Electrostatic charge release device for near space vehicles

Abstract

The application discloses a near-space vehicle electrostatic charge releasing device, and relates to the technical field of electrostatics. The device comprises a discharge brush and a releasing cover. The discharge brush is fixed on a vehicle. The first end port diameter of the releasing cover is smaller than the second end port diameter of the releasing cover. The first end of the releasing cover is fixed on the tail of the discharge brush. Multiple air inlet holes are arranged on the first end of the releasing cover. The application can meet the electrostatic charge releasing requirement of the near-space vehicle.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of electrostatic technology, in particular to a near space vehicle electrostatic charge release device. BACKGROUND

[0002] In recent years, with the development of aerospace technology, the development of near space has been paid more and more attention. The near space is not only the flight corridor of the supersonic vehicle, but also the necessary place for the spacecraft to go to the space. When the near space vehicle flies at high speed, it is inevitable to collide and rub with the surrounding matter and bring static electricity. The engine exhaust jet effect also makes the vehicle bring static electricity. Under the comprehensive action of various static charging methods, when the static electricity level of the supersonic vehicle reaches a certain degree, electrostatic discharge (ESD) will occur. The discharge energy will produce complex electrostatic effects on the on-board equipment through conduction and radiation coupling, thereby affecting the flight safety of the supersonic vehicle.

[0003] A key technology for the electrostatic safety problem of the high-speed vehicle is the electrostatic charge control technology (here, referring to controlling the static electricity on the vehicle by controlling the electrostatic charge to ensure the electrostatic safety of the vehicle). There are mainly passive and active two ways. The electrostatic charge control of the aircraft and the rocket mainly adopts passive electrostatic discharge device, which is mainly divided into cotton yarn core discharge device, metal wire discharge device, decoupling discharge device, etc. When the accumulated charge of the vehicle exceeds the discharge threshold of the discharge device, corona discharge will occur to realize the charge release of the charged body. The discharge threshold changes with the change of the surrounding atmospheric environment, and the electrostatic charge cannot be released actively. The flight space of the near space vehicle covers the atmosphere, the ionosphere and the near space. When flying in the atmosphere, the surrounding environment pressure is large, and the existing passive discharge device can play a role in electrostatic release, but in the near space and other low pressure or vacuum environment, according to the Paschen law of gas discharge, due to the thin air, the discharge threshold of the existing passive discharge device increases sharply, resulting in a great reduction in the electrostatic charge release efficiency. The active electrostatic charge control technology adopts particle emission device to reduce the potential of the vehicle structure and surface by controlling the injection of charged particles by command, and keeps the electrostatic potential of the vehicle at a safe level. The existing satellite uses the hollow cathode type plasma emission device and other electrostatic active control technology, which needs to carry xenon as ionizing gas, resulting in complex device structure and weight increase, which is not suitable for the lightweight requirement of the on-board equipment of the near space vehicle. The existing electrostatic charge control technology is mainly applied to the aircraft and the satellite. At present, there is no special electrostatic discharge device for the near space supersonic vehicle, which leads to the uncontrollable electrostatic hazard of the near space vehicle, and the existing discharge device cannot be directly applied to the electrostatic charge release of the near space vehicle, so a special electrostatic charge release device needs to be researched. SUMMARY

[0004] The purpose of this invention is to provide a near-space vehicle electrostatic discharge device to meet the electrostatic discharge requirements of near-space vehicles.

[0005] To achieve the above objectives, the present invention provides the following solution:

[0006] A near-space vehicle electrostatic discharge device includes: a discharge brush and a discharge cover;

[0007] The discharge brush is fixed to the aircraft; the first port diameter of the release cover is smaller than the second port diameter of the release cover; the first end of the release cover is fixed to the tail of the discharge brush; and multiple air inlets are provided on the first end of the release cover.

[0008] Optionally, the release cover is a horn cover.

[0009] Optionally, the near-space vehicle electrostatic discharge device further includes an electrode ring; the electrode ring is fitted over the outside of the second end of the discharge cover.

[0010] Optionally, the electrode ring is made of a thin metal film.

[0011] Optionally, the near-space vehicle electrostatic discharge device further includes a power source; the power source is connected to the electrode ring; the power source is used to power the electrode ring to generate a local electric field.

[0012] Optionally, the near-space vehicle electrostatic discharge device further includes a control module; the control module is connected to the power supply.

[0013] Optionally, the near-space vehicle electrostatic discharge device further includes a current monitoring device connected to the control module; the current monitoring device is disposed on the discharge brush.

