Category of engines.
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Associated Engines

15D151 NII125 solid rocket engine. Combined missile (RT20P) stage 1. Out of production. Launch thrust 588 kN. Designed for first stage of combined missile and SLBM; flight tested, no production. First flight 1967. More...

15D206 Yuzhnoye solid rocket engine. RT23 early models stage I. Out of Production. The casebound T9BK composite solid propellant charge had a star shape channel. The case was of organic fibrewound plastic material. More...

15D23 KBMash solid rocket engine. 892 kN. RT2 Stage 1. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/aluminium propellant. Chamber pressure 40 kgf/cm2. More...

15D23P TsKB7 solid rocket engine. 980 kN. RT2P Stage 1. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/ammonium butyl propellant. Chamber pressure 56 kgf/cm2. More...

15D24 TsKB7 solid rocket engine. 431 kN. RT2 Stage 2. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/aluminium propellant. Chamber pressure 40 kgf/cm2. Average thrust 33 tonnes. More...

15D24P TsKB7 solid rocket engine. 437.3 kN. RT2P Stage 2. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/ammonium butyl propellant. Chamber pressure 48 kgf/cm2. More...

15D25 KBMash solid rocket engine. 137 kN. RT2 Stage 3. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/aluminium propellant. More...

15D305 Yuzhnoye, Tsurilnikov solid rocket engine. RT23 stage I. Out of Production. Casebound OPAL composite solid propellant charge with a star shape channel. The case was of organic fibrewound plastic material. More...

15D339 Yuzhnoye. Tsurilnikov solid rocket engine. RT23 stage II. Out of Production. The casebound START composite solid propellant charge had a cylindricalconical umbrella shape channel. The case was of organic fibrewound plastic material. More...

15D94 TsKB7 solid rocket engine. 180.4 kN. RT2P Stage 3. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/ammonium butyl propellant. Chamber pressure 48 kgf/cm2. More...

2.5KS18000 Multiplesource solid rocket engine. 80 kN. Typical ideal dV=259 m/s; gravity and drag losses = 25 m/s. More...

200 inch solid segment x 4 Notional solid rocket engine. 11,120 kN. Study 1960. Isp=285s. 4 used as first stage of NASA allsolid Nova design. Extended highexpansion nozzles. More...

23KS20000 Bristol Aerospace solid rocket engine. 89 kN. Twofinned version. More...

26KS20000 Bristol Aerospace solid rocket engine. 75.7 kN. Fourfinned version. More...

280 inch solid Notional solid rocket engine. 46,208 kN. Study 1963. Operational date would have been February 1973 Isp=265s. Used on Nova MM 14B launch vehicle. More...

293P Kartukov solid rocket engine. P70 Ametist. Out of Production. More...

300 inch solid Notional solid rocket engine. 63,595 kN. Study 1963. Operational date would have been April 1973 Isp=263s. Used on Nova MM 14A launch vehicle. More...

325 in solid Notional solid rocket engine in GD Nova studies. 69,047 kN. Study 1963. Isp=263s. Recoverable motors; separation at 1,972 m/s at 53,000 m altitude; splashdown using retrorockets under 3 61 m diameter parachutes 610 km downrange. More...

Aerojet SRB Aerojet solid rocket engine. 1270 kN. In production. Isp=275s. First flight 2002. More...

AJ2601/3 Aerojet solid rocket engine. 10,105 kN. Design concept 1960's. Isp=275s. Used on Saturn INT05B launch vehicle. More...

AJ2602 Aerojet solid rocket engine. 17,695.3 kN. Study 1965. Isp=263s. 260 inch solid rocket booster half length. The version tested and also proposed for use as a first stage with the Saturn IVB. More...

AJ260X Aerojet solid rocket engine. 35,390.7 kN. Study 1967. Full length version of 260 inch motor tested in 1960's. Proposed for use in various Saturn and Nova configurations. Isp=263s. More...

AJ260X 1/3 Aerojet solid rocket engine. 11,143 kN. Design concept 1960's. Isp=263s. More...

Alcor Aerojet solid rocket engine. Originally developed for the Air Force as a third Stage for the Athena sounding rocket; in some applications known as Zebra. One of its main attractions was a very high mass fraction First flight 1960. More...

Algol 3 CSD solid rocket engine. 471.9 kN. Isp=284s. Used on Advanced Scout, Scout D, Scout F, Scout G. First flight 1972. More...

Algol 1 Aerojet solid rocket engine. 470.9 kN. Isp=236s. This rocket started as a Polaris test motor with a 40 inch diameter, which at the time was the largest solid motor ever tested. First flight 1960. More...

Algol 2 CSD solid rocket engine. 564.2 kN. Isp=255s. Used on Scout A, Scout B, Scout X3, Scout X4; proposed as strapon for Titan 3BAS2. First flight 1962. More...

Algol 3A CSD solid rocket engine. 464.7 kN. In Production. Isp=259s. More...

BB7 Bristol Aerospace solid rocket engine. 1 kN. More...

Black Arrow3 British solid rocket engine. 29.4 kN. Out of production. Isp=278s. Used on Black Arrow launch vehicle. First flight 1969. More...

Castor 120 Thiokol solid rocket engine. 1650 kN. Isp=280s. Motor similar in size to the Peacekeeper missile stage 1 motor; filled the gap between Castor 4A and the large segmented motors. First flight 1989. More...

Castor 4 Thiokol solid rocket engine. 407.2 kN. Series of motors used as Delta strapon boosters and as first and upper stages for lowcost allsolidpropellant designs. Isp=261s. First flight 1975. More...

Castor 4A Thiokol solid rocket engine. 478.3 kN. Out of production. Isp=266s. Castor 4A improved Delta performance by 11% by replacing the old fuel with HTPB propellant. Used in Delta 6900; Atlas IIAS; Castor 4A. First flight 1982. More...

