Angle of Attack and Sideslip Estimation Using an Inertial Reference Platform
Abstract
The purpose of this research is to develope and flight test concepts for the estimation of angle of attack (alpha) and sideslip (beta) using an inertial reference platform. This development was further broken down into real- time, inflight estimation of alpha and post-flight estimation of alpha and beta. Following theoretical development, the concepts were tested with NASA F-15A flight data and examined real-time during a nasa Highly Integrated Digital Engine Control (HIDEC) flight test using the F-15A aircraft. Angle of attack is a critical parameter in the maneuverable, high performance aircraft of today. Yet many errors are present in the current methods of obtaining this angle. An accurate method of alpha and beta estimation could eliminate the need for such probes, and allow these quantities to be used for a broad range of applications. An inflight estimator was developed for computational speed and accuracy using inertial navigation system linear accelerations and angular rates. A second system based on linear recursive modeling was developed for post-flight estimation of alpha and beta. The data and programs specified in this research are applicable only to those aircraft mentioned, but the methods of estimation are universal.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1988
- Accession Number
- ADA194876
Entities
People
- Joseph E.
Organizations
- Air Force Institute of Technology