IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0604296
(2006-11-27)
|
등록번호 |
US-8561948
(2013-10-22)
|
우선권정보 |
FR-05 12048 (2005-11-29) |
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
4 |
초록
▼
A method for ensuring the safety of an aircraft flying horizontally at low speed includes an operation in which, when the flaps of the aircraft are disposed in a maximum extended position and are blown on by airscrews, the flaps are at least partially retracted, automatically, based on whether the t
A method for ensuring the safety of an aircraft flying horizontally at low speed includes an operation in which, when the flaps of the aircraft are disposed in a maximum extended position and are blown on by airscrews, the flaps are at least partially retracted, automatically, based on whether the thrust of the engines is at least equal to a predetermined lift value.
대표청구항
▼
1. A method to ensure the safety of an aircraft flying horizontally at low speed, comprising the steps of: providing an aircraft comprised of: a vertical tail group supporting a tilt-adjustable horizontal tail group that includes elevators,an airscrew provided on an engine supported by a fixed wing
1. A method to ensure the safety of an aircraft flying horizontally at low speed, comprising the steps of: providing an aircraft comprised of: a vertical tail group supporting a tilt-adjustable horizontal tail group that includes elevators,an airscrew provided on an engine supported by a fixed wing of the aircraft,extendable and retractable trailing-edge high-lift flaps on the wing of the aircraft, anda controller configured to control extension and retraction of the high-lift flaps;flying the aircraft horizontally at low speed;orienting said high-lift flaps in an extended position during the horizontal flight of the aircraft;blowing wind generated by said airscrew onto the wing of the aircraft and onto the high-lift flaps oriented in said extended position to generate a nose-down moment;deflecting the tilt-adjustable horizontal tail group during the horizontal flight to generate a nose-up moment and counteract the nose-down moment; andretracting the high-lift flaps by the controller during the horizontal flight, wherein the controller is configured to retract the high-lift flaps at a condition in which an engine thrust signal received by the controller becomes equal to or greater than a predetermined high value that corresponds to the engine thrust needed for the aircraft to take-off. 2. The method as claimed in claim 1, wherein the retracting step is applied only when said aircraft is at an altitude greater than a threshold HS. 3. The method as claimed in claim 2, wherein said threshold HS is approximately equal to 30 meters. 4. The method as claimed in claim 1, wherein the high-lift flaps are retracted to an extent that prevents a stalling effect for the horizontal tail group in the event of a dive and subsequent flare of the aircraft. 5. The method as in claim 1, wherein the tilt-adjustable horizontal tail group is located at a top end of the vertical tail group. 6. The method as in claim 1, wherein the elevators are hinged to the adjustable horizontal tail group. 7. A method to ensure the safety of an aircraft flying horizontally at low speed, comprising the steps of: providing an aircraft comprised of: a vertical tail group supporting a tilt-adjustable horizontal tail group that includes elevators,an airscrew provided on an engine supported by a fixed wing of the aircraft,extendable and retractable trailing-edge high-lift flaps on the wing of the aircraft, anda controller configured to control extension and retraction of the high-lift flaps;flying the aircraft horizontally at low speed;orienting said high-lift flaps in an extended position during the horizontal flight of the aircraft;blowing wind generated by said airscrew onto the wing of the aircraft and onto the high-lift flaps oriented in said extended position to generate a nose-down moment;deflecting the tilt-adjustable horizontal tail group during the horizontal flight to generate a nose-up moment and counteract the nose-down moment; andretracting the high-lift flaps by the controller during the horizontal flight, wherein the controller is configured to retract the high-lift flaps at conditions corresponding to a first threshold condition in which engine thrust is less than the engine thrust needed for the aircraft to take-off and a second threshold condition in which a nose-down command is applied to the elevators. 8. The method as claimed in claim 7, wherein said first threshold is approximately equal to 60% of the engine thrust needed for take-off. 9. The method as claimed in claim 7, wherein said second threshold corresponds to approximately 60% of a total nose-down travel of a control column. 10. An aircraft comprising: a vertical tail group supporting a tilt-adjustable horizontal tail group that includes elevators;an airscrew provided on an engine supported by a fixed wing of the aircraft;extendable and retractable trailing-edge high-lift flaps on the wing of the aircraft;a sensor configured to sense an extended position of the flaps and deliver a signal that the flaps are in an extended position; anda controller for controlling the extension and retraction of the flaps, wherein the controller is configured to receive the signal sent from the sensor and an engine thrust signal from a gas lever, and controls the high-lift flaps to retract from the extended position at conditions in which: the aircraft is flying horizontally,the high-lift flaps are oriented in the extended position during the horizontal flight,wind generated by the airscrew is blown onto the wing of the aircraft and onto the high-lift flaps oriented in the extended position during the horizontal flight to generate a nose-down moment,the tilt-adjustable horizontal tail group is deflected during the horizontal flight to generate a nose-up moment and counteract the nose-down moment, andthe controller receives the engine thrust signal, in which the signal is equal to or greater than a predetermined value corresponding to the engine thrust needed for the aircraft to take-off. 11. An aircraft comprising: a vertical tail group supporting a tilt-adjustable horizontal tail group that includes elevators;an airscrew provided on an engine supported by a fixed wing of the aircraft;extendable and retractable trailing-edge high-lift flaps on the wing of the aircraft;a sensor configured to sense an extended position of the flaps and deliver a signal that the flaps are in the extended position; anda controller for controlling the extension and retraction of the flaps, wherein the controller is configured to receive an engine thrust signal from an on-board computer, and controls the high-lift flaps to retract from the extended position at conditions in which: the aircraft is flying horizontally,the high-lift flaps are oriented in the extended position during the horizontal flight,wind generated by the airscrew is blown onto the wing of the aircraft and onto the high-lift flaps oriented in the extended position during the horizontal flight to generate a nose-down moment,the tilt-adjustable horizontal tail group is deflected during the horizontal flight to generate a nose-up moment and counteract the nose-down moment, andthe controller receives the thrust signal at a predetermined value corresponding to a first threshold condition in which the engine thrust is less than the engine thrust needed for the aircraft to take-off and a second threshold based on a nose-down command being applied to the elevators.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.