Taurus Media Gallery

Pad-launched launch vehicle using Pegasus upper stages and Castor-120 first stage. First launch used slightly larger Peacekeeper ICBM first stage instead of Castor-120. Under a 2002 contract from Boeing, Orbital developed a three-stage version of Taurus to serve as the interceptor boost vehicles for the US government's missile intercept system. The firm portion of the company's contract, awarded in early 2002, was valued at $450 million and extended through 2007.

The Taurus rocket offered an affordable, reliable means of launching small satellites into low-Earth orbit. Developed under the sponsorship of the Defense Advanced Research Projects Agency (DARPA), Taurus was designed for easy transportability and rapid set-up and launch and was a ground-based variant of Orbital's air-launched Pegasus rocket. The four-stage, inertially guided, all solid propellant vehicle could deploy a 1,350-kilogram satellite into low-Earth orbit. Two fairing sizes offered flexibility in designing a particular mission. The addition of a structural adapter allowed launch of multiple payloads.

The Taurus incorporated a simplified integration and test capability that included horizontal integration of the rocket's upper stages and offline encapsulation of the payload within the fairing. The upper stages and the encapsulated cargo were delivered to the launch site, where they were mated. The whole assembly was then stacked on the first stage using a mobile crane.

The Taurus launch system included a complete set of ground support equipment to ensure the ability to operate from austere sites. Taurus was approved for launch from the US Government's Western range at Vandenberg Air Force Base (VAFB), Cape Canaveral Air Station (CCAS) in Florida, Wallops Flight Facility (WFF) in Virginia, and Kodiak Launch Complex, Alaska.

Manufacturer: OSC. Launches: 8. Failures: 1. Success Rate: 87.50%. First Launch Date: 1989-12-21. Last Launch Date: 2004-05-20. Launch data is: continuing. LEO Payload: 1,363 kg (3,004 lb). to: 185 km Orbit. at: 28.50 degrees. Payload: 431 kg (950 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: ACRIMSAT , Celestis, DARPASAT, GFO, KOMPSAT, Microstar, MTI, Orbview, QuikTOMS, SBD, STEX, TAOS, TiPS. Liftoff Thrust: 1,286.400 kN (289,194 lbf). Total Mass: 73,030 kg (161,000 lb). Core Diameter: 2.36 m (7.74 ft). Total Length: 27.90 m (91.50 ft). Launch Price $: 20.000 million. in: 1999 price dollars.

4 stage version consisting of 1 x TU-904 + 1 x Orion 50 + 1 x Orion 50 + 1 x Orion 38

LEO Payload: 1,320 kg (2,910 lb). Apogee: 1,000 km (600 mi). Liftoff Thrust: 1,711.000 kN (384,648 lbf). Total Mass: 73,000 kg (160,000 lb). Core Diameter: 2.35 m (7.70 ft). Total Length: 27.90 m (91.50 ft).

LEO Payload: 1,320 kg (2,910 lb).

LEO Payload: 1,380 kg (3,040 lb).

LEO Payload: 1,380 kg (3,040 lb).

• Stage Number: 1. 1 x Stage: Castor 120. Gross Mass: 53,020 kg (116,880 lb). Empty Mass: 4,211 kg (9,283 lb). Thrust (vac): 1,606.594 kN (361,177 lbf). Isp: 286 sec. Burn time: 83 sec. Isp(sl): 229 sec. Diameter: 2.36 m (7.74 ft). Span: 2.36 m (7.74 ft). Length: 10.70 m (35.10 ft). Propellants: Solid. No Engines: 1. Engine: Castor 120. Modification of Peackeeper ICBM first stage.

