CN115822814B - Coaxial annular multi-electrode electric control solid thruster - Google Patents
Coaxial annular multi-electrode electric control solid thruster Download PDFInfo
- Publication number
- CN115822814B CN115822814B CN202211166126.7A CN202211166126A CN115822814B CN 115822814 B CN115822814 B CN 115822814B CN 202211166126 A CN202211166126 A CN 202211166126A CN 115822814 B CN115822814 B CN 115822814B
- Authority
- CN
- China
- Prior art keywords
- electrode
- thruster
- shell
- power supply
- electric control
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Plasma Technology (AREA)
Abstract
The invention discloses a coaxial annular multi-electrode electric control solid thruster, belongs to the technical field of electric control solid thrusters, and aims to solve the problem that the existing coaxial electric control solid thruster is formed by a group of central electrodes and outer electrodes and has a small thrust adjustment range. The invention comprises a shell, a spray pipe, a central electrode, an annular electrode, an electric control solid propellant and a power supply control module; the top and the bottom of the shell are respectively connected with a spray pipe and a power supply control module, and the inner wall of the bottom end of the shell is provided with concentric circle slots; the central electrode is a cylinder and is fixed at the central position inside the shell through the slot; the multi-layer annular electrode is concentrically fixed in the slot of the shell by taking the central electrode as the center, the annular part between the innermost layer annular electrode and the central electrode forms a combustion chamber, and the annular parts between the other two adjacent layers of annular electrodes form the combustion chamber; filling electric control solid propellant into each stage of combustion chamber; each electrode penetrates through the bottom end of the shell through the cylindrical guide structure and is electrically connected with the power supply control module; the dimensions of the combustion chambers of each stage satisfy the following formula definition to ensure that the electronically controlled solid propellant in all combustion chambers is synchronously burned out:
Description
Technical Field
The invention belongs to the technical field of electric control solid thrusters.
Background
The electric control solid thruster has the outstanding advantages of simple structure, high working reliability, mature technology, easy manufacture, good economy and the like, is convenient to maintain and transport in daily life, can be arranged on a vehicle, a ship and an airplane, and can be ignited at any time according to the needs of the situation. However, once the traditional solid space thruster is ignited, unless the fuel is exhausted and the flame-out cannot be actively flame-out, the traditional solid space thruster cannot be started again, and the traditional solid space thruster can only work according to a thrust scheme determined by a grain, unlike a liquid space thruster, because the traditional solid space thruster can not realize multiple starting and thrust adjustment, and can only work according to the thrust scheme determined by the grain until the grain combustion is ended.
In addition, the cold air propulsion has the advantages of low response speed, low specific impulse and needs to carry more multiple working substances to prolong the service life, but the device has the advantages of simple structure, mature technology, low cost, low risk and relatively low overall cost-effectiveness ratio, but has the advantages of low thrust force, wide-range adjustment, low response speed and low specific impulse, and is difficult to meet the situation of space countermeasure.
The electric propulsion has ionization and acceleration efficiency under the micro-flow condition, has long service life and high response speed, but the charged particles generated by ionization in operation can generate unavoidable interaction with the wall surface of the thruster, so that the wall surface loss is increased, the efficiency is reduced, even the problems of unstable discharge, flameout and the like occur, and the requirements of high reliability are not met.
The electronically controlled solid propellant has unique electrochemical characteristics, proper voltage is loaded at two ends of the electrode, and the propellant is ignited and continuously combusted under the condition of no ignition charge; the electric field is removed, the propellant extinguishes, and the propellant can burn again by reapplying the voltage. In addition, the control of the burning speed of the propellant and the adjustment of the thrust can be realized by changing the voltage. Therefore, the electric control solid thruster has the characteristics of controllable thrust and repeated starting. In addition, the electric control solid propellant engine has higher safety performance, and the propellant has obvious insensitive characteristic and is insensitive to flame and impact.
