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Elastic hypersonic aircraft modeling method based on computational mechanics

A hypersonic, modeling method technology, applied in the field of computational mechanics, can solve the problems of large amount of calculation and high difficulty in formula derivation, and achieve the effect of reducing complexity

Pending Publication Date: 2021-12-31
TIANJIN UNIV +1
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Problems solved by technology

These complex characteristics make the establishment of a six-degree-of-freedom hypersonic vehicle mathematical model require a large amount of calculations, and the formula derivation is difficult

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  • Elastic hypersonic aircraft modeling method based on computational mechanics
  • Elastic hypersonic aircraft modeling method based on computational mechanics
  • Elastic hypersonic aircraft modeling method based on computational mechanics

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Embodiment Construction

[0091] In order to make the purpose, technical solutions and advantages of the present invention clearer, the present invention will be discussed in detail below in conjunction with the accompanying drawings and examples. The following examples are only descriptive, not restrictive, and cannot limit the protection scope of the present invention with this .

[0092] The flight environment and flight conditions of hypersonic vehicles are very complex, requiring complex controllers and control algorithms to control them, which puts higher requirements on the model of the controlled object, but the current consideration of six degrees of freedom is flexible The dynamic model of the hypersonic vehicle is relatively complex, and has the characteristics of nonlinearity and strong coupling, which brings difficulties to the design of the controller. Therefore, the present invention proposes a method for establishing an elastic model based on simulation data. In the simulation calculat...

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Abstract

The invention discloses an elastic hypersonic aircraft modeling method based on computational mechanics. The method comprises the following steps: step 1, establishing a geometric model of a hypersonic aircraft and performing grid division; 2, based on computational fluid mechanics and computational structural mechanics, performing simulation calculation on elastic characteristics and aerodynamic parameters of the hypersonic aircraft under different working conditions to obtain fitting data; 3, establishing a rigid body dynamic model of the hypersonic aircraft according to the fitting data, and obtaining deformation angles of different positions according to a vibration equation; and 4, according to the rigid body dynamic model and the vibration equation, in combination with simulation calculation results in the above steps, obtaining a six-degree-of-freedom elastic dynamic model of the elastic hypersonic aircraft through curve fitting. On the basis that elastic characteristics under different working conditions are obtained, the aircraft rigid body dynamic model is expanded, the influence of the elastic characteristic is added, and a basis is provided for the integrated design of the shape of the aircraft and the design of a controller.

Description

technical field [0001] The invention belongs to the field of computational mechanics, in particular to a computational mechanics-based elastic hypersonic aircraft modeling method. Background technique [0002] Hypersonic vehicles have the characteristics of high flight speed, strong penetration capability, and large strike range. They have important strategic significance and extremely high application value. They are at the forefront of the development of aerospace technology. However, due to its extremely high flight speed, its control model has characteristics such as strong nonlinearity, strong coupling, fast time-varying, and uncertainty. From the point of view of fluid mechanics, the aerothermodynamic environment around a hypersonic vehicle is very complex; from the point of view of structural mechanics, the complex flow field environment makes the force situation of the vehicle very complicated, and there is also the influence of elastic characteristics. These comple...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/23G06F30/28G06F113/08G06F119/14
CPCG06F30/15G06F30/23G06F30/28G06F2113/08G06F2119/14Y02T90/00
Inventor 胡超芳米涵芃杨晓荷胡永太
Owner TIANJIN UNIV
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