System for maneuvering an aircraft landing gear and aircraft comprising same
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
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출원번호 |
US-0663413
(2005-09-15)
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등록번호 |
US-8191827
(2012-06-05)
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우선권정보 |
FR-04 52105 (2004-09-21) |
국제출원번호 |
PCT/FR2005/050746
(2005-09-15)
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§371/§102 date |
20080620
(20080620)
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국제공개번호 |
WO2006/032811
(2006-03-30)
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발명자
/ 주소 |
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출원인 / 주소 |
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대리인 / 주소 |
Patterson Thuente Christensen Pedersen, P.A.
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인용정보 |
피인용 횟수 :
0 인용 특허 :
3 |
초록
▼
The invention concerns a system for maneuvering an aircraft landing gear mounted in a landing gear box closed by a set of hatches, comprising: a general control unit of the landing gear box to trigger the different maneuvers, a control channel for the hatches (16), a control channel for the landing
The invention concerns a system for maneuvering an aircraft landing gear mounted in a landing gear box closed by a set of hatches, comprising: a general control unit of the landing gear box to trigger the different maneuvers, a control channel for the hatches (16), a control channel for the landing gear (15), the general control unit, the hatch control channel and the landing gear control channel being controlled by an electric power source, when the aircraft is in normal operating conditions, emergency operating conditions and in maintenance phase. The invention also concerns an aircraft comprising such a system.
대표청구항
▼
1. A system for maneuvering a landing gear of an aircraft mounted so as to be hinged in a gear compartment closed by a set of doors, comprising: a general control unit of the gear compartment to trigger the different maneuvers;a door control channel;a landing-gear control channel; anda single common
1. A system for maneuvering a landing gear of an aircraft mounted so as to be hinged in a gear compartment closed by a set of doors, comprising: a general control unit of the gear compartment to trigger the different maneuvers;a door control channel;a landing-gear control channel; anda single commonly shared system for controlling the landing gear and the set of doors, the single commonly shared system configured to be implemented in each of a normal operation, an emergency operation and a maintenance phase of the aircraft, the single commonly shared system comprising the general control unit, the door control channel and the landing-gear control channel such that the single commonly shared system is controlled by a single source of electrical energy in each of the normal operation, the emergency operation and the maintenance phase,and wherein the door control channel and the gear control channel being each connected to the general control unit solely by an electrical link and being capable of receiving control commands sent by the general control unit according to a predetermined sequencing. 2. A system according to claim 1, wherein the door control channel comprises at least one electrically controlled door-locking device, at least one door-actuation unit and one electrically controlled unit to control the actuation unit. 3. A system according to claim 2, wherein the door control channel comprises at least one electrical actuating mechanism associated with the door-locking device and one electrical actuating mechanism associated with the control unit for the door actuation unit. 4. A system according to claim 2, wherein the door control channel comprises an electrical control unit placed outside the aircraft, activating the opening of the main door in maintenance phase. 5. A system according to claim 1, wherein the gear control channel comprises at least one electrically controlled landing-gear holding device, at least one gear actuation unit and one electrically controlled unit to control the actuation unit. 6. A system according to claim 5, wherein the gear control channel comprises at least one electrical actuating mechanism associated with the gear-holding device and one electrical actuating mechanism associated with the control unit for the gear actuating unit. 7. A system according to claim 1 wherein, in normal operation, the source of energy is an available general electrical power supply of the aircraft. 8. A system according to claim 1 wherein, in emergency operation, the source of energy is a general electrical supply of the aircraft or a secondary electrical source of the aircraft, comprising a propeller. 9. A system according to claim 1 wherein, in the maintenance phase, the source of energy is an available electrical source of the aircraft or an auxiliary electrical source on the ground. 10. A system according to claim 1, wherein the electrical link between the general control unit and the door control and gear control channels is a wire link. 11. A system according to claim 1, wherein the general control unit provides for a sequencing in the actuation of the door-locking and gear-holding device and in the actuation units. 12. An aircraft comprising a retractable landing gear, comprising a system for maneuvering the landing gear according to claim 1.
이 특허에 인용된 특허 (3)
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Anderson James M. (San Jose CA) Hassel Richard O. (San Jose CA) Inghram Donald M. (Santa Clara CA) Winkler Edwin (Santa Cruz CA), Aircraft cargo loading method and apparatus.
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Yourkowski Frank M. (Enumclaw WA) Zoerb Melvin C. (Renton WA), Integrated alternate gear extension and ground-crew door opening/closing system for an aircraft.
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Blakeley Anthony (Rockford IL) Konicek Timothy S. (Rockford IL) Horihan Gregory E. (Rockford IL) Sherman William D. (Hampshire IL), Support strut for ram air driven turbine.
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