Castor 4AXL Thiokol solid rocket engine. 599.8 kN. In production. Isp=269s. Strapon booster version, first tested May 1992. Its 30% performance increase would improve performance of Atlas and other vehicles. First flight 2001. More...

Castor 4B Thiokol solid rocket engine. 430.6 kN. Out of production. The Castor 4B, which incorporated thrust vector control in the series for the first time, was developed for ESA's Maxus (first flown in 1991). Isp=281s. First flight 1982. More...

Castor 4BXL Thiokol solid rocket engine. 429 kN. In Production. Isp=267s. ORBEX version, combined the 4XL motor with 4B's TVC system (6 degree). More...

CZ1D3 Fourth Academy solid rocket engine. Out of production. Motor for proposed CZ1D launch vehicle. Isp=291s. First flight 1995. More...

DFH2 AKM Fourth Academy solid rocket engine. 43.460 kN. DFH series apogee kick motor. Out of Production. Isp=287s. First flight 1984. First use in China of glass fibre wound cases, carbon/carbon nozzle throat insert material, contoured divergent nozzle. More...

EPKM Fourth Academy solid rocket engine. 189.994 kN. Isp=292s. Chinese kick stage for use on CZ2E for launch of Asiasat2 and Echostar1. Diameter increased to 1.7 m in comparison to basic 1.4 m diameter motor. Spin stabilised. First flight 1990. More...

FFAR Multiplesource American solid rocket engine. 3.6 kN. More...

FSW Retromotor Fourth Academy solid rocket engine. 40.660 kN. In Production. Isp=280s. Retrorocket designed for deorbit of FSW recoverable satellite. First flight 1975. More...

FW4D Thiokol solid rocket engine. 25 kN. Isp=287s. Kick stage motor for Delta E, Delta L. First flight 1965. More...

FW4S TEM640 Thiokol solid rocket engine. 27.4 kN. Isp=280s. Used on Advanced Scout, Scout B, Scout D, Scout F, Scout G. First flight 1965. More...

GCRC GCR solid rocket engine. 11.6 kN. Isp=230s. Used on Vanguard launch vehicle. First flight 1957. More...

GEM 40 Hercules solid rocket engine. 499.2 kN. Airignited versions have nozzle ratio of 16:1, specific impulse of 283.4 sec. Isp=274s. Used on Delta 7925 launch vehicle. First flight 1990. More...

GEM 46 Hercules solid rocket engine. 608.1 kN. Airignited versions have nozzle ratio of 24.8:1, specific impulse of 284 sec. Isp=274s. First flight 1998. More...

GEM 60 Hercules solid rocket engine. 851.5 kN. In production. Isp=275s. Used as strapon boosters for Delta 3 , Delta IV Medium. First flight 2002. More...

GF02 Fourth Academy solid rocket engine. 181 kN. CZ1 launch vehicle. Out of production. Isp=254s. First upper stage, zeroG, vacuumstart solid rocket motor developed in China. Inserted China's first satellite into orbit on 24 April 1970. More...

Goldfinch Royal Ordnance solid rocket engine. Out of production. Used on Skylark launch vehicle. More...

H13 Nissan solid rocket engine. 77 kN. Isp=291s. Used on H1 launch vehicle. First flight 1986. More...

H20 Nissan solid rocket engine. 1540 kN. Isp=273s. Used as strapon booster on H2, first stage on J1. First flight 1994. More...

H2/J11 Nissan solid rocket engine. 1556.6 kN. In Production. Used in J11. Isp=273s. More...

Hercules Hercules solid rocket engine. 15,565.8 kN. In development. Isp=286s. Planned replacement for shuttle solid rocket boosters after Challenger disaster. A billion dollars spent in development, but contract terminated. NASA decided to stay with Thiokol RSRM. More...

Iris BPD solid rocket engine. 29.4 kN. Out of production. Isp=291s. Used on CZ1M launch vehicle. More...

Kartukov Soyuz SAS Kartukov solid rocket engine. 785 kN. Soyuz 7KOK, Soyuz 7KTOK, Soyuz 7KT. Out of Production. Thrust 76 tf at cutout  80.1tf at ignition. More...

Kartukov LL Kartukov solid rocket engine. 14.7 kN. LL1, LL2, LL3. Developed 194648. More...

LK1 IAI solid rocket engine. 774 kN. In production. Isp=272s. Lengthened version of Shavit rocket motor. Lower stage used 9:1 nozzle. 23.6:1 nozzle for upper stage use inceased Isp to 279 seconds, First flight 1995. More...

M13 Nissan solid rocket engine. 1262.4 kN. Isp=263s. Used on Mu3S launch vehicle. First flight 1969. More...

M23J Nissan solid rocket engine. 524.8 kN. In development. Isp=282s. Used on J1 launch vehicle. First flight 1996. More...

M23Mu Nissan solid rocket engine. 524 kN. Isp=285s. Used on Mu3S launch vehicle. First flight 1969. More...

M3BMu Nissan solid rocket engine. 132.1 kN. Isp=294s. Used on Mu3S launch vehicle. First flight 1969. More...

M3BJ Nissan solid rocket engine. 132.1 kN. In development. Isp=294s. Used on J1 launch vehicle. First flight 1996. More...

M6 Hercules solid rocket engine. 365 kN. Taurus rocket motor originally developed for the Army Honest John tactical missile. In sounding rocket applications the interstage adapter was bolted to the front of the Taurus. More...

MV4 Nissan solid rocket engine. 52 kN. Isp=298s. Used on MV launch vehicle. First flight 1997. More...

M14 Nissan solid rocket engine. 3780.3 kN. Isp=276s. Used on MV launch vehicle. First flight 1997. More...

