초록 ▼

A backup system is provided that has a local electric motor and pump for some or all of the hydraulic actuators on an aircraft. A local backup hydraulic actuator has two power sources, hydraulic as primary and electrical as backup. During normal operation, the hydraulic actuator receives pressurized

A backup system is provided that has a local electric motor and pump for some or all of the hydraulic actuators on an aircraft. A local backup hydraulic actuator has two power sources, hydraulic as primary and electrical as backup. During normal operation, the hydraulic actuator receives pressurized fluid from a hydraulic system and the fluid flow to the chambers is controlled by a servo valve. If the hydraulic system fails, the electronic controller detects the failure by observing the signal indicative of the pressure from the pressure sensor, and the controller powers the local hydraulic pump to provide high pressure hydraulic fluid to the hydraulic actuator via the servo valve.

대표청구항 ▼

The invention claimed is: 1. A flight control system for an aircraft, comprising: a plurality of flight control surfaces movably attached to said aircraft; a plurality of hydraulic actuators coupled to said aircraft, said hydraulic actuators configured to position said flight control surfaces; a fi

The invention claimed is: 1. A flight control system for an aircraft, comprising: a plurality of flight control surfaces movably attached to said aircraft; a plurality of hydraulic actuators coupled to said aircraft, said hydraulic actuators configured to position said flight control surfaces; a first central pressure source providing hydraulic fluid under high pressure to a first group of said plurality of hydraulic actuators; a second central pressure source for providing hydraulic fluid under pressure to a second group of said plurality of hydraulic actuators; at least one local pump unit coupled to a first hydraulic actuator within the plurality of hydraulic actuators, each local pump unit including a one-way pressure pump for providing hydraulic fluid under high pressure to said hydraulic actuator, a connection to the first central pressure source for providing hydraulic fluid under high pressure to said first actuator, and a motor for driving said pump, each of said hydraulic actuators being coupled to one of said flight control surfaces; a pressure sensor outputting a signal indicative of the pressure of the first central pressure source; a controller receiving the signal from the pressure sensor and configured to active said one-way pressure pump upon the signal indicating a pressure reduction below a threshold value of the first central pressure source; and a flight control surface within said plurality of flight control surfaces having said first hydraulic actuator coupled thereto and also having a second hydraulic actuator within the plurality coupled thereto to cause movement of the flight control surface when either the first or second or both of the hydraulic actuators are activated, the first hydraulic actuator being coupled to both the first central pressure source and the at least one local pump unit and the second hydraulic actuator being coupled solely to the second central pressure source, and not coupled to the at least one local pump unit. 2. The flight control system for an aircraft of claim 1, wherein said flight control surfaces comprise at least one of: rudder, elevators, ailerons, or spoilers. 3. The flight control system for an aircraft of claim 1, wherein a single local pump unit is coupled to a second plurality of hydraulic actuators with the plurality of hydraulic actuators that are coupled to the first central pressure source and are adjacent to the single local pump. 4. The flight control system of claim 1 wherein the first and second hydraulic actuators that are coupled to the same flight control surface are identical to each other in structural configuration. 5. The flight control system of claim 1 wherein each hydraulic actuator that is part of the plurality of hydraulic actuators throughout the aircraft are identical to each other in structural configuration. 6. The flight control system for an aircraft of claim 1, further comprising: a third plurality of hydraulic actuators within the plurality of hydraulic actuators coupled to a single flight control surface, each of the third plurality of hydraulic actuators that are coupled to the single flight control surface having a local pump unit connected thereto. 7. The flight control system of claim 6 further comprising: a mode select valve coupled to each hydraulic actuator, the mode select valve having only two modes of selection, active control under hydraulic pressure and damped operation that provides some resistance to movement. 8. The flight control system of claim 7 wherein the single flight control surface is a rudder. 9. The system according to 1 further including: a pressure sensor coupled to the second central pressure source, said second pressure sensor outputting a signal indicative of the pressure value in the second central pressure source. 