This paper deals with the application of linear filtering theory to post-flight guidance error analysis. The primary concern is to reconstruct the powered flight trajectory and to recover the systematic errors of the inertial measurement unit (IMU) and the radar tracking systems from all the available flight data. For a launch vehicle with a strapdown inertial navigation system, an effective estimation algorithm with several simulation programs is developed by linearizing the strapdown vehicle dynamics along a selected reference trajectory. The guidance reconstructed trajectory (GRT) is recommended here, and then Kalman filter is applied in order to process both IMU telemetry data and the noisy tracking data at the downrange stations. Some results of digital simulation are presented.
Guidance error analysis via Kalman filtering
Fehleranalyse bei der Raumfahrtnavigation mittels Kalman-Filter
Titel japanisch
Systems and Control ; 19 , 3 ; 152-161
1975
, 5 Quellen
Article (Journal)
Japanese
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