Energy protection method and device for an aircraft
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-015/02
B64D-025/00
B64D-031/06
B64D-031/10
출원번호
US-0922420
(2015-10-26)
등록번호
US-9505488
(2016-11-29)
우선권정보
FR-14 60707 (2014-11-06)
발명자
/ 주소
Moune, Marie-Claire
출원인 / 주소
Airbus Operations (SAS)
대리인 / 주소
Greer, Burns & Crain, Ltd.
인용정보
피인용 횟수 :
0인용 특허 :
7
초록▼
An energy protection device comprising an activation unit for, in a low energy situation, automatically activating an energy protection function comprising automatically engaging an autothrust and automatically controlling the engines of the aircraft for the engines to supply a maximum thrust, an au
An energy protection device comprising an activation unit for, in a low energy situation, automatically activating an energy protection function comprising automatically engaging an autothrust and automatically controlling the engines of the aircraft for the engines to supply a maximum thrust, an auxiliary monitoring unit configured to perform a monitoring to detect an absence of activation of a protection mode by at least one of the engines of the aircraft although an activation command has been transmitted, and a disconnection unit to automatically disconnect the autothrust in case of the detection of such a situation, a disconnection of the autothrust resulting in the triggering of the protection function being stopped.
대표청구항▼
1. An energy protection method for an aircraft which is provided with a plurality of engines and an autothrust, said method having a protection function comprising automatically engaging the autothrust if the autothrust is not already engaged and in automatically increasing a thrust of the engines t
1. An energy protection method for an aircraft which is provided with a plurality of engines and an autothrust, said method having a protection function comprising automatically engaging the autothrust if the autothrust is not already engaged and in automatically increasing a thrust of the engines to a maximum thrust when conditions for triggering the protection function are fulfilled, said method comprising: transmitting an activation command to each of the engines of the aircraft for the triggering of the protection function,activating a corresponding protection mode by each of the engines in response to the transmission of the activation command,performing a monitoring in a monitoring step so as to be able to detect an absence of activation of the protection mode by at least one of said engines although an activation command has been transmitted, andautomatically disconnecting the autothrust in a disconnection step, in case of the detection of an absence of activation of the protection mode by at least one engine although an activation command has been transmitted, a disconnection of the autothrust resulting in the triggering of the protection function being stopped. 2. The method as claimed in claim 1, further including an auxiliary step comprising, in case of the detection of the absence of activation of the protection mode by at least one engine although an activation command has been transmitted, automatically bringing each of said engines into a manual thrust control mode. 3. The method as claimed in claim 1, wherein, in case of the reception of an activation command, each of said engines engaging the corresponding protection mode and transmitting a response indicating whether or not the protection mode has been engaged, and wherein the monitoring step comprises detecting an absence of activation if the following conditions are simultaneously fulfilled: a protection function activation command has been transmitted;the response transmitted by at least one of said engines indicates that the corresponding protection mode has not been engaged. 4. An energy protection device for an aircraft provided with a plurality of engines and an autothrust, said device comprising: a monitoring unit configured to monitor, during a flight of the aircraft, a plurality of data of the aircraft so as to be able to detect a triggering situation, for which energy protection triggering conditions are fulfilled;an activation unit configured, in case of the detection of a situation of triggering by the monitoring unit, to automatically activate a protection function comprising automatically engaging the autothrust if the autothrust is not already engaged and automatically controlling the engines for them to supply a maximum thrust, the activation unit comprising an element configured to transmit an activation command to each of the engines of the aircraft, a corresponding protection mode being activated by each of the engines in response to the transmission of an activation command;an auxiliary monitoring unit configured to perform a monitoring so as to detect an absence of activation of the protection mode by at least one of said engines although an activation command has been transmitted by the transmission element; anda disconnection unit configured to automatically disconnect the autothrust, in case of the detection of an absence of activation of the protection mode by at least one engine although an activation command has been transmitted, a disconnection of the autothrust resulting in the triggering of the protection function being stopped. 5. The device as claimed in claim 4, further comprising a control unit configured, in case of the detection of an absence of activation of the protection mode by at least one engine although an activation command has been transmitted, to automatically bring each of said engines into a manual thrust control mode. 6. The device as claimed in claim 4, wherein the auxiliary monitoring unit is configured to detect an absence of activation if the following conditions are simultaneously fulfilled: a protection function activation command has been transmitted;a response transmitted by at least one of said engines indicates that the corresponding protection mode has not been engaged. 7. An aircraft comprising a plurality of engines, an autothrust and an energy protection device, said device comprising: a monitoring unit configured to monitor, during a flight of the aircraft, a plurality of data of the aircraft so as to be able to detect a triggering situation, for which energy protection triggering conditions are fulfilled;an activation unit configured, in case of the detection of a situation of triggering by the monitoring unit, to automatically activate a protection function comprising automatically engaging the autothrust if the autothrust is not already engaged and automatically controlling the engines for them to supply a maximum thrust, the activation unit comprising an element configured to transmit an activation command to each of the engines of the aircraft, a corresponding protection mode being activated by each of the engines in response to the transmission of an activation command;an auxiliary monitoring unit configured to perform a monitoring so as to detect an absence of activation of the protection mode by at least one of said engines although an activation command has been transmitted by the transmission element; anda disconnection unit configured to automatically disconnect the autothrust, in case of the detection of an absence of activation of the protection mode by at least one engine although an activation command has been transmitted, a disconnection of the autothrust resulting in the triggering of the protection function being stopped. 8. The aircraft as claimed in claim 7, further comprising a control unit configured, in case of the detection of an absence of activation of the protection mode by at least one engine although an activation command has been transmitted, to automatically bring each of said engines into a manual thrust control mode. 9. The aircraft as claimed in claim 7, wherein the auxiliary monitoring unit is configured to detect an absence of activation if the following conditions are simultaneously fulfilled: a protection function activation command has been transmitted;a response transmitted by at least one of said engines indicates that the corresponding protection mode has not been engaged.
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이 특허에 인용된 특허 (7)
Moune, Marie-Claire; Muller, Jean, Energy protection device for an aircraft.
Eggold, David P.; Shapiro, Daniel R.; Gardner, Kyle J., Varying engine thrust for directional control of an aircraft experiencing engine thrust asymmetry.
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