CN110469473A - A kind of side feedback feedway for pulsed plasma electric propulsion device - Google Patents
A kind of side feedback feedway for pulsed plasma electric propulsion device Download PDFInfo
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- CN110469473A CN110469473A CN201910702764.8A CN201910702764A CN110469473A CN 110469473 A CN110469473 A CN 110469473A CN 201910702764 A CN201910702764 A CN 201910702764A CN 110469473 A CN110469473 A CN 110469473A
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- solid propellant
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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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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
The invention discloses a kind of sides for pulsed plasma electric propulsion device to present feedway, including the symmetrical feeding assembly of two nested structures, feeding assembly is fixedly connected on the bottom plate of electric propulsion device, feeding assembly includes the first supply bracket, first tension spring, first push rod, first supply washer, first solid propellant and the second supply bracket, second tension spring, second push rod, second supply washer and the second solid propellant, first solid propellant, the opposite end of second solid propellant is bevel structure, the two constitutes V-type discharge groove, the opening of V-type discharge groove is towards the end of electrode plate, inside in anode plate and the angle positioned at V-type discharge groove, it is provided with cone limiting stand.The present invention can feed two pieces of solid propellants, and the propellant ablation end face for being located at arc chamber constitutes V-type, and so as to increase the inswept area of electrical discharge arc, the ablation quality of single pulse also be will increase under the same conditions.
Description
Technical field
The invention belongs to spacecraft propulsion technical fields, are related to a kind of working substance supply device for space electric propulsion, special
It is not related to a kind of side feedback feedway for pulsed plasma electric propulsion device.
Background technique
In recent years, with the hair of the emerging space exploration technology such as moonlet, planetary probe, deep space exploration and interplanetary flight
Exhibition, the demand that the mankind explore cosmic space is more more and more urgent, the kind of Aerospace Satellite also more and more to the Exploratory behavior in space
Class and quantity increase and increasingly advanced therewith.This requires spaceborne propulsion-system mass gentlier, volume is smaller, effect
Rate is higher, therefore development is than leaping high, compact-sized, consumption propellant is few, low-cost Push Technology is too impatient to wait.
Traditional chemical thruster is because of the too big requirement it is impossible to meet micro-satellite to dynamical system of fuel mass, then scientist
Start to greatly develop the electric thruster that can generate more low thrust.Electric propulsion is as a kind of novel advanced propulsion mode, tool
There is the ratio punching performance promoted much higher than traditional chemical.It is to reduce spacecraft mass using electric propulsion, improves payload capability, prolong
One of the most effective approach of its long in-orbit life-span.
In numerous electric propulsion devices, pulsed plasma thruster is that the first is successfully applied to space flight task
Electric propulsion device.Since using solid polymer, as propellant, which has working medium stable and easily storage, safety
Reliably, No leakage, without storage tank and pipeline, the advantage convenient for being integrated with spacecraft, additionally have that mean power is small, thrust control
The features such as convenient, flexible, order magnitude range is wide is made, gesture stability, Orbit Transformation, position holding, drag compensation, accurate volume are suitable for
The propulsion task of a variety of minitype spacecrafts such as team's flight, thus become various countries and carry out grinding for advanced space power technology and its application
Study carefully emphasis.However, thrust degraded performance is always the critical issue for limiting pulsed plasma electric propulsion development and space application.
How to develop high-performance solid ablative-type protective coating pulsed plasma electric propulsion device and has become the important of current international electric propulsion technology
Developing direction.
The mode of propellant feed affects thrust performance.Pulsed plasma electric propulsion at present generally uses rectangular end face
Propellant configuration and the supply mode that is fed by tail portion, however the inswept area of electrical discharge arc is smaller under this mode, system
About the promotion of momentum.It a kind of be simply and effectively capable of increasing working medium ablation amount for this purpose, designing and then big thrust and total is provided
The working substance supply device of punching has the exploitation and space application of realizing the electric propulsion of high-performance pulse plasma highly important
Meaning.
Summary of the invention
Problems solved by the invention is: to overcome the shortcomings of that existing measuring technology, the present invention devise a kind of for pulse
Plasma electrically propelling presents feedway into the side of device, and the arc chamber configuration being laterally supplied to by using two pieces of solid propellants increases
Big electric discharge ablated area feeds more ablation quality to arc chamber, and then promotes thrust and Zong Chong.
Technical solution of the invention:
Feedway is presented in a kind of side for pulsed plasma electric propulsion device, including the symmetrical supply group of two nested structures
Part, feeding assembly are fixedly connected on the bottom plate of electric propulsion device, and feeding assembly includes the first supply bracket, the first tension spring, first
Push rod, the first supply washer, the first solid propellant and the second supply bracket, the second tension spring, the second push rod, the second supply washer
With the second solid propellant,
The first supply bracket is rectangular block, is provided with one and the first solid propellant propulsion on the top of the first supply bracket
The corresponding cavity of agent contour structures, for placing the first solid propellant；First supply washer is fixedly connected on the first supply branch
On the outside of the cavity of frame, one end of the first tension spring is fixed on the first supply washer, and the other end is embedded in first supply bracket one end
On the first card slot in；One end of first push rod penetrates the cavity of the first supply bracket and connects with the end face of the first solid propellant
Touching, the other end are penetrated in the first tension spring and are fixed by the first card slot and the first tension spring；
The second supply bracket is rectangular block, is provided with one and the second solid propellant propulsion on the top of the second supply bracket
The corresponding cavity of agent contour structures, for placing the second solid propellant；Second supply washer is fixedly connected on the second supply branch
On the outside of the cavity of frame, one end of the second tension spring is fixed on the second supply washer, on the second supply of other end insertion bracket one end
The second card slot in；One end of second push rod penetrates the cavity of the second supply bracket and connects with the end face of the second solid propellant
Touching, the other end are penetrated in the second tension spring and are fixed by the second card slot and the second tension spring；
First solid propellant, the opposite of the second solid propellant are held as bevel structure, the two composition V-type discharge groove, V-type
For the opening of discharge groove towards the end of electrode plate, the inside in anode plate and the angle positioned at V-type discharge groove are provided with cone
Limiting stand；Potsherd is located at anode plate, cathode plate, the first supply bracket, the second supply bracket and the first solid propellant, second
Between solid propellant；Propeller single pulse, which is discharged, promotes dosage m consumed by workbitWith the discharge energy E of propeller0、
Relationship between ablated area A are as follows:
First solid propellant and cavity clearance cooperate, fit clearance 0.5mm-1.5mm.
Second solid propellant and cavity clearance cooperate, fit clearance 0.5-1.5mm.
The cone height of cone limiting stand is 1mm-3mm, cone angle is 20 ° -50 °.
Angle between first solid propellant and the second solid propellant is α, the first solid propellant and the second solid
The width and height of propellant are respectively w and h, then ablated area are as follows: A=2hw/cos α.
Vertical range is 0.5mm~2mm between spark plug diameter outer and propellant ablation inclined-plane.
It further include storage capacitor, storage capacitor is column construction, and column construction upper end includes post ends and annular end, cylindricality
Structure lower end is fixed on bottom plate.
Anode plate and cathode plate are the narrow miniature structure in end, and there are a subtended angle, subtended angles between anode plate and cathode plate
Range be 5 ° -10 °, the width of the non-narrow place of anode plate and cathode plate is greater than the first solid propellant and the second solid propellant
Between maximal clearance.
The post ends of the annular end of anode plate and storage capacitor, cathode plate and storage capacitor connect by the way that fastener is fixed
It connects, anode plate and cathode plate end is region of discharge, is located at V-type discharge groove two sides up and down.
It is provided with spark plug on cathode plate, spark plug sparking triggering storage capacitor discharges in V-type discharge groove, and then ablation the
V-arrangement surface between one solid propellant and the second solid propellant.
Beneficial effects of the present invention:
(1) the advantages of supply mode of present invention proposition parallel feed V-type propellant ablation end face, this structure, is first is that energy
Two pieces of solid propellants are enough fed, and the propellant ablation end face for being located at arc chamber constitutes V-type, so as to increase electric discharge electricity
The area that arc is inswept, the ablation quality of single pulse also will increase under the same conditions；Second is that in the initial of ignition discharge ablation
In the stage, being formed by ablation gas can concentrate between the propellant of two sides, and two sides propellant constitutes V-arrangement discharge cavity, in this way
The electrocaloric effect of electric thruster is improved simultaneously, and then promotes the thrust and Zong Chong of thruster；
(2) present invention uses conical limit structure.The device is fixed on thruster arc chamber anode surface, on the one hand can
The opposite position of propellant when being laterally supplied to is fixed, the limit function after realizing multiple pulses electric discharge ablation consumption propellant；Separately
On the one hand the conical limit structure will not block the bottom of propellant electric discharge ablation end face, to guarantee the equal of electrical discharge arc ablation
Even property, guarantees the supply of propellant；
(3) present invention increases the area of pulsed discharge ablation, improves supply compared with existing domestic and international existing scheme
Quality thrust and thrust performance, and since structure simply has the raising across property, Yi Shixian in reliability index.
