Aerothermoelasticity calculation technology of multi-field coupling of trajectory status of hypersonic aircraft

A technology of hypersonic speed and computing technology, which is applied in computing, computer-aided design, instruments, etc., and can solve problems such as few prediction methods

Active Publication Date: 2018-04-20
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

However, there are few methods for predicting the thermal environment of structures under complex ballistic states.

Method used

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  • Aerothermoelasticity calculation technology of multi-field coupling of trajectory status of hypersonic aircraft
  • Aerothermoelasticity calculation technology of multi-field coupling of trajectory status of hypersonic aircraft
  • Aerothermoelasticity calculation technology of multi-field coupling of trajectory status of hypersonic aircraft

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Embodiment Construction

[0095] A thermoaeroelastic calculation method for multi-field coupling of a hypersonic vehicle ballistic state, comprising the following steps:

[0096] Under complex trajectories, the time-domain dynamic aeroelastic analysis of the entire trajectory is expensive, and can generally be simplified by ignoring weaker couplings and aerodynamic pressures that affect aerodynamic heating. This simplifies the thermoaeroelastic analysis into an aerothermal problem and a separate aeroelastic problem. figure 1 A general analysis procedure is given. That is, according to the ballistic state, the transient aerodynamic thermal environment at each point on the ballistic trajectory is predicted first, and then the structural temperature field is calculated based on the thermal environment, then the thermal mode of the structure under thermal action is analyzed, and finally the thermoaeroelastic analysis is carried out . The specific steps include:

[0097] Step 1. Long-term aerodynamic hea...

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Abstract

The invention discloses an aerothermoelasticity calculation method of multi-field coupling of trajectory status of hypersonic aircraft, and belongs to the field of aircraft aerodynamic-calculation. Inthe engineering fields of aerospace and the like, aircraft structures suffer severe aerodynamic heating effects with increasing of flying speed of the supersonic aircraft; and at the same time, flying trajectories are more complex due to more and more complex mission requirements, and aerodynamic heat environments are also more difficult to predict. Therefore, the aerothermoelasticity problem under the complex trajectories deserves attention. According to the method of the invention, a method of combination of inviscid-external-flow solutions and an engineering method is adopted for aerodynamic heating calculation of the high-speed aircraft, compared with a pure numerical method, the method of combination can save massive memory and calculation time, and reduces calculation costs, and compared with a pure engineering method, the same is wider in an application range, can be adapted to relatively complex shapes, and can also provide relatively-accurate aerodynamic heat solutions at thesame time.

Description

technical field [0001] The invention belongs to the field of aircraft aerodynamic calculation methods, in particular to a thermoaeroelastic calculation method for multi-field coupling of hypersonic aircraft ballistic state. Background technique [0002] In engineering fields such as aerospace, as the flight speed of supersonic vehicles increases, the structure of the aircraft suffers from severe aerodynamic heating. At the same time, due to the increasingly complex mission requirements, the flight trajectory is more complicated, and the aerodynamic and thermal environment is also more difficult to predict. The high temperature and temperature gradient generated by aerodynamic heating on the structure will reduce the mechanical properties of the structural material, and the uneven thermal deformation and thermal stress inside the structure will change the stiffness characteristics of the structure, and at the same time change the inherent vibration characteristics of the stru...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20G06F2119/08Y02T90/00
Inventor 李佳伟杨天鹏王江峰王钰涵李龙飞王丁
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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