CN117163307A - Static charge releasing device of near space vehicle - Google Patents
Static charge releasing device of near space vehicle Download PDFInfo
- Publication number
- CN117163307A CN117163307A CN202311309334.2A CN202311309334A CN117163307A CN 117163307 A CN117163307 A CN 117163307A CN 202311309334 A CN202311309334 A CN 202311309334A CN 117163307 A CN117163307 A CN 117163307A
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- discharge
- near space
- space vehicle
- electrostatic charge
- release cover
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- 230000003068 static effect Effects 0.000 title claims abstract description 26
- 238000007599 discharging Methods 0.000 claims abstract description 26
- 230000005684 electric field Effects 0.000 claims description 14
- 238000012806 monitoring device Methods 0.000 claims description 13
- 238000012544 monitoring process Methods 0.000 claims description 7
- 239000000463 material Substances 0.000 claims description 4
- 238000001514 detection method Methods 0.000 claims description 3
- 239000003989 dielectric material Substances 0.000 claims description 3
- 230000005611 electricity Effects 0.000 abstract description 7
- 239000003570 air Substances 0.000 description 19
- 208000032826 Ring chromosome 3 syndrome Diseases 0.000 description 10
- 238000005516 engineering process Methods 0.000 description 7
- 230000001105 regulatory effect Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- 229920000742 Cotton Polymers 0.000 description 1
- 239000012080 ambient air Substances 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000007786 electrostatic charging Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000005433 ionosphere Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 229910052724 xenon Inorganic materials 0.000 description 1
- FHNFHKCVQCLJFQ-UHFFFAOYSA-N xenon atom Chemical compound [Xe] FHNFHKCVQCLJFQ-UHFFFAOYSA-N 0.000 description 1
Abstract
The invention discloses an electrostatic charge releasing device of a near space aircraft, which relates to the technical field of static electricity, and comprises a discharging brush and a releasing cover; the discharge brush is fixed on the aircraft; the caliber of the first end of the release cover is smaller than that of the second end of the release cover; the first end of the release cover is fixed at the tail part of the discharge brush; the first end of the release cover is provided with a plurality of air inlets. The invention can meet the electrostatic charge release requirement of the near space vehicle.
Description
Technical Field
The invention relates to the technical field of static electricity, in particular to a static charge releasing device of a near space vehicle.
Background
In recent years, with the development of aerospace technology, development of near space is increasingly emphasized, and the near space is not only a flight corridor of an ultra-high speed aircraft, but also a place where the aircraft must travel to and from space. When the near space aircraft flies at a high speed, the unavoidable collision friction with surrounding substances causes static electricity, and the jet effect of engine tail gas also causes static electricity to be charged on the aircraft. Under the comprehensive action of a plurality of electrostatic charging modes, electrostatic discharge (ESD) can be generated when the electrostatic magnitude of the supersonic aircraft reaches a certain degree, and the discharge energy generates a complex electrostatic effect on airborne equipment through a conduction and radiation coupling mode, so that the flight safety of the supersonic aircraft is affected.
One key technology for the electrostatic safety problem of the high-speed aircraft is an electrostatic charge control technology (here, the electrostatic charge is controlled to control the electrostatic charge on the aircraft so as to ensure the electrostatic safety of the aircraft), and the electrostatic charge control technology mainly comprises a passive mode and an active mode. The static charge control of the aircraft and the rocket mainly adopts a passive static discharger, and is mainly divided into a cotton yarn core discharger, a metal wire discharger, a decoupling discharger and the like, when the accumulated charges of the aircraft exceed the discharge threshold of the discharger, corona discharge can occur to realize the charge release of a charged body, the discharge threshold of the corona discharge varies along with the change of the surrounding atmospheric environment, and the static charge release cannot be actively carried out. The flying space of the near space aircraft covers an atmosphere layer, an ionosphere and the near space, the ambient air pressure is large when the atmosphere flies, the existing passive discharger can play a role of releasing static electricity, but the discharging threshold value of the existing passive discharger is sharply increased according to the Paschen law of gas discharging under low air pressure or vacuum environment such as the near space, and the static electricity releasing efficiency is greatly reduced due to the fact that the air is thin. The active static charge control technology adopts a particle emission device, and the static electric potential of the aircraft is kept at a safe level by controlling the ejection of charged particles to reduce the structure and the surface electric potential of the aircraft through instructions. The existing static active control technology such as a hollow cathode type plasma emission device used on a satellite needs to carry xenon as ionized gas, so that the device has a complex structure and increased weight, and is not suitable for the lightweight requirement of airborne equipment of an adjacent space vehicle. The existing static charge control technology is mainly applied to airplanes and satellites, a special static discharger is not used for the current near-space ultra-high-speed aircraft, so that static hazard of the near-space aircraft is uncontrollable, the existing discharger cannot be directly applied to static charge discharge of the near-space aircraft, and a special static charge releaser needs to be studied.
Disclosure of Invention
The invention aims to provide a static charge discharging device of a near-space aircraft, which meets the static charge discharging requirement of the near-space aircraft.
