CN117345572A - Water-forced ion engine - Google Patents
Water-forced ion engine Download PDFInfo
- Publication number
- CN117345572A CN117345572A CN202311416406.3A CN202311416406A CN117345572A CN 117345572 A CN117345572 A CN 117345572A CN 202311416406 A CN202311416406 A CN 202311416406A CN 117345572 A CN117345572 A CN 117345572A
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- CN
- China
- Prior art keywords
- water
- ion
- ion engine
- thrust
- speed
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 150000002500 ions Chemical class 0.000 claims abstract description 41
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 22
- 239000007921 spray Substances 0.000 claims abstract description 8
- 238000005507 spraying Methods 0.000 claims abstract description 6
- 238000001816 cooling Methods 0.000 claims abstract description 5
- 230000000694 effects Effects 0.000 claims abstract description 5
- 238000002347 injection Methods 0.000 abstract description 2
- 239000007924 injection Substances 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 5
- 238000012360 testing method Methods 0.000 description 5
- 239000000243 solution Substances 0.000 description 4
- 230000001133 acceleration Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 239000003380 propellant Substances 0.000 description 3
- 239000000126 substance Substances 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- BSYNRYMUTXBXSQ-UHFFFAOYSA-N Aspirin Chemical compound CC(=O)OC1=CC=CC=C1C(O)=O BSYNRYMUTXBXSQ-UHFFFAOYSA-N 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 229910052786 argon Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009835 boiling Methods 0.000 description 1
- JJWKPURADFRFRB-UHFFFAOYSA-N carbonyl sulfide Chemical compound O=C=S JJWKPURADFRFRB-UHFFFAOYSA-N 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000005672 electromagnetic field Effects 0.000 description 1
- 230000005686 electrostatic field Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 235000013305 food Nutrition 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 239000010453 quartz Substances 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 239000000523 sample Substances 0.000 description 1
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Classifications
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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
- F03H1/0006—Details applicable to different types of plasma thrusters
- F03H1/0031—Thermal management, heating or cooling parts of the thruster
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
-
- 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
- F03H1/0006—Details applicable to different types of plasma thrusters
-
- 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
- F03H1/0093—Electro-thermal plasma thrusters, i.e. thrusters heating the particles in a plasma
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Plasma Technology (AREA)
Abstract
A water-forced ion engine is disclosed, in which water is injected into an injection nozzle, and the water is gasified under high temperature and high pressure and is significantly pressurized, and the water is injected together with ions, so that a higher thrust force and a higher speed are obtained. The water has good cooling effect on the spray nozzle. The water spraying speed is reasonably controlled, so that the water-forced ion engine can continuously work and obtain the highest thrust and maximum speed.
Description
Technical Field
The invention relates to a water-forced ion engine with energy saving, large thrust and high speed.
Background
The ion propeller is one kind of electric propulsion and features small thrust and high specific impulse, and may be used widely in space propulsion, such as spacecraft attitude control, position maintaining, orbit maneuver, interstellar flight, etc.
Ion propulsion uses ionization of working medium to generate ions, which are accelerated to be ejected under the action of electrostatic field to generate thrust, so that the ion propulsion is also called electrostatic propulsion. The acceleration principle of ion propulsion is simple, and in theory, no energy is lost in the acceleration process, so that the efficiency is high, and thousands of seconds of specific impulse can be obtained under the acceleration voltage of 1 kV. Ion propulsion is the first electric propulsion developed in time and sufficient for both ground and space flight tests.
Ion propulsion as early as 1965, SERT-I space flight tests were started, and SERT-II space flight tests were performed in 1970; 1997. from year to year, it is formally applied to commercial satellites; 1999. the first years of use as a primary propulsion system for a spacecraft.
With the increasing demands on satellite operational life, especially for large communication satellites, which can last up to 15 years, more and more propellant is required to maintain the fixed point position of the orbit, which is a significant weight factor for the payload. Therefore, propulsion systems for large communication satellites are imperative to use electric propulsion. In addition, the popularity of satellites has raised a need for electrical propulsion (including ion propulsion).
Traditional rockets are propelled forward by a tail jet of high velocity gas. The ion propeller adopts the same jet-type principle, but the ion propeller discharges hot gas instead of fuel combustion, and adopts a chemical combustion mode, and the high-speed ion flow is excited by the electric energy to propel backwards. It ejects a band of charged particles or ions. The propulsion provided by it may be relatively weak, but it is critical that such an ion thruster requires much less fuel than a conventional rocket. As long as the ion thruster can remain stable for a long period of time, it will eventually be able to accelerate the spaceship to a higher speed. The related art has been applied to some space ships such as "falcon" space probes in japan, "intelligent No. 1" space ship in europe and "dawn" in the united states, etc., and the technology has made great progress. The most promising future spacecraft propulsion for further outer space travel is the VASIMR plasma rocket. This rocket is slightly different from a general ion thruster. While a conventional ion thruster uses a strong electromagnetic field to accelerate ions, a vacmr plasma rocket uses a radio frequency generator to heat ions to 100 ten thousand degrees celsius. In a strong magnetic field, the ions rotate at a fixed frequency, tuning the rf generator to this frequency, implanting ions with extra strong energy, and increasing the propulsive force. Preliminary experiments have shown that if everything is successful, the VASIMR plasma rocket will be able to propel a manned spacecraft to Mars within 39 days.
