Shuttle Orbiter stellar-inertial reference system
Previously cited in issue 19, p. 2997, Accession no. A82-38963
Engineering topics
Publications and source records attributed to Manry, C. E..
Previously cited in issue 19, p. 2997, Accession no. A82-38963
The Space Shuttle stellar-inertial reference system is a velocity and attitude data source during flight operations. An overview of the reference system is presented as well as specifics discussing design concepts, functional operation, and performance capabilities. Techniques for star sighting and inertial measurement unit alignment and calibration are described, and alignment accuracy, star tracker capability, and gyro and accelerometer accuracy are discussed, with emphasis on flight test results. Test programs have confirmed that the system meets performance requirements such as being accurate to within 0.26 degree at the 400,000 foot altitude entry interface in order to execute an accurate touchdown, as well as demonstrating reusability, payload capability, and operational flexibility. Growth possibilities, such as the implementation of rendezvous target tracking, are discussed.
The objective was to measure the visual contrast of landmarks with the surroundings to determine the relative visibility of terrestrial landmarks from positions outside the atmosphere. Because of a malfunction of the photometer, no photometric data were obtained. A trial sighting run was performed in which a landmark on the western African coast was sighted, tracked through the nadir, and photographed. The telemetry record of the photograph was examined. Telemetry data were inconsistent with the known conditions of the landmark.
Apollo optics system ground and flight performance tests results, suggesting possible design changes for sunlit space environments
Proposed visual contrast measurements during Gemini 10 flight
Visibility and optical tracking studies for concentric flight plan of lunar orbit rendezvous