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Ablation-free self-adaptive heat-resistant and damping system for high supersonic aerocraft

A hypersonic, aircraft technology, applied in aircraft, aerospace aircraft, aircraft parts, etc., can solve the problems of complex aerodynamic structure on the surface of the aircraft, increase the weight of the aircraft, etc., and achieve the effect of reducing shock wave resistance and reducing surface temperature.

Inactive Publication Date: 2008-10-08
INST OF MECHANICS - CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, several kinds of passive heat protection structures that are widely used increase the weight of the aircraft to varying degrees, and at the same time complicate the surface aerodynamic structure of the aircraft, and the damage of a certain part of these thermal protection systems may cause catastrophic consequences

Method used

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  • Ablation-free self-adaptive heat-resistant and damping system for high supersonic aerocraft
  • Ablation-free self-adaptive heat-resistant and damping system for high supersonic aerocraft

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Embodiment Construction

[0015] As shown in Figure 1, the present invention is to arrange a heat-resistant and good heat transfer pressure vessel 2 at the front end of the aircraft 1. The vessel 2 can be designed as a hemispherical shape suitable for gas flow, or it can be other suitable shapes such as a hemispheroid. The shape, as long as it satisfies the fluidity of the gas is relatively good. A certain amount of heated and evaporated liquid 5 is filled in the container 2, and a strut 3 and a strut top baffle 4 are arranged on the end face of the container 2 away from the aircraft 1 .

[0016] When flying at hypersonic speed, a head cone shock wave 8 will be formed around the aircraft 1, as shown in FIG. 2 . The high-temperature gas after the shock wave 8 will heat the pressure vessel 2 at the head of the aircraft, and the liquid 5 will absorb the heat of the container wall and evaporate, and will be ejected from the top of the strut 3, and cool the baffle plate 4 at the top of the strut, maintainin...

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PUM

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Abstract

The invention relates to a non-erosion self-adaptive flameproof damping system of hypersonic speed airplane, wherein the front end of airplane is arranged with one pressure container with better thermal conductivity; the container has some liquid; the head of airplane has one support rod; the top of support rod has baffle plate; when airplane is at hypersonic speed, via the support rod, the head flow field can be rectified to change the wave activation structure; since the wave can heat air and via the friction resistance, the surface temperature of airplane will increase quickly; the pressure container transmits energy to the liquid; and the liquid will be evaporated to be ejected at the sealing open at the top of support rod, to cool the baffle plate, and hold the head flow field.

Description

Technical field: [0001] The present invention is a high-tech aerospace engineering, which relates to a method of controlling the flow field structure of the head of a hypersonic aircraft, reducing the thermal environment, reducing the aerodynamic resistance of the aircraft, and forming a set of self-adaptive heat protection and heat protection without ablation on the surface of the aircraft. Drag reduction system. Background technique: [0002] For a class of hypersonic aircraft such as space shuttles and re-entry vehicles capable of re-entry into the atmosphere, hypersonic aircraft, interceptor missiles, and maneuverable missiles that can fly in the atmosphere, during flight at hypersonic speeds, due to the head bow shock The air around it is aerodynamically heated, and the temperature rises rapidly to thousands or even tens of thousands of degrees Celsius, which puts forward extremely high thermal protection requirements for the materials and structures of the aircraft its...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C1/38B64G1/22
Inventor 姜宗林韩桂来李岐
Owner INST OF MECHANICS - CHINESE ACAD OF SCI
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