CN116378856A - Split-assembled solid rocket engine with actively-controlled performance and working method - Google Patents
Split-assembled solid rocket engine with actively-controlled performance and working method Download PDFInfo
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- CN116378856A CN116378856A CN202310428237.9A CN202310428237A CN116378856A CN 116378856 A CN116378856 A CN 116378856A CN 202310428237 A CN202310428237 A CN 202310428237A CN 116378856 A CN116378856 A CN 116378856A
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- combustion chamber
- flow regulating
- regulating device
- rocket engine
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- 239000007787 solid Substances 0.000 title claims abstract description 26
- 238000000034 method Methods 0.000 title claims abstract description 7
- 230000001105 regulatory effect Effects 0.000 claims abstract description 56
- 238000002485 combustion reaction Methods 0.000 claims abstract description 54
- 230000005540 biological transmission Effects 0.000 claims abstract description 17
- 238000007789 sealing Methods 0.000 claims abstract description 12
- 239000003638 chemical reducing agent Substances 0.000 claims abstract description 9
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 25
- 239000001301 oxygen Substances 0.000 claims description 25
- 229910052760 oxygen Inorganic materials 0.000 claims description 25
- 239000004449 solid propellant Substances 0.000 claims description 17
- 230000007246 mechanism Effects 0.000 claims description 10
- 239000002737 fuel gas Substances 0.000 claims description 8
- 239000000567 combustion gas Substances 0.000 claims description 6
- 230000001276 controlling effect Effects 0.000 claims description 6
- 239000007789 gas Substances 0.000 claims description 4
- 230000008859 change Effects 0.000 claims description 3
- 238000011144 upstream manufacturing Methods 0.000 claims description 3
- 230000008878 coupling Effects 0.000 claims description 2
- 238000010168 coupling process Methods 0.000 claims description 2
- 238000005859 coupling reaction Methods 0.000 claims description 2
- 239000003380 propellant Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004806 packaging method and process Methods 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
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Classifications
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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
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
- F02K9/86—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using nozzle throats of adjustable cross- section
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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
- F02K9/26—Burning control
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/34—Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Transmission Devices (AREA)
Abstract
The invention relates to a split charging combined solid rocket engine with actively-controlled performance and a working method thereof, wherein the split charging combined solid rocket engine comprises a sealing cover, a rich combustion chamber, a flow regulating device, an rich combustion chamber, a mixed combustion chamber and a tail nozzle which are connected in sequence; the flow regulating device comprises a convergence section, a sliding disc type flow regulating valve, an expansion section, a motor fixing frame, a rotary servo motor, a control panel, a star gear reducer and a star transmission gear; the sliding disc type flow regulating valve comprises two sliding disc valves, wherein the center of each sliding disc valve is provided with an inward concave circular hole for placing a ball bearing, the two sliding disc valves are connected through a rotating shaft, and the two sliding disc valves are sealed and can mutually rotate; the rotary servo motor is connected with a star-shaped transmission gear through a star-shaped gear reducer; the rotary servo motor is fixed with the motor fixing frame through a flange plate arranged at the tail end of the convergence section of the flow regulating device; the control panel is connected with the rotary servo motor. The invention has compact structure and convenient assembly control, and can simultaneously realize the high-energy and performance regulation of the solid rocket engine.
Description
Technical Field
The invention belongs to the field of solid rocket engines, and particularly relates to a split charging combined solid rocket engine with actively-controlled performance and a working method thereof.
Background
With the increasing demand for combat missiles, thrust control is an option to meet these increasing demands. Historically, the primary propulsion system for controlled thrust has been a liquid propulsion system. However, packaging limitations and other problems associated with liquid systems are the cause of many strategic missile systems employing solid propellant propulsion systems. The improvement of delivery range and maneuverability is an essential feature of strategic missiles in China, so that the solid engine is developed to high energy and performance follow-up control.
The existing scheme for realizing thrust adjustment of the solid rocket engine mainly comprises the following steps: a variable thrust engine for adjusting the throat area of the spray pipe; a variable thrust engine for controlling the mass and the combustion speed of the propellant; a mass-added engine; a gelatinous propellant motor; a layered engine; the engine is turned off. The engine with adjustable throat area has the longest research history, good theoretical and experimental basis and large thrust regulation ratio.
Disclosure of Invention
The invention aims to provide a split charging combined solid rocket engine with actively-controlled performance and a working method thereof.
The aim of the invention is realized by the following technical scheme:
a split charging combined solid rocket engine with actively-controlled performance comprises a sealing cover, a rich combustion chamber, a flow regulating device, an rich combustion chamber, a mixed combustion chamber, a tail nozzle and an ignition device positioned in the rich combustion chamber, which are sequentially connected;
the flow regulating device comprises a convergence section, a sliding disc type flow regulating valve, an expansion section, a motor fixing frame, a rotary servo motor, a control panel, a star gear reducer and a star transmission gear; the sliding disc type flow regulating valve comprises two sliding disc valves, wherein the center of each sliding disc valve is provided with an inward concave circular hole for placing a ball bearing, and the two sliding disc valves are connected through a rotating shaft, sealed and can mutually rotate; the rotary servo motor is connected with a star-shaped transmission gear through a star-shaped gear reducer; the rotary servo motor and the motor fixing frame are fixed through a flange plate arranged at the tail end of the convergence section of the flow regulating device; the control panel is connected with the rotary servo motor and is used for controlling the rotation angle of the rotary servo motor.
Further, the sealing cover and the rich combustion chamber are poured into a whole through an integrated design, and the rich combustion chamber is connected with the upstream of the flow regulating device through a flange; the oxygen-enriched combustion chamber and the mixed combustion chamber and the tail nozzle are poured into a whole through an integrated design, and the oxygen-enriched combustion chamber is connected with the downstream of the flow regulating device through a flange plate.
Further, the rich combustion chamber is filled with a rich solid propellant; filling an oxygen-enriched solid propellant into the oxygen-enriched combustion chamber; the oxygen-enriched combustion chamber is connected with the mixed combustion chamber, so that the fuel gas of the rich-combustion solid propellant and the oxygen-enriched solid propellant is fully mixed and combusted.
Further, the right-end slide disc valve is fixed and can not rotate, and the left-end slide disc valve drives the star-shaped transmission gear to rotate through the servo mechanism, so that the flow passage area flowing through the flow regulating device is controlled.
Further, the expansion section of the flow regulating device and the non-rotatable slide disc valve are integrally designed, the left rotatable slide disc valve is in sealing connection with the convergence section of the flow regulating device and can rotate relatively, four vent holes are respectively formed in one circle of the two slide disc valves, and the four vent holes of the two slide disc valves are opposite to each other.
A working method of a split combined solid rocket engine with actively-controlled performance includes that the engine starts to work, and a rich solid propellant in a rich combustion chamber is combusted in a self-sustaining mode to generate rich fuel gas; the rich combustion gas enters an oxygen-enriched combustion chamber, an oxygen-enriched solid propellant is ignited, and a coupling combustion reaction occurs between the rich combustion gas and the oxygen-enriched gas; the fuel gas and the oxygen-enriched gas which are not fully reacted are in a mixed combustion chamber; when the thrust of the engine is regulated, the control panel controls the driving mechanism to rotate the rotating angle of the servo motor, and simultaneously, the star-shaped transmission gear rotates the slide disk valve to regulate the effective throat area of the flow regulating device, change the pressure intensity and regulate the thrust.
The invention has the beneficial effects that:
the invention can adjust the thrust in a certain range according to the operation requirement, the driving mechanism is controlled by the control board to rotate the servo motor by a specified angle, and the sliding disk valve is rotated by the transmission gear, so that the effective throat area of the flow adjusting device is adjusted, and the pressure is changed to realize the accurate adjustment of the thrust.
The sliding disc type flow regulating valve is simple in structure, convenient to operate and capable of adapting to the working environment. The servo mechanisms of the adjusting device are all arranged outside the engine, so that the charging space is enlarged, and the problem of heat protection of the servo mechanisms is avoided.
The control panel and the rotary servo mechanism used have quick response capability, and when the control panel sends out a specified rotary instruction, the rotary servo mechanism can quickly respond according to the instruction of the control panel, so that the adverse effect of the actuating speed of the regulating valve on the engine operation is reduced.
The inner section of the flow regulating device is in a tapered-suddenly-expanded mode, so that the effect of accelerating the flow of the fuel gas is achieved, meanwhile, the rotation angle of the sliding disc valve can be controlled to realize the difference of equivalent throat areas of the flow channels, and the mass flow of the fuel gas is controlled to realize the purpose of regulating and controlling the performance.
Drawings
FIG. 1 is a schematic diagram of the overall structure of a split-charging combined solid rocket engine with actively controlled performance;
FIG. 2 is a schematic diagram of a split-charging combined solid rocket engine flow regulating device with actively controlled performance;
FIG. 3 is a schematic cross-sectional view of a split-charging combined solid rocket engine with actively controlled performance;
FIG. 4 is a graph of effective throat area of a slider plate valve in a split-charging combined solid rocket engine flow regulating device with active performance regulation.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
With reference to fig. 1, 2 and 3, the split-charging combined solid rocket engine with actively-controlled performance comprises a sealing cover 1, a rich combustion chamber 2, a flow regulating device 3, an rich combustion chamber 4, a mixed combustion chamber 5, a tail nozzle 6, an ignition device 15, a rich solid propellant 16 and an rich solid propellant 17; the flow regulating device comprises a convergence section 7, a slide disc type flow regulating valve 13, an expansion section 11, a motor fixing frame 8, a rotary servo motor 12, a control panel 9, a star gear reducer 10 and a star transmission gear 14.
The sealing cover 1 and the rich combustion chamber 2 are poured into a whole through an integrated design, and the rich solid propellant 16 is filled to the position according to related requirements, and the rich combustion chamber 2 is connected with the upstream of the flow regulating device 3 through a flange; the oxygen-enriched combustion chamber 4, the mixed combustion chamber 5 and the tail nozzle 6 are cast into a whole through an integrated design, and the oxygen-enriched solid propellant 17 is filled to the position according to related requirements.
The oxygen-enriched combustion chamber 4 is connected with the downstream of the flow regulating device 3; the motor fixing frame 8 is installed and fixed through a flange plate arranged at the tail end of the convergence section 7 of the flow regulating device 3; the rotary servo motor 12 is connected with a star-shaped transmission gear 14 through a star-shaped gear reducer 10; the sliding disc type flow regulating valves 13 are two sliding disc valves in total, each sliding disc valve is provided with an inward concave round hole at the center for placing a ball bearing 18, the two sliding disc valves are connected through a rotating shaft 19, the two sliding disc valves are sealed and can mutually rotate, four vent holes are respectively arranged on one circle of each sliding disc valve, and the four vent holes of each sliding disc valve are opposite to each other; the right end slide disk valve is fixed and can not rotate, and the left end drives the star-shaped transmission gear 14 to rotate through the servo mechanism so as to control the flow passage area flowing through the flow regulating device 3; the expansion section 11 of the flow regulating device 3 and the non-rotatable slide disc valve are integrally designed, and the left rotatable slide disc valve is in sealing connection with the convergence section of the flow regulating device and can rotate relatively; the control panel is connected with the rotary servo motor and is used for controlling the rotation angle of the rotary servo motor.
Five circular holes are formed in each sliding disc valve, one of the five circular holes is located in the center of each sliding disc valve and used for being connected with two sliding disc valves to ensure that the sliding disc valves are sealed and can rotate mutually, and the other four adjusting holes are circumferentially distributed along the center hole. Once the sliding disk valve rotates, the effective rotating throat area of four circumferentially distributed regulating holes is changed, so that the purpose of flow regulation is achieved. The flow throat area schematic is shown in FIG. 4, where the shaded portion is the effective throat area of the tuning orifice.
In one embodiment, the engine is provided with sealing rings for sealing each section of connection.
When the split combined solid rocket engine with actively regulated performance performs performance regulation, the rotary servo motor 12 receives a rotation instruction from the control panel 9, the control panel 9 drives the star-shaped transmission gear 14 to rotate through the star-shaped gear reducer 10, the star-shaped transmission gear 14 rotates to drive the rotatable slide disc valves to rotate around the axis, the vent holes of the two slide disc valves are staggered by a certain angle, and the effective throat area of the flow regulating device 3 is changed, so that the flow and the pressure of the rich-combustion oxygen-enriched combustion chamber are changed, and the purpose of regulating the thrust of the engine is realized.