The traditional coaxial electric control solid thruster consists of a group of central electrodes and outer electrodes, wherein the outer electrodes are electrodes formed by processing a metal cylinder. The combustion chamber formed by the central electrode and the outer electrode cannot be designed into a large-spacing structure to increase the drug loading amount due to the current density required by stable combustion of the electric control solid thrust agent, so that the upper limit and the adjustment range of the thrust are smaller.
Disclosure of Invention
Aiming at the problem that the existing coaxial electric control solid thruster is formed by a group of central electrodes and outer electrodes, the thrust adjustment range is small, the invention provides a coaxial annular multi-electrode electric control solid thruster. The outer electrode of the thruster designed by the invention is a ring electrode which is arranged in a multi-stage way to form a multi-stage combustion chamber, and the multi-chamber simultaneous electrifying ignition can be realized through the control circuit, so that the upper limit of the thrust is increased and the adjusting range of the thrust is widened on the basis of adjusting the thrust by changing the power.
The invention relates to a coaxial annular multi-electrode electric control solid thruster, which comprises a shell 1, a spray pipe 2, a central electrode 3, an annular electrode 4, an electric control solid propellant 6 and a power supply control module 7;
The open end at the top of the shell 1 is connected with the spray pipe 2, the outer part of the bottom end of the shell 1 is connected with the power supply control module 7, and the inner wall of the bottom end of the shell 1 is provided with concentric circle slots;
the central electrode 3 is a cylinder and is fixed at the central position inside the shell 1 through a slot;
The multi-layer annular electrode 4 is concentrically fixed in the slot of the shell 1 by taking the central electrode 3 as the center, the annular part between the innermost layer annular electrode 4 and the central electrode 3 forms a combustion chamber, and the annular parts between the other two adjacent layers of annular electrodes 4 form the combustion chamber; filling electric control solid propellant 6 in each stage of combustion chamber;
Each electrode penetrates through the bottom end of the shell 1 through a cylindrical guide structure and is electrically connected with the power supply control module 7;
The dimensions of the combustion chambers of each stage satisfy the following formula definition to ensure synchronous burnout of the electronically controlled solid propellant 6 in all combustion chambers:
wherein d n is the charge radius of the n-th stage combustion chamber, n=1, 2, …, H is the number of combustion chambers;
r n is the outer radius of the inner electrode of the two electrodes constructing the nth stage combustion chamber;
j is the lower limit of the current density of the combustion end face, expressed as: Meets the limiting conditions: 7.0E-09 (A/m 2) < j;
u is the working voltage of the thruster when working at maximum power;
Sigma is the conductivity of the propellant;
η is the energy coefficient of the thruster;
v B is the combustion rate of the propellant at maximum power of the thruster;
ρ is the density of the propellant;
P max is the maximum power of the thruster; expressed as: p max＝ηSvB 3 P, where the total charge face area of all combustion chambers is expressed as:
Preferably, the electric control solid propellant combustion chamber further comprises an insulating layer 5, wherein the insulating layer 5 is coated on the side wall of the electrode of the combustion chamber, and a gap of 1mm is formed between the insulating layer 5 and the top end of the electrode, so that the electric control solid propellant combustion can be ensured when the electric control solid propellant combustion chamber is electrified.
Preferably, the power supply control module 7 is fixed to the bottom open end of the casing 1 of the thruster by a cylindrical guide structure, and the bottom open end of the power supply control module 7 encloses the control circuit in the casing by a rear cover 11 of insulating material.
Preferably, the power supply control module 7 comprises a spring electrode 8, a spring 9, a control circuit 10 and an extraction electrode 12;
The bottom of the shell 1 is provided with H+1 through holes, the top end of the control circuit 10 is welded with H+1 spring electrodes 8, the H+1 spring electrodes 8 extend into the interior of the shell along the H+1 through holes at the bottom of the shell 1, and the H+1 spring electrodes 8 are ensured to be in close contact with the bottom ends of the central electrode 3 and the annular electrodes 4 of each layer through springs 9 arranged in the interior to realize electric connection,
Seven extraction electrodes 12 are welded at the bottom end of the power supply control module 7 and are used for being connected with an external power supply.
