RS-25 Engine Testing Blazes Forward for NASA's Space Launch System" 3750:"SLS trades lean towards opening with four RS-25s on the core stage" 3678:"Return to SSME – Ares V undergoes evaluation into potential switch" 3201:. American Institute of Aeronautics and Astronautics. Archived from 3127:"Constellation transition – phased retirement plan for the SSME set" 1321:

result, several versions of the RS-25 were used during the program:

954:

valves closed and remained closed for the remainder of the mission.

7735: 7730: 7650: 7635: 7620: 7324: 7028: 6131: 5856: 5838: 5830: 5003:"NASA Conducts 1st Hot Fire of New RS-25 Certification Test Series" 2856:"MSFC Propulsion Center of Excellence is Built on Solid Foundation" 1665: 1653: 1641: 1634: 1341: 1199: 1090: 1016: 938: 903: 707: 669: 260: 4969: 3995:"PRCB managers recommend Atlantis and Endeavour become SLS donors" 1911:

On 16 November 2022, Artemis I launched from Kennedy Space Center

1825: 507: 7830: 7385: 7380: 7375: 7370: 7365: 7360: 7355: 7350: 7070: 7033: 7023: 7018: 6992: 6881: 6768: 6713: 6707: 6279: 6115: 5060: 5037: 4962: 4939: 4890: 4841: 3927:

This article incorporates text from this source, which is in the

3440:

Riding Rockets: The Outrageous Tales of a Space Shuttle Astronaut

3404:"NASA Continues Key Test Series with Moon Rocket Engine Hot Fire" 3314: 3199:"Space Shuttle Main Engine (SSME) Options for the Future Shuttle" 1916: 1761: 1757: 1715: 1392: 1289: 1242: 1161: 958: 852: 768: 625: 4857:"NASA Enters Stretch in Critical Moon Rocket Engine Test Series" 4658:"NASA Conducts First 2023 Test of Redesigned Moon Rocket Engine" 3880:"Artemis 1's RS-25 Engines Have Gone to Space Many Times Before" 1140:

to provide increased efficiency over a wide range of altitudes.

941:, data from these units was retrieved for forensic examination. 7785: 7519: 7514: 7483: 7452: 7447: 7442: 7437: 7432: 7422: 7411: 7405: 7400: 7395: 7390: 7334: 7284: 7159: 7103: 7096: 7080: 7064: 7058: 7053: 7048: 7043: 7038: 6973: 6967: 6957: 6833: 6826: 6665: 6616: 6284: 6274: 5075:"NASA Tests In-Flight Capability of Artemis Moon Rocket Engine" 1784: 1780: 1721: 1705: 1693: 1681: 1385: 1373: 1366: 1359: 1352: 1174: 1011: 1000: 831: 776: 772: 733: 540: 415: 5309:"NASA to Continue Testing for New Artemis Moon Rocket Engines" 5223: 4906:"NASA Nears Completion of Key RS-25 Certification Test Series" 4449: 4195:"Liftoff! NASA's Artemis I Mega Rocket Launches Orion to Moon" 4192: 629:

high-pressure oxidizer pump to operate at high speeds without

586:, which then splits into the oxidizer tank pressurization and 7835: 7775: 7645: 7604: 7599: 7594: 7589: 7550: 7544: 7488: 7477: 7467: 7417: 7269: 7259: 7211: 7179: 7164: 7154: 7013: 7008: 7003: 6951: 6945: 6819: 6813: 6808: 6788: 6753: 6725: 6702: 6670: 6634: 6627: 6621: 6611: 6606: 6301: 5520: 3723:"NASA Announces Design For New Deep Space Exploration System" 2925:"A bat outta Hell: the ISINGLASS Mach 22 follow-on to OXCART" 1970: 1337: 1330: 1326: 1282: 1191: 1086: 783: 419: 69: 5335:"SLS RS-25 Engine Test, 29 February 2024 (615 seconds test)" 7472: 7462: 7254: 7090: 6929: 6844: 6743: 6732: 6691: 6685: 6680: 6645: 5608:"Boeing drops out of DARPA Experimental Spaceplane program" 4723: 4661: 4630: 4599: 4533: 4498: 4459:. AIAA 2018 Joint Propulsion Conference. Cincinnati, Ohio: 4424: 4421:"NASA Concludes Series of Engine Tests for Next-Gen Rocket" 4393: 4362: 4328: 4297: 4266: 4236: 4198: 4167: 4132: 3595: 3564: 3533: 3474: 3407: 3284: 3168: 3084: 2760: 2448: 2384: 2311:"SLS finally announced by NASA – Forward path taking shape" 2273: 1082: 1066: 915: 792: 723:

pre-burner (also black, with brown pipe entering at right).

456: 372: 5231:"Halfway there: NASA completes 6 of 12 RS-25 engine tests" 4418: 4390:"Countdown to Deep Space Continues with Latest RS-25 Test" 4052:"Artemis III Core Stage Engine Section Arrives at Kennedy" 3897: 2263:(December 15, 2008). "2.16 Main Propulsion System (MPS)". 7765: 7760: 7755: 7745: 4995: 1369:, the Block IA engine offered main injector improvements. 165: 5361:"SLS RS-25 Engine Test, 6 March 2024 (600 seconds test)" 4078:"NASA and Boeing change SLS core stage assembly process" 3300: 3298: 814: 657:

low-pressure oxidizer duct to be ingested in the HPOTP.

3505:

Space Shuttle Challenger: Ten Journeys into the Unknown

1833:'s core stage with four RS-25 engines attached, at the 1065:

The history of the RS-25 traces back to the 1960s when

594:

Meanwhile, fuel flows through the main fuel valve into

3934: 2417:. Copper Development Association. 1992. Archived from 910:

type, which functions in a manner similar to magnetic

5379: 5353: 3295: 2259: 4656:

Dean, LaToya; Thompson, C. Lacy (February 8, 2023).

4625:

Thompson, C. Lacy; Dean, LaToya (January 12, 2023).

3960: 2916: 1806:

engine for the Ares I second stage and six modified

6925: 5517:"DARPA Picks Design for Next-Generation Spaceplane" 5457: 5431: 5327: 5275: 5171: 2955:"Space Shuttle Main Engine: 30 Years of Innovation" 2055:

