CN107054698B

CN107054698B - Heat removing device for outer surface of spacecraft

Info

Publication number: CN107054698B
Application number: CN201710151664.1A
Authority: CN
Inventors: 沈武云
Original assignee: Individual
Current assignee: Individual
Priority date: 2017-03-07
Filing date: 2017-03-07
Publication date: 2021-04-06
Anticipated expiration: 2037-03-07
Also published as: CN107054698A

Abstract

After the engine (5) is started, suction force is generated in front of the engine, rear exhaust airflow enters the cone pipe (4), air pressure and flow velocity are increased, the flow is unchanged, the exhaust airflow enters the straight cylinders (2) with different diameters after exiting from the mouth of the cone pipe, a negative pressure vortex is formed at the outlet of each cone pipe and the outlet of each straight cylinder, the suction force generated by the rotation of the negative pressure vortex sucks air in the atmosphere into the negative pressure cavity (3) from micropores in the outer skin (1) and is mixed with high-speed air sprayed out of the cone pipe (4), the flow velocity of the mixed air is unchanged, the flow is increased, the horsepower of the engine is increased, and the air temperature in the negative pressure cavity (3) is lower than the temperature of the outside atmosphere. High temperature is not generated in the engine room any more, and heat generated by friction between the outer skin (1) and air is timely exhausted out of the engine body along with airflow sprayed by the engine. The engine works stably, and the temperature in the negative pressure cavity is constant. Therefore, the spacecraft can fly at any speed, and the safety of the spacecraft and the astronauts is ensured.

Description

Heat removing device for outer surface of spacecraft

The technical field is as follows: aerospace and the like.

Secondly, background art:

according to the situation known by the people at present, the space shuttle in America is characterized in that a layer of high-temperature resistant ceramic chip is adhered to the outer surface of a body of the space shuttle in the aspect of heat protection of the outer surface of the space shuttle, and the space shuttle enters the atmosphere in the previous year when the space shuttle returns to the earth, so that the space shuttle is burnt in the air due to the falling of the ceramic chip, and the death of people and people caused by machine damage is. The spacecraft returning capsule in China adopts a high-temperature-resistant steel plate on the surface and possibly has a speed reducing device, and the surface of the returned spacecraft returning capsule is burnt black. The temperature in the air is also estimated to exceed 1000 deg.c. This is also the speed at which it falls freely into the atmosphere, which would be the case if the flight speed were increased by a further factor of 2 to 10. The spacecraft can burn up due to high temperature generated by long-time and long-distance friction with air just like a meteor, and the spacecraft is changed into dust to be scattered in the universe.

Thirdly, the invention content:

more wonders in the universe are explored by modern human dreams, and the flight speed of the spacecraft is too slow and is not in direct proportion to the distant distance between the universe. The flight speed of the aircraft is too high, the spacecraft is changed into ash due to high temperature generated by the friction between the outer surface of the aircraft body and the air, the problem is that the current spaceman is always winding around, the realization of dream of the spaceman is prevented, the problem that the aerospace aircraft can fly at a high speed is solved, the problem that how the high temperature is not generated due to the friction between the outer surface of the spacecraft and the air is solved, the life safety of the aircraft and a spacecraft is protected, the problem that people conquer the universe and explore more wonderful universe, and people need to obtain more freedom in the universe is also an important problem which is not overcome. To solve this problem, the following two natural senses, namely, physical phenomena, must be recognized. The object moves in space, the higher the moving speed is, the higher the temperature generated by the friction between the surface of the object and the air is, and the generation process of the phenomenon is that the air is static and the object moves, the motion of the object is active, the air is passive, and the high temperature generated on the surface of the object cannot be eliminated in time, so that the temperature of the surface of the object is higher and higher until the object is completely gray. The flowing air is low in temperature, and the higher the flow rate, the lower the temperature. The designed heat removing device for the outer surface of the spacecraft utilizes the characteristic of low-temperature air of flowing air, before the spacecraft takes off, the surface of a cabin, namely the space between a cabin skin and an outer skin, enables the air in a negative pressure cavity to flow, the temperature of the air is firstly reduced and then the spacecraft takes off, the air in the negative pressure cavity flows from a turbine engine during working, the suction force generated by air inlet in front of the engine, namely the negative pressure, and the negative pressure generated by a wind power amplifier behind the engine are jointly used for sucking the air in the atmosphere into the negative pressure cavity through micropores on the outer skin of the spacecraft so as to reduce the temperature of the air in the negative pressure cavity to be lower than the temperature of the air outside the spacecraft, when the spacecraft flies at high speed or ultrahigh speed, the heat generated by friction between the outer skin of the spacecraft and the air can be timely discharged out of the spacecraft along with the air flow in the negative pressure, as long as the engine works and keeps a normal working state, the temperature in the negative pressure cavity can be kept in a low-temperature state all the time, and the temperature in the engine room can be lower than the temperature of the outside atmosphere, so cold-proof and warm-keeping measures are required to be taken in the engine room. Therefore, the dilemma that the spacecraft generates high temperature due to friction with air when flying at high speed is thoroughly eliminated, the spacecraft can fly at any speed in the universe and in the atmosphere and is not limited by the flying speed any more, and the life safety of the spacecraft and the astronauts is reliably guaranteed.

