Evaluation of a Proposed INS Kalman Filter in a Dynamic Flight Environment
Abstract
This report is an evaluation of a proposed Kalman filter for an advanced manned aircraft. The evaluation is performed under simulated flight profiles which include straight and level and maneuvering flight. The aided inertial navigation system is represented by a 54-state linear system error model and the filter by a 17-state error model with decoupled horizontal and vertical channel mechanization. The simulated flight profiles include two hours of straight and level flight and one additional hour of either straight and level or maneuvering flight. A comparison of filter effectiveness with the optimal filter is made for the two hour straight and level flight. The decoupled 17-state filter effectiveness is evaluated during one additional hour of maneuvering flight based on the filter performance in straight and level flight for the same time period. In addition, an error budget is determined for both flight profiles.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1974
- Accession Number
- ADA008472
Entities
People
- Jerry E. Hammett
Organizations
- Air Force Institute of Technology