• Stage Number: 2. 1 x Stage: Taurus-1. Gross Mass: 13,242 kg (29,193 lb). Empty Mass: 1,088 kg (2,398 lb). Thrust (vac): 484.909 kN (109,012 lbf). Isp: 285 sec. Burn time: 73 sec. Diameter: 1.27 m (4.16 ft). Span: 1.27 m (4.16 ft). Length: 7.60 m (24.90 ft). Propellants: Solid. No Engines: 1. Engine: Pegasus-1. Pegasus stage 1 without the wings and stabilisers.

• Stage Number: 3. 1 x Stage: Pegasus-2. Gross Mass: 3,370 kg (7,420 lb). Empty Mass: 345 kg (760 lb). Thrust (vac): 118.199 kN (26,572 lbf). Isp: 292 sec. Burn time: 73 sec. Isp(sl): 240 sec. Diameter: 1.27 m (4.16 ft). Span: 1.27 m (4.16 ft). Length: 2.65 m (8.69 ft). Propellants: Solid. No Engines: 1. Engine: Pegasus-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.

1989 December 21 - 20:06 GMT - Launch Site: Wallops Island. Launch Vehicle: Taurus. LV Configuration: Taurus NASA 12.43WT.

• Test mission Nation: USA. Agency: NASA. Apogee: 10 km (6 mi). References: 931.

• USA 101 Nation: USA. Program: STEP. Payload: STEP-0 / STEP M0. Mass: 502 kg (1,106 lb). Class: Military. Type: SDI. Spacecraft: TAOS. Agency: USAF. Perigee: 555 km (344 mi). Apogee: 561 km (348 mi). Inclination: 105.00 deg. Period: 95.80 min. COSPAR: 1994-017A. USAF Sat Cat: 23030. Space Test Experiment Program; 10 satellite subsystem experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• USA 102 Nation: USA. Payload: DarpaSat. Mass: 203 kg (447 lb). Class: Technology. Spacecraft: DARPASAT. Agency: DARPA. Perigee: 532 km (330 mi). Apogee: 556 km (345 mi). Inclination: 105.00 deg. Period: 95.50 min. COSPAR: 1994-017B. USAF Sat Cat: 23031. GPS receiver and data processor technology tests. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• GFO Nation: USA. Class: Earth. Type: Radarsat. Spacecraft: GFO. Agency: USN. Manufacturer: Ball Aerospace, Boulder. Perigee: 786 km (488 mi). Apogee: 788 km (489 mi). Inclination: 108.10 deg. Period: 100.60 min. COSPAR: 1998-007A. USAF Sat Cat: 25157. Altimeter. References: 4, 276.

• Orbcomm G1 Nation: USA. Program: Orbcomm. Payload: Orbcomm s/n FM3. Class: Communications. Spacecraft: Microstar. Agency: Orbcomm. Manufacturer: Orbital Sciences Corp., Germantown (formerly Fairchild). Perigee: 781 km (485 mi). Apogee: 874 km (543 mi). Inclination: 107.99 deg. Period: 101.46 min. COSPAR: 1998-007B. USAF Sat Cat: 25158. Plane G. Ascending node 297.9 degrees. References: 4, 276.

• Orbcomm G2 Nation: USA. Program: Orbcomm. Payload: Orbcomm s/n FM4. Class: Communications. Spacecraft: Microstar. Agency: Orbcomm. Manufacturer: Orbital Sciences Corp., Germantown (formerly Fairchild). Perigee: 783 km (486 mi). Apogee: 871 km (541 mi). Inclination: 107.99 deg. Period: 101.45 min. COSPAR: 1998-007C. USAF Sat Cat: 25159. Plane G. Ascending node 298.1 degrees. References: 4, 276.

• Celestis-02 Nation: USA. Payload: Celestis-02/Orion 38. Class: Burial . Spacecraft: Celestis. Agency: OSC. Manufacturer: Orbital Sciences Corp., Germantown (formerly Fairchild). Perigee: 780 km (480 mi). Apogee: 876 km (544 mi). Inclination: 108.00 deg. Period: 101.50 min. COSPAR: 1998-007D. USAF Sat Cat: 25160. References: 4.

