Minotaur Credit - OSC

Minotaur was developed for the US Air Force's Orbital/Suborbital Program (OSP) as a low-cost, four-stage Space Launch Vehicle (SLV) using a combination of government-supplied surplus Minuteman II ICBM motors and proven Orbital space launch technologies. Proposed growth versions would use surplus Peacekeeper rocket stages.

The Minuteman motors served as the vehicle's first and second stages. Minotaur's third and fourth stages, structures and payload fairing were taken directly from Orbital's existing Pegasus XL rocket. Its capabilities were enhanced with the addition of improved avionics systems, including a Modular Avionics Control Hardware (MACH), already used on many of Orbital's suborbital launch vehicles.

Minotaur made its inaugural flight in January 2000, successfully delivering a number of small military and university satellites into orbit and marking the first-use of surplus Minuteman boosters in a space launch.

Several derivatives of Minotaur were developed or proposed:

• Minotaur I (the original Minotaur), consisting of an M55A1 first stage, SR19 second stage, Orion 50XL third stage, Orion 38 fourth stage, and optional HAPS fifth stage for velocity trim and multiple payload deployment. Payload 580 kg to an 185 km, 28.5 degree orbit from Cape Canaveral; 310 kg to a 740 km sun-synchronous orbit from Vandenberg.
• Minotaur II (a suborbital target vehicle), consisting of an M55A1 first stage, SR19 second stage, and M57 third stage - essentially a Minuteman II with Orbital guidance and control systems. 440 kg payload on a 6700 km suborbital trajectory. (Launches are listed at the Minuteman 2 page).
• Minotaur III (a suborbital target vehicle), using surplus Peacekeeper rocket stages, with an SR-118 first stage, SR-119 second stage, SR-120 third stage, and Super HAPS fourth stage. 3060 kg payload on a 6700 km suborbital trajectory.
• Minotaur IV (space launch vehicle), as Minotaur III but with an Orion 38 fourth stage and optional HAPS fifth stage. Payload 1720 kg to an 185 km, 28.5 degree orbit from Cape Canaveral; 1000 kg to a 740 km sun-synchronous orbit from Vandenberg.
• Minotaur V (space launch vehicle for putting small spacecraft on high-energy trajectories, such as GTO, HEO, and lunar), as Minotaur IV but with a Star 48V fourth stage and Orion 38 fifth stage. Payload 560 kg to a geosynchronous transfer orbit.

All of the Minotaur-family launches to date have been from Vandenberg AFB, CA. Minotaur I launches were from Space Launch Complex 8 (SLC-8), the Spaceport Systems Incorporated (SSI) Commercial Launch Facility (CLF). Minotaur II launches have all been from Launch Facility 06 (LF-06).

Manufacturer: OSC. Launches: 8. First Launch Date: 2000-01-27. Last Launch Date: 2007-04-24. Launch data is: continuing. LEO Payload: 640 kg (1,410 lb). to: 185 km Orbit. at: 28.50 degrees. Payload: 335 kg (738 lb). to a: Sun synchronous, 741 km, 98.6 deg inclination trajectory. Apogee: 1,000 km (600 mi). Associated Spacecraft: MEMS, Mightysat 1, Picosat. Liftoff Thrust: 720.000 kN (161,860 lbf). Total Mass: 36,200 kg (79,800 lb). Core Diameter: 1.67 m (5.47 ft). Total Length: 19.21 m (63.02 ft). Recurring Price $: 12.500 million. in: 1999 price dollars.

• Stage Number: 1. 1 x Stage: Minuteman-1. Gross Mass: 23,077 kg (50,876 lb). Empty Mass: 2,292 kg (5,052 lb). Thrust (vac): 791.300 kN (177,891 lbf). Isp: 262 sec. Burn time: 60 sec. Isp(sl): 237 sec. Diameter: 1.67 m (5.47 ft). Span: 1.67 m (5.47 ft). Length: 7.49 m (24.57 ft). Propellants: Solid. No Engines: 1. Engine: M55/TX-55/Tu-122. Status: In production. First stage of Minuteman I. Proposed as zero stage for various Saturn variants in 1960's. Surplus motors used in ABM SDI tests in 1980's and 1990's.

