|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/76C ; 244/213|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 16 인용 특허 : 1|
On an aircraft having spoilers on the wing, the spoilers are converted, according to this invention, following the ACT philosophy, for use in countering gust effects. Accordingly, a sensor of gusts is arranged to transmit warning of the arrival of a significant gust to a spoiler operator which, taking into account airspeed, deploys the spoilers in a mode so that a phase of spoiler generated lift decrement is timed to coincide with effective arrival of the gust.
Gust alleviating spoiler apparatus on an aircraft, said apparatus comprising hinged spoilers on the mainplanes of the aircraft, wherein said spoilers are hinged at their leading edges, a sensor of gusts in the aircraft\s path, said sensor being at a forward location on the aircraft, and spoiler drive means responsive to output from said sensor for rotating said spoilers at a first angular rate to a first angular displacement, said first angular rate being sufficiently low to ensure that significant positive lift is not generated thereby, and for further ...