Encyclopedia Astronautica
Thiokol


American manufacturer of rocket engines and rockets. Thiokol Corporation, Ogden, UT, USA.

Developed liquid polymer in 1943, leading to polysulphide liquid polymer, the first solid rocket fuel suitable for mass production.

AKA: Thiokol Chemical Copr (1929); Morton Thiokol (1982); Thiokol Corporation (1989).
Location: Ogden, UT.

More... - Chronology...


Associated Countries
Associated Engines
  • 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...
  • 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 strap-on boosters and as first and upper stages for low-cost all-solid-propellant 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. Strap-on 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...
  • FW-4D Thiokol solid rocket engine. 25 kN. Isp=287s. Kick stage motor for Delta E, Delta L. First flight 1965. More...
  • FW-4S 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...
  • LR44 Thiokol liquid rocket engine. Sparrow AAM-N-6, White Lance GAM-79. More...
  • LR58 Thiokol liquid rocket engine. Bullpup AGM-12B, Bulldog AGM-83. More...
  • LR62 Thiokol liquid rocket engine. Bullpup AGM-12C/E. More...
  • M33-20-4 Thiokol solid rocket engine. 286 kN. Isp=247s. Used as apogee kick motor on Delta D, LT Thor Agena D, Scout X-1, Scout X-2, Scout X-3, Scout X-4, TA Thor Agena B, TA Thor Agena D. First flight 1960. More...
  • M55/TX-55/Tu-122 Thiokol solid rocket engine. 792 kN. In production. Isp=262s. Proposed as strap-on booster for Saturn IB-C, Saturn INT-14, Saturn INT-15, Saturn INT-19 variants. First flight 2000. 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...
  • 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...
  • 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...
  • SR109 Thiokol solid rocket engine. Maverick AGM-65. More...
  • SR114 Thiokol solid rocket engine. Maverick AGM-65. More...
  • SR49 Thiokol solid rocket engine. Genie AIR-2. More...
  • SR51 Thiokol solid rocket engine. Titan 2 LGM-25C Retro Motor. 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 1981-1985, after which superseded by RSRM's. More...
  • SSUS-A 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 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 37X Thiokol solid rocket engine. 51.1 kN. Out of Production. Total impulse 310,668 kgf-sec. Motor propellant mass fraction 0.928. Isp=295s. More...
  • Star 40 Thiokol solid rocket engine. Out of Production. Total impulse 200,882 kgf-sec. Motor propellant mass fraction 0.925. Isp=207s. 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 6Al-4V titanium case. More...
  • Star 37XF 8 Thiokol solid rocket engine. Out of Production. Total impulse 238,809 kgf-sec. Motor propellant mass fraction 0.924. Isp=291s. More...
  • Star 37XF Thiokol solid rocket engine. 45 kN. Out of Production. Total flown included in total for Star-37XF-8. Total impulse 259,123 kgf-sec. Motor propellant mass fraction 0.929. Isp=290s. More...
  • Star 37Y Thiokol solid rocket engine. Out of Production. Total impulse 317,856 kgf-sec. Motor propellant mass fraction 0.93. Isp=297s. More...
  • Star 37S Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 190,590 kgf-sec. Motor propellant mass fraction 0.925. Isp=287s. More...
  • Star 48 Thiokol solid rocket engine. 67.2 kN. Used in Delta 3900; Conesotga; PAM-S; PAM-D. Total flown included in total for Star-48-8. Total impulse 575,682 kgf-sec. Motor propellant mass fraction 0.946. Isp=286s. First flight 1982. More...
  • Star 37G Thiokol solid rocket engine. Out of Production. Total impulse 304,620 kgf-sec. Motor propellant mass fraction 0.925. Isp=289s. More...
  • Star 48B s Thiokol solid rocket engine. 77.109 kN. In Production. Isp=286s. Short nozzle upper-stage motor qualified for the McDonnell Douglas Payload Assist Module (PAM) Space Transportation System (STS). More...
