CN114278463A - Electric control solid thruster - Google Patents
Electric control solid thruster Download PDFInfo
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- CN114278463A CN114278463A CN202111628353.2A CN202111628353A CN114278463A CN 114278463 A CN114278463 A CN 114278463A CN 202111628353 A CN202111628353 A CN 202111628353A CN 114278463 A CN114278463 A CN 114278463A
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Abstract
The invention discloses an electric control solid thruster, belongs to the field of special solid propellant rocket engines, and aims to solve the problem of unstable thrust control of an existing end face combustion type thruster. The scheme of the invention is as follows: the square ring electrode comprises four electrode plates and a square fixing frame, and the four electrode plates enclose a square area which is adjustable in size and is axially transparent; the combustion electrode fixing sleeve is provided with a circular notch, the combustion electrode is clamped at the circular notch, and the circular notch is filled up by plugging with an electrode pressing sheet; the tail end of the electric control solid propellant grain penetrates through a square area formed by the four electrode plates and is propped against the end face of the combustion electrode, and an axial working gap is formed between the square annular electrode and the combustion electrode.
Description
Technical Field
The invention relates to a rocket engine which adopts an electric control solid propellant and has adjustable thrust and can be started for multiple times, belonging to the field of special solid propellant rocket engines.
Background
The electric control solid thruster realizes the controllable starting and stopping of the rocket and the adjustable thrust, but the existing electric control solid thruster has a plurality of problems. The existing electric control solid thruster mainly comprises a thruster with a coaxial electrode structure and an end face combustion electrode structure.
The coaxial micro thruster has small thrust, small medicine loading amount and short working time. The thrust of the thruster can be increased in a parallel mode, but the self weight of the thruster can be increased at the same time.
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 approach is that the initial ignition power required increases as the initial length of propellant increases. With the continuous combustion of the propellant, the length of the propellant is also continuously changed, so that the resistance value of the propellant is continuously changed, the current flowing through the propellant is continuously changed, and finally the combustion of the propellant is unstable.
Therefore, in response to the above deficiencies, it is desirable to provide a device capable of accurately controlling thrust that provides a stable resistance parameter for control even if the propellant burns causing a change in its length.
Disclosure of Invention
Aiming at the problem that the thrust control of the existing end face combustion type thruster is unstable, the invention provides the electric control solid thruster, which adopts a unique electrode structure to keep the resistance of a propellant between two electrodes unchanged and improve the precision of the thrust control.
The invention relates to an electric control solid thruster, which comprises a shell 1, a heat insulation insulating sleeve 2, an electrode pressing sheet 3, a combustion electrode fixing sleeve 4, a combustion electrode 5, a spray pipe 6, a square annular electrode, an electric control solid propellant grain 9, a propellant grain push plate 10, a supply spring 11, a front seal head baffle 13 and a front seal head 14, wherein the shell is provided with a heat insulation insulating sleeve 2;
the square ring-shaped electrode comprises four electrode plates 7 and a square fixing frame 8, the square fixing frame 8 is a conductive part, and the four electrode plates 7 are symmetrically arranged on the square fixing frame 8; the suspended ends of the electrode plates 7 are inclined towards the central shaft and are provided with arc-shaped contact surfaces, and the four electrode plates 7 are enclosed into a square area with adjustable size and through axial direction;
the shell 1 is of a structure with openings at two ends, a combustion electrode fixing sleeve 4 is arranged at the tail end of an inner cavity of the shell 1, an annular gap is formed in the combustion electrode fixing sleeve 4, a combustion electrode 5 is clamped at the annular gap, and the annular gap is filled by plugging of an electrode pressing sheet 3;
the heat insulation insulating sleeve 2 and the combustion electrode fixing sleeve 4 are coaxially arranged in parallel in the inner cavity of the shell 1, and the inner cavities of the two are communicated; the tail end of the heat insulation insulating sleeve 2 is provided with an electrode mounting groove 2-1 with a square section, a square fixing frame 8 is clamped in the electrode mounting groove 2-1, the tail end of an electric control solid propellant grain 9 penetrates through a square area surrounded by four electrode plates 7 and is pressed on the end surface of the combustion electrode 5, the electric control solid propellant grain 9 is of a square structure, and the tail ends of the four electrode plates 7 are respectively contacted with four side surfaces of the electric control solid propellant grain 9;
an axial working gap is formed between the square annular electrode and the combustion electrode 5;
the inner end surface of the front end enclosure baffle 13 is fixed with the head end of the supply spring 11, the tail end of the supply spring 11 is fixed with the propellant grain push plate 10, and the propellant grain push plate 10 is pressed against the head end of the electric control solid propellant grain 9;
the front end enclosure 14 is buckled outside the front end enclosure baffle 13 and is fixedly connected with the head end of the shell 1;
the end of the housing 1 is fixedly connected with the large opening of the spray pipe 6.
Preferably, the electrode plate 7 is fixed on the square fixing frame 8 through a stud, and the electrode plate 7 rotates around the stud to adjust the size of the enclosed square area so as to fill the electric control solid propellant grains 9 with different sizes.
Preferably, a square ring electrode post 12 and a combustion electrode post 15 are also included;
the heat insulation insulating sleeve 2 is provided with a first axial through hole 2-2, a first through hole communicated with the front end enclosure baffle 13 and the front end enclosure 14 is arranged at the corresponding position, and the square ring-shaped electrode binding post 12 sequentially penetrates through the first through hole corresponding to the front end enclosure 14, the first through hole corresponding to the front end enclosure baffle 13 and the first axial through hole 2-2 and is connected with the square fixing frame 8 of the square ring-shaped electrode;
the heat insulation insulating sleeve 2 is provided with a second axial through hole 2-3, the corresponding positions of the front end enclosure baffle 13, the front end enclosure 14 and the electrode pressing sheet 3 are provided with a second through hole communicated with the front end enclosure baffle 13, the front end enclosure 14 and the electrode pressing sheet 3, and the combustion electrode binding post 15 sequentially penetrates through the second through hole corresponding to the front end enclosure 14, the second through hole corresponding to the front end enclosure baffle 13, the second axial through hole 2-3 and the through hole corresponding to the electrode pressing sheet 3 and is connected with the combustion electrode 5.
Preferably, the combustion electrode 5 is a plate hole electrode.
Preferably, the heat insulating and insulating sleeve 2 is made of heat insulating ceramic material.
The invention has the beneficial effects that:
(1) the invention can realize repeated ignition and flameout by applying or removing voltage, and can change the loading voltage according to requirements so as to change the thrust of the thruster. The novel electrode structure can keep the resistance of the propellant between the electrodes unchanged, and can effectively improve the precision of thrust control.
(2) The contact mode of the electrode of the conventional electric control solid thruster and the propellant grain is changed.
(3) The design of the combustion electrode is optimized, the contact area is reduced, the current density is improved, the ignition power is reduced, and the propellant is more stably combusted.
(4) The wiring terminal of the electrode is embedded into the heat insulation sleeve, so that the ablation effect of high-temperature gas generated by propellant combustion on a circuit is reduced, and the service life of the thruster is prolonged.
Drawings
FIG. 1 is a schematic plan view of an electrically controlled solid thruster according to the present invention;
FIG. 2 is a schematic plan view of a square ring electrode;
FIG. 3 is a schematic plan view of the insulating sleeve;
FIG. 4 is a schematic view of a configuration in which the combustion electrode is mounted in the housing;
FIG. 5 is a schematic view of a square ring electrode mounted within a housing;
figure 6 is a schematic view of the assembly of a square ring electrode, a combustion electrode and an electrically controlled solid propellant charge.
In the figure: 1-a shell; 2-heat insulation and insulation sleeve; 3-electrode tabletting; 4-combustion electrode fixing sleeve; 5-a combustion electrode; 6-spraying a pipe; 7-electrode slice; 8-electrode plate fixing sleeve; 9-electrically controlled solid propellant grains; 10-propellant grain push plate; 11-supply spring; 12-a square ring electrode post; 13-front head baffle; 14-front end enclosure; 15-combustion electrode terminal.
2-1, mounting a groove on the electrode; 2-2, a first axial through hole; 2-3 and a second axial through hole.
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.
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 6, and the electric control solid thruster in the present embodiment includes a casing 1, a heat insulation insulating sleeve 2, an electrode pressing sheet 3, a combustion electrode fixing sleeve 4, a combustion electrode 5, a nozzle 6, a square annular electrode, an electric control solid propellant grain 9, a propellant grain pushing plate 10, a supply spring 11, a front seal head baffle 13, and a front seal head 14;
the square ring-shaped electrode comprises four electrode plates 7 and a square fixing frame 8, the square fixing frame 8 is a conductive part, and the four electrode plates 7 are symmetrically arranged on the square fixing frame 8; the suspended ends of the electrode plates 7 are inclined towards the central shaft and are provided with arc-shaped contact surfaces, and the four electrode plates 7 are enclosed into a square area with adjustable size and through axial direction;
the shell 1 is of a structure with openings at two ends, a combustion electrode fixing sleeve 4 is arranged at the tail end of an inner cavity of the shell 1, an annular gap is formed in the combustion electrode fixing sleeve 4, a combustion electrode 5 is clamped at the annular gap, and the annular gap is filled by plugging of an electrode pressing sheet 3;
the heat insulation insulating sleeve 2 and the combustion electrode fixing sleeve 4 are coaxially arranged in parallel in the inner cavity of the shell 1, and the inner cavities of the two are communicated; the tail end of the heat insulation insulating sleeve 2 is provided with an electrode mounting groove 2-1 with a square section, a square fixing frame 8 is clamped in the electrode mounting groove 2-1, the tail end of an electric control solid propellant grain 9 penetrates through a square area surrounded by four electrode plates 7 and is pressed on the end surface of the combustion electrode 5, the electric control solid propellant grain 9 is of a square structure, and the tail ends of the four electrode plates 7 are respectively contacted with four side surfaces of the electric control solid propellant grain 9;
an axial working gap is formed between the square annular electrode and the combustion electrode 5;
the inner end surface of the front end enclosure baffle 13 is fixed with the head end of the supply spring 11, the tail end of the supply spring 11 is fixed with the propellant grain push plate 10, and the propellant grain push plate 10 is pressed against the head end of the electric control solid propellant grain 9;
the front end enclosure 14 is buckled outside the front end enclosure baffle 13 and is fixedly connected with the head end of the shell 1;
the end of the housing 1 is fixedly connected with the large opening of the spray pipe 6.
The electric control solid thruster changes the electrode structure of the original electric control solid thruster, improves the combustion stability of the propellant, and simultaneously improves the working controllability of the thruster. The combustion mode that annular electrode contact and end face combustion are combined is adopted, so that the length of the propellant between the electrodes is kept constant, and the resistance between the two electrodes is kept constant when the thruster works. When voltage is applied, it is ensured that the magnitude of the generated thrust remains constant. When the voltage is adjusted, the linear relation between the voltage and the thrust is utilized to realize accurate adjustment of the thrust.
The present embodiment focuses on including two electrodes: the combustion electrode 5 and square ring electrode, wherein the combustion electrode 5 is located the terminal of automatically controlled solid propellant powder column 9, and automatically controlled solid propellant powder column 9 is in the combustion chamber, and under the effect of supply spring 11 pretension, the terminal surface of combustion electrode 5 keeps the close contact with combustion electrode 5 all the time.
The square annular electrode comprises four electrode plates 7 and a square fixing frame 8, the electrode plates 7 are all inclined inwards, and arc-shaped contact surfaces at the tail ends of the four electrode plates 7 respectively press one side surface of an electric control solid propellant grain 9, so that the electric control solid propellant grain is tangent to the side surfaces of electric control solid propellants with different sizes, relative sliding between the electric control solid propellant grains and the electric control solid propellant grains is facilitated, and the sliding resistance of the propellant is reduced. The electrode plate 7 is fixed on the square fixing frame 8 through a stud, and the electrode plate 7 can rotate around the stud to adjust the size of the enclosed square area so as to fill the electric control solid propellant grains 9 with different sizes. The electrically-controlled solid propellant grain 9 is in a cuboid shape, and the transverse section of the electrically-controlled solid propellant grain is square.
Because square mount 8 is electrically conductive parts, four electrode slices 7 and square mount 8 electric intercommunication each other constitute an electrode jointly: and a square ring electrode.
A certain axial distance is reserved between the combustion electrode 5 and the square annular electrode, once the size of the filled electric control solid propellant grain 9 is fixed, the axial distance between the two electrodes is kept constant, the length of the propellant between the two electrodes is ensured to be constant, the resistance is constant, and the thrust output adjustment of the thruster is not influenced by the combustion length change of the propellant.
Further, the fuel cell comprises a square ring electrode binding post 12 and a combustion electrode binding post 15 which are respectively connected with the square ring electrode and the combustion electrode 5.
The assembly process is as follows: firstly, a combustion electrode 5 is arranged in an annular gap of a combustion electrode fixing sleeve 4, then an electrode pressing sheet 3 is arranged, the through hole is aligned with a combustion electrode binding post, and the combustion electrode binding post 15 is connected, so that the composition structure is shown in figure 4.
Secondly, the square annular electrode is assembled, after the wiring hole is aligned with the through hole in the heat insulation insulating sleeve 2, the square annular electrode is fixed into the electrode mounting groove 2-1 of the heat insulation insulating sleeve 2, then the wiring terminal 12 of the square annular electrode is inserted, and the assembled structure slides into the shell 1 from the head end of the shell 1 until the heat insulation insulating sleeve 2 is contacted with the combustion electrode fixing sleeve 4.
Thirdly, inserting the electrically-controlled solid propellant grain 9 from the middle of the square annular electrode to be pressed on the end surface of the combustion electrode 5;
then, the front end enclosure baffle 13, the supply spring 11 and the propellant grain push plate 10 are assembled and fixed together and are arranged in the shell 1, the propellant grain push plate 10 is contacted with the electric control solid propellant grains 9, and the supply spring 11 applies pretightening force to the electric control solid propellant grains 9;
and finally, welding the front seal head 14 with the head end of the shell 1, and welding the spray pipe 6 with the tail end of the shell 1 to complete the assembling of the thruster.
The main working process is as follows: the square ring electrode and the combustion electrode 5 are respectively connected with the negative pole and the positive pole of a direct current power supply. An initial ignition voltage is set according to the thrust requirement. The distance between the square annular electrode and the combustion electrode 5 is kept unchanged, the length of the propellant between the electrodes is kept constant, and then the resistance of the propellant is kept constant after the thruster enters stable work, so that the burning speed of the propellant is kept constant, and the stable control of the thrust of the thruster is realized. 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.
The second embodiment is as follows: the present embodiment will be described with reference to fig. 2, and the combustion electrode 5 is a plate hole electrode in the first embodiment. The combustion electrode 5 is provided with a plurality of exhaust holes, which is beneficial to the discharge of high-temperature gas generated by the combustion of the electric control solid propellant.
The combustion electrode is fixed by electrode preforming 3 and combustion electrode fixed cover 4, optimizes the combustion electrode structure in the past, increases the electrode hole diameter, reduces the interval between the hole, reduces the area of contact with the propellant, reduces the ignition power of propellant.
As an embodiment, the electrode hole diameter of the combustion electrode (5) is 2mm, and the distance between holes is 0.7 mm.
The third concrete implementation mode: the present embodiment will be described with reference to fig. 2, and the present embodiment will further describe the first embodiment in which a heat insulating ceramic material is used for the heat insulating sheath 2.
The heat insulation insulating sleeve 2 is used for isolating high-temperature gas in the combustion chamber and current of the binding post, and plays a role in protecting other parts of the thruster. The outermost layer of the thruster is a shell 1, and the spray pipe 6 is arranged at the other end and directly welded with the shell 1.
The insulating integrated design is adopted, the independent design structure of the prior insulating layer and the insulating layer is simplified, and the groove and the through hole are formed in the insulating integrated design structure and are used for fixing the electrode plate fixing sleeve 4 and the protective electrode binding post. The heat insulation ceramic material is adopted, on one hand, heat generated by propellant combustion is isolated, the shell and the binding post embedded in the shell are protected, on the other hand, electrified elements such as the binding post, an electrode and the like are insulated, and other parts of the thruster are prevented from being electrified.
The heat insulation insulating sleeve 2 is provided with a first axial through hole 2-2, a first through hole communicated with the front end enclosure baffle 13 and the front end enclosure 14 is arranged at the corresponding position, and the square ring-shaped electrode binding post 12 sequentially penetrates through the first through hole corresponding to the front end enclosure 14, the first through hole corresponding to the front end enclosure baffle 13 and the first axial through hole 2-2 and is connected with the square fixing frame 8 of the square ring-shaped electrode;
the heat insulation insulating sleeve 2 is provided with a second axial through hole 2-3, the corresponding positions of the front end enclosure baffle 13, the front end enclosure 14 and the electrode pressing sheet 3 are provided with a second through hole communicated with the front end enclosure baffle 13, the front end enclosure 14 and the electrode pressing sheet 3, and the combustion electrode binding post 15 sequentially penetrates through the second through hole corresponding to the front end enclosure 14, the second through hole corresponding to the front end enclosure baffle 13, the second axial through hole 2-3 and the through hole corresponding to the electrode pressing sheet 3 and is connected with the combustion electrode 5.
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 (5)
1. An electric control solid thruster is characterized by comprising a shell (1), a heat insulation insulating sleeve (2), an electrode pressing sheet (3), a combustion electrode fixing sleeve (4), a combustion electrode (5), a spray pipe (6), a square annular electrode, an electric control solid propellant grain (9), a propellant grain push plate (10), a supply spring (11), a front seal head baffle (13) and a front seal head (14);
the square ring-shaped electrode comprises four electrode plates (7) and a square fixing frame (8), the square fixing frame (8) is a conductive part, and the four electrode plates (7) are symmetrically arranged on the square fixing frame (8); the suspended ends of the electrode plates (7) are inclined towards the central shaft and are provided with arc-shaped contact surfaces, and the four electrode plates (7) enclose a square area with adjustable size and axial permeability;
the shell (1) is of a structure with openings at two ends, a combustion electrode fixing sleeve (4) is arranged at the tail end of an inner cavity of the shell (1), an annular gap is formed in the combustion electrode fixing sleeve (4), a combustion electrode (5) is clamped at the annular gap, and the annular gap is filled by plugging of an electrode pressing sheet (3);
the heat insulation insulating sleeve (2) and the combustion electrode fixing sleeve (4) are arranged in parallel and coaxially in the inner cavity of the shell (1), and the inner cavities of the two are communicated; the tail end of the heat insulation insulating sleeve (2) is provided with an electrode mounting groove (2-1) with a square section, a square fixing frame (8) is clamped in the electrode mounting groove (2-1), the tail end of an electric control solid propellant grain (9) penetrates through a square area surrounded by four electrode plates (7) and is propped against the end surface of a combustion electrode (5), the electric control solid propellant grain (9) is of a square structure, and the tail ends of the four electrode plates (7) are respectively contacted with four side surfaces of the electric control solid propellant grain (9);
an axial working gap is formed between the square annular electrode and the combustion electrode (5);
the inner end surface of the front end enclosure baffle (13) is fixed with the head end of the supply spring (11), the tail end of the supply spring (11) is fixed with the propellant grain push plate (10), and the propellant grain push plate (10) is pressed against the head end of the electric control solid propellant grain (9);
the front seal head (14) is buckled outside the front seal head baffle (13) and is fixedly connected with the head end of the shell (1);
the tail end of the shell (1) is fixedly connected with the large opening of the spray pipe (6).
2. The electric control solid thruster of claim 1, wherein the electrode plate (7) is fixed on the square fixing frame (8) through a stud, and the electrode plate (7) can rotate around the stud to adjust the size of the enclosed square area so as to fill electric control solid propellant grains (9) with different sizes.
3. The electrically controlled solid thruster of claim 1, further comprising a square ring electrode post (12) and a combustion electrode post (15);
the heat insulation insulating sleeve (2) is provided with a first axial through hole (2-2), a first through hole communicated with the front seal head baffle (13) and the front seal head (14) is arranged at a corresponding position, and the square ring-shaped electrode binding post (12) sequentially penetrates through the first through hole corresponding to the front seal head (14), the first through hole corresponding to the front seal head baffle (13) and the first axial through hole (2-2) and is connected with the square fixing frame (8) of the square ring-shaped electrode;
the heat insulation insulating sleeve (2) is provided with a second axial through hole (2-3), the corresponding positions of the front end enclosure baffle plate (13), the front end enclosure (14) and the electrode pressing sheet (3) are provided with a second through hole communicated with the front end enclosure baffle plate, and the combustion electrode binding post (15) sequentially penetrates through the second through hole corresponding to the front end enclosure (14), the second through hole corresponding to the front end enclosure baffle plate (13), the second axial through hole (2-3) and the through hole corresponding to the electrode pressing sheet (3) and is connected with the combustion electrode (5).
4. The electrically controlled solid thruster of claim 1, wherein the combustion electrode (5) is a plate hole electrode.
5. The electrically controlled solid thruster of claim 1, wherein the heat insulating and insulating sleeve (2) is made of a heat insulating ceramic material.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111628353.2A CN114278463A (en) | 2021-12-28 | 2021-12-28 | Electric control solid thruster |
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| CN202111628353.2A CN114278463A (en) | 2021-12-28 | 2021-12-28 | Electric control solid thruster |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114645800A (en) * | 2022-04-21 | 2022-06-21 | 哈尔滨工业大学 | High-thrust electric control solid thruster |
| CN114991999A (en) * | 2022-05-31 | 2022-09-02 | 西安近代化学研究所 | Electric ignition device without pyrotechnic compound |
| CN115822814A (en) * | 2022-09-23 | 2023-03-21 | 哈尔滨工业大学 | Coaxial annular multi-electrode electric control solid thruster |
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| CN115822814A (en) * | 2022-09-23 | 2023-03-21 | 哈尔滨工业大学 | Coaxial annular multi-electrode electric control solid thruster |
| CN115822814B (en) * | 2022-09-23 | 2024-07-02 | 哈尔滨工业大学 | Coaxial annular multi-electrode electric control solid thruster |
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