M24 Nissan solid rocket engine. 1245.3 kN. Isp=288s. Used on MV launch vehicle. First flight 1997. More...

M33204 Thiokol solid rocket engine. 286 kN. Isp=247s. Used as apogee kick motor on Delta D, LT Thor Agena D, Scout X1, Scout X2, Scout X3, Scout X4, TA Thor Agena B, TA Thor Agena D. First flight 1960. More...

M34 Nissan solid rocket engine. 294.2 kN. Isp=301s. Used on MV launch vehicle. First flight 1997. More...

M55/TX55/Tu122 Thiokol solid rocket engine. 792 kN. In production. Isp=262s. Proposed as strapon booster for Saturn IBC, Saturn INT14, Saturn INT15, Saturn INT19 variants. First flight 2000. More...

M56A1 Aerojet solid rocket engine. 228.5 kN. Out of Production. Used in Aries. Isp=297s. More...

M5E1 Hercules solid rocket engine. 195.6 kN. Nike booster motor. The interstage adapter was bolted to the front of the Nike in sounding rocket applications and lipfit into the second stage nozzle. More...

Mage 1 SEP solid rocket engine. 19.4 kN. Out of production. Orbital circularization motor. Isp=295s. First flight 1979. More...

Mage 2 SEP solid rocket engine. 45.5 kN. Orbital circularization motor for Advanced Scout, Ariane 2/3. Isp=293s. First flight 1984. More...

Mammouth French solid rocket engine. 190 kN. 1900 kg 'Plastolite' propellant. Empty mass estimated. Originally developed as the booster for the SSBT missile. Isp=180s. Used on Agate launch vehicle. First flight 1961. More...

Martlet 41 Bull solid rocket engine. 67.7 kN. Development ended 1966. Isp=300s. Used on Martlet 4 launch vehicle. More...

Martlet 43 Bull solid rocket engine. 5.390 kN. Development ended 1966. Isp=300s. Used on Martlet 4 launch vehicle. More...

Martlet 42 Bull solid rocket engine. 20.6 kN. Development ended 1966. Isp=300s. Used on Martlet 4 launch vehicle. More...

Melanie SEPR solid rocket engine. 11.1 kN. Out of production. 22 kg propellant. Empty mass estimated. Isp=227s. Used on Berenice launch vehicle. First flight 1962. More...

MIHT2 solid rocket engine. 490.3 kN. Start2. In production. Used in Start2. Estimated values. Isp=280s. First flight 1993. More...

MIHT3 MIHT solid rocket engine. 245.2 kN. Start3. In production. Used in Start3. Estimated values. Isp=280s. First flight 1993. More...

MIHT1 MIHT solid rocket engine. 980.6 kN. Start1. In production. Used in Start1. Estimated values. Isp=263s. First flight 1993. More...

MIHT4 MIHT solid rocket engine. 9.8 kN. Start4. In production. Used in Start4. Estimated values. Isp=295s. First flight 1993. More...

Mk7 Multiplesource solid rocket engine. 9.8 kN. More...

Nihka Bristol Aerospace solid rocket engine. 50.5 kN. Upper stages. Out of production. Isp=284s. Used on Black Brant 10 launch vehicle. First flight 1981. More...

NOTS3 NOTS solid rocket engine. 2.260 kN. Out of production. Isp=250s. Used on Caleb launch vehicle. First flight 1960. More...

NOTS1 NOTS solid rocket engine. 53.4 kN. Out of production. Isp=204s. Used on Caleb launch vehicle. First flight 1960. More...

NOTS 100A NOTS solid rocket engine. Used on Blue Scout Junior launch vehicle. First flight 1960. More...

NOTS4 NOTS solid rocket engine. 0.700 kN. Out of production. Isp=250s. Used on Caleb launch vehicle. First flight 1960. More...

Orion Aerojet solid rocket engine. 13 kN. Improved Orion motor was a biphase propellant system with thrust levels of 84.5 kN during the first four seconds of motor burn, trailing off to 13.3 kN at burnout at 25 seconds. More...

P230 SNPE solid rocket engine. 6472.3 kN. In production. Isp=286s. Used on Ariane 5 launch vehicle. First flight 1996. More...

P241 SEP solid rocket engine. 6470 kN. In development. Isp=275s. First flight 2002. More...

P4 SNPE solid rocket engine. 176.5 kN. Out of Production. Isp=273s. Used on Diamant B launch vehicle. First flight 1970. More...

P6 SNPE solid rocket engine for Diamant launcher. 29.4 kN. Out of production. Isp=211s. First flight 1965. More...

P80 FiatAvio solid rocket engine. 3040 kN. In production. Isp=279s. Vega's first stage, introduced advanced lowcost technologies that could be reused for future evolutions of Ariane5 boosters. More...

P9.5 SNPE solid rocket engine. 690 kN. Isp=263s. Strapon booster engine for Ariane 42P, Ariane 44LP, Ariane 44P. First flight 1988. More...

Peacekeeper 1 Thiokol solid rocket engine. 2204.5 kN. In Production. MX Stage 1. Used as first stage of Taurus launch vehicle for initial test. Isp=282s. More...

Pegasus3 Hercules solid rocket engine. 34.6 kN. Isp=287s. Upper stage engine for Pegasus, Pegasus XL, Taurus. First flight 1989. More...

Pegasus XL1 Hercules solid rocket engine. 589 kN. Isp=293s. Used on Pegasus XL launch vehicle. First flight 1994. More...

Pegasus XL2 Hercules solid rocket engine. 153.5 kN. Isp=290s. Used on Pegasus XL launch vehicle. First flight 1994. More...

