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.
Fundamental limitations on V/STOL terminal guidance due to aircraft characteristics
1971-12-01
Report
No indication
English
AIAA | 1971
|Four-D guidance of STOL aircraft in the terminal area
NTRS | 1972
|The 4-D guidance of STOL aircraft in the terminal area
NTRS | 1972
|