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Augmenting flight control surface actuation system and method

A technology of flight control surfaces and actuators, which is applied in the field of flight control surface actuation systems, and can solve problems such as low efficiency and low PCU efficiency

Active Publication Date: 2006-02-08
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] PCU designed according to stall load and required speed results in inefficiency due to flight dynamics
That said, at high speeds and low load conditions (e.g., near "aerodynamic neutral" or zero load on flight control surfaces), conventional PCUs are relatively inefficient in terms of required horsepower and hydraulic system weight

Method used

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  • Augmenting flight control surface actuation system and method
  • Augmenting flight control surface actuation system and method
  • Augmenting flight control surface actuation system and method

Examples

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Embodiment Construction

[0016] See attached figure 1 , shows an enlarged flight control surface actuation system, generally indicated at 10, in accordance with a preferred embodiment of the present invention. Typically system 10 includes an enlarged PCU 12 including a manifold 14, a first actuator 16 and a second actuator 18 having an assist mode and a bypass mode. The enlarged PCU 12 is fluidly connected to a pressure source P (eg, a fluid reservoir 20 and a pump 22 ) that provides pressurized working fluid to the enlarged PCU 12 . In use, the mode of operation of the second actuator 18 (i.e. assist and bypass modes) is based at least in part on the internal pressure differential across the first actuator 16 such that the second actuator 18 does not absorb any hydraulic pressure until high loads are required.

[0017] During low load conditions, the second actuator 18 is bypassed and remains in a passive or standby mode so that the first actuator 16 provides power to the flight control surfaces. ...

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Abstract

Apparatus (10) for providing actuation power to an aircraft flight control surface. The apparatus includes a first actuator (16) and a second actuator(18), where the second actuator has a bypass mode and an assist mode. The mode of the second actuator is determined by an internal differential pressure across the first actuator. The apparatus further includes a mode select valve (40) for selecting between the bypass mode and the assist mode for the second actuator, and a solenoid valve (48) that when energized causes the mode select valve (40) to select the other mode for the second actuator. When the second actuator is in the bypass mode, the first actuator provides the actuation power for the aircraft flight control surface. But, when the second actuator is in the assist mode, both the first and second actuators provide the actuation power for the aircraft flight control surface. Accordingly, the apparatus allows the flight control surface to be operated in a more efficient manner with less hydraulic flow being required.

Description

technical field [0001] The present invention relates to actuation systems of aircraft and more particularly of flight control surfaces. Background technique [0002] The Power Controller (PCU) is used to apply loads to position and maintain aircraft flight control surfaces such as ailerons, elevators, rudders, spoilers, etc. in position. Traditional PCUs are usually sized based on stall load and required speed. The required speed generally refers to low load, or an unloaded condition, a low load condition, or a maximum allowable time to move from a surface faired to a specified surface position in a specified flight condition. For simplicity, the description below is based on the no-load speed requirements. Stall load refers to the maximum force that the PCU actuator can exert. Maximum idle speed refers to the fastest movable speed of the actuator's piston when the control valve is wide open and no load is acting on the actuator. [0003] Designing the PCU according to t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C13/42F15B11/036F15B18/00B64C13/40
CPCY02T50/44B64C13/42B64C13/40Y02T50/40
Inventor 理查德·M·克兰茨
Owner THE BOEING CO
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