阅读说明：本技术 一种飞行器高温防护设备 (High-temperature protection equipment for aircraft ) 是由 王春生 李宽 尚东星 于 2019-09-23 设计创作，主要内容包括：本发明公开了一种飞行器高温防护设备,属于热防护技术领域,包括容纳腔、转轴和转盖,容纳腔为中空的圆柱形,容纳腔底部封闭,顶部为半圆形容纳腔盖体半封闭,容纳腔盖体上开有倾斜的粒子出孔,转轴为中空的圆柱形,转轴中心安装有磁芯,转轴设置在容纳腔的中心位置,转轴外部为可绕转轴旋转的转盖,转盖包括转盖空心轴和半圆形转盖本体,转盖空心轴底部为带动整个转盖旋转的转动电机,转盖空心轴上端为半圆形转盖本体,容纳腔对应开口端的外侧贴有外磁体,容纳腔对应容纳腔盖体的底部安装有正极板,容纳腔盖体外侧安装有负极板。本发明结构简单,可实现飞行器返航过程中对关键待防护器件防护,避免待防护器件因高温而毁坏。(The invention discloses high-temperature protection equipment for an aircraft, which belongs to the technical field of thermal protection and comprises a containing cavity, a rotating shaft and a rotating cover, wherein the containing cavity is hollow and cylindrical, the bottom of the containing cavity is closed, the top of the containing cavity is semi-closed, a semi-circular containing cavity cover body is arranged on the cover body of the containing cavity, an inclined particle outlet hole is formed in the cover body of the containing cavity, the rotating shaft is hollow and cylindrical, a magnetic core is arranged at the center of the rotating shaft, the rotating shaft is arranged at the center of the containing cavity, the rotating cover capable of rotating around the rotating shaft is arranged outside the rotating shaft, the rotating cover comprises a rotating cover hollow shaft and a semi-circular rotating cover body, a rotating motor for driving the whole rotating cover to rotate is arranged at the bottom of the rotating cover hollow shaft, the upper end of the rotating cover hollow shaft is a semi-circular rotating cover. The device has a simple structure, can protect the key device to be protected in the process of returning the aircraft, and avoids the device to be protected from being damaged due to high temperature.)

1. An aircraft high temperature protection device characterized in that: comprises a containing cavity (1), a rotating shaft (4) and a rotating cover (2), wherein the containing cavity (1) is hollow and cylindrical, the bottom of the containing cavity (1) is closed, the top of the containing cavity is semi-closed, a semi-circular containing cavity cover body is semi-closed, an inclined particle outlet hole (1-1) is formed in the containing cavity cover body, the rotating shaft (4) is hollow and cylindrical, a magnetic core (3) is installed in the center of the rotating shaft (4), the rotating shaft (4) is arranged at the central position of the containing cavity (1), the rotating cover (2) which can rotate around the rotating shaft (4) is arranged outside the rotating shaft (4), the rotating cover (2) comprises a rotating cover hollow shaft (2-1) and a semi-circular rotating cover body (2-2), the rotating shaft (4) is arranged in the rotating cover hollow shaft (2-1), a rotating motor (8) which drives the whole rotating cover (2) to rotate is arranged at the bottom of the rotating cover hollow shaft (2-1), the semi-, outer magnet (5) are pasted in the outside that holds chamber (1) and correspond the open end, hold chamber (1) and correspond the bottom that holds the chamber lid and install positive plate (7), hold the chamber lid outside and install negative plate (6), are equipped with the negative plate through-hole corresponding to particle outlet hole (1-1) position on negative plate (6), rotate motor (8), positive plate (7) and negative plate (6) and all connect aircraft control system.

2. an aircraft high temperature protection device according to claim 1, characterized in that: the magnetic core (3) and the outer magnet (5) are both made of permanent magnets, the magnetic core (3) is cylindrical, and the outer magnet (5) is of an arc-shaped structure.

3. An aircraft high temperature protection device according to claim 1, characterized in that: the included angle between the particle outlet (1-1) and the vertical direction is 5-10 degrees.

4. An aircraft high temperature protection device according to claim 1, characterized in that: the particle outlet (1-1) is inclined towards the outside of the accommodating cavity (1).

5. An aircraft high temperature protection device according to claim 1, characterized in that: the semicircular rotary cover body (2-2) is arranged in the accommodating cavity (1) and is positioned on the inner side of the cover body of the accommodating cavity.

