Pegasus Media Gallery

Privately-funded, air-launched winged light satellite launcher. 4 stage vehicle consisting of 1 x NB-52 + 1 x Orion 50S + 1 x Orion 50 + 1 x Orion 38.

Manufacturer: OSC. Launches: 11. Failures: 1. Success Rate: 90.91%. First Launch Date: 1990-04-05. Last Launch Date: 2004-11-16. Launch data is: continuing. LEO Payload: 375 kg (826 lb). to: 200 km Orbit. Associated Spacecraft: Alexis, APEX, CDS, Eagle, GLOMR, HETE, Microlab, Microstar, MSTI, Orbcomm, Pegsat, SCD. Liftoff Thrust: 486.640 kN (109,401 lbf). Total Mass: 19,000 kg (41,000 lb). Core Diameter: 1.27 m (4.16 ft). Total Length: 15.50 m (50.80 ft). Development Cost $: 55.000 million. in: 1999 average dollars. Launch Price $: 11.000 million. in: 1994 price dollars.

4 stage vehicle consisting of 1 x NB-52 + 1 x Orion 50S + 1 x Orion 50 + 1 x Orion 38.

LEO Payload: 375 kg (826 lb). to: 200 km Orbit. Liftoff Thrust: 486.640 kN (109,401 lbf). Total Mass: 19,000 kg (41,000 lb). Core Diameter: 1.27 m (4.16 ft). Total Length: 15.50 m (50.80 ft).

4 stage vehicle consisting of 1 x L-1011 + 1 x Orion 50S + 1 x Orion 50 + 1 x Orion 38

LEO Payload: 350 kg (770 lb). Apogee: 4,000 km (2,400 mi). Liftoff Thrust: 580.000 kN (130,380 lbf). Total Mass: 18,500 kg (40,700 lb). Core Diameter: 1.28 m (4.19 ft). Total Length: 15.50 m (50.80 ft).

5 stage version consisting of 1 x NB-52 + 1 x Orion 50S + 1 x Orion 50 + 1 x Orion 38 + 1 x HAPS

LEO Payload: 250 kg (550 lb). Apogee: 4,000 km (2,400 mi). Liftoff Thrust: 580.000 kN (130,380 lbf). Total Mass: 18,500 kg (40,700 lb). Core Diameter: 1.28 m (4.19 ft). Total Length: 15.50 m (50.80 ft).

• Stage Number: 0. 1 x Stage: L-1011. Gross Mass: 156,000 kg (343,000 lb). Empty Mass: 109,629 kg (241,690 lb). Thrust (vac): 561.900 kN (126,320 lbf). Isp: 9,900 sec. Burn time: 4,590 sec. Isp(sl): 9,000 sec. Diameter: 16.86 m (55.31 ft). Span: 47.00 m (154.00 ft). Length: 54.00 m (177.00 ft). Propellants: Air/Kerosene. No Engines: 3. Engine: RB-211-22B. Lockheed airliner swept wing. Release conditions: Belly-mounted, 36,800 kg, 17.1 m length x 7.9 m span at 925 kph at 11,890 m altitude

• Stage Number: 1. 1 x Stage: Pegasus-1. Gross Mass: 14,020 kg (30,900 lb). Empty Mass: 1,868 kg (4,118 lb). Thrust (vac): 484.909 kN (109,012 lbf). Isp: 294 sec. Burn time: 72 sec. Isp(sl): 180 sec. Diameter: 1.27 m (4.16 ft). Span: 6.71 m (22.01 ft). Length: 8.88 m (29.13 ft). Propellants: Solid. No Engines: 1. Engine: Pegasus-1.

• Stage Number: 2. 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: 3. 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.

• Stage Number: 4. 1 x Stage: Pegasus-4. Gross Mass: 90 kg (198 lb). Empty Mass: 17 kg (37 lb). Thrust (vac): 666 N (149 lbf). Isp: 236 sec. Burn time: 241 sec. Isp(sl): 0 sec. Diameter: 0.97 m (3.18 ft). Span: 0.97 m (3.18 ft). Length: 0.25 m (0.82 ft). Propellants: Hydrazine. No Engines: 3. Engine: MR-107.

1990 April 5 - 19:10 GMT - Launch Site: Edwards. Launch Complex: RW04. Launch Pad: NB-52 008. Launch Vehicle: Pegasus. Model: Pegasus. LV Configuration: Pegasus 001/F1.