When the motion of the rotary servo motor 12 changes according to a certain rule, the effective throat area of the flow regulating device 3 also presents a certain change rule, so that the purposes of regulating the gas flow flowing through the flow regulating device 3 and regulating the pressure of the combustion chamber are realized, and further, the thrust regulation is realized. When the thrust of the engine needs to be increased, the rotary servo motor 12 controls the star-shaped transmission gear 14 to rotate, so that the slide disc valve rotates in the direction of reducing the effective throat area of the flow regulating device 3, the pressure of the rich combustion chamber 2 is increased, the combustion speed of the propellant is increased, and the flow of the rich combustion gas is also increased; the size of the tail nozzle 6 is unchanged, so that the pressure of the oxygen-enriched combustion chamber 4 is increased, the combustion speed and the flow rate are also increased, and the aim of increasing the thrust is fulfilled, and vice versa.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. A split charging combined solid rocket engine with actively regulated performance is characterized in that: comprises a sealing cover (1), a rich combustion chamber (2), a flow regulating device (3), an rich combustion chamber (4), a mixed combustion chamber (5), a tail nozzle (6) and an ignition device (15) positioned in the rich combustion chamber (2) which are sequentially connected;
the flow regulating device (3) comprises a convergence section (7), a sliding disc type flow regulating valve (13), an expansion section (11), a motor fixing frame (8), a rotary servo motor (12), a control board (9), a star gear reducer (10) and a star transmission gear (14); the sliding disc type flow regulating valve (13) comprises two sliding disc valves, wherein the center of each sliding disc valve is provided with an inward concave circular hole for placing a ball bearing (18), the two sliding disc valves are connected through a rotating shaft (19), and the two sliding disc valves are sealed and can mutually rotate; the rotary servo motor (12) is connected with a star-shaped transmission gear (14) through a star-shaped gear reducer (10); the rotary servo motor (12) and the motor fixing frame (8) are fixed through a flange plate arranged at the tail end of the convergence section (7) of the flow regulating device (3); the control board (9) is connected with the rotary servo motor (12) and is used for controlling the rotation angle of the rotary servo motor (12).
2. The split charging combined solid rocket engine with actively controlled performance according to claim 1, wherein: the sealing cover (1) and the rich combustion chamber (2) are poured into a whole through an integrated design, and the rich combustion chamber (2) is connected with the upstream of the flow regulating device (3) through a flange plate; the oxygen-enriched combustion chamber (4), the mixed combustion chamber (5) and the tail nozzle (6) are integrally cast, and the oxygen-enriched combustion chamber (4) is connected with the downstream of the flow regulating device (3) through a flange plate.
3. The split charging combined solid rocket engine with active performance regulation and control according to claim 2, wherein: the rich combustion chamber (2) is filled with a rich solid propellant (16); the oxygen-enriched combustion chamber (4) is filled with oxygen-enriched solid propellant (17); the oxygen-enriched combustion chamber (4) is connected with the mixed combustion chamber (5) so that the fuel gas of the rich solid propellant (16) and the oxygen-enriched solid propellant (17) is fully mixed and combusted.
4. The split-charging combined solid rocket engine capable of realizing active performance regulation and control according to claim 1, wherein the split-charging combined solid rocket engine is characterized in that: the right-end slide disc valve is fixed and non-rotatable, and the left-end slide disc valve drives the star-shaped transmission gear (14) to rotate through the servo mechanism and is used for controlling the flow passage area flowing through the flow regulating device (3).
5. The split charging combined solid rocket engine with active performance regulation and control according to claim 4, wherein: the expansion section (11) of the flow regulating device (3) and the non-rotatable slide disc valve are integrally designed, the left rotatable slide disc valve is in sealing connection with the convergence section (7) of the flow regulating device (3) and can rotate relatively, four vent holes are respectively formed in one circle of each of the two slide disc valves, and the four vent holes of the two slide disc valves are opposite to each other.
6. The split charging combined solid rocket engine with actively controlled performance according to claim 1, wherein: the inner section of the flow regulating device (3) is in a form of 'taper-sudden expansion'.
7. The method for operating a split combined solid rocket engine with actively controlled performance according to any one of claims 1 to 6, wherein: the engine starts to work, and the rich solid propellant (16) in the rich combustion chamber (2) is combusted in a self-sustaining manner to generate rich fuel gas; the rich combustion gas enters an oxygen-enriched combustion chamber (4), an oxygen-enriched solid propellant (17) is ignited, and a coupling combustion reaction occurs between the rich combustion gas and the oxygen-enriched combustion gas; the fuel gas and the oxygen-enriched gas which are not fully reacted are in a mixed combustion chamber (5); when the thrust of the engine is regulated, the control panel (9) controls the driving mechanism to rotate the rotating angle of the servo motor (12), and meanwhile, the star-shaped transmission gear (14) rotates the sliding disk valve to regulate the effective throat area of the flow regulating device (3), change the pressure and regulate the thrust.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310428237.9A CN116378856A (en) | 2023-04-20 | 2023-04-20 | Split-assembled solid rocket engine with actively-controlled performance and working method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310428237.9A CN116378856A (en) | 2023-04-20 | 2023-04-20 | Split-assembled solid rocket engine with actively-controlled performance and working method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116378856A true CN116378856A (en) | 2023-07-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310428237.9A Pending CN116378856A (en) | 2023-04-20 | 2023-04-20 | Split-assembled solid rocket engine with actively-controlled performance and working method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116378856A (en) |
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2023
- 2023-04-20 CN CN202310428237.9A patent/CN116378856A/en active Pending
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