Detailed description of the invention
Fig. 1 is structure of the invention main view；
Fig. 2 is structure of the invention top view；
Fig. 3 is the structure top view of feeding assembly part of the present invention；
Fig. 4 is the structural schematic diagram of V-type part of the present invention；
Fig. 5 is structure of the invention left view.
Specific embodiment
The present invention will be further described with reference to the accompanying drawing.
The present invention in view of the defects existing in the prior art, proposes a kind of using putting of being laterally supplied to of two pieces of solid propellants
Electric room configuration.For the work requirements of the configuration, devise that a kind of structure is simple, the reliable and side feedback supply dress that is easily achieved
It sets.The device increases electric discharge ablated area, and arc chamber can be given to feed more ablation quality, and then promotes thrust and total
Punching.
The purpose of the present invention is to provide a kind of structures simply, electric discharge ablated area is big, can satisfy high power, high thrust
The working substance supply device of the space electric propulsion on-board propulsion of demand, the device is by can effectively increase the ablation of electrical discharge arc institute
Propellant area solves the problems, such as that solid ablation type pulsed plasma electric propulsion electric discharge ablation and propulsive performance are low.
One of the essential reason of solid ablation type pulsed plasma electric propulsion degraded performance is caused to be in the pulse period
Propellant feed and utilization rate are low.In order to solve the above technical problems, achieving the object of the present invention, the invention proposes a kind of novel
Working medium shape and its feedway design scheme, the program realize tension spring reliablely and stablely directional push effect and propellant
It is reliablely and stablely displaced sideways, can effectively promote the quality that propellant ablation is fed into arc chamber, at high power may be used
Ionization forms more plasmas, the final performance for improving thruster.
The specific scheme is that feedway is presented in a kind of side for pulsed plasma electric propulsion device, as shown in Fig. 2, including
The symmetrical feeding assembly 18 of two nested structures, feeding assembly 18 are fixedly connected on the bottom plate 1 of electric propulsion device, as shown in Figure 1,3, are supplied
It include the first supply bracket 2, the first tension spring 6, the first push rod 4, first supply washer 3,7 and of the first solid propellant to component 18
Second supply bracket 17, the second tension spring 14, the second push rod 15, second supply washer 16, the second solid propellant 8,
The first supply bracket 2 is rectangular block, is provided with one on the top of the first supply bracket 2 and pushes away with the first solid
Into the corresponding cavity of 7 contour structures of agent, for placing the first solid propellant 7, the first solid propellant 7 is matched with cavity clearance
It closes, fit clearance 0.5-1.5mm；First supply washer 3 is fixedly connected on the outside of the cavity of the first supply bracket 2, the first tension spring 6
One end be fixed on the first supply washer 3, the first card slot 5 on the first supply of other end insertion 2 one end of bracket；First push rod 4
One end penetrate the cavity of the first supply bracket 2 and contacted with the end face of solid propellant, the other end penetrates in the first tension spring 6 simultaneously
It is fixed by the first card slot 5 and the first tension spring 6.
The second supply bracket 17 is rectangular block, is provided with one and the second solid on the top of the second supply bracket 17
The corresponding cavity of 8 contour structures of propellant, for placing the second solid propellant 8, the second solid propellant 8 is matched with cavity clearance
It closes, fit clearance 0.5-1.5mm；Second supply washer 16 is fixedly connected on the outside of the cavity of the second supply bracket 17, and second draws
One end of spring 14 is fixed on the second supply washer 16, the second card slot 20 on the second supply of other end insertion 17 one end of bracket；The
One end of two push rods 15 penetrates the cavity of the second supply bracket 17 and contacts with the end face of solid propellant, and the other end penetrates second
It is in tension spring 14 and fixed by the second card slot 20 and the second tension spring 14.
