Accession Number:

ADA080133

Title:

Research and Development of Control Actuation Systems for Aircraft. Volume I.

Descriptive Note:

Final rept. Jun 77-Feb 79,

Corporate Author:

DYNAMIC CONTROLS INC DAYTON OHIO

Personal Author(s):

Report Date:

1979-08-01

Pagination or Media Count:

211.0

Abstract:

This report describes the development of a flutter suppression actuator technique and the wind tunnel evaluation of that technique. The report also describes the flightworthiness testing of a direct drive Fly-By-Wire flight control system applied to the aileron axis of an F-4 aircraft. Also included is an evaluation of an angular rate sensing augmentation actuator supplied to the Air Force for evaluation. Presented in the material are the test results of all three experimental evaluations. Further testing of the flutter suppression is recommended to clarify an anomoly in the results of the testing. The direct drive control system passed its environmental testing used to establish flight worthiness. The rate sensing actuator operated as designed.

Subject Categories:

  • Attack and Fighter Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE