CN-115949562-B - Self-cooling air suction type radio frequency plasma electric thruster

CN115949562BCN 115949562 BCN115949562 BCN 115949562BCN-115949562-B

Abstract

The invention provides a self-cooling air suction type radio frequency plasma electric thruster which comprises an air inlet channel, an ionization chamber and a spray pipe, wherein the air inlet channel is divided into a main air inlet channel and an auxiliary air inlet channel, the main air inlet channel is communicated with the ionization chamber, a cooling flow channel is arranged at the periphery of the ionization chamber, the auxiliary air inlet channel is communicated with a guide channel through a cooling flow channel inlet, the guide channel is communicated with the ionization chamber through a cooling flow channel outlet, gas taken by the main air inlet channel directly enters the ionization chamber to be ionized, gas taken by the auxiliary air inlet channel is guided to the cooling flow channel inlet through the guide channel, enters the cooling flow channel to be ionized through the cooling flow channel outlet after entering the ionization chamber, and two airflows entering the ionization chamber are ionized and then accelerated through the spray pipe, so that the thruster generates thrust. The cooling design provided by the invention has the advantages of simple structure and high energy utilization rate.

Inventors

HU ZEJUN
ZHONG YUXUAN
ZHANG YU
WU JIANJUN
LIU YUWEI
ZHENG PENG
PENG JIANYU

Assignees

中国人民解放军国防科技大学

Dates

Publication Date: 20260508
Application Date: 20230227

Claims (8)

1. The self-cooling air suction type radio frequency plasma electric thruster comprises a thruster shell, and an air inlet channel, an ionization chamber and a spray pipe which are arranged in the thruster shell, and is characterized in that the air inlet channel is divided into a main air inlet channel and an auxiliary air inlet channel, the main air inlet channel is communicated with the ionization chamber, the ionization chamber is communicated with the spray pipe, a cooling flow channel is arranged on the periphery of the ionization chamber, the auxiliary air inlet channel is communicated with the cooling flow channel through a cooling flow channel inlet, the cooling flow channel is communicated with the ionization chamber through a cooling flow channel outlet, the main air inlet channel, the ionization chamber and the spray pipe are sequentially connected and coaxially arranged, the air inlet channel is an annular channel between the air inlet channel shell and the thruster shell, the air inlet channel shell is sleeved with the main air inlet channel rear section, the ionization chamber and the spray pipe, and an annular space between the air inlet channel shell and the main air inlet channel outer side wall, the ionization chamber outer side wall and the spray pipe outer side wall form a cooling flow channel; The gas taken by the main air inlet channel directly enters the ionization chamber for ionization, the gas taken by the auxiliary air inlet channel is guided to the cooling flow channel inlet through the air guide channel, enters the cooling flow channel through the cooling flow channel inlet for cooling the ionization chamber, enters the ionization chamber through the cooling flow channel outlet for ionization, and two airflows entering the ionization chamber are accelerated through the spray pipe after being ionized, so that the thruster generates thrust.
2. The self-cooling air suction type radio frequency plasma electric thruster of claim 1, wherein the inlet of the air inlet channel is of a honeycomb structure and is formed by closely arranging a plurality of air inlet holes in a honeycomb shape, a plurality of layers of air inlet holes positioned in the middle are used as a main air inlet channel air inlet, and one or more layers of air inlet holes positioned at the periphery are used as auxiliary air inlet channel air inlets.
3. The self-cooling, air-sucking, radio-frequency plasma electric thruster of claim 2, wherein the main air inlet is horn-shaped and has a parabolic cross-section tapered structure along the direction of airflow.
4. The self-cooling, gettering, RF plasma thruster of claim 3 in which the primary air intake channel is coated with aluminized reflective material on its inner sidewall.
5. The self-cooling, gas-absorbing RF plasma thruster of claim 1, 2, 3 or 4, wherein the ionization chamber and the nozzle are of a split design or of an integrated design.
6. The self-cooling, air-breathing, radio-frequency plasma electric thruster of claim 5, wherein the air duct housing near the end of the nozzle is provided with a plurality of first air ducts which are annularly distributed, the first air ducts are used as cooling flow passage inlets, and the outer side wall of the main air inlet duct in the cooling flow passage or the outer side wall of the ionization chamber near the end of the main air inlet duct is provided with a plurality of second air ducts which are annularly distributed, and the second air ducts are used as cooling flow passage outlets.
7. A self-coolable, gas-absorbing RF plasma thruster as set forth in claim 1 or 2 or 3 or 4 or 6 wherein said nozzle expansion ratio is 2.
8. The self-cooling, gas-sucking RF plasma thruster of claim 1, 2,3, 4 or 6, wherein the RF coil diffracted outside the ionization chamber is located in the cooling flow channel, and the electromagnetic coil diffracted outside the rear section of the ionization chamber and outside the front section of the nozzle is located in the cooling flow channel, so that the gas flowing through the cooling flow channel can sufficiently cool the electromagnetic coil.