• STEX Nation: USA. Payload: STEX. Class: Technology. Type: Ion Engine. Spacecraft: STEX. Agency: NRO. Manufacturer: Naval Research Lab, Washington, DC. Perigee: 744 km (462 mi). Apogee: 759 km (472 mi). Inclination: 84.99 deg. Period: 99.77 min. COSPAR: 1998-055A. USAF Sat Cat: 25489. Tested TAL-D55 plasma engine and was to be part of the NRO's ATex tether experiment. The ATeX lower end mass was meant to remain attached to the STEX parent spacecraft, but with only 21 m of tether deployed, it appeared the tether was so far off vertical that automatic safety systems jettisoned the base to protect the remainder of the STEX satellite. Thus, the upper and lower ATeX end masses were in orbit as one object connected by a 21 m tether, and designated USA 141 (1998-055C). The main STEX satellite was in orbit as a separate object, 1998-055A.References: 279.

• USA 141 Nation: USA. Payload: ATEX. Class: Technology. Type: Tether. Spacecraft: TiPS. Agency: NRO/NRL. Perigee: 750 km (466 mi). Apogee: 766 km (476 mi). Inclination: 84.99 deg. Period: 99.90 min. COSPAR: 1998-055C. USAF Sat Cat: 25615. NRO's ATeX (Advanced Tether eXperiment) reportedly failed on January 16. The ATeX lower end mass was meant to remain attached to the STEX parent spacecraft, but with only 21 m of tether deployed, it appeared the tether was so far off vertical that automatic safety systems jettisoned the base to protect the remainder of the STEX satellite. Thus, the upper and lower ATeX end masses were in orbit as one object connected by a 21 m tether, and designated USA 141 (1998-055C). The main STEX satellite was in orbit as a separate object, 1998-055A.References: 279.

• Kompsat Nation: Korea South. Payload: Arirang. Mass: 470 kg (1,030 lb). Class: Earth. Type: Oceansat. Spacecraft: KOMPSAT. Agency: KARI. Manufacturer: Korea Advanced Institute for Space Technology. Perigee: 690 km (420 mi). Apogee: 722 km (448 mi). Inclination: 98.30 deg. COSPAR: 1999-070A. USAF Sat Cat: 26032. Korean Multipurpose Satellite; carried an ocean color sensor developed by TRW and particle detectors. KOMPSAT was built by the Korean Aerospace Research Institute (KARI) based on a test model built by TRW; it used the TRW STEP Lightsat bus and had a mass of around 500 kg, with 73 kg of hydrazine fuel.References: 4, 552, 554.

• ACRIMSAT Nation: USA. Mass: 115 kg (253 lb). Class: Earth. Spacecraft: ACRIMSAT . Agency: NASA/JPL. Manufacturer: Orbital Sciences Corp., Germantown. Perigee: 683 km (424 mi). Apogee: 724 km (449 mi). Inclination: 98.30 deg. COSPAR: 1999-070B. USAF Sat Cat: 26033. Measured the integrated solar energy output from 0.2 to 2 microns. Carried instrument deleted from Terra spacecraft. References: 4, 552, 554.

• Celestis-03 Nation: USA. Class: Burial. Spacecraft: Celestis. Agency: OSC. Perigee: 683 km (424 mi). Apogee: 723 km (449 mi). Inclination: 98.30 deg. COSPAR: 1999-070C. USAF Sat Cat: 26034. Decay Date: 1971-03-01. Burial satellite containing cremated human remains. References: 4, 552, 554.

• MTI Nation: USA. Mass: 587 kg (1,294 lb). Class: Surveillance. Type: Military. Spacecraft: MTI. Agency: Sandia. Manufacturer: Sandia/LANL. Perigee: 574 km (357 mi). Apogee: 609 km (378 mi). Inclination: 97.40 deg. Period: 96.42 min. COSPAR: 2000-014A. USAF Sat Cat: 26102. Military Technology. Sandia Multispectral Thermal Imager (MTI), aka USAF Space Test Program mission P97-3. The satellite was equipped with a hyperspectral imager for military target recognition / treaty monitoring applications. References: 4, 552, 554.