Pegasus1 Hercules solid rocket engine. 484.9 kN. Isp=285s. Used on Pegasus, Taurus. First flight 1989. More...

Pegasus2 Hercules solid rocket engine. 118.2 kN. Isp=290s. Used on Pegasus, Taurus. First flight 1989. More...

Perigee Orbit Transfer Motor Fourth Academy solid rocket engine. 222.840 kN. In Production. Isp=280s. Basic perigee kick motor for CZ2E launch vehicle. Featured glass fibrewound case, HTPB propellant, 3D finocyl propellant grain, and carbon/carbon throat insert. First flight 1990. More...

PRD70 Kartukov solid rocket engine. 400/5V11 stage I. Out of Production. More...

PRD15 Kartukov solid rocket engine. 392 kN. Strela1 missile. Out of Production. More...

PRD19M Kartukov solid rocket engine. KSShch Shchuka. Out of Production. More...

PRD22 Kartukov solid rocket engine. 3.920 kN. SM30. Out of Production. More...

PRD36 Kartukov solid rocket engine. V600. Out of Production. More...

PRD52 Kartukov solid rocket engine. 784 kN. DBR1 Yastreb. Out of Production. Thrust 80 tf at ignition, 75 tf at cutout. More...

PRD61 Kartukov solid rocket engine. 036 Vikhr. Out of Production. More...

PSLV3 ISRO solid rocket engine. 328.7 kN. Isp=291s. Used on PSLV launch vehicle. First flight 1993. More...

PSLV1 ISRO solid rocket engine. 4860 kN. Isp=264s. Used on GSLV, PSLV. First flight 1993. More...

RD127 Yuzhnoye solid rocket engine. Maneuvering vehicle bangbang propulsion, consisted of 25 small solidpropellant motors, probably for homing vehicles or multiple warhead dispensing applications. More...

Redesigned SRM Thiokol solid rocket engine. 11,520 kN. In Production. Isp=268s. Replacement shuttle solid rocket booster with redesigned field joints to prevent failure that caused the Challenger disaster. More...

Rook Royal Ordnance solid rocket engine. 300 kN. Out of production. Fastburning version of Raven. Rook was fired 70 times altogether, in 65 flights and 16 different vehicle designs. More...

RSA31 South Africansolid rocket engine. 500 kN. Out of production. Built in both Israel and South Africa for RSA3 and Shavit. Source: Missile exhibit and placards, AF Museum, South Africa. Isp=273s. First flight 1988. More...

RSA32 South African solid rocket engine. 519 kN. In production. Built in both Israel and South Africa for RSA3 and Shavit. Source: Missile exhibit and placards, AF Museum, South Africa. Isp=284s. First flight 1988. More...

RSA33 South Africansolid rocket engine. 51 kN. In production. Israeli AUS51 rocket motor, built in both Israel and South Africa. Isp=292s. Upper stage engine for RSA3, RSA4, Shavit, Shavit 1. First flight 1988. More...

RSA41 South Africansolid rocket engine. 1520 kN. Development ended 1994. Isp=263s. Used on RSA4 launch vehicle. More...

RSA42 South African solid rocket engine. 676 kN. Development ended 1994. Isp=275s. Used on RSA4 launch vehicle. More...

RSRM Thiokol solid rocket engine. 11,520 kN. Study 1996. After the Challenger disaster the redesigned solid rocket motors had a slight reduction in performance due to reliability improvements. Isp=267s. More...

S30 IAE solid rocket engine. 20.490 kN. Development ended 1997. Isp=275s. More...

S40TM IAE solid rocket engine. 208.4 kN. Isp=272s. Used on VLS launch vehicle. First flight 1985. More...

S43 IAE solid rocket engine. 303 kN. Isp=265s. Used on VLS launch vehicle. First flight 1985. More...

S43TM IAE solid rocket engine. 321.7 kN. Isp=276s. Used on VLS launch vehicle. First flight 1985. More...

S44 IAE solid rocket engine. 33.2 kN. Isp=282s. Used on VLS launch vehicle. First flight 1985. More...

SB735 Nissan solid rocket engine. 327.8 kN. Isp=263s. Used on Mu3S launch vehicle. First flight 1969. More...

SEPR 740 SEPR solid rocket engine. 91.7 kN. Out of production. Isp=230s. Used on Berenice, Titus. First flight 1962. More...

Sergeant Multiplesource solid rocket engine. 6.660 kN. Out of Production. Used in Jupiter C, Juno 2. Isp=235s. First flight 1956. More...

SLV1 ISRO solid rocket engine. 502.6 kN. Isp=253s. Used on ASLV, PSLV, SLV. First flight 1979. More...

SLV2 ISRO solid rocket engine. 267 kN. Isp=267s. Used on ASLV, SLV. First flight 1979. More...

SLV3 ISRO solid rocket engine. 90.7 kN. Isp=277s. Used on ASLV, SLV. First flight 1979. More...

SLV4 ISRO solid rocket engine. 26.8 kN. Isp=283s. Used on ASLV, SLV. First flight 1979. More...

Soleil NA803 Nord solid rocket engine. 147 kN. 2200 kg Isolane propellant. Stretched version of the NA802. Used on Topaze launch vehicle. First flight 1964. More...

Soleil French solid rocket engine. 120 kN. 1500 kg Isolane propellant. Used on Topaze launch vehicle. First flight 1962. More...

SpaB54 Fourth Academy solid rocket engine. In Production. Kick stage for orbital insertion of Iridium satellites Used on CZ2C/SD launch vehicle. First flight 1997. More...

SPB 7.35 SNPE solid rocket engine. 690 kN. Isp=263s. Strapon booster for Advanced Scout, Ariane 2/3. First flight 1984. More...

