|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||364/424 ; 364/187 ; 364/434 ; 318/564|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 38 인용 특허 : 6|
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 an aerodynamic vehicle, comprising: a flight control surface divided into a plurality of flight control surface segments, each control surface segment being independently mounted for angular movement about a hinge axis; a power actuator for each said control surface segment, connected adjacent to each said control surface segment for independent angular movement thereof; a manually operable controller for generating a first signal related to direction and magnitude of displacement of said controller; air data sensing means i...