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Hypersonic speed guided missile multi-field coupling dynamics integrated simulation analysis method

A hypersonic missile and coupled dynamics technology, applied in special data processing applications, instruments, electrical digital data processing, etc., to achieve the effect of correct and reliable calculation results and improved calculation efficiency

Inactive Publication Date: 2013-05-01
SHANGHAI INST OF ELECTROMECHANICAL ENG
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Problems solved by technology

[0004] The purpose of the present invention is to provide an integrated simulation analysis method for hypersonic missile multi-field coupling dynamics, and comprehensively solve the stability problems of aeroelasticity and aeroservoelasticity

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  • Hypersonic speed guided missile multi-field coupling dynamics integrated simulation analysis method
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  • Hypersonic speed guided missile multi-field coupling dynamics integrated simulation analysis method

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Embodiment Construction

[0031] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0032] Such as figure 1 As shown, the multi-field coupled dynamics integration simulation analysis steps of the present invention are as follows:

[0033] 1) Establish a coupled structural equation of motion

[0034] Considering the physical model of high-speed winged missile composed of body, wing and empennage, when performing structural dynamics analysis or simulation, the mass matrix and stiffness matrix solutions are usually obtained by using the mode superposition method or branch mode method Coupled or quasi-decoupled differential equations of motion

[0035] [ M ] { ξ · · } + [ C ] { ξ · } + [ K ] ...

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Abstract

The invention provides a hypersonic speed guided missile multi-field coupling dynamics integrated simulation analysis method, which comprises the following steps of: establishing a coupled structural motion equation; improving an aerodynamic heating calculation method; improving an unsteady aerodynamics calculation method; establishing an integrated simulation analysis technique process; designing a relationship between an integrated simulation analysis operation model and data; and realizing an integrated simulation analysis system. Compared with the prior art, the aerodynamic heating calculation method and the unsteady aerodynamics calculation method are improved; various techniques of flutter analysis, thermal flutter analysis, pneumatic servo elastic analysis and thermal pneumatic servo elastic analysis are integrated; and an effective integration method for integrally solving and optimally designing a high-speed winged missile all-missile combination body coupling dynamics problem is provided.

Description

technical field [0001] The present invention relates to the overall technology of missiles, and specifically belongs to an analysis method of aeroelasticity and aeroservoelastic stability of hypersonic missiles considering the influence of aerodynamic heating, which realizes aerodynamic heating, three-dimensional temperature field, thermal mode, and unsteady gas flow for missiles with complex shapes. Integrated simulation analysis of dynamic, thermal flutter and aeroservoelastic stability. Background technique [0002] When the missile is flying at high speed and high maneuverability, it will bring serious aerodynamic heating and aeroelastic coupling, as well as the coupling effect between the servo control system and the elastic deformation of the projectile, which will seriously affect the aeroservoelastic stability of the missile, leading to suddenness and disaster The permanent projectile fracture accident is a problem that exists in the integrated design of high-speed m...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCY02T90/00
Inventor 刘超峰杨炳渊史晓鸣许斌李海东唐晓峰
Owner SHANGHAI INST OF ELECTROMECHANICAL ENG
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