SPRD15 Kartukov solid rocket engine. 402 kN. S2 Strela2 missile, Sopka. Out of Production. Thrust 27 tf at cutout  41at ignition. More...

SPRD30 Kartukov solid rocket engine. 294 kN. P15 Termit. Out of Production. Thrust 28 tf at cutout  30 tf at ignition. More...

SPRD99 Kartukov solid rocket engine. 24.5 kN. MiG21PFM. Out of Production. More...

SPT100SEP Stechkin solid rocket engine. In Production. The French company SEP is developing this uprated version of the SPT100 in cooperation with OKB Fakel. Isp=2200s. More...

SPT70 Stechkin solid rocket engine. 0.098 kN. Yamal. In Production. Thrust variable 1 to 10 kgf Isp=2500s. More...

SPT50 Stechkin solid rocket engine. MeteorPriroda. In Production. More...

SPT100 Stechkin electric rocket engine. 0.196 kN. Meteor, Gals. In Production. 1.35 kW Hall thruster. Thrust variable 2 to 20 kgf. Marketed in USA by Space Systems/Loral and Fakel. Isp=2500s. More...

SPT200 Stechkin solid rocket engine. 0.780 kN. In Production. Thrust variable 8 to 80 kgf Isp=3000s. More...

SR19 Aerojet solid rocket engine. 267.7 kN. Minuteman 2 2nd stage. In production. Second stage of Minuteman 2. Surplus motors used as second stage of Minotaur launch vehicle and various SDI targets in 1980's. Isp=287s. First flight 2000. More...

SR105 Aerojet solid rocket engine. 12.75" Improved FFAR . More...

SR116 Aerojet solid rocket engine. Sidewinder AIM9J/P. More...

SR110 Aerodyne solid rocket engine. Super Loki PWN10, PWN11, PWN12. More...

SR11 Hercules solid rocket engine. LGM30 Retro Motor . Used on Minuteman 1 launch vehicle. More...

SR121 Naval Propellant Plant solid rocket engine. Streaker MQM107 Booster. More...

SR122 Rocketdyne solid rocket engine. Also designated WPU9/B1 (AGM130). More...

SR45 Atlantic Research solid rocket engine. Kitty PWN6, Rooster PWN7. More...

SR51 Thiokol solid rocket engine. Titan 2 LGM25C Retro Motor. More...

SR55 United Technology Center solid rocket engine. Titan 2 LGM25C Staging Motor. More...

SR59 Atlantic Research solid rocket engine. Minuteman 1 LGM30 Pitch Motor. More...

SR61 Atlantic Research solid rocket engine. Minuteman 1 LGM30 Spin Motor. More...

SR73 Aerojet solid rocket engine. Minuteman 1 LGM30 3rd stage. More...

SR75 Lockheed solid rocket engine. SRAM AGM69, ASAT ASM135. More...

SRB Thiokol solid rocket engine. 11,520 kN. Isp=269s. Segmented solid rocket boosters for the compromised space shuttle design. Field joint design led to Challenger shuttle disaster. Production 19811985, after which superseded by RSRM's. More...

SRBA Nissan solid rocket engine. 2250 kN. In production. Monolithic motor, shorter than that for H2, using Thiokol filament wound composite structure. Isp=280s. First flight 2001. More...

SRM1 CSD solid rocket engine. 181.5 kN. Used in TOS; IUS1 on Shuttle, Titan 34D. Known by manufacturer as Orbus 21. Propellant: 86% solids made up of HTPB UTP19360A. Shape: cylindrical. Isp=296s. First flight 1982. More...

SRM2 CSD solid rocket engine. 78.4 kN. Used in Shuttle, Titan 34D; IUS2. Known by manufacturer as Orbus 6. Isp=304s. First flight 1982. More...

SSUSA Motor Thiokol solid rocket engine. In Production. A slightly modified stage 3 Minuteman 3 with TVC and roll control systems removed, provided propulsion for the Douglas Spinning Solid Upper Stage for use with Space Shuttle payloads. More...

Star 37X Thiokol solid rocket engine. 51.1 kN. Out of Production. Total impulse 310,668 kgfsec. Motor propellant mass fraction 0.928. Isp=295s. More...

Star 37Y Thiokol solid rocket engine. Out of Production. Total impulse 317,856 kgfsec. Motor propellant mass fraction 0.93. Isp=297s. More...

Star 37XFP Thiokol solid rocket engine. 31.5 kN. In Production. Isp=290s. Orbit insertion motor qualified for Global Positioning Satellite. Used as a replacement for the discontinued STAR 37F. Propellant: 884 kg of AP/HTPB/Al in 6Al4V titanium case. More...

Star 37XF 8 Thiokol solid rocket engine. Out of Production. Total impulse 238,809 kgfsec. Motor propellant mass fraction 0.924. Isp=291s. More...

Star 37F Thiokol solid rocket engine. 55.5 kN. Out of Production. Total impulse 249,177 kgfsec. Motor propellant mass fraction 0.928. Isp=286s. More...

Star 37XF Thiokol solid rocket engine. 45 kN. Out of Production. Total flown included in total for Star37XF8. Total impulse 259,123 kgfsec. Motor propellant mass fraction 0.929. Isp=290s. More...

Star 40 Thiokol solid rocket engine. Out of Production. Total impulse 200,882 kgfsec. Motor propellant mass fraction 0.925. Isp=207s. More...

Star 37S Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 190,590 kgfsec. Motor propellant mass fraction 0.925. Isp=287s. More...

Star 37N Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 162,102 kgfsec. Motor propellant mass fraction 0.898. Isp=290s. More...

Star 37G Thiokol solid rocket engine. Out of Production. Total impulse 304,620 kgfsec. Motor propellant mass fraction 0.925. Isp=289s. More...

