Space Shuttle Solid Rocket Booster

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pulled away from the SRB by the drogue chute. The main chute suspension lines are pulled out from deployment bags that remain in the frustum. At full extension of the lines, which are 203 ft (62 m) long, the three main chutes are pulled from their deployment bags and inflate to their first reefed condition. The frustum and drogue parachute continue on a separate trajectory to splashdown. After specified time delays (using redundant 10- and 17-second reefing line cutters), the main chute reefing lines are cut and the chutes inflate to their second reefed and full open configurations. The main chute cluster decelerates the SRB to terminal conditions. Each of the 136 ft (41 m) diameter, 20° conical ribbon parachutes have a design load of approximately 195,000 lb (88 t) and each weighs approximately 2,180 lb (990 kg). These parachutes are the largest that have ever been used, in both deployed size and load weight. The RSRM nozzle extension is severed by a pyrotechnic charge about 20 seconds after frustum separation.

1914: 922:

bearing loads. Without the hold-down bolts the SSMEs would violently tip the flight stack (orbiter, external tank, SRBs) over onto the external tank. That rotating moment is initially countered by the hold-bolts. Prior to release of the vehicle stack for liftoff, the SRBs must simultaneously ignite and pressurize their combustion chambers and exhaust nozzles to produce a thrust-derived, net counter-rotating moment exactly equal to the SSME's rotating moment. With the SRBs reaching full thrust, the hold-down bolts are blown, releasing the vehicle stack, the net rotating moment is zero, and the net vehicle thrust (opposing gravity) is positive, lifting the orbiter stack vertically from the launch pedestal, controllable through the coordinated

685: 1724: 1884: 1241: 1070: 761: 2715:

identified; (4) NASA has launched the shuttle with no evidence of any significant solid rocket motor safety problems; (5) development costs have increased $ 575 million due to reductions in the program's annual funding levels; and (6) NASA estimates that it would cost $ 212 million to terminate existing contracts as of September 30, 1993. - Actual report says 'the estimated development costs had increased by about 95 percent--to $ 3.25 billion from the program's January 1988 initial estimate and that the first flight schedule had slipped by over 2-l/2 years.'

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hydraulic power to both servoactuators within 115% operational limits in the event that hydraulic pressure from the other HPU should drop below 2,050 psi (14.1 MPa). A switch contact on the switching valve closed when the valve was in the secondary position. When the valve was closed, a signal was sent to the APU controller, that inhibited the 100% APU speed control logic and enabled the 112% APU speed control logic. The 100-percent APU speed enabled one APU/HPU to supply sufficient operating hydraulic pressure to both servoactuators of that SRB.

947:

is less than or equal to 50 psi (340 kPa). A backup cue is the time elapsed from booster ignition. The separation sequence is initiated, commanding the thrust vector control actuators to the null position and putting the main propulsion system into a second-stage configuration (0.8 seconds from sequence initialization), which ensures the thrust of each SRB is less than 100,000 lbf (440 kN). Orbiter yaw attitude is held for four seconds, and SRB thrust drops to less than 60,000 lbf (270 kN).

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right SRB failed at launch and allowed hot gases from within that rocket booster to sear a hole into the adjacent main external fuel tank and also weaken the lower strut holding the SRB to the external tank. The leak in the SRB joint caused the eventually catastrophic failure of the lower strut and partial detachment of the SRB, which led to a collision between the SRB and the external tank. With the external tank being destroyed and the shuttle stack, traveling at a speed of Mach

1105: 6683: 1549: 532: 1145:, recover the SRBs and descent/recovery hardware. Once the boosters are located, the Diver Operated Plug (DOP) is maneuvered by divers into place to plug the SRB nozzle and drain the water from the motor case. Pumping air into and water out of the SRB causes the SRB to change from a nose-up floating position to a horizontal attitude more suitable for towing. The retrieval vessels then tow the boosters and other objects recovered back to 1496: 479: 29: 958:(BSMs) on each end of each SRB. The BSMs separate the SRBs from the external tank. The solid rocket motors in each cluster of four are ignited by firing redundant NSD pressure cartridges into redundant confined detonating fuse manifolds. The separation commands issued from the orbiter by the SRB separation sequence initiate the redundant NSD pressure cartridge in each bolt and ignite the BSMs to effect a clean separation. 1030: 1066:

54 ft (16 m) diameter conical ribbon drogue parachute inflates to its initial reefed condition. The drogue disreefs twice after specified time delays (using redundant 7- and 12-second reefing line cutters), and it reorients/stabilizes the SRB for main chute deployment. The drogue parachute has a design load of approximately 315,000 lb (143 t) and weighs approximately 1,200 lb (540 kg).

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carries the range safety system cross-strap wiring connecting each SRB Range Safety System (RSS) and the ET RSS with each other. The aft attachment points consist of three separate struts: upper, diagonal and lower. Each strut contains one bolt with an NSD pressure cartridge at each end. The upper strut also carries the umbilical interface between its SRB and the external tank and on to the orbiter.

1905:(SRBs), which were developed from the four-segment SRBs used for the Shuttle. Modifications for the SLS included the addition of a center booster segment, new avionics, and new insulation which eliminates the Shuttle SRB's asbestos and is 860 kg (1,900 lb) lighter. The five-segment SRBs provide approximately 25% more total impulse than the Shuttle SRB, and are not recovered after use. 1950: 1212: 1225:

and ensure higher strength margins during ascent, the attach ring was redesigned to encircle the motor case completely (360°). Previously, the attachment ring formed a 'C' shape and encircled the motor case just 270°. Additionally, special structural tests were performed on the aft skirt. During this test program, an anomaly occurred in a critical

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Space Shuttle that was part of the original launch team. USBI was absorbed by United Space Alliance as the Solid Rocket Booster Element division in 1998 and the USBI division was disbanded at Pratt & Whitney the following year. At its peak, USBI had over 1500 personnel working on the Shuttle Boosters at KSC, FL and Huntsville, Alabama.

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Control (ATVC) drivers, which transmitted signals proportional to the commands to each servoactuator of the main engines and SRBs. Four independent flight control system channels and four ATVC channels controlled six main engine and four SRB ATVC drivers, with each driver controlling one hydraulic port on each main and SRB servoactuator.

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differential-pressure sensing detected the erroneous input persisting over a predetermined time, an isolating valve would be selected, excluding it from the force-sum entirely. Failure monitors were provided for each channel to indicate which channel had been bypassed, and the isolation valve on each channel could be reset.

1124:(initial impact and slapdown). Salt Water Activated Release (SWAR) devices are now incorporated into the main chute riser lines to simplify recovery efforts and reduce damage to the SRB. The drogue deployment bag/pilot parachutes, drogue parachutes and frustums, each main chute, and the SRBs are buoyant and are recovered. 930:

and motor nozzle gimbal commands, which orient the vehicle about its center of mass. As the forces on the vehicle change due to propellant consumption, increasing speed, changes in aerodynamic drag, and other factors, the vehicle automatically adjusts its orientation in response to its dynamic control command inputs.

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its own lubrication pump, and the HPU hydraulic pump. A startup bypass line went around the pump and fed the gas generator using the nitrogen tank pressure until the APU speed was such that the fuel pump outlet pressure exceeded that of the bypass line, at which point all the fuel was supplied to the fuel pump.

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United Space Boosters Inc. (USBI), a division of Pratt & Whitney, under United Technologies, was the original SRB prime contractor for SRB assembly, checkout and refurbishment for all non-solid-rocket-motor components and for SRB integration. They were the longest-running prime contractor for the

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The SRBs are jettisoned from the space shuttle at an altitude of about 146,000 ft (45 km). SRB separation is initiated when the three solid-rocket motor-chamber pressure transducers are processed in the redundancy-management middle-value select and the head-end chamber pressure of both SRBs

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SRB ignition can occur only when a manual lock pin from each SRB safe and arm device has been removed. The ground crew removes the pin during prelaunch activities. At T−5:00, the SRB safe and arm device is rotated to the arm position. The solid rocket motor ignition commands are issued when the three

2714:

GAO noted that: (1) the need for the advanced motor has diminished since the development program was first approved in 1988; (2) NASA had no actual flight experience with the advanced motors when the program was approved; (3) the advanced motor might not be used for launching the payloads originally

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into low-Earth orbit for later on-orbit assembly. Unlike the 5-segment SRB for the Ares I, the 5.5-segment boosters for the Ares V were to be identical in design, construction, and function to the current SRBs except for the extra segments. Like the shuttle boosters, the Ares V boosters would fly an

1041:

The SRBs are jettisoned from the shuttle system at 2 minutes and an altitude of about 146,000 feet (45 km). After continuing to rise to about 220,000 feet (67 km), the SRBs begin to fall back to earth and once back in the denser atmosphere are slowed by a parachute system to prevent damage

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system (RSS) provides for destruction of a rocket or part of it with on-board explosives by remote command if the rocket is out of control, in order to limit the danger to people on the ground from crashing pieces, explosions, fire, poisonous substances, etc. The RSS was only activated once – during

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and generated mechanical shaft power to drive a hydraulic pump that produced hydraulic pressure for the SRB hydraulic system. The two separate HPUs and two hydraulic systems were located on the aft end of each SRB between the SRB nozzle and aft skirt. The HPU components were mounted on the aft skirt

559:

When the two NSDs were ignited at each hold down, the frangible nut fractured, releasing the hold-down stud. The stud traveled downward because of the release of tension in the stud (pretensioned before launch), NSD gas pressure and gravity. The stud was stopped by the stud deceleration stand, which

362:

The SRBs committed the shuttle to liftoff and ascent, without the possibility of launch abort, until both motors had fully consumed their propellants and had simultaneously been jettisoned by explosive jettisoning bolts from the remainder of the vehicle. Only then could any conceivable set of launch

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retention straps. This allows the pilot chute to pull the drogue pack from the SRB, causing the drogue suspension lines to deploy from their stored position. At full extension of the twelve 105 ft (32 m) suspension lines, the drogue deployment bag is stripped away from the canopy, and the

950:

The SRBs separate from the external tank within 30 milliseconds of the ordnance firing command. The forward attachment point consists of a ball (SRB) and socket (External Tank; ET) held together by one bolt. The bolt contains one NSD pressure cartridge at each end. The forward attachment point also

929:

During ascent, multiple all-axis accelerometers detect and report the vehicle's flight and orientation (referencing the flight deck aboard the orbiter), as the flight reference computers translate navigation commands (steering to a particular waypoint in space, and at a particular time) into engine

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assemblies (RGAs), with each RGA containing one pitch and one yaw gyro. These provided an output proportional to angular rates about the pitch and yaw axes to the orbiter computers and guidance, navigation and control system during first-stage ascent flight in conjunction with the orbiter roll rate

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decomposed the hydrazine into hot, high-pressure gas; a two-stage turbine converted this into mechanical power, driving a gearbox. The waste gas, now cooler and at low pressure, was passed back over the gas generator housing to cool it before being dumped overboard. The gearbox drove the fuel pump,

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collapsed. The train was carrying eight SRB segments intended for STS-120 and STS-122. Four segments dropped approximately 10 feet (3.0 m). Four other segments along with a car carrying aft exit cones (nozzles), not yet on the trestle, remained on solid ground. The segments that fell from the

1224:

One of the areas was the attachment ring where the SRBs are connected to the external tank. Areas of distress were noted in some of the fasteners where the ring attaches to the SRB motor case. This situation was attributed to the high loads encountered during water impact. To correct the situation

1198:

and allowing them to extrude further into the joint and erode as hot exhaust gases passed through during past launches. Additionally, the O-rings were not resilient at low temperatures like those of the January 1986 morning of the accident (36 °F; 2.2 °C). A cold-compromised joint in the

