SELF-ORGANIZING CONTROL OF AIRCRAFT PITCH RATE AND NORMAL ACCLERATION.
Abstract
This report describes an aircraft self-organizing adaptive flight control augmentation system which has been evaluated relative to pitch-rate and normal-acceleration handling-qualities requirements of a simulated F-101B. The self-organizing controller (SOC) employs probability state variable devices and suitable means for high-speed, on-line assessments of system performance. Inputs to the SOC consist of the output of a model(prefilter) used to shape the pilot's commands, rate-gyro and normal-accelerometer signals, and an optional elevator position feedback signal used to improve the compensation of rate-gyro dynamics. The SOC output is an analog signal used either singly or in summation with the output of a conventional longitudinal-axis controller to drive the elevator servo. A breadboard self-organizing controller (the Mark 3) has been fabricated and used in conjunction with analog and hybrid computer simulations of F-101B short-period airframe dynamics. The simulation included a representative nonlinear actuator and typical sensor transfer functions. It is shown that the SOC provides excellent transient and steady-state response characteristics in terms of both pitch rate and a blended pitch-rate and normal-acceleration feedback function. These characteristics are maintained essentially uniform throughout the Mach number- altitude envelope of the F-101B. The SOC appears to cope satisfactorily with wind gusts, air turbulence, and noise from sensors or other sources, and exhibits ability to adapt to simulated logic failures within the SOC as well as to degradation-type failures of other control-loop elements. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1966
- Accession Number
- AD0801157
Entities
People
- John M. Davies
- Richard F. Snyder
- Rober M. Mckechnie Iii
- Roger L. Barron