• Stage Number: 2. 1 x Stage: Minuteman 2-2. Gross Mass: 7,032 kg (15,502 lb). Empty Mass: 795 kg (1,752 lb). Thrust (vac): 267.700 kN (60,181 lbf). Isp: 288 sec. Burn time: 66 sec. Diameter: 1.33 m (4.36 ft). Span: 1.33 m (4.36 ft). Length: 4.12 m (13.51 ft). Propellants: Solid. No Engines: 1. Engine: SR-19. Status: In production. Second stage of Minuteman 2. Used as second stage of Minotaur launch vehicle and various SDI targets in 1980's.

• Stage Number: 3. 1 x Stage: Pegasus XL-2. Gross Mass: 4,331 kg (9,548 lb). Empty Mass: 416 kg (917 lb). Thrust (vac): 153.503 kN (34,509 lbf). Isp: 290 sec. Burn time: 73 sec. Isp(sl): 240 sec. Diameter: 1.27 m (4.16 ft). Span: 1.27 m (4.16 ft). Length: 3.58 m (11.74 ft). Propellants: Solid. No Engines: 1. Engine: Pegasus XL-2.

• Stage Number: 4. 1 x Stage: Pegasus-3. Gross Mass: 985 kg (2,171 lb). Empty Mass: 203 kg (447 lb). Thrust (vac): 34.568 kN (7,771 lbf). Isp: 293 sec. Burn time: 65 sec. Isp(sl): 240 sec. Diameter: 0.97 m (3.18 ft). Span: 0.97 m (3.18 ft). Length: 2.08 m (6.82 ft). Propellants: Solid. No Engines: 1. Engine: Pegasus-3.

2000 January 27 - 03:03 GMT - Launch Site: Vandenberg. Launch Complex: CLF. Launch Pad: CLF. Launch Vehicle: Minotaur. Model: Minotaur 1. LV Configuration: Minotaur 1OSP / SLV-1.

• JAWSAT Nation: USA. Payload: P98-1. Mass: 64 kg (141 lb). Class: Technology. Spacecraft: JAWSAT. Agency: Weber St. Manufacturer: Weber State University, Utah. Perigee: 753 km (468 mi). Apogee: 805 km (501 mi). Inclination: 100.20 deg. Period: 100.36 min. COSPAR: 2000-004A. USAF Sat Cat: 26061. Joint USAF Academy/Weber State Satellite. Payloads included a plasma experiment, a particle detector, and a technology test. References: 4, 552, 554.

• OCSE Nation: USA. Payload: Optical Calibration Sphere. Mass: 22 kg (48 lb). Class: Technology. Agency: USAF SOR. Manufacturer: L'Garde, Inc. Perigee: 677 km (421 mi). Apogee: 711 km (442 mi). Inclination: 100.22 deg. Period: 98.57 min. COSPAR: 2000-004B. USAF Sat Cat: 26062. Decay Date: 2001-03-05. Optical Calibration Sphere Experiment, a 3.5m diameter inflatable sphere built by L'Garde Inc. for calibrating the lasers at the AFRL Starfire Optical Range. The 0.48m long 0.41m diameter OCSE canister was ejected from the JAWSAT stack; 42 seconds later, with the canister clear of the other payloads, the canister door opened and 10 seconds after that inflation of the sphere began. The canister remains attached to the inflated sphere. Once inflated, the sphere's material becomes rigidizedReferences: 4, 552, 554.

