CN110195665B - Rechargeable gas storage type solid propellant power device - Google Patents
Rechargeable gas storage type solid propellant power device Download PDFInfo
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- CN110195665B CN110195665B CN201910541656.7A CN201910541656A CN110195665B CN 110195665 B CN110195665 B CN 110195665B CN 201910541656 A CN201910541656 A CN 201910541656A CN 110195665 B CN110195665 B CN 110195665B
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- storage chamber
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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
- F02K9/24—Charging rocket engines with solid propellants; Methods or apparatus specially adapted for working solid propellant charges
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- Combustion & Propulsion (AREA)
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- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention relates to a rechargeable gas storage type solid propellant power device, and belongs to the technical field of solid rocket engines and solid fuel gas generators. The invention adopts the following technical approaches. Firstly, pulse pressurization is adopted: the multistage pulse grains are used for continuous filling and combustion without stopping the combustion process. Secondly, the gas storage link is increased: the charging combustion process and the spray pipe exhaust work-doing process are separated and are independent respectively. The charge combustion is only used for pressurizing the gas storage tank, and does not need to exhaust simultaneously; the work done by exhaust makes the working medium and energy come from the gas storage tank, at this time, it is no longer necessary to charge and burn at the same time. The invention changes the traditional combustion-release process into the combustion-gas storage-release process, and can well solve the problem caused by difficult interruption of the combustion process of the solid propellant. The invention combines two technical approaches of gas storage link and pulse pressurization, and really realizes the active startup and shutdown and repeated startup of the solid propellant power device.
Description
Technical Field
The invention relates to a rechargeable gas storage type solid propellant power device, and belongs to the technical field of solid rocket engines and solid fuel gas generators.
Background
The solid propulsion mode is widely applied, for example, the solid rocket engine is selected as a power device of most missiles and rockets due to the advantages of simple structure, low cost, good reliability, quick response and the like. However, power plants using solid propellants also have inherent disadvantages, typically manifested by poor controllability, and difficulty in achieving thrust control similar to liquid rocket engines.
In order to improve the performance and expand the application range, researchers have made relevant researches on the thrust controllability of a solid propellant power device and have made progress in the fields of thrust vector control, variable thrust engines, attitude and orbit control gas valves and the like. But has been slow in terms of multiple starts of the solid state power plant, i.e., active on-off control. The difficulty of the related research work is caused by two operating characteristics of the solid state power plant:
one is the persistence of combustion of the solid propellant. Once the charge is ignited, the heat transfer from the propellant occurs automatically, causing it to reach ignition conditions and be ignited, during which the chemical reaction is also very vigorous and the combustion is not easily terminated.
The second is the relativity between the gas production rate and the gas exhaust rate. The combustion chamber of the conventional solid rocket engine is a propellant storage place and a place for carrying out combustion reaction, and the fuel gas is accelerated and discharged through the spray pipe. The combustion gas production process and the exhaust process are carried out synchronously, and the gas production rate is equal to the exhaust rate when the engine works stably. That is, on the one hand, the charge must be exhausted simultaneously during combustion, otherwise there is a danger that the combustion chamber pressure will rise all the time; on the other hand, to obtain thrust at a certain moment, the charge must be burning at that moment. By conventional means, it is very difficult to separate the two processes.
Accordingly, those skilled in the art have endeavored to develop a rechargeable, stored-gas, solid propellant power plant, primarily for use in solid attitude control engines, variable thrust engines, and variable flow gas generators.
Disclosure of Invention
In view of the above-mentioned drawbacks of the prior art, the present invention takes the following technical approaches. Firstly, pulse pressurization is adopted: the multistage pulse grains are used for continuous filling and combustion without stopping the combustion process. Secondly, the gas storage link is increased: the charging combustion process and the spray pipe exhaust work-doing process are separated and are independent respectively. The charge combustion is only used for pressurizing the gas storage tank, and does not need to exhaust simultaneously; the work done by exhaust makes the working medium and energy come from the gas storage tank, at this time, it is no longer necessary to charge and burn at the same time.
The purpose of the invention is realized by the following technical scheme.
A rechargeable, gassed, solid propellant power plant comprising: the device comprises a grain transmission device, a charging loader, a gas storage chamber, a controllable spray pipe and a pressure measurement and control device;
the grain transmission device includes: the powder charging storage chamber rotates the motor, the powder charging storage chamber, the first powder charging push rod, the second powder charging push rod, the pulse powder charging and the residual gas releasing device.
The charge storage chamber is of an annular structure; the annular hollow part is used for placing a charge storage chamber rotating motor and is used for controlling the charge storage chamber to rotate; a plurality of through grooves are axially formed in the annular structure and used for placing pulse charge; the first charging push rod pushes out the pulse charging in the through groove and then pushes the pulse charging into a charging loader through a second charging push rod; the residual gas releasing device is connected with the charge loader through a pipeline and is used for discharging residual gas in the charge loader before pulse charge is loaded;
the charge loader consists of a cylindrical rotating structure and a shell, a combustion cavity is formed on the cylindrical surface and used as a place for pulse charge loading and combustion, the shell tightly wraps the rotating structure, and openings are formed in the directions of the gas storage chamber, the residual gas release device and the second charge push rod; the charge loader is used as a sealing element to isolate a charge storage chamber and a fuel gas storage chamber;
the front seal head of a combustion chamber in a solid rocket engine or a fuel gas generator is provided with an opening, and a charge loader is externally connected to form a closed space to form a fuel gas storage chamber, so that high-temperature and high-pressure fuel gas generated by combustion can be stored, and the fuel gas can be released to do work according to needs;
a controllable spray pipe is arranged at a gas outlet of the gas storage chamber and used for adjusting the gas output;
the pressure measurement and control device is used for measuring the pressure in the fuel gas storage chamber and controlling the rotation of the charging loader;
the working process is as follows: in the initial state, an ignition signal is accessed from the outside of the engine to trigger the ignition powder to ignite the main charge. The fuel gas is stored in the fuel gas storage chamber, and is sprayed out through the controllable spray pipe to do work to generate power, and the flow is adjustable. When the pressure measuring and controlling device measures that the pressure in the gas storage chamber is lower than a given threshold value m, the situation that the residual quantity of the gas in the gas storage chamber is insufficient and pulse charging needs to be filled is shown. The motor drives the powder charge loader to rotate to the residual gas release station, and residual gas in the combustion cavity of the powder charge loader is discharged out of the power device through the residual gas release device so as to prevent the impulse powder charge from being ignited in advance during charging. After the residual air is released, the charge loader rotates to the loading station along the same direction, and a pulse charge is pushed into the charge loader from the charge storage chamber through the charge push rod. After filling, the charging loader continuously rotates to the position where the combustion cavity is opposite to the gas storage chamber, and high-temperature and high-pressure gas in the gas storage chamber ignites pulse charging to generate and supplement gas. After the pulse charging combustion is finished, the charging loader turns to the residual gas release station again, and the process is repeated. When the pressure measuring and controlling device measures that the pressure in the gas storage chamber is higher than a given threshold value n, the gas storage chamber is full of gas, and the powder charging loader stops rotating. In addition, after all charges in a logical groove of charge apotheca all the propelling movement finish, first charge push rod resets, and motor drive charge apotheca rotates certain angle, lets the logical groove that next has the charge be in the position of sending the medicine.
Advantageous effects
1. The combination of the gas storage link and the pulse pressurization can well solve the problem of active startup and shutdown of the solid propellant power device, and multiple startup is really realized. In addition, the controllable spray pipe changes the outlet flow of the fuel gas, and the accurate control of the thrust can be realized. The solid power device has the energy management function, and the thrust scheme can be flexibly changed according to the task requirement.
2. The high-temperature high-pressure gas in the gas storage chamber is utilized to ignite the pulse charge, and compared with the traditional multi-pulse solid rocket engine, the design of a multi-stage ignition device is omitted, the ignition mode is simple, and the system reliability is higher.
3. Because the charge storage is separated from the combustion, the charge storage chamber does not need to bear the gas pressure, the strength design requirement is low, and compared with the traditional solid propellant power device, the invention saves more structural materials.
Drawings
FIG. 1 is a block diagram of the apparatus of the present invention;
FIG. 2 is an external schematic view of the present invention;
FIG. 3 is a left side view of the charge storage chamber of the present invention;
FIG. 4 is a cross-sectional view of a charge storage chamber of the present invention;
FIG. 5 is a residual air release map of the present invention;
FIG. 6 is a charge loading station diagram of the present invention;
figure 7 is a charge combustion tooling diagram of the present invention.
The device comprises a rotating motor of a charge storage chamber 1, a first charge push rod 2, a charge storage chamber 3, a second charge push rod 4, a pulse charge 5, a main charge 6, a charge loader 7, a residual gas releasing device 8, a gas storage chamber 9, a pressure measuring and controlling device 10, an igniter 11, a nozzle sealing part 12 and a controllable nozzle 13.
