CN109751214B - micro-Newton-level fast response field emission thruster with continuously adjustable thrust in large range - Google Patents
micro-Newton-level fast response field emission thruster with continuously adjustable thrust in large range Download PDFInfo
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- CN109751214B CN109751214B CN201910228765.3A CN201910228765A CN109751214B CN 109751214 B CN109751214 B CN 109751214B CN 201910228765 A CN201910228765 A CN 201910228765A CN 109751214 B CN109751214 B CN 109751214B
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Abstract
The invention discloses a micro-Newton-level fast response field emission thruster with continuously adjustable thrust in a large range, belongs to the field of aerospace micro-electric propulsion, and aims to solve the problem that the response speed is low when the thrust is changed by adjusting the flow of a traditional needle point type field sounding emission thruster. The scheme of the invention is as follows: the high-voltage electrode group is arranged at the junction of the upper shell and the lower shell, the roots of k emitting electrodes penetrate through the high-voltage electrode group and are immersed into the corresponding propellant storage tanks, and each propellant storage tank is provided with a flow controller; the k emitting electrodes are divided into m groups of arrays, the high-voltage electrode group is formed by stacking m high-voltage electrode plates, and a layer of high-voltage insulating plate is arranged between every two adjacent layers of high-voltage electrode plates to realize insulation; the emitters in the same array are supplied with power from outside by one high-voltage electrode plate, and the emitters in different arrays are supplied with power from outside by different high-voltage electrode plates; the large-range continuous output of the thrust is realized by independently adjusting the voltage levels of the m high-voltage electrode plates.
Description
Technical Field
The invention belongs to the field of aerospace micro-electric propulsion, and relates to a field emission thruster which can realize large-range continuous adjustment of thrust without regulating flow and can quickly respond.
Background
The field emission thruster is a micro-Newton electric thruster which can generate high resolution and low noise, and can be applied to scientific research tasks with extremely high requirements on thrust, such as gravitational wave detection and the like. The device mainly comprises an absorbing electrode, an emitting electrode, a working medium storage tank and a plurality of supporting structures. The working medium generally adopts fluid with low vapor pressure, the working medium is guided to the needle point through the capillary action generated by the micron-level pores in the emitter, the potential of the emitter is higher and generally reaches more than 1000V, the suction electrode is low in potential, and the distance between the suction electrode and the emitter is 1mm-5mm, so that a great electric field can be generated, the working medium at the needle point is ionized and accelerated under the action of the field intensity, and then the working medium leaves the thruster from the suction electrode hole to generate thrust. The field emission thruster can accurately compensate the residual interference force of the spacecraft platform at the micro-Newton level, provides support for high-precision space scientific research tasks such as gravitational wave detection, and realizes non-dragging control.
The basic principle of the conventional field emission thruster is explained with reference to fig. 11, the working medium is guided to the needle tip by the capillary action of the emitter, the emitter is connected with the high potential provided by the high-voltage electrode, the absorber is at the low potential, the working medium on the needle tip cannot be accelerated to generate thrust in the non-electrified state, and the through-flow state of the working medium can be maintained at the needle tip instead of cutting off the flow supply due to the fact that the low vapor pressure of the working medium is limited by the evaporated working medium in the vacuum environment. When the power supply is switched on, a strong electric field is established between the suction electrode and the emitting electrode, and the working medium is ionized and then accelerated out of the thruster along the suction electrode hole to generate thrust.
The traditional needle point type field emission thruster has a single needle point and a plurality of needle points, the multi-needle point type is shown in figure 11, the plurality of needle points are uniformly supplied with power by a high-voltage electrode and are uniformly supplied with air by a storage tank, the multi-needle point type has the same principle except that the number of the needle points is different from that of the single needle point, and if the thrust is required to be changed, the thrust can be increased by changing the voltage and the working medium flow. In a high-precision scientific research task, not only is the thrust required to have high resolution and low noise, but also the response speed of the thrust is required to be high. The traditional needle-tip field emitter only has two methods for adjusting thrust: increasing the voltage and changing the flow. Since the voltage itself is 1000V, the adjustable multiplying power is about 5 times. The flow rate regulation by the flow controller can also be about 10 times, and the regulation multiple of the generated thrust is less than 50 times. However, when the flow is regulated, long time delay is introduced due to the viscosity of the working medium and the small movement speed, and the response speed is slow.