Description

Self-cooling air suction type radio frequency plasma electric thruster Technical Field The invention mainly relates to the technical field of electric thrusters, in particular to a self-cooling air suction type radio frequency plasma electric thruster. Background The ultra-low orbit space of the earth has the remarkable advantages of low emission cost and contribution to earth observation and communication, and in recent years, with the development of the air suction type electric propulsion technology, people have shown great development enthusiasm for the high orbit space. The satellite at the height can receive the pneumatic resistance which cannot be ignored, so that the air suction type electric thruster cannot work for a long time at the height, the air suction type electric thruster can capture the air with thin orbit space through a special air inlet device, obtain thrust after ionization acceleration, and the thrust compensation can cause impulse loss to the satellite due to the pneumatic resistance, so that the air suction type electric thruster can work for a long time in the ultra-low orbit space. The suction electric thruster needs to provide thrust compensation for the satellite for a long time, and long-term operation can cause a large amount of joule heat to be generated inside, so that a corresponding cooling device needs to be designed. Most of the existing suction electric thrusters do not consider the cooling problem, and the electric thrusters with the cooling devices are additionally provided with a refrigerator for cooling the thrusters, which can certainly increase the volume and the mass of the thrusters, so that the design and the emission cost of the thrusters are greatly increased. Disclosure of Invention Aiming at the technical problems in the prior art, the invention provides a self-cooling air suction type radio frequency plasma electric thruster, which is characterized in that the structure is specially designed, so that part of the air sucked by the electric thruster can pass through a cooling flow channel to cool the high-temperature part of the thruster, and then the part of the air can enter an ionization chamber to be ionized and accelerated. In order to achieve the above purpose, the technical scheme adopted by the invention is as follows: The utility model provides a but self-cooling's air suction type radio frequency plasma electric thruster, includes the thruster shell and sets up intake duct, ionization chamber and spray tube in the thruster shell, the intake duct divide into main intake duct and auxiliary intake duct, main intake duct and ionization chamber UNICOM, ionization chamber UNICOM spray tube, the periphery of ionization chamber is provided with the cooling runner, auxiliary intake duct UNICOM air duct, air duct with cool runner between the entry UNICOM through the cooling runner, cool runner with cool runner outlet UNICOM between the ionization chamber; The gas taken by the main air inlet channel directly enters the ionization chamber for ionization, the gas taken by the auxiliary air inlet channel is guided to the cooling flow channel inlet through the air guide channel, enters the cooling flow channel through the cooling flow channel inlet for cooling the ionization chamber, enters the ionization chamber through the cooling flow channel outlet for ionization, and two airflows entering the ionization chamber are accelerated through the spray pipe after being ionized, so that the thruster generates thrust. Furthermore, the inlet of the air inlet channel is of a honeycomb structure and is formed by closely arranging a plurality of air inlet holes in a honeycomb shape, a plurality of layers of air inlet holes positioned in the middle are used as main air inlet channels, and one or more layers of air inlet holes positioned at the periphery are used as auxiliary air inlet channels. Further, the main air inlet is in a horn shape, and the main air inlet is in a parabolic cross-section tapered structure along the airflow direction. Furthermore, the inner side wall of the main air inlet is coated with aluminized reflecting materials. Further, the ionization chamber and the spray pipe are in an assembled split design or an integrated design. Further, the main air inlet channel, the ionization chamber and the spray pipe are sequentially connected and coaxially arranged. Furthermore, the air guide channel is an annular channel between the air guide channel shell and the thruster shell, the air guide channel shell is sleeved with the rear section of the main air inlet channel, the ionization chamber and the spray pipe, and the air guide channel shell forms a cooling flow channel with the annular space among the outer side wall of the main air inlet channel, the outer side wall of the ionization chamber and the outer side wall of the spray pipe. In the invention, a plurality of first air guide holes which are annularly distributed are formed on the air guide passage s