CN113173266A - Plasma vector propeller without moving part - Google Patents
Plasma vector propeller without moving part Download PDFInfo
- Publication number
- CN113173266A CN113173266A CN202110411851.5A CN202110411851A CN113173266A CN 113173266 A CN113173266 A CN 113173266A CN 202110411851 A CN202110411851 A CN 202110411851A CN 113173266 A CN113173266 A CN 113173266A
- Authority
- CN
- China
- Prior art keywords
- plasma
- vector
- thruster
- discharge tube
- discharge
- 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.)
- Granted
Links
- 230000008878 coupling Effects 0.000 claims abstract description 10
- 238000010168 coupling process Methods 0.000 claims abstract description 10
- 238000005859 coupling reaction Methods 0.000 claims abstract description 10
- 239000007789 gas Substances 0.000 claims description 44
- 239000003570 air Substances 0.000 claims description 7
- 230000001939 inductive effect Effects 0.000 claims description 7
- 239000011261 inert gas Substances 0.000 claims description 7
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 6
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 6
- 229910052786 argon Inorganic materials 0.000 claims description 3
- 238000006880 cross-coupling reaction Methods 0.000 claims description 3
- 239000001307 helium Substances 0.000 claims description 3
- 229910052734 helium Inorganic materials 0.000 claims description 3
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims description 3
- 229910052757 nitrogen Inorganic materials 0.000 claims description 3
- 229910052724 xenon Inorganic materials 0.000 claims description 3
- FHNFHKCVQCLJFQ-UHFFFAOYSA-N xenon atom Chemical compound [Xe] FHNFHKCVQCLJFQ-UHFFFAOYSA-N 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 claims description 2
- 239000007769 metal material Substances 0.000 claims 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims 1
- 238000003491 array Methods 0.000 claims 1
- 229910052802 copper Inorganic materials 0.000 claims 1
- 239000010949 copper Substances 0.000 claims 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims 1
- 229910052721 tungsten Inorganic materials 0.000 claims 1
- 239000010937 tungsten Substances 0.000 claims 1
- 108091092878 Microsatellite Proteins 0.000 abstract description 19
- 238000012423 maintenance Methods 0.000 abstract description 4
- 230000007935 neutral effect Effects 0.000 description 5
- 230000002452 interceptive effect Effects 0.000 description 4
- 150000002500 ions Chemical class 0.000 description 4
- 230000015572 biosynthetic process Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000005284 excitation Effects 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000003384 imaging method Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/242—Orbits and trajectories
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/244—Spacecraft control systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/26—Guiding or controlling apparatus, e.g. for attitude control using jets
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Radar, Positioning & Navigation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automation & Control Theory (AREA)
- Plasma Technology (AREA)
Abstract
The invention discloses a plasma vector thruster without a moving part, which realizes vector propulsion without a mechanical movement deflection part by combining a multi-tube coupling discharge tube. The air supply and the discharge tubes are directly connected through the valves, the valves can independently control air inflow of each discharge tube, the antennas are embedded in the discharge tubes and externally connected with a power supply, the grounding electrodes are sleeved at two ends of the discharge tubes, and each antenna can also be independently controlled. The plasma vector thruster is small in space size and total mass, can work in a single-tube mode and a multi-tube combination mode, can realize thrust of the magnitude of micro-newton to milli-newton, can realize accurate vector control by using the multi-tube combination, and is suitable for being equipped with a micro satellite for high-precision attitude control and relative orbit position maintenance. In addition, the system is single-sided array type, has compact structure, can be installed on one side of the spacecraft, and saves loading space.
Description
Technical Field
The invention is suitable for the technical field of plasma propulsion, namely a micro propulsion system with high integration degree, low power consumption, small thrust and micro impulse, can be applied to formation flight and constellation composition of micro satellites (micro satellites, nano satellites and pico satellites), and is especially designed for the implementation of a propulsion system and a vector propeller of the micro satellites, wherein the propulsion system is mainly designed for inductive and capacitive cross-coupling discharge plasma micro propulsion, and the vector propeller is mainly used for realizing the angular deflection of the satellites through the combination of discharge tubes.