[0014] Optionally, the near-space vehicle electrostatic discharge device further includes an electric field monitoring device connected to the control module; the electric field monitoring device is used to monitor the electric field generated by the discharge brush.

[0015] Optionally, the material of the release cover is a medium material.

[0016] According to specific embodiments provided by the present invention, the present invention discloses the following technical effects:

[0017] The discharge brush is fixed on the aircraft; the first end of the release cover has a smaller diameter than the second end of the release cover; the first end of the release cover is fixed to the tail of the discharge brush; and a plurality of air inlet holes are arranged on the first end of the release cover. The release cover with air inlet holes is arranged on the discharge brush, the local air pressure near the discharge brush is controlled through the release cover, the electrostatic charge release device of the near space aircraft can complete electrostatic discharge in a low pressure environment, and thus the electrostatic charge release requirement of the near space aircraft is met. BRIEF DESCRIPTION OF DRAWINGS

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings needed in the embodiments will be briefly introduced as follows. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative effort.

[0019] Figure 1 The principle diagram of the surface charge passive mode release device of the near space aircraft;

[0020] Figure 2 The principle diagram of the surface charge active mode release device of the near space aircraft electrostatic charge release device is provided.

[0021] Symbol explanation:

[0022] Discharge brush-1, release cover-2, electrode ring-3, power supply-4, control module-5. DETAILED DESCRIPTION

[0023] The technical solutions in the embodiments of the present application will be described clearly and completely in the following with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some embodiments of the present application, not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present application.

[0024] The purpose of the present application is to provide a near space aircraft electrostatic charge release device to meet the electrostatic charge release requirement of the near space aircraft.

[0025] In order to make the above-mentioned purposes, features and advantages of the present application more obvious and easy to understand, the present application will be further described in detail with reference to the drawings and specific embodiments.

[0026] The developed near space aircraft electrostatic release device includes passive mode and active mode. The active mode controls the discharge of the discharge brush 1 by loading the same direction voltage, so that the near space aircraft electrostatic release device meets the index requirement.

[0027] Due to the low air pressure in near-space, ordinary aircraft discharge brushes cannot meet the requirements for electrostatic discharge. A method of local air pressure control (meaning enabling electrostatic discharge on the near-space aircraft to discharge static charge) is used to change the air pressure range of the discharge area. Through structural design, the air pressure in the discharge area is adjusted to the most favorable pressure value for discharge, thus completing the release of static charge from the near-space aircraft. The principle of the passive surface charge release prototype for near-space aircraft is as follows: Figure 1 As shown, the discharge brush 1 is wrapped with a trumpet-shaped structure with an air inlet. The design of the air inlet (including the position and number of openings) generates a flow field vortex in the discharge area, thereby adjusting the air pressure range of the discharge area and causing the discharge brush 1 to form a corona discharge, thereby releasing the static charge of the aircraft.

[0028] Based on the discharge mechanism of a passive electrostatic discharge device, a prototype for active-mode discharge of surface charge on a near-space spacecraft is designed, such as... Figure 2 As shown, the present invention provides an electrostatic discharge device for near-space vehicles, providing technical support for the electrostatic safety design and application of near-space vehicles, comprising: a discharge brush 1 and a discharge cover 2; the discharge brush 1 is fixed on the vehicle; the discharge brush 1 mainly performs the function of electrostatic discharge; the first port diameter of the discharge cover 2 is smaller than the second port diameter of the discharge cover 2; the first end of the discharge cover 2 is fixed to the tail of the discharge brush 1; and multiple air inlets are provided on the first end of the discharge cover 2.

[0029] The release cover 2 is a horn cover. The material of the release cover 2 is a dielectric material. The horn cover is fixed to the tail end of the discharge brush 1. The opening of the horn cover allows airflow to pass through, thereby increasing the local air pressure in the discharge area and ensuring that the aircraft can perform electrostatic discharge in the low-pressure environment of near space, thus completing the release of the static charge of the aircraft.

[0030] The near-space vehicle electrostatic discharge device also includes an electrode ring 3; the electrode ring 3 is sleeved on the outside of the second end of the discharge cover 2. The electrode ring 3 is made of a thin metal film. The near-space vehicle electrostatic discharge device also includes a power supply 4; the power supply 4 is connected to the electrode ring 3; the power supply 4 is used to power the electrode ring 3 to generate a local field strength, and the power supply 4 is also connected to the discharge brush 1 to form a circuit. The power supply 4 provided by the present invention is a high-voltage source. The electrode ring 3 is loaded with high voltage through the high-voltage source to control the local field strength of the discharge area, thereby causing the discharge brush 1 to perform electrostatic discharge; the high-voltage source is connected to the electrode ring 3 and has both positive and negative polarities that can be selected, used to apply high voltage to the electrode ring 3, thereby generating a local field strength.

