Accession Number:

AD0689731

Title:

A NONVARYING-C* CONTROL SCHEME FOR AIRCRAFT.

Descriptive Note:

Technical rept.,

Corporate Author:

NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF

Personal Author(s):

Report Date:

1969-06-04

Pagination or Media Count:

27.0

Abstract:

A sum of normal acceleration and pitch rate appears to be the best variable to use to control aircraft in the longitudinal axis. The C-Criterion specifies that the time response of this quantity called C must fall in a prescribed envelope for all speeds and altitudes. It is equivalent to requiring the control system to hold the coefficients of a certain equation, which describes the aircrafts short-period motion, fixed. This is done by using feedbacks with variable gains. The gain-changing mechanism is found using gradient techniques. The system was shown to be practical by an analog simulation. It was found to be tolerant of instrument noise, elevator hysteresis, and other complications not accounted in the analytical derivations. The study strongly suggests a modification of the C-Criterion. It is proposed that the coefficients in the expression of the quantity C should be representative of the aircrafts parameters rather than have the values currently in use. Author

Subject Categories:

  • Aircraft
  • Flight Control and Instrumentation

Distribution Statement:

APPROVED FOR PUBLIC RELEASE