RS-25 engine controller system test on 27 July 2017

1010:which is bolted to the launch vehicle by its upper 5197: 5145: 5093: 3676:Harris, David; Bergin, Chris (December 26, 2008). 3648:"Recession Special: NASA Cuts Space Shuttle Price" 3437: 3321: 2719:Mattox, Russell M.; White, J. B. (November 1981). 1124:(P&W) to research more efficient conventional 616:The low-pressure oxidizer turbopump (LPOTP) is an 386:Designed and manufactured in the United States by 5569: 4359:"Pedal to the Metal – RS-25 Engine Revs Up Again" 4325:"Longest SLS Engine Test Yet Heats Up Summer Sky" 4025:"SLS Rockets for Artemis 3 and 4 Being Assembled" 3507:. Warwickshire, United Kingdom: Springer-Praxis. 3220: 3022: 1616:was lost on re-entry, from a heat shield failure. 7922:Rocket engines using the staged combustion cycle 7883: 5483: 5301: 5249: 5119: 5067: 4443: 4352: 4350: 4222: 4220: 3940: 3777: 3775: 3397: 3395: 3114:. Pratt & Whitney Rocketdyne. November 2010. 2635:"Computers in the Space Shuttle Avionics System" 2569:"Space Shuttle Main Engine: The First Ten Years" 1811:focusing on building a new heavy-lift launcher. 1316:Flight history of the Space Shuttle Main Engines 1152:Development began in 1970, when NASA released a 346:Data is for RS-25D at 109% of rated power level. 5509: 4583: 4517: 4151: 3941:Mohon, Lee; O'Brien, Kevin (October 27, 2022). 3103: 3101: 2902:. Owners' Workshop Manuals. Haynes Publishing. 2524: 1399:, and certified for 109% FPL for use during an 1241:'s three RS-25D main engines at liftoff during 6094:Shuttle Avionics Integration Laboratory (SAIL) 4294:"Steamy Summer Begins for SLS with RS-25 Test" 3623:Space Shuttle Columbia: Her Missions and Crews 2438: 2436: 1269:prior to the orbiter being transferred to the 7902:Historic American Engineering Record in Texas 6517: 5672: 5578:"AR-22 engine fired 10 times in as many days" 4897: 4848: 4799: 4768: 4742: 4680: 4552: 4486: 4381: 4347: 4316: 4285: 4217: 4120: 4043: 3772: 3498: 3496: 3392: 3329:"Space Launch System RS-25 Core Stage Engine" 2639:Computers in Spaceflight: The NASA Experience 2518: 2342: 2340: 2338: 2336: 2106:National Aeronautics and Space Administration 2031:Time-lapse video of STS-135 SSME installation 4711: 4655: 4649: 4624: 4618: 4069: 3675: 3639: 3361: 3098: 3042: 950:supply system as a backup actuation system. 5405: 5050: 5027: 4952: 4929: 4831: 4412: 4255: 4186: 3304: 3078:"Shuttle-Derived Heavy Lift Launch Vehicle" 2979: 2817:. Encyclopedia Astronautica. Archived from 2718: 2433: 2188: 2186: 2184: 2165:. Encyclopedia Astronautica. Archived from 437: 19:"SSME" redirects here. For other uses, see 6524: 6510: 5679: 5665: 5549:(Press release). Los Angeles, California: 4226: 3842: 3840: 3806: 3671: 3669: 3667: 3583: 3552: 3521: 3493: 3273: 2562: 2560: 2558: 2556: 2554: 2552: 2550: 2548: 2411:"NASA Relies on Copper for Shuttle Engine" 2372: 2333: 847:. The RS-25 nozzle has an unusually large 752: 6252:Shuttle-Derived Heavy Lift Launch Vehicle 5686: 5283:"SLS RS-25 Engine Test, 23 February 2024" 4686: 4559:Davenport, Christian (January 19, 2021). 4558: 3741: 3154: 3152: 3069: 2948: 2946: 2893: 2891: 2889: 2887: 2885: 2883: 2881: 2879: 2877: 2848: 2662: 2660: 2381:"Inside the LEO Doghouse: Light My Fire!" 2129: 2127: 2125: 2123: 2121: 2119: 2117: 2115: 1437: 1422: 830:'s three RS-25s following the landing of 7917:Rocket engines using hydrogen propellant 5179:"SLS RS-25 Engine Test, 23 January 2024" 5101:"SLS RS-25 Engine Test, 17 January 2024" 4880: 4589: 4523: 4387: 4356: 4227:Mohon, Lee; Henry, Kim (June 11, 2015). 3903: 3589: 3558: 3527: 3468: 3462: 3342:. January 29, 2020. FS-2020-10-42-MSFC. 3281:"MSFC and Exploration: Our Path Forward" 3257:. NASA. November 6, 2002. Archived from 2785: 2445:"Space Shuttle Main Engine Enhancements" 2304: 2302: 2300: 2298: 2181: 2156: 2154: 2152: 1824: 1751: 1600: 1591: 1311: 1247: 1225: 1215: 1044: 990: 868:A Block II RS-25D main engine controller 863: 813: 717: 4524:Harbaugh, Jennifer (January 19, 2021). 3904:Harbaugh, Jennifer (November 9, 2019). 3877: 3837: 3812: 3664: 3432: 3226: 3196: 3075: 3018: 3016: 3014: 3012: 3010: 3008: 2931:from the original on September 26, 2022 2694:"Space Shuttle Main Engine Controllers" 2668:"The future of the shuttle's computers" 2645:from the original on September 24, 2022 2545: 2473: 2403: 2348:"Space Shuttle Main Engine Orientation" 2255: 2253: 2251: 2249: 2247: 2245: 1116:, with Rocketdyne asked to investigate 660:The HPOTP consists of two single-stage 636:Then, mounted before the HPOTP, is the 7884: 6448:Rendezvous: A Space Shuttle Simulation 5527:from the original on December 21, 2022 5465:"SLS RS-25 Engine Test, 27 March 2024" 5439:"SLS RS-25 Engine Test, 22 March 2024" 5385: 5204:Howell, Elizabeth (January 24, 2024). 5203: 5152:Howell, Elizabeth (January 20, 2024). 5151: 4774: 4687:Valentine, Andre (February 23, 2023). 4505:from the original on December 11, 2022 4431:from the original on December 23, 2022 4388:Harbaugh, Jennifer (August 14, 2015). 4369:from the original on December 11, 2022 4335:from the original on December 11, 2022 4243:from the original on December 11, 2022 4126: 4049: 3992: 3986: 3912:from the original on November 12, 2019 3846: 3794:from the original on November 28, 2022 3781: 3747: 3692: 3349:from the original on February 11, 2023 3149: 3124: 2943: 2874: 2721:"Space Shuttle Main Engine Controller" 2686: 2657: 2627: 2391:from the original on December 11, 2022 2378: 2308: 2243: 2241: 2239: 2237: 2235: 2233: 2231: 2229: 2227: 2225: 2112: 1814: 732:The oxidizer and fuel pre-burners are 620:which operates at approximately 5,150 193:Fuel-rich dual-shaft staged combustion 114: 6505: 6490:When We Left Earth: The NASA Missions 5660: 5588:from the original on February 2, 2023 5575: 5411: 4637:from the original on January 18, 2023 4590:Harbaugh, Jennifer (March 18, 2021). 4304:from the original on December 6, 2022 4273:from the original on December 7, 2022 4157: 4139:from the original on January 29, 2023 4075: 4005:from the original on January 27, 2023 3966: 3878:Dvorsky, George (September 2, 2022). 3859:from the original on February 1, 2023 3715: 3620: 3502: 3367: 3190: 3137:from the original on February 5, 2023 2897: 2712: 2696:. NASA. April 4, 2004. Archived from 2670:. NASA. July 15, 2005. Archived from 2566: 2295: 2149: 2067:RS-25 test for SLS on 17 October 2023 297:514.49 kg/s (1,134.26 lb/s) 6555:Comparison of orbital rocket engines 5647:Historic American Engineering Record 5386:Howell, Elizabeth (March 15, 2024). 4903: 4854: 4805: 4748: 4717: 4492: 4400:from the original on October 1, 2022 4357:Harbaugh, Jennifer (July 17, 2015). 4322: 4291: 3993:Bergin, Chris (September 20, 2011). 3698: 3645: 3401: 3291:from the original on March 31, 2022. 3247: 3197:Jue, Fred; Kuck, Fritz (July 2002). 3118: 3048: 3026:; & various (January 17, 2012). 3005: 2806: 2360:from the original on August 31, 2022 2309:Bergin, Chris (September 14, 2011). 1841:On 14 September 2011, following the 1837:in Building 103, on 7 November 2019. 