As shown in figure 4, the opposite end of the first solid propellant 7, the second solid propellant 8 is bevel structure, the two constitutes V
Type discharge groove, the opening of V-type discharge groove is towards the end of electrode plate, the inside in anode plate and the angle positioned at V-type discharge groove
Place is provided with limiting stand 10, and limiting stand 10 is cone, and cone height 1mm-3mm, cone angle are 20 ° -50 °；Potsherd 13
Bracket 17 and the first solid propellant 7, the second solid propellant propulsion are supplied positioned at anode plate, cathode plate, the first supply bracket 2, second
Between agent 8, the electric discharge ablation of the face that prevents the first solid propellant 7, the second solid propellant 8 to be in contact with it；
Under certain discharge frequency, the size of thruster average thrust depends on first momentum.And first momentum is pulse ablation
Quality mbitWith the product of movement velocity V.Wherein propellant pulse ablation quality mbit, i.e., propeller single pulse discharge work institute
The propulsion dosage of consumption, the discharge energy E with propeller0, relationship can be assessed by following formula between ablated area A:
WhereinIt is related to the capacitance of storage capacitor and initial discharge voltage.Therefore it is worked normally in propeller
Under the conditions of, when one timing of discharge energy, propellant pulse ablation quality depends mainly on the size of ablated area A.
Assuming that the angle between the first solid propellant 7 and the second solid propellant 8 is α, the first solid propellant 7 and
The width and height of two solid propellants 8 are respectively w and h, then ablated area can be expressed as:
A=2hw/cos α
Vertical range is 0.5mm~2mm between spark plug diameter outer and propellant ablation inclined-plane.Therefore it is limited in the distance
Under the conditions of system, when the angle α between the first solid propellant 7 and the second solid propellant 8 increases from zero degree, that is, gradually become
V-type increases ablated area A and propellant pulse ablation quality mbit, therefore it is proposed by the present invention by the first solid propellant 7
The V-type discharge groove configuration constituted with the second solid propellant 8 improves the first momentum and thrust performance of propeller.
The first supply bracket 2 and the second supply bracket 17 is fixed on bottom plate 1.
Storage capacitor 19 is column construction, and column construction upper end includes post ends and annular end, and column construction lower end is fixed
On bottom plate 1；
As shown in figure 5, anode plate and cathode plate are the narrow miniature structure in end, there are one between anode plate and cathode plate
Subtended angle, the range of subtended angle are 5 ° -10 °, and the width of the non-narrow place of anode plate and cathode plate is greater than the first solid propellant 7 and second
Maximal clearance between solid propellant 8.
It is solid that the post ends of the annular end of anode plate and storage capacitor 19, cathode plate and storage capacitor 19 pass through fastener 12
Fixed connection, anode plate and cathode plate end are region of discharge, are located at V-type discharge groove two sides up and down, are provided with spark on cathode plate
Plug, spark plug sparking triggering storage capacitor 19 discharges in V-type discharge groove, and then ablation the first solid propellant 7 and the second solid
8 V-arrangement surfaces of propellant.
The storage capacitor 19 is fixed on bottom plate 1, is connected to anode 9 and cathode 11 by fastener 12.
The spark plug 21, is connected through a screw thread and is fixed on cathode 11.
First solid propellant 7 and the second solid propellant 8 be in the end face between anode 9 and cathode 11
Inverted v-shaped is simultaneously blocked by limiting stand 10.
The limiting stand 10 uses pyramidal structure, is fixed on anode 9.
Said modules are described as follows:
First solid propellant 7 and the second solid propellant 8 select polytetrafluoroethylene (PTFE).The V-arrangement that two pieces of propellants are constituted
Angular range is 40~50 degree.
The V-arrangement that anode 9 and cathode 11, spark plug 21 and the first solid propellant 7 and the second solid propellant 8 are constituted
End face constitutes the electric discharge ablation chamber of apparatus of the present invention.
First push rod 4, first supplies washer 3, the second push rod 15 and the second supply 16 material of washer and uses stainless steel, bottom plate
1 material selection epoxy resin.First supply bracket 2 and the second supply 17 material of bracket use polyimides.
Anode 9 (including limiting stand 10) and cathode 11 and 12 material of fastener use that electric conductivity is good and hardness is high
The chromium-zirconium-copper of arc resistant ablation.
Spark plug 21 selects breakdown voltage to be lower than the coaxial semiconductor configuration of 1000V, and central electrode is nickel-manganese, diameter
For 6~9mm；Shell is made of high-temperature alloy steel；Insulating material is alumina porcelain；0.5~0.8mm of semiconductor slice width.First draws
Spring 6 and 14 material of the second tension spring use spring steel.
In view of electrion environment and fuel factor, potsherd 13 uses alumina ceramic material in the present invention.Potsherd
13 effects are will to discharge to constrain in anode 9 and cathode 11, spark plug 21 and the first solid propellant 7 and the second solid propellant
The 8 V-arrangement regions constituted.
