CN110469473B - Side feed supply device for pulse plasma electric thruster - Google Patents
Side feed supply device for pulse plasma electric thruster Download PDFInfo
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- CN110469473B CN110469473B CN201910702764.8A CN201910702764A CN110469473B CN 110469473 B CN110469473 B CN 110469473B CN 201910702764 A CN201910702764 A CN 201910702764A CN 110469473 B CN110469473 B CN 110469473B
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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
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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
- F03H1/0093—Electro-thermal plasma thrusters, i.e. thrusters heating the particles in a plasma
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Abstract
The invention discloses a side feed supply device for a pulse plasma electric thruster, which comprises two sets of supply components with symmetrical structures, wherein the supply components are fixedly connected to a bottom plate of the electric thruster and comprise a first supply support, a first tension spring, a first push rod, a first supply baffle, a first solid propellant, a second supply support, a second tension spring, a second push rod, a second supply baffle and a second solid propellant, opposite ends of the first solid propellant and the second solid propellant are of inclined surface structures and form a V-shaped discharge groove, an opening of the V-shaped discharge groove faces to the tail end of an electrode plate, and a cone limiting table is arranged on the inner side of an anode plate and at the included angle of the V-shaped discharge groove. The invention can feed two solid propellants, and the ablation end faces of the propellants positioned in the discharge chamber form a V shape, so that the area swept by a discharge arc can be increased, and the ablation quality of a single pulse under the same condition can be increased.
Description
Technical Field
The invention belongs to the technical field of spacecraft propulsion, relates to a working medium supply device for space electric propulsion, and particularly relates to a side-feed supply device for a pulse plasma electric propeller.
Background
In recent years, with the development of emerging space exploration technologies such as small satellites, planetary detectors, deep space exploration and interstellar navigation, the demand of human beings on space exploration is more and more urgent, space exploration activities are more and more, and the types and the number of space satellites are increased and advanced. This requires lighter weight, smaller size, and higher efficiency propulsion systems on spacecraft, and thus development of higher thrust, compact, less propellant, and lower cost propulsion technologies is not desirable. The conventional chemical thrusters have not been able to satisfy the demands of micro-satellites for power systems due to the large fuel mass, and thus scientists have been vigorously developing electric thrusters capable of generating smaller thrust. Electric propulsion is a novel advanced propulsion mode and has the specific impulse performance far higher than that of the traditional chemical propulsion. The application of electric propulsion is one of the most effective ways to reduce the mass of the spacecraft, improve the effective load capacity and prolong the on-orbit service life of the spacecraft.
Among the electric propulsion devices, the pulsed plasma thruster is the first electric propulsion device successfully applied to the space flight mission. The electric propulsion device has the advantages of stable working medium, easy storage, safety, reliability, no leakage, no need of a storage tank and a pipeline, and convenience for integration with a spacecraft, and has the characteristics of small average power, convenient and flexible thrust control, wide magnitude range and the like, and is suitable for propulsion tasks of various miniature spacecrafts such as attitude control, orbit transfer, position maintenance, resistance compensation, accurate formation flight and the like, so the electric propulsion device becomes a key point for developing advanced space power technology and application thereof in various countries. However, poor thrust performance has been a key issue limiting the development and space utilization of pulsed plasma electric propulsion. How to develop a high-performance solid ablation type pulsed plasma electric propulsion device has become an important development direction of the current international electric propulsion technology.
The manner in which the propellant is supplied affects thrust performance. At present, pulsed plasma electric propulsion generally adopts a propellant configuration with a rectangular end face and a feeding mode of tail feeding, however, the swept area of a discharge arc is small in the mode, and the impulse is restricted to be increased. Therefore, the simple and effective working medium supply device capable of increasing the ablation amount of the working medium and further providing large thrust and total thrust is designed, and the device has very important significance for realizing development and space application of high-performance pulse plasma electric propulsion.
Disclosure of Invention
The invention solves the problems that: in order to overcome the defects of the prior testing technology, the invention designs the side feed supply device for the pulse plasma electric thruster, and the side feed supply device increases the discharge ablation area and feeds more ablation mass to a discharge chamber by adopting the configuration of the discharge chamber with two solid propellants supplied laterally, thereby improving the thrust and the total impact.
The technical solution of the invention is as follows:
a side-feed supply device for a pulse plasma electric thruster comprises two sets of supply components with symmetrical structures, wherein the supply components are fixedly connected to a bottom plate of the electric thruster and comprise a first supply bracket, a first tension spring, a first push rod, a first supply baffle plate, a first solid propellant, a second supply bracket, a second tension spring, a second push rod, a second supply baffle plate and a second solid propellant,
the first supply bracket is a rectangular block, and the upper part of the first supply bracket is provided with a cavity corresponding to the shape structure of the first solid propellant for placing the first solid propellant; the first supply baffle is fixedly connected to the outer side of the cavity of the first supply bracket, one end of a first tension spring is fixed on the first supply baffle, and the other end of the first tension spring is embedded in a first clamping groove at one end of a first push rod; one end of the first push rod penetrates into the cavity of the first supply bracket and is in contact with the end face of the first solid propellant, and the other end of the first push rod penetrates into the first tension spring and is fixed with the first tension spring through the first clamping groove;
the second supply bracket is a rectangular block, and the upper part of the second supply bracket is provided with a cavity corresponding to the shape structure of the second solid propellant for placing the second solid propellant; the second supply baffle is fixedly connected to the outer side of the cavity of the second supply bracket, one end of a second tension spring is fixed on the second supply baffle, and the other end of the second tension spring is embedded into a second clamping groove on one end of a second push rod; one end of the second push rod penetrates into the cavity of the second supply support and is in contact with the end face of the second solid propellant, and the other end of the second push rod penetrates into the second tension spring and is fixed with the second tension spring through the second clamping groove;
the opposite ends of the first solid propellant and the second solid propellant are in an inclined surface structure, the first solid propellant and the second solid propellant form a V-shaped discharge groove, the opening of the V-shaped discharge groove faces to the tail end of the electrode plate, and a cone limiting table is arranged on the inner side of the anode plate and at the included angle of the V-shaped discharge groove; the ceramic plates are positioned among the anode plate, the cathode plate, the first supply bracket, the second supply bracket, the first solid propellant and the second solid propellant; propellant amount m consumed by single pulse discharge work of propellerbitDischarge energy E with propeller0The relationship between the ablation area A is as follows:
the first solid propellant is in clearance fit with the cavity, and the fit clearance is 0.5mm-1.5 mm.
The second solid propellant is in clearance fit with the cavity, and the fit clearance is 0.5-1.5 mm.
The height of the cone limiting table is 1mm-3mm, and the conical angle is 20-50 degrees.
The included angle between the first solid propellant and the second solid propellant is alpha, the width and the height of the first solid propellant and the second solid propellant are w and h respectively, and the ablation area is as follows: and A is 2 h.w/cos alpha.
The vertical distance between the outer edge of the diameter of the spark plug and the ablation inclined plane of the propellant is 0.5 mm-2 mm.
The energy storage capacitor is of a cylindrical structure, the upper end of the cylindrical structure comprises a cylindrical end and an annular end, and the lower end of the cylindrical structure is fixed on the bottom plate.
The anode plate and the cathode plate are both in a tail end narrow-shrinkage structure, an opening angle is formed between the anode plate and the cathode plate, the range of the opening angle is 5-10 degrees, and the width of the non-narrow-shrinkage part of the anode plate and the cathode plate is larger than the maximum gap between the first solid propellant and the second solid propellant.
The annular ends of the anode plate and the energy storage capacitor and the cylindrical ends of the cathode plate and the energy storage capacitor are fixedly connected through fasteners, and the tail ends of the anode plate and the cathode plate are discharge areas and are positioned on the upper side and the lower side of the V-shaped discharge groove.
And a spark plug is arranged on the negative plate, and the spark plug is ignited to trigger the energy storage capacitor to discharge in the V-shaped discharge groove, so that a V-shaped surface between the first solid propellant and the second solid propellant is ablated.
The invention has the beneficial effects that:
(1) the invention provides a supply mode of a lateral feeding V-shaped propellant ablation end face, and the structure has the advantages that two solid propellants can be fed, and the propellant ablation end face positioned in a discharge chamber forms a V shape, so that the area swept by a discharge arc can be increased, and the ablation quality of a single pulse under the same condition can be increased; secondly, in the initial stage of ignition discharge ablation, formed ablation gas can be concentrated between propellants on two sides, and the propellants on the two sides form a V-shaped discharge cavity, so that the electrothermal effect of the electric thruster is improved simultaneously, and the thrust and the total impulse of the thruster are further improved;
(2) the invention adopts a conical limiting structure. The device is fixed on the surface of the anode of a discharge chamber of a thruster, so that on one hand, the opposite positions of the propellant during lateral supply can be fixed, and the limiting function after the propellant is consumed by multiple times of pulse discharge ablation is realized; on the other hand, the conical limiting structure cannot shield the bottom of the discharge ablation end face of the propellant, so that the uniformity of discharge arc ablation is ensured, and the supply of the propellant is ensured;
(3) compared with the existing scheme at home and abroad, the pulse discharge ablation area is increased, the supplied quality thrust and thrust performance are improved, and the structure is simple, so that the leap-over performance is improved on the reliability index, and the realization is easy.
Drawings
FIG. 1 is a front view of the structure of the present invention;
FIG. 2 is a top view of the structure of the present invention;
FIG. 3 is a top view of the feed assembly portion of the present invention;
FIG. 4 is a schematic view of the V-shaped portion of the present invention;
fig. 5 is a left side view of the structure of the present invention.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
Aiming at the defects in the prior art, the invention provides a discharge chamber structure adopting two solid propellants to supply laterally. Aiming at the working requirement of the structure, the side feed supply device which is simple in structure, reliable and easy to realize is designed. The device increases the discharge ablation area, can feed more ablation quality to the discharge chamber, and then promotes thrust and total towards.
The invention aims to provide a working medium supply device for space electric propulsion on-orbit propulsion, which has simple structure and large discharge ablation area and can meet the requirements of high power and large thrust.
One of the essential reasons for the low performance of solid ablation type pulsed plasma electric propulsion is the low supply and utilization of propellant during the pulse period. In order to solve the technical problems and achieve the purpose of the invention, the invention provides a novel working medium shape and a design scheme of a supply device thereof, the scheme realizes the stable and reliable directional pushing action of a tension spring and the stable and reliable lateral movement of propellant, and can effectively improve the quality of propellant supplied into a discharge chamber by ablation, so that more plasmas can be formed by ionization under high power, and finally the performance of a thruster is improved.
The specific scheme is as follows: a side feed supply device for a pulse plasma electric thruster is disclosed, as shown in figure 2, comprising two sets of supply components 18 with symmetrical structures, wherein the supply components 18 are fixedly connected on a bottom plate 1 of the electric thruster, as shown in figures 1 and 3, the supply components 18 comprise a first supply bracket 2, a first tension spring 6, a first push rod 4, a first supply baffle plate 3, a first solid propellant 7, a second supply bracket 17, a second tension spring 14, a second push rod 15, a second supply baffle plate 16 and a second solid propellant 8,
the first supply bracket 2 is a rectangular block, a cavity corresponding to the shape structure of the first solid propellant 7 is formed in the upper part of the first supply bracket 2 and used for placing the first solid propellant 7, and the first solid propellant 7 is in clearance fit with the cavity, and the fit clearance is 0.5-1.5 mm; the first supply baffle 3 is fixedly connected to the outer side of the cavity of the first supply bracket 2, one end of a first tension spring 6 is fixed on the first supply baffle 3, and the other end of the first tension spring is embedded into a first clamping groove 5 on one end of a first push rod 4; one end of the first push rod 4 penetrates into the cavity of the first supply bracket 2 and is in contact with the end face of the solid propellant, and the other end of the first push rod penetrates into the first tension spring 6 and is fixed with the first tension spring 6 through the first clamping groove 5.
The second supply bracket 17 is a rectangular block, a cavity corresponding to the shape structure of the second solid propellant 8 is formed in the upper part of the second supply bracket 17 and used for placing the second solid propellant 8, the second solid propellant 8 is in clearance fit with the cavity, and the fit clearance is 0.5-1.5 mm; the second supply baffle 16 is fixedly connected to the outer side of the cavity of the second supply bracket 17, one end of a second tension spring 14 is fixed on the second supply baffle 16, and the other end is embedded into a second clamping groove 20 on one end of the second push rod 15; one end of the second push rod 15 penetrates into the cavity of the second supply bracket 17 and contacts with the end face of the solid propellant, and the other end penetrates into the second tension spring 14 and is fixed with the second tension spring 14 through the second clamping groove 20.
As shown in fig. 4, the opposite ends of the first solid propellant 7 and the second solid propellant 8 are in an inclined plane structure, the two form a V-shaped discharge groove, the opening of the V-shaped discharge groove faces the tail end of the electrode plate, a limiting table 10 is arranged on the inner side of the anode plate and at the included angle of the V-shaped discharge groove, the limiting table 10 is a cone, the height of the cone is 1mm-3mm, and the cone angle is 20-50 degrees; the ceramic sheets 13 are positioned between the anode plate, the cathode plate, the first supply bracket 2, the second supply bracket 17 and the first solid propellant 7 and the second solid propellant 8, and prevent the surface discharge ablation of the first solid propellant 7 and the second solid propellant 8 contacted with the ceramic sheets;
at a certain discharge frequency, the magnitude of the thruster average thrust depends on the element impulse. And the element impulse is the pulse ablation mass mbitThe product of the speed of movement V. Wherein the propellant pulse ablates a mass mbitI.e. the amount of propellant consumed by a single pulse discharge operation of the thruster, and the discharge energy E of the thruster0The relationship between ablation area a can be evaluated by the following formula:
wherein
Is related to the capacitance of the energy storage capacitor and the initial discharge voltage. Therefore, under the normal working condition of the propeller, when the discharge energy is constant, the ablation quality of the propellant pulse is mainly determined by the ablation area A.
Assuming that the angle between the first solid propellant 7 and the second solid propellant 8 is α and the width and height of the first solid propellant 7 and the second solid propellant 8 are w and h, respectively, the ablation area can be expressed as:
A＝2h·w/cosα
the vertical distance between the outer edge of the diameter of the spark plug and the ablation inclined plane of the propellant is 0.5 mm-2 mm. Therefore, under the condition of the distance limitation, when the included angle alpha between the first solid propellant 7 and the second solid propellant 8 is increased from zero degree, namely gradually changed into a V shape, the ablation area A and the ablation mass m of the propellant pulse are increasedbitTherefore, the V-shaped discharge groove configuration formed by the first solid propellant 7 and the second solid propellant 8 improves the unit impulse and the thrust performance of the propeller.
The first and second supply brackets 2 and 17 are fixed to the base plate 1.
The energy storage capacitor 19 is of a cylindrical structure, the upper end of the cylindrical structure comprises a cylindrical end and an annular end, and the lower end of the cylindrical structure is fixed on the bottom plate 1;
as shown in fig. 5, the anode plate and the cathode plate are both in a narrow-end-shrinking structure, an opening angle exists between the anode plate and the cathode plate, the opening angle ranges from 5 degrees to 10 degrees, and the width of the non-narrowed part of the anode plate and the cathode plate is larger than the maximum gap between the first solid propellant 7 and the second solid propellant 8.
The annular ends of the anode plate and the energy storage capacitor 19 and the cylindrical ends of the cathode plate and the energy storage capacitor 19 are fixedly connected through fasteners 12, the tail ends of the anode plate and the cathode plate are discharge areas and are positioned at the upper side and the lower side of the V-shaped discharge groove, spark plugs are arranged on the cathode plate, the spark plugs are ignited to trigger the energy storage capacitor 19 to discharge in the V-shaped discharge groove, and then the V-shaped surface between the first solid propellant 7 and the second solid propellant 8 is ablated.
