CN113187622B - Electro-chemical hybrid power space thruster - Google Patents
Electro-chemical hybrid power space thruster Download PDFInfo
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- CN113187622B CN113187622B CN202110527585.2A CN202110527585A CN113187622B CN 113187622 B CN113187622 B CN 113187622B CN 202110527585 A CN202110527585 A CN 202110527585A CN 113187622 B CN113187622 B CN 113187622B
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- voltage
- propellant
- solid propellant
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- electric control
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
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- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B25/00—Compositions containing a nitrated organic compound
- C06B25/34—Compositions containing a nitrated organic compound the compound being a nitrated acyclic, alicyclic or heterocyclic amine
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- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06D—MEANS FOR GENERATING SMOKE OR MIST; GAS-ATTACK COMPOSITIONS; GENERATION OF GAS FOR BLASTING OR PROPULSION (CHEMICAL PART)
- C06D5/00—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets
- C06D5/06—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by reaction of two or more solids
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/74—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0087—Electro-dynamic thrusters, e.g. pulsed plasma thrusters
Abstract
The invention discloses an electro-chemical hybrid power space thruster which comprises a shell, an insulating sleeve, a spring, a low-voltage cathode, an electric control solid propellant, a low-voltage anode, an insulating plate, a high-voltage anode, a propellant for electric propulsion, a high-voltage cathode, an insulating sleeve and a fixed contact pin. The electric control solid propellant is used for replacing the traditional solid chemical propellant, so that the repeated ignition and flameout and thrust regulation operations of the solid propellant are realized; the traditional solid chemical thruster is improved, and the traditional solid chemical thruster and the pulse plasma thruster are integrated into a set of electro-chemical hybrid power space thruster, so that the requirements of large thrust and high specific impulse of space propulsion are met; when the thruster burns the electric control solid propellant to work, products generated by burning can be accelerated by the action of an electric field between the high-voltage anode and the high-voltage cathode, and the thrust and the specific impulse during electrochemical propulsion are increased.
Description
Technical Field
The invention relates to the technical field of aerospace propulsion, in particular to an electro-chemical hybrid power space thruster.
Background
With the rapid development of the aerospace industry, particularly the rapid increase of commercial launching tasks and the expansion of space exploration tasks, new requirements are provided for a space propulsion technology for realizing the operations of orbital transfer, attitude adjustment, formation flight and the like of aircrafts. The traditional chemical propulsion technology and the electric propulsion technology are the mainstream of the current space propulsion technology. The traditional chemical propulsion technology has the outstanding characteristics of providing high thrust, but is influenced by the properties of the propellant, is difficult to realize multiple starting and thrust-adjustable operation, and has low specific impulse (the specific impulse is about 450s at most). Performing a long range maneuver using conventional chemical propulsion techniques tends to require the propulsion system to carry a large mass of propellant, which reduces its payload to whole star mass ratio. While the electric propulsion technology has advantages in specific impulse, propellant life and adjustable thrust, the electric propulsion technology requires more time for completing the orbital transfer operation compared with the traditional chemical propulsion because the thrust is small (micro-Newton magnitude). Therefore, the two main propulsion technologies cannot simultaneously reduce the mass of the satellite orbit keeping and maneuvering power system and shorten the operation time required by the satellite remote orbit transfer, that is, cannot simultaneously meet the requirements of high specific impulse and high thrust which are urgently needed by space propulsion.
Disclosure of Invention
The invention provides an electrochemical hybrid power space thruster, aiming at the current situation that the requirements of high specific impulse and high thrust are difficult to meet simultaneously in the prior propelling technology.
The technical scheme for realizing the purpose of the invention is as follows:
an electro-chemical hybrid power space thruster comprises a shell, an insulating sleeve, a spring, a low-voltage cathode, an electric control solid propellant, a low-voltage anode, an insulating plate, a high-voltage anode, a propellant for electric propulsion, a high-voltage cathode, an insulating sleeve and a fixed contact pin.
The propellant for electric propulsion, the high-voltage anode and the high-voltage cathode are all arranged in the flame spraying direction of the electric control solid propellant (4).
In the electro-chemical hybrid power space thruster, the electric control solid propellant is arranged between the low-voltage cathode and the low-voltage anode in a layer electrode contact mode. The insulating and heat-insulating sleeve is arranged outside the electric control solid propellant and used for insulation and heat insulation. The low voltage anode is a flat plate porous structure.
In the electro-chemical hybrid power space thruster, the high-voltage anode, the propellant for electric propulsion, the high-voltage cathode and the insulating sleeve are of coaxial matching structures, and the propellant for electric propulsion is arranged in the insulating sleeve. The high-voltage anode is provided with a 15-degree conical nozzle hole, and the high-voltage cathode is of a flat plate porous structure.
In the above electro-chemical hybrid space thruster, the insulating plate is interposed between the low voltage anode and the high voltage cathode.
In the electro-chemical hybrid power space thruster, the electrically-controlled solid propellant comprises, by weight, 60-80% of an oxidant, 15-20% of a binder and 1-2% of a cross-linking agent. Wherein, the oxidant is hydroxylamine nitrate (HAN), the binder is polyvinyl alcohol (PVA), and the cross-linking agent is boric acid (HB).