Disclosure of Invention
The invention aims to solve the problem that the response speed of the traditional needle point type field sounding emission thruster is low when the thrust is changed by adjusting the flow, and provides a micro-Newton-level quick response field emission thruster with continuously adjustable thrust in a large range.
The invention relates to a micro-Newton-level fast response field emission thruster with continuously adjustable thrust in a large range, which comprises an upper shell 2, a lower shell 5, a suction electrode 1 and k emitting electrodes 11, and is characterized by further comprising a high-voltage electrode group, k propellant storage tanks 6 and k flow controllers 7, wherein k is a positive integer;
the high-voltage electrode group is arranged at the junction of the upper shell 2 and the lower shell 5, a discharge gap exists between the needle points of the k emitting electrodes 11 and the suction electrode 1, the roots of the k emitting electrodes 11 penetrate through the high-voltage electrode group and are immersed into the corresponding propellant storage tanks 6, and each propellant storage tank 6 is provided with one flow controller 7;
the k emitting electrodes 11 are divided into m groups of arrays, each high-voltage electrode group is formed by stacking m high-voltage electrode plates, m is a positive integer and is 2-k, and a layer of high-voltage insulating plate 8 is arranged between every two adjacent layers of high-voltage electrode plates to realize insulation;
the emitters 11 in the same array are supplied with power from the outside by one high-voltage electrode plate, and the emitters in different arrays are supplied with power from the outside by different high-voltage electrode plates;
the large-range continuous output of the thrust is realized by independently adjusting the voltage levels of the m high-voltage electrode plates.
Preferably, the m sets of arrays comprise the same or different number of emitters 11.
Preferably, m is 2, k emitters 11 are divided into 2 arrays of a first array 10 and a second array 9;
the corresponding high-voltage electrode group is formed by stacking 2 high-voltage electrode plates, namely an upper-layer high-voltage electrode plate 3 and a lower-layer high-voltage electrode plate 4; a layer of high-voltage insulating plate 8 is arranged between the upper-layer high-voltage electrode plate 3 and the lower-layer high-voltage electrode plate 4;
the emitters 11 in the first array 10 realize external power supply through the upper-layer high-voltage electrode plate 3, and the emitters 11 in the second array 9 realize external power supply through the lower-layer high-voltage electrode plate 4;
the first array 10 and the second array 9 are insulated from each other by a high voltage insulating plate 8.
Preferably, the emitters 11 of the first array 10 and the second array 9 are arranged in concentric circles.
Preferably, the upper-layer high-voltage electrode plate 3 comprises an upper-layer conductive circular plate 3-1, the upper-layer conductive circular plate 3-1 is provided with n first array pin fixing columns 3-2 and k-n upper-layer through holes 3-3, the n first array pin fixing columns 3-2 are arranged on the lower surface of the upper-layer conductive circular plate 3-1 and are located on the same circumference, the k-n upper-layer through holes 3-3 are located on the same circumference, and the two circumferences are concentric circles;
the lower-layer high-voltage electrode plate 4 comprises a lower-layer conductive circular plate 4-1, the lower-layer conductive circular plate 4-1 is provided with k-n second array needle fixing columns 4-2 and n lower-layer through holes 4-3, the k-n second array needle fixing columns 4-2 are located on the same circumference, the n lower-layer through holes 4-3 are located on the same circumference, and the two circumferences are concentric circles;
the high-voltage insulating plate 8 comprises an insulating circular plate 8-1, a second array needle fixing insulating column 8-2 corresponding to k-n upper-layer via holes 3-3 is arranged on the upper surface of the insulating circular plate 8-1, and a transition insulating column 8-3 corresponding to n lower-layer via holes 4-3 is arranged on the lower surface of the insulating circular plate 8-1;
the upper layer conductive circular plate 3-1, the lower layer conductive circular plate 4-1 and the insulating circular plate 8-1 are circular plates with the same diameter, and the upper layer conductive circular plate, the lower layer conductive circular plate and the insulating circular plate are stacked together without gaps;
the second array needle fixing insulating column 8-2 of the high-voltage insulating plate 8 is correspondingly inserted into k-n upper-layer through holes 3-3 of the upper-layer high-voltage electrode plate 3, the transition insulating column 8-3 of the high-voltage insulating plate 8 is correspondingly inserted into n lower-layer through holes 4-3 of the lower-layer high-voltage electrode plate 4, n first array needle fixing columns 3-2 of the upper-layer high-voltage electrode plate 3 penetrate through a central through hole of the transition insulating column 8-3 of the high-voltage insulating plate 8, and the extending end parts of the first array needle fixing columns 3-2 are respectively communicated with inlets of corresponding propellant storage tanks 6;
the roots of the n emitting electrodes 11 are inserted into n first array needle fixing columns 3-2, and the corresponding n propellant storage tanks 6 provide one-to-one continuous stable gas source;
the roots of the k-n emitting electrodes 11 are sequentially inserted into a second array needle fixing insulating column 8-2 and a second array needle fixing column 4-2, and a one-to-one continuous stable flow is provided by the corresponding k-n propellant storage tanks 6.
