VTOL TRANSITION DYNAMICS AND EQUATIONS OF MOTION WITH APPLICATION TO THE X-22A.
Abstract
This study was to develop some understanding of the dynamics of a VTOL in transition and to develop equations of motion which can be used for flight test parameter identification, for analysis and interpretation of flying qualities. A digital computer model of the X-22A stability and control data was programmed together with full six-degree-of-freedom equations of motion. This was used to determine usable ranges of flight and control variables for takeoffs and landings. A representation of the aerodynamic characteristics was developed for accelerated transitions in the form of a Taylor's series. Responses obtained with the simpler form were checked with responses obtained using the original representation. Nonlinear derivatives were required for a good matching, but a fair representation was still obtained after simplifying to first-order terms which were a function of one variable. The simpler form of equations, with nonlinear derivatives, should be satisfactory for use in developing flight test parameter identification techniques. Linearized constant coefficient equations developed for analysis of accelerated initial conditions gave a good representation of the responses at fixed duct angle. The lateral-directional characteristics were generally more linear and amenable to linearized analysis than the longitudinal characteristics. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1968
- Accession Number
- AD0835996
Entities
People
- David L. Key
- Lowell E. Reed
Organizations
- Calspan