CN114810419B - Charging configuration capable of effectively increasing explosive column combustion surface and electric control engine - Google Patents
Charging configuration capable of effectively increasing explosive column combustion surface and electric control engine Download PDFInfo
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- CN114810419B CN114810419B CN202210473140.5A CN202210473140A CN114810419B CN 114810419 B CN114810419 B CN 114810419B CN 202210473140 A CN202210473140 A CN 202210473140A CN 114810419 B CN114810419 B CN 114810419B
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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
- F02K9/28—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants having two or more propellant charges with the propulsion gases exhausting through a common nozzle
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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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- 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
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
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- Engineering & Computer Science (AREA)
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Electrostatic Spraying Apparatus (AREA)
Abstract
The invention discloses a charging configuration for effectively increasing the combustion surface of a grain and an electric control engine, which comprise a shell, wherein the shell comprises a front end socket, a shell and a spray pipe which are sequentially connected, the front end socket, the shell and the spray pipe form a containing cavity, a front baffle and a rear baffle are arranged in the containing cavity, and the front baffle divides the containing cavity into an air source cavity and a grain storage cavity; according to the method, the electrodes and the explosive columns are arranged in the radial direction inside the engine, compared with the scheme that axial arrangement is adopted based on the end face electrodes in the same mode, the combustion area in the method is approximately equal to the side area of the electrode hollow column, the area can be designed according to the requirement of the engine, the combustion area of the explosive charge of the engine can be remarkably increased along with the increase of the axial length of the electrodes, the working pressure and the thrust of the engine are improved, and the technical problem that the combustion area and the thrust of the engine are limited by the explosive charge and the electrode configuration in the prior art is solved.
Description
Technical Field
The invention belongs to the technical field of solid rocket engines, relates to an electric control solid rocket engine, and particularly relates to a charging configuration capable of effectively increasing a charge surface and an electric control engine.
Background
The electric control solid rocket engine utilizes the electrochemical characteristics of controllable combustion and adjustable combustion speed of the electric control solid propellant, can realize the start-stop controllability and thrust adjustability of the engine, has the advantages of simple structure, safety, reliability, long-term storage and the like of the solid engine, has important application prospect and military application value, and becomes a hot spot for domestic and foreign research.
The basic composition of the electric control solid engine comprises: a shell, a spray pipe, a grain, an electrode and the like. According to the different configurations of the electrodes, the electric control solid rocket engines are mainly divided into two types: firstly, the miniature propulsion device based on the embedded electrode generates thrust of the order of micro-cattle and milli-cattle, and is mainly applied to providing power for satellites; and secondly, the engine based on the end face electrode has the thrust of tens of to hundreds of newtons, and the engine is tried to be applied to a missile attitude and orbit control system abroad due to low thrust, so that the engine cannot be applied to the missile main power in view of the current thrust level.
Factors affecting the thrust of a solid rocket engine, besides the properties of the propellant itself, such as density, specific impulse, burning rate, etc., are also the combustion area. Where the propellant performance is the same, the thrust force is proportional to the combustion area. The combustion area of the electric control solid engine is related to the configurations of the electrode and the charge, in the existing engine scheme based on the end face electrode, the charge column is in a cylindrical shape, and the charge column and the electrode are arranged along the axial direction of the engine, for example, the Chinese patent of application publication No. CN107642435A discloses an electric control solid propellant rocket engine with adjustable thrust and multiple starting, and a sixth air-sky power council paper, namely an engine model machine in electric control solid engine test verification based on positive and negative staggered spiral single-end face electrode, and the like.
The combustion area of the electric control solid engine electrode and the charging configuration is theoretically equal to the cross-sectional area of the explosive column, the existing engine explosive column supply mechanism based on the end face electrode mainly adopts a compression spring, the cross-sectional area of the electric control solid engine explosive column is limited to a small range by the self characteristics of the compression spring, and is generally not more than 100 mm-200 mm, so that the improvement of the thrust of the electric control engine is limited, and the application of the electric control solid engine explosive column is restricted.