• Pegsat Nation: USA. Payload: Pegsat / Orion 38. Mass: 178 kg (392 lb). Class: Earth. Type: Magnetosphere. Spacecraft: Pegsat. Agency: NASA GSF. Perigee: 401 km (249 mi). Apogee: 507 km (315 mi). Inclination: 94.10 deg. Period: 93.70 min. COSPAR: 1990-028A. USAF Sat Cat: 20546. Decay Date: 1998-11-14. Chemical release experiment. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• USA 55 Nation: USA. Payload: GLOMR 2 / TERCEL / SECS. Mass: 25 kg (55 lb). Class: Communications. Type: Military. Spacecraft: GLOMR. Agency: DARPA/US. Perigee: 477 km (296 mi). Apogee: 642 km (398 mi). Inclination: 94.10 deg. Period: 95.90 min. COSPAR: 1990-028B. USAF Sat Cat: 20547. Store and forward. References: 1, 2, 5, 6.

• Microsat 1 Nation: USA. Payload: Microsat 1 / ... / Microsat 7. Mass: 22 kg (48 lb). Class: Technology. Type: Comsat. Spacecraft: Microsat. Agency: DARPA. Perigee: 356 km (221 mi). Apogee: 454 km (282 mi). Inclination: 82.00 deg. Period: 92.70 min. COSPAR: 1991-051A. USAF Sat Cat: 21580. Decay Date: 1992-01-23. Test of LEO network for global communications. References: 1, 2, 5, 6.

• Microsat 2 Nation: USA. Mass: 22 kg (48 lb). Class: Technology. Type: Comsat. Spacecraft: Microsat. Agency: DARPA. Perigee: 355 km (220 mi). Apogee: 454 km (282 mi). Inclination: 82.00 deg. Period: 92.70 min. COSPAR: 1991-051B. USAF Sat Cat: 21581. Decay Date: 1992-01-23. Test of LEO network for global communications. References: 1, 2, 5, 6.

• Microsat 3 Nation: USA. Mass: 22 kg (48 lb). Class: Technology. Type: Comsat. Spacecraft: Microsat. Agency: DARPA. Perigee: 355 km (220 mi). Apogee: 454 km (282 mi). Inclination: 82.00 deg. Period: 92.70 min. COSPAR: 1991-051C. USAF Sat Cat: 21582. Decay Date: 1992-01-24. Test of LEO network for global communications. References: 1, 2, 5, 6.

• Microsat 4 Nation: USA. Mass: 22 kg (48 lb). Class: Technology. Type: Comsat. Spacecraft: Microsat. Agency: DARPA. Perigee: 355 km (220 mi). Apogee: 454 km (282 mi). Inclination: 82.00 deg. Period: 92.70 min. COSPAR: 1991-051D. USAF Sat Cat: 21583. Decay Date: 1992-01-23. Test of LEO network for global communications. References: 1, 2, 5, 6.

• Microsat 5 Nation: USA. Mass: 22 kg (48 lb). Class: Technology. Type: Comsat. Spacecraft: Microsat. Agency: DARPA. Perigee: 355 km (220 mi). Apogee: 455 km (282 mi). Inclination: 82.00 deg. Period: 92.70 min. COSPAR: 1991-051E. USAF Sat Cat: 21584. Decay Date: 1992-01-24. Test of LEO network for global communications. References: 1, 2, 5, 6.

• Microsat 6 Nation: USA. Mass: 22 kg (48 lb). Class: Technology. Type: Comsat. Spacecraft: Microsat. Agency: DARPA. Perigee: 355 km (220 mi). Apogee: 454 km (282 mi). Inclination: 82.00 deg. Period: 92.70 min. COSPAR: 1991-051F. USAF Sat Cat: 21585. Decay Date: 1992-01-25. Test of LEO network for global communications. References: 1, 2, 5, 6.

• Microsat 7 Nation: USA. Mass: 22 kg (48 lb). Class: Technology. Type: Comsat. Spacecraft: Microsat. Agency: DARPA. Perigee: 358 km (222 mi). Apogee: 452 km (280 mi). Inclination: 82.00 deg. Period: 92.70 min. COSPAR: 1991-051G. USAF Sat Cat: 21586. Decay Date: 1992-01-23. Test of LEO network for global communications. References: 1, 2, 5, 6.

