Leading edge impact and tiny cross passage cooling structure for hypersonic vehicle

Abstract

The invention discloses a leading edge impact and tiny cross passage cooling structure for a hypersonic vehicle, which comprises an impact cavity, impact holes and tiny cross passages, wherein the impact cavity is positioned inside the front edge of the hypersonic vehicle, a line of impact holes are arranged in the axis at the middle of one side of the impact cavity, which is close to a hypersonic vehicle body, two ends of the impact holes are communicated with the impact cavity and an air supply cavity; the upper surface and the lower surface of the impact cavity, which are close to the surface of a hypersonic vehicle wedge body, are provided with tiny cross passages; and the tiny cross passages are connected with the impact cavity and tail air. Aiming at the characteristics of larger density of heat flow at the front edge of the hypersonic vehicle, small quantity and more uniform distribution of heat flow on the surface of the wedge body, the impact is combined with the tiny passages mutually, thus the heat exchange efficiency is greatly improved.

Description

technical field [0001] The invention relates to a leading edge impact + tiny staggered channel cooling structure of a hyper-vehicle, which belongs to the field of local heat exchange with high heat flux density in aviation, aerospace, power machinery and the like. Background technique [0002] Hypersonic aircraft is the relentless pursuit of mankind in the new century, and its application prospects are obvious. In terms of business, hypersonic passenger aircraft can travel around the world in a few hours, leaving early and returning late, and the trans-Pacific passenger traffic will increase significantly. Civilian hypersonic passenger aircraft have broad application prospects in the 21st century. In terms of military affairs, for the consideration of space resource development and national defense security, hypersonic military aircraft and missiles will raise the air combat platform to a new level. At present, many countries in the world are starting to study hypersonic te...

AI Technical Summary

Problems solved by technology

Traditional passive cooling, such as radiative cooling, requires a high surface temperature to achieve high radiative heat flux density, so it cannot meet the requirements for material strength and service life. Although the thermal protection structure of the ablation layer can meet the requirements of high heat flux density, However, it cannot be applied to hypersonic vehicles with a flight time of tens of minutes or even hours.

Images