Design, Fabrication, and Flight Testing of Self-Organizing Flight Control System

Item

Title
Design, Fabrication, and Flight Testing of Self-Organizing Flight Control System
Date
1970
Index Abstract
Not Available
Photo Quality
Complete
Report Number
AFFDL TR 70-77
Corporate Author
Adaptronics, Inc. McLean, Virginia
Laboratory
Air Force Flight Dynamics Laboratory
Extent
230
Identifier
AD0872609
Access Rights
Export Control
Distribution Classification
1
Contract
AF 33(615)-5141
DoD Project
None Given
DoD Task
None Given
DTIC Record Exists
No
Distribution Change Authority Correspondence
AFFDL LTR
Abstract
The report summarizes design characteristics, simulations, bench tests, and flight tests of an elementary self-organizing controller (SOC) for the pitch axis of the F-101B aircraft. This controller was flown with a cockpit electric side stick in a pseudo-fly-by-wire configuration, that is, as a fly-by-wire system with a normally disengaged mechanical backup. Blended pitch-rate and forward normal acceleration feedback (C*) and stabilator position feedback were the primary return signals used by the SOC. An optional Mach Trim loop was also investigated. The SOC, which incorporated unique modulated-noise circuits to minimize adverse effects of control-loop nonlinearities, had full authority over the aircraft stabilator within the inherent rate and position limits of the actuator. 32 test flights were conducted with the SOC, constituting a total flying time of approximately 40 hours. These flights encompassed nearly the entire performance envelope of the F-101B and included piloting tasks representative of missions flown with current fighter aircraft. The Air Force pilots rated the SOC between A1 and A2 on the CAL Revised Pilot Rating Scale. There were no in-flight malfunctions of the SOC equipment.
Report Availability
Full text available
Date Issued
1970-06
Provenance
Lockheed Martin Missiles & Fire Control
Type
report
Format
1 online resource
Creator
Barron, Roger L.
Media
AFFDLTR70-077.pdf