Preferably, the propellant tank 6 stores a low vapor pressure working medium therein.
Preferably, the emitter 11 is made of quartz or metal material and has pores with a diameter of 20 μm to 50 μm.
Preferably, the discharge gap between the tip of the emitter electrode 11 and the suction electrode 1 is 1mm to 5 mm.
The invention has the beneficial effects that: in order to realize the rapid adjustment of the thrust, the emitter needle tip always independently maintains stable working medium flow, and the time delay in the flow adjustment process is reduced. Through the combination with the emitter array, according to the requirement of a task on the thrust adjusting range, the field emission thruster which can realize the continuous adjustment of the thrust in a large range and can quickly respond is designed under the condition of not adjusting the flow.
The arrangement mode of the emitter array is not limited to that a plurality of needle points form an array, in order to realize the wide-range adjustment of the thrust force, the needle points can be arranged as many as possible, and the voltage and the flow control can be realized for each needle point. The large-range continuous adjustment of the thrust is realized by controlling different numbers of needle points to generate the thrust and combining with voltage adjustment, and the thrust adjustment range can be realized between 1 mu N and 100 mu N.
In order to realize high integration and miniaturization of the thruster, an MEMS technology can be further introduced, and the array field emission thruster is obtained by combining the flow control and power supply control design of the invention.
Drawings
FIG. 1 is a schematic structural diagram of a large-range continuously adjustable thrust micro-Newton fast response field emission thruster of the present invention;
FIG. 2 is an emitter array structure of the thruster of the present invention, which is divided into two arrays;
FIG. 3 is a schematic plan view of a getter, wherein FIG. 3(a) is a top view and FIG. 3(b) is a sectional view taken along line A-A of FIG. 3 (a);
FIG. 4 is a schematic perspective view of a combination of two sets of high voltage electrodes and high voltage insulating plates, wherein FIGS. 4(a) and (b) are schematic perspective views from different perspectives;
FIG. 5 is a schematic plan view of the upper high voltage electrode, wherein FIG. 5(a) is a plan view of the upper high voltage electrode, and FIG. 5(B) is a sectional view taken along line B-B of FIG. 5 (a);
FIG. 6 is a schematic perspective view of the upper high voltage electrode, wherein FIGS. 6(a) and (b) are schematic perspective views from different viewing angles;
FIG. 7 is a schematic plan view of the lower high voltage electrode, wherein FIG. 7(a) is a top view of the upper high voltage electrode, and FIG. 7(b) is a cross-sectional view taken along line C-C of FIG. 7 (a);
FIG. 8 is a schematic perspective view of a lower high voltage electrode, wherein FIGS. 8(a) and (b) are schematic perspective views from different viewing angles;
FIG. 9 is a schematic plan view of a high voltage insulation plate, wherein FIG. 9(a) is a plan view of the high voltage insulation plate and FIG. 9(b) is a D-D sectional view of FIG. 9 (a); (ii) a
FIG. 10 is a schematic perspective view of a high pressure insulating panel;
fig. 11 is a schematic structural view of a conventional tip field emission thruster, in which fig. 11(a) is an overall structure and fig. 11(b) is an emitter layout.
Detailed Description
The following detailed description of the embodiments of the present invention will be provided with reference to the drawings and examples, so that how to apply the technical means to solve the technical problems and achieve the technical effects can be fully understood and implemented. It should be noted that, as long as there is no conflict, the embodiments and the features of the embodiments of the present invention may be combined with each other, and the technical solutions formed are within the scope of the present invention.
The invention divides k emitters 11 into m groups of arrays, and the arrays are isolated by high voltage insulation, thereby realizing the independent work of the arrays. All emitter arrays can keep stable flow supply at any time, and the thrust adjustment mainly realizes quick response through electric parameter adjustment. Because the adopted working medium has low steam pressure, a large amount of working medium can not be lost due to evaporation in a low-pressure environment. Meanwhile, the multiple thrust adjustment is realized by controlling the power supply of the emitter array, and the purposes of large-range continuous adjustment of the thrust and quick response are finally achieved by combining the multiple voltage adjustment.
Whether a certain emitter works or not, the emitter 11 is always supplied with a stable working medium.
When the small thrust works, the array with a small number of emitting electrodes is selected to work, the flow is unchanged, and the increase of the thrust is realized by adjusting the voltage.
When the medium thrust works, the array with a large number of emitting electrodes is selected to work, the flow is unchanged, and the increase of the thrust is realized by adjusting the voltage.
When the large thrust works, all the emitter arrays work, firstly, the flow is unchanged, the voltage is adjusted to realize the increase of the thrust, and if the thrust cannot meet the requirement, the flow can be increased through the emitter with the flow adjusting capacity, so that the adjustment of the larger thrust is realized.
And determining an optimal regulation path through the three types of rough regulation experimental data. A higher number of emitters, lower voltage mode is preferred to achieve a certain thrust, reducing the dependence on high voltage.
Through reasonable design, as many emitters as possible have independent adjustment capability, and in extreme cases, each emitter has the capability, so that finer adjustment is realized.
The first embodiment: m is 2, k emitters 11 are divided into 2 arrays, namely a first array 10 and a second array 9;
the corresponding high-voltage electrode group is formed by stacking 2 high-voltage electrode plates, namely an upper-layer high-voltage electrode plate 3 and a lower-layer high-voltage electrode plate 4; a layer of high-voltage insulating plate 8 is arranged between the upper-layer high-voltage electrode plate 3 and the lower-layer high-voltage electrode plate 4;
the emitters 11 in the first array 10 realize external power supply through the upper-layer high-voltage electrode plate 3, and the emitters 11 in the second array 9 realize external power supply through the lower-layer high-voltage electrode plate 4;
the first array 10 and the second array 9 are insulated from each other by a high voltage insulating plate 8.
The emitters 11 of the first array 10 and the second array 9 are arranged in concentric circles.
The upper-layer high-voltage electrode plate 3 comprises an upper-layer conductive circular plate 3-1, the upper-layer conductive circular plate 3-1 is provided with n first array pin fixing columns 3-2 and k-n upper-layer through holes 3-3, the n first array pin fixing columns 3-2 are arranged on the lower surface of the upper-layer conductive circular plate 3-1 and are located on the same circumference, the k-n upper-layer through holes 3-3 are located on the same circumference, and the two circumferences are concentric circles;
the lower-layer high-voltage electrode plate 4 comprises a lower-layer conductive circular plate 4-1, the lower-layer conductive circular plate 4-1 is provided with k-n second array needle fixing columns 4-2 and n lower-layer through holes 4-3, the k-n second array needle fixing columns 4-2 are located on the same circumference, the n lower-layer through holes 4-3 are located on the same circumference, and the two circumferences are concentric circles;
the high-voltage insulating plate 8 comprises an insulating circular plate 8-1, a second array needle fixing insulating column 8-2 corresponding to k-n upper-layer via holes 3-3 is arranged on the upper surface of the insulating circular plate 8-1, and a transition insulating column 8-3 corresponding to n lower-layer via holes 4-3 is arranged on the lower surface of the insulating circular plate 8-1;
the upper layer conductive circular plate 3-1, the lower layer conductive circular plate 4-1 and the insulating circular plate 8-1 are circular plates with the same diameter, and the upper layer conductive circular plate, the lower layer conductive circular plate and the insulating circular plate are stacked together without gaps; the thickness of the insulating disk 8-1 is determined by the insulating material and the maximum operating voltage.