Technical Field

The invention relates to high-temperature protection equipment for an aircraft, and belongs to the technical field of thermal protection.

Background

the aerospace craft completes the task, and in the process of returning to the ground, the aerospace craft passes through the atmosphere at a high speed, the surface of the aerospace craft rubs the atmosphere to generate high temperature, the high temperature on the surface of the aerospace craft can influence the work of sensitive devices to be protected such as an antenna and a detector arranged on the outer side of the aerospace craft, and even can destroy the sensitive devices to be protected, once the sensitive devices to be protected are destroyed, the communication black-out phenomenon in the process of returning the aerospace craft can occur, and even the accident of the aerospace craft can be caused.

disclosure of Invention

The invention aims to provide high-temperature protection equipment for an aircraft, which has a simple structure, can protect key devices to be protected in the process of returning the aircraft, and avoids the devices to be protected from being damaged due to high temperature.

In order to solve the technical problems, the technical scheme adopted by the invention is as follows:

an aircraft high-temperature protection device comprises a containing cavity, a rotating shaft and a rotating cover, wherein the containing cavity is hollow and cylindrical, the bottom of the containing cavity is closed, the top of the containing cavity is semi-circular, a cover body of the containing cavity is semi-closed, an inclined particle outlet hole is formed in the cover body of the containing cavity, the rotating shaft is hollow and cylindrical, a magnetic core is installed at the center of the rotating shaft, the rotating shaft is arranged at the central position of the containing cavity, the rotating cover capable of rotating around the rotating shaft is arranged outside the rotating shaft, the rotating cover comprises a rotating cover hollow shaft and a semi-circular rotating cover body, the rotating shaft is arranged in the rotating cover hollow shaft, a rotating motor for driving the whole rotating cover to rotate is arranged at the bottom of the rotating cover hollow shaft, the upper end of the rotating cover hollow shaft is a semi-circular rotating cover body, an outer magnet is pasted at the outer side of the containing cavity corresponding to, the rotating motor, the positive plate and the negative plate are all connected with an aircraft control system.

The technical scheme of the invention is further improved as follows: the magnetic core and the outer magnet are both made of permanent magnets, the magnetic core is cylindrical, and the outer magnet is of an arc-shaped structure.

The technical scheme of the invention is further improved as follows: the particle outlet hole has an included angle of 5-10 degrees with the vertical direction.

the technical scheme of the invention is further improved as follows: the particle outlet hole is inclined towards the outer side of the accommodating cavity.

The technical scheme of the invention is further improved as follows: the semicircular rotary cover body is arranged in the accommodating cavity and is positioned on the inner side of the cover body of the accommodating cavity.

Due to the adoption of the technical scheme, the invention has the technical progress that:

The high-temperature protection equipment for the aircraft, disclosed by the invention, has a simple structure, can protect key devices to be protected in the process of returning the aircraft, and avoids the devices to be protected from being damaged due to high temperature.

In the process that the aircraft returns to the ground from the outer space, after the aircraft enters an ionized layer, the aircraft control system controls the rotating motor to work, the rotating motor drives the rotating cover to rotate, so that the accommodating cavity is opened, external plasma can enter the accommodating cavity at the moment, the magnetic core and the outer magnet can form a closed magnetic field at the opening of the accommodating cavity, the closed magnetic field can block electrons from entering the accommodating cavity, the ion particles are less influenced by the magnetic field due to large mass and move, the ion particles can enter the accommodating cavity, and the aircraft accumulates the ion particles in the accommodating cavity in the process of running in the ionized layer; after aircraft entered into the atmosphere, aircraft control system control rotated motor work, it rotates to rotate the motor and drive the commentaries on classics lid and rotate, the closed chamber that holds, loading voltage between aircraft control system control positive plate and the negative plate, form the electric field, the positive ion that holds the intracavity receives the electric field effect can accelerated motion to through particle outlet blowout, form high particle flow, particle collision between the particle flow blows away, and then hits the air molecule of treating the protective device surface, thereby play the effect that the protective device was treated in the protection.