• OPAL Nation: USA. Payload: Orbiting Picosat Launcher. Mass: 13 kg (28 lb). Class: Technology. Agency: Stanford. Manufacturer: Stanford University. Perigee: 754 km (468 mi). Apogee: 808 km (502 mi). Inclination: 100.20 deg. Period: 100.39 min. COSPAR: 2000-004C. USAF Sat Cat: 26063. Stanford University Orbiting Picosat Automated Launcher. Carried an acclerometer, a magnetometer, and six small picosatellites - Picosat 1 and 2, Stensat, and the Artemis triplets (JAK, Thelma, and Louise). The first two were deployed on February 7 at 0334:16 GMT. OPAL transmitter problems delayed the initial release.References: 4, 552, 554.

• Falconsat Nation: USA. Mass: 52 kg (114 lb). Class: Technology. Agency: USAF Aca. Manufacturer: USAF Academy, Colorado Springs. Perigee: 754 km (468 mi). Apogee: 810 km (503 mi). Inclination: 100.20 deg. Period: 100.41 min. COSPAR: 2000-004D. USAF Sat Cat: 26064. USAF Academy satellite, carried the CHAWS-LD (Charging Hazards and Wake Studies-Long Duration) experiment to measure spacecraft charging effects in LEO. References: 4, 552, 554.

• ASUSAT Nation: USA. Mass: 5.00 kg (11.00 lb). Class: Technology. Agency: Arizona. Manufacturer: Arizona State University. Perigee: 754 km (468 mi). Apogee: 809 km (502 mi). Inclination: 100.20 deg. Period: 100.40 min. COSPAR: 2000-004E. USAF Sat Cat: 26065. Arizona State University satellite with an Earth imager and an amateur radio transponder. References: 4, 552, 554.

• Picosat 1 Nation: USA. Mass: 0 kg ( lb). Class: Technology. Spacecraft: MEMS. Agency: DARPA. Manufacturer: Aerospace Corp., El Segundo. Perigee: 746 km (463 mi). Apogee: 796 km (494 mi). Inclination: 100.20 deg. COSPAR: 2000-004H. USAF Sat Cat: 26080. Deployed by the OPAL satellite on February 7 at 0334:16 GMT. Picosat 1 and 2 were each 0.25 kg DARPA/Aerospace Corp. MEMS (Micro Electro-mechanical Systems) picosatellites, each carrying intersatellite communications experiment and connected by a 30-m tether.References: 4, 552, 554.

• Picosat 2 Nation: USA. Mass: 0 kg ( lb). Class: Technology. Spacecraft: MEMS. Agency: DARPA. Manufacturer: Aerospace Corp., El Segundo. Perigee: 746 km (463 mi). Apogee: 796 km (494 mi). Inclination: 100.20 deg. COSPAR: 2000-004H. USAF Sat Cat: 26080. Deployed by the OPAL satellite on February 7 at 0334:16 GMT. Picosat 1 and 2 were each 0.25 kg DARPA/Aerospace Corp. MEMS (Micro Electro-mechanical Systems) picosatellites, each carrying intersatellite communications experiment and connected by a 30-m tether.References: 4, 552, 554.

• Thelma Nation: USA. Mass: 68 kg (149 lb). Class: Technology. Agency: SCREEM. Manufacturer: Santa Clara University. Perigee: 747 km (464 mi). Apogee: 797 km (495 mi). Inclination: 100.20 deg. COSPAR: 2000-004J. USAF Sat Cat: 26091. Three picosatellites (JAK, Thelma, and Louise), developed by the Artemis team of women undergraduates at Santa Clara University, were deployed from the OPAL satellite. Mass 0.5 kg; size around 0.1-0.2m. Carried a VLF wave experiment. Ejected from OPAL on February 12; unfortunately no data was received thereafter.References: 4, 552, 554.