Background
The propulsion system is a key subsystem for the spacecraft to execute the tasks of orbit maneuver, special attitude control and the like, but the micro-satellite developed internationally in the last two decades is almost not provided with the propulsion system or has only extremely limited maneuvering capability, mainly because the traditional propulsion system has large volume and mass and is not suitable for the micro-satellite. However, with the development of the micro satellite technology and the expansion of the application field thereof, and the current continuous depth of space exploration at home and abroad, the micro propulsion system is required to be more and more urgent. The micro satellites are formed into a formation flying and form a constellation, so that the work which cannot be completed by a plurality of complex and expensive large satellites can be completed, the efficiency of completing the work in many times is higher, and the cost is lower, such as forming a distributed satellite-borne carrier radar, satellite three-dimensional imaging, high-resolution synthetic aperture ground remote sensing and the like. However, to accomplish the above task, very high requirements are put forward for maintaining the relative orbit position between satellites and controlling the attitude with high precision, which are specifically as follows:
firstly, the micro satellite has small volume, light weight and small rotational inertia, and has small thrust required by the control of the satellite orbit and attitude and high required precision, which is generally in the magnitude of micro-newton to milli-newton;
second, the goal of the formation of miniature satellites is to maintain the relative positions of the satellites without regard to the position of the satellitesIs an absolute position, the minimum impulse required is very small, usually the required impulse range is 10 according to the control precision requirement and the control period9Ns～103Ns magnitude;
third, the microsatellites can provide a low supply voltage, typically 3V to 12V, up to 28V, with a total power typically on the order of 1W to tens of watts.
Therefore, a micro propulsion system suitable for micro satellite orbit keeping, orbit maneuver and attitude control, high integration, low power consumption, small thrust and micro impulse has to be researched, i.e. a vector micro propulsion system is needed.
There are many plasma propulsion systems, such as hall thruster and ion thruster, which have been developed rapidly in recent years, but they are all electromagnetic propulsion, and they eject ion jet, and they need cathode electron to neutralize and maintain electric neutrality, and their propulsion devices all need magnet to generate magnetic field to restrain plasma, resulting in complex device, not suitable for propulsion of micro satellite. At present, a plasma propeller which discharges interactively through inductive and capacitive properties belongs to electrothermal micro propulsion, the space size and the total quality of the plasma propeller are very suitable for propelling a micro satellite, impulse pulse is very low, the thrust of the magnitude of micro-newton to millinewton can be realized, the average power consumption is only 10-100W, and the plasma propeller is very suitable for being equipped with the micro satellite for high-precision attitude control and relative orbit position maintenance. But because the thrust of a single pipe is very small and vector propulsion cannot be realized, the combination of multiple pipes is needed in practical application.
Disclosure of Invention
In order to solve the defects in the prior art, the invention provides a plasma vector thruster without a moving part. The invention mainly improves the disadvantages of small thrust and single-direction propulsion of a single electrothermal inductive capacitive interactive discharge plasma thruster, improves the thrust by single-side array combination of a plurality of inductive-capacitive interactive coupling discharge plasma thrusters, and realizes vector propulsion by controlling the ignition of a plurality of thrusters in array combination.
The plasma vector propeller without moving parts adopts a plurality of inductive-capacitive interactive coupling discharge plasma propulsion systems, is formed by combining a plurality of plasma propulsion systems, and comprises an air source, a valve, an inductive-capacitive interactive coupling antenna, a grounding electrode, a discharge tube and a radio frequency power supply. In a plasma propulsion system, one end of a gas source is connected with a gas collection chamber, plasma is generated by excitation in a discharge tube, gas of the gas source is heated when passing through a plasma region, then the gas is expanded and sprayed out to the other end to form thrust, and the gas is required to be placed in a vacuum environment constructed in a vacuum chamber during experiments.