1092:

After the drogue chute has stabilized the SRB in a tail-first attitude, the frustum is separated from the forward skirt by a pyrotechnic charge triggered by the low-altitude baroswitch at a nominal altitude of 5,500 ft (1,700 m) about 243 seconds after SRB separation. The frustum is then

1373:

Disaster in 1986, the FWC boosters had the "double tang" joint design (necessary to keep the boosters properly in alignment during the "twang" movement when the SSMEs are ignited prior to liftoff), but used the two O-ring seals. With the closure of SLC-6, the FWC boosters were scrapped by ATK and

1005:

The antenna couplers provide the proper impedance for radio frequency and ground support equipment commands. The command receivers are tuned to RSS command frequencies and provide the input signal to the distributors when an RSS command is sent. The command decoders use a code plug to prevent any

888:

The GPC launch sequence also controls certain critical main propulsion system valves and monitors the engine ready indications from the SSMEs. The MPS start commands are issued by the onboard computers at T−6.6 seconds (staggered start engine three, engine two, engine one all approximately within

706:

The ascent thrust vector control portion of the flight control system directed the thrust of the three shuttle main engines and the two SRB nozzles to control shuttle attitude and trajectory during lift-off and ascent. Commands from the guidance system were transmitted to the Ascent Thrust Vector

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on that SRB by a switching valve that allowed the hydraulic power to be distributed from either HPU to both actuators if necessary. Each HPU served as the primary hydraulic source for one servoactuator, and a secondary source for the other servoactuator. Each HPU possessed the capacity to provide

1638:

rocket engine used on the Delta IV EELV system. Initially, NASA switched over to a system using the 5-segment boosters and a cluster of 5 RS-68s (which resulted in a widening of the Ares V core unit), then NASA reconfigured the vehicle with 6 RS-68B engines, with the boosters themselves becoming

441:

Each booster was attached to the external tank at the SRB's aft frame by two lateral sway braces and a diagonal attachment. The forward end of each SRB was attached to the external tank at the forward end of the SRB's forward skirt. On the launch pad, each booster also was attached to the mobile

1123:

Formerly, the main chutes were released from the SRB at impact using a parachute release nut ordnance system (residual loads in the main chutes would deploy the parachute attach fittings with floats tethered to each fitting). The current design keeps the main chutes attached during water impact

921:

Timing sequence referencing in ignition is critical for a successful liftoff and ascent flight. The explosive hold-down bolts relieve (through the launch support pedestals and pad structure) the asymmetric vehicle dynamic loads caused by the SSME ignition and thrust buildup, and applied thrust

370:

ever flown and the first of such large rockets designed for reuse. Each is 149.16 ft (45.46 m) long and 12.17 ft (3.71 m) in diameter. Each SRB weighed approximately 1,300,000 lb (590 t) at launch. The two SRBs constituted about 69% of the total lift-off mass. The

896:

The fire 2 commands cause the redundant NSDs to fire through a thin barrier seal down a flame tunnel. This ignites a pyro. booster charge, which is retained in the safe and arm device behind a perforated plate. The booster charge ignites the propellant in the igniter initiator; and combustion

892:

Normal thrust buildup to the required 90% thrust level will result in the SSMEs being commanded to the lift off position at T−3 seconds as well as the fire 1 command being issued to arm the SRBs. At T−3 seconds, the vehicle base bending load modes are allowed to initialize (referred to as the

714:

The four servovalves operating each actuator provided a force-summed majority-voting arrangement to position the power spool. With four identical commands to the four servovalves, the actuator force-sum action prevented, instantaneously, a single erroneous input affecting power ram motion. If

1271:

Components of the SRBs were transported from Utah to the Kennedy Space Center in Florida via rail over twelve days covering 2,000 miles (3,200 km) and eight states. Each segment and its custom built rail car weighed approximately 300,000 pounds (140,000 kg). Cars carrying SRBs were

583:

bus power to each SRB via SRB buses labeled A, B and C. Orbiter main DC buses A, B and C supplied main DC bus power to corresponding SRB buses A, B and C. In addition, orbiter main DC bus C supplied backup power to SRB buses A and B, and orbiter bus B supplied backup power to SRB bus C. This

1272:

separated by empty cars to distribute the load over bridges and trestles, particularly the bridge over the Indian River, the last bridge on the train's journey. Following recovery, spent segments were loaded onto those same train cars and returned to Utah for refurbishment and refueling.

1061:. Nose cap separation occurs at a nominal altitude of 15,704 ft (4,787 m), about 218 seconds after SRB separation. The 11.5 ft (3.5 m) diameter conical ribbon pilot parachute provides the force to pull lanyards attached to cut knives, which cut the loop securing the 914: 1020:

Electrical power from the RSS battery in each SRB is routed to RSS system A. The recovery battery in each SRB is used to power RSS system B as well as the recovery system in the SRB. The SRB RSS is powered down during the separation sequence, and the SRB recovery system is powered up.

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to be "a faulty design unacceptably sensitive to a number of factors" of the SRB joints compounded by unusually cold weather the morning of the flight. The field joint design was flawed, with flexure of the joints during launch compromising the seal of the large rubber

739:

The SRB RGA rates passed through the orbiter flight aft multiplexers/demultiplexers to the orbiter GPCs. The RGA rates were then mid-value-selected in redundancy management to provide SRB pitch and yaw rates to the user software. The RGAs were designed for 20 missions.

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When the APU speed reached 100%, the APU primary control valve closed, and the APU speed was controlled by the APU controller electronics. If the primary control valve logic failed to the open state, the secondary control valve assumed control of the APU at 112% speed.

449:

The boosters were composed of seven individually manufactured steel segments. These were assembled in pairs by the manufacturer and then shipped to Kennedy Space Center by rail for final assembly. The segments were fixed together using circumferential tang, clevis, and

710:

Each SRB servoactuator consisted of four independent, two-stage servovalves that received signals from the drivers. Each servovalve controlled one power spool in each actuator, which positioned an actuator ram and the nozzle to control the direction of thrust.

904:

on each SRB is initiated; the two T-0 umbilicals (one on each side of the spacecraft) are retracted; the onboard master timing unit, event timer and mission event timers are started; the three SSMEs are at 100%; and the ground launch sequence is terminated.

880:

in each SRB. A PIC single-channel capacitor discharge device controls the firing of each pyrotechnic device. Three signals must be present simultaneously for the PIC to generate the pyro firing output. These signals, arm, fire 1 and fire 2, originate in the

1434:

rocket was planned to use five-segment SRBs; in September 2009 a five-segment Space Shuttle SRB (DM-1) was static fired on the ground in ATK's desert testing area in Utah. Additional tests (DM-2 and DM-3) were carried out in Aug 2010 and Sept 2011.

1220:

During the subsequent downtime, detailed structural analyses were performed on critical structural elements of the SRB. Analyses were primarily focused on areas where anomalies had been noted during postflight inspection of recovered hardware.

994:

The shuttle vehicle had two RSS, one in each SRB. Both were capable of receiving two command messages (arm and fire) transmitted from the ground station. The RSS was used only when the shuttle vehicle violates a launch trajectory red line.

1009:

The NSDs provide the spark to ignite the CDF, which in turn ignites the LSC for booster destruction. The safe and arm device provides mechanical isolation between the NSDs and the CDF before launch and during the SRB separation sequence.

1321:

The ASRM would be slightly wider (the booster's diameter would be increased from 146 inches to 150 inches) and have 200,000 pounds of extra propellant, and have produced additional thrust in order to increase shuttle payload by about

1042:

on ocean impact. A command is sent from the orbiter to the SRB just before separation to apply battery power to the recovery logic network. A second, simultaneous command arms the three nose cap thrusters (for deploying the pilot and

1013:

The first message, called arm, allows the onboard logic to enable a destruct and illuminates a light on the flight deck display and control panel at the commander and pilot station. The second message transmitted is the fire command.

1913: 1215:

The right SRB shows an anomalous plume at T+58.788 seconds recorded via NASA chase-camera E-207. O-Ring sealant failure resulting in visible SRB thrust gas impinging against, penetrating, and then detonating the LH2 reservoir of the

889:

0.25 of a second), and the sequence monitors the thrust buildup of each engine. All three SSMEs must reach the required 90% thrust within three seconds; otherwise, an orderly shutdown is commanded and safing functions are initiated.

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products of this propellant ignite the solid rocket motor initiator, which fires down the entire vertical length of the solid rocket motor igniting the solid rocket motor propellant along its entire surface area instantaneously.

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EELV technologies. The 5-segment SRB, which would have required little change to the current shuttle infrastructure, would have allowed the space shuttle to carry an additional 20,000 lb (9,100 kg) of payload in an

1289:

trestle were recovered and returned to Utah for inspection. After analyses of the forces put on the remaining four segments that had not fallen were found to be well within tolerances, those segments continued on to Florida.

619:

between the rock and tilt actuators. The two systems operated from T minus 28 seconds until SRB separation from the orbiter and external tank. The two independent hydraulic systems were connected to the nozzle rock and tilt

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NASA, but their field joints, albeit modified to incorporate the current three O-ring seals and joint heaters, were later (after STS-51L) incorporated into the field joints on the SRBs used until the last flight in 2011.

722:

for position feedback to the thrust vector control system. Within each servoactuator ram was a splashdown load relief assembly to cushion the nozzle at water splashdown and prevent damage to the nozzle flexible bearing.

571:. They provided the ignition to the hold-down NSDs. The launch processing system monitored the SRB hold-down PICs for low voltage during the last 16 seconds before launch. PIC low voltage would initiate a launch hold. 1101:. Because the parachutes provide for a nozzle-first impact, air is trapped in the empty (burned out) motor casing, causing the booster to float with the forward end approximately 30 feet (9 m) out of the water. 437:

applied to the entire rocket assembly, which included the rocket motor as well as the recovery parachutes, electronic instrumentation, separation rockets, range safety destruct system, and thrust vector control.

1442:(SLS) was designated to use five-segment boosters. The first test of a SRB for SLS (QM-1) was completed in early 2015, a second test (QM-2) was performed in mid 2016 at Orbital ATK's Promontory, Utah facility. 1096:

Water impact occurs about 279 seconds after SRB separation at a nominal velocity of 76 feet per second (23 m/s). The water impact range is approximately 130 nmi (240 km) off the eastern coast of

359:) downrange, after which the two SRBs were recovered. The SRBs helped take the Space Shuttle to an altitude of 28 miles (45 km) and a speed of 3,094 mph (4,979 km/h) along with the main engines. 1207:

disintegrated. Both SRBs survived the accident. Shortly before the disaster, engineers representing Thiokol recommended scrubbing the launch due to the cold temperatures, but were overridden by NASA managers.

1341:

The ASRM program was cancelled in 1993 after robotic assembly systems and computers were on-site and approximately 2 billion dollars spent, in favor of continued use of the SRB after design flaw corrections.

629:

The HPUs and their fuel systems were isolated from each other. Each fuel supply module (tank) contained 22 lb (10.0 kg) of hydrazine. The fuel tank was pressurized with gaseous nitrogen at 400

241:. With a combined mass of about 1,180 t (1,160 long tons; 1,300 short tons), they comprised over half the mass of the Shuttle stack at liftoff. The motor segments of the SRBs were manufactured by 560:

contained sand. The hold-down stud was 28 in (710 mm) long and 3.5 in (89 mm) in diameter. The frangible nut was captured in a blast container mounted on the aft skirt of the SRB.

828:

perforation in each of the aft segments and aft closure. This configuration provided high thrust at ignition and then reduced the thrust by approximately a third 50 seconds after lift-off to avoid

814:

of 242 seconds (2.37 km/s) at sea level or 268 seconds (2.63 km/s) in a vacuum. Upon ignition, the motor burned the fuel at a nominal chamber pressure of 906.8 psi (6.252 MPa).