The energy storage capacitor 19 is fixed on the bottom plate 1 and is connected with the anode 9 and the cathode 11 through a fastener 12.
The spark plug 21 is fixed to the cathode 11 by screw-fastening.
The first solid propellant 7 and the second solid propellant 8 are in an inverted V shape on the end surface between the anode 9 and the cathode 11 and are clamped by a limit table 10.
The limiting table 10 is of a conical structure and is fixed on the anode 9.
The above components are specifically described as follows:
the first solid propellant 7 and the second solid propellant 8 are made of polytetrafluoroethylene. The V-shaped angle formed by the two propellants is 40-50 degrees.
The V-shaped end faces formed by the anode 9, the cathode 11, the spark plug 21 and the first solid propellant 7 and the second solid propellant 8 form a discharge ablation cavity of the device.
The first push rod 4, the first supply baffle 3, the second push rod 15 and the second supply baffle 16 are made of stainless steel, and the bottom plate 1 is made of epoxy resin. Polyimide is used as the material of the first supply holder 2 and the second supply holder 17.
The anode 9 (including the limit table 10), the cathode 11 and the fastener 12 are made of chromium zirconium copper with good conductivity, high hardness and arc ablation resistance.
The spark plug 21 is of a coaxial semiconductor configuration with breakdown voltage lower than 1000V, and a central electrode is made of nickel-manganese alloy and has the diameter of 6-9 mm; the housing is made of high temperature alloy steel; the insulator material is high-alumina porcelain; the width of the semiconductor layer is 0.5-0.8 mm. The first tension spring 6 and the second tension spring 14 are made of spring steel.
In consideration of the high-voltage discharge environment and the thermal effect, the ceramic sheet 13 of the present invention is made of an alumina ceramic material. The ceramic plates 13 act to confine the discharge to the V-shaped region formed by the anode 9 and cathode 11, the spark plug 21 and the first and second solid propellants 7, 8.
The energy storage capacitor 19 is a metallized polypropylene film capacitor, the capacitance value is between 20 muF and 80 muF, and the applied voltage range is between 1kv and 2 kv.
The whole working process of the electric propulsion side feed supply device is as follows:
the stretched first tension spring 6 and the stretched second tension spring 14 respectively generate opposite thrust effects on the first solid propellant 7 and the second solid propellant 8, and under the action of the limiting table 10, the first solid propellant 7 and the second solid propellant 8 are respectively fixed in the first supply bracket 2 and the second supply bracket 17.
During operation, the energy storage capacitor 19 is charged to a corresponding voltage; when the electric propulsion device needs to work by discharging, the spark plug 21 is ignited, namely, micro-discharge is generated between the anode 9 and the cathode 11 and between the V-shaped surfaces of the first solid propellant 7 and the second solid propellant 8; electrons generated by micro discharge impact the surface of the propellant under the action of electric field force, the surface of the propellant is further disintegrated and dissociated to generate more electrons, and the electrons are accelerated and collided with the V-shaped surfaces of the first solid propellant 7 and the second solid propellant 8; the V-shaped surfaces frequently collide with each other and more charged particle areas are gradually formed between the two poles, and finally the energy storage capacitor 19 forms high-current arc discharge along the V-shaped surfaces of the propellant at the anode 9 and the cathode 11; the high-temperature electric arc caused by the electric discharge then ablates the V-shaped surfaces between the first solid propellant 7 and the second solid propellant 8; after a V-shaped surface thin layer between a first solid propellant 7 and a second solid propellant 8 is ablated, the two solid propellants are respectively pushed by a first tension spring 6 and a second tension spring 14, and are oppositely moved to a limiting table 10 and then clamped; with the multiple pulse discharges, the first solid propellant 7 and the second solid propellant 8 are continuously ablated, and the first tension spring 6 and the second tension spring 14 are correspondingly pushed, so that the function of stable lateral feeding of the two solid propellants by the feeding assembly is realized.