Preferably, seven extraction electrodes 12 are arranged in a regular hexagonal structure and occupy the vertex and the center of the hexagon respectively; to mate with an aerial plug.
Preferably, the spring electrode 8 is made of copper alloy material, and the spring 9 is made of carbon nanomaterial.
Preferably, the casing 1 of the thruster is removably connected to the lance 2 by means of a flange or screw thread.
Preferably, the housing 1 of the thruster is detachably connected to the power supply control module 7 by means of flanges or threads.
Preferably, the electrically controlled solid propellant 6 comprises an oxidant, a binder, a cross-linking agent and a propellant which are mixed according to the mass fraction ratio of 2-5:1-2:1-2.5:3.5-4.5.
Preferably, the insulating layer 5 is composed of a filler material and a modified resin paint; wherein the filling material is one or more of modified kaolin, silicon dioxide, titanium dioxide, molybdenum disulfide, talcum powder, calcium carbonate powder, calcined clay, magnesium hydroxide or aluminum hydroxide; the modified resin coating is one or more of polyphenylene sulfide, polyamide, fluorocarbon resin, polyvinyl alcohol or polytetrafluoroethylene.
The invention has the beneficial effects that:
1. according to the coaxial annular multi-electrode electric control solid thruster provided by the invention, the central electrode and the plurality of groups of annular electrodes are arranged in a multistage manner, so that a plurality of combustion chambers are formed, and the power of the thruster is greatly improved;
2. The problems of small thrust adjustment range and low precision of the single-stage structure are solved, the multi-stage combustion chamber is added on the original basis, the loading capacity can be increased, the sizes of the stages are reasonably distributed to ensure the current density of the combustion end face, the combustion efficiency is not reduced, the propellants of the stages are synchronously burnt out, and the control precision of the thrust is improved.
3. The invention does not need a traditional ignition device, is insensitive to stimulation such as flame, impact and the like, can be safely transported through air transportation and other ways, can keep a combat readiness state for a long time, and has wide application prospect.
Drawings
FIG. 1 is a schematic structural view of a coaxial annular multi-electrode electronically controlled solid thruster according to the present invention;
FIG. 2 is a schematic structural view of a center electrode and ring electrode configuration;
FIG. 3 is a schematic structural view of an electrode, insulating layer and electronically controlled solid propellant assembly;
FIG. 4 is a schematic diagram of the dimensional relationship of the combustion chambers;
fig. 5 is a schematic view of the structure of the spring electrode connected to the center electrode and the ring electrode.
In the figure: 1-thruster casing, 2-spray pipe, 3-center electrode, 4-annular electrode, 5-insulating layer, 6-automatically controlled solid propellant, 7-power supply control module, 8-spring electrode, 9-spring, 10-control circuit, 11-back lid, 12-bottom electrode.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be noted that all directional indicators (such as up, down, left, right, front, and rear … …) in the embodiments of the present invention are merely used to explain the relative positional relationship, movement, etc. between the components in a particular posture (as shown in the drawings), and if the particular posture is changed, the directional indicator is changed accordingly.
Furthermore, descriptions such as those referred to as "first," "second," and the like, are provided for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implying an order of magnitude of the indicated technical features in the present disclosure. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present invention, the meaning of "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.
In the present invention, unless specifically stated and limited otherwise, the terms "connected," "affixed," and the like are to be construed broadly, and for example, "affixed" may be a fixed connection, a removable connection, or an integral body; the device can be mechanically connected, electrically connected, physically connected or wirelessly connected; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In addition, the technical solutions of the embodiments of the present invention may be combined with each other, but it is necessary to be based on the fact that those skilled in the art can implement the technical solutions, and when the technical solutions are contradictory or cannot be implemented, the combination of the technical solutions should be considered as not existing, and not falling within the scope of protection claimed by the present invention.
