Performance of an aided redundant navigator in normal and failure modes
Abstract
The performance of a redundant strapdown inertial navigation system in the normal mode, failure mode and reconfiguration mode is characterized by a single figure-of-merit representing the probability of mission success. A sensitivity matrix derived from a linearized error analysis relates attitude, position and velocity errors to initial condition errors as well as inertial sensor static and dynamic errors. The implementation of state vector updates is described. Numerical results are presented for an orbit insertion mission.
- Publication:
-
In: Guidance and Control Mini-Symposium
- Pub Date:
- 1980
- Bibcode:
- 1980guco.symp...57H
- Keywords:
-
- Failure Modes;
- Orbital Maneuvers;
- Redundant Components;
- Spacecraft Guidance;
- Strapdown Inertial Guidance;
- System Effectiveness;
- Attitude Control;
- Error Analysis;
- Fail-Safe Systems;
- Figure Of Merit;
- Inertial Navigation;
- Performance Prediction;
- Position Errors;
- Space Navigation;
- State Vectors;
- Velocity Errors;
- Space Communications, Spacecraft Communications, Command and Tracking