Star 27E Thiokol solid rocket engine. In Production. Total impulse 88,301 kgfsec. Motor propellant mass fraction 0.921. Isp=287s. More...

Star 48 Thiokol solid rocket engine. 67.2 kN. Used in Delta 3900; Conesotga; PAMS; PAMD. Total flown included in total for Star488. Total impulse 575,682 kgfsec. Motor propellant mass fraction 0.946. Isp=286s. First flight 1982. More...

Star 75 Thiokol solid rocket engine. 242.8 kN. In Production. Isp=288s. A demonstration motor tested as a first step in the development of a perigee kick motor in the 40807940 kg propellant range. More...

Star 5 Thiokol solid rocket engine. Out of Production. Total impulse 405 kgfsec. Motor propellant mass fraction 0.87. Isp=189s. More...

Star 37E Thiokol solid rocket engine. 68 kN. Out of Production. Total impulse 296,635 kgfsec. Motor propellant mass fraction 0.926. Isp=283s. More...

Star 37D Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 189,489 kgfsec. Motor propellant mass fraction 0.91. Isp=266s. More...

Star 37C Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 275,959 kgfsec. Motor propellant mass fraction 0.921. Isp=285s. More...

Star 37FM Thiokol solid rocket engine. 47.9 kN. In Production. Isp=289s. Apogee kick motor for the FLTSTACOM satellite. The motor case contained the same volume as the discontinued STAR 37E. More...

Star 5C/CB Thiokol solid rocket engine. 1.951 kN. In Production. Isp=266s. Titan Retro designed to separate the second stage from the transtage on the Titan II missile and Titan launch vehicle. The motor was also adapted for other uses. More...

Star 37B Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 189,489 kgfsec. Motor propellant mass fraction 0.91. Isp=291s. More...

Star 6B Thiokol solid rocket engine. 2.510 kN. In Production. Isp=273s. DeltaV reentry motor developed as a spinup and propulsion motor for reentry vehicles. The design incorporated an aluminum case and a plastic nozzle assembly. More...

Star 6A Thiokol solid rocket engine. Out of Production. Total impulse 935 kgfsec. Motor propellant mass fraction 0.723. Isp=285s. More...

Star 63F Thiokol solid rocket engine. 104.627 kN. In Production. Isp=297s. Provided perigee kick for the McDonnell PAMD2 system. Another version was the Star 63D (TU936). More...

Star 63D Thiokol solid rocket engine. 84.739 kN. In Production. Isp=283s. Perigee motor with a range of propellant loads, yielding GTO payloads from 3,080 to 4,588 pounds at a constant velocity of 8,012 feet per second. More...

Star 63 Thiokol solid rocket engine. 107.2 kN. Used in Shuttle,Titan 34D. Isp=282s. Used on Delta 7925 launch vehicle. First flight 1990. More...

Star 62 Thiokol solid rocket engine. Out of Production. Total impulse 725,491 kgfsec. Motor propellant mass fraction 0.94. Isp=294s. More...

Star 48B s Thiokol solid rocket engine. 77.109 kN. In Production. Isp=286s. Short nozzle upperstage motor qualified for the McDonnell Douglas Payload Assist Module (PAM) Space Transportation System (STS). More...

Star 5CB Thiokol solid rocket engine. 2 kN. In Production. Reduced Al HTPB propellant (2.1 kg) minimizes contamination when Used in a Titan 4 stage separation motor. Diameter: 121 mm. Length: 341 mm. Mass: 4.5 kg. Itotal: 5.5 kNs. Burn Time: 2.77 sec. More...

Star 48 8 Thiokol solid rocket engine. Out of Production. Total impulse 587,784 kgfsec. Motor propellant mass fraction 0.945. Isp=292s. More...

Star 5C Thiokol solid rocket engine. 2.039 kN. Out of Production. Titan Retro designed to separate the second stage from the upper stage of the Titan IV launch vehicle. More...

Star 5A Thiokol solid rocket engine. 0.166 kN. In Production. Isp=249s. Space Gnat was designed to provide a minimum acceleration, extended burn deltaV impulse, for small payload replacement or spinup applications. More...

Star 48V Thiokol solid rocket engine. In Production. Developed for Conestoga's upper stage, providing some ±4 degrees capability at 30 degree/sec using the same loaded casing as the 48B. First Flight: 1994. More...

Star 48B l Thiokol solid rocket engine. In Production. Isp=292s. Lengthened version of Star 48B to provide increased payload capability. The design incorporates a longer cylindrical section in the motor case. More...

Star 48B Thiokol solid rocket engine. 66 kN. In Production. Isp=286s. Long nozzle upperstage motor qualified for the McDonnell Payload Assist Module (PAM) Delta. More...

Star 48A s Thiokol solid rocket engine. 77.109 kN. In Production. Isp=283s. Short nozzle upperstage motor designed to fit within the dimensional envelope of the long nozzle. More...

Star 48A l Thiokol solid rocket engine. In Production. Total impulse 709,062 kgfsec. Motor propellant mass fraction 0.941. Isp=289s. More...

Star 6 Thiokol solid rocket engine. Out of Production. Total flown included in total for Star6A. Total impulse 1,395 kgfsec. Motor propellant mass fraction 0.795. Isp=287s. More...

Star 13C Thiokol solid rocket engine. Out of Production. Total impulse 8,252 kgfsec. Motor propellant mass fraction 0.795. Isp=218s. More...

Star 20A Thiokol solid rocket engine. Out of Production. Total impulse 83,839 kgfsec. Motor propellant mass fraction 0.91. Isp=291s. More...

Star 37 Thiokol solid rocket engine. 43.5 kN. Total impulse 161,512 kgfsec. Motor propellant mass fraction 0.899. Isp=260s. First flight 1963. More...