The invention is further described below with reference to the drawings and specific examples, which are not intended to be limiting.
The first embodiment is as follows: the following describes the present embodiment with reference to fig. 1 to 5, and the coaxial annular multi-electrode electric control solid thruster of the present embodiment includes a housing 1, a nozzle 2, a central electrode 3, an annular electrode 4, an electric control solid propellant 6 and a power supply control module 7;
The open end at the top of the shell 1 is connected with the spray pipe 2, the outer part of the bottom end of the shell 1 is connected with the power supply control module 7, and the inner wall of the bottom end of the shell 1 is provided with concentric circle slots;
the central electrode 3 is a cylinder and is fixed at the central position inside the shell 1 through a slot;
The multi-layer annular electrode 4 is concentrically fixed in the slot of the shell 1 by taking the central electrode 3 as the center, the annular part between the innermost layer annular electrode 4 and the central electrode 3 forms a combustion chamber, and the annular parts between the other two adjacent layers of annular electrodes 4 form the combustion chamber; filling electric control solid propellant 6 in each stage of combustion chamber;
Each electrode penetrates through the bottom end of the shell 1 through a cylindrical guide structure and is electrically connected with the power supply control module 7;
The dimensions of the combustion chambers of each stage satisfy the following formula definition to ensure synchronous burnout of the electronically controlled solid propellant 6 in all combustion chambers:
wherein d n is the charge radius of the n-th stage combustion chamber, n=1, 2, …, H is the number of combustion chambers;
r n is the outer radius of the inner electrode of the two electrodes constructing the nth stage combustion chamber;
j is the lower limit of the current density of the combustion end face, expressed as: Meets the limiting conditions: 7.0E-09 (A/m 2) < j;
u is the working voltage of the thruster when working at maximum power;
Sigma is the conductivity of the propellant;
η is the energy coefficient of the thruster;
v B is the combustion rate of the propellant at maximum power of the thruster;
ρ is the density of the propellant;
P max is the maximum power of the thruster; expressed as: p max＝ηSvB 3 P, where the total charge face area of all combustion chambers is expressed as:
Further, the electric control solid propellant combustion chamber further comprises an insulating layer 5, wherein the insulating layer 5 is coated on the side wall of the electrode of the combustion chamber, and a gap of 1mm is reserved between the insulating layer 5 and the top end of the electrode, so that the electric control solid propellant can be subjected to layer combustion when being electrified.
Referring to fig. 1, the housing 1 of the thruster is detachably connected to the lance 2 by means of a flange or screw thread. The shell 1 of the thruster is detachably connected with the power supply control module 7 through a flange or threads.
The central electrode 3 and the annular electrode 4 are powered by a power supply control module 7, wherein the surface of the electrode with positive voltage is coated with an insulating layer 5 for limiting the speed of the electric control solid propellant 6 to meet the requirement of layer combustion;
before assembly, the surface of the electrode is frosted, and an insulating coating 5 is sprayed on the surface of the electrode, and then plasticization is carried out in a muffle furnace;
The electric control solid propellant 6 is filled in a combustion chamber formed by the central electrode 3 and the annular electrode 4 by casting, spraying or integral filling and the like;
The power supply control module 7 is fixed with the bottom of the thruster casing 1 through threads or flanges; the power supply control module 7 is fixed with the bottom open end of the shell 1 of the thruster through a cylindrical guide structure, and the bottom open end of the power supply control module 7 is encapsulated in the shell by an insulating material rear cover 11.
