TEST OF THE INTELSAT III COMMUNICATION SPACECRAFT AND APOGEE MOTOR UNDER THE COMBINED EFFECTS OF SIMULATED ALTITUDE AND ROTATIONAL SPIN
Abstract
An Aerojet-General Corporation SVM-2 solid-propellant apogee rocket motor installed in an Engineering Model (EM-2) of the INTELSAT III communications spacecraft was fired while spinning at 100 rpm at a pressure altitude of 125,000 ft. The primary objective of the program was verification of vacuum performance of the apogee motor after being conditioned at 75 plus or minus 5F. Secondary objectives were to evaluate the thermal and mechanical interactions on the spacecraft as a result of the motor firing. Electrical heaters were utilized in the EM-2 to simulate the heat loads of the active electrical equipment contained in the actual spacecraft. Altitude ignition characteristics and ballistic performance are presented and discussed. Temperature-time histories of thermocouples placed at selected locations on the motor are presented. Spacecraft vibration data and motor exhaust plume heat flux data are also presented and discussed.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1967
- Accession Number
- AD0825758
Entities
People
- L. R. Bahor
- R. M. Brooksbank
Organizations
- Arnold Engineering Development Complex