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Missile wing active-flutter suppressing method based on L1 adaptive control algorithm

A self-adaptive control and wing technology, applied in the direction of projectiles, offensive equipment, weapon types, etc., to achieve the effect of improving the flutter boundary speed, good stability, and good effect

Active Publication Date: 2020-05-19
西安智芯通达科技有限公司
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Problems solved by technology

In the process of changing the sweep angle, the aerodynamic parameters, aerodynamic center, center of gravity, and moment of inertia of the aircraft will change greatly, and the conditions for flutter caused by the elastic structure and aerodynamic coupling will also change. Flutter suppression for missiles presents significant challenges

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  • Missile wing active-flutter suppressing method based on L1 adaptive control algorithm
  • Missile wing active-flutter suppressing method based on L1 adaptive control algorithm
  • Missile wing active-flutter suppressing method based on L1 adaptive control algorithm

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Embodiment Construction

[0036] The present invention will now be further described in conjunction with the embodiments and drawings:

[0037] The present invention takes the variant cruise missile as the research object, and proposes a method suitable for the active flutter suppression of the missile wing during the process of changing the sweep angle of the variant cruise missile. First, the binary wing section with front and trailing edge control surfaces is used as the research object, and the aeroelastic system model of the binary wing is established; then the flutter velocity of the system is solved, and the flutter analysis of the model is carried out; The aeroelastic system model of the two-element missile wing is established to design the L1 adaptive controller; finally, the flutter suppression effect of the L1 adaptive controller in the process of varying the sweep angle is simulated and analyzed.

[0038] The present invention includes the following steps:

[0039] Step 1 According to the wing ty...

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Abstract

The invention relates to a missile wing active-flutter suppressing method based on an L1 adaptive control algorithm. The missile wing active-flutter suppressing method based on the L1 adaptive controlalgorithm comprises the steps that firstly, a binary wing segment with a front edge control surface and a rear edge control surface is taken as a research object to establish an aeroelastic system model of a binary missile wing; then the flutter speed of the system is solved, and the model is subjected to flutter analysis; then an L1 adaptive controller is designed for the established aeroelasticsystem model of the binary missile wing; and finally, the flutter suppressing effect of the L1 adaptive controller is subjected to simulated analysis during the variable sweep angle.

Description

Technical field [0001] This invention belongs to the field of missile body control technology. This technical invention takes the variant cruise missile as the research object, and establishes the aeroelastic system model of the binary missile wing based on the binary wing section with front and rear edge control surfaces. An algorithm based on L1 adaptive control that actively suppresses the flutter of the wing during the process of changing the sweep angle of the variant cruise missile. Background technique [0002] The rudder surface of the traditional missile is relatively small, so that it has a relatively fast speed, can achieve rapid attack on the target, but the empty time is relatively short, can only attack the target that has been found, does not have the "second strike" capability. Then came the cruise missile, which is a new type of ammunition that can patrol over the target area for a long time and perform single or multiple combat tasks on standby. The cruise miss...

Claims

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Application Information

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IPC IPC(8): F42B10/02
CPCF42B10/02
Inventor 智永锋
Owner 西安智芯通达科技有限公司
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