Storage capacitor 19 is metallized polypropylene film capacitor, and for capacitance between 20 μ of μ F~80 F, added voltage range is 1kv
Between~2kv.
Present feedway whole work process in electric propulsion side of the present invention are as follows:
The first tension spring 6 and the second tension spring 14 stretched respectively generates the first solid propellant 7 and the second solid propellant 8
Opposite thrust, under the action of limiting stand 10, the first solid propellant 7 and the second solid propellant 8 are separately fixed at
In first supply bracket 2 and the second supply bracket 17.
When work, storage capacitor 19 charges to corresponding voltage first；When needing the electric discharge work of electric propulsion device, spark
21 igniting of plug, i.e., produce between the first solid propellant 7 and the V-arrangement surface of the second solid propellant 8 between anode 9 and cathode 11
Raw micro electric discharge；The electronics that micro electric discharge generates hits propellant surface under electric field force effect, and propellant surface is further divided
It collapses and dissociation generates more electronics, these electronics are accelerated and collide again the first solid propellant 7 and the second solid propellant propulsion
The V-arrangement surface of agent 8；V-arrangement surface frequent impact gradually forms more charged particle areas simultaneously between the two poles of the earth, finally makes energy storage
Capacitor 19 forms the large-current electric arc discharge along propellant V-arrangement surface in anode 9 and cathode 11；Discharge caused by high-temperature electric arc after
And V-arrangement surface between ablation the first solid propellant 7 and the second solid propellant 8；First solid propellant 7 and the second solid propellant propulsion
8 V-arrangement skin layers of agent it is ablated fall after, the promotion by the first tension spring 6 and the second tension spring 14 respectively, two pieces of solid propellants
It is blocked after moving towards to limiting stand 10；As multiple pulses are discharged, the first solid propellant 7 and the second solid propellant 8 are not
Disconnected ablation, the first tension spring 6 and the second tension spring 14 accordingly push, and realize that feeding assembly stablizes parallel feed to two pieces of solid propellants
Function.
The innovative point of the present embodiment is to realize the ability of two pieces of solid propellant parallel feeds, and at two when discharging
Propellant surface region forms a V-arrangement discharge cavity, this will be effectively improved is formed by under the big ablation supply conditions of propellant
The electrocaloric effect of ablation gas.On the one hand increase the inswept area that discharges, increases pulse ablation and supply quality；On the other hand exist
Electric propulsion is discharged in the ablation course of work, the air accumulation that institute's ablation is formed V-arrangement discharge cavity between two pieces of solid propellants, this will
The pressure of ablation gas is improved to a certain extent, to enhance the electric heating acceleration effect of electric propulsion, and then promotes thruster
Thrust and Zong Chong.
Curve guide impeller thinking and corresponding embodiment of the invention above described embodiment only expresses, but can not be therefore
And it is interpreted as limitations on the scope of the patent of the present invention.It should be pointed out that for those of ordinary skill in the art, not
Under the premise of being detached from present inventive concept, various modifications and improvements can be made, and these are all within the scope of protection of the present invention.Cause
This, the scope of protection of the patent of the invention shall be subject to the appended claims, and it is art technology that the present invention, which is not described in detail content,
Personnel's well-known technique.