The innovation of the embodiment is the capability of realizing the lateral feeding of the two solid propellants, and a V-shaped discharge cavity is formed in the surface areas of the two propellants during discharging, so that the electrothermal effect of the formed ablation gas under the condition of large ablation supply of the propellants is effectively improved. On one hand, the area swept by the discharge is increased, and the pulse ablation supply quality is increased; on the other hand, in the electric propulsion discharge ablation working process, gas formed by ablation is gathered in the V-shaped discharge cavity between the two solid propellants, so that the pressure of the ablation gas is improved to a certain extent, the electric heating acceleration effect of electric propulsion is enhanced, and the thrust and the total thrust of the thruster are further improved.
The above-mentioned embodiments only express the design idea of the improvement and the corresponding embodiments of the present invention, but not be construed as limiting the scope of the present invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention. Therefore, the protection scope of the present invention should be subject to the appended claims, and the present invention is not described in detail in the details known to those skilled in the art.
Claims (10)
1. A side-fed feeding arrangement for a pulsed plasma electric thruster, characterised by: comprises two sets of supply components (18) with symmetrical structures, wherein the supply components (18) are fixedly connected on a bottom plate (1) of the electric propeller, the supply components (18) comprise a first supply bracket (2), a first tension spring (6), a first push rod (4), a first supply baffle plate (3), a first solid propellant (7), a second supply bracket (17), a second tension spring (14), a second push rod (15), a second supply baffle plate (16) and a second solid propellant (8),
the first supply bracket (2) is a rectangular block, and a cavity corresponding to the shape structure of the first solid propellant (7) is formed in the upper part of the first supply bracket (2) and used for placing the first solid propellant (7); the first supply baffle (3) is fixedly connected to the outer side of the cavity of the first supply bracket (2), one end of a first tension spring (6) is fixed on the first supply baffle (3), and the other end of the first tension spring is embedded into a first clamping groove (5) at one end of a first push rod (4); one end of the first push rod (4) penetrates into the cavity of the first supply bracket (2) and is contacted with the end face of the first solid propellant (7), and the other end of the first push rod penetrates into the first tension spring (6) and is fixed with the first tension spring (6) through the first clamping groove (5);
the second supply bracket (17) is a rectangular block, and the upper part of the second supply bracket (17) is provided with a cavity corresponding to the shape structure of the second solid propellant (8) for placing the second solid propellant (8); a second supply baffle (16) is fixedly connected to the outer side of the cavity of the second supply bracket (17), one end of a second tension spring (14) is fixed on the second supply baffle (16), and the other end of the second tension spring is embedded into a second clamping groove (20) at one end of a second push rod (15); one end of a second push rod (15) penetrates through a cavity of the second supply bracket (17) and is in contact with the end face of the second solid propellant (8), and the other end of the second push rod penetrates into a second tension spring (14) and is fixed with the second tension spring (14) through a second clamping groove (20);
the opposite ends of the first solid propellant (7) and the second solid propellant (8) are in inclined surface structures, the first solid propellant and the second solid propellant form a V-shaped discharge groove, and the opening of the V-shaped discharge groove faces to the electrodeA cone limiting table (10) is arranged at the tail end of the plate, on the inner side of the anode plate and at the included angle of the V-shaped discharge groove; the ceramic plates (13) are positioned among the anode plate, the cathode plate, the first supply bracket (2), the second supply bracket (17), the first solid propellant (7) and the second solid propellant (8); propellant amount m consumed by single pulse discharge work of propellerbitDischarge energy E with propeller0The relationship between the ablation area A is as follows:
2. a side-fed feeding arrangement for a pulsed plasma electric thruster as claimed in claim 1 wherein: the first solid propellant (7) is in clearance fit with the cavity, and the fit clearance is 0.5mm-1.5 mm.
3. A side-fed feeding arrangement for a pulsed plasma electric thruster as claimed in claim 1 wherein: the second solid propellant (8) is in clearance fit with the cavity, and the fit clearance is 0.5-1.5 mm.
