Equations for angles of attack and sideslip relative to both a rolling and nonrolling body axis system are derived for a flight vehicle for which radar and gyroscopic attitude data are available. The method is limited to application where a flat, nonrotating earth may be assumed. The gyro measures attitude relative to an inertial reference in an Euler angle sequence. In particular, a pitch, yaw, and roll sequence is used as an example in the derivation. Sample calculations based on flight data are presented to illustrate the method. Results obtained with the present gyro method are compared with another technique that uses onboard camera data.
Determination of angles of attack and sideslip from radar data and a roll-stabilized platform
1972-03-01
Report
No indication
English
Nonlinear Analysis of Flight Dynamics at Large Angles of Attack and Sideslip
SAE Technical Papers | 1994
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