• Louise Nation: USA. Mass: 68 kg (149 lb). Class: Technology. Agency: SCREEM. Manufacturer: Santa Clara University. Perigee: 746 km (463 mi). Apogee: 800 km (490 mi). Inclination: 100.20 deg. COSPAR: 2000-004K. USAF Sat Cat: 26092. Three picosatellites (JAK, Thelma, and Louise), developed by the Artemis team of women undergraduates at Santa Clara University, were deployed from the OPAL satellite. Mass 0.5 kg; size around 0.1-0.2m. Carried a VLF wave experiment. Ejected from OPAL on February 12; unfortunately no data was received thereafter.References: 4, 552, 554.

• JAK Nation: USA. Mass: 1.00 kg (2.20 lb). Class: Technology. Agency: SCREEM. Manufacturer: Santa Clara University. Perigee: 744 km (462 mi). Apogee: 797 km (495 mi). Inclination: 100.20 deg. COSPAR: 2000-004L. USAF Sat Cat: 26093. Three picosatellites (JAK, Thelma, and Louise), developed by the Artemis team of women undergraduates at Santa Clara University, were deployed from the OPAL satellite. . JAK is the initials of the infant son of the Artemis' team's advisor Mass 0.2 kg; size around 0.1 - 0.2m. Carried a VLF wave experiment. Ejected from OPAL on February 11; unfortunately no data was received thereafter.References: 4, 552, 554.

• STENSAT Nation: USA. Mass: 0 kg ( lb). Class: Technology. Agency: AMSAT-NA. Manufacturer: STENSAT, Washington DC. Perigee: 747 km (464 mi). Apogee: 801 km (497 mi). Inclination: 100.10 deg. COSPAR: 2000-004M. USAF Sat Cat: 26094. Picosat. Built by built by the AMSAT-NA (Amateur Satellite, North America) group, and carried an amateur radio transponder. Ejected from OPAL on February 11; unfortunately no data was received thereafter. References: 4, 552, 554.

• Mightysat 2.1 Nation: USA. Payload: SA-200B. Mass: 120 kg (260 lb). Class: Surveillance. Type: Military. Spacecraft: SA-200. Agency: USAF STP. Manufacturer: Spectrum Astro. Perigee: 547 km (340 mi). Apogee: 581 km (361 mi). Inclination: 97.78 deg. Period: 95.86 min. COSPAR: 2000-042A. USAF Sat Cat: 26414. Decay Date: 2002-11-12. Mightysat 2.1, also known as Sindri, used a Spectrum Astro SA-200B satellite bus. The spacecraft carried a hyperspectral imager for earth imaging and spectroscopy, as well as satellite technology experiments such as advanced solar arrays. An Aerospace Corp./DARPA picosatellite experiment, consisting of two small boxes connected by a deployable tether, was deployed later. Similar picosats were deployed on the previous Minotaur launch in January 2000.References: 4, 552, 554.

• Picosat 7/8 Nation: USA. Class: Technology. Agency: USAF AFSPC. Perigee: 266 km (165 mi). Apogee: 286 km (177 mi). Inclination: 97.80 deg. Period: 90.00 min. COSPAR: 2000-042C. USAF Sat Cat: 26929. Decay Date: 2002-07-11. Picosat 7/Picosat 8, were ejected from the Mightysat II.1 satellite on September 7 at 1939 UTC into a 511 x 539 km x 97.8 deg orbit. The 0.25 kg satellites were connected by a 30 m tether and were cataloged as a single object. Mightysat II.1 (Sindri) was launched in July 2000, and the deployment of the picosats was planned for a year after launch.References: 4, 552, 554.

• USA 165 Nation: USA. Payload: XSS-11. Mass: 145 kg (319 lb). Class: Technology. Type: Rendezvous. Spacecraft: XSS. Agency: USAF Research Laboratory. Manufacturer: Lockheed Martin Space Systems. Perigee: 840 km (520 mi). Apogee: 872 km (541 mi). Inclination: 98.80 deg. Period: 102.10 min. COSPAR: 2005-011A. USAF Sat Cat: 28636. Delayed from November 9, 2004; January 19, March 18, 2005. Military Autonomous Rendezvous Technology. It tested navigation technologies for rendezvous that directly measured relative position to the target satellite. It was have to rendezvoused with several defunct American satellites. However it was only known to have conducted operations with its own Minotaur upper stage

• USA 185 Nation: USA. Payload: Streak STP-R1. Mass: 417 kg (919 lb). Agency: DARPA. Manufacturer: General Dynamics C4 Systems. Perigee: 295 km (183 mi). Apogee: 318 km (197 mi). Inclination: 96.30 deg. Period: 90.70 min. COSPAR: 2005-037A. USAF Sat Cat: 28871. Delayed from May, June, July, 2005. Classified research satellite, said to carry instruments to characterise the space environment in a sun-synchronous orbit.

• Formosat 3A Nation: Taiwan. Mass: 70 kg (154 lb). Class: Technology. Spacecraft: MicroStar. Agency: NSPO. Manufacturer: OSC. Perigee: 496 km (308 mi). Apogee: 538 km (334 mi). Inclination: 72.00 deg. Period: 95.00 min. COSPAR: 2006-011A. USAF Sat Cat: 29047. FORMOSAT-3 consisted of six small 62 kg Orbcomm-type satellites with GPS receivers which were to measure atmospheric conditions by studying the effect of the atmosphere on GPS satellite signals passing through it. The satellites, also known as COSMIC (Constellation Observing System for Meteorology, Ionosphere and Climate), would eventually be positioned in equally spaced orbit planes at around 800 km altitude.

• Formosat 3B Nation: Taiwan. Mass: 70 kg (154 lb). Class: Technology. Spacecraft: MicroStar. Agency: NSPO. Manufacturer: OSC. Perigee: 500 km (310 mi). Apogee: 541 km (336 mi). Inclination: 72.00 deg. Period: 95.00 min. COSPAR: 2006-011B. USAF Sat Cat: 29048.

• Formosat 3C Nation: Taiwan. Mass: 70 kg (154 lb). Class: Technology. Spacecraft: MicroStar. Agency: NSPO. Manufacturer: OSC. Perigee: 567 km (352 mi). Apogee: 681 km (423 mi). Inclination: 72.00 deg. Period: 97.20 min. COSPAR: 2006-011C. USAF Sat Cat: 29049.

• Formosat 3D Nation: Taiwan. Mass: 70 kg (154 lb). Class: Technology. Spacecraft: MicroStar. Agency: NSPO. Manufacturer: OSC. Perigee: 496 km (308 mi). Apogee: 538 km (334 mi). Inclination: 72.00 deg. Period: 95.00 min. COSPAR: 2006-011D. USAF Sat Cat: 29050.

• Formosat 3E Nation: Taiwan. Mass: 70 kg (154 lb). Class: Technology. Spacecraft: MicroStar. Agency: NSPO. Manufacturer: OSC. Perigee: 496 km (308 mi). Apogee: 538 km (334 mi). Inclination: 72.00 deg. Period: 95.00 min. COSPAR: 2006-011E. USAF Sat Cat: 29051.

• Formosat 3F Nation: Taiwan. Mass: 70 kg (154 lb). Class: Technology. Spacecraft: MicroStar. Agency: NSPO. Manufacturer: OSC. Perigee: 497 km (308 mi). Apogee: 542 km (336 mi). Inclination: 72.00 deg. Period: 95.00 min. COSPAR: 2006-011F. USAF Sat Cat: 29052.