• Orbview-4 Nation: USA. Mass: 368 kg (811 lb). Class: Surveillance. Type: Civilian. Spacecraft: Orbview. Agency: Orbimage (U.S.). Manufacturer: Orbital Sciences Corp. COSPAR: F010921A. Launch delayed from June 27, July 18/22, August 12/21 and September1. The Orbital Sciences Taurus 2110 failed to remain in orbit. A problem a few seconds after first stage separation caused the T6 rocket to go off course; the rocket recovered and the remainder of the stages fired, but final cutoff velocity was too low to reach a sustainable orbit. The Castor 120 zero stage was on course but the Orion 50S first stage motor went off course. The satellites separated from the final stage as planned but burned up in the earth's atmosphere northeast of Madagascar before completing the first orbit. The final orbit was about 75-80 km x 425-430 km x 97 deg. The primary payload was the OrbView-4 imaging satellite. OrbView-4, built by Orbital, was a 368 kg box-shaped spacecraft carrying a 1-m resolution panchromatic camera and an 8-m resolution 200-channel hyperspectral imager with a 0.45-meter aperture. It was to be used by the US Air Force.References: 4, 552, 554.

• QuikTOMS Nation: USA. Mass: 368 kg (811 lb). Class: Earth. Type: Ionosphere. Spacecraft: Microstar. Agency: Orbimage (U.S.). Manufacturer: Orbital Sciences Corp. COSPAR: F010921B. The QuikTOMS satellite was a NASA-GSFC project carrying the TOMS-5 ozone mapper. QuikTOMS used a 168 kg double Microstar bus and was to have replaced TOMS instruments on a delayed Russian weather satellite and the failed ADEOS. The loss of QuikTOMS put a hole in NASA's attempts to monitor the ozone layer.References: 4, 552, 554.

• SBD Nation: USA. Mass: 368 kg (811 lb). Class: Technology. Spacecraft: SBD. Agency: Orbimage (U.S.). Manufacturer: Orbital Sciences Corp. COSPAR: F010921C. SBD, the Orbital Sciences' Special Bus Design. The 73 kg satellite was a test version of an enlarged Microstar bus. It would have remained attached to the third stage, together with two Celestis burial canisters containing cremated human remains, and an experimental third stage avionics box.References: 4, 552, 554.

• Celestis-4 Nation: USA. Mass: 368 kg (811 lb). Class: Burial. Spacecraft: Celestis. Agency: Orbimage (U.S.). Manufacturer: Orbital Sciences Corp. COSPAR: F010921D. Celestis-4 consisted of two Celestis burial canisters containing cremated human remains. After the launch vehicle failure Celestis guaranteed a relaunch of back-up remains. References: 4, 552, 554.

• ROCSAT 2 Nation: Taiwan. Payload: LeoStar 500XO. Mass: 760 kg (1,670 lb). Class: Surveillance. Type: Civilian. Spacecraft: ROCSAT. Agency: NSPO (Taiwan). Manufacturer: EADS Astrium. Perigee: 887 km (551 mi). Apogee: 891 km (553 mi). Inclination: 99.10 deg. Period: 102.80 min. COSPAR: 2004-018A. USAF Sat Cat: 28254. Delayed from October, November 25, 2003; January 17, February 26, April 9 and 22, May 17, 2004.

• 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.

• Hesse, Walter J and Mumford, Nicholas VS Jr;, Jet Propulsion for Aerospace Applications - Second Edition, Pitman Publishing, New York, 1964. This textbook, produced in the mid-1960's, remains the best introduction to jet propulsion for air and spacecraft.