A wind power amplifier is arranged behind an engine, the working principle of the wind power amplifier is that gas exhausted by the engine enters a cone pipe, the gas pressure is gradually increased along with the gradual reduction of the sectional area of the cone pipe, the flow speed is gradually increased, the flow is unchanged, high-speed airflow exhausted from a cone pipe opening enters a plurality of straight cylinders with different diameters, the straight cylinders are staggered mutually to form a tower-shaped pipe, and a negative pressure vortex is formed at each outlet under the action of the high-speed airflow at the outlet of the cone pipe opening and the outlets of the straight cylinders. The negative pressure air is attractive, air in the atmosphere can be sucked into a negative pressure cavity from micropores on the outer skin of the machine body, sucked air molecules and high-pressure and high-speed airflow sprayed out of the cone pipe orifice are mixed and then discharged out of the machine body under the action of negative pressure vortex through the negative pressure cavity, the flow rate of the mixed air is unchanged, the flow is increased, and the horsepower of the engine is increased. The air flow in the negative pressure cavity reduces the air temperature, the heat generated by the friction between the outer surface of the engine body and the air is exhausted out of the engine body along with the flow of the air, and the tower-shaped pipe formed by the straight cylinder in the process also plays a role in noise elimination, so that the noise generated by the engine can be eliminated, and the problem of noise pollution of the high-horsepower turbine engine is solved.

Air molecules in the atmosphere are sucked into the negative pressure cavity under the combined action of front intake negative pressure and negative pressure generated by the wind power amplifier during the operation of the engine, and at the moment, the surface of the outer skin provided with the micropores can form a negative pressure surface, the air resistance of the negative pressure surface on the windward side can be reduced, the lift force of the spacecraft can be increased on the negative pressure surface above the aircraft body, and the load capacity of the spacecraft is improved. The part of the outer skin provided with the micropores can also play a role in ice prevention. The air flowing at high speed can not be frozen, other ice breaking measures are not needed, the aircraft can not be stalled due to surface icing, and the safety factor of the aircraft is increased. And meanwhile, the flying speed is also improved.

Fourthly, explanation of the attached drawings:

FIG. 1 is a schematic diagram of an external surface heat removal device for a spacecraft.