Detailed Description
The conception, the specific structure and the technical effects of the present invention will be further described with reference to the accompanying drawings and embodiments, so as to understand the objects, the features and the effects of the present invention.
As shown in fig. 1, a rechargeable gas-storing solid rocket engine comprises: the device comprises a charge storage chamber rotating motor 1, a first charge push rod 2, a charge storage chamber 3, a second charge push rod 4, pulse charge 5, main charge 6, a charge loader 7, a residual gas release device 8, a gas storage chamber 9, a pressure measurement and control device 10, an igniter 11, a spray pipe sealing element 12 and a valve control spray pipe 13. The residual gas release device 8 is connected with the charging loader 7 through a pipeline, an opening at the front seal head of the gas storage chamber 9 is connected with the charging loader 7 to form a closed space, and the tail part of the gas storage chamber is connected with the controllable spray pipe 13. The main charge 6 is designed into an internal combustion tube type charge column, which is cast in the gas storage chamber 9 in advance in a way of clinging to the wall surface, the igniter 11 is arranged on the surface of the main charge 6 and close to the end of the spray pipe, and the ignition wire of the igniter is led out backwards through the sealing part 12 of the spray pipe and is communicated with an external control circuit.
As shown in fig. 2, there are through slot openings at a, b of the charge storage chamber 3 and openings at c of the conduit. The charge loader 7 is driven by a motor and can axially rotate for 360 degrees, and the first charge push rod 2 and the second charge push rod 4 are driven by the motor and can realize linear feeding and resetting motion.
As shown in fig. 3 and 4, the charge storage chamber 3 is annularly hollow, the charge storage chamber rotating motor 1 is placed in the annular hollow part, the charge storage chamber rotating motor is used for controlling the charge storage chamber to rotate, and eight through grooves are formed in the annular structure and are distributed in a regular octagon shape. The pulse charges 5 are designed in a cuboid charge shape, and five pulse charges 5 are regularly arranged in each through groove of the charge storage chamber 3. The first charge pushrod 2 pushes the pulsed charge 5 in the charge storage 3 into the right side conduit and then into the charge loader 7 by the second charge pushrod 4.
In the initial state, an ignition signal is input from the outside of the engine through an ignition wire, the igniter 11 is excited to ignite the main charge 6, and the nozzle seal 12 is broken by the impact of the gas and is ejected out of the engine. The gas is stored in the gas storage chamber 9 and is released through the nozzle to do work to generate power. The jet pipe uses 13-valve control jet pipes, and can control the flow of a fuel gas outlet by opening and closing the throat part, adjusting the area of the throat part and the like, thereby realizing opening and closing control and thrust control. When the pressure measuring and controlling device 10 measures that the pressure in the gas storage chamber 9 is lower than a given threshold value m, the filling operation flow is started.
As shown in fig. 5, the charge loader 7 rotates 90 degrees counterclockwise to the residual gas release station, and residual gas in the combustion chamber is discharged out of the power device through the residual gas release device 8, so that the impulse charge 5 is prevented from being ignited in advance during the later filling. As shown in fig. 6, after the residual gas is released, the charge loader 7 rotates 180 degrees counterclockwise to the loading station, the opening of the combustion chamber faces the charge conveying pipeline, the second charge push rod 4 performs feed motion, and a pulse charge is pushed into the cavity of the loader and then resets. As shown in fig. 7, after the filling is finished, the charge loader 7 rotates 90 degrees anticlockwise, the opening of the combustion cavity faces the gas storage chamber 9, and the pulse charge 5 is ignited by high-temperature and high-pressure gas in the gas storage chamber 9 to generate and supplement gas. Meanwhile, the first charging push rod 2 pushes a pulse charging charge 5 from the charging storage chamber 3 to be sent into a charging pipeline for the next charging. After the pulse charging 5 is completely combusted, the charging loader 7 turns to the residual gas releasing station again, and the process is repeated. When the pressure measuring and controlling device 10 measures that the pressure in the gas storage chamber 9 is higher than a given threshold value n, the gas storage chamber 9 is full of gas, and the powder charging loader 7 stops rotating.
What has been described in particular is that, after five pulse charges 5 in a logical groove of charge apotheca 3 all pushed and finish, first charge push rod 2 resets, and charge apotheca rotates motor 1 drive charge apotheca 3 clockwise rotation 45, lets the logical groove that next has the charge be in the position of sending the medicine. Further, the charge filler 7 performs a sealing process as a seal for isolating the charge storage chamber 3 and the gas storage chamber 9 to prevent gas leakage.
