The Spacecraft Structure and Thermal Design Considerations

Abstract

This paper covers the general structural and thermal design considerations of the Telstar satellite. The basic objectives were to maintain the electronic components in a near room temperature environment and to protect the electronics package from high‐frequency vibration excitation. These objectives were realized by dividing the satellite into two lumped masses, the shell and the centrally located electronics package, and by utilizing nylon lacing for support of the electronics package. The package was provided with an active temperature control, regulating radiative heat flow between the skin and the package. Results of on‐the‐ground experimental evaluation and of telemetry data are given.

Attitude Determination and Prediction of Spin-Stabilized Satellites

“…8 In general, B may range from 0°to 360°. All quadrant ambiguities presented by (10) are resolved by noting the algebraic signs of (9) and (9a).…”