This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Pitch Axis Control System Design for QF-4 Full-Scale Aircraft Target
Annotation ability available
Sector:
Language:
English
Abstract
The pitch axis control system of the QF-4 Full-Scale Aircraft Target is a digital control system which allows a remote operator to control the remotely piloted vehicle in an interactive mode or in one of the automatic hold modes. The interactive all-attitude pitch rate controller is designed to meet the MIL-F-8785C flying qualities specification for damping ratio and normal acceleration to angle of attack sensitivity at Level 2 or better for combat aircraft. The pitch rate controller is used as an inner loop for all of the automatic hold modes to provide increased damping and more accurate holding capability. The automatic hold modes include attitude hold, altitude hold, Mach hold, and normal acceleration hold. The basic analyses are presented in this report deriving the control models and determining the gain schedules required to meet system specifications.
Authors
Citation
Hartley, G., "Pitch Axis Control System Design for QF-4 Full-Scale Aircraft Target," SAE Technical Paper 861852, 1986, https://doi.org/10.4271/861852.Also In
References
- Wright-Patterson Air Force Base Military Specification Flying Qualities of Piloted Airplanes Dayton, Ohio WPAFB 5 November 1980
- Naval Weapons Center Naval Weapons Center Department of the Navy System Specification for QF-4 Full Scale Aircraft Target China Lake, Calif. NWC 5 June 1984
- Naval Air Systems Command NATOPS Flight Manual Washington, D.C. NAVAIR 1 May 1975
- Blakelock J. H. Automatic Control of Aircraft and Missiles New York John Wiley and Sons. Inc. 1965
- McDonnell Aircraft Corp. Calculated Longitudinal Stability Performance Characteristics of the F-4 B/C/D/J and RF-4 B/C Aircraft Plus the AN/ASA-32H Automatic Flight Control System St. Louis, Mo. MAC April 1968 MAC Report F934