The power supply control module 7 comprises a spring electrode 8, a spring 9, a control circuit 10 and an extraction electrode 12; the bottom of the shell 1 is provided with H+1 through holes, the top end of the control circuit 10 is welded with H+1 spring electrodes 8, the H+1 spring electrodes 8 extend into the shell along the H+1 through holes at the bottom of the shell 1, the H+1 spring electrodes 8 are ensured to be in close contact with the central electrode 3 and the bottom ends of all layers of ring electrodes 4 through springs 9 arranged in the shell to realize electric connection, and the bottom end of the power supply control module 7 is welded with seven extraction electrodes 12 for being connected with an external power supply. The external power supply adopts any one of alternating current, direct current or capacitor discharge. Seven extraction electrodes 12 are arranged and are arranged according to a regular hexagonal structure, and occupy the vertex and the center of the hexagon respectively; to mate with an aerial plug.
The spring electrode 8 is fixed at the top of the control circuit 10, and contacts with the central electrode 3 and the annular electrode 4 through the apertures on the power supply control module 7 and the thruster casing 1 to form a closed loop; the center electrode 3, the first layer ring electrode 4, the second layer ring electrode 4, and the third layer ring electrode 4 are applied with voltages in the order of negative, positive, negative, and positive.
The innovation point of the embodiment is that the multi-layer combustion chamber is arranged, the drug loading capacity is increased on the premise of not reducing the combustion efficiency of the electric control solid propellant 6, and the upper limit and the adjusting range of the engine thrust are also increased. the bottom of the shell 1 is provided with concentric multi-layer clamping grooves, the central clamping groove is used for clamping and fixing the central electrode 3, the rest clamping grooves are used for clamping and fixing the multi-layer annular electrode 4, referring to figure 4, an annular space between the central electrode 3 and the first layer annular electrode 4 is provided with a 1 st stage combustion chamber, the charging radius of the 1 st stage combustion chamber is d 1, the 1 st stage combustion chamber is provided with two electrodes, the inner layer electrode is the central electrode 3, the outer radius of the central electrode 3 is R 1, The charging end surface area of the 1 st stage combustion chamber is S 1, and so on, the charging radius of the 2 nd stage combustion chamber is d 2, the outer radius of the first layer ring electrode 4 of the inner layer electrode is R 2, the charging end surface area of the 2 nd stage combustion chamber is S 2, The charging radius of the 3 rd-stage combustion chamber is d 3, the outer radius of the second-layer circular ring electrode 4 of the inner-layer electrode is R 3, the charging end surface area of the 3 rd-stage combustion chamber is S 3, taking the H=3-layer combustion chamber as an example, the total charging end surface area of the combustion chamber is S=S 1+S2+S3, When the circuit between the power supply control module 7 and the electric control solid propellant 6 is conducted, the power supply control module, the central electrode 3, the annular electrode 4 and the electric control solid propellant 6 form a closed loop, the electric control solid propellant 6 in each annular groove is electrified to ignite and burn, and the thruster generates thrust; When the circuit between the power supply control module 7 and the electric control solid propellant 6 is disconnected, the electric control solid propellant 6 in each annular groove is powered off to stop burning, and then the thruster stops generating thrust; in order to facilitate synchronous replacement of all layers of electric control solid propellant 6, the layers are expected to burn out synchronously, so that the size of each combustion chamber is designed in the embodiment, the thrust generated by the combustion of the propellant is matched with the required thrust, and all stages of medicaments are synchronously burned out as much as possible, so that the current density of the combustion end face is ensured, the combustion efficiency is improved, and the control accuracy of the thrust is improved.
When the power applied to each electrode is changed by the power supply control module 7, the combustion rate of the electronically controlled solid propellant in the combustion chamber is changed, so that the thrust of the engine is changed.
The shape preparation process is as follows: the surface of the positive electrode is frosted firstly, then the insulating layer 5 is sprayed on the surface of the electrode after treatment, and finally the electrode is put into a muffle furnace for plasticizing treatment. The treated electrode is inserted into an annular slot in the thruster casing 1.
Next, the electronically controlled solid propellant 6, which is fully cured, is slurry-cast into a combustion chamber formed by the center electrode 3 and the ring electrode 4 and cured in a vacuum oven at 40 ℃ for 3-4 days.
And finally, respectively fixing the spray pipe and the power supply control module at the upper end and the lower end of the shell of the thruster so as to complete the assembly of the engine.
The main working process is as follows: the central electrode 3 and the ring electrode 4 in the invention are connected with the positive electrode and the negative electrode of a power supply through a spring electrode 8. The number of the annular electrodes can be increased or decreased according to the thrust requirement. The individual design of the electrode spacing in the engine can enable the propellant to burn out synchronously. When the circuit is closed, the power supply circuit 10 forms a loop with the central electrode 3, the annular electrode 4 and the electric control solid propellant 6, the electric control solid propellant in the combustion chamber is electrified and combusted to generate high-temperature high-pressure gas, and the engine is accelerated to generate thrust through the spray pipe. When the engine operation is required to be stopped, the control circuit 10 can be realized by opening the communicated loop, and when the loop is closed again, the secondary ignition can be realized, and the whole process can be repeated.
The second embodiment is as follows: in this embodiment, the first embodiment is further defined, and the electronically controlled solid propellant 6 is formed by mixing an oxidizing agent, a binder, a crosslinking agent and a propellant according to a mass fraction ratio of 2-5:1-2:1-2.5:3.5-4.5.
And a third specific embodiment: in this embodiment, the first embodiment is further defined, and the insulating layer 5 is composed of a filler and a modified resin paint; wherein the filling material is one or more of modified kaolin, silicon dioxide, titanium dioxide, molybdenum disulfide, talcum powder, calcium carbonate powder, calcined clay, magnesium hydroxide or aluminum hydroxide; the modified resin coating is one or more of polyphenylene sulfide, polyamide, fluorocarbon resin, polyvinyl alcohol or polytetrafluoroethylene.
When the modified resin coating is a composition, the components are in any ratio. When the filler material is a composition, the components are in any ratio.
Although the invention herein has been described with reference to particular embodiments, it is to be understood that these embodiments are merely illustrative of the principles and applications of the present invention. It is therefore to be understood that numerous modifications may be made to the illustrative embodiments and that other arrangements may be devised without departing from the spirit and scope of the present invention as defined by the appended claims. It should be understood that the different dependent claims and the features described herein may be combined in ways other than as described in the original claims. It is also to be understood that features described in connection with separate embodiments may be used in other described embodiments.
Claims (10)
1. The coaxial annular multi-electrode electric control solid thruster is characterized by comprising a shell (1), a spray pipe (2), a central electrode (3), an annular electrode (4), an electric control solid propellant (6) and a power supply control module (7);
the open end at the top of the shell (1) is connected with the spray pipe (2), the outer part of the bottom end of the shell (1) is connected with the power supply control module (7), and the inner wall of the bottom end of the shell (1) is provided with concentric circle slots;
The central electrode (3) is a cylinder and is fixed at the central position inside the shell (1) through a slot;
the multi-layer annular electrode (4) is concentrically fixed in a slot of the shell (1) by taking the central electrode (3) as a center, a circular ring part between the innermost-layer annular electrode (4) and the central electrode (3) forms a combustion chamber, and circular ring parts between the other two adjacent layers of annular electrodes (4) form the combustion chamber; filling electric control solid propellant (6) in each stage of combustion chamber;
Each electrode penetrates through the bottom end of the shell (1) through a cylindrical guide structure and is electrically connected with the power supply control module (7);
The dimensions of the combustion chambers of each stage satisfy the following formula definition to ensure the synchronous burnout of the electronically controlled solid propellant (6) in all combustion chambers:
wherein d n is the charge radius of the n-th stage combustion chamber, n=1, 2, …, H is the number of combustion chambers;
r n is the outer radius of the inner electrode of the two electrodes constructing the nth stage combustion chamber;
j is the lower limit of the current density of the combustion end face, expressed as: Meets the limiting conditions: 7.0E-09 (A/m 2) < j;
u is the working voltage of the thruster when working at maximum power;
Sigma is the conductivity of the propellant;
η is the energy coefficient of the thruster;
v B is the combustion rate of the propellant at maximum power of the thruster;
ρ is the density of the propellant;
P max is the maximum power of the thruster; expressed as: p max＝ηSvB 3 P, where the total charge face area of all combustion chambers is expressed as:
2. The coaxial annular multi-electrode electric-controlled solid thruster according to claim 1, further comprising an insulating layer (5) coated on the electrode side wall of the combustion chamber, wherein a gap of 1mm is formed between the insulating layer (5) and the top end of the electrode, so that the electric-controlled solid thruster can generate layer combustion when being electrified.