The gas source is directly connected with each discharge tube, and the gas inlet of each discharge tube is independently controlled by a valve;
the antenna is connected with a radio frequency power supply and embedded in the middle of the discharge tube, and 2 grounding electrodes are sleeved at two ends of the discharge tube and used for exciting plasma;
the frequency of the radio frequency power supply is 13.56 MHz.
The gas inlet end of the gas source is filled with gas, the other end of the gas source is connected with the discharge tube through a valve, the used gas is air, nitrogen or inert gas, and the inert gas comprises one of argon, helium and xenon.
The gas used for the gas source can be air, nitrogen or inert gas, and the inert gas comprises argon, helium, xenon and the like.
Has the advantages that:
1. the plasma vector propeller without moving parts belongs to an electric propulsion system, does not generate blockage compared with a chemical propulsion system, and can realize micro thrust by using a small-size nozzle throat.
2. When the device is used for accurately controlling the attitude and the orbital position of the micro satellite, the plasma vector thruster without mechanical moving parts has smaller overall mass compared with the traditional vector thruster, the generated thrust is larger than that of a single-tube vector thruster, and the angle deflection is more accurate.
3. In addition, the electric propulsion has the advantages of high specific impulse and small thrust, but the traditional electric propulsion needs a large amount of electric power (1-2kW), the plasma vector propulsion without moving parts has low power consumption, and in one embodiment, the average power consumption of each discharge tube is only 10-100W, so that the plasma vector propulsion without moving parts can work in a single tube mode and a multi-tube combination mode, not only can realize the thrust in the magnitude of micro-newton to milli-newton, but also can realize accurate vector control by using a multi-tube combination, and is very suitable for a micro satellite with limited power to realize high-precision attitude control and relative orbit position maintenance.
4. The system is single-sided array type, has compact structure, can be installed on one side of a spacecraft, and saves loading space.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings in one example are briefly described below.
FIG. 1 is a schematic diagram and three-dimensional view of a single-sided 3X 3 array plasma vector thruster; FIG. 1(a) -side view, FIG. 1(b) -front view, FIG. 1(c) -rear view, in mm;
FIG. 2 is a schematic diagram illustrating a principle of measuring a corresponding relationship between ignition distribution of a plasma vector thruster and angular deflection of a satellite model; FIG. 2(a) shows the discharge tube fully ignited with no tilt in the horizontal plane, and FIG. 2(b) shows the discharge tube partially ignited with a tilt in the horizontal plane toward no ignition; fig. 2(c) is a partially enlarged view.
Description of reference numerals: the method comprises the following steps of 1-gas source, 2-valve, 3-antenna, 4-grounding electrode, 5-discharge tube, 6-radio frequency power supply, 7-hot gas jet, 8-level meter and 9-graduated scale. The hot gas jet 7 is a component of the non-plasma vector thruster, ions in plasma generated by discharge collide with neutral gas in charge exchange to generate heat, and the neutral gas is heated and sprayed out to the other end to generate the hot gas jet 7.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, rather than all embodiments, and all other embodiments obtained by a person skilled in the art based on the embodiments of the present invention belong to the protection scope of the present invention without creative efforts.
According to an embodiment of the present invention, a plasma vector thruster without moving parts, comprising one or more propulsion systems, wherein each individual propulsion system is an inductive-capacitive intercoupled discharge plasma propulsion system, comprising: the device comprises a gas source (1), a valve (2), an antenna (3), a grounding electrode (4), a discharge tube (5) and a radio frequency power supply (6);
the gas source (1) is directly connected with each discharge tube (5) and is independently controlled by the valve (2);
the antenna (3) is connected with the radio frequency power supply (6) and is embedded in the middle of the discharge tube (5) to form inductive coupling discharge for exciting plasma and heating gas entering the discharge tube (5) from the gas source (1);
the grounding electrode (4) is sleeved at two ends of the discharge tube (5) and forms inductive-capacitive cross coupling discharge with the antenna (3) for exciting plasma.