  • Star 37F Thiokol solid rocket engine. 55.5 kN. Out of Production. Total impulse 249,177 kgf-sec. Motor propellant mass fraction 0.928. Isp=286s. More...
  • Star 37E Thiokol solid rocket engine. 68 kN. Out of Production. Total impulse 296,635 kgf-sec. Motor propellant mass fraction 0.926. Isp=283s. More...
  • Star 37B Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 189,489 kgf-sec. Motor propellant mass fraction 0.91. Isp=291s. More...
  • Star 37C Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 275,959 kgf-sec. Motor propellant mass fraction 0.921. Isp=285s. 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 4080-7940 kg propellant range. More...
  • Star 37N Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 162,102 kgf-sec. Motor propellant mass fraction 0.898. Isp=290s. 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 37 Thiokol solid rocket engine. 43.5 kN. Total impulse 161,512 kgf-sec. Motor propellant mass fraction 0.899. Isp=260s. First flight 1963. More...
  • Star 6B Thiokol solid rocket engine. 2.510 kN. In Production. Isp=273s. Delta-V reentry motor developed as a spin-up 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 kgf-sec. 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 PAM-D2 system. Another version was the Star 63D (TU-936). 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 kgf-sec. Motor propellant mass fraction 0.94. Isp=294s. More...
  • Star 48B Thiokol solid rocket engine. 66 kN. In Production. Isp=286s. Long nozzle upper-stage motor qualified for the McDonnell Payload Assist Module (PAM) Delta. 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 kgf-sec. 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 delta-V impulse, for small payload replacement or spin-up applications. More...
  • Star 5 Thiokol solid rocket engine. Out of Production. Total impulse 405 kgf-sec. Motor propellant mass fraction 0.87. Isp=189s. 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 48A s Thiokol solid rocket engine. 77.109 kN. In Production. Isp=283s. Short nozzle upper-stage 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 kgf-sec. Motor propellant mass fraction 0.941. Isp=289s. More...
  • Star 6 Thiokol solid rocket engine. Out of Production. Total flown included in total for Star-6A. Total impulse 1,395 kgf-sec. Motor propellant mass fraction 0.795. Isp=287s. More...
  • Star 13C Thiokol solid rocket engine. Out of Production. Total impulse 8,252 kgf-sec. Motor propellant mass fraction 0.795. Isp=218s. 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 filament-wound, fiberglass-epoxy case contained the CTPB propellant grain. More...
  • Star 20 Spherical Thiokol solid rocket engine. Out of Production. Total impulse 30,198 kgf-sec. Motor propellant mass fraction 0.934. Isp=234s. More...
  • Star 31 Thiokol solid rocket engine. 80 kN. In Production. Isp=293s. Antares III, third-generation third stage for Scout launch vehicle. Propellant: AP/HTPB/Al propellant in a filament wound Kevlar case. 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 IMP-H & J satellites. More...
  • Star 17 Thiokol solid rocket engine. 10.9 kN. Skynet 1, NATO 1, and IMP-H & J. Out of production. Isp=286s. Used on Atlas LV-3A / Agena D launch vehicle. First flight 1963. More...
  • Star 15 Thiokol solid rocket engine. Out of Production. Total impulse 11,109 kgf-sec. Motor propellant mass fraction 0.926. Isp=228s. More...
  • Star 13F Thiokol solid rocket engine. Out of Production. Total impulse 9,608 kgf-sec. 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 kgf-sec. Motor propellant mass fraction 0.81. Isp=223s. More...
  • Star 20A Thiokol solid rocket engine. Out of Production. Total impulse 83,839 kgf-sec. Motor propellant mass fraction 0.91. Isp=291s. 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 TE-M-516 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 TE-M-444 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 60-pound 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, high-performance motor designed for use as a retrograde rocket for an unmanned satellite vehicle. More...
  • Star 37D Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 189,489 kgf-sec. Motor propellant mass fraction 0.91. Isp=266s. More...
  • Star 13E Thiokol solid rocket engine. Out of Production. Total impulse 6,438 kgf-sec. Motor propellant mass fraction 0.822. Isp=211s. More...