(1) The outer skin is of a stainless steel or aluminum alloy structure, phi 3 mm micropores are formed in the skin, the lower skin of the fuselage is not provided with micropores, the upper part of the fuselage and each windward side are provided with micropores, and the sum of the areas of the micropores is 3-4 times larger than that of an air inlet of the engine and is used for air intake. (2) The device comprises a plurality of straight cylinders and a stainless steel structure, wherein the diameters of the straight cylinders are different, and the difference between the diameters of the straight cylinders is 10-20 mm. (3) And the negative pressure cavity is used for air flow. (4) Cone tube, one piece, heat resistant stainless steel construction. (5) The aerospace engine, one, the type of engine, the ordinary turbojet engine, the liquid hydrogen liquid oxygen engine or the air energy engine are most ideal. Such air-powered engines are under examination. (6) A nacelle. (7) Nacelle skin, one piece, stainless steel or aluminum alloy construction.

The fifth embodiment is as follows:

after the engine <5> is started, high-pressure high-speed gas is sprayed out to enter the cone pipe <4> during working, the sectional area of the cone pipe is gradually reduced, the pressure intensity of the gas is gradually increased, the flow rate is correspondingly increased, and the flow is unchanged. High-pressure high-speed gas formed after the gas flows out of the conical pipe orifice flows into a plurality of straight cylinders <2> (5-10 mm gaps are reserved between every two straight cylinders) which are staggered and amplified step by step, and a negative pressure vortex is formed at the outlet of the conical pipe and the outlet of every straight cylinder under the action of high-speed airflow. The negative pressure vortex can suck the air in the atmosphere into the negative pressure cavity <3> from the outer skin <1> and then flows into the negative pressure vortex, the negative pressure vortex has the silencing effect, and the air in the atmosphere is swirled into the airflow sprayed out from the opening of the cone body to be mixed when the vortex rotates. The flow rate of the mixed gas is unchanged, but the flow is increased. Accordingly, the horsepower of the engine is increased and the air temperature is decreased, and the noise generated by the engine exhaust during the air mixing process can be greatly reduced. The air in the negative pressure cavity flows (the temperature of flowing air is low) to discharge the heat generated by the friction between the outer skin <1> and the air out of the aircraft body along with the flowing air in time, so that the outer surface of the whole spacecraft does not generate high temperature when in high-speed flight by the friction with the air, the safety of the whole aircraft is protected, the high temperature cannot be generated in the aircraft cabin, and the cold-proof and warm-keeping measures are required to be taken in the aircraft cabin because the temperature in the negative pressure cavity is always lower than the external air temperature. Air in the atmosphere enters the negative pressure cavity from the micropores of the outer skin <1>, and the surfaces of the outer skin on which the micropores are arranged form a negative pressure surface. The negative pressure surface of the windward side can reduce air resistance, and the negative pressure surface of the upper skin of the aircraft body, which is provided with the micropores, can generate lift force, so that the load capacity of the spacecraft is improved. (body lower outer skin is not provided with micropores) is stable due to the operation of the engine. The temperature in the negative pressure cavity <3> is relatively stable, so the negative pressure cavity is not limited by the flying speed, and the outer surface of the aircraft body can not generate high temperature during ultrahigh-speed flying, thereby ensuring the safety of the spacecraft and astronauts.

Claims

1. A spacecraft external surface heat removal device, characterized in that: the air purifier comprises an engine room (6) and an engine (5) arranged in the engine room (6), wherein a cone pipe (4) is arranged at the outlet of the engine (5), the sectional area of the cone pipe (4) is gradually reduced, a plurality of straight cylinders (2) with diameters being gradually enlarged are arranged behind the cone pipe (4), the straight cylinders (2) are staggered with each other and have gaps with each other, air sprayed out when the engine (5) works enters the cone pipe (4), the air enters the straight cylinders (2) after being accelerated by the cone pipe (4), a negative pressure vortex is formed at the outlet of each straight cylinder (2) and the inner wall of the next straight cylinder (2) under the action of high-speed airflow, and air in the atmosphere can be sucked from micropores of an outer skin (1) by suction force generated by the negative pressure vortex and is mixed with the airflow sprayed by the engine (5), thereby realizing the purpose of temperature reduction.

2. A spacecraft external surface heat removal device according to claim 1, wherein: the heat removal device on the outer surface of the spacecraft can be applied to space shuttles, aviation shuttles, rockets and missiles.