In the embodiment of fig. 1, the individual propulsion systems are arranged in an array, employing a single-sided 3 x 3 array of plasma vector propellers without moving parts. Or in other combinations, the discharge tubes may be in a 2 x 2, 4 x 4, annular array or other embodiments.
The antenna (3) is wound on the discharge tube (5), and common plasma excitation antennas such as a capacitive coupling antenna, an inductive coupling antenna and a helical wave antenna can be used as the antenna.
Each discharge tube (5) is controlled to be opened and closed independently by a valve (2).
Placing the plasma vector propeller in a vacuum chamber, vacuumizing to make the air pressure reach a specified value of 7 multiplied by 10-7Torr。
Introducing gas from a gas source (1), wherein the gas is air or inert gas, the gas pressure of a gas collection chamber of the gas source is controlled at 1.6Torr, and the gas pressure in a discharge tube is 2.5X 10-4Torr。
And (3) turning on a radio frequency power supply (6) to adjust the power, controlling the power to be 10-100W, exciting in the discharge tube to generate plasma, wherein ions and neutral gas generate heat through charge exchange collision to heat the neutral gas, and the neutral gas expands to spray hot gas jet flow (7) to the other end to generate thrust.
The angle formed by the plane of the single-sided array type plasma vector thruster and the horizontal plane of the level gauge is measured, so that accurate vector control of the micro-satellite is achieved.
The plasma vector thruster, without moving parts, is very small in both spatial dimension and overall mass, and in one embodiment has dimensions of 100 x 38 (units: mm).
The control model for realizing the angular deflection when the plasma vector thruster is applied to the high-precision attitude control of the micro satellite is specifically explained in the following by combining with fig. 2.
When accurate vector control is realized, the discharge tube combination is assembled on a plane of a satellite model in an array type plasma vector thruster form, the height difference of horizontal plane deflection of a level gauge (8) placed on the plane of the model is measured by using a graduated scale (9), and the deflection angle of the model is determined. Where fig. 2(a) shows the discharge tube being fully ignited and advancing forward with no tilt in the horizontal plane, and fig. 2(b) shows the discharge tube being partially ignited and advancing forward with the horizontal plane of the level being tilted in the direction of no ignition (as shown in the enlarged partial view (c) of fig. 2 (b)), i.e., the angle of the advancing direction is deflected. With the relationship:
wherein R is the radius of the level, L is the horizontal plane inclination change height of the level, and theta is the deflection angle; the corresponding relation between the two-dimensional ignition distribution and the satellite model steering can be determined, and finally, the accurate vector control model of the two-dimensional planar array type plasma vector thruster is established.
In conclusion, the plasma vector thruster disclosed by the invention is small in space size and total mass, can work in a single-pipe mode and a multi-pipe combination mode, can realize thrust of the magnitude of micro-newton to millinewton, can realize accurate vector control by using a multi-pipe combination, and is suitable for being equipped with a micro satellite for high-precision attitude control and relative orbit position maintenance. In addition, the system is single-sided array type, has compact structure, can be installed on one side of the spacecraft, and saves loading space.
The above-mentioned embodiments are further detailed to explain the technical solutions of the present invention, and any modifications and substitutions made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. A plasma vector thruster without moving parts, comprising: the non-motion deflection mechanical part combines a plurality of independent propulsion systems, wherein each independent propulsion system is fixed on the same combined surface, and then vector propulsion is realized by jointly controlling the ignition of each propulsion system, and the advance and the angle deflection of the aircraft are controlled, so that the vector propulsion of the non-motion deflection mechanical part is realized;
the self-contained propulsion system is an inductive-capacitive intercoupled discharge plasma propulsion system comprising: the device comprises a gas source (1), a valve (2), an antenna (3), a grounding electrode (4), a discharge tube (5) and a radio frequency power supply (6);
the gas source (1) is directly connected with each discharge tube (5) and is independently controlled by the valve (2);
the antenna (3) is connected with the radio frequency power supply (6) and is embedded in the middle of the discharge tube (5) to form inductive coupling discharge for exciting plasma and heating gas entering the discharge tube (5) from the gas source (1);
the grounding electrode (4) is sleeved at two ends of the discharge tube (5) and forms inductive-capacitive cross coupling discharge with the antenna (3) for exciting plasma.
