|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/230 ; 244/223|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 30 인용 특허 : 0|
An all-electric powered flight control system for an aircraft incorporating fault-tolerant avionics combined with a redundant power actuation control system utilizing electro-mechanical devices for actuating aerodynamic control surfaces; and wherein, the redundancy is implemented through the division of the total aerodynamic surface area to be actuated into multi-segments, with each control segment having its own channel in the avionic control system. The avionic control system is effective in minimizing the effects of power actuated control loads reacti...
An avionic control system for aircraft, comprising: a flight control surface divided into multi-control segments and each control segment being independently mounted for angular motion about a hinge axis; and actuator separately connected to each individual control segment for angular movement thereof; a manually operable controller for generating a first signal related to direction and magnitude of displacement of said controller; means for tansmitting said first signal to each of said actuators for controlling angular movement of their respective contr...