CN115822814A - Coaxial annular multi-electrode electric control solid thruster - Google Patents
Coaxial annular multi-electrode electric control solid thruster Download PDFInfo
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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 conventional coaxial electric control solid thruster is small in thrust adjusting range and consists of a group of central electrodes and outer electrodes. 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 the spray pipe and the power supply control module, and the inner wall of the bottom end of the shell is provided with a concentric circle type slot; the central electrode is a cylinder and is fixed at the central position in the shell through a slot; the multilayer annular electrodes are concentrically fixed in the slots of the shell by taking the central electrode as the center, the annular part between the innermost 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 electrically-controlled solid propellant in 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 sizes of all stages of combustion chambers meet the following definition so as to ensure that the electric control solid propellant in all the combustion chambers is burnt out synchronously:
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 vehicles, ships and airplanes, and can be ignited at any time according to the requirements of conditions. However, once the conventional solid space thruster is ignited to work, the conventional solid space thruster cannot be actively flamed unless fuel is exhausted and flamed out, certainly cannot be restarted, cannot be started for many times and control thrust in real time like a liquid space thruster, and can only work according to a thrust scheme determined by the grain until combustion of the grain is terminated, so that the conventional solid space thruster is difficult to realize multiple starting and thrust adjustment.
In addition, although the cold air propulsion has a slow response speed and a low specific impulse and needs to carry more working media to prolong the service life, the device has a simple structure and mature technology, so the cost is low, the risk is low, the overall cost-effectiveness ratio is relatively low, the device only has small thrust and wide range adjustment, the response speed is slow, the specific impulse is low, and the situation of space confrontation is difficult to meet.
The electric propulsion has ionization and acceleration efficiency under the condition of micro flow, has long service life and high response speed, but the charged particles generated by ionization can generate inevitable interaction with the wall surface of the thruster in work, so that the wall surface loss is increased, the efficiency is reduced, the problems of unstable discharge, flameout and the like even occur, and the requirement of high reliability is not met.
The electric control solid propellant has unique electrochemical characteristics, proper voltage is loaded at two ends of an electrode, and the propellant is ignited and continuously burnt without ignition powder; the electric field is removed, the propellant is extinguished, and the propellant can be combusted 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 high safety performance, and the propellant has obvious insensitive characteristic and is insensitive to flame and impact.
The traditional coaxial electric control solid thruster is composed of a group of central electrodes and outer electrodes, wherein the outer electrodes are processed by a metal cylinder. Because of the current density required by stable combustion of the electric control solid thrust agent, a combustion chamber formed by the central electrode and the outer electrode cannot be designed into a large-spacing structure to increase the medicine loading amount, so that the upper limit and the adjusting range of the thrust are smaller.
Disclosure of Invention
The invention provides a coaxial annular multi-electrode electric control solid thruster, aiming at the problem that the conventional coaxial electric control solid thruster is small in thrust regulation range and consists of a group of central electrodes and outer electrodes. According to the thruster designed by the invention, the outer electrode is the annular electrode which is arranged in multiple stages to form a multi-stage combustion chamber, the multi-chamber simultaneous electrification ignition can be realized through the control circuit, the upper limit of the thrust is increased on the basis of regulating the thrust by changing the power, and the regulation range of the thrust is widened.
