Accession Number:

AD0750501

Title:

Self-Adjusting Automatic Control Systems of Aeroelastic Aircraft,

Descriptive Note:

Corporate Author:

FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

Report Date:

1972-08-17

Pagination or Media Count:

16.0

Abstract:

High quality control of an aircraft as a rigid body can be achieved with allowance for the nonlinearity and inertia of the actuator by using appropriate compensating devices and by placing adaptive filters in the angular velocity sensor circuits to eliminate noise caused by high and low frequency elastic oscillations. The primary low frequency components flexural vibrations in the wings and fuselage can be damped by special control surfaces on the wings and fuselage. This damping should not be altered from accelerometer sensors positioned in selected points. Required phase relationships are obtained with compensating necessary and either phase lead or phase lag filters. Automatic control of optimal gain in the stabilization loops is accomplished with the aid of spectrum analyzers. The synthesis of controller structure and parameters should be based on graph theory methods. Author

Subject Categories:

  • Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE