Design and performance characteristics of the Viking Lander Inertial Reference Unit /IRU/
Abstract
The design, pre-launch testing, and performance of the Inertial Reference Unit (IRU) guidance system of the Viking Lander are discussed. Design requirements for the IRU included redundancy of the sensors, resistance to wide temperature variations, and capability of providing continuous attitude information during very high displacement rates encountered at parachute opening. Preconditioning of the gyro subassemblies and accelerometers to insure resistance to heat and vibration is described; problems detected during testing of the IRU, including failure of gyro endstones, breakage of flexleads, and leakage in the gyro shield, are also considered. Data on the bias stability of the gyros and accelerometers and the deorbiting and entry performance of the IRU are given.
- Publication:
-
Guidance and Control Conference
- Pub Date:
- 1977
- Bibcode:
- 1977guco.conf..512V
- Keywords:
-
- Inertial Reference Systems;
- Performance Tests;
- Prelaunch Tests;
- Spacecraft Design;
- Spacecraft Guidance;
- Viking Lander Spacecraft;
- Accelerometers;
- Fail-Safe Systems;
- Gyroscopes;
- Redundant Components;
- Reliability Engineering;
- Space Communications, Spacecraft Communications, Command and Tracking