Launch vehicle and nominal sequence of orbital injection
Abstract
The structural and propulsion elements of the three-stage Delta 2913 launch vehicle are examined. The Delta launcher was chosen because its performance capacity made it possible to achieve a 90-degree inclination of the satellite's orbital plane, thereby providing a long useful time in orbit (part of the orbit outside of the Van Allen belts), a ground coverage of 90% of useful time in orbit, and great flexibility in the observation program. The sequence of events following ignition at lift-off to separation of the spacecraft from the third stage, 53 min after lift-off is discussed and illustrated.
- Publication:
-
ESA Bulletin
- Pub Date:
- August 1975
- Bibcode:
- 1975ESABu.......31.
- Keywords:
-
- Cos-B Satellite;
- Launch Vehicles;
- Spacecraft Launching;
- Control Stability;
- European Space Programs;
- Ground Based Control;
- Inertial Platforms;
- Orbit Calculation;
- Satellite Observation;
- Spacecraft Guidance;
- Spacecraft Propulsion;
- Strapdown Inertial Guidance;
- Launch Vehicles and Space Vehicles