Pegasus - A geosynchronous launch profile
Abstract
A preliminary propulsion design analysis for the launching of a small geosynchronous satellite aboard Pegasus was performed. The Pegasus is a low-cost system which can carry a 600 pound payload to 250 nautical mile polar orbits as well as larger payloads to lower altitude/lower inclination orbits or suborbital trajectories. It is 49.2 ft in length, has a diameter of 50 inches, and a gross weight of 41,000 lbs. The payload can have a length up to 72 in. and a diameter of 46 in. A 3-axis, gravity gradient, or spin-stabilized spacecraft can be achieved, or a number of small satellites can be inserted. The profile for the positioning of a geosynchronous satellite is presented with emphasis on the parametric effects of parking orbit altitude and launch site latitude on the BOL mass of the satellite. Based on these parameters, the propellant mass required for the Apogee Boost and Perigee Motor was calculated and the fourth stage sized. It was concluded that for an ideal 0 deg inclination launch a fourth stage modified Pegasus could place a 130-kg usable payload into geosynchronous orbit.
- Publication:
-
Annual AIAA/Utah State University 4th Conference on Small Satellites, Volume 1
- Pub Date:
- 1990
- Bibcode:
- 1990aiaa....1.....S
- Keywords:
-
- Apogee Boost Motors;
- Earth Orbital Environments;
- Pegasus Air-Launched Booster;
- Polar Orbits;
- Propulsion System Configurations;
- Synchronous Satellites;
- Engine Design;
- Perigees;
- Spacecraft Launching;
- Launch Vehicles and Space Vehicles