An Automatic-Throttle Device for Airspeed Control During Flare to Field Landings.

Abstract

This study is a continuation of the investigations in the use of automatic-throttle compensation systems. The previous investigations demonstrated the capability of such systems in alleviating the problems of aircraft speed instability in the carrier landing approach. The feasibility of adapting the system with sensed-input variables of angle-of-attack and normal acceleration to the condition of field landings with flare was investigated. An analysis of the ground effect prevalent in field landings was performed and the significant influences on aircraft response were included in the investigation. The desired airspeed control with zero rate of descent at touchdown was obtained by incorporating additional commands in the basic auto-throttle device during the flare maneuver. The analog computer was utilized for problem simulation.