SCATHA's primary mission was to obtain information about the processes and effects of spacecraft charging, a phenomenon known to have contributed to several on-orbit satellite failures. The mission's specific objectives were to (1) obtain environmental and engineering data to allow the creation of design criteria, materials, techniques, tests and analytical methods to control charging of spacecraft surfaces and (2) collect scientific data about plasma wave interactions, substorms, and the energetic ring. (Spacecraft shown in stowed configuration, with experiment booms stowed). The spacecraft was also known as P78-2.
Spacecraft: Spin stabilised (~1 rpm) with 5 deg pointing accuracy. Hydrazine propulsion system with 8 thrusters and 2 tanks. Body mounted solar cells generated 290 watts. Three 8Ahr NiCd batteries. Downlink at 8.2 kbps at S-Band from redundant 10 W transmitters. Aluminum, titanium, magnesium, glass fibre structure. Seven deployed experiment booms.2 tape recorders with ~350 Mb storage each. Payload: SC1 - Engineering Experiments plus VLF and HF Receivers - measured surface potentials of various spacecraft materials, measured RF waves between 0-300 kHz, 2-30 Mhz. SC2 Spacecraft Sheath Fields Plus Energetic Ions - measured low energy electrons and ions, energetic protons, and electrons. SC3 High Energy Particle Spectrometer - measured high energy electrons and protons. SC4 Satellite Electron and Positive Ion Beam System - used ion and electron beam guns to control spacecraft surface potential. SC5 Rapid Scan Particle Detector - measured electrons and ions. SC6 Thermal Plasma Analyser (failed soon after initial turn on) - designed to measure thermal electrons and ions. SC7 Light Ion Mass Spectrometer (failed soon after initial turn on) - designed to measure light ion density, temperature and composition. SC8 Energetic Ion Compositions Experiment - measured low energy electrons and the ion composition of energetic plasma. SC9 UCSD Charged Particle Experiment - measured electrons and ions. SC10 Electric Field Detector - measured DC and ELF electric fields and satellite potential. SC11 Magnetic Field Monitor - measured DC and ELF magnetic fields. ML12 Spacecraft Contamination Plus Thermal Control Materials Monitoring -measured contamination rates and property changes of several thermal control material samples. TPM Transient Pulse Monitor - supported the other experiments by providing supporting data about the electromagnetic pulse environment. The twelve experiments had a total mass of 87 kg and consumed 110 W.
Design Life: 1 year. Total Length: 1.8 m. Maximum Diameter: 1.8 m. Total Mass: 360 kg.
Spacecraft charging experiments. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).