  • Star 27E Thiokol solid rocket engine. In Production. Total impulse 88,301 kgf-sec. Motor propellant mass fraction 0.921. Isp=287s. 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 G-STAR 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 89-percent-solids HTPB propellant in a 6AI-4V titanium case insulated with silica-filled EPDM rubber. More...
  • Star 30B Thiokol solid rocket engine. Out of Production. Total impulse 148,816 kgf-sec. Motor propellant mass fraction 0.941. Isp=293s. 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 filament-wound, fiberglass-epoxy case contained the CTPB propellant grain. More...
  • Star 30 Thiokol solid rocket engine. Out of Production. Total flown included in total for Star-30A. Total impulse 136,455 kgf-sec. Motor propellant mass fraction 0.943. Isp=293s. More...
  • Star 24A Thiokol solid rocket engine. Out of Production. Total flown included in total for Star-24C. Total impulse 50,965 kgf-sec. Motor propellant mass fraction 0.903. Isp=282s. More...
  • Star 27D Thiokol solid rocket engine. In Production. Total flown included in total for Star-27E. Total impulse 88,668 kgf-sec. Motor propellant mass fraction 0.921. Isp=287s. More...
  • Star 27C Thiokol solid rocket engine. In Production. Total flown included in total for Star-27E. Total impulse 88,555 kgf-sec. Motor propellant mass fraction 0.918. Isp=287s. 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 30A Thiokol solid rocket engine. Out of Production. Total impulse 137,095 kgf-sec. Motor propellant mass fraction 0.942. Isp=294s. More...
  • Star 24B Thiokol solid rocket engine. Out of Production. Total flown included in total for Star-24C. Total impulse 57,236 kgf-sec. Motor propellant mass fraction 0.915. Isp=282s. More...
  • Star 27B Thiokol solid rocket engine. In Production. Total flown included in total for Star-27E. Total impulse 92,296 kgf-sec. Motor propellant mass fraction 0.921. Isp=288s. More...
  • Star 25 Thiokol solid rocket engine. Out of Production. Total impulse 61,086 kgf-sec. Motor propellant mass fraction 0.917. Isp=240s. 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 Star-26C. Total impulse 62,800 kgf-sec. Motor propellant mass fraction 0.86. Isp=271s. First flight 1965. 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 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 high-spin-rate applications. 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 27A Thiokol solid rocket engine. In Production. Total flown included in total for Star-27E. Total impulse 89,684 kgf-sec. Motor propellant mass fraction 0.919. Isp=287s. More...
  • Thiokol 156 Thiokol solid rocket engine. 14,746.1 kN. Developed to 1966. Isp=263s. More...
  • TX-354-3 Thiokol solid rocket engine. 258.9 kN. Used in Scout A; Delta E; H-1-0; Castor 2. License built in Japan for H-1. Isp=262s. First flight 1960. More...
  • X-248 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...
  • X-248A Thiokol solid rocket engine. 13.8 kN. Isp=255s. Used on Scout X-1, Scout X-2, Scout X-3. First flight 1960. More...
  • X-259A Thiokol solid rocket engine. 80.8 kN. Out of production. Isp=295s. Used on Scout G launch vehicle. First flight 1979. More...
  • X-254 Thiokol solid rocket engine. 60.5 kN. Isp=256s. Used on Blue Scout 1, Blue Scout 2, Blue Scout Junior, Scout X-1. First flight 1960. More...
  • X-258 Thiokol solid rocket engine. 22.2 kN. Isp=266s. Kick stage motor for Delta D, Scout A, Scout X-4. First flight 1963. More...
  • X-259 Thiokol solid rocket engine. 93.1 kN. Isp=293s. Used on Scout A, Scout B, Scout D, Scout F, Scout X-2, Scout X-3, Scout X-4. First flight 1962. More...
  • XLR11 Reaction Motors, Thiokol Lox/Alcohol rocket engine. Out of Production. Launch thrust 26.67 kN. Rocket engine developed for X-1 in 1940s to break the sound barrier and used twenty years later to power experimental lifting bodies. Four combustion chambers. More...