The second array needle fixing insulating column 8-2 of the high-voltage insulating plate 8 is correspondingly inserted into k-n upper-layer through holes 3-3 of the upper-layer high-voltage electrode plate 3, the transition insulating column 8-3 of the high-voltage insulating plate 8 is correspondingly inserted into n lower-layer through holes 4-3 of the lower-layer high-voltage electrode plate 4, n first array needle fixing columns 3-2 of the upper-layer high-voltage electrode plate 3 penetrate through a central through hole of the transition insulating column 8-3 of the high-voltage insulating plate 8, and the extending end parts of the first array needle fixing columns 3-2 are respectively communicated with inlets of corresponding propellant storage tanks 6;
the roots of the n emitting electrodes 11 are inserted into n first array needle fixing columns 3-2, and the corresponding n propellant storage tanks 6 provide one-to-one continuous stable gas source;
the roots of the k-n emitting electrodes 11 are sequentially inserted into a second array needle fixing insulating column 8-2 and a second array needle fixing column 4-2, and a one-to-one continuous stable flow is provided by the corresponding k-n propellant storage tanks 6.
The length of the upper housing 2 is determined by the mission requirements total punch and tip life.
The emitters 11 are made of quartz or metal materials, and have capillary holes with the diameter of 20-50 μm, and the distance between any two emitters 11 in the array is determined by the breakdown voltage.
The discharge gap between the needle point of the emitter 11 and the suction electrode 1 is 1mm-5mm, and is used for generating a strong electric field E, wherein the E is 1000V-10000V and is used for forming a strong ionization working medium of the strong electric field and accelerating plasma. One end of the emitting electrode 11 is immersed into the propellant storage tank 6, and the working medium is conveyed to the needle point through capillary action. In order to improve the response speed of the thrust, the needle tip always maintains stable working medium supply. When the thrust exceeds the maximum thrust which can be generated by the flow, the upper limit of the thrust is expanded by means of increasing the flow.
The propellant storage tank 6 stores low vapor pressure working medium, so that evaporation consumption in a vacuum environment is prevented. The k propellant storage tanks 6 can be integrated with the lower shell 5 or can be separated, and are customized according to requirements. Meanwhile, in order to meet the demand of occasional larger thrust, the purpose of increasing the thrust is achieved by flow adjustment of a part of the flow controller 7, and the remaining flow supply of the emitter tip is kept stable by the flow controller 7 control.
The independent and continuous supply flow of k propellant storage tanks 6 reduces the time delay in the flow regulation process, and the thrust regulation with quick response is realized through voltage regulation.
Second embodiment: and m is k, in the embodiment, each array only comprises one emitter 11, so that independent power supply and working medium supply can be realized for each needle point, and the adjustment range for improving the thrust is maximally limited.
Although the embodiments of the present invention have been described above, the above descriptions are only for the convenience of understanding the present invention, and are not intended to limit the present invention. Any person skilled in the art can combine the MEMS technology to realize the miniaturization and miniaturization of the thruster without departing from the spirit and scope of the present disclosure, and can make any modification and change in the form and details of implementation to realize the thruster with fast thrust response and continuously adjustable in a wide range. The scope of the present invention is defined by the appended claims.
Claims (6)
1. A micro-Newton-level fast response field emission thruster with continuously adjustable thrust in a large range comprises an upper shell (2), a lower shell (5), a suction electrode (1) and k emitting electrodes (11), and is characterized by further comprising a high-voltage electrode group, k propellant storage tanks (6) and k flow controllers (7), wherein k is a positive integer;
the high-voltage electrode group is arranged at the junction of the upper outer shell (2) and the lower outer shell (5), a discharge gap exists between the needle points of the k emitting electrodes (11) and the suction electrode (1), the roots of the k emitting electrodes (11) penetrate through the high-voltage electrode group and are immersed into the corresponding propellant storage tanks (6), and each propellant storage tank (6) is provided with a flow controller (7);
the k emitting electrodes (11) are divided into 2 groups of arrays, namely a first array (10) and a second array (9);
the corresponding high-voltage electrode group is formed by stacking 2 high-voltage electrode plates, namely an upper-layer high-voltage electrode plate (3) and a lower-layer high-voltage electrode plate (4); a high-voltage insulating plate (8) is arranged between the upper-layer high-voltage electrode plate (3) and the lower-layer high-voltage electrode plate (4);
the emitters (11) in the first array (10) realize external power supply through the upper-layer high-voltage electrode plate (3), and the emitters (11) in the second array (9) realize external power supply through the lower-layer high-voltage electrode plate (4);