4. A side-fed feeding arrangement for a pulsed plasma electric thruster as claimed in claim 1 wherein: the height of the cone limiting table (10) is 1mm-3mm, and the conical angle is 20-50 degrees.
5. A side-fed feeding arrangement for a pulsed plasma electric thruster as claimed in claim 1 wherein: the included angle between the first solid propellant (7) and the second solid propellant (8) is alpha, the width and the height of the first solid propellant (7) and the second solid propellant (8) are w and h respectively, and the ablation area is as follows: and A is 2 h.w/cos alpha.
6. A side-fed feeding arrangement for a pulsed plasma electric thruster as claimed in claim 1 wherein: the vertical distance between the outer edge of the diameter of the spark plug and the ablation inclined plane of the propellant is 0.5 mm-2 mm.
7. A side-fed feeding arrangement for a pulsed plasma electric thruster as claimed in claim 1 wherein: still include energy storage capacitor (19), energy storage capacitor (19) are the cylindricality structure, and cylindricality structure upper end includes cylindricality end and annular end, and the cylindricality structure lower extreme is fixed on bottom plate (1).
8. The side feed supply device for the pulsed plasma electric thruster, according to claim 1, characterized in that the anode plate and the cathode plate are both of a narrow end type structure, an opening angle exists between the anode plate and the cathode plate, the opening angle is in the range of 5 degrees to 10 degrees, and the width of the non-narrow part of the anode plate and the cathode plate is larger than the maximum gap between the first solid propellant (7) and the second solid propellant (8).
9. A side-fed feeding arrangement for a pulsed plasma electric thruster as claimed in claim 7, wherein: the annular ends of the anode plate and the energy storage capacitor (19) and the cylindrical ends of the cathode plate and the energy storage capacitor (19) are fixedly connected through a fastener (12), and the tail ends of the anode plate and the cathode plate are discharge areas and are positioned on the upper side and the lower side of the V-shaped discharge groove.
10. A side-fed feeding arrangement for a pulsed plasma electric thruster as claimed in claim 9, wherein: and a spark plug is arranged on the cathode plate, and the spark plug is ignited to trigger the energy storage capacitor (19) to discharge in the V-shaped discharge groove, so that the V-shaped surface between the first solid propellant (7) and the second solid propellant (8) is ablated.
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| CN111076937B (en) * | 2019-12-09 | 2021-03-05 | 北京理工大学 | System and method for testing ablation quality of energetic working medium pulse plasma thruster |
| CN112360710B (en) * | 2020-10-23 | 2021-09-07 | 北京精密机电控制设备研究所 | Working medium feeding device for coaxial electrothermal plasma thruster |
| CN113623159A (en) * | 2021-09-18 | 2021-11-09 | 西安交通大学 | Propellant automatic supply device of coaxial vacuum arc propeller |
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| US6153976A (en) * | 1999-02-04 | 2000-11-28 | The United States Of America As Represented By The Secretary Of The Air Force | Pulsed plasma thruster with electric switch enabling use of a solid electrically conductive propellant |
| CN101260873B (en) * | 2008-01-10 | 2010-12-15 | 上海交通大学 | Pulsed plasma thruster with ceramic air spout electrode |
| WO2011079138A2 (en) * | 2009-12-21 | 2011-06-30 | California Institute Of Technology | Microfluidic electrospray thruster |
| US8875485B2 (en) * | 2010-04-06 | 2014-11-04 | The George Washington University | Micro-cathode thruster and a method of increasing thrust output for a micro-cathode thruster |
| CN106523313B (en) * | 2016-12-07 | 2019-03-15 | 兰州空间技术物理研究所 | A kind of micropulse plasma thruster |
| CN107654347B (en) * | 2017-08-29 | 2019-06-18 | 北京精密机电控制设备研究所 | A kind of high-performance solid ablative-type protective coating pulsed plasma electric propulsion device |
| CN109578234B (en) * | 2018-12-10 | 2020-03-17 | 兰州空间技术物理研究所 | Working medium supply assembly of pulse plasma thruster |
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