CN114645800A - High-thrust electric control solid thruster - Google Patents
High-thrust electric control solid thruster Download PDFInfo
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- CN114645800A CN114645800A CN202210422768.2A CN202210422768A CN114645800A CN 114645800 A CN114645800 A CN 114645800A CN 202210422768 A CN202210422768 A CN 202210422768A CN 114645800 A CN114645800 A CN 114645800A
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- negative electrode
- positive electrode
- electrode
- thruster
- thrust
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/36—Propellant charge supports
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/94—Re-ignitable or restartable rocket- engine plants; Intermittently operated rocket-engine plants
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
The invention discloses a high-thrust electric control solid thruster, belongs to the field of solid thrusters, and aims to solve the problems of small medicine loading amount and small thrust of the existing electric control solid thruster. The scheme of the invention is as follows: the front side opening end of the square shell is connected with the large opening end of the spray pipe, the positive electrode and the negative electrode are fixed in the heat insulation sleeve and integrally assembled in the inner cavity of the square shell, the positive electrode is provided with a positive terminal, and the negative electrode is provided with a negative terminal; the rear side bottom plate of the square shell is provided with two insulation through holes, and the positive terminal and the negative terminal extend out of the square shell from the two insulation through holes; the structure of the negative electrode is the same as that of the positive electrode, the negative electrode comprises a plurality of parallel straight sheets with equal intervals, the end parts of any two adjacent straight sheets are connected through arc-shaped plates, the arc-shaped plates of the negative electrode and the positive electrode are oppositely arranged on two sides, the straight sheets of the negative electrode and the positive electrode are oppositely crossed to form an equal interval staggered layout, and a gap formed by the staggered layout of the negative electrode and the positive electrode is filled with an electric control solid propellant.
Description
Technical Field
The invention relates to a high-thrust adjustable solid rocket engine capable of being started for multiple times by adopting an electric control solid propellant, belonging to the field of solid thrusters.
Background
Compared with the traditional solid thruster, the electric control solid thruster realizes the purposes of controllable starting and stopping and adjustable thrust, but the technical development of the existing electric control solid thruster is immature, has a plurality of problems and has great improvement space. The existing electric control solid thruster mainly comprises a thruster with a coaxial electrode structure and an end face combustion electrode structure.
The coaxial electric control solid thruster has small thrust, small medicine loading amount and short working time. Although the thrust of the thruster can be increased in a parallel mode, the design can increase the self weight of the thruster and reduce the charge ratio.
The end face combustion type thruster applies an electric field between two end faces of the propellant so as to control the combustion of the propellant. The disadvantage of this method of charging is that a certain space is reserved for the spring in the engine, which can greatly reduce the charging amount of the thruster, and at the same time, the spacecraft is often in an overweight or weightless state during operation, which can affect the performance of the spring, the propellant cannot be pressed against the combustion electrode, once the propellant and the combustion electrode are not in contact, the thruster will fail, and the normal operation of the spacecraft is affected.
Therefore, in view of the above disadvantages, it is desirable to provide an electrically controlled solid thruster capable of greatly increasing the charge ratio, so as to achieve the purpose of outputting a large thrust.
Disclosure of Invention
The invention provides a high-thrust electric control solid thruster, aiming at the problems of small medicine loading and small thrust of the existing electric control solid thruster.
The invention relates to a high-thrust electric control solid thruster which comprises a square shell 3, a heat insulation insulating sleeve 4, a positive terminal 5, a negative terminal 6, a negative electrode 7, a positive electrode 8, an electric control solid propellant 10 and a spray pipe 11, wherein the square shell is provided with a heat insulation insulating sleeve;
the front side opening end of the square shell 3 is connected with the large opening end of the spray pipe 11, the anode 8 and the cathode 7 are fixed in the heat insulation insulating sleeve 4 and are integrally assembled in the inner cavity of the square shell 3, the anode 8 is provided with an anode binding post 5, and the cathode 7 is provided with a cathode binding post 6;
the rear side bottom plate of the square shell 3 is provided with two insulation through holes, and the positive terminal 5 and the negative terminal 6 extend out of the square shell 3 from the two insulation through holes;
the structure of the negative electrode 7 is the same as that of the positive electrode 8, the negative electrode 7 comprises a plurality of parallel straight sheets with equal intervals, the end parts of any two adjacent straight sheets are connected through arc-shaped plates, the arc-shaped plates of the negative electrode 7 and the positive electrode 8 are oppositely arranged on two sides, the straight sheets of the negative electrode 7 and the positive electrode 8 are oppositely crossed to form an equal interval staggered layout, and a gap formed by the staggered layout of the negative electrode 7 and the positive electrode 8 is filled with an electric control solid propellant 10.
Preferably, the surface of the positive electrode 8 is frosted and the insulating coating 9 is sprayed on the surface before assembly and then plasticized in a muffle furnace.
Preferably, the heat insulating sleeve 4 is of a rectangular-like structure with one open end and one closed end, and the inner surface of the closed end plate of the heat insulating sleeve 4 is provided with a plurality of grooves adapted to the pole pieces of the negative electrode 7 and the positive electrode 8, so that the ends of the straight thin sheet and the arc-shaped plate are clamped in the grooves of the heat insulating sleeve 4.
Preferably, the insulating sheath 4 is made of asbestos material.
Preferably, a titanium alloy material is used for both the positive electrode 8 and the negative electrode 7.
Preferably, the front open end of the square housing 3 is connected to the large open end of the lance 11 by means of bolts 1.
Preferably, a sealing gasket 2 is further included, and the sealing gasket 2 is arranged between the square shell 3 and the spray pipe 11.
The invention has the beneficial effects that:
(1) the invention can realize repeated ignition and flameout by applying or withdrawing voltage, and can change the loading voltage through requirements so as to change the thrust of the thruster.
(2) The contact mode of the electrode of the end-burning thruster and the propellant grain is different, a spring supply structure is omitted, the loading capacity of the thruster is greatly increased while the stable work of the thruster is improved, and the on-orbit service life of the spacecraft can be effectively prolonged.
(3) Compared with a coaxial thruster, the thruster has more combustion areas, can provide larger thrust, can reduce the thickness of an electrode plate as much as possible, and effectively improves the charging quality ratio of the thruster.
(4) The distances between each group of electrode plates are equal, so that the combustion rate of the propellant in each combustion area is kept constant, and the working stability of the thruster is improved
Drawings
Figure 1 is a schematic plan view of an electrically controlled solid thruster according to the present invention;
FIG. 2 is a schematic diagram of the structure of an electrode;
FIG. 3 is a schematic diagram of the configuration of the positive and negative electrodes;
FIG. 4 is a schematic view of the structure of an electrode, insulating coating, propellant assembly;
FIG. 5 is a schematic view of the electrodes mounted within the insulating sheath;
in the figure: 1-bolt, 2-sealing gasket, 3-square shell, 4-heat insulation insulating sleeve, 5-positive terminal, 6-negative terminal, 7-negative, 8-positive, 9-insulating coating, 10-electric control solid propellant and 11-spray pipe;
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 derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The electric control solid thruster changes the electrode structure of the original electric control solid thruster, increases the charging amount of the propellant, improves the thrust of the thruster, and can meet more use requirements.
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
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, and the electric control solid thruster with high thrust according to the present embodiment includes a square housing 3, a heat insulation sleeve 4, a positive terminal 5, a negative terminal 6, a negative electrode 7, a positive electrode 8, an electric control solid propellant 10, and a nozzle 11;
the front side opening end of the square shell 3 is connected with the large opening end of the spray pipe 11, the anode 8 and the cathode 7 are fixed in the heat insulation sleeve 4 and are integrally assembled in the inner cavity of the square shell 3, the anode 8 is provided with an anode binding post 5, and the cathode 7 is provided with a cathode binding post 6;
the rear side bottom plate of the square shell 3 is provided with two insulation through holes, and the positive terminal 5 and the negative terminal 6 extend out of the square shell 3 from the two insulation through holes; one side of the positive terminal 5 is connected with a positive electrode, and the other side of the positive terminal is connected with a power supply positive electrode through a heat-insulating sleeve 4 extending out of the square shell 3; one side of the negative terminal 6 is connected with a negative electrode, and the other side of the negative terminal extends out of the outer side of the square shell 3 through a through hole of the heat insulation insulating sleeve 4 and is connected with a power supply negative electrode;
the structure of the negative electrode 7 is the same as that of the positive electrode 8, the negative electrode 7 comprises a plurality of parallel straight sheets with equal intervals, the end parts of any two adjacent straight sheets are connected through arc-shaped plates, the arc-shaped plates of the negative electrode 7 and the positive electrode 8 are oppositely arranged on two sides, the straight sheets of the negative electrode 7 and the positive electrode 8 are oppositely crossed to form an equal interval staggered layout, and a gap formed by the staggered layout of the negative electrode 7 and the positive electrode 8 is filled with an electric control solid propellant 10. The positive electrode 8 and the negative electrode 7 have the same structural design, and in one embodiment, the positive electrode 8 and the negative electrode 7 both comprise 5 electrode plates, and the side surfaces of the electrode plates are arc-shaped.
Before assembly, the surface of the positive electrode 8 is sanded and the insulating coating 9 is sprayed on the surface and then plasticized in a muffle furnace.
The heat insulation insulating sleeve 4 is of a similar rectangular structure with one open end and one closed end, and a plurality of grooves matched with the pole pieces of the negative pole 7 and the positive pole 8 are formed in the inner surface of the closed end plate of the heat insulation insulating sleeve 4, so that the straight thin sheet and the end part of the arc-shaped plate are clamped in the grooves of the heat insulation insulating sleeve 4. The electrically controlled solid propellant 10 is poured into the semi-closed space formed by the anode 8, the cathode 7 and the heat insulating sleeve 4 before solidification.
The heat insulation and insulation sleeve 4 is made of asbestos material.
The anode 8 and the cathode 7 are made of titanium alloy materials.
The front opening end of the square shell 3 is connected with the large opening end of the spray pipe 11 through a bolt 1.
A sealing gasket 2 is arranged between the square shell 3 and the spray pipe 11.
The electrode plates are arranged in a cross mode, electric control solid propellant is filled between the electrode plates, and the positive electrode plate is coated with an insulating coating to prevent the propellant from burning quickly. The positive and negative terminals are respectively connected with the positive and negative poles of the direct current power supply, and the combustion rate of the propellant can be controlled by adjusting the input power of the direct current power supply, so that the thrust of the thruster is controlled. The middle electrode is composed of a straight thin section and a curved surface two-section, and the straight thin section is adopted, so that the thickness is extremely small, the increase of the medicine loading amount of the thruster is facilitated, and the medicine loading ratio is improved; the distance between the straight thin electrode plates is equal, propellant between each group of electrode plates can be synchronously combusted, the design can obtain large thrust, the charging amount of the thruster is increased, the controllable working requirement of the propellant can be met, and repeated starting and adjustable thrust under a large thrust mode of the thruster are realized.
The present embodiment focuses on including two electrodes: a positive electrode 8 and a negative electrode 7. In the invention, the electrode structure of the conventional electric control solid thruster is changed, and the contact mode of the propellant and the electrode is optimized. In contrast, the thrust of the thruster is improved while the loading capacity of the thruster is improved.
The positive electrode and the negative electrode are arranged in a staggered mode, all the electrode distances are kept equal, and the mode can ensure that the burning rate of the electric control solid propellant in each unit is kept constant. The electrode structure and the arrangement mode are the improvement of the electrode structure of the original coaxial thruster, the thruster adopting the electrode arrangement mode has higher charge ratio, and simultaneously can meet the simultaneous combustion of multi-unit electronic control solid propellant and generate larger thrust.
The assembly process is as follows: firstly, the surface of the anode 8 is frosted, then the insulating coating 9 is sprayed on the surface of the treated anode 8, and finally the electrode is placed into a muffle furnace for plasticizing treatment. The electrode plates of the processed positive electrode 8 and the negative electrode 7 are mutually staggered, then the binding posts of the positive electrode 8 and the negative electrode 7 penetrate through the through holes of the heat insulation insulating layer 4, and the positive electrode 8 and the negative electrode 7 are fixed in the corresponding grooves. The composition structure is shown in fig. 3 and 5.
Next, the assembled assembly is loaded into the open end of the square housing 3.
And thirdly, pouring the uncured electric control solid propellant 10 slurry into a semi-closed space surrounded by the anode 8, the cathode 7 and the heat insulation shell 4. Curing in an oven at 35 deg.C for 7-10 days.
And finally, fixing the spray pipe 11 and the open end of the square shell 3 by using a bolt to complete the assembling of the thruster.
The main working process is as follows: the positive terminal and the negative terminal are respectively connected with the negative electrode and the positive electrode of the direct current power supply. An initial ignition voltage is set according to the thrust requirement. The electric control solid used in the invention has good conductivity, and can realize better combustion. All the electrode distances in the thruster are equal, so that the electrically-controlled solid propellant in different units can be kept to be burnt identically. The electric control solid propellant can be combusted at the same time, so that the thruster can generate huge thrust to meet more use requirements. If the thrust is adjusted according to actual conditions, the thrust can be adjusted by changing the adjusting voltage. When the thruster is required to stop, the power supply is turned off. When the voltage is loaded again, the thruster realizes secondary ignition. The whole process can be repeated.
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 various dependent claims and the features described 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 (7)
1. A high-thrust electric control solid thruster is characterized by comprising a square shell (3), a heat insulation sleeve (4), a positive terminal (5), a negative terminal (6), a negative electrode (7), a positive electrode (8), an electric control solid propellant (10) and a spray pipe (11);
the front side opening end of the square shell (3) is connected with the large opening end of the spray pipe (11), the positive electrode (8) and the negative electrode (7) are fixed in the heat insulation insulating sleeve (4) and are integrally assembled in the inner cavity of the square shell (3), the positive electrode (8) is provided with a positive terminal (5), and the negative electrode (7) is provided with a negative terminal (6);
the rear side bottom plate of the square shell (3) is provided with two insulation through holes, and the positive terminal (5) and the negative terminal (6) extend out of the square shell (3) from the two insulation through holes;
the structure of the negative electrode (7) is the same as that of the positive electrode (8), the negative electrode (7) comprises a plurality of parallel straight sheets with equal intervals, the end parts of any two adjacent straight sheets are connected through arc-shaped plates, the arc-shaped plates of the negative electrode (7) and the positive electrode (8) are oppositely arranged on two sides, the straight sheets of the negative electrode (7) and the positive electrode (8) are oppositely crossed to form an equal interval staggered layout, and a gap formed by the staggered layout of the negative electrode (7) and the positive electrode (8) is filled with an electric control solid propellant (10).
2. The high-thrust electrically-controlled solid thruster of claim 1, wherein the surface of the positive electrode (8) is sanded and an insulating coating (9) is sprayed on the surface before assembly, and then plasticized in a muffle furnace.
3. The high-thrust electric-control solid thruster of claim 1, wherein the heat-insulating sleeve (4) is of a rectangular-like structure with one open end and one closed end, and the inner surface of the closed end plate of the heat-insulating sleeve (4) is provided with a plurality of grooves corresponding to the pole pieces of the negative pole (7) and the positive pole (8), so that the ends of the straight sheets and the arc-shaped plate are clamped in the grooves of the heat-insulating sleeve (4).
4. The high-thrust electrically-controlled solid thruster of claim 1, wherein the heat-insulating sleeve (4) is made of asbestos material.
5. The high-thrust electric-control solid thruster of claim 1, wherein the positive electrode (8) and the negative electrode (7) are made of titanium alloy materials.
6. The high-thrust electric-control solid thruster of claim 1, wherein the front opening end of the square housing (3) is connected with the large opening end of the nozzle (11) through a bolt 1.
7. The electric control solid thruster with large thrust as claimed in claim 1, further comprising a sealing gasket (2), wherein the sealing gasket (2) is disposed between the square casing (3) and the nozzle (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210422768.2A CN114645800B (en) | 2022-04-21 | 2022-04-21 | High-thrust electric control solid thruster |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210422768.2A CN114645800B (en) | 2022-04-21 | 2022-04-21 | High-thrust electric control solid thruster |
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| CN114645800A true CN114645800A (en) | 2022-06-21 |
| CN114645800B CN114645800B (en) | 2023-03-24 |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106770900A (en) * | 2016-12-08 | 2017-05-31 | 中国人民解放军国防科学技术大学 | A kind of micro-sized metal particle ignition experimental rig |
| CN107587989A (en) * | 2017-10-17 | 2018-01-16 | 北京理工大学 | A kind of double state solid pulsed plasma thrusters of high efficiency |
| CN108666378A (en) * | 2018-07-11 | 2018-10-16 | 泰州隆基乐叶光伏科技有限公司 | A kind of p-type back contacts solar cell and preparation method thereof |
| CN111577483A (en) * | 2020-05-18 | 2020-08-25 | 中国人民解放军国防科技大学 | Multi-pulse solid rocket engine |
| CN112160849A (en) * | 2020-09-30 | 2021-01-01 | 内蒙动力机械研究所 | Electrode device for electric control solid rocket engine |
| CN114278463A (en) * | 2021-12-28 | 2022-04-05 | 哈尔滨工业大学 | Electric control solid thruster |
-
2022
- 2022-04-21 CN CN202210422768.2A patent/CN114645800B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106770900A (en) * | 2016-12-08 | 2017-05-31 | 中国人民解放军国防科学技术大学 | A kind of micro-sized metal particle ignition experimental rig |
| CN107587989A (en) * | 2017-10-17 | 2018-01-16 | 北京理工大学 | A kind of double state solid pulsed plasma thrusters of high efficiency |
| CN108666378A (en) * | 2018-07-11 | 2018-10-16 | 泰州隆基乐叶光伏科技有限公司 | A kind of p-type back contacts solar cell and preparation method thereof |
| CN111577483A (en) * | 2020-05-18 | 2020-08-25 | 中国人民解放军国防科技大学 | Multi-pulse solid rocket engine |
| CN112160849A (en) * | 2020-09-30 | 2021-01-01 | 内蒙动力机械研究所 | Electrode device for electric control solid rocket engine |
| CN114278463A (en) * | 2021-12-28 | 2022-04-05 | 哈尔滨工业大学 | Electric control solid thruster |
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