Drawings

FIG. 1 is a cross-sectional view of the present invention;

FIG. 2 is a top view of the present invention;

FIG. 3 is a top plan view of the swivel cap of the present invention;

FIG. 4 is a cross-sectional view of the flip cover of the present invention;

FIG. 5 is a schematic diagram of the invention in operation to collect ion particles;

FIG. 6 is a schematic diagram of the emitted ion particles in operation of the present invention;

The device comprises a containing cavity 1, an accommodating cavity 2, a rotating cover 3, a magnetic core 4, a rotating shaft 5, an outer magnet 6, a negative plate 7, a positive plate 8, a rotating motor 9, an aircraft surface 10, a device to be protected 1-1, a particle outlet 2-1, a rotating cover hollow shaft 2-2 and a semicircular rotating cover body.

Detailed Description

The present invention will be described in further detail with reference to the following examples:

As shown in fig. 1-4, an aircraft high temperature protection device comprises a containing cavity 1, a rotating shaft 4 and a rotating cover 2, wherein the containing cavity 1 is hollow and cylindrical, the bottom of the containing cavity 1 is closed, the top of the containing cavity is semi-closed, the containing cavity is provided with an inclined particle outlet 1-1, the included angle between the particle outlet 1-1 and the vertical direction is 5-10 degrees, the inclined direction of the particle outlet 1-1 faces the outside of the containing cavity 1, the rotating shaft 4 is hollow and cylindrical, a magnetic core 3 is arranged at the center of the rotating shaft 4, the magnetic core 3 is cylindrical, the rotating shaft 4 is arranged at the center of the containing cavity 1, the rotating cover 2 capable of rotating around the rotating shaft 4 is arranged outside the rotating shaft 4, the rotating cover 2 comprises a rotating cover hollow shaft 2-1 and a semi-circular rotating cover body 2-2, the rotating shaft 4 is arranged in the rotating cover hollow shaft 2-1, the bottom of the rotating cover hollow shaft 2-1 is provided with a rotating, the upper end of the rotary cover hollow shaft 2-1 is a semicircular rotary cover body 2-2, the semicircular rotary cover body 2-2 is arranged in the accommodating cavity 1 and is positioned at the inner side of the accommodating cavity cover body, an outer magnet 5 is attached to the outer side of the accommodating cavity 1 corresponding to the opening end, the outer magnet 5 is of an arc-shaped structure, the bottom of the accommodating cavity 1 corresponding to the accommodating cavity cover body is provided with a positive plate 7, the outer side of the accommodating cavity cover body is provided with a negative plate 6, a negative plate through hole is formed in the negative plate 6 corresponding to a particle outlet 1-1, the rotary motor 8, the positive plate 7 and the negative plate 6 are connected with an aircraft control system, and the magnetic core 3 and the.

When the high-temperature protection device for the aircraft works, as shown in fig. 5 and 6, the high-temperature protection device can be embedded into the aircraft, the semi-closed end of the accommodating cavity is close to a device to be protected, and the semi-open end of the semi-circular rotary cover body 2-2 of the rotary cover 2 is closed. In the process that the aircraft returns to the ground from the outer space, the ionized layer is firstly contacted with the air layer and is a plasma layer formed by cosmic rays and ultraviolet rays, and then the aircraft enters the air layer.

After the aircraft enters the ionized layer, the aircraft control system controls the rotating motor 8 to work, the rotating motor 8 drives the rotating cover 2 to rotate, so that the accommodating cavity 1 is opened, and the state is shown in fig. 5. At the moment, external plasma enters the accommodating cavity 1, a closed magnetic field is formed at the opening of the accommodating cavity by the magnetic core 3 and the outer magnet 5, electrons can be prevented from entering the accommodating cavity 1 by the closed magnetic field, the motion of ion particles is slightly influenced by the magnetic field due to large mass, the ion particles can enter the accommodating cavity 1, and the ion particles are accumulated inside the accommodating cavity when the aircraft runs in an ionosphere; after the aircraft entered into the atmosphere, aircraft control system control rotates motor 8 work, it rotates to rotate motor 8 and drive and change lid 2 and rotate, the closed chamber 1 that holds, its state is as shown in fig. 6, loading voltage between aircraft control system control positive plate 7 and the negative plate 6, form the electric field, it receives the electric field effect can accelerated motion to hold the positive ion in the chamber 1, and spout through particle export 1-1, form high particle flow, particle collision between the particle flow blows off, and then hits the air molecule on treating the protective device surface, thereby play the protection and treat the effect of protective device.