10. The system according to claim 1 wherein the first flight control surface is an elevator and further including a rudder as a second flight control surface within the plurality of flight control surfaces; a third hydraulic actuator within the plurality of hydraulic actuators coupled to said rudder; a fluid pressure line coupling the third hydraulic actuator to the first central pressure source; a fluid pressure line from the at least one local pump unit to the third hydraulic actuator, the local pump unit configured to provide fluid under pressure to both the first and third hydraulic actuators when it is activated. 11. The system according to claim 1 wherein the first flight control surface is an aileron and further including a spoiler as a second flight control surface within the plurality of flight control surfaces; a third hydraulic actuator within the plurality of hydraulic actuators coupled to said spoiler; a fluid pressure line coupling the third hydraulic actuator to the first central pressure source; a fluid pressure line from the at least one local pump unit to the third hydraulic actuator, the local pump unit configured to provide fluid under pressure to both the first and third hydraulic actuators when it is activated. 12. The system according to claim 1 wherein the controller outputs an activation signal during take-off and landing to provide fluid under pressure to the first hydraulic actuator from both the first central pressure system and the local pump unit during take-off and landing. 13. The flight control system of claim 1, further including: a second flight control surface acting as a spoiler within said plurality of flight control surfaces having a third hydraulic actuator within the plurality of hydraulic actuators coupled thereto to cause movement of the flight control surface when the hydraulic actuator is activated, the third hydraulic actuator being coupled to both the first central pressure source and the local pump unit. 14. The flight control system of claim 1, further including: a second flight control surface acting as a rudder within said plurality of flight control surfaces having two hydraulic actuators coupled thereto within the plurality of hydraulic actuators coupled thereto to cause movement of the flight control surface when either of the two hydraulic actuators or both of the hydraulic actuators are activated, a first hydraulic actuator of the two hydraulic actuators being coupled to both the first central pressure source and a first local pump unit and a second hydraulic actuator of the two hydraulic actuators being coupled to both the second central pressure source, and a second local pump unit. 15. A hydraulic control system for an aircraft, comprising: a plurality of flight control surface actuator assemblies within said aircraft, each flight control surface actuator assembly including a hydraulic actuator and a cylinder/piston assembly; first and second central pump systems coupled respectively to each of the flight control surface actuator assemblies within the plurality of actuator assemblies, all flight control surface actuator assemblies in the aircraft being coupled to either the first or second central pump systems and none of them coupled to a third central pump system; a first flight control surface having solely first and second flight control surface actuators of the plurality of actuators assemblies coupled thereto; a second flight control surface having solely third and fourth flight control surface actuators of the plurality of actuators assemblies coupled thereto; the first central pressure pump system providing hydraulic fluid under high pressure to said first and third actuators assemblies; the second central pressure pump system providing hydraulic fluid under high pressure to said second and fourth actuators assemblies; a first local pressure pump assembly comprising a first one-way pressure pump configured to provide hydraulic fluid under high pressure to the first flight control surface actuator assembly and not to the second flight control surface actuator assembly upon receiving an activation signal; a second local pressure pump assembly comprising a second one-way pressure pump configured to provide hydraulic fluid under high pressure to the fourth flight control surface actuator assembly and not to the third flight control surface actuator assembly upon receiving an activation signal; pressure sensors coupled respectively to the first and second central pressure pump systems for detecting a reduction in operational hydraulic pressure provided either of said first or second central pressure pump system and generating a low pressure indication signal that causes said activation signal to be sent to the first local pressure pump configured to provide pressure to the first hydraulic actuator assembly when the pressure in the first central pump system is lower than a threshold amount and generating a low pressure indication signal that causes said activation signal to be sent to the second local pressure pump configured to provide pressure to the fourth hydraulic actuator assembly when the pressure in the second central pump system is lower than a threshold amount.