Star 20 Thiokol solid rocket engine. 27.135 kN. In Production. Isp=286s. Altair III was developed as the propulsion unit for the fourth stage of the Scout launch vehicle. A filamentwound, fiberglassepoxy case contained the CTPB propellant grain. More...

Star 17A Thiokol solid rocket engine. 16.014 kN. In Production. Isp=286s. Apogee kick motor, modified with 175 mm straight section added to the Star 17. The 17A was used to circularize orbits for the Skynet 1, NATO 1, and IMPH & J satellites. More...

Star 17 Thiokol solid rocket engine. 10.9 kN. Skynet 1, NATO 1, and IMPH & J. Out of production. Isp=286s. Used on Atlas LV3A / Agena D launch vehicle. First flight 1963. More...

Star 15 Thiokol solid rocket engine. Out of Production. Total impulse 11,109 kgfsec. Motor propellant mass fraction 0.926. Isp=228s. More...

Star 13F Thiokol solid rocket engine. Out of Production. Total impulse 9,608 kgfsec. Motor propellant mass fraction 0.83. Isp=240s. More...

Star 24 Thiokol solid rocket engine. 20 kN. Skynet 2. In Production. Isp=282s. Apogee boost motor was qualified and flown for the Skynet II, later apogee boost motor for NRL and SAMSO. More...

Star 13D Thiokol solid rocket engine. Out of Production. Total impulse 7,799 kgfsec. Motor propellant mass fraction 0.81. Isp=223s. More...

Star 20B Thiokol solid rocket engine. 24.467 kN. In Production. Isp=289s. Modified version of the STAR 20 with increased case structural capability over the. A filamentwound, fiberglassepoxy case contained the CTPB propellant grain. More...

Star 13B Thiokol solid rocket engine. 7.6 kN. Out of Production. Isp=285s. Orbit insertion motor incorporated the lightweight case developed for the STAR 13 with the propellant and nozzle design of the earlier TEM516 apogee motor. More...

Star 13A Thiokol solid rocket engine. 5.874 kN. In Production. Isp=286s. Orbit insertion motor incorporated the lightweight titanium case developed for the STAR 13 with the propellant and nozzle design of the earlier TEM444 apogee motor. More...

Star 13 Thiokol solid rocket engine. 3.8 kN. Out of Production. Isp=273s. A braking motor used by NASA for the Anchored Interplanetary Monitoring Platform program. More...

Star 12A Thiokol solid rocket engine. 7.247 kN. In Production. Isp=270s. Super SARV Retro was a longer, higher impulse version of the STAR 12, used as a retrograde rocket for an unmanned satellite vehicle. More...

Star 12 Thiokol solid rocket engine. 5.560 kN. In Production. Isp=252s. SARV Retro, MK IV and V was a 60pound motor using 40 pounds of propellant. It was designed for use as a retrograde rocket for an unmanned satellite vehicle. More...

Star 10 Thiokol solid rocket engine. 3.353 kN. In Production. Isp=251s. SARV Retro MK I was a small, highperformance motor designed for use as a retrograde rocket for an unmanned satellite vehicle. More...

Star 30A Thiokol solid rocket engine. Out of Production. Total impulse 137,095 kgfsec. Motor propellant mass fraction 0.942. Isp=294s. More...

Star 13E Thiokol solid rocket engine. Out of Production. Total impulse 6,438 kgfsec. Motor propellant mass fraction 0.822. Isp=211s. More...

Star 27C Thiokol solid rocket engine. In Production. Total flown included in total for Star27E. Total impulse 88,555 kgfsec. Motor propellant mass fraction 0.918. Isp=287s. More...

Star 31 Thiokol solid rocket engine. 80 kN. In Production. Isp=293s. Antares III, thirdgeneration third stage for Scout launch vehicle. Propellant: AP/HTPB/Al propellant in a filament wound Kevlar case. More...

Star 30E Thiokol solid rocket engine. 35.4 kN. Koreasat. In Production. Isp=290s. Apogee motor used for the BAe Skynet 4 satellite, Koreasat and by the ORBEX small orbital launcher. More...

Star 30C Thiokol solid rocket engine. 32.6 kN. AS 3000. In Production. Isp=286s. Apogee motor used for the RCA GSTAR and Martin Marietta series 3000 telecom satelllites. More...

Star 30BP Thiokol solid rocket engine. 27 kN. In Production. Isp=292s. Apogee motor used for the HS 376 satellite bus. Incorporated an 89percentsolids HTPB propellant in a 6AI4V titanium case insulated with silicafilled EPDM rubber. More...

Star 30B Thiokol solid rocket engine. Out of Production. Total impulse 148,816 kgfsec. Motor propellant mass fraction 0.941. Isp=293s. More...

Star 20 Spherical Thiokol solid rocket engine. Out of Production. Total impulse 30,198 kgfsec. Motor propellant mass fraction 0.934. Isp=234s. More...

Star 27D Thiokol solid rocket engine. In Production. Total flown included in total for Star27E. Total impulse 88,668 kgfsec. Motor propellant mass fraction 0.921. Isp=287s. More...

Star 24A Thiokol solid rocket engine. Out of Production. Total flown included in total for Star24C. Total impulse 50,965 kgfsec. Motor propellant mass fraction 0.903. Isp=282s. More...

Star 27B Thiokol solid rocket engine. In Production. Total flown included in total for Star27E. Total impulse 92,296 kgfsec. Motor propellant mass fraction 0.921. Isp=288s. More...

Star 27A Thiokol solid rocket engine. In Production. Total flown included in total for Star27E. Total impulse 89,684 kgfsec. Motor propellant mass fraction 0.919. Isp=287s. More...

Star 27 Thiokol solid rocket engine. 27 kN. Apogee motor used on CTS, GMS, BS, GPS, GOES satellites. In Production. Isp=288s. More...

