THERMAL AND DYNAMIC INVESTIGATION OF THE HUGHES ATS SPACECRAFT AND APOGEE MOTOR SYSTEM AT SIMULATED HIGH ALTITUDE (S/S SYNCHRONOUS SPACECRAFT THERMAL MODEL S/N T-4)
Abstract
An Applications Technology Satellite (ATS) spacecraft, modified for captive testing, was used in an investigation at near vacuum conditions to determine if various spacecraft components would overheat following operation of the apogee kick motor. The apogee motor system, a Jet Propulsion Laboratory solid-propellant rocket motor (S/N SR-28-3), was installed in ATS spacecraft (S/N T-4) and fired in a soft stand (nonspinning) which isolated the motor/spacecraft thermally and dynamically. The motor was ignited and operated at a pressure simulated altitude of 110,000 ft. The thermal data were recorded for 3600 sec after ignition at an average altitude of 125,000 ft. The highest temperature recorded was 935 F and was sensed on the apogee motor nozzle. The highest temperature recorded on the spacecraft was approximately 400 F and was sensed on the thermal barrier at 250 sec after apogee motor ignition. The highest spacecraft structural temperature was approximately 240 F, which was sensed 750 sec after apogee motor ignition. The spacecraft electronic component temperatures did not exceed 150 F throughout the entire 3600-sec heat soak period. The vibration data analysis indicated that the motor operation was relatively smooth, and no large power spectral density levels were found.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1966
- Accession Number
- AD0800083
Entities
People
- A. F. Domal
Organizations
- Arnold Engineering Development Complex