Navigation and attitude reference for autonomous satellite launch and orbital operations

Details Navigation and attitude reference for autonomous satellite launch and orbital operations Navigation and attitude reference for autonomous satellite launch and orbital operations

Apr 1979

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1979fmet.symp..149k&link_type=abstract

In NASA. Goddard Space Flight Center Flight Mech./Estimation Theory Symp. p 149-166 (SEE N79-26082 17-13)

Computer Science

Performance

Airborne/Spaceborne Computers, Data Processing, Guidance Sensors, Satellite Attitude Control, Satellite Orbits, Flight Mechanics, Geodetic Coordinates, Inertial Navigation, Military Spacecraft, Orbital Mechanics, Orbital Position Estimation, Satellite Orbits

Scientific paper

The navigation and attitude reference performance of a strapdown system are investigated for applications to autonomous satellite launch and orbital operations. It is assumed that satellite payloads are integrated into existing missile systems and that the boost, orbit insertion, and in-orbit operation of the satellite are performed autonomously without relying on external support facilities. Autonomous and long term accurate navigation and attitude reference are provided by a strapdown inertial navigation system aided by a star sensor and earth landmark sensor. Sensor measurement geometry and navigation and attitude update mechanizations are discussed. Performance analysis data are presented for following functional elements: (1) prelaunch alignment; (2) boost navigation and attitude reference; (3) post boost stellar attitude and navigation updates; (4) orbital navigation update using sensor landmark measurements; and (5) in-orbit stellar attitude update and gyro calibration. The system performances are shown to satisfy the requirements of a large class of satellite payload applications.

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