In order to achieve the above object, the present invention provides the following solutions:
a near space vehicle electrostatic charge discharge device comprising: a discharge brush and a release cover;
the discharge brush is fixed on the aircraft; the caliber of the first end of the release cover is smaller than that of the second end of the release cover; the first end of the release cover is fixed at the tail part of the discharge brush; the first end of the release cover is provided with a plurality of air inlets.
Optionally, the release cover is a horn cover.
Optionally, the spacecraft electrostatic charge discharge device further comprises an electrode ring; the electrode ring is sleeved outside the second end of the release cover.
Optionally, the electrode ring is made of a metal film.
Optionally, the near space vehicle electrostatic charge discharging device further comprises a power supply; the power supply is connected with the electrode ring; the power supply is used for supplying power to the electrode ring to generate local field intensity.
Optionally, the near space vehicle electrostatic charge discharging device further comprises a control module; the control module is connected with the power supply.
Optionally, the electrostatic charge discharging device of the near space vehicle further comprises a current monitoring device connected with the control module; the current monitoring device is arranged on the discharge brush.
Optionally, the electrostatic charge releasing device of the near space vehicle further comprises an electric field monitoring device connected with the control module; the electric field detection device is used for monitoring the generated electric field of the discharge brush.
Optionally, the material of the release cover is a dielectric material.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects:
the discharge brush is fixed on an aircraft; the caliber of the first end of the release cover is smaller than that of the second end of the release cover; the first end of the release cover is fixed at the tail part of the discharge brush; the first end of the release cover is provided with a plurality of air inlets. The discharge brush is provided with the discharge cover with the air inlet, and the local air pressure near the discharge brush is controlled through the discharge cover, so that the electrostatic discharge of the electrostatic discharge device of the near-space aircraft can be completed in a low-air-pressure environment, and the electrostatic discharge requirement of the near-space aircraft is met.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a passive mode release prototype of surface charge on a spacecraft;
fig. 2 is a schematic diagram of the active mode surface charge discharge of the electrostatic charge discharge device for a spacecraft according to the present invention.
Symbol description:
discharging brush-1, releasing cover-2, electrode ring-3, power supply-4 and control module-5.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention aims to provide a static charge discharging device of a near-space aircraft, which meets the static charge discharging requirement of the near-space aircraft.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
The developed electrostatic discharge device for the near space vehicle comprises a passive mode and an active mode. The active mode controls the discharge of the discharge brush 1 by loading the same-direction voltage, so that the electrostatic discharge device of the near space vehicle meets the index requirement.
Because the air pressure in the near space environment is low, the common aircraft discharging brush 1 cannot meet the requirement of electrostatic discharge of the aircraft. The electrostatic discharge device on the near space vehicle can generate electrostatic discharge by a local air pressure control method (here, the electrostatic discharge device on the near space vehicle can release electrostatic charges on the vehicle), so that the air pressure range of the discharge area of the electrostatic discharge device is changed, the air pressure of the discharge area is regulated to a pressure value which is most favorable for discharge by structural design, and the electrostatic discharge of the near space vehicle is completed. The principle of the passive discharge model machine of the surface charge of the near space aircraft is shown in fig. 1, the discharge brush 1 is wrapped by a horn-shaped structure, an air inlet hole is formed in the structure, and through the design of the air inlet hole (including the position of the opening and the number of the opening), a flow field vortex is generated in a discharge area, so that the purpose of adjusting the air pressure range of the discharge area is achieved, the discharge brush 1 forms corona discharge, and the electrostatic charge of the aircraft is discharged.
Based on the discharging of the passive electrostatic discharge device, the invention designs a near-space aircraft surface charge active mode discharging prototype, as shown in fig. 2, and provides a near-space aircraft electrostatic discharge device, which provides technical support for the near-space aircraft electrostatic safety design and application, and comprises the following steps: a discharge brush 1 and a release cover 2; the discharge brush 1 is fixed on an aircraft; the discharging brush 1 mainly completes the electrostatic discharge function; the first end caliber of the release cover 2 is smaller than the second end caliber of the release cover 2; the first end of the release cover 2 is fixed at the tail part of the discharge brush 1; a plurality of air inlet holes are arranged on the first end of the release cover 2.
The release cover 2 is a horn cover. The material of the release cover 2 is a dielectric material. The horn cover is fixed at the tail end of the discharge brush 1, and the horn cover is provided with holes for ensuring the air flow to pass through, so that the local air pressure of a discharge area is increased, the electrostatic discharge of the aircraft can be ensured under the low air pressure environment in the near space, and the electrostatic discharge of the aircraft is further completed.
The electrostatic charge discharging device of the near space vehicle further comprises an electrode ring 3; the electrode ring 3 is sleeved outside the second end of the release cover 2. The electrode ring 3 is made of a metal film. The near space vehicle electrostatic charge discharging device also comprises a power supply 4; the power supply 4 is connected with the electrode ring 3; the power supply 4 is used for energizing the electrode ring 3 to generate a local field strength, and the power supply 4 is also connected with the discharge brush 1 to form a circuit. The power supply 4 provided by the invention is a high voltage source. The electrode ring 3 is loaded with high voltage through a high voltage source to control the local field intensity of a discharge local area, so that the discharge brush 1 is promoted to generate electrostatic discharge; a high voltage source is connected to the electrode ring 3, and has a polarity which is selectable between positive and negative, for applying a high voltage to the electrode ring 3, thereby generating a local field strength.
The electrostatic charge discharging device of the near space vehicle further comprises a control module 5; the control module 5 is connected to the power supply 4. The electrostatic charge releasing device of the near space vehicle further comprises a current monitoring device connected with the control module 5; the current monitoring device is arranged on the discharge brush 1. The electrostatic charge releasing device of the near space vehicle further comprises an electric field monitoring device connected with the control module 5; the electric field detection means is for monitoring the generated electric field of the discharge brush 1.
The control module 5 is connected with the high-voltage source and respectively adjusts the positive and negative polarities and the voltage output of the high-voltage source through the electric field monitoring data and the current monitoring data; the electric field monitoring device is arranged near the discharge brush 1 and connected with the control module 5 and is used for monitoring the polarity of static electricity charged on the surface of the aircraft, so that the polarity of the high-voltage source is regulated to be consistent with the polarity of the surface of the aircraft through the control module 5; the current monitoring device is arranged on the discharge brush 1 and is connected with the control module 5, and the discharge current is monitored, so that the output size of the high-voltage source is regulated through the control module 5 to control the loading electric field size of the discharge area, the discharge current is controlled within a certain range, and the discharge of the electrostatic charge of the aircraft can be completed without large radio frequency interference.
The invention adopts the perforated horn cover to control the local air pressure of the accessory of the discharge brush 1, thereby enabling the electrostatic discharge device of the invention to finish electrostatic discharge in a low air pressure environment; the discharge of the discharge brush 1 is regulated by loading a high-voltage electrode, and the high-voltage electrode generates an electric field in a discharge area to promote the discharge of the discharge brush 1; the high voltage source and the electrode ring 3 are adopted to increase the local field intensity of the discharge area, so that the electrostatic charge release of the electrostatic discharge device of the aircraft can be actively controlled. The polarity of the discharge brush 1 is monitored through the electric field monitoring device, and the polarity of the loading power supply is adjusted by the control module 5 according to the monitoring result, so that the polarity of the loading voltage can be automatically adjusted by the high-voltage source according to the polarity of the electric power supplied by the aircraft; the discharge current is monitored by the current monitoring device, and the discharge power supply voltage is regulated by the control module 5 to control the discharge current, so that the high-voltage source can be ensured to regulate the output voltage to increase and decrease the discharge current according to the discharge current, and the discharge current of the electrostatic discharge device is kept within a certain range.
In the present specification, each embodiment is described in a progressive manner, and each embodiment is mainly described in a different point from other embodiments, and identical and similar parts between the embodiments are all enough to refer to each other. The principles and embodiments of the present invention have been described herein with reference to specific examples, the above examples being provided only to assist in understanding the device and its core ideas of the present invention; also, it is within the scope of the present invention to be modified by those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.
Claims (9)
1. An apparatus for electrostatic discharge of a spacecraft, comprising: a discharge brush and a release cover;
the discharge brush is fixed on the aircraft; the caliber of the first end of the release cover is smaller than that of the second end of the release cover; the first end of the release cover is fixed at the tail part of the discharge brush; the first end of the release cover is provided with a plurality of air inlets.
2. The near space vehicle electrostatic charge discharging device of claim 1, wherein said discharging hood is a horn hood.
3. The near space vehicle electrostatic charge discharging device of claim 1, further comprising an electrode ring; the electrode ring is sleeved outside the second end of the release cover.
4. A spacecraft electrostatic charge discharge device according to claim 3, wherein the material of the electrode ring is a metallic film.
5. The near space vehicle electrostatic charge discharging device of claim 3, further comprising a power source; the power supply is connected with the electrode ring; the power supply is used for supplying power to the electrode ring to generate local field intensity.
6. The near space vehicle electrostatic charge discharging device of claim 5, further comprising a control module; the control module is connected with the power supply.
7. The near space vehicle electrostatic charge discharging device of claim 6, further comprising a current monitoring device coupled to said control module; the current monitoring device is arranged on the discharge brush.
8. The near space vehicle electrostatic charge discharging device of claim 6, further comprising an electric field monitoring device coupled to said control module; the electric field detection device is used for monitoring the generated electric field of the discharge brush.
9. The near space vehicle static charge discharging device of claim 1, wherein said discharge cap material is a dielectric material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311309334.2A CN117163307A (en) | 2023-10-11 | 2023-10-11 | Static charge releasing device of near space vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311309334.2A CN117163307A (en) | 2023-10-11 | 2023-10-11 | Static charge releasing device of near space vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117163307A true CN117163307A (en) | 2023-12-05 |
Family
ID=88945082
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311309334.2A Pending CN117163307A (en) | 2023-10-11 | 2023-10-11 | Static charge releasing device of near space vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117163307A (en) |
-
2023
- 2023-10-11 CN CN202311309334.2A patent/CN117163307A/en active Pending
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