363:

or post-liftoff abort procedures be contemplated. In addition, failure of an individual SRB's thrust output or ability to adhere to the designed performance profile was probably not survivable.

1580:

NASA initially planned to reuse the four-segment SRB design and infrastructure in several Ares rockets, which would have propelled the Orion spacecraft into orbit. In 2005, NASA announced the

1615:. In place of the standard SRB nosecone, the Ares I would have a tapered interstage assembly connecting the booster proper with the second stage, an attitude control system derived from the 1369:(FWC) were designed to be more lightweight than the steel cases used on Kennedy Space Center-launched SRBs. Unlike the regular SRBs, which had the flawed field joint design that led to the 1389:

in 2003, NASA investigated the replacement of the current 4-segment SRBs with either a 5-segment SRB design or replacing them altogether with liquid-fueled "flyback" boosters using either

817:

Aluminum was chosen as a propellant due to high volumetric energy density, and its resilience to accidental ignition. Aluminum has a specific energy density of about 31.0 MJ/kg .

637:), which provided the force to expel (positive expulsion) the fuel from the tank to the fuel distribution line, maintaining a positive fuel supply to the APU throughout its operation. 6038: 1006:

command signal other than the proper command signal from getting into the distributors. The distributors contain the logic to supply valid destruct commands to the RSS pyrotechnics.

885:(GPCs) and are transmitted to the MECs. The MECs reformat them to 28 volt DC signals for the PICs. The arm signal charges the PIC capacitor to 40 volts DC (minimum of 20 volts DC). 5395: 1599:

The Ares I design updated in 2006 featured one 5-segment SRB (originally developed for the Shuttle, but never used) as a first stage; the second stage was powered by an uprated

1560:

Over time several proposals to reuse the SRB design were presented – however, as of 2016 none of these proposals progressed to regular flights before being cancelled. Until the

253:. The prime contractor for most other components of the SRBs, as well as for the integration of all the components and retrieval of the spent SRBs, was USBI, a subsidiary of 2202: 5419: 599:

There were two self-contained, independent Hydraulic Power Units (HPUs) on each SRB, used to actuate the thrust vector control (TVC) system. Each HPU consisted of an

2750: 1674:

proposal for a new, Shuttle-Derived Launch Vehicle, unlike the Ares I and Ares V boosters, uses a pair of classic 4-segment SRBs with the SSMEs used on the Shuttle.

5441: 5104: 1017:

The SRB distributors in the SRBs are cross-strapped together. Thus, if one SRB received an arm or destruct signal, the signal would also be sent to the other SRB.

3293: 6721: 2581: 1232:

These two modifications added approximately 450 lb (200 kg) to the weight of each SRB. The result is called a Redesigned Solid Rocket Motor (RSRM).

1634:

standard-production SSMEs and a pair of 5-segment boosters identical to those proposed for the Shuttle, while later plans redesigned the boosters around the

663:

The hydraulic pump speed was 3,600 rpm and supplied hydraulic pressure of 3,050 ± 50 psi (21.03 ± 0.34 MPa). A high pressure

319:

and up to an altitude of about 150,000 ft (28 mi; 46 km). While on the pad, the two SRBs carried the entire weight of the external tank and

5860: 1513: 496: 203:'s thrust at liftoff and for the first two minutes of ascent. After burnout, they were jettisoned and parachuted into the Atlantic Ocean where they were 2629: 3045: 1229:

between the hold-down post and skin of the skirt. A redesign was implemented to add reinforcement brackets and fittings in the aft ring of the skirt.

6568: 5099: 2044: 2865: 2788: 1937: 876:

The solid rocket motor ignition commands are sent by the orbiter computers through the Master Events Controllers (MECs) to the safe and arm device

893:"twang", movement of approximately 25.5 in (650 mm) measured at the tip of the external tank, with movement towards the external tank). 5552: 3005: 2438: 974:

and subsequent self-destruction of the SRB via RSS radio command; the first and only time ever activated in a NASA-controlled human space-launch.

6633: 6558: 6045: 1958: 1423:, NASA shelved the five-segment SRB for the Shuttle Program. One five-segment engineering test motor, ETM-03, was fired on October 23, 2003. 5389: 5302: 1552:

The Ares I-X prototype launches from LC-39B, 15:30 UTC, October 28, 2009 – this was as of October 2022 the sole flight of a launch vehicle

1054: 626:

The HPU controller electronics were located in the SRB aft integrated electronic assemblies (IEAs) on the aft external tank attach rings.

6339: 6315: 5341: 2890: 1662:

The Constellation program, including Ares I and Ares V, was canceled in October 2010 by the passage of the 2010 NASA authorization bill.

544:

Each solid rocket booster had four hold-down posts that fit into corresponding support posts on the mobile launcher platform. Hold-down

6261: 5674: 3406: 1974: 1691: 563:

The solid rocket motor ignition commands were issued by the orbiter's computers through the master events controllers to the hold-down

6349: 6268: 3650: 1871: 806: 171: 2464: 6344: 5094: 5089: 5084: 4708: 3922: 3502: 299:. Recovery also allowed post-flight examination of the boosters, identification of anomalies, and incremental design improvements. 6653: 6386: 3492: 3286: 3281: 3153: 3077: 3050:

Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

2308: 2775:"Most powerful Space Shuttle Solid Rocket Motor ever tested proves it can be pushed close to edge, yet still perform flawlessly" 2030: 218:(SLS) SRBs, adapted from the shuttle, surpassed it as the most powerful solid rocket motors ever flown, after the launch of the 5530: 5525: 3846: 3761: 3276: 1459: 1088:. On this occasion, the boosters landed several miles apart, but overnight winds and currents drifted them to the same location 6231: 5669: 5401: 3888: 3450: 3308: 2014: 339:) at sea level, increasing shortly after liftoff to about 3,300,000 lbf (15 MN). They were ignited after the three 3477: 584:

electrical power distribution arrangement allowed all SRB buses to remain powered in the event one orbiter main bus failed.

6628: 6435: 5958: 3953: 1451: 2912: 2866:"March Field Air Museum In Riverside, CA - SRB - Solid Rocket Booster, United Space Alliance & ATK Thiokol Propulsion" 2757: 2482: 2148: 6736: 6211: 6185: 6141: 3867: 3298: 2097: 1416:

The five-segment SRB would use a wider nozzle throat to keep within the pressure limit of the existing segment casings.

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modes, and, by using a so-called dog-leg maneuver, fly south-to-north polar orbiting flights from Kennedy Space Center.

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lb, so that it could carry modules and construction components to the ISS. They were expected to be safer than the post-

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An RSS consists of two antenna couplers, command receivers/decoders, a dual distributor, a safe and arm device with two

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That final redesign would have made the Ares V booster taller and more powerful than the now-retired Saturn V/INT-20,

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Crew Exploration Vehicle into low-Earth orbit and later to the Moon. The SRB-derived Crew Launch Vehicle (CLV), named

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Jenkins, Dennis R. "Space Shuttle: History of the National Space Transportation System – The First 100 Flights"

6731: 6428: 6418: 6116: 3328: 3260: 3102: 1581: 1517: 500: 5359: 3900: 1592:, was planned to feature a single modified 4-segment SRB for its first stage; a single liquid-fueled modified 1002:(NSD), two confined detonating fuse manifolds (CDF), seven CDF assemblies and one linear-shaped charge (LSC). 6621: 5461: 5456: 3739: 3607: 3030: 749: 5249: 2647: 2283: 736:

gyros until SRB separation. At SRB separation, a switchover was made from the SRB RGAs to the orbiter RGAs.

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On May 2, 2007, a freight train carrying segments of the space shuttle's solid rocket boosters derailed in

33:

Space Shuttle Solid Rocket Booster (SRB) pair, as used for the initial United States Space Shuttle program.

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provided overpressure protection to the hydraulic system and relieved at 3,750 psi (25.9 MPa).

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In the APU, a fuel pump boosted the hydrazine pressure and fed it to a gas generator. The gas generator

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held the SRB and launcher platform posts together. Each stud had a nut at each end, the top one being a

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At T−0, the two SRBs are ignited, under command of the four onboard computers; separation of the four

291:). Over 5,000 parts were refurbished for reuse after each flight. The final set of SRBs that launched 6478: 6396: 6391: 6065: 5520: 5478: 4538: 4533: 3809: 3586: 3509: 3386: 3370: 3365: 3360: 3355: 3245: 1623: 1593: 1403: 1355: 1203:

1.92 at 46,000 feet (14 km), thrusted off-axis by the right SRB as well as the tank's collapse,

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The APU 100-percent speed corresponded to 72,000 rpm, 110% to 79,200 rpm, and 112% to 80,640 rpm.

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Cary Rutland Collection, The University of Alabama in Huntsville Archives and Special Collections

1506: 1310:

at a new facility, designed by subcontractor, RUST International, on the location of a cancelled

1074: 1057:, which triggers the pyrotechnic nose cap thrusters. This ejects the nose cap, which deploys the 999: 877: 553: 489: 192: 2214: 1887:

Comparison of the Saturn V, Space Shuttle, Ares I, Ares V, Ares IV, SLS Block I and SLS Block II

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system, and larger, heavier parachutes to lower the stage into the Atlantic Ocean for recovery.

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originated with a system failure of one of its SRBs. The cause of the accident was found by the

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5.5-segment boosters, with an additional half-segment to provide additional thrust at liftoff.

1463: 1383: 1069: 208: 4600: 3035: 2898: 6698: 6611: 6601: 6543: 6413: 6408: 6249: 5914: 5876: 5845: 5754: 5653: 5635: 5535: 5244: 5194: 5114: 5074: 5069: 5064: 4938: 4713: 4663: 4601: 4049: 3853: 3840: 3751: 3168: 3123: 3086: 2468: 2367: 1651: 1427: 630: 564: 392: 320: 258: 214:

The Space Shuttle SRBs were the most powerful solid rocket motors to ever launch humans. The

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bn. Morton Thiokol would build the nozzles. The first test flight was expected around 1994.

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ring detonator (for main parachute deployment), and the main parachute disconnect ordnance.