In the electro-chemical hybrid power space thruster, the propellant for electric propulsion is polytetrafluoroethylene.
In the electro-chemical hybrid power space thruster, the insulating and heat-insulating sleeve is made of phenolic aldehyde-asbestos material.
In the electro-chemical hybrid power space thruster, the insulating plate and the insulating sleeve are made of ceramic materials.
Compared with the prior art, the invention has the advantages that:
1. the electric control solid propellant is used for replacing the traditional solid chemical propellant, the action of ignition powder is not needed, the self-loading quantity is increased, the electric control solid propellant only reacts to voltage stimulation, multiple times of ignition and flameout and thrust regulation operations are realized, and the potential hazard caused by violent response due to external impact, friction and the like is avoided;
2. the traditional solid chemical thruster is improved, and the traditional solid chemical thruster and the pulsed plasma thruster are integrated into a set of electro-chemical hybrid power space thrusters. The thruster has two working modes, and the high thrust can be realized by adopting the mode of burning the electric control solid propellant; the high specific impulse can be realized by adopting the mode of ablating polytetrafluoroethylene, so that one thruster can meet the requirements of different tasks of the aircraft;
3. when the thruster burns the electric control solid propellant to work, the products generated by burning can be accelerated by the action of an electric field between the high-voltage anode and the high-voltage cathode, and the thrust and the specific impulse during electrochemical propulsion are increased.
Drawings
Fig. 1 is a schematic view illustrating an operation mode of an electro-chemical hybrid space thruster according to the present invention.
Fig. 2 is a schematic structural view of an electro-chemical hybrid space thruster of the present invention.
Detailed Description
The invention will be further explained with reference to the drawings
As shown in fig. 1, when a satellite executes a low orbit task, an attitude and orbit control engine is required to provide 1N-10N of thrust, at the moment, the electro-chemical hybrid power space thruster adopts an electrochemical propulsion working mode, voltage is applied by a pulse power supply to burn an electrically controlled solid propellant to generate target thrust, and the process converts the internal energy of the propellant into kinetic energy. When the satellite executes a high orbit or deep space exploration task, the attitude and orbit control engine is required to provide a specific impulse of more than 1000s, at the moment, the electro-chemical hybrid power space thruster adopts an electric propulsion working mode, a pulse power supply applies voltage to ablate polytetrafluoroethylene for ionization to generate target specific impulse, and the stored electric energy is converted into kinetic energy in the process.
As shown in fig. 2, the electro-chemical hybrid space thruster of the present invention includes a casing 1, an insulating sheath 2, a low voltage cathode 3, an electrically controlled solid propellant 4, a low voltage anode 5, an insulating plate 6, an insulating sheath 7, a high voltage anode 8, a propellant 9 for electric propulsion, a high voltage cathode 10, a spring 11, and a fixed pin 12. An insulating sleeve 2, a low-voltage cathode 3, an electric control solid propellant 4, a low-voltage anode 5, an insulating plate 6, an insulating sleeve 7, a high-voltage anode 8, a propellant 9 for electric propulsion, a high-voltage cathode 10 and a spring 11 are arranged in the shell 1, and a fixed contact pin 12 is arranged at the bottom end of the shell 1.
The electric control solid propellant 4 is arranged between the low-voltage cathode 3 and the low-voltage anode 5, the front end of the electric control solid propellant 4 is contacted with the low-voltage anode 5, the rear end of the electric control solid propellant 4 is contacted with the low-voltage cathode 3, and the spring 11 pushes the low-voltage cathode 3 and the low-voltage anode 5 to be tightly contacted with the electric control solid propellant grain 4. The low voltage anode 5 has a plate porous structure, and the pores serve to discharge fuel gas.
The electric control solid propellant 4 is placed in the insulating sleeve 2, and the insulating sleeve 2 is made of phenolic-asbestos materials and is used for keeping heat insulation and insulation.
The gas products generated during the combustion of the electrically-controlled solid propellant 4 can be accelerated by the action of the electric field between the high-voltage anode 8 and the high-voltage cathode 10, so that the thrust and the specific impulse generated by the electrochemical propulsion can be improved.
The electrically controlled solid propellant 4 consists of an oxidizer, a binder and a cross-linking agent. The mass percentage of the oxidant hydroxylamine nitrate (HAN) accounts for 60-80% of the electrically-controlled solid propellant 4, the binder polyvinyl alcohol (PVA) accounts for 15-20% of the electrically-controlled solid propellant 4, and the cross-linking agent boric acid (HB) accounts for 1-2% of the electrically-controlled solid propellant 4.
The insulating sleeve 7, the high-voltage anode 8, the propellant 9 for electric propulsion and the high-voltage cathode 10 are of a coaxial matching structure, and the propellant 9 for electric propulsion is arranged in the insulating sleeve 7. The insulating sleeve 7 is made of ceramic material. The high-voltage anode 8 is provided with a 15-degree conical nozzle hole, and the high-voltage cathode 10 is of a flat plate porous structure. The propellant 9 for electric propulsion is a polytetrafluoroethylene material.
The insulating plate 6 is made of a ceramic material and is disposed between the low voltage anode 4 and the high voltage cathode 10 to insulate them.
Claims (3)
1. An electro-chemical hybrid space thruster, characterized by: comprises a shell (1),
An insulating and heat-insulating sleeve (2), a low-voltage cathode (3), an electric control solid propellant (4), a low-voltage anode (5), an insulating sleeve (7), a high-voltage anode (8), a propellant (9) for electric propulsion, a high-voltage cathode (10) and a spring (11) are arranged in the shell (1), and a fixed contact pin (12) is arranged at the bottom of the shell (1);
the electric control solid propellant (4) is arranged between the low-voltage cathode (3) and the low-voltage anode (5), the front end of the electric control solid propellant (4) is contacted with the low-voltage anode (5), the rear end of the electric control solid propellant (4) is contacted with the low-voltage cathode (3), and the spring (11) pushes the low-voltage cathode (3) and the low-voltage anode (5) to be tightly contacted with the electric control solid propellant grain (4);
the propellant (9) for electric propulsion, the high-voltage anode (8) and the high-voltage cathode (10) are all arranged in the flame spraying direction of the electric control solid propellant (4);
the insulating sleeve (7), the high-voltage anode (8), the propellant (9) for electric propulsion and the high-voltage cathode (10) are of a coaxial matching structure, and the propellant (9) for electric propulsion is arranged in the insulating sleeve (7);
the electronic control solid propellant (4) comprises an oxidant, a binder and a cross-linking agent, wherein the oxidant is hydroxylamine nitrate, the binder is polyvinyl alcohol, and the cross-linking agent is boric acid;
the mass percentage of the oxidant hydroxylamine nitrate accounts for 60-80% of the electrically-controlled solid propellant (4), the binder polyvinyl alcohol PVA accounts for 15-20% of the electrically-controlled solid propellant (4), and the cross-linking agent boric acid HB accounts for 1-2% of the electrically-controlled solid propellant (4);
the high-voltage anode (8) is provided with a 15-degree conical nozzle hole, and the high-voltage cathode (10) is of a flat plate porous structure;
an insulating plate (6) is disposed between the low voltage anode (5) and the high voltage cathode (10).
2. The electro-chemical hybrid space thruster of claim 1, wherein: the gas product generated during the combustion of the electric control solid propellant (4) can be accelerated by the action of an electric field between a high-voltage anode (8) and a high-voltage cathode (10), so that the thrust and the specific impulse generated by electrochemical propulsion are improved.
3. The electro-chemical hybrid space thruster of claim 2, wherein: the electric control solid propellant (4) is placed in the insulating sleeve (2), and the insulating sleeve (2) is made of phenolic aldehyde-asbestos materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110527585.2A CN113187622B (en) | 2021-05-14 | 2021-05-14 | Electro-chemical hybrid power space thruster |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110527585.2A CN113187622B (en) | 2021-05-14 | 2021-05-14 | Electro-chemical hybrid power space thruster |
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| Publication Number | Publication Date |
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| CN113187622A CN113187622A (en) | 2021-07-30 |
| CN113187622B true CN113187622B (en) | 2022-08-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110527585.2A Active CN113187622B (en) | 2021-05-14 | 2021-05-14 | Electro-chemical hybrid power space thruster |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115234459B (en) * | 2022-08-30 | 2023-10-20 | 兰州空间技术物理研究所 | High discharge stability's micropulse plasma thruster nozzle assembly |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107642435A (en) * | 2016-12-16 | 2018-01-30 | 湖北航天化学技术研究所 | A kind of adjustable thrust, it can repeatedly start automatically controlled solid engine |
| CN108612599A (en) * | 2016-12-10 | 2018-10-02 | 中国科学院大连化学物理研究所 | A kind of liquid-electricity interblock space thruster |
| CN110714855A (en) * | 2018-07-12 | 2020-01-21 | 南京理工大学 | Electric control power device with real-time controllable thrust and capable of repeatedly igniting and extinguishing |
| CN111169659A (en) * | 2020-01-16 | 2020-05-19 | 南京理工大学 | Intelligent controllable supercharging device for cold air propulsion |
-
2021
- 2021-05-14 CN CN202110527585.2A patent/CN113187622B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108612599A (en) * | 2016-12-10 | 2018-10-02 | 中国科学院大连化学物理研究所 | A kind of liquid-electricity interblock space thruster |
| CN107642435A (en) * | 2016-12-16 | 2018-01-30 | 湖北航天化学技术研究所 | A kind of adjustable thrust, it can repeatedly start automatically controlled solid engine |
| CN110714855A (en) * | 2018-07-12 | 2020-01-21 | 南京理工大学 | Electric control power device with real-time controllable thrust and capable of repeatedly igniting and extinguishing |
| CN111169659A (en) * | 2020-01-16 | 2020-05-19 | 南京理工大学 | Intelligent controllable supercharging device for cold air propulsion |
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| CN113187622A (en) | 2021-07-30 |
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