Claims (10)
1. feedway is presented in a kind of side for pulsed plasma electric propulsion device, it is characterised in that: symmetrical including two nested structures
Feeding assembly (18), feeding assembly (18) is fixedly connected on the bottom plate (1) of electric propulsion device, and feeding assembly (18) includes first
Supply bracket (2), the first tension spring (6), the first push rod (4), the first supply washer (3), the first solid propellant (7) and the second confession
Washer (16) and the second solid propellant (8) are supplied to bracket (17), the second tension spring (14), the second push rod (15), second,
First supply bracket (2) is rectangular block, is provided with one on the top of the first supply bracket (2) and pushes away with the first solid
Into the corresponding cavity of agent (7) contour structures, for placing the first solid propellant 7；First supply washer (3) is fixedly connected on the
On the outside of the cavity of one supply bracket (2), one end of the first tension spring (6) is fixed on the first supply washer (3), and the other end is embedded in
In the first card slot (5) on first supply bracket (2) one end；One end of first push rod (4) penetrates the sky of the first supply bracket (2)
Chamber is simultaneously contacted with the end face of the first solid propellant (7), the other end penetrate in the first tension spring (6) and by the first card slot (5) with
First tension spring (6) is fixed；
Second supply bracket (17) is rectangular block, is provided with one and the second solid on the top of the second supply bracket (17)
The corresponding cavity of propellant (8) contour structures, for placing the second solid propellant (8)；Second supply washer (16) is fixed to be connected
It connects on the outside of the cavity of the second supply bracket (17), one end of the second tension spring (14) is fixed on the second supply washer (16), separately
The second card slot (20) on the second supply of one end insertion bracket (17) one end is inner；One end of second push rod (15) penetrates the second supply
The cavity of bracket (17) is simultaneously contacted with the end face of the second solid propellant (8), and the other end penetrates in the second tension spring (14) and passes through
Second card slot (20) and the second tension spring (14) are fixed；
First solid propellant (7), the opposite of the second solid propellant (8) are held as bevel structure, the two composition V-type discharge groove, V
For the opening of type discharge groove towards the end of electrode plate, the inside in anode plate and the angle positioned at V-type discharge groove are provided with cone
Body limiting stand (10)；Potsherd (13) is located at anode plate, cathode plate, the first supply bracket (2), the second supply bracket (17) and the
Between one solid propellant (7), the second solid propellant (8)；Propeller single pulse, which is discharged, promotes dosage consumed by work
mbitWith the discharge energy E of propeller0, relationship between ablated area A are as follows:
2. feedway is presented in a kind of side for pulsed plasma electric propulsion device as described in claim 1, it is characterised in that:
First solid propellant (7) and cavity clearance cooperate, fit clearance 0.5mm-1.5mm.
3. feedway is presented in a kind of side for pulsed plasma electric propulsion device as described in claim 1, it is characterised in that:
Second solid propellant (8) and cavity clearance cooperate, fit clearance 0.5-1.5mm.
4. feedway is presented in a kind of side for pulsed plasma electric propulsion device as described in claim 1, it is characterised in that:
The cone height of cone limiting stand (10) is 1mm-3mm, cone angle is 20 ° -50 °.
5. feedway is presented in a kind of side for pulsed plasma electric propulsion device as described in claim 1, it is characterised in that:
Angle between first solid propellant (7) and the second solid propellant (8) is α, the first solid propellant (7) and the second solid
The width and height of propellant (8) are respectively w and h, then ablated area are as follows: A=2hw/cos α.
6. feedway is presented in a kind of side for pulsed plasma electric propulsion device as described in claim 1, it is characterised in that:
Vertical range is 0.5mm~2mm between spark plug diameter outer and propellant ablation inclined-plane.
7. feedway is presented in a kind of side for pulsed plasma electric propulsion device as described in claim 1, it is characterised in that:
It further include storage capacitor (19), storage capacitor (19) is column construction, and column construction upper end includes post ends and annular end, cylindricality
Structure lower end is fixed on bottom plate (1).
8. feedway is presented in a kind of side for pulsed plasma electric propulsion device as described in claim 1, which is characterized in that
Anode plate and cathode plate are the narrow miniature structure in end, and there are a subtended angle between anode plate and cathode plate, the range of subtended angle is
5 ° -10 °, the width of the non-narrow place of anode plate and cathode plate be greater than the first solid propellant (7) and the second solid propellant (8) it
Between maximal clearance.
9. feedway is presented in a kind of side for pulsed plasma electric propulsion device as claimed in claim 7, it is characterised in that:
It is fixed that the post ends of the annular end of anode plate and storage capacitor (19), cathode plate and storage capacitor (19) pass through fastener (12)
Connection, anode plate and cathode plate end are region of discharge, are located at V-type discharge groove two sides up and down.
10. feedway is presented in a kind of side for pulsed plasma electric propulsion device as claimed in claim 9, feature exists
In: it is provided with spark plug on cathode plate, spark plug sparking triggering storage capacitor (19) is discharged in V-type discharge groove, and then ablation the
V-arrangement surface between one solid propellant (7) and the second solid propellant (8).
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| CN201910702764.8A CN110469473B (en) | 2019-07-31 | 2019-07-31 | Side feed supply device for pulse plasma electric thruster |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111076937A (en) * | 2019-12-09 | 2020-04-28 | 北京理工大学 | System and method for testing ablation quality of energetic working medium pulse plasma thruster |
| CN112360710A (en) * | 2020-10-23 | 2021-02-12 | 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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| CN112360710A (en) * | 2020-10-23 | 2021-02-12 | 北京精密机电控制设备研究所 | Working medium feeding device for coaxial electrothermal plasma thruster |
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