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Out of 270 SRBs launched over the Shuttle program, all but four were recovered – those from

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Primary elements of each booster were the motor (including case, propellant, igniter, and

8: 6528: 6494: 6025: 6006: 5595: 5383: 5224: 5044: 4744: 4614: 4299: 3939: 3880: 3695: 3602: 3467: 1898: 1892: 1769: 1741: 1600: 1565: 1439: 1350:

In order to provide the necessary performance to launch polar-orbiting shuttles from the

1281: 1245: 459: 406:), structure, separation systems, operational flight instrumentation, recovery avionics, 250: 215: 204: 46: 3250: 2009:. Government Printing Office: National Aeronautics and Space Administration. p. 5. 343:

main engines' thrust level was verified. Seventy-five seconds after SRB separation, SRB

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Origins of the shuttle SRB, engineering study for NASA 1971, volume 2, technical report

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Bn contract was to be for 12 motors, with an option for another 88 at maybe another $ 1

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are often used interchangeably, in technical use they have specific meanings. The term

254: 246: 231: 51: 3024: 2751:"A Review of ETM-03 (A Five Segment Shuttle RSRM Configuration) Ballistic Performance" 1211: 6289: 6173: 6133: 6093: 6013: 5973: 5840: 5830: 5578: 3581: 2345: 2335: 2010: 1655: 769: 196: 2560: 2417: 1954: 869:

Initiator Controller (PIC) low voltage is indicated and there are no holds from the

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Wings in Orbit: Scientific and Engineering Legacies of the Space Shuttle, 1971-2010

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occurred at an altitude of approximately 220,000 ft (42 mi; 67 km);

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Sections of the SRB filled with propellant being connected for the STS-134 mision

611: 266: 2175:"Reusable Solid Rocket Motor—Accomplishments, Lessons, and a Culture of Success" 6658: 6538: 6295: 5981: 5779: 5769: 5615: 5610: 5468: 4543: 4523: 4518: 4513: 4137: 3974: 3942: 3930: 3640: 2552: 2536: 2518: 2504: 2490: 1604: 1285: 1085: 966: 653: 620: 580: 238: 2995:

Origins of the shuttle SRB, engineering study for NASA 1971, volume 1, summary

2607: 2261: 865:(SSMEs) are at or above 90% of rated thrust, no SSME fail and/or SRB ignition 399:). The inert weight of each SRB was approximately 200,000 pounds (91 t). 6715: 6686: 6668: 6563: 6553: 6485: 6330: 5963: 5694: 5473: 4548: 4332: 4248: 4174: 3993: 3931: 3817: 3771: 3097: 1166: 917:

Early ignition and lift-off view of main-engines and SRB (ground-camera view)

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Electrical power distribution in each SRB consisted of orbiter-supplied main

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servoactuators, to move the nozzle up/down and side-to-side. This provided

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The two reusable SRBs provided the main thrust to lift the shuttle off the

281: 2913:"Space shuttle solid rocket booster arrives for display at Arizona museum" 1553: 5495: 5371: 4638: 4605: 1683: 1467: 1297: 1261: 1058: 866: 821: 372: 5264:* Different versions of the engine use different propellant combinations 5054: 3055: 3049: 1104: 938: 6226: 5928: 5921: 5436: 4693: 3052:", 32 photos, 3 measured drawings, 8 photo caption pages 2284:"The Solid Rocket Booster Auxiliary Power Unit - Meeting the Challenge" 2000: 1643: 1520: in this section. Unsourced material may be challenged and removed. 1359: 1256:

The prime contractor for the manufacture of the SRB motor segments was

882: 789: 719: 503: in this section. Unsourced material may be challenged and removed. 451: 316: 2697: 2309:"Shuttle Boosters to sport APU fuel pump safety redesign from STS-134" 1572:

prototype in 2009 was the furthest any of these proposals progressed.

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to help control the vehicle in all three axes (roll, pitch, and yaw).

351:

were then deployed and impact occurred in the ocean approximately 122

307: 6643: 6616: 6464: 6376: 6236: 6205: 6198: 5995: 5893: 5647: 5029: 5024: 4673: 3660: 2237:"Space Shuttle Solid Rocket Booster - Frangible Nut Crossover System" 1612: 1561: 1548: 1053:

The recovery sequence begins with the operation of the high-altitude

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mission in 2022. Each Space Shuttle SRB provided a maximum 14.7

219: 1495: 1170:

Camera captures grey smoke being emitted from the right-hand SRB on

556:(NSDs), which were ignited at solid rocket motor ignition commands. 478: 5134: 5129: 5049: 5034: 5019: 4723: 4427: 3530: 3255: 3237: 3229: 2730:" NASA Johnson Space Center Oral History Project, January 26, 2004. 1608: 1569: 1394: 1178: 793: 781: 777: 670:

The APUs/HPUs and hydraulic systems were reusable for 20 missions.

384: 380: 277: 28: 2291:

Structures and Propulsion Laboratory, Marshall Space Flight Centre

1306:

SRBs with a new Advanced Solid Rocket Motor (ASRM) to be built by

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Two Space Launch System SRBs launching Artemis 1 mission to space

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mission being recovered and transported to Cape Canaveral by the

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curing agent (1.96%). This propellant is commonly referred to as

295:

included parts that had flown on 59 previous missions, including

292: 242: 42: 913: 824:

perforation in the forward motor segment and a double-truncated-

442:

launcher platform at the aft skirt by four holddown studs, with

16:

Solid propellant rocket used to launch the Space Shuttle orbiter

6192: 6123: 5620: 5485: 5184: 4918: 4913: 4882: 4851: 4846: 4841: 4836: 4831: 4821: 4810: 4804: 4799: 4794: 4789: 4733: 4683: 4558: 4502: 4495: 4479: 4463: 4457: 4452: 4447: 4442: 4437: 4372: 4366: 4356: 4232: 4225: 4064: 4015: 3683: 3673: 2262:"Solid Rocket Booster Integrated Electronic Assemblies Support" 2003:; Lane, Helen; Chapline, Gail; Lulla, Kamlesh (April 7, 2011). 1671: 1627: 1589: 1438:

After the Constellation Program was cancelled in 2011, the new

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and transmitted the weight load through their structure to the

262: 2968:"Space Launch System: How to launch NASA's new monster rocket" 2031:"Liftoff! NASA's Artemis I Mega Rocket Launches Orion to Moon" 1659:

almost-identical flight trajectory from launch to splashdown.

1084:, floating in the Atlantic Ocean about 150 miles northeast of 6216: 5989: 5953: 5948: 5739: 5234: 5174: 5003: 4998: 4993: 4988: 4949: 4943: 4887: 4876: 4866: 4816: 4668: 4658: 4610: 4578: 4563: 4553: 4412: 4407: 4402: 4350: 4344: 4218: 4212: 4207: 4187: 4152: 4147: 4124: 4101: 4069: 4033: 4026: 4020: 4010: 4005: 3700: 3138: 1650:

rockets, and would have allowed the Ares V to place both the

1635: 1351: 844: 833: 801: 545: 340: 296: 273: 2519:"Report of the Presidential Commission on the Space Shuttle 2483:"Report of the Presidential Commission on the Space Shuttle 5311: 4871: 4861: 4653: 4489: 4328: 4243: 4142: 4131: 4090: 4084: 4079: 4044: 3038:

Files of Cary Rutland, deputy of the SRB program after the

785: 607: 552:. The top nut contained two explosive charges initiated by 388: 1450:

Space Shuttle Solid Rocket Boosters are on display at the

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just after booster ignition at the start of the ill-fated

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weighed approximately 1,100,000 lb (500 t) (see

5164: 5159: 5154: 5144: 2816:"NASA successfully tests five-segment solid rocket motor" 2385: 1474:. A partial filament-wound booster case is on display at 1260:(formerly Morton Thiokol Inc.) Wasatch Division based in 1292: 195:

to be used for primary propulsion on a vehicle used for

5280: 2789:"NASA and ATK Successfully Test Ares First Stage Motor" 2418:"Space Shuttle Propulsion Master's Forum Presentation" 2149:"STS-134 IFA Review: SRBs and RSRMs Perform Admirably" 1302:

In 1988–1989, NASA was planning on replacing the post-

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Advanced Solid Rocket Motor (ASRM) Project (1988–1993)

1999: 1993: 433:

applied to the propellant, case, igniter and nozzle.

311:

Solid Rocket Booster (SRB) separation during STS-117.

2960: 2939:"Five-segment Solid Rocket Motor Development Status" 2698:"Advanced Solid Rocket Motor Status (NSIAD-93-258R)" 2124:"Booster stacking finished for final shuttle flight" 1485: 1033:

Splashdown of the right hand SRB from the launch of

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movements of the SSMEs and the SRB exhaust nozzles.

810:(APCP). This mixture gave the solid rocket motors a 4324: 2704:. Government Accountability Office. August 13, 1993 1314:

