SIMULATOR STUDY OF DIRECT LIFT CONTROL DURING CARRIER LANDING APPROACHES
Abstract
Fixed-base simulator tests of direct lift control were conducted during carrier landing approaches as a means of increasing flight path control pre cision. The direct lift control system that was tested consists of controlling the trailing-edge flaps of a Model A-3 = 10 degrees from the normal 35-degree deflection at normal flight control rates. Control of the flaps was achieved through a three-position switch on the control stick, operating in the same sense as the basic longitu dinal control and trim. The system was designed to supplement and not replace normal longitudinal control. The effectiveness of direct lift con trol was evaluated over a wide range of aerody namics characteristics variations, including phugoid and short-period mode frequency and damp ing, and operation on the backside of the power required curve. Direct lift control provided nominal improvements in landing approach, flight path control precision in those cases with good handling qualities or stability and control char acteristicsonsiderable improvements in those cases with substandard handling qualities. Pilot opinion was strongly favorable to direct lift control although the quantitative effects were in some cases only nominal. Although the effects of direct lift control on minimum usable approach speed were not evaluated directly, im provements in flight path control precision and apparent handling qualities can reasonably be expected to permit reductions in minimum usable approach speed.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 08, 1963
- Accession Number
- AD0406168
Entities
Organizations
- Douglas