Space Shuttle Orbiter descent navigationThe entry operational sequence (OPS 3) begins approximately 2 hours prior to the deorbit maneuver and continues through atmospheric entry, terminal area energy management (TAEM), approach and landing, and rollout. During this flight phase, the navigation state vector is estimated by the Space Shuttle Orbiter onboard navigation system. This estimate is computed using a six-element sequential Kalman filter, which blends inertial measurement unit (IMU) delta-velocity data with external navaid data. The external navaids available to the filter are tactical air navigation (TACAN), barometric altimeter, and microwave scan beam landing system (MSBLS). Attention is given to the functional design of the Orbiter navigation system, the descent navigation sensors and measurement processing, predicted Kalman gains, correlation coefficients, and current flights navigation performance.
Document ID
19820055429
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Montez, M. N. (NASA Johnson Space Center Houston, TX, United States)
Madden, M. F. (Rockwell International Corp. Downey, CA, United States)