[0031] The near-space vehicle electrostatic discharge device also includes a control module 5; the control module 5 is connected to the power supply 4. The near-space vehicle electrostatic discharge device also includes a current monitoring device connected to the control module 5; the current monitoring device is mounted on the discharge brush 1. The near-space vehicle electrostatic discharge device also includes an electric field monitoring device connected to the control module 5; the electric field monitoring device is used to monitor the electric field generated by the discharge brush 1.

[0032] Control module 5 is connected to a high-voltage source. It adjusts the positive and negative polarities and voltage output of the high-voltage source based on electric field and current monitoring data. An electric field monitoring device, installed near discharge brush 1 and connected to control module 5, monitors the polarity of the static electricity on the aircraft surface. Control module 5 then adjusts the polarity of the high-voltage source to match the polarity of the aircraft surface. A current monitoring device, installed on discharge brush 1 and connected to control module 5, monitors the discharge current. Control module 5 then adjusts the output of the high-voltage source to control the magnitude of the electric field applied to the discharge area. This ensures the discharge current remains within a certain range, effectively releasing the static charge on the aircraft without generating significant radio frequency interference.

[0033] This invention employs an open-mouth horn cover to control the local air pressure of the discharge brush 1 accessory, enabling the electrostatic discharge device to complete electrostatic discharge in a low-pressure environment. A high-voltage electrode is applied to regulate the discharge of the discharge brush 1; the high-voltage electrode generates an electric field in the discharge area, causing the discharge brush 1 to discharge. A high-voltage source and electrode ring 3 are used to increase the local field strength in the discharge area, thereby actively controlling the release of static charge from the aircraft's electrostatic discharge device. An electric field monitoring device monitors the polarity of the discharge brush 1, and the control module 5 adjusts the polarity of the applied power supply based on the monitoring results, ensuring that the high-voltage source automatically adjusts the polarity of the applied voltage according to the voltage polarity of the aircraft. A current monitoring device monitors the magnitude of the discharge current, and the control module 5 adjusts the discharge power supply voltage to control the discharge current, ensuring that the high-voltage source adjusts the output voltage to increase or decrease the discharge current according to the magnitude of the discharge current, keeping the discharge current of the electrostatic discharge device within a certain range.

[0034] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. Specific examples have been used to illustrate the principles and implementation methods of the invention. The descriptions of the embodiments above are merely for the purpose of helping to understand the device and its core ideas; furthermore, those skilled in the art will recognize that, based on the ideas of this invention, there will be changes in specific implementation methods and application scope. Therefore, the content of this specification should not be construed as limiting the invention.

Claims

1. A near-space vehicle electrostatic charge release device, characterized in that, The application relates to a near-space vehicle electrostatic discharge device, which comprises the following parts: a discharge brush and a release cover; the discharge brush is fixed on an aircraft; the first port diameter of the release cover is smaller than the second port diameter of the release cover; the first end of the release cover is fixed on the tail of the discharge brush; a plurality of air inlet holes are arranged on the first end of the release cover; the near-space vehicle electrostatic discharge device comprises two modes, i.e. a passive mode and an active mode; the active mode controls the discharge of the discharge brush by loading a same-direction voltage, so that the near-space vehicle electrostatic discharge device meets the index requirements; and the release cover is a horn cover. The application further comprises an electrode ring; the electrode ring is sleeved outside the second end of the release cover.

2. The near space vehicle electrostatic charge release device of claim 1, wherein, The material of the electrode ring is a metal film.

3. The near space vehicle electrostatic charge release device of claim 2, wherein, The application further comprises a power supply; the power supply is connected with the electrode ring; and the power supply is used for supplying energy to the electrode ring to generate a local field intensity.

4. The near space vehicle electrostatic charge release device of claim 2, wherein, The application further comprises a control module; the control module is connected with the power supply.

5. The near space vehicle electrostatic charge release device of claim 4, wherein, The application further comprises a current monitoring device connected with the control module; the current monitoring device is arranged on the discharge brush.

6. The near space vehicle electrostatic charge release device of claim 5, wherein, The application further comprises an electric field monitoring device connected with the control module; the electric field monitoring device is used for monitoring the generated electric field of the discharge brush.

7. The near space vehicle electrostatic charge release device of claim 5, wherein, The material of the release cover is a dielectric material.

8. The near space vehicle electrostatic charge release device of claim 1, wherein, ​

Images