876:, each MEC originally comprised two 7907:Rocket engines of the United States 6469:Space Shuttle: A Journey into Space 4668:from the original on March 20, 2023 4571:from the original on March 29, 2023 4540:from the original on April 19, 2023 4174:from the original on March 29, 2023 4050:Cawley, James (December 19, 2022). 3760:from the original on March 27, 2023 3701:"Obama signs Nasa up to new future" 3699:Amos, Jonathan (October 11, 2010). 3368:Sloss, Philip (February 21, 2018). 3227:Crierie, Ryan (November 13, 2011). 3094:from the original on April 4, 2023. 3049:Ryba, Jeanne (September 17, 2009). 2922: 2839: 2779: 2525:O'Leary, R.A.; Beck, J. E. (1992). 2455:from the original on April 19, 2023 2442: 2321:from the original on March 22, 2023 2283:from the original on April 11, 2023 2222: 1372:Block IIA (RS-25C): First flown on 1279:Space Shuttle Solid Rocket Boosters 1257:SSME startup and shutdown sequences 13: 5051:@NASAStennis (November 15, 2023). 5028:@NASAStennis (November 15, 2023). 4606:from the original on April 4, 2023 4493:Dean, LaToya (February 28, 2019). 4465:/NASA Marshall Space Flight Center 3847:Bergin, Chris (January 22, 2012). 3782:Bergin, Chris (January 13, 2012). 3380:from the original on April 4, 2023 3161:Report of the SSME Assessment Team 3125:Bergin, Chris (December 3, 2007). 3057:from the original on March 8, 2023 2733:from the original on June 25, 2021 2104:from websites or documents of the 1771:During the period preceding final 1391:Block II (RS-25D): First flown on 1365:Block IA (RS-25B): First flown on 1351:Phase II (RS-25A): First flown on 611: 14: 7933: 5629: 4730:from the original on May 24, 2023 4474:from the original on May 26, 2022 4158:Kraft, Rachel (August 30, 2022). 3967:Mohon, Lee (September 25, 2023). 3815:"NASA Will Retain Block II SSMEs" 3748:Bergin, Chris (October 4, 2011). 3646:Dunn, Marcia (January 15, 2010). 3414:from the original on May 24, 2023 3178:from the original on May 25, 2023 2786:Dumoulin, Jim (August 31, 2000). 2767:from the original on May 10, 2023 2379:Greene, Bill (January 24, 2014). 2043:RS-25 test for SLS on 28 May 2015 1973:announced that they had selected 1891:Space Station Processing Facility 1358:Block I (RS-25B): First flown on 16:Space Shuttle and SLS main engine 7566: 5600: 5539: 4777:"This Week @NASA, April 7, 2023" 4205:from the original on May 9, 2023 4076:Foust, Jeff (December 7, 2022). 3922: 3813:Carreau, Mark (March 29, 2011). 2991:Canoga Park Neighborhood Council 2812: 2611:. March 16, 2009. Archived from 2353:. Boeing/Rocketdyne. June 1998. 2160: 2100: This article incorporates 2095: 2061: 2049: 2037: 2025: 2013: 1889:; they will be installed in the 1747: 1479: 1026: 999:Each engine is installed with a 978: 520: 506: 492: 478: 236:1,860 kN (418,000 lbf) 34: 6214:Spartan Packet Radio Experiment 5044: 5021: 4946: 4923: 4874: 4825: 4806:Dean, LaToya (April 26, 2023). 4749:Dean, LaToya (March 21, 2023). 4095: 4017: 3871: 3614: 3590:Dumoulin, Jim (June 29, 2001). 3559:Dumoulin, Jim (June 29, 2001). 3528:Dumoulin, Jim (June 29, 2001). 3469:Dumoulin, Jim (June 29, 2001). 3426: 3076:Shannon, John (June 17, 2009). 2952: 2833: 2745: 2601: 2467: 2276:. pp. 577–618. USA007587. 2076: 1922: 1843:retirement of the Space Shuttle 1605:Recovered power-head of one of 1406:RS-25E: It will be used on the 265:2,994 psi (20.64 MPa) 6483:Orbiter Space Flight Simulator 5862:Multi-Purpose Logistics Module 5576:Rhian, Jason (July 12, 2018). 5553:. May 24, 2017. Archived from 5412:Noble, Noah (March 20, 2024). 4953:@NASAStennis (June 22, 2023). 4930:@NASAStennis (June 21, 2023). 4904:Dean, LaToya (June 15, 2023). 4775:Daines, Gary (April 7, 2023). 4718:Dean, LaToya (March 8, 2023). 4461:Jacobs Space Exploration Group 4323:Dean, LaToya (June 26, 2015). 3621:Evans, Ben (August 30, 2005). 3305:@NASAStennis (June 22, 2023). 3229:"Reference Spacecraft Engines" 2923:Day, Dwayne (April 12, 2010). 2842:"F-1A Task Assignment Program" 2535:Pratt & Whitney Rocketdyne 2266:Shuttle Crew Operations Manual 2201:Pratt & Whitney Rocketdyne 2019:STS-49 Flight Readiness Firing 1829:Aft view of the bottom of the 1621:SSME failure occurring during 1573:2,362 kN (531,000 lb 1566:1,887 kN (424,000 lb 1551:2,320 kN (521,000 lb 1534:2,280 kN (510,000 lb 1527:1,860 kN (420,000 lb 1512:2,170 kN (490,000 lb 1505:1,750 kN (390,000 lb 1490:2,090 kN (470,000 lb 1483:1,670 kN (380,000 lb 1468:1,406 kN (316,100 lb 1333:(engines 2005, 2006 and 2007). 1222:List of Space Shuttle missions 1206:in 1979 and installed on 1040: 944: 688: 392:Pratt & Whitney Rocketdyne 276:452.3 s (4.436 km/s) 97:Pratt & Whitney Rocketdyne 1: 7351:RD-0202 to 0206, 0208 to 0213 6438:(2020 documentary miniseries) 6209:Inflatable Antenna Experiment 4855:Dean, LaToya (June 1, 2023). 4292:Dean, LaToya (May 29, 2015). 3402:Dean, LaToya (May 23, 2023). 2844:– via Internet Archive. 2571:. In Stephen E. Doyle (ed.). 2567:Biggs, Robert E. (May 1992). 2090: 1300:on one of the test stands at 859: 727: 606: 469: 326:3,177 kg (7,004 lb) 6435:Challenger: The Final Flight 6336:Space Shuttle design process 6178:Shuttle Ejection Escape Suit 6173:Extravehicular Mobility Unit 5341:. SciNews. February 29, 2024 5289:. SciNews. February 23, 2024 4832:@NASAStennis (May 9, 2023). 4233:Marshall Space Flight Center 4127:Potter, Sean (May 1, 2020). 3340:Marshall Space Flight Center 2858:. NASA. 1995. Archived from 1756:The six RS-25Ds used during 1587: 1200:Main Propulsion Test Article 1136:, which used a two-position 1071:Marshall Space Flight Center 937:. After they were dried and 713: 7: 6358:International Space Station 6142:Journalist in Space Project 6089:Orbiter Processing Facility 5649:(HAER) No. TX-116-I, " 5185:. SciNews. January 23, 2024 4881:@NASA_SLS (June 11, 2023). 4269:. January 9, 2015. 15-007. 2898:Baker, David (April 2011). 2753:"The Cause of the Accident" 2194:"Space Shuttle Main Engine" 1988: 1382:International Space Station 1336:Phase I: Used for missions 1307: 1267:Orbiter Processing Facility 569:umbilical disconnect valves 559:) from the Space Shuttle's 499:Simplified diagram of RS-25 447:, with fuel drawn from the 287:366 s (3.59 km/s) 10: 7938: 6476:Space Shuttle Mission 2007 6016:Approach and Landing Tests 5745:Orbital Maneuvering System 2443:Roy, Steve (August 2000). 1962: 1893:at Kennedy beginning with 1818: 1499:Nominal power level (NPL) 1457:Minimum power level (MPL) 1219: 1035: 460:orbital maneuvering system 18: 7861: 7575: 7564: 7504: 7194: 6916: 6764: 6583: 6574: 6563: 6550: 6411:Columbia: The Tragic Loss 6328: 6310: 6232: 6196: 6188:Advanced Crew Escape Suit 6165: 6124: 6111:Shuttle Training Aircraft 6061: 6024: 5980: 5972:Shuttle Training Aircraft 5967:Shuttle Mission Simulator 5962:Rendezvous pitch maneuver 5920: 5870: 5852:Remote Controlled Orbiter 5847:Extended Duration Orbiter 5823: 5768: 5755:Thermal protection system 5717: 5694: 3028:"An SSME-related request" 2060: 2048: 2036: 2024: 2012: 2007: 1887:Michoud Assembly Facility 1835:Michoud Assembly Facility 1783:cargo-launch vehicle and 1560:Production Restart Abort 1443: 1435: 1433: 1271:Vehicle Assembly Building 977: 972: 965: 892:general purpose computers 809: 804:ceramic-matrix composites 644:and charged with gaseous 591:chamber (MCC) injectors. 