• Orbcomm OXP-1 Nation: USA. Payload: Orbcomm CDS. Mass: 15 kg (33 lb). Class: Communications. Spacecraft: CDS. Agency: Orbcomm. Perigee: 731 km (454 mi). Apogee: 794 km (493 mi). Inclination: 25.00 deg. Period: 100.10 min. COSPAR: 1993-009A. USAF Sat Cat: 22489. Experimental spacecraft. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• SCD-1 Nation: Brazil. Payload: SCD 1 / Orbcomm CDS. Mass: 115 kg (253 lb). Class: Communications. Spacecraft: SCD. Agency: INPE. Perigee: 729 km (452 mi). Apogee: 793 km (492 mi). Inclination: 25.00 deg. Period: 100.10 min. COSPAR: 1993-009B. USAF Sat Cat: 22490. Environmental data relay. The SCD-1 (Data Collection Satellite 1) was a Brazilian satellite designed for the collection of meteorological data relayed by data collection platforms spread throughout the Brazilian territory. References: 1, 2, 5, 6.

• Alexis Nation: USA. Payload: Alexis (P 89-1B). Mass: 115 kg (253 lb). Class: Astronomy. Spacecraft: Alexis. Agency: USAF STP. Perigee: 741 km (460 mi). Apogee: 746 km (463 mi). Inclination: 69.80 deg. Period: 99.70 min. COSPAR: 1993-026A. USAF Sat Cat: 22638. Test of X-ray imaging sensors; solar array deployment malfunction. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• Orbcomm OXP-2 Nation: USA. Payload: VSUM. Spacecraft: Orbcomm. Agency: OSC. Perigee: 752 km (468 mi). Apogee: 843 km (524 mi). Inclination: 69.92 deg. Period: 100.74 min. COSPAR: 1993-026B. USAF Sat Cat: 22639. References: 279.

• STEP 2 (SIDEX) Nation: USA. Program: STEP. Payload: STEP M2 / P 91-A. Mass: 180 kg (390 lb). Class: Military. Type: SDI. Spacecraft: Eagle. Agency: USAF STP. Perigee: 597 km (370 mi). Apogee: 813 km (505 mi). Inclination: 82.00 deg. Period: 98.90 min. COSPAR: 1994-029A. USAF Sat Cat: 23105. Did not achieve planned orbit, though still useful. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• P90-6 APEX Nation: USA. Payload: APEX/Orion 38. Mass: 260 kg (570 lb). Class: Technology. Spacecraft: APEX. Agency: USAF STP. Perigee: 360 km (220 mi). Apogee: 2,534 km (1,574 mi). Inclination: 69.98 deg. Period: 114.82 min. COSPAR: 1994-046A. USAF Sat Cat: 23191. Advanced Photovoltaic and Electronic Experiments; studied radiation and plasma effects on solar power systems. References: 2, 5, 6.

• Orbcomm F1 Nation: USA. Program: Orbcomm. Payload: Orbcomm s/n FM1. Mass: 40 kg (88 lb). Class: Communications. Spacecraft: Microstar. Agency: Orbcomm. Perigee: 728 km (452 mi). Apogee: 747 km (464 mi). Inclination: 69.98 deg. Period: 99.56 min. COSPAR: 1995-017A. USAF Sat Cat: 23545. Commercial communications testbed. Plane F. Ascending node 199.1 degrees. References: 2, 5, 6.

• Orbcomm F2 Nation: USA. Program: Orbcomm. Payload: Orbcomm s/n FM2. Mass: 40 kg (88 lb). Class: Communications. Spacecraft: Microstar. Agency: Orbcomm. Perigee: 728 km (452 mi). Apogee: 747 km (464 mi). Inclination: 69.98 deg. Period: 99.56 min. COSPAR: 1995-017B. USAF Sat Cat: 23546. Commercial communications testbed. Plane F. Ascending node 198.5 degrees. References: 2, 5, 6.

• Orbview-1 Nation: USA. Payload: Microlab 1. Mass: 74 kg (163 lb). Class: Earth. Type: Atmosphere. Spacecraft: Microstar. Agency: Orbimage. Perigee: 733 km (455 mi). Apogee: 747 km (464 mi). Inclination: 70.00 deg. Period: 99.60 min. COSPAR: 1995-017C. USAF Sat Cat: 23547. Lightning mapper; GPS radio occultation. References: 2, 5, 6.

• MSTI-3 Nation: USA. Payload: MSTI 3. Class: Military. Type: SDI. Spacecraft: MSTI. Agency: BMDO. Perigee: 420 km (260 mi). Apogee: 432 km (268 mi). Inclination: 97.10 deg. Period: 90.70 min. COSPAR: 1996-031A. USAF Sat Cat: 23868. Decay Date: 1997-12-11. LEO. Sensor technology tests References: 4, 6, 276.

