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Deployable aerodynamic devices with reduced actuator loads

An actuator device and actuator technology, applied in the direction of aircraft transmission, aircraft power device, power amplification, etc., can solve the problems of reducing aircraft efficiency, difficulty in incorporating into aircraft, and consumption of large actuators

Inactive Publication Date: 2012-12-05
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] A disadvantage with many conventional leading and trailing edge devices is that the actuators used to power these devices tend to be large in size in order to overcome the aerodynamic forces acting against the device as the device deploys into the adjacent airflow,
Large devices are difficult to incorporate into aircraft, and the weight of such devices reduces aircraft efficiency
Additionally, large actuators consume an extremely large amount of power and thus further reduce aircraft efficiency

Method used

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  • Deployable aerodynamic devices with reduced actuator loads
  • Deployable aerodynamic devices with reduced actuator loads
  • Deployable aerodynamic devices with reduced actuator loads

Examples

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Embodiment Construction

[0062] Aspects of the invention generally relate to deployable devices with reduced actuator loading, and systems and methods therefor. In the context of aircraft equipment (eg, fixed-wing and rotary-wing aircraft), a representative deployable device will be described below, although in other embodiments the device can be mounted on other external fluids. For the sake of brevity, some details describing structures or processes that are well known and at times associated with the systems and methods are not mentioned in the following description. Additionally, while the following disclosure presents some representative embodiments of systems and methods that can include actuators with reduced load requirements, some other embodiments can have configurations and / or or parts. Accordingly, this embodiment may include additional elements and / or may remove the following references Figure 1-8 One or more elements described.

[0063] figure 1 An isometric view of an aircraft 105 ...

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Abstract

The invention relates to deployable aerodynamic devices with reduced actuator loads, and related systems and methods. An external flow system in accordance with a particular embodiment includes an external flow body, a deployable device carried by and movable relative to the external flow body, and a coupling connected between the external flow body and the deployable device. The system can further include an actuator device operatively coupled between the external flow body and the deployable device, with the actuator device positioned to move the deployable device along a motion path between a stowed position and the deployed position. The motion path can have a first portion over which the load delivered by the actuator device increases as the deployed device moves toward the deployed position, and a second portion over which the load delivered by the actuator device decreases as the deployed device moves toward the deployed position.

Description

[0001] related application [0002] This application is a continuation-in-part of U.S. Patent Application Serial No. 11 / 953672, filed December 10, 2007, and claims priority therefrom. technical field [0003] Aspects of the invention generally relate to deployable devices (eg, pneumatic devices) with reduced actuator loading, and related systems and methods. Background technique [0004] For many years, deployable leading and trailing edge devices have been used to control the attitude and lift / drag characteristics of modern aircraft. In particular, conventional trailing edge ailerons located on the left and right aircraft wings are deployed asymmetrically, thereby turning the aircraft. Conventional trailing edge flaps are usually deployed symmetrically, resulting in a high-lift wing configuration suitable for landing and takeoff. The flaps are then stowed for more efficient operation in cruise conditions. Conventional leading edge devices such as slats can also be deploy...

Claims

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Application Information

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IPC IPC(8): B64C9/02B64C9/10B64C9/32B64C9/34B64C13/38
CPCY02T50/44B64C9/02Y02T50/32Y02T50/30Y02T50/40
Inventor G·S·布什内尔
Owner THE BOEING CO