Flight Investigation of Stability and Control Characteristics of a 0.18-scale Model of a Four-duct Tandem V/STOL Transport
| Author | : William A. Newsome |
| Publisher | : |
| Total Pages | : 54 |
| Release | : 1966 |
| Genre | : Damping (Mechanics) |
| ISBN | : |
Flight Investigation Of Stability And Control Characteristics Of A 018 Scale Model Of A Four Duct Tandem V Stol Transport
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Scientific and Technical Aerospace Reports
| Author | : |
| Publisher | : |
| Total Pages | : 1282 |
| Release | : 1982 |
| Genre | : Aeronautics |
| ISBN | : |
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Predictive Methods for the Dynamic Response of a Quad Tilt-duct V/STOL Aircraft in Transition
| Author | : Irving Carl Statler |
| Publisher | : |
| Total Pages | : 466 |
| Release | : 1970 |
| Genre | : Short take-off and landing aircraft |
| ISBN | : |
VTOL/STOL Aircraft
| Author | : North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development |
| Publisher | : |
| Total Pages | : 344 |
| Release | : 1966 |
| Genre | : Short take-off and landing aircraft |
| ISBN | : |
Fundamental Limitations on V/STOL Terminal Guidance Due to Aircraft Characteristics
| Author | : Julian Wolkovitch |
| Publisher | : |
| Total Pages | : 188 |
| Release | : 1971 |
| Genre | : Short take-off and landing aircraft |
| ISBN | : |
A review is given of limitations on approach flight paths of V/STOL aircraft, including limits on descent angle due to maximum drag/lift ratio. A method of calculating maximum drag/lift ratio of tilt-wing and deflected slipstream aircraft is presented. Derivatives and transfer functions for the CL-84 tilt-wing and X-22A tilt-duct aircraft are presented. For the unaugmented CL-84 in steep descents the transfer function relating descent angle to thrust contains a right-half plane zero. Using optimal control theory, it is shown that this zero causes a serious degradation in the accuracy with which steep flight paths can be followed in the presence of gusts.