358:Space Shuttle Main Engine 342: 335: 330: 322: 314: 306: 301: 291: 280: 269: 258: 248: 240: 232: 216: 211: 203: 198: 188: 180: 161: 154: 146: 136: 112: 86: 76: 56: 48: 33: 6219:Shuttle pallet satellite 6147:Teacher in Space Project 6099:Shuttle Carrier Aircraft 6079:Mobile Launcher Platform 5905:Shuttle Landing Facility 5760:Booster separation motor 3255:"The Roar of Innovation" 3109:"SSME Flight Experience" 2960:. Boeing. Archived from 2840:NON (January 15, 1970). 2788:"Main Propulsion System" 2000: 1773:Space Shuttle retirement 1477:Rated power level (RPL) 1414:missions beginning with 1188:Canoga Park, Los Angeles 1108:Meanwhile, in 1967, the 800:thermal barrier coatings 310:4.3 m (168 in) 60:April 12, 1981 7396:RD-250 to 252, 261, 262 6427:The Challenger Disaster 5750:Reaction control system 2641:. NASA. July 15, 2005. 2451:. FS-2000-07-159-MSFC. 1958: 1543:SLS Production Restart 1521:Full power level (FPL) 1194:both on test stands at 753:Main combustion chamber 402:(very low temperature) 369:cryogenic rocket engine 318:2.4 m (96 in) 5895:Space Launch Complex 6 3725:. NASA. Archived from 2790:. NASA. Archived from 2415:Discover Copper Online 2203:. 2005. Archived from 2102:public domain material 1882:structure at the top. 1838: 1768: 1617: 1598: 1423:Engine throttle/output 1317: 1258: 1245: 1062: 996: 869: 835: 771:which is lined with a 724: 624:driven by a six-stage 455:and the orbiter's two 425:The engine produces a 250:Thrust-to-weight ratio 93:Rocketdyne (1981–2005) 7912:Space Shuttle program 7872:are under development 7260:YF-20, 21, 22, 24, 25 7039:RD-107, 108, 117, 118 6455:Space Shuttle Project 6442:Space Shuttle America 6353:Payload Assist Module 6010:(engine test article) 5688:Space Shuttle program 3729:on September 21, 2011 3711:on November 14, 2022. 3680:. NASASpaceflight.com 3030:. NASASpaceflight.com 2421:on September 20, 2013 2261:United Space Alliance 1828: 1777:Constellation program 1755: 1604: 1595: 1315: 1263:Space Shuttle orbiter 1256: 1229: 1216:Space Shuttle program 1198:and installed on the 1056: 1008:ball and socket joint 994: 867: 817: 721: 533:RS-25 propellant flow 453:solid rocket boosters 21:SSME (disambiguation) 6348:Inertial Upper Stage 6224:Wake Shield Facility 6204:Freestar experiments 5730:Solid Rocket Booster 3660:on January 18, 2010. 3481:on December 17, 2021 3436:(February 3, 2007). 3167:(Technical report). 2927:. The Space Review. 2862:on November 15, 2005 2821:on November 15, 2011 2794:on November 23, 2021 2589:on December 25, 2011 2272:(Technical report). 2169:on December 28, 2016 1766:Kennedy Space Center 1302:Stennis Space Center 1298:flight qualification 1204:Kennedy Space Center 1196:Stennis Space Center 1154:request for proposal 1089:upper stages of the 1059:Stennis Space Center 596:regenerative cooling 356:, also known as the 7897:Space Launch System 7361:RD-0216, 0217, 0235 7024:RD-0107, 0108, 0110 6297:Space Launch System 6069:Crawler-transporter 5910:Abort landing sites 5582:SpaceFlight Insider 5315:. February 22, 2024 5081:. November 29, 2023 3999:NASASpaceflight.com 3853:NASASpaceflight.com 3788:NASASpaceflight.com 3754:NASASpaceflight.com 3625:. Springer Praxis. 3540:on January 20, 2022 3503:Evans, Ben (2007). 3374:NASASpaceFlight.com 3261:on November 8, 2002 3131:NASASpaceflight.com 2700:on January 24, 2001 2488:2016NatMa..15..804P 2315:NASASpaceflight.com 2210:on February 8, 2012 1919:, on 21 July 2011. 1847:Space Launch System 1831:Space Launch System 1821:Space Launch System 1815:Space Launch System 1408:Space Launch System 1346:Challenger Disaster 1122:Pratt & Whitney 874:Honeywell Aerospace 573:Space Launch System 398:), the RS-25 burns 381:Space Launch System 379:and is used on the 128:Space Launch System 30: 7892:Rocketdyne engines 6422:(2010 documentary) 6414:(2004 documentary) 6406:(1994 documentary) 6390:(1985 documentary) 6387:The Dream Is Alive 6382:(1982 documentary) 6084:NASA recovery ship 6074:Mate-Demate Device 5614:. January 22, 2020 5551:Aerojet Rocketdyne 5263:. January 29, 2024 5237:. January 29, 2024 5133:. January 18, 2024 5009:. October 18, 2023 4983:. October 13, 2023 3602:on January 3, 2022 3287:. September 2005. 3235:on January 5, 2020 3208:on October 9, 2007 2900:NASA Space Shuttle 2674:on October 4, 2022 2615:on October 2, 2011 2541:on March 16, 2008. 2139:Aerojet Rocketdyne 1979:Aerojet Rocketdyne 1975:The Boeing Company 1913:Launch Complex 39B 1839: 1769: 1618: 1599: 1318: 1259: 1246: 1132:engine called the 1093:rocket during the 1063: 997: 870: 836: 725: 396:Aerojet Rocketdyne 156:Liquid-fuel engine 103:Aerojet Rocketdyne 28: 7879: 7878: 7821:Space Shuttle SRB 7562: 7561: 7500: 7499: 7190: 7189: 6912: 6911: 6499: 6498: 6183:Launch Entry Suit 6011: 6003: 5993: 5938: 5878:Launch Complex 39 5843: 5835: 5519:(Press release). 4722:(Press release). 4660:(Press release). 4629:(Press release). 4423:(Press release). 4265:(Press release). 4197:(Press release). 4131:(Press release). 3825:on April 20, 2011 3632:978-0-387-21517-4 3514:978-0-387-46355-1 3455:978-0-7432-7682-5 2909:978-1-84425-866-6 2582:978-0-87703-350-9 2072: 2071: 1969:On May 24, 2017, 1965:XS-1 (spacecraft) 1581: 1580: 1397:contingency abort 1304:prior to flight. 1254: 1158:staged combustion 1114:Project Isinglass 1057:RS-25 testing at 1054: 995:RS-25 gimbal test 989: 988: 984:RS-25 gimbal test 662:centrifugal pumps 438:rated power level 371:that was used on 350: 349: 233:Thrust, sea-level 49:Country of origin 7929: 7570: 7569: 7406:RD-263, 268, 273 7337:along other LREs 7199: 7198: 7059:RD-191, 151, 181 6923: 6922: 6581: 6580: 6572: 6571: 6526: 6519: 6512: 6503: 6502: 6403:Destiny in Space 6009: 6001: 5991: 5947:Mission timeline 5932: 5841: 5833: 5704:List of missions 5681: 5674: 5667: 5658: 5657: 5624: 5623: 5621: 5619: 5604: 5598: 5597: 5595: 5593: 5573: 5567: 5566: 5564: 5562: 5543: 5537: 5536: 5534: 5532: 5523:. May 24, 2017. 5513: 5507: 5506: 5504: 5502: 5487: 5481: 5480: 5478: 5476: 5471:. March 27, 2024 5461: 5455: 5454: 5452: 5450: 5445:. March 22, 2024 5435: 5429: 5428: 5426: 5424: 5409: 5403: 5402: 5400: 5398: 5383: 5377: 5376: 5374: 5372: 5357: 5351: 5350: 5348: 5346: 5331: 5325: 5324: 5322: 5320: 5305: 5299: 5298: 5296: 5294: 5279: 5273: 5272: 5270: 5268: 5253: 5247: 5246: 5244: 5242: 5227: 5221: 5220: 5218: 5216: 5201: 5195: 5194: 5192: 5190: 5175: 5169: 5168: 5166: 5164: 5149: 5143: 5142: 5140: 5138: 5123: 5117: 5116: 5114: 5112: 5097: 5091: 5090: 5088: 5086: 5071: 5065: 5064: 5048: 5042: 5041: 5025: 5019: 5018: 5016: 5014: 4999: 4993: 4992: 4990: 4988: 4973: 4967: 4966: 4950: 4944: 4943: 4927: 4921: 4920: 4918: 4916: 4901: 4895: 4894: 4878: 4872: 4871: 4869: 4867: 4852: 4846: 4845: 4829: 4823: 4822: 4820: 4818: 4803: 4797: 4796: 4794: 4792: 4787:on June 20, 2023 4783:. 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August 2, 2022 4021: 4015: 4014: 4012: 4010: 3990: 3984: 3983: 3981: 3979: 3964: 3958: 3957: 3955: 3953: 3938: 3932: 3926: 3925: 3921: 3919: 3917: 3901: 3895: 3894: 3892: 3890: 3875: 3869: 3868: 3866: 3864: 3844: 3835: 3834: 3832: 3830: 3821:. Archived from 3810: 3804: 3803: 3801: 3799: 3779: 3770: 3769: 3767: 3765: 3745: 3739: 3738: 3736: 3734: 3719: 3713: 3712: 3707:. Archived from 3696: 3690: 3689: 3687: 3685: 3673: 3662: 3661: 3656:. Archived from 3643: 3637: 3636: 3618: 3612: 3611: 3609: 3607: 3598:. Archived from 3587: 3581: 3580: 3578: 3576: 3571:on April 2, 2022 3567:. Archived from 3556: 3550: 3549: 3547: 3545: 3536:. Archived from 3525: 3519: 3518: 3500: 3491: 3490: 3488: 3486: 3477:. Archived from 3466: 3460: 3459: 3443: 3430: 3424: 3423: 3421: 3419: 3399: 3390: 3389: 3387: 3385: 3365: 3359: 3358: 3356: 3354: 3348: 3333: 3325: 3319: 3318: 3302: 3293: 3292: 3277: 3271: 3270: 3268: 3266: 3251: 3245: 3244: 3242: 3240: 3231:. Archived from 3224: 3218: 3217: 3215: 3213: 3207: 3194: 3188: 3187: 3185: 3183: 3177: 3171:. January 1993. 3166: 3156: 3147: 3146: 3144: 3142: 3122: 3116: 3115: 3113: 3105: 3096: 3095: 3093: 3082: 3073: 3067: 3066: 3064: 3062: 3046: 3040: 3039: 3037: 3035: 3020: 3003: 3002: 3000: 2998: 2993:. August 8, 2016 2983: 2977: 2976: 2974: 2972: 2966: 2959: 2950: 2941: 2940: 2938: 2936: 2920: 2914: 2913: 2895: 2872: 2871: 2869: 2867: 2852: 2846: 2845: 2837: 2831: 2830: 2828: 2826: 2810: 2804: 2803: 2801: 2799: 2783: 2777: 2776: 2774: 2772: 2763:. June 6, 1986. 2749: 2743: 2742: 2740: 2738: 2732: 2725: 2716: 2710: 2709: 2707: 2705: 2690: 2684: 2683: 2681: 2679: 2664: 2655: 2654: 2652: 2650: 2631: 2625: 2624: 2622: 2620: 2605: 2599: 2598: 2596: 2594: 2585:. Archived from 2564: 2543: 2542: 2537:. Archived from 2522: 2516: 2515: 2496:10.1038/nmat4687 2476:Nature Materials 2471: 2465: 2464: 2462: 2460: 2440: 2431: 2430: 2428: 2426: 2407: 2401: 2400: 2398: 2396: 2376: 2370: 2369: 2367: 2365: 2359: 2352: 2344: 2331: 2330: 2328: 2326: 2306: 2293: 2292: 2290: 2288: 2282: 2271: 2257: 2220: 2219: 2217: 2215: 2209: 2198: 2190: 2179: 2178: 2176: 2174: 2158: 2147: 2146: 2145:on July 3, 2014. 2141:. Archived from 2131: 2099: 2098: 2084: 2080: 2065: 2064: 2053: 2052: 2041: 2040: 2029: 2028: 2017: 2016: 2005: 2004: 1737: 1733: 1626: 1612:s main engines. 1611: 1462: 1439: 1431: 1430: 1378:specific impulse 1255: 1234: 1146:state of the art 1138:expanding nozzle 1055: 982: 981: 970: 969: 823: 655: 654: 653: 643: 638:pogo oscillation 598:systems for the 524: 510: 496: 482: 427:specific impulse 282:Specific impulse 271:Specific impulse 176: 116: 67: 65: 38: 31: 27: 7937: 7936: 7932: 7931: 7930: 7928: 7927: 7926: 7882: 7881: 7880: 7875: 7857: 7578: 7571: 7567: 7558: 7496: 7386:RD-0255 to 0257 7381:RD-0243 to 0245 7243: 7232: 7228: 7222: 7210: 7186: 6927: 6918: 6908: 6772: 6766: 6760: 6591: 6585: 6566: 6559: 6546: 6544:launch vehicles 6530: 6500: 6495: 6341:studied designs 6324: 6306: 6267:Shuttle-Centaur 6228: 6192: 6161: 6137:Getaway Special 6120: 6057: 6020: 5976: 5922: 5916: 5866: 5819: 5764: 5713: 5690: 5685: 5632: 5627: 5617: 5615: 5606: 5605: 5601: 5591: 5589: 5574: 5570: 5560: 5558: 5557:on May 30, 2017 5545: 5544: 5540: 5530: 5528: 5515: 5514: 5510: 5500: 5498: 5497:. April 4, 2024 5489: 5488: 5484: 5474: 5472: 5463: 5462: 5458: 5448: 5446: 5437: 5436: 5432: 5422: 5420: 5410: 5406: 5396: 5394: 5384: 5380: 5370: 5368: 5367:. March 6, 2024 5359: 5358: 5354: 5344: 5342: 5333: 5332: 5328: 5318: 5316: 5307: 5306: 5302: 5292: 5290: 5281: 5280: 5276: 5266: 5264: 5255: 5254: 5250: 5240: 5238: 5229: 5228: 5224: 5214: 5212: 5202: 5198: 5188: 5186: 5177: 5176: 5172: 5162: 5160: 5150: 5146: 5136: 5134: 5125: 5124: 5120: 5110: 5108: 5099: 5098: 5094: 5084: 5082: 5073: 5072: 5068: 5049: 5045: 5026: 5022: 5012: 5010: 5001: 5000: 4996: 4986: 4984: 4975: 4974: 4970: 4951: 4947: 4928: 4924: 4914: 4912: 4902: 4898: 4879: 4875: 4865: 4863: 4853: 4849: 4830: 4826: 4816: 4814: 4804: 4800: 4790: 4788: 4773: 4769: 4759: 4757: 4747: 4743: 4733: 4731: 4716: 4712: 4702: 4700: 4685: 4681: 4671: 4669: 4654: 4650: 4640: 4638: 4623: 4619: 4609: 4607: 4588: 4584: 4574: 4572: 4565:Washington Post 4557: 4553: 4543: 4541: 4522: 4518: 4508: 4506: 4491: 4487: 4477: 4475: 4471: 4467:. 20180006338. 4456: 4448: 4444: 4434: 4432: 4417: 4413: 4403: 4401: 4386: 4382: 4372: 4370: 4355: 4348: 4338: 4336: 4321: 4317: 4307: 4305: 4290: 4286: 4276: 4274: 4261: 4260: 4256: 4246: 4244: 4225: 4218: 4208: 4206: 4191: 4187: 4177: 4175: 4156: 4152: 4142: 4140: 4125: 4121: 4111: 4109: 4101: 4100: 4096: 4086: 4084: 4074: 4070: 4060: 4058: 4048: 4044: 4034: 4032: 4023: 4022: 4018: 4008: 4006: 3991: 3987: 3977: 3975: 3965: 3961: 3951: 3949: 3939: 3935: 3923: 3915: 3913: 3902: 3898: 3888: 3886: 3876: 3872: 3862: 3860: 3845: 3838: 3828: 3826: 3811: 3807: 3797: 3795: 3780: 3773: 3763: 3761: 3746: 3742: 3732: 3730: 3721: 3720: 3716: 3697: 3693: 3683: 3681: 3674: 3665: 3644: 3640: 3633: 3619: 3615: 3605: 3603: 3588: 3584: 3574: 3572: 3557: 3553: 3543: 3541: 3526: 3522: 3515: 3501: 3494: 3484: 3482: 3467: 3463: 3456: 3431: 3427: 3417: 3415: 3400: 3393: 3383: 3381: 3366: 3362: 3352: 3350: 3346: 3331: 3327: 3326: 3322: 3303: 3296: 3279: 3278: 3274: 3264: 3262: 3253: 3252: 3248: 3238: 3236: 3225: 3221: 3211: 3209: 3205: 3195: 3191: 3181: 3179: 3175: 3164: 3158: 3157: 3150: 3140: 3138: 3123: 3119: 3111: 3107: 3106: 3099: 3091: 3080: 3074: 3070: 3060: 3058: 3051:"Countdown 101" 3047: 3043: 3033: 3031: 3021: 3006: 2996: 2994: 2985: 2984: 2980: 2970: 2968: 2967:on May 28, 2010 2964: 2957: 2951: 2944: 2934: 2932: 2921: 2917: 2910: 2896: 2875: 2865: 2863: 2854: 2853: 2849: 2838: 2834: 2824: 2822: 2811: 2807: 2797: 2795: 2784: 2780: 2770: 2768: 2751: 2750: 2746: 2736: 2734: 2730: 2723: 2717: 2713: 2703: 2701: 2692: 2691: 2687: 2677: 2675: 2666: 2665: 2658: 2648: 2646: 2633: 2632: 2628: 2618: 2616: 2609:"Nozzle Design" 2607: 2606: 2602: 2592: 2590: 2583: 2565: 2546: 2527:"Nozzle Design" 2523: 2519: 2472: 2468: 2458: 2456: 2441: 2434: 2424: 2422: 2409: 2408: 2404: 2394: 2392: 2377: 2373: 2363: 2361: 2357: 2350: 2346: 2345: 2334: 2324: 2322: 2307: 2296: 2286: 2284: 2280: 2269: 2258: 2223: 2213: 2211: 2207: 2196: 2192: 2191: 2182: 2172: 2170: 2159: 2150: 2133: 2132: 2113: 2096: 2093: 2088: 2087: 2081: 2077: 2062: 2050: 2038: 2026: 2014: 2008:External videos 2003: 1991: 1967: 1961: 1925: 1823: 1817: 1750: 1742: 1735: 1731: 1622: 1609: 1590: 1576: 1569: 1554: 1537: 1530: 1515: 1508: 1493: 1486: 1471: 1460: 1440: 1425: 1412:Artemis program 1310: 1248: 1230: 1224: 1218: 1162:Aerojet General 1131: 1126:de Laval nozzle 1045: 1043: 1038: 1029: 979: 973:External videos 968: 947: 935:deionized water 862: 849:expansion ratio 845:de Laval nozzle 819: 818:The nozzles of 812: 765: 761: 755: 730: 716: 691: 652: 649: 648: 647: 645: 641: 618:axial-flow pump 614: 612:Oxidizer system 609: 549:liquid hydrogen 537: 536: 535: 534: 530: 529: 528: 525: 516: 515: 514: 511: 502: 501: 500: 497: 488: 487: 486: 485:RS-25 schematic 483: 472: 435: 413: 404:liquid hydrogen 174: 169: 132: 108: 63: 61: 44: 24: 17: 12: 11: 5: 7935: 7925: 7924: 7919: 7914: 7909: 7904: 7899: 7894: 7877: 7876: 7874: 7873: 7866: 7862: 7859: 7858: 7856: 7855: 7854: 7853: 7848: 7843: 7838: 7833: 7828: 7823: 7818: 7813: 7808: 7803: 7798: 7793: 7788: 7782:United States 7780: 7779: 7778: 7773: 7768: 7763: 7758: 7753: 7748: 7740: 7739: 7738: 7733: 7725: 7724: 7723: 7718: 7710: 7709: 7708: 7703: 7698: 7693: 7688: 7680: 7679: 7678: 7673: 7668: 7663: 7658: 7653: 7648: 7643: 7638: 7633: 7628: 7623: 7615: 7614: 7613: 7610: 7607: 7602: 7597: 7592: 7583: 7581: 7573: 7572: 7565: 7563: 7560: 7559: 7557: 7556: 