Accession Number:

AD0871424

Title:

Feedback Control of VTOL Aircraft

Descriptive Note:

Final rept.

Corporate Author:

PRINCETON UNIV NJ DEPT OF AEROSPACE AND MECHANICAL SCIENCES

Personal Author(s):

Report Date:

1970-04-01

Pagination or Media Count:

69.0

Abstract:

An approximative analysis and discussion is given of the behavior of poles and zeros characterizing the longitudinal dynamics of VTOL aircraft in transition. In feedback design, it is a desirable goal to create a dominant attitude response mode which is separated in frequency and varies little throughout the transition. The investigation demonstrated that this goal can be achieved at fixed operating points in transition without accurate prior knowledge about the behavior of the stability and control derivatives during transition. In the longitudinal degrees of freedom, pitch attitude and pitch rate feedback were used. In the lateral-directional degrees of freedom, the same goal was achieved by using yaw rate, roll angle, and roll rate feedback. The gains were determined by an approximate procedure. Longitudinal and lateral- directional experiments were performed with a 0.1 scale model of the XC-142A tilt-wing VTOL aircraft. Pulse responses of the free-flying model are presented.

Subject Categories:

  • Transport Aircraft
  • VSTOL

Distribution Statement:

APPROVED FOR PUBLIC RELEASE