The above detailed description is intended to illustrate the objects, aspects and advantages of the present invention, and it should be understood that the above detailed description is only exemplary of the present invention and is not intended to limit the scope of the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (4)
1. A rechargeable, gas-storing, solid propellant power plant, comprising: the method comprises the following steps: the device comprises a grain transmission device, a charging loader, a gas storage chamber, a controllable spray pipe and a pressure measurement and control device;
the grain transmission device includes: the device comprises a charge storage chamber rotating motor, a charge storage chamber, a first charge push rod, a second charge push rod, pulse charge and residual gas release devices;
the charge storage chamber is of an annular structure; the annular hollow part is used for placing a charge storage chamber rotating motor and is used for controlling the charge storage chamber to rotate; a plurality of through grooves are axially formed in the annular structure and used for placing pulse charge; the first charging push rod pushes out the pulse charging in the through groove to the right pipeline along the axial direction, and then the pulse charging is pushed into the charging loader through the second charging push rod; the residual gas releasing device is connected with the charge loader through a pipeline and is used for discharging residual gas in the charge loader before pulse charge is loaded;
the charge loader consists of a cylindrical rotating structure and a shell, a combustion cavity is formed on the cylindrical surface and used as a place for pulse charge loading and combustion, the shell tightly wraps the rotating structure, and openings are formed in the directions of the gas storage chamber, the residual gas release device and the second charge push rod; the charge loader is positioned at the axis of the gas storage chamber and is used as a sealing piece to isolate the charge storage chamber and the gas storage chamber;
the front seal head of the combustion chamber in the solid rocket engine or the fuel gas generator is provided with an opening, and a sealed space is formed by externally connecting a charging loader to form a fuel gas storage chamber for storing high-temperature and high-pressure fuel gas generated by combustion and releasing the fuel gas to do work according to needs.
2. A rechargeable, stored-gas, solid propellant power plant as claimed in claim 1, characterised in that: and a controllable spray pipe is arranged at a gas outlet of the gas storage chamber and used for adjusting the gas output.
3. A rechargeable, stored-gas, solid propellant power plant as claimed in claim 1, characterised in that: the pressure measurement and control device is used for measuring the pressure in the fuel gas storage chamber and controlling the rotation of the charging loader.
4. A rechargeable, stored-gas, solid propellant power plant as claimed in claim 1, characterised in that: the working process is as follows: in the initial state, an ignition signal is accessed from the outside of the engine and initiates an ignition charge to ignite the main charge; the fuel gas is stored in the fuel gas storage chamber, is sprayed out through the controllable spray pipe to do work to generate power, and the flow is adjustable; when the pressure measuring and controlling device measures that the pressure in the gas storage chamber is lower than a given threshold value m, indicating that the residual gas in the gas storage chamber is insufficient, and filling pulse charge is needed; the motor drives the powder charging loader to rotate to the residual gas release station, and residual gas in a combustion cavity of the powder charging loader is discharged out of the power device through the residual gas release device so as to prevent the impulse powder charging from being ignited in advance during charging; after the residual air is released, the charge loader rotates to a loading station along the same direction, and a pulse charge is pushed into the charge loader from the charge storage chamber through the charge push rod; after the filling is finished, the charging loader continuously rotates to the position where the combustion cavity is opposite to the gas storage chamber, and high-temperature and high-pressure gas in the gas storage chamber ignites pulse charging to generate and supplement gas; after the pulse charging is finished, the charging loader turns to the residual gas releasing station again, and the process is repeated; when the pressure measuring and controlling device measures that the pressure in the gas storage chamber is higher than a given threshold value n, indicating that the gas storage chamber is full of gas, stopping rotating the charging loader; in addition, after all charges in a logical groove of charge apotheca all the propelling movement finish, first charge push rod resets, and motor drive charge apotheca rotates certain angle, lets the logical groove that next has the charge be in the position of sending the medicine.
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| CN201910541656.7A CN110195665B (en) | 2019-06-21 | 2019-06-21 | Rechargeable gas storage type solid propellant power device |
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| CN201910541656.7A CN110195665B (en) | 2019-06-21 | 2019-06-21 | Rechargeable gas storage type solid propellant power device |
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| CN110195665B true CN110195665B (en) | 2020-06-05 |
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| CN110778416B (en) * | 2019-09-26 | 2021-02-19 | 湖北三江航天红林探控有限公司 | Pulse type attitude control thruster based on shared combustion chamber |
| CN110966116B (en) * | 2019-11-08 | 2021-03-09 | 上海新力动力设备研究所 | Free charge grain assembly fixture of solid rocket engine |
| CN111071491B (en) * | 2019-12-09 | 2023-08-11 | 西安近代化学研究所 | Annular solid propellant charging structure |
| CN111622863B (en) * | 2020-06-05 | 2021-04-06 | 湖北三江航天红林探控有限公司 | Thrust termination device of small solid rocket engine |
| CN115258200B (en) * | 2022-07-01 | 2024-07-26 | 宁波天擎航天科技有限公司 | Dual-mode thrust-variable propulsion system and propulsion method |
| CN115822814B (en) * | 2022-09-23 | 2024-07-02 | 哈尔滨工业大学 | Coaxial annular multi-electrode electric control solid thruster |
| CN115467762B (en) * | 2022-10-24 | 2024-06-25 | 中北大学 | Multi-pulse solid rocket engine grain storage and drug supply device |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3567174A (en) * | 1968-03-18 | 1971-03-02 | Thiokol Chemical Corp | Breakdown core for forming a cavity in a solid propellant grain |
| US4085173A (en) * | 1964-10-05 | 1978-04-18 | Hercules Incorporated | Manufacture of solid propellant |
| SE421444B (en) * | 1966-06-29 | 1981-12-21 | Aerojet General Co | PROCEDURE FOR MANUFACTURING A TWO STEP ROCKET ENGINE |
| CN101545416A (en) * | 2008-03-24 | 2009-09-30 | 沈阳理工大学 | Solid rocket engine |
| US8079308B1 (en) * | 1988-10-12 | 2011-12-20 | Aerospatiale Societe Nationale Industrielle | Ramjet engine incorporating a tubular structure and a missile propelled by a ramjet engines of this type |
| CN103644046A (en) * | 2013-11-21 | 2014-03-19 | 北京动力机械研究所 | Charging grain structure of solid rocket engine |
| CN206221090U (en) * | 2016-10-08 | 2017-06-06 | 北京航空航天大学 | The propellant filling equipment of micro combustions room |
| CN207513702U (en) * | 2017-11-29 | 2018-06-19 | 宜宾北方川安化工有限公司 | A kind of charge constitution of front end suspension isolation |
| CN208106595U (en) * | 2018-04-26 | 2018-11-16 | 湖南宏大日晟航天动力技术有限公司 | A kind of Novel end face propulsion charge |
| CN109723572A (en) * | 2018-12-20 | 2019-05-07 | 西安近代化学研究所 | A kind of impulse rocket cluster engine |
-
2019
- 2019-06-21 CN CN201910541656.7A patent/CN110195665B/en not_active Expired - Fee Related
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4085173A (en) * | 1964-10-05 | 1978-04-18 | Hercules Incorporated | Manufacture of solid propellant |
| SE421444B (en) * | 1966-06-29 | 1981-12-21 | Aerojet General Co | PROCEDURE FOR MANUFACTURING A TWO STEP ROCKET ENGINE |
| US3567174A (en) * | 1968-03-18 | 1971-03-02 | Thiokol Chemical Corp | Breakdown core for forming a cavity in a solid propellant grain |
| US8079308B1 (en) * | 1988-10-12 | 2011-12-20 | Aerospatiale Societe Nationale Industrielle | Ramjet engine incorporating a tubular structure and a missile propelled by a ramjet engines of this type |
| CN101545416A (en) * | 2008-03-24 | 2009-09-30 | 沈阳理工大学 | Solid rocket engine |
| CN103644046A (en) * | 2013-11-21 | 2014-03-19 | 北京动力机械研究所 | Charging grain structure of solid rocket engine |
| CN206221090U (en) * | 2016-10-08 | 2017-06-06 | 北京航空航天大学 | The propellant filling equipment of micro combustions room |
| CN207513702U (en) * | 2017-11-29 | 2018-06-19 | 宜宾北方川安化工有限公司 | A kind of charge constitution of front end suspension isolation |
| CN208106595U (en) * | 2018-04-26 | 2018-11-16 | 湖南宏大日晟航天动力技术有限公司 | A kind of Novel end face propulsion charge |
| CN109723572A (en) * | 2018-12-20 | 2019-05-07 | 西安近代化学研究所 | A kind of impulse rocket cluster engine |
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