7555: 7554: 7548: 7542: 7536:United States 7534: 7533: 7532: 7524: 7523: 7522: 7517: 7508: 7506: 7502: 7501: 7498: 7497: 7495: 7494: 7493: 7492: 7486: 7481: 7475: 7470: 7465: 7459:United States 7457: 7456: 7455: 7450: 7445: 7440: 7435: 7427: 7426: 7425: 7420: 7415: 7408: 7403: 7398: 7393: 7388: 7383: 7378: 7373: 7368: 7363: 7358: 7353: 7348: 7340: 7339: 7338: 7329: 7328: 7327: 7319: 7318: 7317: 7312: 7304: 7303: 7302: 7297: 7292: 7287: 7279: 7278: 7277: 7272: 7267: 7262: 7257: 7248: 7246: 7241: 7230: 7226: 7196: 7192: 7191: 7188: 7187: 7185: 7184: 7183: 7182: 7177: 7172: 7167: 7162: 7157: 7152: 7147: 7145:LR70-NA , S-3D 7142: 7137: 7132: 7127: 7122: 7117: 7111:United States 7109: 7108: 7107: 7100: 7093: 7085: 7084: 7083: 7075: 7074: 7073: 7068: 7061: 7056: 7051: 7046: 7041: 7036: 7031: 7026: 7021: 7016: 7011: 7006: 6998: 6997: 6996: 6986: 6985: 6984: 6977: 6970: 6965: 6960: 6955: 6948: 6939: 6937: 6920: 6914: 6913: 6910: 6909: 6907: 6906: 6905: 6904: 6897: 6887: 6886: 6885: 6875: 6874: 6873: 6866: 6859: 6852: 6847: 6841:United States 6839: 6838: 6837: 6830: 6823: 6816: 6811: 6806: 6799: 6792: 6781: 6779: 6770: 6762: 6761: 6759: 6758: 6757: 6756: 6751: 6746: 6741: 6736: 6729: 6721:United States 6719: 6718: 6717: 6710: 6705: 6697: 6696: 6695: 6688: 6683: 6675: 6674: 6673: 6668: 6660: 6659: 6658: 6653: 6648: 6640: 6639: 6638: 6631: 6624: 6619: 6614: 6609: 6600: 6598: 6589: 6578: 6569: 6561: 6560: 6558: 6557: 6551: 6548: 6547: 6533:Rocket engines 6529: 6528: 6521: 6514: 6506: 6497: 6496: 6494: 6493: 6486: 6479: 6472: 6465: 6458: 6451: 6444: 6439: 6431: 6423: 6415: 6407: 6399: 6391: 6383: 6375: 6370: 6365: 6360: 6355: 6350: 6345: 6344: 6343: 6332: 6330: 6326: 6325: 6323: 6322: 6314: 6312: 6308: 6307: 6305: 6304: 6299: 6294: 6289: 6288: 6287: 6282: 6277: 6269: 6264: 6259: 6254: 6249: 6244: 6242:Saturn-Shuttle 6238: 6236: 6230: 6229: 6227: 6226: 6221: 6216: 6211: 6206: 6200: 6198: 6194: 6193: 6191: 6190: 6185: 6180: 6175: 6169: 6167: 6163: 6162: 6160: 6159: 6154: 6149: 6144: 6139: 6134: 6128: 6126: 6122: 6121: 6119: 6118: 6113: 6108: 6107: 6106: 6096: 6091: 6086: 6081: 6076: 6071: 6065: 6063: 6059: 6058: 6056: 6055: 6042: 6028: 6026: 6022: 6021: 6019: 6018: 6013: 6005: 5995: 5984: 5982: 5978: 5977: 5975: 5974: 5969: 5964: 5959: 5954: 5949: 5944: 5939: 5926: 5924: 5918: 5917: 5915: 5914: 5913: 5912: 5907: 5897: 5892: 5891: 5890: 5885: 5874: 5872: 5868: 5867: 5865: 5864: 5859: 5854: 5849: 5844: 5836: 5827: 5825: 5821: 5820: 5818: 5817: 5810: 5803: 5796: 5789: 5782: 5774: 5772: 5766: 5765: 5763: 5762: 5757: 5752: 5747: 5742: 5737: 5732: 5727: 5721: 5719: 5715: 5714: 5712: 5711: 5706: 5701: 5695: 5692: 5691: 5684: 5683: 5676: 5669: 5661: 5655: 5654: 5644: 5638: 5631: 5630:External links 5628: 5626: 5625: 5599: 5568: 5538: 5508: 5482: 5456: 5430: 5404: 5378: 5352: 5326: 5300: 5274: 5248: 5222: 5196: 5170: 5144: 5118: 5092: 5066: 5059:) – via 5043: 5036:) – via 5020: 4994: 4968: 4961:) – via 4945: 4938:) – via 4922: 4896: 4889:) – via 4873: 4847: 4840:) – via 4824: 4798: 4767: 4741: 4710: 4679: 4648: 4617: 4582: 4551: 4516: 4485: 4442: 4411: 4380: 4346: 4315: 4284: 4254: 4216: 4185: 4164:blogs.nasa.gov 4150: 4119: 4094: 4068: 4042: 4016: 3985: 3959: 3933: 3896: 3870: 3836: 3805: 3771: 3740: 3714: 3691: 3663: 3638: 3631: 3613: 3582: 3551: 3520: 3513: 3492: 3461: 3454: 3425: 3391: 3360: 3320: 3313:) – via 3294: 3272: 3246: 3219: 3189: 3148: 3117: 3097: 3068: 3041: 3004: 2978: 2942: 2915: 2908: 2873: 2847: 2832: 2805: 2778: 2744: 2711: 2685: 2656: 2626: 2600: 2581: 2544: 2517: 2482:(8): 804–809. 2466: 2432: 2402: 2371: 2332: 2294: 2221: 2180: 2148: 2135:"RS-25 Engine" 2110: 2092: 2089: 2086: 2085: 2074: 2073: 2070: 2069: 2058: 2057: 2046: 2045: 2034: 2033: 2022: 2021: 2010: 2009: 2002: 1999: 1998: 1997: 1990: 1987: 1960: 1957: 1942: 1924: 1921: 1816: 1813: 1800: 1799: 1796: 1793: 1764:in storage at 1749: 1746: 1745: 1744: 1740: 1719: 1703: 1691: 1679: 1676:abort to orbit 1663: 1651: 1589: 1586: 1579: 1578: 1574: 1571: 1567: 1564: 1561: 1557: 1556: 1552: 1549: 1547: 1544: 1540: 1539: 1535: 1532: 1528: 1525: 1522: 1518: 1517: 1513: 1510: 1506: 1503: 1500: 1496: 1495: 1491: 1488: 1484: 1481: 1478: 1474: 1473: 1469: 1466: 1464: 1458: 1454: 1453: 1450: 1446: 1445: 1442: 1434: 1424: 1421: 1420: 1419: 1404: 1389: 1370: 1363: 1356: 1349: 1334: 1309: 1306: 1217: 1214: 1129: 1095:Apollo program 1042: 1039: 1037: 1034: 1028: 1025: 1006:, a universal 987: 986: 975: 974: 967: 964: 946: 943: 888:Motorola 68000 861: 858: 811: 808: 763: 759: 754: 751: 729: 726: 715: 712: 690: 687: 674:heat exchanger 650: 613: 610: 608: 605: 584:heat exchanger 532: 531: 526: 519: 518: 517: 512: 505: 504: 503: 498: 491: 490: 489: 484: 477: 476: 475: 474: 473: 471: 468: 433: 411: 348: 347: 344: 340: 339: 337: 333: 332: 328: 327: 324: 320: 319: 316: 312: 311: 308: 304: 303: 299: 298: 295: 289: 288: 285: 278: 277: 274: 267: 266: 263: 256: 255: 252: 246: 245: 242: 241:Throttle range 238: 237: 234: 230: 229: 224:(512,300 218: 217:Thrust, vacuum 214: 213: 209: 208: 205: 201: 200: 196: 195: 190: 186: 185: 182: 178: 177: 172: 163: 159: 158: 152: 151: 148: 144: 143: 138: 134: 133: 131: 130: 125: 119: 117: 110: 109: 107: 106: 105:(2013–present) 100: 94: 90: 88: 84: 83: 78: 74: 73: 58: 54: 53: 50: 46: 45: 39: 15: 9: 6: 4: 3: 2: 7934: 7923: 7920: 7918: 7915: 7913: 7910: 7908: 7905: 7903: 7900: 7898: 7895: 7893: 7890: 7889: 7887: 7871: 7867: 7864: 7863: 7860: 7852: 7849: 7847: 7844: 7842: 7839: 7837: 7834: 7832: 7829: 7827: 7824: 7822: 7819: 7817: 7814: 7812: 7809: 7807: 7804: 7802: 7799: 7797: 7794: 7792: 7789: 7787: 7784: 7783: 7781: 7777: 7774: 7772: 7769: 7767: 7764: 7762: 7759: 7757: 7754: 7752: 7749: 7747: 7744: 7743: 7741: 7737: 7734: 7732: 7729: 7728: 7726: 7722: 7719: 7717: 7714: 7713: 7711: 7707: 7704: 7702: 7699: 7697: 7694: 7692: 7689: 7687: 7684: 7683: 7681: 7677: 7674: 7672: 7669: 7667: 7664: 7662: 7659: 7657: 7654: 7652: 7649: 7647: 7644: 7642: 7639: 7637: 7634: 7632: 7629: 7627: 7624: 7622: 7619: 7618: 7616: 7611: 7608: 7606: 7603: 7601: 7598: 7596: 7593: 7591: 7588: 7587: 7585: 7584: 7582: 7580: 7574: 7552: 7549: 7546: 7543: 7541: 7538: 7537: 7535: 7531: 7528: 7527: 7525: 7521: 7520:RD-211 to 214 7518: 7516: 7513: 7512: 7510: 7509: 7507: 7503: 7490: 7487: 7485: 7482: 7479: 7476: 7474: 7471: 7469: 7466: 7464: 7461: 7460: 7458: 7454: 7451: 7449: 7446: 7444: 7441: 7439: 7436: 7434: 7431: 7430: 7428: 7424: 7421: 7419: 7416: 7414: 7413: 7409: 7407: 7404: 7402: 7399: 7397: 7394: 7392: 7391:RD-215 to 219 7389: 7387: 7384: 7382: 7379: 7377: 7374: 7372: 7369: 7367: 7366:RD-0233, 0234 7364: 7362: 7359: 7357: 7356:RD-0207, 0214 7354: 7352: 7349: 7347: 7344: 7343: 7341: 7336: 7335:Paektusan LRE 7333: 7332: 7330: 7326: 7323: 7322: 7320: 7316: 7313: 7311: 7308: 7307: 7305: 7301: 7298: 7296: 7293: 7291: 7288: 7286: 7283: 7282: 7280: 7276: 7273: 7271: 7268: 7266: 7263: 7261: 7258: 7256: 7253: 7252: 7250: 7249: 7247: 7244: 7237: 7233: 7221: 7217: 7213: 7208: 7204: 7200: 7197: 7193: 7181: 7178: 7176: 7173: 7171: 7168: 7166: 7163: 7161: 7158: 7156: 7153: 7151: 7148: 7146: 7143: 7141: 7138: 7136: 7133: 7131: 7128: 7126: 7123: 7121: 7118: 7116: 7113: 7112: 7110: 7106: 7105: 7101: 7099: 7098: 7094: 7092: 7089: 7088: 7086: 7082: 7079: 7078: 7076: 7072: 7069: 7067: 7066: 7062: 7060: 7057: 7055: 7052: 7050: 7047: 7045: 7042: 7040: 7037: 7035: 7032: 7030: 7027: 7025: 7022: 7020: 7019:RD-0105, 0109 7017: 7015: 7012: 7010: 7007: 7005: 7002: 7001: 6999: 6995: 6994: 6990: 6989: 6987: 6983: 6982: 6978: 6976: 6975: 6971: 6969: 6966: 6964: 6961: 6959: 6956: 6954: 6953: 6949: 6947: 6944: 6943: 6941: 6940: 6938: 6935: 6931: 6924: 6921: 6915: 6903: 6902: 6898: 6896: 6895: 6891: 6890: 6888: 6884: 6883: 6879: 6878: 6876: 6872: 6871: 6867: 6865: 6864: 6860: 6858: 6857: 6853: 6851: 6848: 6846: 6843: 6842: 6840: 6836: 6835: 6831: 6829: 6828: 6824: 6822: 6821: 6817: 6815: 6812: 6810: 6807: 6805: 6804: 6800: 6798: 6797: 6793: 6791: 6790: 6786: 6785: 6783: 6782: 6780: 6777: 6773: 6763: 6755: 6752: 6750: 6747: 6745: 6742: 6740: 6737: 6735: 6734: 6730: 6728: 6727: 6723: 6722: 6720: 6716: 6715: 6711: 6709: 6706: 6704: 6703:KVD-1 (RD-56) 6701: 6700: 6698: 6694: 6693: 6689: 6687: 6684: 6682: 6679: 6678: 6676: 6672: 6669: 6667: 6664: 6663: 6661: 6657: 6654: 6652: 6649: 6647: 6644: 6643: 6641: 6637: 6636: 6632: 6630: 6629: 6625: 6623: 6620: 6618: 6615: 6613: 6610: 6608: 6605: 6604: 6602: 6601: 6599: 6596: 6592: 6582: 6579: 6577: 6573: 6570: 6568: 6562: 6556: 6553: 6552: 6549: 6545: 6542: 6538: 6534: 6527: 6522: 6520: 6515: 6513: 6508: 6507: 6504: 6492: 6491: 6487: 6485: 6484: 6480: 6478: 6477: 6473: 6471: 6470: 6466: 6464: 6463: 6459: 6457: 6456: 6452: 6450: 6449: 6445: 6443: 6440: 6437: 6436: 6432: 6429: 6428: 6424: 6421: 6420: 6416: 6413: 6412: 6408: 6405: 6404: 6400: 6397: 6396: 6392: 6389: 6388: 6384: 6381: 6380: 6379:Hail Columbia 6376: 6374: 6373:Conroy Virtus 6371: 6369: 6366: 6364: 6361: 6359: 6356: 6354: 6351: 6349: 6346: 6342: 6339: 6338: 6337: 6334: 6333: 6331: 6327: 6321: 6320: 6316: 6315: 6313: 6309: 6303: 6300: 6298: 6295: 6293: 6290: 6286: 6283: 6281: 6278: 6276: 6273: 6272: 6270: 6268: 6265: 6263: 6260: 6258: 6255: 6253: 6250: 6248: 6245: 6243: 6240: 6239: 6237: 6235: 6231: 6225: 6222: 6220: 6217: 6215: 6212: 6210: 6207: 6205: 6202: 6201: 6199: 6195: 6189: 6186: 6184: 6181: 6179: 6176: 6174: 6171: 6170: 6168: 6164: 6158: 6155: 6153: 6150: 6148: 6145: 6143: 6140: 6138: 6135: 6133: 6132:Deutschland-1 6130: 6129: 6127: 6123: 6117: 6114: 6112: 6109: 6105: 6102: 6101: 6100: 6097: 6095: 6092: 6090: 6087: 6085: 6082: 6080: 6077: 6075: 6072: 6070: 6067: 6066: 6064: 6060: 6053: 6049: 6047: 6043: 6040: 6036: 6034: 6030: 6029: 6027: 6023: 6017: 6014: 6012: 6006: 6004: 6000: 5996: 5994: 5990: 5986: 5985: 5983: 5979: 5973: 5970: 5968: 5965: 5963: 5960: 5958: 5955: 5953: 5950: 5948: 5945: 5943: 5940: 5936: 5931: 5928: 5927: 5925: 5919: 5911: 5908: 5906: 5903: 5902: 5901: 5900:Landing sites 5898: 5896: 5893: 5889: 5886: 5884: 5881: 5880: 5879: 5876: 5875: 5873: 5869: 5863: 5860: 5858: 5855: 5853: 5850: 5848: 5845: 5840: 5837: 5832: 5829: 5828: 5826: 5822: 5816: 5815: 5811: 5809: 5808: 5804: 5802: 5801: 5797: 5795: 5794: 5790: 5788: 5787: 5783: 5781: 5780: 5776: 5775: 5773: 5771: 5767: 5761: 5758: 5756: 5753: 5751: 5748: 5746: 5743: 5741: 5738: 5736: 5735:External tank 5733: 5731: 5728: 5726: 5723: 5722: 5720: 5716: 5710: 5709:List of crews 5707: 5705: 5702: 5700: 5699:Space Shuttle 5697: 5696: 5693: 5689: 5682: 5677: 5675: 5670: 5668: 5663: 5662: 5659: 5652: 5648: 5645: 5642: 5639: 5637: 5634: 5633: 5613: 5609: 5603: 5587: 5583: 5579: 5572: 5556: 5552: 5548: 5542: 5526: 5522: 5518: 5512: 5496: 5492: 5486: 5470: 5466: 5460: 5444: 5440: 5434: 5419: 5415: 5408: 5393: 5389: 5382: 5366: 5362: 5356: 5340: 5336: 5330: 5314: 5310: 5304: 5288: 5284: 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Fred H. 2949: 2947: 2930: 2926: 2919: 2911: 2905: 2901: 2894: 2892: 2890: 2888: 2886: 2884: 2882: 2880: 2878: 2861: 2857: 2851: 2843: 2836: 2820: 2816: 2809: 2793: 2789: 2782: 2766: 2762: 2758: 2754: 2748: 2729: 2722: 2715: 2699: 2695: 2689: 2673: 2669: 2663: 2661: 2644: 2640: 2636: 2630: 2614: 2610: 2604: 2588: 2584: 2578: 2574: 2570: 2563: 2561: 2559: 2557: 2555: 2553: 2551: 2549: 2540: 2536: 2532: 2528: 2521: 2513: 2509: 2505: 2501: 2497: 2493: 2489: 2485: 2481: 2477: 2470: 2454: 2450: 2446: 2439: 2437: 2420: 2416: 2412: 2406: 2390: 2386: 2382: 2375: 2356: 2349: 2343: 2341: 2339: 2337: 2320: 2316: 2312: 2305: 2303: 2301: 2299: 2279: 2275: 2268: 2267: 2262: 2256: 2254: 2252: 2250: 2248: 2246: 2244: 2242: 2240: 2238: 2236: 2234: 2232: 2230: 2228: 2226: 2206: 2202: 2195: 2189: 2187: 2185: 2168: 2164: 2157: 2155: 2153: 2144: 2140: 2136: 2130: 2128: 2126: 2124: 2122: 2120: 2118: 2116: 2111: 2109: 2107: 2103: 2079: 2075: 2068: 2059: 2056: 2047: 2044: 2035: 2032: 2023: 2020: 2011: 2006: 1996: 1993: 1992: 1986: 1983: 1980: 1976: 1972: 1966: 1956: 1952: 1948: 1944: 1940: 1936: 1932: 1929: 1920: 1918: 1914: 1909: 1906: 1902: 1898: 1896: 1892: 1888: 1883: 1881: 1876: 1875: 1870: 1869: 1864: 1860: 1854: 1852: 1848: 1844: 1836: 1832: 1827: 1822: 1812: 1809: 1805: 1797: 1794: 1791: 1790: 1789: 1786: 1782: 1778: 1774: 1767: 1763: 1759: 1754: 1748:Constellation 1729: 1728: 1723: 1720: 1717: 1713: 1712: 1707: 1704: 1701: 1700: 1695: 1692: 1689: 1688: 1683: 1680: 1677: 1673: 1672: 1667: 1664: 1661: 1660: 1655: 1652: 1649: 1648: 1643: 1640: 1639: 1638: 1636: 1632: 1631: 1625: 1624:Space Shuttle 1615: 1608: 1603: 1594: 1585: 1572: 1565: 1562: 1559: 1558: 1550: 1548: 1545: 1542: 1541: 1533: 1526: 1523: 1520: 1519: 1511: 1504: 1501: 1498: 1497: 1489: 1482: 1476: 1475: 1467: 1465: 1459: 1456: 1455: 1451: 1448: 1447: 1432: 1429: 1417: 1413: 1409: 1405: 1402: 1398: 1394: 1390: 1387: 1383: 1379: 1375: 1371: 1368: 1364: 1361: 1357: 1354: 1350: 1347: 1343: 1339: 1335: 1332: 1328: 1324: 1323: 1322: 1314: 1305: 1303: 1299: 1293: 1291: 1287: 1286: 1280: 1276: 1272: 1268: 1264: 1244: 1240: 1239: 1233: 1232:Space Shuttle 1228: 1223: 1213: 1211: 1210: 1205: 1201: 1197: 1193: 1189: 1183: 1180: 1176: 1170: 1168: 1163: 1159: 1155: 1150: 1147: 1141: 1139: 1135: 1127: 1123: 1119: 1115: 1111: 1106: 1104: 1100: 1096: 1092: 1088: 1084: 1080: 1076: 1072: 1068: 1061:in early 2015 1060: 1033: 1027:Helium system 1024: 1020: 1018: 1013: 1009: 1005: 1002: 993: 985: 976: 971: 963: 960: 955: 951: 942: 940: 936: 931: 929: 923: 921: 917: 913: 909: 905: 901: 895: 893: 889: 885: 882: 879: 875: 866: 857: 854: 850: 846: 841: 838:The engine's 833: 829: 828: 822: 821:Space Shuttle 816: 807: 805: 801: 796: 794: 790: 789:boiling point 785: 782: 778: 774: 770: 750: 746: 742: 739: 735: 720: 711: 709: 705: 699: 697: 686: 682: 679: 675: 671: 667: 663: 658: 639: 634: 632: 627: 623: 619: 604: 601: 597: 592: 589: 585: 581: 576: 574: 570: 566: 562: 561:external tank 558: 557:liquid oxygen 554: 550: 546: 542: 527:Oxidizer flow 523: 509: 495: 481: 467: 463: 461: 458: 454: 450: 449:external tank 446: 441: 439: 432: 428: 423: 421: 417: 409: 408:liquid oxygen 405: 401: 397: 393: 389: 384: 382: 378: 377:Space Shuttle 374: 370: 367: 363: 359: 355: 345: 341: 338: 334: 329: 325: 321: 317: 313: 309: 305: 300: 296: 294: 290: 286: 283: 279: 275: 272: 268: 264: 262: 257: 253: 251: 247: 243: 239: 235: 231: 227: 223: 219: 215: 210: 206: 202: 199:Configuration 197: 194: 191: 187: 183: 181:Mixture ratio 179: 175: 167: 164: 160: 157: 153: 149: 