3. The coaxial annular multi-electrode electric control solid thruster according to claim 1, characterized in that the power supply control module (7) is fixed with the bottom open end of the casing (1) of the thruster by a cylindrical guiding structure, the bottom open end of the power supply control module (7) is encapsulated in the casing by a rear cover (11) of insulating material.
4. A coaxial annular multi-electrode electrically controlled solid thruster according to claim 3, characterized in that the power supply control module (7) comprises a spring electrode (8), a spring (9), a control circuit (10) and an extraction electrode (12);
The bottom of the shell (1) is provided with H+1 through holes, the top end of the control circuit (10) is welded with H+1 spring electrodes (8), the H+1 spring electrodes (8) extend into the interior of the shell along the H+1 through holes at the bottom of the shell (1), the H+1 spring electrodes (8) are ensured to be in close contact with the bottom ends of the central electrode (3) and the annular electrodes (4) of each layer through springs (9) arranged in the interior to realize electric connection,
Seven extraction electrodes (12) are welded at the bottom end of the power supply control module (7) and are used for being connected with an external power supply.
5. The coaxial annular multi-electrode electrically controlled solid thruster according to claim 4, characterized in that the extraction electrodes (12) are seven and are arranged in a regular hexagonal structure, occupying the vertices and the center of the hexagon respectively; to mate with an aerial plug.
6. The coaxial annular multi-electrode electric control solid thruster according to claim 4, wherein the spring electrode (8) is made of copper alloy material, and the spring (9) is made of carbon nanomaterial.
7. The coaxial annular multi-electrode electronically controlled solid thruster of claim 4, wherein the casing (1) of the thruster is detachably connected to the lance (2) by means of a flange or screw thread.
8. The coaxial annular multi-electrode electronically controlled solid thruster according to claim 4, characterized in that the casing (1) of the thruster is detachably connected to the power supply control module (7) by means of flanges or threads.
9. The coaxial annular multi-electrode electric control solid thruster according to claim 1, wherein the electric control solid propellant (6) comprises an oxidant, a binder, a cross-linking agent and a propellant which are mixed according to the mass fraction ratio of 2-5:1-2:1-2.5:3.5-4.5.
