IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0417667
(2012-03-12)
|
등록번호 |
US-8684314
(2014-04-01)
|
우선권정보 |
EP-11290147 (2011-03-25) |
발명자
/ 주소 |
- Chaduc, Bruno
- Hellio, Patrick
- Gemmati, Bernard
- Krok, Karsten
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
10 |
초록
▼
For emergency piloting of a manual flight control system (7) of an aircraft (1), in the event of flexible connection means (26) breaking, an upstream control device (8) takes authority over the electronic control unit (29) of series actuator (21). An output pivoting quadrant (25) is subjected by a c
For emergency piloting of a manual flight control system (7) of an aircraft (1), in the event of flexible connection means (26) breaking, an upstream control device (8) takes authority over the electronic control unit (29) of series actuator (21). An output pivoting quadrant (25) is subjected by a centering rod (22) to a blocking and centering action. In the event of the system breaking, the output pivoting quadrant (25) forms a bearing point for the series actuator (21), so that an emergency control actuate a airfoil surface (11).
대표청구항
▼
1. An emergency piloting method for a manual flight control system of an aircraft, the manual flight control system being arranged to include from upstream to downstream, at least: a manual flight control device, intermediate mechanical connections for control transmission, and an airfoil surface fo
1. An emergency piloting method for a manual flight control system of an aircraft, the manual flight control system being arranged to include from upstream to downstream, at least: a manual flight control device, intermediate mechanical connections for control transmission, and an airfoil surface for changing the flight attitude of the aircraft; the method providing at least one intermediate mechanical connection that is arranged to include a mechanical terminal transmission with an input pivoting quadrant upstream therefrom, at its upstream end, an output pivoting quadrant at its downstream end, and at least one flexible connection means, and that is arranged for said manual flight control system that includes at least one centering rod to be provided with at least one series actuator coupled to an electronic control unit, wherein said mechanical terminal transmission is arranged to include towards the downstream end, at least one series actuator in parallel with at least one centering rod, said output pivoting quadrant possessing at least two distinct off-center pivoting hinges; one of these hinges being an off-center hinge for transmitting control to said airfoil surface so that said airfoil surface is under the authority of said system, the method making provision for using said off-center control transmission hinge to connect said series actuator to the output pivoting quadrant, while another off-center hinge, which is an emergency centering hinge is arranged to connect said centering rod to the output pivoting quadrant; and wherein in the event of a breakage of said flexible connection means, the upstream control device takes authority over the electronic control unit of the series actuator, while the output pivoting quadrant is subjected by said centering rod to a centering action, such that said output pivoting quadrant forms a bearing point for the series actuator, and emergency control is transmitted from the control device to the electronic control unit in such a manner as to actuate the airfoil surface downstream. 2. A manual flight control system for an aircraft, said manual flight control system comprising from upstream to downstream, at least: a manual flight control device, intermediate mechanical connections for control transmission, and an airfoil surface for changing flight attitude of the aircraft, at least one intermediate mechanical connection including a mechanical terminal transmission, with: an upstream input pivoting quadrant, a downstream output pivoting quadrant, and at least one flexible connection means, the flexible connection means being arranged between the input pivoting quadrant and the output pivoting quadrant and being arranged to transmit rotary control movements between said pivoting quadrants, the manual flight control system including at least one centering rod and at least one series actuator logically connected to an electronic control unit for said series actuator, wherein said mechanical terminal transmission includes downstream at least one series actuator in parallel with at least one centering rod, said output pivoting quadrant possessing at least two distinct off-center pivot hinges: one off-center hinge for transmitting control to said airfoil surface under the authority of the manual flight control system, said off-center hinge for transmitting control connecting said series actuator to the output pivoting quadrant, another off-center hinge being an emergency centering hinge that connects said centering rod to the output pivoting quadrant, a hinge remote from the manual flight control system connecting said centering rod to a fixed structure of the aircraft to be equipped with this system longitudinally opposite from the output pivoting quadrant, said output pivoting quadrant thus acting, in the event of said flexible connection means breaking, to form a bearing point for said series actuator, with said series actuator being subjected to the authority of the manual flight control device via the electronic control unit. 3. A manual flight control system according to claim 2, wherein said mechanical terminal transmission includes, downstream: a single series actuator in parallel with a single centering rod, said single series actuator being hinged directly firstly to the output pivoting quadrant and secondly to crank means leading to said airfoil surface, the single centering rod being hinged directly firstly to the output pivoting quadrant and secondly to a fixed structural pivot. 4. A manual flight control system according to claim 2, wherein said mechanical terminal transmission includes, downstream: at least one pair of series actuators, and interposed between the series actuators of a pair, a rocker having a middle pivot in a fixed location, each pair of series actuators being in parallel with at least one centering rod. 5. A manual flight control system according to claim 2, wherein said electronic control unit of the series actuator(s) downstream from the output quadrant is logically under the shared authority of an autopilot system and of said manual flight control device. 6. A manual flight control system according to claim 2, wherein the manual flight control system transmits piloting authority concerning a change in flight attitude of the aircraft in yaw, and said manual flight control device in the form of a pedal. 7. A manual flight control system according to claim 6, wherein the airfoil surface is in the form of blades of an anti-torque tail rotor. 8. A manual flight control system according to claim 2, wherein the manual flight control system transmits piloting authority concerning a change of flight attitude of the aircraft in roll, and said manual flight control device is in the form of a cyclic stick. 9. A manual flight control system according to claim 2, wherein said manual flight control system transmits piloting authority over a change of flight attitude of the aircraft in pitching, and said manual flight control device is in the form of a cyclic stick. 10. A manual flight control system according to claim 2, wherein said manual flight control system includes power assistance downstream from said series actuator hinged to the output pivoting quadrant, the power assistance being in the form of a servo-control or the like interposed upstream from the airfoil surface under the authority of the manual flight control system and downstream from said output quadrant. 11. A manual flight control system according to claim 2, wherein said manual flight control system includes a mixer upstream from said mechanical terminal transmission, the mixer being interposed between the manual flight control device and said input pivoting quadrant. 12. A manual flight control system according to claim 2, wherein the manual flight control system includes flexible connection means provided with two cables in parallel, each having an upstream end and a downstream end, an upstream of each of the two parallel cables being coupled to the input pivoting quadrant while a downstream end of each cable of the flexible connection means is coupled in normal operation to the output pivoting quadrant. 13. A manual flight control system according to claim 2, wherein in the mechanical terminal transmission along a longitudinal axis (X) each series actuator in parallel with said centering rod is at least in part contiguous or substantially colinear with said centering rod. 14. An aircraft implementing the method according to claim 1, wherein the aircraft is a rotary wing aircraft. 15. An aircraft according to claim 14, wherein the airfoil surface is an anti-torque tail rotor, and the manual flight control system acts on a flight attitude of the aircraft in yaw. 16. An aircraft including one or more manual flight control systems according to claim 2, wherein the aircraft is a rotary wing aircraft. 17. An aircraft according to claim 16, wherein the airfoil surface is an anti-torque tail rotor, and the manual flight control system acts on a flight attitude of the aircraft (1) in yaw.
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