the first array (10) and the second array (9) are mutually insulated through a high-voltage insulating plate (8);
the upper-layer high-voltage electrode plate (3) comprises an upper-layer conductive circular plate (3-1), the upper-layer conductive circular plate (3-1) is provided with n first array needle fixing columns (3-2) and k-n upper-layer through holes (3-3), the n first array needle fixing columns (3-2) are arranged on the lower surface of the upper-layer conductive circular plate (3-1) and are positioned on the same circumference, the k-n upper-layer through holes (3-3) are positioned on the same circumference, and the two circumferences are concentric circles;
the lower-layer high-voltage electrode plate (4) comprises a lower-layer conductive circular plate (4-1), the lower-layer conductive circular plate (4-1) is provided with k-n second array needle fixing columns (4-2) and n lower-layer through holes (4-3), the k-n second array needle fixing columns (4-2) are located on the same circumference, the n lower-layer through holes (4-3) are located on the same circumference, and the two circumferences are concentric circles;
the high-voltage insulating plate (8) comprises an insulating circular plate (8-1), a second array needle fixing insulating column (8-2) corresponding to k-n upper-layer via holes (3-3) is arranged on the upper surface of the insulating circular plate (8-1), and a transition insulating column (8-3) corresponding to n lower-layer via holes (4-3) is arranged on the lower surface of the insulating circular plate (8-1);
the upper layer conductive circular plate (3-1), the lower layer conductive circular plate (4-1) and the insulating circular plate (8-1) are circular plates with the same diameter, and the upper layer conductive circular plate, the lower layer conductive circular plate and the insulating circular plate are stacked together without gaps;
the second array needle fixing insulating columns (8-2) of the high-voltage insulating plate (8) are correspondingly inserted into k-n upper-layer through holes (3-3) of the upper-layer high-voltage electrode plate (3), the transition insulating columns (8-3) of the high-voltage insulating plate (8) are correspondingly inserted into n lower-layer through holes (4-3) of the lower-layer high-voltage electrode plate (4), n first array needle fixing columns (3-2) of the upper-layer high-voltage electrode plate (3) penetrate through central through holes of the transition insulating columns (8-3) of the high-voltage insulating plate (8), and the extending end parts of the first array needle fixing columns (3-2) are respectively communicated with inlets of corresponding propellant storage tanks (6);
the roots of the n emitting electrodes (11) are inserted into n first array needle fixing columns (3-2), and a one-to-one continuous stable gas source is provided by the corresponding n propellant storage tanks (6);
the roots of the k-n emitting electrodes (11) are sequentially inserted into a second array needle fixing insulating column (8-2) and a second array needle fixing column (4-2), and a one-to-one continuous stable flow is provided by the corresponding k-n propellant storage tanks (6);
the large-range continuous output of the thrust is realized by independently adjusting the voltage levels of the 2 high-voltage electrode plates.
2. The micro-Newton fast response field emission thruster with continuously adjustable wide thrust range according to claim 1, wherein the number of the emitting electrodes (11) included in the 2 arrays is the same or different.
3. The micro-Newton fast response field emission thruster with the thrust force being continuously adjustable in a large range according to claim 1, wherein the emitting electrodes (11) of the first array (10) and the second array (9) are arranged in concentric circles.
4. The micro-Newton-scale rapid response field emission thruster with the thrust continuously adjustable in a wide range according to claim 1, wherein a working medium with low vapor pressure is stored in the propellant storage tank (6).
5. The micro-Newton fast response field emission thruster with continuously adjustable wide thrust range according to claim 1, wherein the emitter (11) is made of quartz or metal material and has capillary holes with diameter of 20 μm-50 μm.
6. The micro-Newton fast response field emission thruster with the thrust continuously adjustable in a large range according to claim 1, wherein a discharge gap between the needle point of the emitter (11) and the suction electrode (1) is 1mm-5 mm.
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| CN112780514B (en) * | 2021-02-22 | 2022-03-18 | 北京理工大学 | Ionic liquid electric spraying thruster for electric field control liquid supply |
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| US8453426B2 (en) * | 2009-04-06 | 2013-06-04 | Raytheon Company | Current controlled field emission thruster |
| CN105156290A (en) * | 2015-07-13 | 2015-12-16 | 兰州空间技术物理研究所 | Novel three-annulus mixed electric thruster |
| CN105402099B (en) * | 2015-12-07 | 2018-08-03 | 上海空间推进研究所 | A kind of miniature Flied emission electric thruster of pin type porous material emitter array |
| CN108317062A (en) * | 2017-12-22 | 2018-07-24 | 兰州空间技术物理研究所 | A kind of mixing thruster |
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