145: 142: 139: 135: 129: 126: 124: 123:Space Shuttle 121: 120: 118: 111: 104: 101: 98: 95: 92: 91: 89: 85: 82: 79: 75: 71: 59: 55: 52:United States 51: 47: 43: 42:Shock diamond 37: 32: 26: 22: 7869: 7410: 7331:North Korea 7102: 7095: 7063: 6991: 6979: 6972: 6950: 6899: 6892: 6880: 6868: 6861: 6854: 6832: 6825: 6818: 6801: 6794: 6787: 6748: 6731: 6724: 6712: 6690: 6633: 6626: 6537:solid motors 6488: 6482: 6474: 6467: 6460: 6453: 6446: 6433: 6425: 6417: 6409: 6401: 6393: 6385: 6377: 6319:Independence 6318: 6045: 6032: 5998: 5988: 5923:and training 5813: 5806: 5799: 5792: 5785: 5778: 5739: 5616:. Retrieved 5611: 5602: 5590:. Retrieved 5581: 5571: 5561:February 13, 5559:. Retrieved 5555:the original 5541: 5531:February 13, 5529:. Retrieved 5511: 5499:. Retrieved 5494: 5485: 5473:. Retrieved 5468: 5459: 5447:. Retrieved 5442: 5433: 5421:. Retrieved 5418:www.wlox.com 5417: 5407: 5395:. Retrieved 5391: 5381: 5369:. Retrieved 5364: 5355: 5343:. Retrieved 5338: 5329: 5319:February 26, 5317:. Retrieved 5312: 5303: 5293:February 26, 5291:. Retrieved 5286: 5277: 5265:. Retrieved 5260: 5251: 5239:. Retrieved 5235:www.wlox.com 5234: 5225: 5213:. Retrieved 5209: 5199: 5187:. Retrieved 5182: 5173: 5161:. Retrieved 5157: 5147: 5135:. Retrieved 5130: 5121: 5109:. Retrieved 5104: 5095: 5083:. Retrieved 5078: 5069: 5046: 5023: 5011:. Retrieved 5006: 4997: 4985:. Retrieved 4980: 4971: 4948: 4925: 4913:. Retrieved 4909: 4899: 4876: 4864:. Retrieved 4860: 4850: 4827: 4815:. Retrieved 4811: 4801: 4789:. Retrieved 4785:the original 4780: 4770: 4758:. Retrieved 4754: 4744: 4732:. 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Retrieved 2167:the original 2161:Wade, Mark. 2143:the original 2094: 2078: 1984: 1968: 1953: 1949: 1945: 1937: 1933: 1930: 1926: 1923:Engine tests 1910: 1907: 1903: 1899: 1884: 1873: 1867: 1855: 1840: 1801: 1770: 1726: 1710: 1698: 1686: 1670: 1658: 1646: 1629: 1619: 1613: 1606: 1582: 1426: 1401:intact abort 1319: 1294: 1284: 1260: 1237: 1208: 1184: 1171: 1151: 1142: 1120:engines and 1110:US Air Force 1107: 1081:used on the 1064: 1030: 1021: 998: 956: 952: 948: 939:vacuum baked 927: 924: 896: 871: 837: 826: 797: 756: 747: 743: 731: 706:(53.05 702:71,140 700: 692: 683: 668:(17.34 659: 635: 615: 593: 577: 563:entered the 538: 464: 442: 430: 424: 385: 361: 357: 353: 351: 204:Nozzle ratio 87:Manufacturer 57:First flight 25: 7868:Engines in 7515:RD-109, 119 7453:RD-864, 869 7438:RD-854, 861 7401:RD-253, 275 7049:RD-170, 171 6430:(2013 film) 6398:(1990 film) 6234:Derivatives 6197:Experiments 6166:Space suits 6152:Shuttle-Mir 6002:(simulator) 5989:Inspiration 5957:Abort modes 5740:Main engine 5618:January 20, 5592:January 20, 5267:January 30, 5241:January 30, 5215:January 30, 5189:January 30, 5163:January 30, 5137:January 30, 5111:January 30, 5085:December 2, 5013:October 24, 4987:October 24, 4726:. S23-021. 4664:. S23-015. 4633:. S23-001. 4575:January 20, 4544:January 20, 3863:January 23, 3798:January 16, 3606:January 16, 3575:January 16, 3544:January 16, 3485:January 16, 3265:December 7, 3141:January 23, 3034:January 17, 3024:Hale, Wayne 2798:January 16, 2771:December 8, 2704:December 8, 2459:December 7, 2425:January 19, 1895:Artemis III 1734:1A and SSME 1410:for future 1103:F-1 engines 1041:Development 945:Main valves 912:core memory 908:plated-wire 802:(TBCs) and 769:Inconel 718 689:Fuel system 366:liquid-fuel 284:, sea-level 220:2,279 212:Performance 137:Predecessor 113:Associated 99:(2005–2013) 7886:Categories 7255:YF-1, 2, 3 7203:Hypergolic 7175:Rutherford 6894:Prometheus 6856:Archimedes 6395:Challenger 6368:Retirement 6157:Hitchhiker 6033:Challenger 5999:Pathfinder 5921:Operations 5793:Challenger 5779:Enterprise 5718:Components 4596:NASA Blogs 4530:NASA Blogs 4427:. 15-178. 4201:. 22-117. 4178:August 31, 4135:. 20-050. 3973:NASA Blogs 3336:NASA Facts 3239:January 8, 3061:January 8, 2935:January 8, 2091:References 1963:See also: 1880:interstage 1863:Artemis II 1851:core stage 1819:See also: 1671:Challenger 1659:Challenger 1630:Challenger 1449:Sea level 1220:See also: 1167:M-1 engine 1079:J-2 engine 1075:Rocketdyne 928:Challenger 860:Controller 728:Preburners 631:cavitating 607:Turbopumps 580:turbopumps 470:Components 388:Rocketdyne 336:References 331:References 302:Dimensions 162:Propellant 81:Rocketdyne 64:1981-04-12 7796:Castor 30 7676:Zefiro 40 7671:Zefiro 23 7612:SpaB-140C 7009:NK-33, 44 6919:cryogenic 6765:Methalox 6584:Hydrolox 6576:Cryogenic 6363:Criticism 6262:Shuttle-C 6025:Disasters 5952:Rollbacks 5814:Endeavour 5800:Discovery 5612:SpaceNews 5475:March 28, 5449:March 28, 5423:March 22, 5397:March 22, 5392:Space.com 5210:Space.com 5158:Space.com 5107:. SciNews 4082:SpaceNews 4029:Futuramic 3829:March 30, 2531:Threshold 2504:1476-4660 2395:March 15, 1995:Shuttle-C 1874:Endeavour 1871:and 1859:Artemis I 1711:Endeavour 1699:Discovery 1647:Discovery 1588:Incidents 1416:Artemis V 1179:zirconium 1118:aerospike 900:lock-step 881:Honeywell 878:redundant 781:zirconium 714:Powerhead 513:Fuel flow 400:cryogenic 293:Mass flow 7811:Orbus-21 7666:Zefiro 9 7429:Ukraine 7207:Aerozine 7195:Storable 7087:Ukraine 7029:RD-0110R 6926:Kerolox 6311:Replicas 6048:disaster 6046:Columbia 6035:disaster 5992:(design) 5935:canceled 5930:Missions 5857:Spacehab 5839:Canadarm 5831:Spacelab 5807:Atlantis 5786:Columbia 5770:Orbiters 5586:Archived 5525:Archived 5501:April 8, 5371:March 9, 5345:March 9, 4915:June 20, 4866:June 20, 4817:June 20, 4791:June 20, 4760:June 20, 4728:Archived 4703:June 20, 4666:Archived 4635:Archived 4604:Archived 4569:Archived 4538:Archived 4503:Archived 4469:Archived 4429:Archived 4398:Archived 4367:Archived 4333:Archived 4302:Archived 4271:Archived 4241:Archived 4203:Archived 4172:Archived 4137:Archived 4087:June 24, 4061:June 24, 4035:June 24, 4003:Archived 3952:June 26, 3910:Archived 3908:. NASA. 3889:June 15, 3857:Archived 3792:Archived 3758:Archived 3705:BBC News 3653:ABC News 3592:"STS-68" 3561:"STS-51" 3530:"STS-55" 3446:Scribner 3412:Archived 3378:Archived 3344:Archived 3289:Archived 3173:Archived 3135:Archived 3089:Archived 3055:Archived 3053:. NASA. 2929:Archived 2765:Archived 2728:Archived 2726:. NASA. 2643:Archived 2512:27443899 2453:Archived 2389:Archived 2355:Archived 2319:Archived 2278:Archived 1989:See also 1868:Atlantis 1727:Columbia 1687:Columbia 1666:STS-51-F 1654:STS-51-F 1642:STS-41-D 1635:STS-51-F 1614:Columbia 1607:Columbia 1342:STS-51-L 1308:Upgrades 1238:Atlantis 1209:Columbia 1091:Saturn V 1017:titanium 930:accident 827:Columbia 553:oxidizer 364:), is a 323:Dry mass 315:Diameter 273:, vacuum 261:pressure 259:Chamber 77:Designer 7870:italics 7831:Star 48 7826:Star 37 7806:Orbus-6 7727:Israel 7661:Waxwing 7617:Europe 7609:SpaB-65 7511:Russia 7376:RD-0237 7371:RD-0236 7342:Russia 7321:Israel 7281:Europe 7125:Kestrel 7071:S1.5400 7034:RD-0124 7000:Russia 6993:SCE-200 6889:Europe 6882:RD-0169 6877:Russia 6803:Longyun 6796:Lingyun 6714:RD-0146 6708:RD-0120 6699:Russia 6656:Vulcain 6642:Europe 6565:Liquid 6541:orbital 6462:Shuttle 6329:Related 6292:Liberty 6257:Jupiter 6125:Special 6116:STS-3xx 6104:flights 6062:Support 5981:Testing 5824:Add-ons 5725:Orbiter 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