• Tacsat-2 Nation: USA. Mass: 370 kg (810 lb). Class: Surveillance. Type: Military. Spacecraft: Tacsat-2. Agency: AFRL. Manufacturer: MicroSat Systems. Perigee: 410 km (250 mi). Apogee: 426 km (264 mi). Inclination: 40.01 deg. Period: 92.93 min. COSPAR: 2006-058A. USAF Sat Cat: 29653. Tacsat-2 was a prototype rapid development/rapid deployment tactical military satellite that provided American Joint Task Force commanders direct control of a satellite providing both SIGINT and imagery with a resolution of better than 1-m. The known communications payload used an 8 GHz (X-band) downlink. This was the first orbital launch from Wallops Island since 1985. TacSat-2 was to have been launched by a Falcon-1 from Vandenberg into a sun-synchronous orbit. However, the failure of Falcon-1 on its long-delayed maiden in March 2006 caused AFRL to award a new launch contract for TacSat-2 and TacSat-3 to OSC in May 2006. The launch was achieved using OSC's Minotaur launch vehicle only seven months after contract award.

• GeneSat-1 Nation: USA. Mass: 7.00 kg (15.40 lb). Class: Biosat. Spacecraft: GeneSat. Agency: NASA. Manufacturer: NASA Ames. Perigee: 410 km (250 mi). Apogee: 426 km (264 mi). Inclination: 40.01 deg. Period: 92.93 min. COSPAR: 2006-058B. USAF Sat Cat: 29654. Nanosatellite launched as a secondary payload. A collaboration of NASA, industry, and local universities resulted in this fully-automated, miniaturized spaceflight system that provided life support, nutrient delivery, and performed assays to monitor genetic changes of E. coli bacteria in space conditions.

• TLV-5 / SBX Target Nation: USA.

• NFIRE Nation: USA. Payload: SA-200B. Mass: 494 kg (1,089 lb). Class: Technology. Spacecraft: SA-200. Agency: USAFRL. Manufacturer: Spectrum Astro. Perigee: 489 km (303 mi). Apogee: 497 km (308 mi). Inclination: 48.20 deg. Period: 94.50 min. COSPAR: 2007-014A. USAF Sat Cat: 31140. Near Field Infrared Experiment conducted by the US Missile Defense Agency. Its Track Sensor Payload included visible and short, medium and long wave infrared sensors to observe missiles launched from the ground, and obtain basic data to distinguish between the missile and its hot rocket exhaust plume for application to anti-ballistic missile systems. Secondary payloads included Tesat, a German laser communications terminal, and its hydrazine propulsion system. This was used to maneuver the satellite from its initial 255 km x 465 km x 48.2 deg orbit to 489 km x 497 km by 18 May. The orbit was changed to 243 km x 487 km on 9 August and by 23 August was 219 km x 450 km. The satellite had a dry mass of 380 kg dry, was 2.7 m long and 1.3 m in diameter.

  The first major sensor test occurred when Minotaur II rocket TLV-7, was fired at 08:30 GMT on 23 August from Vandenberg in NFIRE Mission 2a. The Minotaur II was aimed to pass within 4 and 20 km of the NFIRE satellite while its third stage motor burning, to allow NFIRE to get a close look at the rocket and its exhaust. The Missile Defense Agency reported that the experiment was successful.

• TLV-7 Payload: NFIRE 2a. Agency: USAF. Apogee: 1,300 km (800 mi). Mission 2a sensor target for the NFIRE satellite. The Minotaur II, a three-stage refurbished Minuteman 2 missile with a new guidance and payload section, was aimed to pass within 4 and 20 km of the NFIRE satellite while its third stage motor was burning, to allow NFIRE's sensors to characterize the the rocket and its exhaust. The Missile Defense Agency reported that Mission 2a was successful.

• McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Jonathan McDowell's complete on-line listing of all objects orbited and over 20,000 rocket launches Accessed at: http://www.planet4589.org/jsr.html.

• California SpacePort Home Page, . Accessed at: http://www.calspace.com/.

• Isakowitz, Steven J, Hopkins, Joshua B, and Hopkins, Joseph P, International Reference to Space Launch Systems, AIAA, Washington DC, 2004. ISBN: 156347591X. The best reference on launch vehicles ever produced. More at amazon.com...