Star 26C Thiokol solid rocket engine. 35 kN. In Production. Isp=272s. Upper stage motor used the titanium alloy case and nozzle attachment ring of the STAR 26B design to provide high propellant mass fraction and was insulated for highspinrate applications. More...

Star 26B Thiokol solid rocket engine. 34.627 kN. In Production. Isp=271s. Upper stage motor flown on the Burner IIA spacecraft for Boeing and the U.S. Air Force. More...

Star 26 Thiokol solid rocket engine. 39.1 kN. In Production. Upper stage motor used in the Sandia Strypi IV vehicle. Total flown included in total for Star26C. Total impulse 62,800 kgfsec. Motor propellant mass fraction 0.86. Isp=271s. First flight 1965. More...

Star 25 Thiokol solid rocket engine. Out of Production. Total impulse 61,086 kgfsec. Motor propellant mass fraction 0.917. Isp=240s. More...

Star 24C Thiokol solid rocket engine. 21.466 kN. In Production. Isp=282s. Apogee motor designed and qualified for the NASA International Ultraviolet Experiment satellite. More...

Star 24B Thiokol solid rocket engine. Out of Production. Total flown included in total for Star24C. Total impulse 57,236 kgfsec. Motor propellant mass fraction 0.915. Isp=282s. More...

Star 30 Thiokol solid rocket engine. Out of Production. Total flown included in total for Star30A. Total impulse 136,455 kgfsec. Motor propellant mass fraction 0.943. Isp=293s. More...

Stonechat I RO solid rocket engine. 232 kN. Largest solid rocket motor ever produced in Britain. Motor developed for hypersonic research vehicle. Subsequently used in Falstaff test vehicle. More...

Stonechat Mk 2 Royal Ordnance solid rocket engine. Out of production. There seem to have been even larger classified versions. Used on Falstaff launch vehicle. More...

Stromboli SEPR solid rocket engine. 143 kN. Out of production. Isp=235s. Used on Berenice, Tacite, Titus. First flight 1962. More...

T7A Booster Fourth Academy solid rocket engine. 46 kN. T7 sounding rocket. Out of Production. Isp=209s. China's first flight solid rocket. First flight 1965. Polysulfide binder with aluminium binder fuel in case of high strength steel with a graphite throat insert. More...

Talos Mk 11 Mod 2 Hercules solid rocket engine. 516 kN. Talos motor fitted with a conical adapter for mating to the second stage. More...

Terrier Mk12 Mod 0 Naval Prop Plant solid rocket engine. 257.5 kN. The Terrier MK 12 Mod 1 rocket motor was typically equipped with four 0.22 square meter fin panels arranged in a cruciform configuration. More...

Thiokol 156 Thiokol solid rocket engine. 14,746.1 kN. Developed to 1966. Isp=263s. More...

Tramontane SEPR solid rocket engine. 50 kN. Out of production. Isp=220s. Used on Berenice launch vehicle. First flight 1962. More...

TX3543 Thiokol solid rocket engine. 258.9 kN. Used in Scout A; Delta E; H10; Castor 2. License built in Japan for H1. Isp=262s. First flight 1960. More...

UA156 CSD solid rocket engine. 8924.3 kN. Tested 1968. Isp=263s. Proposed as strapon booster for Saturn INT27, Saturn V25(S)B, Saturn V25(S)U. More...

UA1205 CSD solid rocket engine. 5849.3 kN. Out of production. Isp=263s. Strapon boosters for Titan 3C, 3D, 3E. Proposed for advanced Saturn IB versions. First flight 1965. More...

UA1206 CSD solid rocket engine. 6226.9 kN. Isp=265s. Used on Titan 34D launch vehicle. First flight 1982. More...

UA1207 CSD solid rocket engine. 7116.9 kN. Isp=272s. First flight 1989. More...

UM129A Nissan solid rocket engine. 77.5 kN. In Production. Used in H13. Isp=291s. More...

USRM Hercules solid rocket engine. 7560.5 kN. Isp=286s.Strapon booster for Titan 4B. First flight 1997. More...

Viper20 Multiplesource American solid rocket engine. 20 kN. Viper More...

X248 Thiokol solid rocket engine. 12.4 kN. Isp=256s. Used on Atlas Able, Blue Scout 2, Caleb, Delta, Delta A, Delta B, Delta C. First flight 1959. More...

X248A Thiokol solid rocket engine. 13.8 kN. Isp=255s. Used on Scout X1, Scout X2, Scout X3. First flight 1960. More...

X254 Thiokol solid rocket engine. 60.5 kN. Isp=256s. Used on Blue Scout 1, Blue Scout 2, Blue Scout Junior, Scout X1. First flight 1960. More...

X258 Thiokol solid rocket engine. 22.2 kN. Isp=266s. Kick stage motor for Delta D, Scout A, Scout X4. First flight 1963. More...

X259 Thiokol solid rocket engine. 93.1 kN. Isp=293s. Used on Scout A, Scout B, Scout D, Scout F, Scout X2, Scout X3, Scout X4. First flight 1962. More...

X259A Thiokol solid rocket engine. 80.8 kN. Out of production. Isp=295s. Used on Scout G launch vehicle. First flight 1979. More...

Zefiro 23 FiatAvio solid rocket engine. 1200 kN. In production. Isp=289s. Carbon epoxy filament wound case; low density EPDM insulation; HTPB 1912 composite propellant. Used on Vega launch vehicle. More...

Zefiro 9 FiatAvio solid rocket engine. 313 kN. In production. Isp=294s. Motor derived from the 16metricton Zefiro 16. Carbon epoxy filament wound case; low density EPDM insulation; HTPB 1912 composite propellant. More...
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