Construction of valsimr was the idea proposed by Zhang Fulin in the 70 s of the 20 th century. It can have the capabilities of both chemical rocket engines and ion engines. The traditional chemical rocket engine has high thrust and low specific impulse, and the ion engine has low thrust and high specific impulse. While VASIMR, which enables free switching between high thrust, low specific impulse and low thrust, high specific impulse, adjusts the parameters between the two, so is called "variable specific impulse". Zhang Fulin has been devoted to this project but he was busy 7 times into space as astronauts for more than 20 years later. Until 2005 he had built Ad Astra rocket from NASA retirement, the pilot was in the aviation center near his birth place go dadadadadaga. The breakthrough result comes in 2008, namely a VX-200 plasma engine test bench, which achieves full power of 30 kilowatts in the first stage by using argon as a propellant. VX-200 has all-round exceeded traditional plasma engines: the specific impulse is randomly switched between 3000 and 30000 seconds, namely the speed of the jet plasma is 30 to 300 km/s, and the energy conversion efficiency is up to 67 percent. Zhang Fulin it is: "it only takes 39 days to fly to Mars, thus saving a lot of fuel, food, water and air, and astronauts can get rid of long-time cosmic ray radiation. "VX-200 is divided into three parts: in the front unit, the ejected gas is ionized first to generate plasma, similar to boiling water in a steamer, which is realized by a helical wave radio frequency antenna (helicon RF antennas); the central unit acts as an amplifier which further heats the plasma to several million degrees with the energy of electromagnetic waves; and the magnetic nozzle of the tail unit can convert the energy of the plasma into the speed of the air jet, so that reverse thrust is generated. Zhang Fulin it is explained that VX-200 uses a new algorithm to control and stabilize the plasma, mainly controlling the superconducting magnetic field. In general, the higher the temperature of the jet gas at the time of rocket launch, the higher the specific impulse. To maximize efficiency, the temperature of the central unit of the VASIMR rocket corresponds to the temperature of the sun center. But the temperature to which the jet nozzle of the rocket engine is subjected is limited. The nozzle temperature is too high and what material is used is a problem. As with the nuclear fusion device, the solution is to use a magnetic field. Under a strong magnetic field, such as that generated by a superconducting magnet, the plasma rotates at a fixed frequency. The middle unit of the engine rotates around the magnetic field at natural frequency under the control of the magnetic field, and after the temperature rises rapidly, the rotation is changed into axial movement from the tail unit and released. All these extremely varying environments require precise control of the magnetic field and electromagnetic waves, which is the work done by the new control algorithm. By the end of 5 months in 2009, VX-200 has started the test on a truly primitive prototype, which can achieve orbital transfer from the near earth orbit to the lunar orbit.
Disclosure of Invention
In order to make the ion engine obtain larger thrust and higher speed, the water-forced ion engine is invented.
The technical scheme adopted for solving the technical problems is as follows:
water is sprayed in the spray nozzle, and the water is gasified under high temperature and high pressure and is obviously pressurized, and the water is sprayed together with ions, so that higher thrust and higher speed are obtained.
The water has good cooling effect on the spray nozzle. The water spraying speed is reasonably controlled, so that the water-forced ion engine can continuously work and obtain the highest thrust and maximum speed.
The beneficial effects of the invention are as follows: and the higher thrust and higher speed are obtained on the premise of not increasing the energy consumption. The water has good cooling effect on the spray nozzle.
Drawings
Fig. 1 is a schematic diagram of an ion engine principle (from a network).
Fig. 2 is a schematic diagram of a water-forced ion engine.
The components marked in the figures are: (1) the method comprises the following steps A gas propellant injection system, (2) a quartz tube, (3): spiral coil, (4): magnet windings, (5): an ion cyclotron heating coil, (6) a magnetic nozzle, a: and a water spraying device.
Description of the embodiments
The following description of the technical solutions in the embodiments of the present invention will be clear and complete, and it is obvious that the described embodiments 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 any inventive effort, are intended to be within the scope of the invention.
Fig. 2 is a schematic diagram of a water-forced ion engine.
A water spraying device is arranged in a spray nozzle of the existing ion engine, and the water spraying speed is reasonably controlled, so that the ion engine works normally.
The water is gasified under high temperature and high pressure and is pressurized obviously, and is ejected together with ions so as to obtain higher thrust and higher speed. The water has good cooling protection effect on the spray nozzle.
Those of ordinary skill in the art will appreciate that: the modules or flows of the embodiments are not necessarily required to practice the invention.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (1)
1. A water-forced ion engine is characterized in that: water is sprayed in the spray nozzle, and the water is gasified and pressurized under high temperature and high pressure, and is sprayed together with ions, so that higher thrust and higher speed are obtained; the water has good cooling effect on the spray nozzle; the water spraying speed is reasonably controlled, so that the water-forced ion engine can continuously work and obtain the highest thrust and maximum speed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311416406.3A CN117345572A (en) | 2023-10-30 | 2023-10-30 | Water-forced ion engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311416406.3A CN117345572A (en) | 2023-10-30 | 2023-10-30 | Water-forced ion engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117345572A true CN117345572A (en) | 2024-01-05 |
Family
ID=89370904
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311416406.3A Pending CN117345572A (en) | 2023-10-30 | 2023-10-30 | Water-forced ion engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117345572A (en) |
-
2023
- 2023-10-30 CN CN202311416406.3A patent/CN117345572A/en active Pending
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