  • XLR99 Thiokol Lox/Ammonia rocket engine. 262.4 kN. Out of production. Isp=276s. The first large, man-rated, throttleable, restartable liquid propellant rocket engine, boosted the X-15A. First flight 1959. More...

See also
Associated Launch Vehicles
  • Hermes C-1 American tactical ballistic missile. The Hermes C1 was a clustered-engine intercontinental ballistic missile proposed by General Electric in June 1946. It was eventually down-scoped to a single-engine tactical missile, which flew as the Redstone in 1953. More...
  • Hermes A-2 American tactical ballistic missile. The Army Hermes A-2 single stage test rocket proved the technology of large solid rocket motors as developed by H L Thackwell at Thiokol. But the Army preferred to have further development done in-house and JPL was selected to develop the Sergeant rocket. In addition to the flight tests, a total of 22 motors were static fired, including one after seven years of storage. More...
  • Nike Cajun American sounding rocket. Two stage vehicle sounding rocket consisting of a Nike booster together with a Cajun upper stage. Aside from the Soviet MMR-06, the Nike-Cajun was the most often launched sounding rocket. The Cajun motor was developed for NASA in the 1950's by Thiokol, providing a more modern but still affordable replacement for the World War II-era Deacon. More...
  • Cajun American sounding rocket. The Cajun research rocket was developed as a dimensionally-similar but higher performance successor to the Deacon. More...
  • Kisha Judi American sounding rocket. Two stage vehicle consisting of 1 x Kisha + 1 x Judi III More...
  • Bullpup Cajun American sounding rocket. Two stage vehicle consisting of 1 x Bullpup + 1 x Cajun More...
  • Ute Tomahawk American sounding rocket. The Ute (TU-715) motor was developed from the Genie motor baseline to serve as a first stage booster in the Ute-Tomahawk sounding rocket vehicle. 2 stage vehicle consisting of 1 x Ute + 1 x Tomahawk More...
  • Ute American sounding rocket. The Ute (TU-715) motor was developed from the Genie motor baseline. Later derivatives were combined with booster or upper stages. More...
  • Ute Apache American sounding rocket. Two stage vehicle consisting of 1 x Ute + 1 x Apache More...
  • Paiute Apache American sounding rocket. Two stage vehicle consisting of 1 x Paiute + 1 x Apache More...
  • Nike Malemute American sounding rocket. Two stage vehicle consisting of 1 x Nike + 1 x Malemute More...
  • Heavy Lift Carrier 2011 American heavy-lift orbital launch vehicle. ATK Thiokol concept for a shuttle-derived heavy lift vehicle. The shuttle orbiter would be replaced by a 6.5 m diameter x 35 m long cargo container, powered by three Space Shuttle main engines. The shuttle RSRM motors would have a fifth segment added, and the External Tank would be stretched to 56 m long. Availability would be six years after go-ahead. More...
  • Heavy Lift Carrier 2015 American heavy-lift orbital launch vehicle. ATK Thiokol concept for a shuttle-derived heavy lift vehicle with a lift equivalent to the Saturn V. The radical reconfiguration would put all elements in-line. Four SSME engines would be at the base of a stretched external tank, flanked by two shuttle RSRM motors with a fifth segment added. Atop this would be an 8.7 m diameter Lox/LH2 stage, followed by a 10-m diameter payload fairing. Availability would be ten years after go-ahead. More...
  • Heavy Lift Carrier 2008 American heavy-lift orbital launch vehicle. ATK Thiokol concept corresponding to earlier Shuttle-C proposals. The shuttle orbiter is replaced by a 6.5 m diameter x 25 m long cargo container, powered by two Space Shuttle main engines. Availability would be three to four years after go-ahead. More...
  • SRB CEV American heavy-lift orbital launch vehicle. Launch vehicle design preferred by NASA Administrator Mike Griffin to boost the manned CEV Crew Exploration Vehicle into low earth orbit. A single shuttle solid rocket booster would be mated with an upper stage in the 100 tonne class. More...