2. The plasma vector thruster of claim 1 wherein the plasma vector thruster is free of moving parts and comprises: one end of the gas source (1) is filled with gas, the other end of the gas source is connected with the discharge tube (5), the filled gas is air, nitrogen or inert gas, and the inert gas comprises one of argon, helium and xenon.
3. The plasma vector thruster of claim 1 wherein the plasma vector thruster is free of moving parts and comprises: the number of the discharge tubes (5) is multiple, and the discharge tubes (5) are combined to form different arrays and are arranged on the same surface of the air source.
4. The plasma vector thruster of claim 1 wherein the plasma vector thruster is free of moving parts and comprises: the antenna (3) comprises a capacitive coupling antenna, an inductive coupling antenna and a helical wave antenna, wherein the antenna (3) is made of metal materials with good conductivity, including copper and tungsten.
5. The plasma vector thruster of claim 1 wherein the plasma vector thruster is free of moving parts and comprises: the grounding electrodes (4) are distributed on two sides of the discharge tube (5) and are used for grounding the discharge tube; the grounding electrode (4) is made of a metal material with good conductivity.
6. The plasma vector thruster of claim 1 wherein the plasma vector thruster is free of moving parts and comprises: the frequency of the radio frequency power supply (6) is 13.56 MHz.
7. The plasma vector thruster of claim 1 wherein the plasma vector thruster is free of moving parts and comprises: when accurate vector control is realized, the discharge tube combination is assembled on a plane of a satellite model in an array type plasma vector thruster, the height difference of horizontal plane deflection of a level gauge (8) placed on the plane of the model is measured by using a graduated scale (9), and the deflection angle of the model is determined; with the relationship:
wherein R is the radius of the level, L is the horizontal plane inclination change height of the level, and theta is the deflection angle; the corresponding relation between the two-dimensional ignition distribution and the satellite model steering can be determined, and finally, the accurate vector control model of the two-dimensional planar array type plasma vector thruster is established.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110411851.5A CN113173266B (en) | 2021-04-16 | 2021-04-16 | Plasma vector propeller without moving parts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110411851.5A CN113173266B (en) | 2021-04-16 | 2021-04-16 | Plasma vector propeller without moving parts |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113173266A true CN113173266A (en) | 2021-07-27 |
| CN113173266B CN113173266B (en) | 2024-04-09 |
Family
ID=76923475
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110411851.5A Active CN113173266B (en) | 2021-04-16 | 2021-04-16 | Plasma vector propeller without moving parts |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113173266B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118270253A (en) * | 2024-04-11 | 2024-07-02 | 上海大学 | Integrated global micro-propulsion system and satellite |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6293090B1 (en) * | 1998-07-22 | 2001-09-25 | New England Space Works, Inc. | More efficient RF plasma electric thruster |
| US6565043B1 (en) * | 2001-12-21 | 2003-05-20 | The Boeing Company | Redundant system for satellite inclination control with electric thrusters |
| CN108631047A (en) * | 2018-03-23 | 2018-10-09 | 四川大学 | Blocking type inductant-capacitance coupling helicon plasma antenna |
| CN109386443A (en) * | 2018-09-28 | 2019-02-26 | 四川大学 | Array type capacity Coupled RF Plasma micro-thruster |
| CN110913558A (en) * | 2019-12-10 | 2020-03-24 | 四川大学 | High-efficiency radio frequency plasma discharge device under near space air pressure condition |
