Feedback Control of VTOL Aircraft
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1970
- Accession Number
- AD0871424
Entities
People
- Theodor A. Dukes
Organizations
- Princeton University