• SCD-2 Nation: Brazil. Mass: 110 kg (240 lb). Class: Communications. Spacecraft: SCD. Agency: INPE. Manufacturer: Instituto Nacional de Pesquisas Espacias, Sao Jose dos Campos. Perigee: 742 km (461 mi). Apogee: 768 km (477 mi). Inclination: 25.00 deg. COSPAR: 1998-060A. USAF Sat Cat: 25504. Brazil's SCD-2 satellite was aboard Orbital Science's L-1011 Stargazer aircraft when it took off from the Cape Canaveral Air Station's Skid Strip (Runway 02/20, 28.2N 80.6W) at 23:05 GMT on Oct 22 and flew to the drop zone near Cape Canaveral (in the Mayport, Florida, Warning Area) at 29.0N 78.3W. The Pegasus ignited 5 seconds after drop. The first stage carried a NASA experiment attached to its right wing, to study hypersonic boundary layer separation. The 115 kg Satelite de Coleta de Dados (Data Collection Satellite) relays data from environmental monitoring stations.

• HETE-2 Nation: USA. Mass: 130 kg (280 lb). Class: Astronomy. Spacecraft: HETE. Agency: NASA GSF. Manufacturer: Massachusetts Institute of Technology. Perigee: 598 km (372 mi). Apogee: 641 km (399 mi). Inclination: 1.95 deg. Period: 97.02 min. COSPAR: 2000-061A. USAF Sat Cat: 26561. First orbital launch from Kwajalein. Second High Energy Transient Explorer; built by MIT using leftover parts from the first HETE. This failed to operate because of a Pegasus adapter failure during launch in November 1996. MIT operates the satellite, while the program is managed by NASA GSFC as an Explorer mission of opportunity. HETE's main instrument is FREGATE, the French Gamma Telescope, a hard X-ray spectrometer operating in the 6 to 400 keV energy range. This gamma ray burst detector, together with a Wide Field X-ray Monitor hard X-ray coded mask telescope, is used to trigger searches with the two Soft X-ray Imagers which have 33-arcsecond spatial resolution. This will let astronomers get precise locations for gamma-ray bursts, allowing detailed follow-up with optical instruments. The satellite is in a 595 x 636 km x 2.0 deg equatorial orbit, and sends data to a network of small ground terminals spaced around the equator.References: 4, 552, 554.

• X-43A Test mission Nation: USA. Class: Technology. Type: Spaceplane. Spacecraft: X-43. Agency: NASA. Apogee: 7.00 km (4.30 mi). Hypersonic scramjet vehicle test. The X-43A/Pegasus booster combination was air-launched at 7600 m altitude. However the booster disintegrated at Max-Q. The redesign of the launch profile and modifications to the booster would take NASA almost three years.References: 1823.

• X-43A-2 (Hyper X) Nation: USA. Mass: 1,400 kg (3,000 lb). Class: Technology. Type: Spaceplane. Spacecraft: X-43. Agency: NASA. Manufacturer: MicroCraft. The second X-43 launch incorporated modifications to the first flight vehicle, including an upgraded control system, redesigned autopilot, off-loaded rocket motor, and improved analytical models. The second flight was launched at 12,200 m instead of the 7600 m altitude of the failed first launch to reduce transonic aerodynamic loads and improve structural and control system margins. An offloaded Orion 50S solid rocket motor reduced maximum dynamic pressure during the flight.

• HXLV Nation: USA. Mass: 1,400 kg (3,000 lb). Class: Technology. Type: Spaceplane. Spacecraft: X-43. Agency: NASA. Manufacturer: ATK GASL. Delayed from September, November 9 and 15. Final test of NASA's X-43A-3 Hyper X hypersonic scramjet demonstrated air-frame integrated scramjet performance at speeds approaching Mach 10. Changes to the launch vehicle compared to Flight 2 included high-temperature thermal protection system tiles on the wing and fin leading edge, elimination of all ballast, a full propellant load on the ATK Orion 50S booster, lightweight aluminum structures, and updated control laws and aerodynamics.

• 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.

• Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition). ISBN: 1563473534. Superseded by the later editions. More at amazon.com...

• Wilson, Andrew, editor,, Jane's/Interavia Space Directory, Jane's Information Group, Coulsdon, Surrey, 1992 et al. ISBN: 0710618107. The most comprehensive source of information for current space projects. Too expensive for human beings and most libraries. More at amazon.com...