10. The coaxial annular multi-electrode electronically controlled solid thruster according to claim 2, characterized in that the insulating layer (5) consists of a filler material and a modified resin coating; wherein the filling material is one or more of modified kaolin, silicon dioxide, titanium dioxide, molybdenum disulfide, talcum powder, calcium carbonate powder, calcined clay, magnesium hydroxide or aluminum hydroxide; the modified resin coating is one or more of polyphenylene sulfide, polyamide, fluorocarbon resin, polyvinyl alcohol or polytetrafluoroethylene.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211166126.7A CN115822814B (en) | 2022-09-23 | 2022-09-23 | Coaxial annular multi-electrode electric control solid thruster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211166126.7A CN115822814B (en) | 2022-09-23 | 2022-09-23 | Coaxial annular multi-electrode electric control solid thruster |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115822814A CN115822814A (en) | 2023-03-21 |
| CN115822814B true CN115822814B (en) | 2024-07-02 |
Family
ID=85523888
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211166126.7A Active CN115822814B (en) | 2022-09-23 | 2022-09-23 | Coaxial annular multi-electrode electric control solid thruster |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115822814B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR102846116B1 (en) * | 2023-09-15 | 2025-08-12 | 포항공과대학교 산학협력단 | Thruster for micro-satellite and manufacturing method thereof |
| KR102846117B1 (en) * | 2023-09-15 | 2025-08-12 | 포항공과대학교 산학협력단 | Thruster for micro-satellite and manufacturing method thereof |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110195665A (en) * | 2019-06-21 | 2019-09-03 | 北京理工大学 | A kind of air storing type solid propellant power device of reloading |
| CN114278463A (en) * | 2021-12-28 | 2022-04-05 | 哈尔滨工业大学 | Electric control solid thruster |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7788900B2 (en) * | 2002-01-16 | 2010-09-07 | Michael Dulligan | Electrically controlled extinguishable solid propellant motors |
| US8857338B2 (en) * | 2008-05-16 | 2014-10-14 | Digital Solid State Propulsion Llc | Electrode ignition and control of electrically ignitable materials |
-
2022
- 2022-09-23 CN CN202211166126.7A patent/CN115822814B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110195665A (en) * | 2019-06-21 | 2019-09-03 | 北京理工大学 | A kind of air storing type solid propellant power device of reloading |
| CN114278463A (en) * | 2021-12-28 | 2022-04-05 | 哈尔滨工业大学 | Electric control solid thruster |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115822814A (en) | 2023-03-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN115822814B (en) | Coaxial annular multi-electrode electric control solid thruster | |
| CN114320662B (en) | A wide speed range and high maneuverability air-breathing combined propulsion system and missile | |
| CN113187622B (en) | An electro-chemical hybrid space thruster | |
| CN114718765A (en) | Arc igniter for micro-nano satellite | |
| WO2023240782A1 (en) | Pressure relief structure, battery cell, battery and electric device | |
| CN107218857A (en) | Micro missile | |
| CN115420156B (en) | Variable-power antiriot ammunition based on multi-medicine-room technology | |
| US3032978A (en) | Magnetic compression engine | |
| CN114962077A (en) | Dinitramide ammonium-based liquid single-component engine based on electric ignition mode | |
| US11953298B2 (en) | Brake arrangement for a projectile | |
| US7059249B2 (en) | Transverse plasma injector ignitor | |
| CN114909232A (en) | Solid-solid-liquid combined rocket motor and its working method and aircraft | |
| CN117365784A (en) | A multi-start solid rocket motor | |
| CN115247632A (en) | Array Type Electronically Controlled Solid Arc Microthrust | |
| CN113494386B (en) | Miniaturized multifunctional rocket engine | |
| Sinyaev et al. | Plasma-replacement technology of ETC-ignition of powder charges in high-velocity launchers | |
| CN121539405A (en) | A hybrid solid propulsion device for microsatellites | |
| CN112360710B (en) | Working medium feeding device for coaxial electrothermal plasma thruster | |
| CN115265302B (en) | A variable-power anti-riot ammunition based on electronically controlled combustion propellant | |
| CN219959317U (en) | Flue gas treatment devices, batteries and energy storage bins | |
| CN114810419A (en) | Charging configuration capable of effectively increasing combustion surface of explosive column and electric control engine | |
| US12060852B2 (en) | Electrochemical rocket motor | |
| CN119825578B (en) | Solid rocket ramjet engine arc discharge plasma combustion aid | |
| CN112179215A (en) | Flight guidance weapon control device based on plasma jet technology | |
| CN113432150B (en) | Controllable Flame Holders, Engines, and Aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant |