CN-224216278-U - System for slowing down plasma sheath

Abstract

The utility model discloses a system for slowing down a plasma sheath, which comprises a pressure sensor arranged at the forefront end of a shock tube, a time delay synchronous machine connected with the pressure sensor through an optical fiber I, and a spraying device connected with the time delay synchronous machine through an optical fiber II, wherein the spraying device comprises a circuit module connected with the time delay synchronous machine, and a water-passing electromagnetic valve module electrically connected with the circuit module so as to switch on-off states of a medium in a liquid storage tank and a reserved small hole on an aircraft model. The utility model provides a system for slowing down a plasma sheath, which has the characteristic of short valve opening time, is suitable for researching the relevant fields of plasma shock waves and the like, and meanwhile, in a plasma shock tunnel experiment, a spraying device can realize liquid spraying and flow control, and has important significance for researching the slowing down or eliminating of the plasma sheath.

Inventors

• ZHU HONGXIAN
• ZHAO HAISHENG
• WU CHUN
• ZHANG CHENGQI
• Ouyang Shuyu
• HUANG YUPENG
• ZHANG XIULU
• XIE SHOUZHI
• ZHANG ZHENMING
• CHEN LIANG
• HUANG YAQI
• MOU JINGYU
• FENG JIE
• Xiao jinshui

Assignees

• 西南科技大学
• 中国电波传播研究所（中国电子科技集团公司第二十二研究所）
• 中国工程物理研究院流体物理研究所

Dates

Publication Date

20260508

Application Date

20250509

Claims (6)

1. 1. A system for mitigating plasma sheath comprising a pressure sensor disposed at a foremost end of a shock tube, further comprising: the delay synchronous machine is connected with the pressure sensor through an optical fiber I; the spraying device is connected with the delay synchronous machine through an optical fiber II; Wherein, sprinkler includes: the circuit module is connected with the delay synchronous machine; And the water-passing electromagnetic valve module is electrically connected with the circuit module to switch the on-off state of a medium in the liquid storage tank and a reserved small hole on the aircraft model.
2. 2. The plasma sheath mitigation system of claim 1, wherein the circuit module is configured to comprise: a thyristor connected with the delay synchronous machine; a switch arranged between the thyristor and the water-passing electromagnetic valve module; A DC power supply for supplying power to the thyristor; the resistor is arranged in parallel with the water-through electromagnetic valve in the water-through electromagnetic valve module; The direct current power supply, the switch, the thyristor and the resistor are integrated on the PVC board.
3. 3. The plasma sheath mitigation system of claim 2, wherein the water-passing electromagnetic valve module is configured to comprise: An air supply pipeline for communicating the liquid storage tank with an external driving air source, and a ball valve I arranged on the air supply pipeline; A water-passing electromagnetic valve for communicating the liquid storage tank with the reserved small hole on the aircraft model through a water-feeding pipeline; wherein a ball valve II is also arranged between the water-through valve and the reserved small hole on the aircraft model; and a pressure gauge is further arranged on a connecting branch of the ball valve I and the liquid storage tank.
4. 4. A system for mitigating a plasma sheath as recited in claim 3, wherein a pressure relief valve is further provided between the drive gas source and the ball valve I.
5. 5. A system for mitigating a plasma sheath as recited in claim 3, wherein the water-passing valve is a bi-directional control valve.
6. 6. The system for slowing down a plasma sheath according to claim 2, wherein a plurality of sink slots matched with the external structures of the direct current power supply, the switch and the thyristor are arranged on the PVC plate; Wherein, the inner edge of each sinking groove is respectively provided with a flexible layer; the PVC plates are provided with mounting holes in pairs at positions matched with the sinking grooves.

Description

System for slowing down plasma sheath Technical Field The utility model relates to the field of ground plasma shock tunnel tests. More particularly, the present utility model relates to a system for mitigating plasma sheath. Background In the aerospace field, the spacecraft is in an ultra-high speed state, the surrounding atmospheric density changes sharply, a super strong shock wave appears at the front end, and the super strong shock wave and the strong friction action between high-speed airflow and the surface of the spacecraft cause the surrounding air temperature to rise rapidly, so that the surrounding atmosphere and the surface of the spacecraft are ionized, and a layer of high-temperature plasma is covered, namely a plasma sheath (also called a black barrier). The plasma sheath is unavoidable at the present stage, the plasma sheath appears when any spacecraft enters the atmosphere of any planet, and the plasma sheath formed by the spacecraft crossing the atmosphere also causes the interruption of radio signals. In order to solve the problem of radio signal interruption, in the ground plasma shock tunnel test, water is sprayed nearby a plasma sheath so as to achieve the purpose of slowing down the plasma sheath, but a spraying system special for slowing down the plasma sheath test is not provided. Although the prior art also discloses a related spraying device, such as a method for relieving the black barrier communication of a high-speed aircraft, as disclosed in patent application number 202110716664.8, a storage device and a spraying device are arranged in the aircraft, the storage device is used for storing carbon dioxide, the spraying device is used for spraying carbon dioxide, when the communication between the aircraft and the ground is interrupted, the spraying device is started, the carbon dioxide stored in the storage device is sprayed out of the aircraft, the direction of the spraying device spraying the carbon dioxide forms an acute angle with the direction of a plasma flow field, and the CO 2 finally generates neutral oxygen atoms through reaction, so that the electron density around the aircraft is reduced. However, the structure of the injection device is not described, and the following problems exist in the ground plasma shock tunnel experiment: Firstly, in the shock tunnel experiment, the time from the generation of a trigger signal to the opening of a water-through electromagnetic valve is very harsh due to the high generated shock speed, secondly, the plasma shock tunnel experiment is repeatedly carried out, so that the stability of the device is good, and a spraying system special for slowing down the plasma sheath experiment is not disclosed in the prior art, so that the device can be directly applied to the ground plasma shock tunnel experiment, and can rapidly open the water-through electromagnetic valve to finish the water spraying operation while ensuring the stability. Disclosure of utility model It is an object of the present utility model to address the above problems and/or disadvantages and to provide advantages which will be described below. To achieve these objects and other advantages and in accordance with the purpose of the utility model, there is provided a system for mitigating a plasma sheath, including a pressure sensor disposed at a foremost end of a shock tube, further comprising: the delay synchronous machine is connected with the pressure sensor through an optical fiber I; the spraying device is connected with the delay synchronous machine through an optical fiber II; Wherein, sprinkler includes: the circuit module is connected with the delay synchronous machine; And the water-passing electromagnetic valve module is electrically connected with the circuit module to switch the on-off state of a medium in the liquid storage tank and a reserved small hole on the aircraft model. Preferably, the circuit module is configured to include: a thyristor connected with the delay synchronous machine; a switch arranged between the thyristor and the water-passing electromagnetic valve module; A DC power supply for supplying power to the thyristor; the resistor is arranged in parallel with the water-through electromagnetic valve in the water-through electromagnetic valve module; The direct current power supply, the switch, the thyristor and the resistor are integrated on the PVC board. Preferably, the water passing solenoid valve module is configured to include: An air supply pipeline for communicating the liquid storage tank with an external driving air source, and a ball valve I arranged on the air supply pipeline; A water-passing electromagnetic valve for communicating the liquid storage tank with the reserved small hole on the aircraft model through a water-feeding pipeline; wherein a ball valve II is also arranged between the water-through valve and the reserved small hole on the aircraft model; and a pressure gauge is further arranged on a connecting branch of the ba