nuclear power plant, at Yellow Creek, Mississippi (

2692: 2690: 2630:"Solid Rocket Boosters and Post-Launch Processing" 2361: 2359: 1690:launch vehicle for ISS resupply flights under the 230:) thrust, roughly double the most powerful single- 2334:. Upper Saddle River, NJ: Pearson/Prentice Hall. 257:. This contract was subsequently transitioned to 6713: 2511: 2487:Accident, Chapter IV: The Cause of the Accident" 1938:Studied Space Shuttle variations and derivatives 772:mixture in each solid rocket motor consisted of 574: 2687: 2356: 1073:The solid rocket boosters, jettisoned from the 3493:Shuttle Avionics Integration Laboratory (SAIL) 6722:Historic American Engineering Record in Texas 5296: 3916: 3071: 1959:National Aeronautics and Space Administration 1841:3,280,000 lbf (14,600 kN) sea level 141:3,300,000 lbf (15,000 kN) sea level 2733: 2672: 2670: 2668: 2666: 2664: 2648:"RSRM Segment Train Derailment and Recovery" 1897:The first versions (Blocks 1 and 1B) of the 1711: 1607:, which had been used in the upper stage of 1402:-inclination orbit, eliminate the dangerous 1235: 800:(binder, also acts as fuel, 12.04%), and an 458:(originally two, changed to three after the 2748: 2529: 614:manifold assembly. The APUs were fueled by 5675:Commercial Orbital Transportation Services 5303: 5289: 3923: 3909: 3078: 3064: 2329: 2323: 2067: 2065: 2045:"Space Launch System Solid Rocket Booster" 1722: 6569:Hubble Space Telescope anniversary images 3651:Shuttle-Derived Heavy Lift Launch Vehicle 3085: 2661: 2302: 2300: 1902: 1536:Learn how and when to remove this message 807:ammonium perchlorate composite propellant 652:Each HPU on an SRB was connected to both 519:Learn how and when to remove this message 2970:. NASASpaceFlight.com. February 20, 2012 2332:Manufacturing engineering and technology 2167: 1912: 1882: 1547: 1239: 1210: 1165: 1103: 1068: 1028: 965: 937: 912: 843: 759: 683: 673: 594: 530: 306: 6654:NASA International Space Apps Challenge 2936: 2813: 2062: 1708:segments from the original SRB design. 1630:. Early designs of the Ares V utilized 1460:United States Space & Rocket Center 1377: 1345: 1024: 942:On-board camera-view of SRB separation. 726: 6714: 5442:Administrator and Deputy Administrator 3847:Rendezvous: A Space Shuttle Simulation 3031:Liberty Star and Freedom Star bio page 2365: 2306: 2297: 1972: 1966: 1152: 961: 908: 199:. A pair of these provided 85% of the 6232:Transiting Exoplanet Survey Satellite 5284: 3904: 3889:When We Left Earth: The NASA Missions 3059: 2609:NASA Railroad Keeps Boosters on Track 2467:. NASA. April 7, 2002. Archived from 2215:"Space Shuttle Solid Rocket Boosters" 1596:would have powered the second stage. 1293:Upgrade projects not put into service 391:), and the total propellant for each 276:(due to a parachute malfunction) and 6694: 3954:Comparison of orbital rocket engines 3046:Historic American Engineering Record 2895:A Field Guide to American Spacecraft 2781: 2720: 2582:"Orbiter Manufacturing and Assembly" 2523:Accident, Chapter III: The Accident" 1518:adding citations to reliable sources 1489: 1458:in Hancock County, Mississippi, the 1452:Kennedy Space Center Visitor Complex 718:Each actuator ram was equipped with 501:adding citations to reliable sources 472: 3868:Space Shuttle: A Journey into Space 2307:Bergin, Chris (February 28, 2010). 1901:(SLS) are planned to use a pair of 1466:on March ARB in California, and at 465:in 1986) and heat-resistant putty. 13: 5348:National Aeronautics and Space Act 2814:Kanigan, Dan (September 9, 2011). 2645: 2281: 1957:from websites or documents of the 1908: 1903:five-segment Solid Rocket Boosters 1626:Cargo Launch Vehicle (CaLV) named 587:The nominal operating voltage was 539: 185:Space Shuttle Solid Rocket Booster 14: 6748: 6302:Nancy Grace Roman Space Telescope 5856:Commercial Lunar Payload Services 2999:NASA Technical Report 19720015135 2993:NASA Technical Report 19720007149 2986: 2678:"NASA Picks Lockheed and Aerojet" 2537:"The history of the flawed joint" 2073:"Space Launchers - Space Shuttle" 1568:(SLS), a sole test-flight of the 1486:Current, future and proposed uses 1248:in preparation for the launch of 1162:Space Shuttle Challenger disaster 883:orbiter general-purpose computers 6693: 6682: 6681: 6597:Apollo 15 postal covers incident 6355:Space Flight Operations Facility 5541:Operations and Checkout Building 4965: 2749:McMillin, J. E.; Furfaro, J. A. 1953: This article incorporates 1948: 1494: 1382:Prior to the destruction of the 848:SRB sea-level thrust, data from 743: 477: 27: 5816:Lunar Precursor Robotic Program 3613:Spartan Packet Radio Experiment 3025:Solid Rocket Booster Separation 2930: 2905: 2883: 2858: 2833: 2807: 2767: 2742: 2639: 2622: 2600: 2574: 2505:"Space Shuttle Challenger Case" 2497: 2475: 2457: 2431: 2410: 2275: 2254: 2229: 2207: 2196: 1973:Dunbar, Brian (March 5, 2006). 1622:Also introduced in 2005, was a 1505:needs additional citations for 878:NASA standard detonators (NSDs) 488:needs additional citations for 396: 249:, which was later purchased by 3882:Orbiter Space Flight Simulator 3261:Multi-Purpose Logistics Module 2141: 2116: 2090: 2037: 2023: 1808:1,400,000 lb (640 t) 1800:1,600,000 lb (730 t) 1582:Shuttle-Derived Launch Vehicle 1244:Two Space Shuttle SRBs on the 446:that were severed at liftoff. 108:1,100,000 lb (500 t) 100:1,300,000 lb (590 t) 1: 4750:RD-0202 to 0206, 0208 to 0213 3837:(2020 documentary miniseries) 3608:Inflatable Antenna Experiment 2946:NASA Technical Reports Server 2937:Priskos, Alex (May 7, 2012). 2655:NASA Technical Reports Server 2366:Wilson, Jim (March 5, 2006). 1943: 1677: 933: 780:, 69.6% by weight), atomized 755: 750:high-strength low-alloy steel 575:Electrical power distribution 468: 327:. Each booster had a liftoff 207:, examined, refurbished, and 84:149.16 ft (45.46 m) 6634:Space program on U.S. stamps 6559:Gemini and Apollo medallions 6509:Solar System Family Portrait 6285:Joint Polar Satellite System 6154:Lunar Reconnaissance Orbiter 5408:Vision for Space Exploration 5378:Space Exploration Initiative 3834:Challenger: The Final Flight 3735:Space Shuttle design process 3577:Shuttle Ejection Escape Suit 3572:Extravehicular Mobility Unit 1851:269 seconds (2.64 km/s) 1745:United Space Boosters Inc., 1462:in Huntsville, Alabama, the 1108:Solid rocket booster of the 748:Made out of 2-cm-thick D6AC 151:242 seconds (2.37 km/s) 50:United Space Boosters Inc., 7: 6629:U.S. Astronaut Hall of Fame 6586:We choose to go to the Moon 6549:Apollo 11 goodwill messages 6107:International Space Station 6087:Mars Reconnaissance Orbiter 5826:Great Observatories program 5670:International Space Station 5648:Roscosmos State Corporation 5565:Science Mission Directorate 5511:Manned Space Flight Network 3757:International Space Station 3541:Journalist in Space Project 3488:Orbiter Processing Facility 3048:(HAER) No. TX-116-K, " 2917:Pima Air & Space Museum 2330:Kalpakjian, Serope (2006). 1921: 1816:200,000 lb (91 t) 1792:12.17 ft (3.71 m) 1476:Pima Air & Space Museum 1445: 1400:International Space Station 1275: 855: 839: 603:(APU), fuel supply module, 454:fastening, and sealed with 331:of approximately 2,800,000 302: 116:200,000 lb (91 t) 92:12.17 ft (3.71 m) 10: 6753: 6737:NASA space launch vehicles 6446:NASA cameras on spacecraft 6257:James Webb Space Telescope 6169:Solar Dynamics Observatory 5390:U.S. National Space Policy 3875:Space Shuttle Mission 2007 3415:Approach and Landing Tests 3144:Orbital Maneuvering System 2553:10.1109/MSPEC.1987.6448025 2033:. NASA. November 16, 2022. 1890: 1316:Yellow Creek Nuclear Plant 1312:Tennessee Valley Authority 1185:The loss of Space Shuttle 1159: 863:Space Shuttle Main Engines 677: 610:, hydraulic reservoir and 567:controllers (PICs) on the 366:The SRBs were the largest 6677: 6577: 6454: 6369: 6314: 6277: 6076: 5886: 5873: 5803: 5717: 5707: 5662: 5588: 5577: 5521:Vehicle Assembly Building 5429: 5328: 5318: 5260: 4974: 4963: 4903: 4593: 4315: 4163: 3982: 3973: 3962: 3949: 3810:Columbia: The Tragic Loss 3727: 3709: 3631: 3595: 3587:Advanced Crew Escape Suit 3564: 3523: 3510:Shuttle Training Aircraft 3460: 3423: 3379: 3371:Shuttle Training Aircraft 3366:Shuttle Mission Simulator 3361:Rendezvous pitch maneuver 3319: 3269: 3251:Remote Controlled Orbiter 3246:Extended Duration Orbiter 3222: 3167: 3154:Thermal protection system 3116: 3093: 1877: 1863: 1855: 1845: 1837: 1829: 1824: 1820: 1812: 1804: 1796: 1788: 1780: 1775: 1765: 1757: 1733: 1721: 1712:Space Launch System (SLS) 1694:; it would have featured 1665: 1603:engine, derived from the 1594:Space Shuttle Main Engine 1430:, the first stage of the 1419:After the destruction of 1356:Vandenberg Air Force Base 1236:Construction and delivery 956:booster separation motors 731:Each SRB contained three 688:Static test firing, 1978. 