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A Modeling Method for Elastic Motion of Trailing Edge Rudder Glide Vehicle

A modeling method and elastic motion technology, applied in the direction of instruments, adaptive control, control/regulation systems, etc.

Active Publication Date: 2019-01-08
BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST +1
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Problems solved by technology

However, the traditional simplified elastic motion modeling method (reference: "Missile and Aerospace Series - Control System (Part 1)", section 2.3.4) is no longer suitable for a new generation of hypersonic plane symmetric aircraft controlled by trailing edge rudders. then apply

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  • A Modeling Method for Elastic Motion of Trailing Edge Rudder Glide Vehicle
  • A Modeling Method for Elastic Motion of Trailing Edge Rudder Glide Vehicle
  • A Modeling Method for Elastic Motion of Trailing Edge Rudder Glide Vehicle

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Embodiment Construction

[0110] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0111] For strategic missiles and launch vehicles, when researching and designing their attitude control systems, the influence of elastic deformation of the missile body must be considered. The elastic motion modeling method of trailing edge rudder gliding aircraft of the present invention is:

[0112] (1) Using the modal orthogonality, the lateral free vibration of the projectile can be converted into the superposition of independent main vibrations; (2) According to the linear small disturbance assumption, under the action of external force, the lateral vibration of the projectile can still be approximated by Mode superposition is described, and the mode shape function is determined by the structural characteristics (stiffness and mass distribution) of the projectile and the boundary conditions of the projectile; (3) establish a vibration ...

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Abstract

The invention belongs to the technical field of aircraft elastic motion modeling, and specifically relates to an elastic motion modeling method of a trailing edge rudder gliding aircraft. The method comprises the following steps: (1) converting an elastic body transverse free vibration into superposition of various mutually independent main vibrations by utilizing modal orthogonality; (2) according to a linear small disturbance hypothesis, under the action of external forces, still describing the transverse vibration of an elastic body approximatively by utilizing modal superposition, and determining a vibration mode function by structural characteristics (rigidity and quality distribution) of the elastic body and a boundary condition of the elastic body; (3) establishing a vibration differential equation according to the d'almbert's principle and other methods; and (4) analyzing the external forces, which comprise an aerodynamic force, a rudder surface control force, a posture jet pipe control force, a rudder surface swinging inertia force and the like, influencing an elastic vibration of the gliding aircraft. A traditional elastic motion modeling method is corrected and improved.

Description

technical field [0001] The invention belongs to the technical field of aircraft elastic motion modeling, and in particular relates to an elastic motion modeling method of a trailing edge rudder gliding aircraft. Background technique [0002] With the continuous improvement of flight speed and maneuverability, the dynamics of aircraft elastic structure coupled with aerodynamic and control systems has been paid more and more attention. As the control object of the elastic aircraft, the sensitive components of the attitude control system not only sense the motion of the rigid body, but also feel the vibration of the elastic structure. The elastic motion equation used to describe the elastic vibration of the aircraft, the correctness of the model is related to the success or failure of the attitude control system design. However, the traditional simplified elastic motion modeling method (reference: "Missile and Aerospace Series - Control System (Part 1)", section 2.3.4) is no l...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04
Inventor 袁锐知高庆张皓卢凤翎梁德利杨巍王建滨王骁峰
Owner BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST
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