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A distributed drive integral tension deformable wing device and control method

A technology of overall tensioning and control methods, applied in the direction of program control, computer control, general control system, etc., can solve the problems of few existing achievements

Inactive Publication Date: 2019-01-29
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, there are few existing achievements in the control system design of distributed-driven deformable wings

Method used

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  • A distributed drive integral tension deformable wing device and control method
  • A distributed drive integral tension deformable wing device and control method
  • A distributed drive integral tension deformable wing device and control method

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Embodiment Construction

[0060] The present invention provides a distributed-driven overall tension-type deformable wing device and control method. In order to make the technical solution and effect of the present invention clearer and clearer; this embodiment further describes the present invention in detail with reference to the accompanying drawings and examples. It should be understood that the specific implementations described here are only used to explain the present invention, not to limit the present invention.

[0061] The specific steps of a distributed-driven overall tension-type deformable wing device and control method are as follows:

[0062] Step 1: Build the whole stretched deformation wing device.

[0063] The integrally tensioned deformation wing device with distributed drive is mainly composed of a two-layer three-unit distributed tensioned integral structure, a driver, a sensor and a control computer. The distributed tension overall structure is composed of trusses, ropes and ten...

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Abstract

A distributed driven overall tensioning type morphing wing device disclosed by the present invention comprises two layers of three-unit distributed tensioning overall structures, a driver, a sensor and a control computer. A control method of the morphing wing device also disclosed by the present invention concretely comprises the steps of 1 building the overall tensioning type morphing wing device; 2 establishing a non-linear dynamic model of a morphing wing; 3 establishing the first layer of control structures to enable a nominal system to track the desired shapes; 4 establishing the second layer of control structures to enable an actual morphing wing system to track the nominal system and converge to the desired shapes finally. By the control method of the two layers of control structures, the aerodynamic configuration active change of an aircraft is realized, thereby providing an effective method for improving the aerodynamic efficiency. The device is concise in structure, and the control method is strong in robustness, so that the shape tracking control of the morphing wing can be guaranteed on a condition of larger uncertainty.

Description

technical field [0001] The invention belongs to the field of active control of flexible structures, and specifically relates to a distributed-driven overall tension-type deformable wing device and a control method. Background technique [0002] The morphing aircraft improves the aerodynamic performance and expands the flight envelope by actively changing the shape of the wings. Deformable wings are key components of morphing aircraft. There are two types of deformation structures, the centralized drive type and the distributed drive type, in the current research on the variant aircraft. Among them, the centralized drive deformation structure has the advantage of being relatively simple to manufacture, but the drive bears a large load and requires high strength, resulting in a large structure weight, and the deformation form is fixed and single. At the same time, when the drive fails, it will cause the aircraft to fail. . In contrast, in the distributed drive deformation s...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B19/042
CPCG05B19/042
Inventor 何真袁亮于晓至
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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