The coaxial annular multi-electrode electric control solid thruster 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 top opening end of the shell 1 is connected with the spray pipe 2, the outside of the bottom end of the shell 1 is connected with a power supply control module 7, and the inner wall of the bottom end of the shell 1 is provided with a concentric circle type slot;
the central electrode 3 is a cylinder and is fixed at the central position inside the shell 1 through a slot;
the multilayer annular electrodes 4 are concentrically fixed in the slots of the shell 1 by taking the central electrode 3 as the center, the annular part between the innermost 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; electrically controlled solid propellant 6 is filled in each stage of combustion chamber;
each electrode penetrates through the bottom end of the shell 1 through the cylindrical guide structure and is electrically connected with the power supply control module 7;
the size of each stage of combustion chamber meets the following definition so as to ensure that the electric control solid propellant 6 in all the combustion chambers is burnt out synchronously:
in the formula (d) n The radius of the charge of the nth-stage combustion chamber is n =1,2, \ 8230;, H and H are the number of combustion chambers;
R n the outer radius of the inner electrode in the two electrodes for constructing the nth-stage combustion chamber;
j is the lower current density limit of the burner face and is expressed as:
the limiting conditions are satisfied: 7.0E-09 (A/m) 2 )＜j；
u is the working voltage of the thruster when working at the maximum power;
σ is the electrical conductivity of the propellant;
eta is the energy coefficient of the thruster;
v B a combustion rate of the propellant at maximum power for the thruster;
ρ is the density of the propellant;
P max is the maximum power of the thruster; expressed as: p max ＝ηSv B 3 ρ, wherein the total charge face area of all combustion chambers is expressed as:
preferably, the electric control solid propellant powder further comprises an insulating layer 5 which is coated on the side wall of the electrode of the combustion chamber, and the insulating layer 5 has a clearance of 1mm with the top end of the electrode, so that the electric control solid propellant powder can generate layer combustion when being electrified.
Preferably, the power supply control module 7 is fixed with the bottom opening end of the shell 1 of the thruster through a cylindrical guide structure, and the bottom opening end of the power supply control module 7 encapsulates the control circuit in the shell through the rear cover 11 made 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, H +1 spring electrodes 8 extend into 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 tightly contacted with the central electrode 3 and the bottom ends of the annular electrodes 4 of each layer through the springs 9 arranged inside to realize electric connection,
seven leading-out 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 and arranged in a regular hexagonal structure, and respectively occupy the vertex and the center of the hexagon; to mate with an aviation plug.
Preferably, the spring electrode 8 is made of copper alloy material, and the spring 9 is made of carbon nano material.
Preferably, the housing 1 of the thruster is detachably connected with the nozzle 2 by a flange or a thread.
Preferably, the housing 1 of the thruster is detachably connected with the power supply control module 7 by a flange or a thread.
Preferably, the electrically-controlled solid propellant 6 comprises an oxidant, a binder, a cross-linking agent and a propellant, and is prepared by mixing the following components in a mass fraction ratio of 2-5.
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 argil, 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. the coaxial annular multi-electrode electric control solid thruster provided by the invention has the advantages that the central electrode and the plurality of groups of annular electrodes are arranged in a multi-stage mode to form a plurality of combustion chambers, so that the power of the thruster is greatly improved;
2. the problems of single-stage structure of limited charging amount, small thrust adjusting range and low precision are solved, the charging amount can be increased by adding a multi-stage combustion chamber on the original basis, the current density of the combustion end face is ensured by reasonably distributing the sizes of all stages, the combustion efficiency is not reduced, all stages of propellants are synchronously burned out, and the control precision of the thrust is improved.
3. The invention does not need the traditional ignition device, is not sensitive to the stimulation of flame, impact and the like, can be safely transported by air transportation and other ways, keeps the combat readiness state for a long time, and has wide application prospect.
Drawings
FIG. 1 is a schematic structural diagram of a coaxial annular multi-electrode electrically-controlled solid thruster provided by the invention;
FIG. 2 is a schematic structural view of a center electrode and ring electrode configuration;
FIG. 3 is a schematic diagram of the structure of an electrode, insulation and electrically controlled solid propellant assembly;
FIG. 4 is a schematic diagram of the relationship of the sizes of the combustion chambers;
fig. 5 is a schematic view of the structure in which the spring electrode is connected to the center electrode and the ring electrode.
In the figure: the device comprises a thruster shell, a thrust device 2, a spray pipe 3, a center electrode 4, a ring electrode 5, an insulating layer 6, an electric control solid propellant 7, a power supply control module 8, a spring electrode 8, a spring 9, a control circuit 10, a rear cover 11 and a bottom electrode 12.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without inventive step based on the embodiments of the present invention, are within the scope of protection of the present invention.
It should be noted that all directional indicators (such as up, down, left, right, front, back \8230;) in the embodiments of the present invention are only used to explain the relative positional relationship between the components, the motion situation, etc. in a specific posture (as shown in the attached drawings), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; the connection can be mechanical connection, electrical connection, physical connection or wireless communication connection; they may be directly connected or indirectly connected through intervening media, or they may be interconnected within two elements or in a relationship where two elements interact with each other unless otherwise specifically limited. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.
The invention is further described with reference to the following 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, where the coaxial annular multi-electrode electronic control solid thruster includes a housing 1, a nozzle 2, a center electrode 3, an annular electrode 4, an electronic control solid propellant 6, and a power supply control module 7;
the top opening end of the shell 1 is connected with the spray pipe 2, the outside of the bottom end of the shell 1 is connected with a power supply control module 7, and the inner wall of the bottom end of the shell 1 is provided with a concentric circle type slot;
the central electrode 3 is a cylinder and is fixed at the central position inside the shell 1 through a slot;
the multilayer annular electrodes 4 are concentrically fixed in the slots of the shell 1 by taking the central electrode 3 as the center, the annular part between the innermost 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; electrically controlled solid propellant 6 is filled in each stage of combustion chamber;
each electrode penetrates through the bottom end of the shell 1 through the cylindrical guide structure and is electrically connected with the power supply control module 7;
the size of each stage of combustion chamber meets the following definition so as to ensure that the electric control solid propellant 6 in all the combustion chambers is burnt out synchronously:
in the formula (d) n The radius of the charge of the nth-stage combustion chamber is n =1,2, \ 8230;, H and H are the number of combustion chambers;
R n the outer radius of the inner electrode in the two electrodes for constructing the nth-stage combustion chamber;
j is the current of the combustion end faceLower density limit, expressed as:
the limiting conditions are satisfied: 7.0E-09 (A/m) 2 )＜j；
u is the working voltage of the thruster when working at the maximum power;
σ is the electrical conductivity of the propellant;
eta is the energy coefficient of the thruster;
v B to propel the combustion rate of the agent for the thruster at maximum power;
ρ is the density of the propellant;
P max the maximum power of the thruster; expressed as: p is max ＝ηSv B 3 ρ, wherein the total charge face area of all combustion chambers is expressed as:
further, the electric control solid propellant powder combustion chamber comprises an insulating layer 5 which 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 powder combustion chamber can generate layer combustion when being electrified.
Referring to fig. 1, a housing 1 of the thruster is detachably connected to a nozzle 2 by a flange or a screw. 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 realize the requirement of stratified combustion;
before assembly, the surface of the electrode is subjected to frosting treatment, an insulating coating 5 is sprayed on the surface of the electrode, and then plasticizing 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 methods of pouring, spraying or integral filling and the like;
the power supply control module 7 is fixed with the bottom of the thruster shell 1 through threads or a flange; the power supply control module 7 is fixed with the bottom opening end of the shell 1 of the thruster through a cylindrical guide structure, and the bottom opening end of the power supply control module 7 encapsulates a control circuit in a shell through a rear cover 11 made of insulating materials.
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, 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 annular electrodes 4 through the internally arranged springs 9 to realize electric connection, and the bottom end of the power supply control module 7 is welded with seven leading-out 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 arranged according to a regular hexagon structure, and respectively occupy the vertexes and the center of the hexagon; to mate with an aircraft plug.
The spring electrode 8 is fixed at the top of the control circuit 10 and is in contact with the central electrode 3 and the annular electrode 4 through the power supply control module 7 and the hole diameter on the thruster shell 1 to form a closed loop; the central electrode 3, the first layer of annular electrode 4, the second layer of annular electrode 4 and the third layer of annular electrode 4 are loaded with voltage according to the sequence of negative, positive, negative and positive.
The innovation point of the embodiment is that the multilayer combustion chambers are arranged, so that the charge amount 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 thrust of the engine are increased. The bottom of the shell 1 is provided with concentric multi-layer clamping grooves, the central clamping grooves are used for clamping and fixing the central electrode 3, the other clamping grooves are used for clamping and fixing the multi-layer annular electrode 4, referring to fig. 4, an annular space between the central electrode 3 and the first layer annular electrode 4 forms a 1 st-stage combustion chamber, and the charging radius of the combustion chamber is d 1 The 1 st stage combustion chamber is constructed by two electrodes, the inner electrode is a central electrode 3, and the outer radius of the central electrode 3 is R 1 The charge 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 Inner layer electrode ofThe outer radius of one layer of the ring electrode 4 is R 2 The charge end surface area of the 2 nd-stage combustion chamber is S 2 Class 3 combustion chamber charge radius is d 3 The outer radius of the second layer of the ring electrode 4 of the inner layer electrode is R 3 The charge end surface area of the 3 rd-stage combustion chamber is S 3 Taking H =3 layers of combustion chambers as an example, the total charge end surface area of the combustion chambers is S = S 1 +S 2 +S 3 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 for ignition and combustion, 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 circular groove is powered off to stop burning, and then the thruster stops generating thrust; the ignition is synchronously carried out in different times, the synchronous stop is carried out, and in order to facilitate the synchronous replacement of the electric control solid propellant 6 on all layers, each layer can be expected to be synchronously burnt out, 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, all levels of the propellant are synchronously burnt out as much as possible, the current density of the combustion end face is ensured, the combustion efficiency is improved, and the control precision of the thrust is improved.
When the power applied to each electrode is changed through the power supply control module 7, the combustion rate of the electric control solid propellant in the combustion chamber is changed, so that the thrust of the engine is changed.
The shape matching process is as follows: the surface of the positive electrode is frosted, then the insulating layer 5 is sprayed on the surface of the processed electrode, and finally the electrode is placed into a muffle furnace for plasticizing treatment. The processed electrode is inserted into an annular slot in the thruster housing 1.
And secondly, pouring the electrically-controlled solid propellant 6 slurry for complete solidification into a combustion chamber formed by the central electrode 3 and the annular electrode 4, and placing the chamber in a vacuum oven at 40 ℃ for solidification 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 thruster shell to finish the assembly of the engine.
The main working process comprises the following steps: the central electrode 3 and the annular electrode 4 are connected with the positive electrode and the negative electrode of a power supply through the spring electrode 8. The number of the annular electrodes can be increased or decreased according to the thrust requirement. The distance between the electrodes in the engine is individually designed, so that the propellant can be burnt out synchronously. When the circuit is closed, the power supply circuit 10, the central electrode 3, the annular electrode 4 and the electric control solid propellant 6 form a loop, the electric control solid propellant in the combustion chamber is electrified and combusted to generate high-temperature and high-pressure gas, and the engine is accelerated by the jet pipe to generate thrust. When the engine needs to be stopped, the control circuit 10 can realize that the connected loop is disconnected, and can realize secondary ignition when the loop is closed again, and the whole process can be repeated.
The second embodiment is as follows: the first embodiment is further limited, and the electrically-controlled solid propellant 6 comprises an oxidant, a binder, a cross-linking agent and a propellant, which are mixed and prepared according to the mass fraction ratio of 2-5.
The third concrete implementation mode: in this embodiment, the insulating layer 5 is composed of a filler 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 argil, 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 features described in different dependent claims and herein may be combined in ways different from those described in the original claims. It is also to be understood that features described in connection with individual embodiments may be used in other described embodiments.
Claims (10)
1. The coaxial annular multi-electrode electronic control solid thruster is characterized by comprising a shell (1), a spray pipe (2), a central electrode (3), an annular electrode (4), an electronic control solid propellant (6) and a power supply control module (7);
the top opening end of the shell (1) is connected with the spray pipe (2), the outside of the bottom end of the shell (1) is connected with a power supply control module (7), and the inner wall of the bottom end of the shell (1) is provided with a concentric circle type slot;
the central electrode (3) is a cylinder and is fixed at the central position inside the shell (1) through a slot;
the multilayer annular electrodes (4) are concentrically fixed in the slots of the shell (1) by taking the central electrode (3) as the center, the annular part between the innermost 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; electrically controlled solid propellant (6) is filled 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 size of each stage of combustion chamber satisfies the following formula to guarantee that the electric control solid propellant (6) in all the combustion chambers is burnt out synchronously:
in the formula (d) n The radius of the charge of the nth-stage combustion chamber is n =1,2, \ 8230;, H and H are the number of combustion chambers;
R n the outer radius of the inner electrode in the two electrodes for constructing the nth-stage combustion chamber;
j is the lower current density limit of the burner face and is expressed as:
the following limiting conditions are met: 7.0E-09 (A/m) 2 )＜j；
u is the working voltage of the thruster when working at the maximum power;
σ is the electrical conductivity of the propellant;
eta is the energy coefficient of the thruster;
v B to propel the combustion rate of the agent for the thruster at maximum power;
ρ is the density of the propellant;
P max the maximum power of the thruster; expressed as: p max ＝ηSv B 3 ρ, wherein the total charge face area of all combustion chambers is expressed as:
2. the coaxial annular multi-electrode electric control solid thruster is characterized by further comprising an insulating layer (5) coated on the side wall of the electrode of the combustion chamber, wherein the insulating layer (5) has a clearance of 1mm with the top end of the electrode, and the electric control solid thruster can generate layer combustion when being electrified.
3. The coaxial annular multi-electrode electronic control solid thruster is characterized in that a power supply control module (7) is fixed to the bottom opening end of the shell (1) of the thruster through a cylindrical guide structure, and the bottom opening end of the power supply control module (7) is sealed in a shell through a rear cover (11) made of insulating materials.
4. The coaxial annular multi-electrode electronic control solid thruster is 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 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 tightly contacted with the bottom ends of the central electrode (3) and each layer of annular electrode (4) through springs (9) arranged inside 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, wherein seven extraction electrodes (12) are arranged and arranged in a regular hexagonal structure to respectively occupy the vertexes and the center of the hexagon; to mate with an aviation plug.
6. The coaxial annular multi-electrode electronic control solid thruster is characterized in that the spring electrode (8) is made of a copper alloy material, and the spring (9) is made of a carbon nano material.
7. The coaxial ring-shaped multi-electrode electronic control solid thruster of claim 4, wherein the outer casing (1) of the thruster is detachably connected with the nozzle pipe (2) through a flange or a thread.
8. The coaxial ring-shaped multi-electrode electronically controlled solid thruster of claim 4, wherein the housing (1) of the thruster is detachably connected with the power supply control module (7) by a flange or a thread.
9. The coaxial annular multi-electrode electric control solid thruster is characterized in that the electric control solid propellant (6) comprises an oxidizer, a binder, a cross-linking agent and a propellant, which are mixed and prepared according to the mass fraction ratio of 2-5.
10. The coaxial annular multi-electrode electrically controlled solid thruster according to claim 2, wherein 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 argil, magnesium hydroxide or aluminum hydroxide; the modified resin coating is one or more of polyphenylene sulfide, polyamide, fluorocarbon resin, polyvinyl alcohol or polytetrafluoroethylene.
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080092521A1 (en) * | 2002-01-16 | 2008-04-24 | Michael Dulligan | Electrically controlled extinguishable solid propellant motors |
| US20110259230A1 (en) * | 2008-05-16 | 2011-10-27 | Sawka Wayne N | Electrode ignition and control of electrically ignitable materials |
| 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 |
-
2022
- 2022-09-23 CN CN202211166126.7A patent/CN115822814B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080092521A1 (en) * | 2002-01-16 | 2008-04-24 | Michael Dulligan | Electrically controlled extinguishable solid propellant motors |
| US20110259230A1 (en) * | 2008-05-16 | 2011-10-27 | Sawka Wayne N | Electrode ignition and control of electrically ignitable materials |
| 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 |
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| CN115822814B (en) | 2024-07-02 |
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