177: 163: 155: 145: 137: 129: 124: 120: 112: 104: 96: 88: 80: 75: 65: 57: 38: 26: 6592:Apollo 8 Genesis reading 6516:The Day the Earth Smiled 5851:Solar Terrestrial Probes 5310: 3618:Shuttle pallet satellite 3546:Teacher in Space Project 3498:Shuttle Carrier Aircraft 3478:Mobile Launcher Platform 3304:Shuttle Landing Facility 3159:Booster separation motor 1080:following the launch of 1000:NASA standard detonators 871:Launch Processing System 834:maximum dynamic pressure 569:mobile launcher platform 554:NASA standard detonators 325:mobile launcher platform 235:liquid-propellant rocket 6649:Other primates in space 6361:Deep Space Atomic Clock 6181:Mars Science Laboratory 5969:Spitzer Space Telescope 5558:Lunar Sample Laboratory 5501:Launch Services Program 4795:RD-250 to 252, 261, 262 3826:The Challenger Disaster 3149:Reaction control system 3006:"Solid Rocket Boosters" 2439:"Solid Rocket Boosters" 2393:"Solid Rocket Boosters" 2368:"Solid Rocket Boosters" 1975:"Solid Rocket Boosters" 1784:177 ft (54 m) 1776:General characteristics 1717:Space Launch System SRB 1575: 1330:SRBs. The initial $ 1.2 410:, deceleration system, 368:solid-propellant motors 282:terminated by the range 237:engine ever flown, the 193:solid-propellant rocket 76:General characteristics 6664:National Astronaut Day 6607:The Astronaut Monument 6429:Space Shuttle missions 6129:Mars Exploration Rover 6112:Hubble Space Telescope 6021:Kepler space telescope 5821:Earth Observing System 5795:Mars Exploration Rover 5506:Mercury Control Center 3294:Space Launch Complex 6 3008:. NASA. Archived from 2791:. NASA. Archived from 2584:. NASA. Archived from 2489:. NASA. Archived from 2441:. NASA. Archived from 1977:. NASA. Archived from 1955:public domain material 1918: 1917:Labeled diagram of SRB 1888: 1562:2022 first test flight 1557: 1464:March Field Air Museum 1253: 1217: 1182: 1120: 1089: 1038: 975: 943: 918: 852: 822:11-pointed star-shaped 820:The propellant had an 765: 689: 536: 312: 6732:Space Shuttle program 6612:Lunar sample displays 6602:Space Mirror Memorial 6544:Voyager Golden Record 6436:United States rockets 5628: (with the 5536:Launch Control Center 5271:are under development 4659:YF-20, 21, 22, 24, 25 4438:RD-107, 108, 117, 118 3854:Space Shuttle Project 3841:Space Shuttle America 3752:Payload Assist Module 3409:(engine test article) 3087:Space Shuttle program 2311:. NASASpaceflight.com 1916: 1886: 1652:Earth Departure Stage 1551: 1428:Constellation Program 1405:Return-to-Launch Site 1243: 1214: 1169: 1107: 1072: 1032: 969: 941: 916: 847: 763: 687: 678:Further information: 674:Thrust vector control 595:Hydraulic power units 565:pyrotechnic initiator 534: 310: 261:, a joint venture of 259:United Space Alliance 5630:Soviet space program 5548:Johnson Space Center 5516:Kennedy Space Center 5479:spinoff technologies 3747:Inertial Upper Stage 3623:Wake Shield Facility 3603:Freestar experiments 3129:Solid Rocket Booster 3012:on February 16, 2012 2471:on February 3, 2002. 2184:. September 27, 2011 1928:Solid rocket booster 1584:slated to carry the 1514:improve this article 1456:Stennis Space Center 1378:Five-segment booster 1346:Filament-wound cases 1147:Kennedy Space Center 1025:Descent and recovery 774:ammonium perchlorate 727:Rate gyro assemblies 601:auxiliary power unit 497:improve this article 435:Solid rocket booster 427:solid rocket booster 414:control system, and 377:ammonium perchlorate 6639:Apollo 17 Moon mice 6495:Pillars of Creation 6402:Space Shuttle crews 5880:(human and robotic) 5874:Individual featured 5457:Ranks and positions 4760:RD-0216, 0217, 0235 4423:RD-0107, 0108, 0110 3696:Space Launch System 3468:Crawler-transporter 3309:Abort landing sites 2153:NASASpaceFlight.com 2102:NASASpaceFlight.com 1899:Space Launch System 1893:Space Launch System 1770:Space Launch System 1747:Pratt & Whitney 1718: 1566:Space Launch System 1440:Space Launch System 1409:Trans-Oceanic Abort 1282:Myrtlewood, Alabama 1246:crawler-transporter 1129:NASA recovery ships 962:Range safety system 909:Lift-off and ascent 832:the vehicle during 255:Pratt & Whitney 216:Space Launch System 52:Pratt & Whitney 23: 6727:Solid-fuel rockets 6441:NASA cancellations 6336:Deep Space Network 6326:Near Earth Network 5811:Living With a Star 5785:Project Prometheus 5765:Planetary Observer 3821:(2010 documentary) 3813:(2004 documentary) 3805:(1994 documentary) 3789:(1985 documentary) 3786:The Dream Is Alive 3781:(1982 documentary) 3483:NASA recovery ship 3473:Mate-Demate Device 2901:on March 12, 2010. 2870:www.marchfield.org 2845:www.orbitalatk.com 2676:Leary, Warren E., 2547:(2): 39–44. 1987. 2128:Spaceflightnow.com 1919: 1889: 1716: 1558: 1258:ATK Launch Systems 1254: 1218: 1183: 1121: 1090: 1039: 976: 944: 919: 853: 766: 690: 537: 431:solid rocket motor 423:solid rocket motor 393:solid rocket motor 313: 247:Brigham City, Utah 232:combustion chamber 21: 6709: 6708: 6622:stolen or missing 6419:uncrewed missions 6397:Apollo astronauts 6392:Gemini astronauts 6310: 6309: 6094:2001 Mars Odyssey 5869: 5868: 5745:Mars Surveyor '98 5703: 5702: 5646: (with 5579:Human spaceflight 5573: 5572: 5531:Launch Complex 48 5526:Launch Complex 39 5278: 5277: 5220:Space Shuttle SRB 4961: 4960: 4899: 4898: 4589: 4588: 4311: 4310: 3898: 3897: 3582:Launch Entry Suit 3410: 3402: 3392: 3337: 3277:Launch Complex 39 3242: 3234: 2891:"Launch Vehicles" 2795:on March 25, 2010 2763:on July 19, 2011. 2588:on April 25, 2021 2016:978-0-16-086847-4 1881: 1880: 1758:Country of origin 1656:Altair spacecraft 1546: 1545: 1538: 1470:'s facility near 1191:Rogers Commission 1127:Specially fitted 770:rocket propellant 692:Each SRB had two 529: 528: 521: 418:destruct system. 397:§ Propellant 197:human spaceflight 181: 180: 58:Country of origin 22:Space Shuttle SRB 6744: 6697: 6696: 6685: 6684: 6523:Fallen Astronaut 6164:Van Allen Probes 5884: 5883: 5790:Mars Exploration 5715: 5714: 5586: 5585: 5354:Space Task Group 5326: 5325: 5305: 5298: 5291: 5282: 5281: 4969: 4968: 4805:RD-263, 268, 273 4736:along other LREs 4598: 4597: 4458:RD-191, 151, 181 4322: 4321: 3980: 3979: 3971: 3970: 3925: 3918: 3911: 3902: 3901: 3802:Destiny in Space 3408: 3400: 3390: 3346:Mission timeline 3331: 3240: 3232: 3103:List of missions 3080: 3073: 3066: 3057: 3056: 3021: 3019: 3017: 2980: 2979: 2977: 2975: 2964: 2958: 2957: 2955: 2953: 2943: 2934: 2928: 2927: 2925: 2923: 2909: 2903: 2902: 2897:. 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Archived from 2755: 2746: 2740: 2737: 2731: 2724: 2718: 2717: 2711: 2709: 2694: 2685: 2684:, April 22, 1989 2674: 2659: 2658: 2652: 2646:Taylor, Robert. 2643: 2637: 2636: 2634: 2626: 2620: 2619: 2618: 2616: 2604: 2598: 2597: 2595: 2593: 2578: 2572: 2571: 2569: 2567: 2533: 2527: 2526: 2515: 2509: 2508: 2501: 2495: 2494: 2493:on May 11, 2013. 2479: 2473: 2472: 2461: 2455: 2454: 2452: 2450: 2445:on July 25, 2010 2435: 2429: 2428: 2422: 2414: 2408: 2407: 2405: 2403: 2389: 2383: 2382: 2380: 2378: 2363: 2354: 2353: 2327: 2321: 2320: 2318: 2316: 2304: 2295: 2294: 2288: 2282:Hughes, Robert. 2279: 2273: 2272: 2270: 2268: 2258: 2252: 2251: 2249: 2247: 2241: 2233: 2227: 2226: 2224: 2222: 2211: 2205: 2200: 2194: 2193: 2191: 2189: 2179: 2171: 2165: 2164: 2162: 2160: 2145: 2139: 2138: 2136: 2134: 2120: 2114: 2113: 2111: 2109: 2094: 2088: 2087: 2085: 2083: 2069: 2060: 2059: 2057: 2055: 2049: 2041: 2035: 2034: 2027: 2021: 2020: 1997: 1991: 1990: 1988: 1986: 1981:on April 6, 2013 1970: 1952: 1951: 1847:Specific impulse 1752:Northrop Grumman 1726: 1719: 1715: 1707: 1706: 1702: 1699: 1541: 1534: 1530: 1527: 1521: 1498: 1490: 1472:Promontory, Utah 1454:in Florida, the 1337: 1333: 1325: 1202: 1044:drogue parachute 812:specific impulse 701:thrust vectoring 680:thrust vectoring 590: 524: 517: 513: 510: 504: 481: 473: 421:While the terms 226:(3,300,000 191:) was the first 147:Specific impulse 31: 24: 20: 6752: 6751: 6747: 6746: 6745: 6743: 6742: 6741: 6712: 6711: 6710: 6705: 6673: 6573: 6564:Mission patches 6539:Pioneer plaques 6502:Mystic Mountain 6479:Family Portrait 6472:The Blue Marble 6456: 6450: 6424:Apollo missions 6365: 6317: 6306: 6273: 6078: 6072: 5909:Mercury-Atlas 6 5879: 5875: 5865: 5799: 5735:Mariner Mark II 5699: 5680:Commercial Crew 5658: 5581: 5569: 5553:Mission Control 5452:Astronaut Corps 5447:Chief Scientist 5425: 5330: 5314: 5309: 5279: 5274: 5256: 4977: 4970: 4966: 4957: 4895: 4785:RD-0255 to 0257 4780:RD-0243 to 0245 4642: 4631: 4627: 4621: 4609: 4585: 4326: 4317: 4307: 4171: 4165: 4159: 3990: 3984: 3965: 3958: 3945: 3943:launch vehicles 3929: 3899: 3894: 3740:studied designs 3723: 3705: 3666:Shuttle-Centaur 3627: 3591: 3560: 3536:Getaway Special 3519: 3456: 3419: 3375: 3321: 3315: 3265: 3218: 3163: 3112: 3089: 3084: 3015: 3013: 3004: 2989: 2984: 2983: 2973: 2971: 2966: 2965: 2961: 2951: 2949: 2941: 2935: 2931: 2921: 2919: 2911: 2910: 2906: 2889: 2888: 2884: 2874: 2872: 2864: 2863: 2859: 2849: 2847: 2839: 2838: 2834: 2824: 2822: 2812: 2808: 2798: 2796: 2787: 2786: 2782: 2773: 2772: 2768: 2760: 2753: 2747: 2743: 2738: 2734: 2725: 2721: 2707: 2705: 2696: 2695: 2688: 2675: 2662: 2650: 2644: 2640: 2632: 2628: 2627: 2623: 2614: 2612: 2606: 2605: 2601: 2591: 2589: 2580: 2579: 2575: 2565: 2563: 2535: 2534: 2530: 2517: 2516: 2512: 2503: 2502: 2498: 2481: 2480: 2476: 2463: 2462: 2458: 2448: 2446: 2437: 2436: 2432: 2420: 2416: 2415: 2411: 2401: 2399: 2391: 2390: 2386: 2376: 2374: 2364: 2357: 2342: 2328: 2324: 2314: 2312: 2305: 2298: 2286: 2280: 2276: 2266: 2264: 2260: 2259: 2255: 2245: 2243: 2239: 2235: 2234: 2230: 2220: 2218: 2213: 2212: 2208: 2201: 2197: 2187: 2185: 2177: 2173: 2172: 2168: 2158: 2156: 2155:. June 27, 2011 2147: 2146: 2142: 2132: 2130: 2122: 2121: 2117: 2107: 2105: 2096: 2095: 2091: 2081: 2079: 2077:www.braeunig.us 2071: 2070: 2063: 2053: 2051: 2047: 2043: 2042: 2038: 2029: 2028: 2024: 2017: 1998: 1994: 1984: 1982: 1971: 1967: 1949: 1946: 1933:PEPCON disaster 1924: 1911: 1909:Labeled diagram 1895: 1805:Propellant mass 1750: 1744: 1729: 1714: 1704: 1700: 1697: 1695: 1680: 1668: 1617:Regulus missile 1578: 1542: 1531: 1525: 1522: 1511: 1499: 1488: 1480:Tucson, Arizona 1448: 1426:As part of the 1380: 1348: 1335: 1331: 1323: 1300: 1295: 1284:, after a rail 1278: 1238: 1200: 1164: 1158: 1059:pilot parachute 1027: 964: 954:There are four 936: 911: 902:explosive bolts 858: 842: 758: 746: 729: 682: 676: 612:hydraulic fluid 597: 588: 577: 542: 540:Hold-down posts 525: 514: 508: 505: 494: 482: 471: 383:) and atomized 305: 267:Lockheed Martin 105:Propellant mass 49: 34: 17: 12: 11: 5: 6750: 6740: 6739: 6734: 6729: 6724: 6707: 6706: 6704: 6703: 6691: 6678: 6675: 6674: 6672: 6671: 6666: 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, S-3D 4541: 4536: 4531: 4526: 4521: 4516: 4510:United States 4508: 4507: 4506: 4499: 4492: 4484: 4483: 4482: 4474: 4473: 4472: 4467: 4460: 4455: 4450: 4445: 4440: 4435: 4430: 4425: 4420: 4415: 4410: 4405: 4397: 4396: 4395: 4385: 4384: 4383: 4376: 4369: 4364: 4359: 4354: 4347: 4338: 4336: 4319: 4313: 4312: 4309: 4308: 4306: 4305: 4304: 4303: 4296: 4286: 4285: 4284: 4274: 4273: 4272: 4265: 4258: 4251: 4246: 4240:United States 4238: 4237: 4236: 4229: 4222: 4215: 4210: 4205: 4198: 4191: 4180: 4178: 4169: 4161: 4160: 4158: 4157: 4156: 4155: 4150: 4145: 4140: 4135: 4128: 4120:United States 4118: 4117: 4116: 4109: 4104: 4096: 4095: 4094: 4087: 4082: 4074: 4073: 4072: 4067: 4059: 4058: 4057: 4052: 4047: 4039: 4038: 4037: 4030: 4023: 4018: 4013: 4008: 3999: 3997: 3988: 3977: 3968: 3960: 3959: 3957: 3956: 3950: 3947: 3946: 3932:Rocket engines 3928: 3927: 3920: 3913: 3905: 3896: 3895: 3893: 3892: 3885: 3878: 3871: 3864: 3857: 3850: 3843: 3838: 3830: 3822: 3814: 3806: 3798: 3790: 3782: 3774: 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July 8, 2012 2089: 2061: 2036: 2022: 2015: 1992: 1964: 1963: 1945: 1942: 1941: 1940: 1935: 1930: 1923: 1920: 1910: 1907: 1891:Main article: 1879: 1878: 1875: 1874: 1865: 1861: 1860: 1857: 1853: 1852: 1849: 1843: 1842: 1839: 1838:Maximum thrust 1835: 1834: 1831: 1827: 1826: 1822: 1821: 1818: 1817: 1814: 1810: 1809: 1806: 1802: 1801: 1798: 1794: 1793: 1790: 1786: 1785: 1782: 1778: 1777: 1773: 1772: 1767: 1763: 1762: 1759: 1755: 1754: 1735: 1731: 1730: 1727: 1713: 1710: 1679: 1676: 1667: 1664: 1577: 1574: 1544: 1543: 1502: 1500: 1493: 1487: 1484: 1447: 1444: 1384:Space Shuttle 1379: 1376: 1365:filament-wound 1354:launch pad at 1347: 1344: 1299: 1296: 1294: 1291: 1277: 1274: 1237: 1234: 1172:Space Shuttle 1160:Main article: 1157: 1151: 1086:Cape Canaveral 1075:Space Shuttle 1026: 1023: 985:Space Shuttle 963: 960: 935: 932: 910: 907: 857: 854: 841: 838: 757: 754: 745: 742: 728: 725: 675: 672: 654:servoactuators 621:servoactuators 596: 593: 576: 573: 541: 538: 527: 526: 485: 483: 476: 470: 467: 444:frangible nuts 353:nautical miles 304: 301: 239:Rocketdyne F-1 179: 178: 175: 174: 165: 161: 160: 157: 153: 152: 149: 143: 142: 139: 138:Maximum thrust 135: 134: 131: 127: 126: 122: 121: 118: 117: 114: 110: 109: 106: 102: 101: 98: 94: 93: 90: 86: 85: 82: 78: 77: 73: 72: 67: 63: 62: 59: 55: 54: 40: 36: 35: 32: 15: 9: 6: 4: 3: 2: 6749: 6738: 6735: 6733: 6730: 6728: 6725: 6723: 6720: 6719: 6717: 6702: 6701: 6692: 6690: 6689: 6680: 6679: 6676: 6670: 6669:Nikon NASA F4 6667: 6665: 6662: 6660: 6657: 6655: 6652: 6650: 6647: 6645: 6642: 6640: 6637: 6635: 6632: 6630: 6627: 6623: 6620: 6618: 6615: 6614: 6613: 6610: 6608: 6605: 6603: 6600: 6598: 6595: 6593: 6590: 6587: 6583: 6582: 6580: 6576: 6570: 6567: 6565: 6562: 6560: 6557: 6555: 6554:NASA insignia 6552: 6550: 6547: 6545: 6542: 6540: 6537: 6535: 6534:Lunar plaques 6532: 6530: 6527: 6525: 6524: 6520: 6518: 6517: 6513: 6511: 6510: 6506: 6504: 6503: 6499: 6497: 6496: 6492: 6488: 6487: 6486:Pale Blue Dot 6483: 6482: 6481: 6480: 6476: 6474: 6473: 6469: 6467: 6466: 6462: 6461: 6459: 6453: 6447: 6444: 6442: 6439: 6437: 6434: 6430: 6427: 6425: 6422: 6420: 6417: 6416: 6415: 6414:NASA missions 6412: 6410: 6409:NASA aircraft 6407: 6403: 6400: 6398: 6395: 6393: 6390: 6388: 6385: 6383: 6380: 6379: 6378: 6375: 6374: 6372: 6368: 6362: 6359: 6356: 6353: 6351: 6348: 6346: 6343: 6341: 6337: 6334: 6332: 6331:Space Network 6329: 6327: 6324: 6323: 6321: 6319: 6313: 6303: 6300: 6298: 6297: 6293: 6291: 6288: 6286: 6283: 6282: 6280: 6276: 6270: 6267: 6263: 6260: 6259: 6258: 6255: 6251: 6248: 6246: 6244: 6240: 6239: 6238: 6235: 6233: 6230: 6228: 6225: 6223: 6220: 6218: 6215: 6213: 6210: 6208: 6207: 6203: 6201: 6200: 6196: 6194: 6191: 6187: 6184: 6183: 6182: 6179: 6177: 6176: 6172: 6170: 6167: 6165: 6162: 6160: 6157: 6155: 6152: 6150: 6147: 6143: 6140: 6139: 6138: 6136: 6132: 6130: 6127: 6125: 6122: 6120: 6119: 6115: 6113: 6110: 6108: 6105: 6103: 6102: 6098: 6096: 6095: 6091: 6089: 6088: 6084: 6083: 6081: 6075: 6067: 6064: 6063: 6062: 6060: 6056: 6054: 6053: 6049: 6047: 6044: 6040: 6037: 6035: 6032: 6031: 6030: 6028: 6024: 6022: 6019: 6017: 6016: 6012: 6010: 6009: 6005: 6003: 6000: 5998: 5997: 5993: 5991: 5988: 5986: 5984: 5980: 5978: 5976: 5972: 5970: 5967: 5965: 5964:Space Shuttle 5962: 5960: 5957: 5955: 5952: 5950: 5947: 5943: 5940: 5939: 5938: 5937: 5933: 5931: 5930: 5926: 5924: 5923: 5919: 5917: 5916: 5912: 5910: 5907: 5905: 5902: 5900: 5897: 5895: 5892: 5891: 5889: 5885: 5882: 5878: 5872: 5862: 5859: 5857: 5854: 5852: 5849: 5847: 5846:New Frontiers 5844: 5842: 5839: 5837: 5834: 5832: 5829: 5827: 5824: 5822: 5819: 5817: 5814: 5812: 5809: 5808: 5806: 5802: 5796: 5793: 5791: 5788: 5786: 5783: 5781: 5778: 5776: 5773: 5771: 5768: 5766: 5763: 5761: 5758: 5756: 5755:Lunar Orbiter 5753: 5751: 5748: 5746: 5743: 5741: 5738: 5736: 5733: 5731: 5728: 5726: 5723: 5722: 5720: 5716: 5713: 5710: 5706: 5696: 5695:Lunar Gateway 5693: 5691: 5688: 5686: 5683: 5681: 5678: 5676: 5673: 5671: 5668: 5667: 5665: 5661: 5655: 5654:Constellation 5652: 5649: 5645: 5644: 5639: 5637: 5636:Space Shuttle 5634: 5631: 5627: 5624: 5622: 5619: 5617: 5614: 5612: 5609: 5607: 5604: 5601: 5597: 5594: 5593: 5591: 5587: 5584: 5580: 5576: 5566: 5563: 5559: 5556: 5554: 5551: 5550: 5549: 5546: 5542: 5539: 5537: 5534: 5532: 5529: 5527: 5524: 5522: 5519: 5518: 5517: 5514: 5512: 5509: 5507: 5504: 5502: 5499: 5497: 5494: 5492: 5489: 5487: 5484: 5480: 5477: 5476: 5475: 5474:NASA research 5472: 5470: 5467: 5463: 5460: 5458: 5455: 5454: 5453: 5450: 5448: 5445: 5443: 5440: 5438: 5435: 5434: 5432: 5428: 5421: 5418: 5415: 5412: 5409: 5406: 5403: 5400: 5397: 5394: 5391: 5388: 5385: 5382: 5379: 5376: 5373: 5370: 5367: 5364: 5361: 5358: 5355: 5352: 5349: 5346: 5343: 5340: 5339: 5337: 5334: 5327: 5324: 5321: 5317: 5313: 5306: 5301: 5299: 5294: 5292: 5287: 5286: 5283: 5270: 5266: 5263: 5262: 5259: 5251: 5248: 5246: 5243: 5241: 5238: 5236: 5233: 5231: 5228: 5226: 5223: 5221: 5218: 5216: 5213: 5211: 5208: 5206: 5203: 5201: 5198: 5196: 5193: 5191: 5188: 5186: 5183: 5182: 5180: 5176: 5173: 5171: 5168: 5166: 5163: 5161: 5158: 5156: 5153: 5151: 5148: 5146: 5143: 5142: 5140: 5136: 5133: 5131: 5128: 5127: 5125: 5121: 5118: 5116: 5113: 5112: 5110: 5106: 5103: 5101: 5098: 5096: 5093: 5091: 5088: 5086: 5083: 5082: 5080: 5076: 5073: 5071: 5068: 5066: 5063: 5061: 5058: 5056: 5053: 5051: 5048: 5046: 5043: 5041: 5038: 5036: 5033: 5031: 5028: 5026: 5023: 5021: 5018: 5017: 5015: 5010: 5007: 5005: 5002: 5000: 4997: 4995: 4992: 4990: 4987: 4986: 4984: 4983: 4981: 4979: 4973: 4951: 4948: 4945: 4942: 4940: 4937: 4936: 4934: 4930: 4927: 4926: 4924: 4920: 4919:RD-211 to 214 4917: 4915: 4912: 4911: 4909: 4908: 4906: 4902: 4889: 4886: 4884: 4881: 4878: 4875: 4873: 4870: 4868: 4865: 4863: 4860: 4859: 4857: 4853: 4850: 4848: 4845: 4843: 4840: 4838: 4835: 4833: 4830: 4829: 4827: 4823: 4820: 4818: 4815: 4813: 4812: 4808: 4806: 4803: 4801: 4798: 4796: 4793: 4791: 4790:RD-215 to 219 4788: 4786: 4783: 4781: 4778: 4776: 4773: 4771: 4768: 4766: 4765:RD-0233, 0234 4763: 4761: 4758: 4756: 4755:RD-0207, 0214 4753: 4751: 4748: 4746: 4743: 4742: 4740: 4735: 4734:Paektusan LRE 4732: 4731: 4729: 4725: 4722: 4721: 4719: 4715: 4712: 4710: 4707: 4706: 4704: 4700: 4697: 4695: 4692: 4690: 4687: 4685: 4682: 4681: 4679: 4675: 4672: 4670: 4667: 4665: 4662: 4660: 4657: 4655: 4652: 4651: 4649: 4648: 4646: 4643: 4636: 4632: 4620: 4616: 4612: 4607: 4603: 4599: 4596: 4592: 4580: 4577: 4575: 4572: 4570: 4567: 4565: 4562: 4560: 4557: 4555: 4552: 4550: 4547: 4545: 4542: 4540: 4537: 4535: 4532: 4530: 4527: 4525: 4522: 4520: 4517: 4515: 4512: 4511: 4509: 4505: 4504: 4500: 4498: 4497: 4493: 4491: 4488: 4487: 4485: 4481: 4478: 4477: 4475: 4471: 4468: 4466: 4465: 4461: 4459: 4456: 4454: 4451: 4449: 4446: 4444: 4441: 4439: 4436: 4434: 4431: 4429: 4426: 4424: 4421: 4419: 4418:RD-0105, 0109 4416: 4414: 4411: 4409: 4406: 4404: 4401: 4400: 4398: 4394: 4393: 4389: 4388: 4386: 4382: 4381: 4377: 4375: 4374: 4370: 4368: 4365: 4363: 4360: 4358: 4355: 4353: 4352: 4348: 4346: 4343: 4342: 4340: 4339: 4337: 4334: 4330: 4323: 4320: 4314: 4302: 4301: 4297: 4295: 4294: 4290: 4289: 4287: 4283: 4282: 4278: 4277: 4275: 4271: 4270: 4266: 4264: 4263: 4259: 4257: 4256: 4252: 4250: 4247: 4245: 4242: 4241: 4239: 4235: 4234: 4230: 4228: 4227: 4223: 4221: 4220: 4216: 4214: 4211: 4209: 4206: 4204: 4203: 4199: 4197: 4196: 4192: 4190: 4189: 4185: 4184: 4182: 4181: 4179: 4176: 4172: 4162: 4154: 4151: 4149: 4146: 4144: 4141: 4139: 4136: 4134: 4133: 4129: 4127: 4126: 4122: 4121: 4119: 4115: 4114: 4110: 4108: 4105: 4103: 4102:KVD-1 (RD-56) 4100: 4099: 4097: 4093: 4092: 4088: 4086: 4083: 4081: 4078: 4077: 4075: 4071: 4068: 4066: 4063: 4062: 4060: 4056: 4053: 4051: 4048: 4046: 4043: 4042: 4040: 4036: 4035: 4031: 4029: 4028: 4024: 4022: 4019: 4017: 4014: 4012: 4009: 4007: 4004: 4003: 4001: 4000: 3998: 3995: 3991: 3981: 3978: 3976: 3972: 3969: 3967: 3961: 3955: 3952: 3951: 3948: 3944: 3941: 3937: 3933: 3926: 3921: 3919: 3914: 3912: 3907: 3906: 3903: 3891: 3890: 3886: 3884: 3883: 3879: 3877: 3876: 3872: 3870: 3869: 3865: 3863: 3862: 3858: 3856: 3855: 3851: 3849: 3848: 3844: 3842: 3839: 3836: 3835: 3831: 3828: 3827: 3823: 3820: 3819: 3815: 3812: 3811: 3807: 3804: 3803: 3799: 3796: 3795: 3791: 3788: 3787: 3783: 3780: 3779: 3778:Hail Columbia 3775: 3773: 3772:Conroy Virtus 3770: 3768: 3765: 3763: 3760: 3758: 3755: 3753: 3750: 3748: 3745: 3741: 3738: 3737: 3736: 3733: 3732: 3730: 3726: 3720: 3719: 3715: 3714: 3712: 3708: 3702: 3699: 3697: 3694: 3692: 3689: 3685: 3682: 3680: 3677: 3675: 3672: 3671: 3669: 3667: 3664: 3662: 3659: 3657: 3654: 3652: 3649: 3647: 3644: 3642: 3639: 3638: 3636: 3634: 3630: 3624: 3621: 3619: 3616: 3614: 3611: 3609: 3606: 3604: 3601: 3600: 3598: 3594: 3588: 3585: 3583: 3580: 3578: 3575: 3573: 3570: 3569: 3567: 3563: 3557: 3554: 3552: 3549: 3547: 3544: 3542: 3539: 3537: 3534: 3532: 3531:Deutschland-1 3529: 3528: 3526: 3522: 3516: 3513: 3511: 3508: 3504: 3501: 3500: 3499: 3496: 3494: 3491: 3489: 3486: 3484: 3481: 3479: 3476: 3474: 3471: 3469: 3466: 3465: 3463: 3459: 3452: 3448: 3446: 3442: 3439: 3435: 3433: 3429: 3428: 3426: 3422: 3416: 3413: 3411: 3405: 3403: 3399: 3395: 3393: 3389: 3385: 3384: 3382: 3378: 3372: 3369: 3367: 3364: 3362: 3359: 3357: 3354: 3352: 3349: 3347: 3344: 3342: 3339: 3335: 3330: 3327: 3326: 3324: 3318: 3310: 3307: 3305: 3302: 3301: 3300: 3299:Landing sites 3297: 3295: 3292: 3288: 3285: 3283: 3280: 3279: 3278: 3275: 3274: 3272: 3268: 3262: 3259: 3257: 3254: 3252: 3249: 3247: 3244: 3239: 3236: 3231: 3228: 3227: 3225: 3221: 3215: 3214: 3210: 3208: 3207: 3203: 3201: 3200: 3196: 3194: 3193: 3189: 3187: 3186: 3182: 3180: 3179: 3175: 3174: 3172: 3170: 3166: 3160: 3157: 3155: 3152: 3150: 3147: 3145: 3142: 3140: 3137: 3135: 3134:External tank 3132: 3130: 3127: 3125: 3122: 3121: 3119: 3115: 3109: 3108:List of crews 3106: 3104: 3101: 3099: 3098:Space Shuttle 3096: 3095: 3092: 3088: 3081: 3076: 3074: 3069: 3067: 3062: 3061: 3058: 3051: 3047: 3044: 3041: 3037: 3034: 3032: 3029: 3026: 3023: 3011: 3007: 3003: 3000: 2997: 2994: 2991: 2990: 2969: 2963: 2947: 2940: 2933: 2922:September 18, 2918: 2914: 2908: 2900: 2896: 2892: 2886: 2871: 2867: 2861: 2846: 2842: 2836: 2821: 2817: 2810: 2794: 2790: 2784: 2776: 2770: 2759: 2752: 2745: 2736: 2729: 2728:Jerry L. Ross 2723: 2716: 2703: 2699: 2693: 2691: 2683: 2679: 2673: 2671: 2669: 2667: 2665: 2656: 2649: 2642: 2631: 2625: 2611: 2610: 2603: 2587: 2583: 2577: 2562: 2558: 2554: 2550: 2546: 2542: 2541:IEEE Spectrum 2538: 2532: 2524: 2522: 2514: 2506: 2500: 2492: 2488: 2486: 2478: 2470: 2466: 2460: 2444: 2440: 2434: 2426: 2419: 2413: 2398: 2394: 2388: 2373: 2369: 2362: 2360: 2351: 2347: 2343: 2341:0-13-148965-8 2337: 2333: 2326: 2310: 2303: 2301: 2292: 2285: 2278: 2263: 2257: 2246:September 26, 2238: 2232: 2216: 2210: 2204: 2199: 2183: 2182:ntrs.nasa.gov 2176: 2170: 2154: 2150: 2144: 2129: 2125: 2119: 2103: 2099: 2093: 2078: 2074: 2068: 2066: 2046: 2040: 2032: 2026: 2018: 2012: 2008: 2007: 2002: 1996: 1980: 1976: 1969: 1965: 1962: 1960: 1956: 1939: 1936: 1934: 1931: 1929: 1926: 1925: 1915: 1906: 1904: 1900: 1894: 1885: 1876: 1873: 1869: 1866: 1862: 1858: 1854: 1850: 1848: 1844: 1840: 1836: 1832: 1828: 1825:5-segment SRB 1823: 1819: 1815: 1811: 1807: 1803: 1799: 1795: 1791: 1787: 1783: 1779: 1774: 1771: 1768: 1764: 1761:United States 1760: 1756: 1753: 1748: 1743: 1739: 1736: 1732: 1725: 1720: 1709: 1693: 1689: 1686:proposed the 1685: 1675: 1673: 1663: 1660: 1657: 1653: 1649: 1645: 1640: 1637: 1633: 1629: 1625: 1620: 1618: 1614: 1610: 1606: 1602: 1597: 1595: 1591: 1587: 1583: 1573: 1571: 1567: 1563: 1556:from the SRB. 1555: 1550: 1540: 1537: 1529: 1519: 1515: 1509: 1508: 1503:This section 1501: 1497: 1492: 1491: 1483: 1481: 1477: 1473: 1469: 1465: 1461: 1457: 1453: 1443: 1441: 1436: 1433: 1429: 1424: 1422: 1417: 1414: 1412: 1410: 1406: 1401: 1396: 1392: 1388: 1387: 1375: 1372: 1368: 1366: 1362:, SRBs using 1361: 1357: 1353: 1343: 1339: 1329: 1319: 1317: 1313: 1309: 1305: 1290: 1287: 1283: 1273: 1269: 1265: 1263: 1259: 1251: 1247: 1242: 1233: 1230: 1228: 1222: 1213: 1209: 1206: 1197: 1192: 1188: 1180: 1176: 1175: 1168: 1163: 1155: 1150: 1148: 1144: 1143: 1137: 1136: 1130: 1125: 1118: 1117: 1111: 1106: 1102: 1100: 1094: 1087: 1083: 1079: 1078: 1071: 1067: 1064: 1060: 1056: 1051: 1049: 1045: 1036: 1031: 1022: 1018: 1015: 1011: 1007: 1003: 1001: 996: 992: 990: 988: 981: 973: 968: 959: 957: 952: 948: 940: 931: 927: 925: 915: 906: 903: 898: 894: 890: 886: 884: 879: 874: 872: 868: 864: 851: 846: 837: 835: 831: 830:overstressing 827: 823: 818: 815: 813: 809: 808: 803: 799: 795: 791: 787: 783: 779: 775: 771: 762: 753: 751: 744:Segment cases 741: 737: 734: 724: 721: 716: 712: 708: 704: 702: 698: 695: 686: 681: 671: 668: 666: 661: 658: 655: 650: 646: 643: 642:catalytically 638: 636: 632: 627: 624: 622: 617: 613: 609: 606: 602: 592: 585: 582: 572: 570: 566: 561: 557: 555: 551: 550:frangible nut 547: 533: 523: 520: 512: 502: 498: 492: 491: 486:This section 484: 480: 475: 474: 466: 464: 462: 457: 453: 447: 445: 439: 436: 432: 428: 424: 419: 417: 413: 412:thrust vector 409: 405: 400: 398: 394: 390: 386: 382: 378: 374: 369: 364: 360: 358: 354: 350: 346: 342: 338: 334: 330: 326: 322: 318: 309: 300: 298: 294: 290: 288: 283: 279: 275: 270: 268: 264: 260: 256: 252: 248: 244: 240: 236: 233: 229: 225: 221: 217: 212: 210: 206: 202: 201:Space Shuttle 198: 194: 190: 186: 176: 173: 169: 166: 162: 158: 154: 150: 148: 144: 140: 136: 132: 128: 125:4-segment SRB 123: 119: 115: 111: 107: 103: 99: 95: 91: 87: 83: 79: 74: 71: 70:Space Shuttle 68: 64: 61:United States 60: 56: 53: 48: 44: 41: 37: 30: 25: 19: 6699: 6687: 6521: 6514: 6508: 6500: 6493: 6484: 6477: 6470: 6463: 6294: 6243:Perseverance 6242: 6204: 6197: 6174: 6134: 6117: 6101:New Horizons 6099: 6092: 6085: 6058: 6050: 6026: 6014: 6007: 5994: 5982: 5974: 5935: 5927: 5920: 5913: 5642: 5626:Apollo–Soyuz 5268: 5219: 4809: 4730:North Korea 4501: 4494: 4462: 4390: 4378: 4371: 4349: 4298: 4291: 4279: 4267: 4260: 4253: 4231: 4224: 4217: 4200: 4193: 4186: 4130: 4123: 4111: 4089: 4032: 4025: 3936:solid motors 3887: 3881: 3873: 3866: 3859: 3852: 3845: 3832: 3824: 3816: 3808: 3800: 3792: 3784: 3776: 3718:Independence 3717: 3444: 3431: 3397: 3387: 3322:and training 3212: 3205: 3198: 3191: 3184: 3177: 3128: 3039: 3014:. 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NASA. 1985:May 29, 1766:Used on 1738:Thiokol 1703:⁄ 1648:Energia 1564:of the 1554:derived 1391:Atlas V 1308:Aerojet 1286:trestle 1250:STS-134 1196:O-rings 1110:STS-131 1099:Florida 1082:STS-116 1048:frustum 1046:), the 1035:STS-124 873:(LPS). 850:STS-107 456:O-rings 321:orbiter 293:STS-135 243:Thiokol 66:Used on 43:Thiokol 6345:Madrid 6278:Future 6193:NuSTAR 6124:THEMIS 6046:RHESSI 5983:Spirit 5780:Viking 5770:Ranger 5621:Skylab 5616:Apollo 5611:Gemini 5469:Budget 5422:(2009) 5416:(2004) 5410:(2004) 5404:(2003) 5398:(2002) 5396:CFUSAI 5392:(1996) 5386:(1990) 5380:(1989) 5374:(1987) 5368:(1986) 5366:Rogers 5362:(1986) 5356:(1958) 5350:(1958) 5344:(1915) 5320:Policy 5185:AJ-60A 5150:KM-V2b 5141:Japan 5115:Salman 5081:India 5055:Topaze 5020:Mage 1 4985:China 4976:Solid 4883:TR-201 4847:RD-856 4842:RD-855 4832:RD-843 4822:S5.98M 4811:RD-270 4705:India 4699:Viking 4689:Astris 4684:Aestus 4674:YF-50D 4650:China 4559:RS-27A 4549:Merlin 4539:LR-105 4503:RD-810 4496:RD-801 4480:TEPREL 4476:Spain 4464:RD-193 4453:RD-180 4443:RD-120 4387:India 4380:Welkin 4373:YF-130 4367:YF-115 4362:YF-102 4357:YF-100 4341:China 4269:Aeon R 4262:Aeon 1 4249:Raptor 4233:YF-215 4226:YF-209 4219:TQ-15A 4183:China 4076:Japan 4065:CE-7.5 4061:India 4016:YF-75D 4002:China 3818:Hubble 3646:Magnum 3451:report 3438:report 2948:. 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