Associated Stages
  • Castor 4XL Solid propellant rocket stage. Loaded/empty mass 15,400/2,500 kg. Thrust 745.00 kN. Vacuum specific impulse 283 seconds. Provides supplemental thrust for H-2 or H-2A. More...
  • Draco-1 Solid propellant rocket stage. Loaded mass 3,500 kg. Thrust 213.00 kN. More...
  • Draco-2 Solid propellant rocket stage. Loaded mass 2,000 kg. Thrust 44.50 kN. More...
  • Nike Zeus-1 Solid propellant rocket stage. Loaded mass 5,000 kg. Thrust 2,000.00 kN. More...
  • Peacekeeper-1 Solid rocket stage. 1711.00 kN (384,648 lbf) thrust. Mass 53,400 kg (117,727 lb). More...
  • Pershing 2-1 Solid rocket stage. 172.00 kN (38,667 lbf) thrust. Mass 4,100 kg (9,039 lb). More...
  • Pershing 2-2 Solid rocket stage. 134.00 kN (30,124 lbf) thrust. Mass 2,600 kg (5,732 lb). More...
  • SICBM-1 Solid propellant rocket stage. Loaded mass 11,600 kg. Thrust 979.00 kN. More...
  • SM-3-3 Solid propellant rocket stage. Loaded mass 100 kg. Thrust 7.00 kN. More...
  • Star 37F Solid rocket stage. 55.50 kN (12,477 lbf) thrust. Mass 934 kg (2,059 lb). More...
  • Star 48V Solid rocket stage. 68.70 kN (15,444 lbf) thrust. Mass 2,200 kg (4,850 lb). More...
  • Star 37XFP Solid rocket stage. 31.50 kN (7,081 lbf) thrust. Mass 955 kg (2,105 lb). More...
  • Star 37XF Solid rocket stage. 45.00 kN (10,116 lbf) thrust. Mass 953 kg (2,101 lb). More...
  • Star 37N Solid rocket stage. 45.00 kN (10,116 lbf) thrust. Mass 623 kg (1,373 lb). More...
  • Star 37S Solid rocket stage. 45.00 kN (10,116 lbf) thrust. Mass 711 kg (1,567 lb). More...
  • Star 37FM Solid rocket stage. 47.90 kN (10,768 lbf) thrust. Mass 1,147 kg (2,529 lb). More...
  • Star 20 Solid rocket stage. 27.14 kN (6,100 lbf) thrust. Mass 301 kg (664 lb). More...
  • Star 37D Solid rocket stage. 45.00 kN (10,116 lbf) thrust. Mass 718 kg (1,583 lb). More...
  • Star 37XE Solid rocket stage. 45.00 kN (10,116 lbf) thrust. Mass 900 kg (1,984 lb). More...
  • Star 37C Solid rocket stage. 45.00 kN (10,116 lbf) thrust. Mass 1,048 kg (2,310 lb). More...
  • Star 37B Solid rocket stage. 45.00 kN (10,116 lbf) thrust. Mass 718 kg (1,583 lb). More...
  • Star 27 Solid rocket stage. 27.00 kN (6,070 lbf) thrust. Mass 361 kg (796 lb). More...
  • Star 26C Solid rocket stage. 35.00 kN (7,868 lbf) thrust. Mass 264 kg (582 lb). More...
  • Star 26B Solid rocket stage. 34.63 kN (7,784 lbf) thrust. Mass 261 kg (575 lb). More...
  • Star 37E Solid rocket stage. 68.00 kN (15,287 lbf) thrust. Mass 1,123 kg (2,476 lb). More...
  • Terrier Mk 70 Oriole-1 Solid propellant rocket stage. Loaded/empty mass 1,038/290 kg. Thrust kN. The basic Terrier mk70 motor was 3.94 m long with a principal diameter of 46 cm. There was a 7.6-cm interstage adapter which allowed for drag separation at Terrier burnout. Typically, the Terrier booster would utilize two spin motors to reduce dispersion and also serve as drag plates. Each Terrier fin was 0.43 square meters in area. Normally, the fins were canted to provide two revolutions per second spin rate at Terrier burnout. More...

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