NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
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)
Date Acquired
August 10, 2013
Publication Date
January 1, 1982
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 82-1563
Meeting Information
Meeting: Guidance and Control Conference
Location: San Diego, CA
Start Date: August 9, 1982
End Date: August 11, 1982
Accession Number
82A38964
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available