Disclosure of Invention
Aiming at the defects existing in the prior art, the invention aims to provide a charging configuration and an electric control engine for effectively increasing the combustion surface of a grain, and solves the technical problem that the combustion area and thrust of the engine are limited by charging and electrode configuration in the prior art.
In order to solve the technical problems, the invention adopts the following technical scheme:
the utility model provides an effectively increase powder charge configuration of grain combustion face, includes the shell, the shell include preceding head, casing and spray tube that links to each other in proper order, preceding head, casing and spray tube form the appearance chamber, appearance intracavity portion be provided with preceding baffle and backplate, preceding baffle divide into air supply chamber and grain storage chamber with the appearance chamber;
the inside of the grain storage cavity is provided with a first electrode group and a second electrode group, the first electrode group comprises a first conductive plate and a plurality of first electrodes, the first electrodes are uniformly arranged and enclose a hollow column, and one end of each first electrode is fixed on the first conductive plate; the second electrode group comprises a second conductive plate and a plurality of second electrodes, the second electrodes are uniformly arranged and are surrounded into a hollow column, the radius of the hollow column surrounded by the hollow column and the radius of the hollow column surrounded by the first electrodes are equal, one end of each second electrode is fixed on the second conductive plate, the first electrodes and the second electrodes are alternately arranged to jointly surround into an electrode hollow column, and the first electrodes are not contacted with the second electrodes; the first conductive plate is fixed on the axial rear end surface of the front baffle plate, and the second conductive plate is fixed on the axial front end surface of the rear baffle plate;
the outer side of the electrode hollow column is uniformly provided with a plurality of explosive columns along the circumferential direction, the whole body formed by the electrode hollow column and the explosive columns is externally coated with an isolating film, isolating blocks are respectively arranged between the adjacent explosive columns, and the isolating film at the corresponding position of the isolating block is positioned between the isolating block and the electrode hollow column;
the isolating film divides the grain storage cavity into a driving air cavity and a combustion chamber;
the front baffle is circumferentially provided with a through hole for communicating the air source cavity and the driving air cavity, and a one-way valve is arranged in the through hole;
a first insulating ring is arranged between the explosive column and the first conducting plate; a second insulating ring is arranged between the explosive column and the second conducting plate, and the first insulating ring and the second insulating ring are respectively positioned in the isolating film and respectively press the two ends of the isolating film on the axial rear end face of the first conducting plate and the axial front end face of the second conducting plate.
The invention also comprises the following technical characteristics:
sealing layers are arranged between the first conducting plate and the front baffle plate and between the second conducting plate and the rear baffle plate.
The radial outside of first insulating ring be provided with first backing ring, the radial outside of second insulating ring be provided with the second backing ring, first backing ring and second backing ring compress tightly the front and back both ends of barrier film respectively on the outer wall of first insulating ring and second insulating ring.
The first lining ring is provided with a through hole corresponding to the through hole on the front baffle plate.
The shell is fixedly connected with the spray pipe through bolts.
The shell is provided with a pipe joint nozzle.
An electronically controlled engine comprising said charge configuration effective to increase the combustion surface of a charge.
Compared with the prior art, the invention has the beneficial technical effects that:
in the application, the first electrodes and the second electrodes are alternately arranged, the distance between the adjacent electrodes is small, only one surface of each of the first electrodes and the second electrodes is in contact with the explosive column, so that the single-sided combustion mode is adopted, compared with the structure of the explosive column between the existing inner electrode and the existing outer electrode, the current does not need to pass through the whole propellant explosive column when being electrified, only a passage is needed to be formed between the two electrodes, the passage distance formed between the first electrodes and the second electrodes is small, the formed load is small, the required power supply is small under the same voltage, and the power supply is greatly reduced.
(II) have the barrier film through the holistic outside cladding that electrode hollow column and grain formed in this application, the elastic drive grain of barrier film moves to the electrode direction, after the grain burns, when the volume increase and the pressure in drive air cavity reduce, through the pressure in air supply chamber supplementary drive air cavity, the pneumatic drive grain through the barrier film feeds, compare with the scheme that adopts spring drive grain to feed in the current scheme, the power that the grain received is even, and then the removal of grain is more steady, the contact force between grain and the electrode is also more stable, the combustion stability of engine has been ensured.
And (III) by arranging the electrode and the explosive column in the radial direction in the engine, compared with the prior art that the axial arrangement scheme is adopted based on the end face electrode, the combustion area in the engine is approximately equal to the side area of the electrode hollow column, the area can be designed according to the requirement of the engine, the combustion area of the explosive charge of the engine can be obviously increased along with the increase of the axial length of the electrode, the working pressure and the thrust of the engine are improved, and the technical problem that the combustion area and the thrust of the engine are limited by the explosive charge and the electrode configuration in the prior art is solved.
Drawings
FIG. 1 is a cross-sectional view of the overall structure of the present invention;
FIG. 2 is a partially exploded cross-sectional view of the present invention;
FIG. 3 is a schematic diagram of the overall structure of the present invention;
FIG. 4 is a schematic diagram of an assembly structure of a first electrode set and a second electrode set according to the present invention;
FIG. 5 is an enlarged view of a partial structure of the present invention;
fig. 6 is a cross-sectional view of the present invention at the housing.
The meaning of each reference numeral in the figures is: 1-shell, 2-cavity, 3-front baffle, 4-rear baffle, 5-first electrode group, 6-second electrode group, 7-explosive column, 8-isolation block, 9-isolation film, 11-one-way valve, 12-first insulating ring, 13-second insulating ring, 14-first lining ring, 15-second lining ring, 16-bolt, 17-nozzle;
101-front end enclosure, 102-shell and 103-spray pipe;
201-an air source cavity, 202-a grain storage cavity;
20201-driving air cavity, 20202-combustion chamber;
501-a first conductive plate, 502-a first electrode;
601-second conductive plate, 602-second electrode.
The following examples illustrate the invention in further detail.
Detailed Description
All parts in the present invention are known in the art, unless otherwise specified.
The following specific embodiments of the present invention are provided, and it should be noted that the present invention is not limited to the following specific embodiments, and all equivalent changes made on the basis of the technical solutions of the present application fall within the protection scope of the present invention.
Example 1:
the embodiment provides a charging configuration for effectively increasing the combustion surface of a grain, as shown in fig. 1 to 6, the charging configuration comprises a shell 1, wherein the shell comprises a front seal head 101, a shell 102 and a spray pipe 103 which are sequentially connected, the front seal head 101, the shell 102 and the spray pipe 103 form a containing cavity 2, a front baffle 3 and a rear baffle 4 are arranged in the containing cavity 2, and the front baffle 3 divides the containing cavity 2 into an air source cavity 201 and a grain storage cavity 202;
a first electrode group 5 and a second electrode group 6 are arranged in the grain storage cavity 202, the first electrode group 5 comprises a first conductive plate 501 and a plurality of first electrodes 502, the plurality of first electrodes 502 are uniformly arranged and enclose a hollow column, and one end of each first electrode 502 is fixed on the first conductive plate 501; the second electrode group 6 comprises a second conductive plate 601 and a plurality of second electrodes 602, the plurality of second electrodes 602 are uniformly arranged and are surrounded into a hollow column, the radius of the hollow column is equal to that of the hollow column surrounded by the first electrodes 501, one end of each second electrode 602 is fixed on the second conductive plate 601, the first electrodes 502 and the second electrodes 602 are alternately arranged and are surrounded into an electrode hollow column together, and the first electrodes 502 are not contacted with the second electrodes 602; the first conductive plate 501 is fixed on the axial rear end face of the front baffle 3, and the second conductive plate 601 is fixed on the axial front end face of the rear baffle 4;
a plurality of explosive columns 7 are uniformly arranged on the outer side of the electrode hollow column along the circumferential direction, an isolating film 9 is coated on the outer side of the whole body formed by the electrode hollow column and the explosive columns 7, isolating blocks 8 are respectively arranged between the adjacent explosive columns 7, and the isolating film 9 at the corresponding positions of the isolating blocks 8 is positioned between the isolating blocks 8 and the electrode hollow column;
the isolation membrane 9 divides the grain storage cavity 202 into a drive air cavity 20201 and a combustion chamber 20202;
the front baffle plate 3 is provided with a through hole 10 which is communicated with the air source cavity 201 and the driving air cavity 20201 along the circumferential direction, and a one-way valve 11 is arranged in the through hole 10;
a first insulating ring 12 is arranged between the explosive column 7 and the first conductive plate 501; a second insulating ring 13 is arranged between the explosive column 7 and the second conductive plate 601, and the first insulating ring 12 and the second insulating ring 13 are respectively positioned in the isolating membrane 9 and respectively press the two ends of the isolating membrane 9 on the axial rear end face of the first conductive plate 501 and the axial front end face of the second conductive plate 601.
In the above technical solution, the first electrodes 502 and the second electrodes 602 are alternately arranged, the distance between the adjacent electrodes is small, and only one surface of the first electrodes 502 and the second electrodes 602 is in contact with the grain 7, so that the single-sided combustion mode is adopted, compared with the existing grain structure between the inner electrode and the outer electrode, the current does not need to pass through the whole grain 7 when being electrified, only a passage is needed to be formed between the first electrodes 502 and the adjacent second electrodes 602, the passage distance between the first electrodes and the second electrodes is small, the formed load is small, the required power is small under the same voltage, and the power is greatly reduced.
The whole outer circumference formed by the electrode hollow column and the grain 7 is coated with the isolating membrane 9, the first insulating ring 12 and the second insulating ring 13 play an insulating role on the two ends of the motor hollow column and the radial periphery of the motor hollow column, meanwhile, the first insulating ring 12 and the second insulating ring 13 respectively press the two ends of the isolating membrane 9 on the axial rear end face of the first conducting plate 501 and the axial front end face of the second conducting plate 601, a local sealing structure can be formed outside the isolating membrane 9, the fuel gas in the combustion chamber 20202 is prevented from entering the air source cavity 201 and the driving air cavity 20201, the elastic driving grain 7 of the isolating membrane moves towards the electrode direction (namely moves along the radial direction), the pressure of the driving air cavity 20201 is gradually thinned after the grain 7 begins to burn, the volume of the driving air cavity 20201 is increased due to the radial compression effect of the isolating membrane 9, and the pressure is reduced due to the fact that the air source cavity 201 is filled with high-pressure gas in advance, and the high-pressure gas is introduced into the driving air cavity 01 from the through hole 10 and the one-way valve 11 in real time during the combustion process of the grain 7, so that the air source cavity 01 is driven in real time, the air cavity 20201 is prevented from entering the air source cavity 201, the elastic driving grain 7 is prevented from entering the air cavity, the elastic driving air 7, and the elastic driving grain 7 moves towards the direction along the radial direction, and the direction, so that the compressed and the grain 2029 is driven along the radial direction; compared with the scheme of adopting a spring to drive the grain to feed in the prior scheme, the driving force born by the grain 7 is uniform, so that the movement of the grain is stable, the contact force between the grain and the electrode is stable, the combustion stability of the engine is ensured, and full combustion is realized.
By arranging the electrodes and the explosive columns in the radial direction in the engine, compared with the prior art that the axial arrangement is adopted based on the end face electrode, the combustion area in the method is approximately equal to the side area of the electrode hollow column, the area can be designed according to the requirement of the engine, the combustion area of the explosive charge of the engine can be remarkably increased along with the increase of the axial length of the electrode, the working pressure and the thrust of the engine are improved, and the technical problem that the combustion area and the thrust of the engine are limited by the explosive charge and the electrode configuration in the prior art is solved.
Specifically, sealing layers are respectively arranged between the first conductive plate 501 and the front baffle 3 and between the second conductive plate 601 and the rear baffle 4, and can be specifically realized by smearing sealant, so that a sealing effect between the air source cavity 201 and the grain storage cavity 202 is realized.
Specifically, a first liner ring 14 is disposed radially outside the first insulating ring 12, a second liner ring 15 is disposed radially outside the second insulating ring 13, and the first liner ring 14 and the second liner ring 15 respectively press the front and rear ends of the isolation film 9 against the outer walls of the first insulating ring 12 and the second insulating ring 13.
In the above structural design, the front end and the rear end of the isolation film 9 are respectively pressed on the outer side walls of the first insulating ring 12 and the second insulating ring 13 by the first lining ring 14 and the second lining ring 15, so that the tightness of the driving air cavity 20201 is further enhanced, and the gas in the combustion chamber 20202 is prevented from entering the gas source cavity 201 and the driving air cavity 20201.
Specifically, the first liner ring 14 is provided with a through hole corresponding to the through hole 10 in the front barrier 3. This structural design ensures the communication of the air supply chamber 201 with the drive air chamber 20201, ensuring that the high pressure air of the air supply chamber 201 can flow into the drive air chamber 20201.
Specifically, the shell 102 and the spray pipe 103 are fixedly connected through the bolts 16, and the bolt connection is simple and convenient.
Specifically, the casing 102 is provided with a pipe joint 17, and the pipe joint 17 is provided for the lead wires of the first electrode and the second electrode to pass out.
Example 2:
an electronically controlled engine includes a charge configuration effective to increase the charge face.
Claims (7)
1. The utility model provides an effectively increase powder charge configuration of grain combustion face, includes shell (1), the shell include preceding head (101), casing (102) and spray tube (103) that link to each other in proper order, preceding head (101), casing (102) and spray tube (103) form appearance chamber (2), its characterized in that, appearance chamber (2) inside be provided with preceding baffle (3) and backplate (4), preceding baffle (3) divide into air supply chamber (201) and grain storage chamber (202) with appearance chamber (2);
a first electrode group (5) and a second electrode group (6) are arranged in the grain storage cavity (202), the first electrode group (5) comprises a first conductive plate (501) and a plurality of first electrodes (502), the plurality of first electrodes (502) are uniformly arranged and enclose a hollow column, and one end of each first electrode (502) is fixed on the first conductive plate (501); the second electrode group (6) comprises a second conductive plate (601) and a plurality of second electrodes (602), the plurality of second electrodes (602) are uniformly arranged and are surrounded into a hollow column, the radius of the hollow column surrounded by the hollow column and the radius of the hollow column surrounded by the first electrodes (502) are equal, one end of each second electrode (602) is fixed on the second conductive plate (601), the first electrodes (502) and the second electrodes (602) are alternately arranged to jointly surround into an electrode hollow column, and the first electrodes (502) are not contacted with the second electrodes (602); the first conductive plate (501) is fixed on the axial rear end face of the front baffle plate (3), and the second conductive plate (601) is fixed on the axial front end face of the rear baffle plate (4);
a plurality of medicine columns (7) are uniformly arranged on the outer side of the electrode hollow column along the circumferential direction, an isolating film (9) is coated on the outer side of the whole body formed by the electrode hollow column and the medicine columns (7), isolating blocks (8) are respectively arranged between the adjacent medicine columns (7), and the isolating film (9) at the corresponding position of each isolating block (8) is positioned between each isolating block (8) and the electrode hollow column;
the isolating film (9) divides the grain storage cavity (202) into a driving air cavity (20201) and a combustion chamber (20202);
the front baffle (3) is circumferentially provided with a through hole (10) communicated with the air source cavity (201) and the driving air cavity (20201), and a one-way valve (11) is arranged in the through hole (10);
a first insulating ring (12) is arranged between the explosive column (7) and the first conducting plate (501); a second insulating ring (13) is arranged between the explosive column (7) and the second conducting plate (601), and the first insulating ring (12) and the second insulating ring (13) are respectively positioned in the isolating membrane (9) and respectively press two ends of the isolating membrane (9) on the axial rear end face of the first conducting plate (501) and the axial front end face of the second conducting plate (601).
2. A charge configuration effective to increase the charge surface as defined in claim 1 wherein a sealing layer is provided between said first conductive plate (501) and said front baffle (3) and between said second conductive plate (601) and said rear baffle (4).
3. A charge configuration for effectively enlarging a charge face as claimed in claim 1, wherein a first liner ring (14) is provided radially outside of said first insulating ring (12), a second liner ring (15) is provided radially outside of said second insulating ring (13), and said first liner ring (14) and said second liner ring (15) respectively press front and rear ends of said isolation diaphragm (9) against outer walls of said first insulating ring (12) and said second insulating ring (13).
4. A charge configuration effective to enlarge the charge face as claimed in claim 3, wherein said first collar (14) is provided with through holes corresponding to the through holes (10) of the front baffle (3).
5. A charge configuration effective to enlarge the charge face as defined in claim 1 wherein said housing (102) and said nozzle (103) are fixedly connected by bolts (16).
6. A charge configuration effective to enlarge a charge face according to claim 1, wherein said housing (102) is provided with a mouthpiece (17).
7. An electronically controlled engine comprising a charge configuration according to any one of claims 1 to 6 effective to increase the charge face of a charge.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210473140.5A CN114810419B (en) | 2022-04-29 | 2022-04-29 | Charging configuration capable of effectively increasing explosive column combustion surface and electric control engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210473140.5A CN114810419B (en) | 2022-04-29 | 2022-04-29 | Charging configuration capable of effectively increasing explosive column combustion surface and electric control engine |
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| Publication Number | Publication Date |
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| CN114810419A CN114810419A (en) | 2022-07-29 |
| CN114810419B true CN114810419B (en) | 2023-06-09 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210473140.5A Active CN114810419B (en) | 2022-04-29 | 2022-04-29 | Charging configuration capable of effectively increasing explosive column combustion surface and electric control engine |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1192284A (en) * | 1968-04-26 | 1970-05-20 | Aerojet General Co | Rocket Motor |
| CA2018999A1 (en) * | 1989-07-07 | 1991-01-07 | Don L. Berchtold | Precision controlled variable thrust solid propellant rocket motor |
| CN103967653A (en) * | 2014-04-28 | 2014-08-06 | 北京航空航天大学 | Axial injection end combustion solid-liquid rocket engine structure |
| CN108843462A (en) * | 2018-04-28 | 2018-11-20 | 西北工业大学 | It is classified pressurized combustion solid propellant rocket |
| CN110596301A (en) * | 2019-10-14 | 2019-12-20 | 西安近代化学研究所 | Test engine and test method for combustion of double-base propellant in different overload directions |
| CN114320662A (en) * | 2022-01-06 | 2022-04-12 | 中国人民解放军国防科技大学 | Wide-speed-range high-power-driven air-breathing combined propulsion power system and missile |
-
2022
- 2022-04-29 CN CN202210473140.5A patent/CN114810419B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1192284A (en) * | 1968-04-26 | 1970-05-20 | Aerojet General Co | Rocket Motor |
| CA2018999A1 (en) * | 1989-07-07 | 1991-01-07 | Don L. Berchtold | Precision controlled variable thrust solid propellant rocket motor |
| CN103967653A (en) * | 2014-04-28 | 2014-08-06 | 北京航空航天大学 | Axial injection end combustion solid-liquid rocket engine structure |
| CN108843462A (en) * | 2018-04-28 | 2018-11-20 | 西北工业大学 | It is classified pressurized combustion solid propellant rocket |
| CN110596301A (en) * | 2019-10-14 | 2019-12-20 | 西安近代化学研究所 | Test engine and test method for combustion of double-base propellant in different overload directions |
| CN114320662A (en) * | 2022-01-06 | 2022-04-12 | 中国人民解放军国防科技大学 | Wide-speed-range high-power-driven air-breathing combined propulsion power system and missile |
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| Publication number | Publication date |
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| CN114810419A (en) | 2022-07-29 |
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