| CN111924140A (en) * | 2020-08-03 | 2020-11-13 | 西北工业大学 | Vector propulsion device for controlling rotary motion of space tether system |
| CN111997853A (en) * | 2020-06-05 | 2020-11-27 | 中国科学院合肥物质科学研究院 | Near space environment air suction type radio frequency plasma propeller |
-
2021
- 2021-04-16 CN CN202110411851.5A patent/CN113173266B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6293090B1 (en) * | 1998-07-22 | 2001-09-25 | New England Space Works, Inc. | More efficient RF plasma electric thruster |
| US6565043B1 (en) * | 2001-12-21 | 2003-05-20 | The Boeing Company | Redundant system for satellite inclination control with electric thrusters |
| CN108631047A (en) * | 2018-03-23 | 2018-10-09 | 四川大学 | Blocking type inductant-capacitance coupling helicon plasma antenna |
| CN109386443A (en) * | 2018-09-28 | 2019-02-26 | 四川大学 | Array type capacity Coupled RF Plasma micro-thruster |
| CN110913558A (en) * | 2019-12-10 | 2020-03-24 | 四川大学 | High-efficiency radio frequency plasma discharge device under near space air pressure condition |
| CN111997853A (en) * | 2020-06-05 | 2020-11-27 | 中国科学院合肥物质科学研究院 | Near space environment air suction type radio frequency plasma propeller |
| CN111924140A (en) * | 2020-08-03 | 2020-11-13 | 西北工业大学 | Vector propulsion device for controlling rotary motion of space tether system |
Non-Patent Citations (1)
| Title |
|---|
| 苌磊;段炼;胡馨月;姚建尧;胡建新;胡宁: "澳大利亚国立大学等离子体推进研究", 推进技术, vol. 39, no. 03, pages 481 - 493 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118270253A (en) * | 2024-04-11 | 2024-07-02 | 上海大学 | Integrated global micro-propulsion system and satellite |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113173266B (en) | 2024-04-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Manente et al. | REGULUS: A propulsion platform to boost small satellite missions | |
| Micci | Micropropulsion for small spacecraft | |
| Martinez-Sanchez et al. | Spacecraft electric propulsion-an overview | |
| JP6010132B2 (en) | Hall effect thruster | |
| CN109386443A (en) | Array type capacity Coupled RF Plasma micro-thruster | |
| CN105883008B (en) | Satellite Engine layout method | |
| US11661213B2 (en) | Maneuvering system for earth orbiting satellites with electric thrusters | |
| Rafalskyi et al. | Brief review on plasma propulsion with neutralizer-free systems | |
| WO2021082873A1 (en) | Intelligent control gas suction-type electric propulsion system applicable to multi-flow regimes | |
| US9428285B2 (en) | System and method for managing momentum accumulation | |
| US20200294772A1 (en) | Spacecraft Propulsion Devices and Systems with Microwave Excitation | |
| KR102528033B1 (en) | Efficient stationkeeping design for mixed fuel systems | |
| US20160200458A1 (en) | Converging/diverging magnetic nozzle | |
| Imai et al. | Deflections of dynamic momentum flux and electron diamagnetic thrust in a magnetically steered rf plasma thruster | |
| CN113173266A (en) | Plasma vector propeller without moving part | |
| US20210284361A1 (en) | Systems and methods for attitude control for a satellite | |
| Kolbeck et al. | Micropropulsion based on vacuum arc physics and technology: a review | |
| US20240175428A1 (en) | Plasma propulsion systems and associated systems and methods | |
| Duchemin et al. | Multi-channel hall-effect thrusters: mission applications and architecture trade-offs | |
| US11958636B2 (en) | Dynamically adjusted alignment between payload and spacecraft | |
| US20180037340A1 (en) | Satellite management system comprising a propulsion system having individually selectable motors | |
| Koizumi et al. | Performance of the miniature and low power microwave discharge ion engine mu-1 | |
| Nishiyama et al. | The ion engine system for hayabusa2 | |
| Duchemin et al. | Development of a prototype thrust steering device for hall-effect thrusters | |
| King et al. | Nano-sat scale electric propulsion for attitude control-performance analysis |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |