CN110469425B - Thrust-adjustable multi-stage pulse solid rocket engine - Google Patents
Thrust-adjustable multi-stage pulse solid rocket engine Download PDFInfo
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- CN110469425B CN110469425B CN201910781302.XA CN201910781302A CN110469425B CN 110469425 B CN110469425 B CN 110469425B CN 201910781302 A CN201910781302 A CN 201910781302A CN 110469425 B CN110469425 B CN 110469425B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—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)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
- Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)
Abstract
The invention discloses a thrust-adjustable multistage pulse solid rocket engine, which comprises more than two pulse combustion chambers, explosives arranged in the pulse combustion chambers and a bulkhead for connecting adjacent pulse combustion chambers, wherein the bulkhead is provided with more than one T-shaped through hole and more than one I-shaped through hole for communicating the adjacent pulse combustion chambers; the large end of the T-shaped through hole faces to the rear end combustion chamber and is provided with a blocking cover in interference fit with the rear end combustion chamber, the blocking cover is closed under the high pressure action of the rear end combustion chamber and is opened under the high pressure action of the front end combustion chamber; the two ends of the I-shaped through hole are respectively provided with a blocking cover in interference fit with the inner part of the I-shaped through hole, the periphery of the blocking cover positioned at the front end is provided with a blocking cover opening device used for opening the blocking cover in the I-shaped through hole towards the front end combustion chamber, the blocking cover in the I-shaped through hole towards the rear end combustion chamber is opened under high pressure in the front end combustion chamber, the flow area between the adjacent combustion chambers is actively adjustable, and therefore the thrust of the multistage pulse solid rocket is actively adjusted.
Description
Technical Field
The invention relates to the technical field of solid rocket engines, in particular to a thrust-adjustable multi-stage pulse solid rocket engine.
Background
At present, the pulse solid rocket engine is a hot spot of current research as a new way for realizing the energy management technology of the solid rocket engine. The pulse solid rocket engine can effectively control the energy output of the engine in real time in the working process, the optimal distribution of the energy of the engine is realized according to the system requirements, the opening sequence of the multi-stage pulse chambers is orderly controlled, the intermittent release of thrust is further orderly controlled, the energy of the propellant is more reasonably distributed, the utilization efficiency of the energy of the engine is effectively improved, the range of a missile is increased, and the maneuvering capability and the actual combat capability of the missile are improved.
The existing multistage pulse solid rocket engine has the following defects: the prefabricated hole opening modes on the compartment are all passive, namely, for example, a two-stage pulse solid rocket engine is taken as an example, the two-stage pulse combustion chamber is filled with powder, and the blockage on the compartment is flushed by high-temperature and high-pressure gas generated after the fuel in the pulse combustion chamber is ignited. At this time, since the size of the preformed hole in the bay is constant, and the gas passing through the preformed hole is also constant, the thrust of the pulse solid rocket engine cannot be adjusted in real time. The thrust adjusting mode of the thrust adjustable multi-stage pulse solid engine in the prior art is a throat plug type structure and a rotary spray pipe type structure, the structure is complex, and the control difficulty is high when the problems of dynamic sealing, relative motion interface and the like are involved.
Disclosure of Invention
In view of the above, the invention provides a thrust-adjustable multi-stage pulse solid rocket engine, wherein the driving hole is additionally arranged on the bulkhead of the multi-stage pulse solid rocket engine, the structure is simple, the adjustment and control are convenient, and the thrust of the multi-stage pulse solid rocket engine can be adjusted according to engineering requirements.
The technical scheme of the invention is as follows: the multistage pulse solid rocket engine comprises more than two pulse combustion chambers, explosives and compartments, wherein the pulse combustion chambers are sequentially connected, the explosives are arranged in the pulse combustion chambers, the compartments are used for connecting adjacent pulse combustion chambers, and more than one T-shaped through hole and more than one I-shaped through hole are formed in the compartments and are used for communicating the adjacent pulse combustion chambers;
the large end of the T-shaped through hole faces to the rear end combustion chamber, a blocking cover for blocking the T-shaped through hole is arranged in the large end of the T-shaped through hole, the blocking cover falls off under the action of high-temperature and high-pressure gas in the front end combustion chamber, and the corresponding T-shaped through hole is opened;
the high-temperature high-pressure gas in the front end combustion chamber pushes open the blocking cover in the I-shaped through hole towards the rear end combustion chamber, and opens the corresponding I-shaped through hole to adjust the flow area between the adjacent combustion chambers.
As a preferable aspect, the closure opening device includes: the pin, the spring, the initiating explosive device and the exciting device are arranged in the I-shaped through hole, a prefabricated hole is formed in the periphery of the plug cover facing one side of the front end combustion chamber along the radial direction, the pin, the spring and the initiating explosive device are sequentially arranged in the prefabricated hole, the opening of the prefabricated hole is plugged from the periphery of the bulkhead, a through hole is formed in the plugging position, the exciting device penetrates through the through hole to be connected with the initiating explosive device, two ends of the spring are abutted to a shaft shoulder of the pin and the initiating explosive device respectively, the spring is in a compression state before the initiating explosive device acts, and after the exciting device is started to ignite the initiating explosive device, the pin is pushed to smash the plug cover facing one side of the front end combustion chamber in the I-shaped through hole under.
Preferably, the plug cover is a non-metal plug cover.
Preferably, the initiating explosive device is an electric initiating explosive device, the exciting device is an electric exciting device, the electric initiating explosive device and the electric exciting device are electrically connected, and the electric exciting device is electrified to excite the electric initiating explosive device to explode.
Preferably, the material of the compartment is high-strength steel or high-strength stainless steel.
As a preferred scheme, the non-metal blanking cover is made of high-strength engineering plastics.
Has the advantages that:
(1) according to the invention, the active holes are additionally arranged on the compartment of the multistage pulse solid rocket engine in the prior art (or part of passive holes are changed into active holes), and the pulse flow in the solid rocket engine during the working period of the two-pulse combustion chamber can be adjusted by adjusting the opening number of the active holes, so that the thrust of the solid rocket engine can be changed according to engineering requirements; simple structure and convenient regulation and control.
Drawings
FIG. 1 is a schematic structural diagram of a thrust adjustable two-stage pulse solid rocket engine of the present invention.
Figure 2 is an enlarged partial schematic view of the compartment of figure 1.
Wherein, 1-two pulse combustion chambers, 2-two pulse charging, 3-bulkhead, 4-one pulse combustion chamber, 5-one pulse charging, 6-spray pipe, 7-connecting block, 8-O-shaped sealing ring, 9-electric excitation device, 10-non-metal blocking cover, 11-pin, 12-spring, 13-electric initiating explosive device
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
Example 1:
the embodiment provides a thrust-adjustable multi-stage pulse solid rocket engine, and the driving hole is additionally arranged on the bulkhead of the multi-stage pulse solid rocket engine, so that the structure is simple, the adjustment and control are convenient, and the thrust of the multi-stage pulse solid rocket engine can be adjusted according to engineering requirements.
The multi-stage pulse solid rocket engine comprises more than two pulse combustion chambers which are sequentially connected and a bulkhead 3 used for connecting the adjacent pulse combustion chambers, the bulkhead 3 and the two adjacent pulse combustion chambers are connected through a connecting block 7, and the joint is sealed through an O-shaped sealing ring 8.
Taking a two-stage pulse solid rocket engine as an example, two adjacent pulse combustion chambers are respectively a pulse combustion chamber 4 and a two-pulse combustion chamber 1, a pulse charge 5 is arranged in the pulse combustion chamber 4, an opening is arranged at the opposite end of the connecting end of the pulse combustion chamber 4 and a compartment 3, the opening is communicated with and fixed with a spray pipe 6 (the spray pipe 6 and the pulse combustion chamber 4 are connected through a fixture block, a connecting ring or a flange plate), and the two-pulse charge 2 is arranged in the two-pulse combustion chamber 1;
the heat insulation layer is coated on the end faces of two axial ends of the bulkhead 3, more than one T-shaped through hole and more than one I-shaped through hole are formed in the bulkhead 3, and the number and the size of the T-shaped through holes and the I-shaped through holes are determined according to the maximum thrust requirement of the two-stage pulse solid rocket engine and the outer diameter of the bulkhead 3 under the condition that the strength of the bulkhead 3 is considered; the axial directions of the T-shaped through hole and the I-shaped through hole are both parallel to the axial direction of the two-stage pulse solid rocket engine;
the T-shaped through hole is communicated with the first pulse combustion chamber 4 and the second pulse combustion chamber 1, the large end of the T-shaped through hole faces the first pulse combustion chamber 4, and the non-metal blocking cover 10 in interference fit with the large end of the T-shaped through hole is arranged in the large end of the T-shaped through hole and serves as a driven hole; the I-shaped through hole is communicated with the first pulse combustion chamber 4 and the second pulse combustion chamber 1, the two ends of the I-shaped through hole are respectively provided with a non-metal blanking cover 10 in interference fit with the inner part of the two pulse combustion chambers, a blanking cover opening device is arranged on the periphery of the non-metal blanking cover 10 positioned on one side of the second pulse combustion chamber 1, the I-shaped through hole, the non-metal blanking cover 10 and the blanking cover opening device form a driving hole, and the non-metal blanking cover 10 in the I-shaped through hole is opened by the blanking cover opening device, so that the thrust of two-; the joints of the non-metal blanking cap 10 and the T-shaped through holes and the I-shaped through holes are respectively sealed (such as silicon rubber or putty coating and the like), and the thickness of the non-metal blanking cap 10 is a set value so that the non-metal blanking cap cannot be pushed away by high-temperature and high-pressure gas when the non-metal blanking cap abuts against the step.
Specifically, the method comprises the following steps: because the high-temperature high-pressure gas is sprayed out of the spray pipe 6, the end of the spray pipe 6 is the rear end of the two-stage pulse solid rocket engine, the other end of the spray pipe is the front end of the two-stage pulse solid rocket engine, a pulse charge 5 in a pulse combustion chamber 4 is ignited, the generated high-temperature high-pressure gas is sprayed out backwards through the spray pipe 6, and forward thrust is formed to push the two-stage solid rocket engine forwards; during the working period of a pulse combustion chamber 4, the compartment 3 isolates a pulse charge 5 from the two pulse charges 2, meanwhile, the nonmetal blanking cover 10 on the compartment 3 can bear the high pressure generated by a pulse under the limiting action of the step, and the heat insulating layers on two sides of the compartment 3 can also properly prevent the heat of the pulse combustion chamber 4 from being transferred to the two pulse charges 2, so that the two pulse charges 2 are ensured not to be ignited during the working period of the pulse combustion chamber 4.
When the work of the pulse combustion chamber 1 is finished and the pulse combustion chamber 1 starts to work, the pulse charge 2 in the pulse combustion chamber is ignited, the generated high-temperature high-pressure gas pushes the nonmetal blanking cover 10 in the driven hole away towards the direction of the pulse combustion chamber 4, and the fuel gas enters the pulse combustion chamber 4 through the driven hole in the compartment 3 and is discharged backwards through the spray pipe 6 to generate forward thrust; and the non-metal blanking cover 10 in the active hole, which faces to one side of the two-pulse combustion chamber 1, cannot be opened due to the limiting effect of the step.
According to the system requirement, the nonmetal blanking cover 10 on one side of the two-pulse combustion chamber 1 is broken and opened through the blanking cover opening device, the nonmetal blanking cover 10 on one side of the pulse combustion chamber 4 in the I-shaped through hole is rapidly opened by high-temperature high-pressure gas in the two-pulse combustion chamber 1, the high-temperature high-pressure gas enters the pulse combustion chamber 4 through the I-shaped through hole, along with more driving holes are opened, the flow area between the two-pulse combustion chamber 1 and the pulse combustion chamber 4 is increased, more fuel gas is sprayed out from the spray pipe 6, the thrust of the two-stage pulse solid rocket engine can be increased accordingly, and the variable thrust adjustment of the two-stage pulse solid rocket engine is realized.
Example 2:
on the basis of embodiment 1, the closure opening device includes: the ignition device comprises a pin 11, a spring 12, an ignition product and an excitation device, wherein a prefabricated hole is radially formed in the periphery of a non-metal blanking cover 10 on one side, facing a secondary pulse combustion chamber 1, of an I-shaped through hole, after the pin 11, the spring 12 and the ignition product are sequentially arranged in the prefabricated hole, an opening of the prefabricated hole is plugged from the periphery of a compartment 3, a through hole is formed in the plugging position, the excitation device penetrates through the through hole to be connected with the ignition product, two ends of the spring 12 respectively abut against a shaft shoulder of the pin 11 and the ignition product, and before the ignition product acts, the spring 12 is in a compressed state and is used for compacting the ignition product at the plugging position of the compartment; after the initiating device is started to ignite the initiating explosive device, the initiating explosive device explodes to generate explosion shock waves, and the pin 11 is rapidly pushed under the combined action of the explosion shock waves and the restoring force of the spring 12, so that the nonmetal blanking cover 10 facing one side of the two-pulse combustion chamber 1 in the driving hole is broken.
Example 3:
on the basis of the embodiment 2, the initiating explosive device is an electric initiating explosive device 13, the exciting device is an electric exciting device 9, the electric initiating explosive device 13 is electrically connected with the electric exciting device 9, and the electric exciting device 9 is electrified to excite the electric initiating explosive device 13 to explode.
Example 4:
in any of embodiments 1 to 3, the compartment 3 is made of high-strength steel or high-strength stainless steel, and the non-metallic closure 10 is made of high-strength engineering plastic.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. The multistage pulse solid rocket engine with the adjustable thrust comprises more than two pulse combustion chambers, explosives and a bulkhead (3), wherein the pulse combustion chambers are sequentially connected, the explosives are arranged in the pulse combustion chambers, and the bulkhead (3) is used for connecting adjacent pulse combustion chambers, and is characterized in that more than one T-shaped through hole and more than one I-shaped through hole are formed in the bulkhead (3) and are used for communicating the adjacent pulse combustion chambers;
the large end of the T-shaped through hole faces to the rear end combustion chamber, a blocking cover for blocking the T-shaped through hole is arranged in the large end of the T-shaped through hole, the blocking cover falls off under the action of high-temperature and high-pressure gas in the front end combustion chamber, and the corresponding T-shaped through hole is opened;
the high-temperature high-pressure gas in the front end combustion chamber pushes open the blocking cover in the I-shaped through hole towards the rear end combustion chamber, and opens the corresponding I-shaped through hole to adjust the flow area between the adjacent combustion chambers.
2. The thrust adjustable multi-stage pulsed solid rocket engine of claim 1 wherein said cap opening means comprises: the novel explosive device comprises a pin (11), a spring (12), an explosive device and an excitation device, wherein a prefabricated hole is radially formed in the periphery of a blocking cover, facing one side of a front-end combustion chamber, of an I-shaped through hole, after the pin (11), the spring (12) and the explosive device are sequentially installed in the prefabricated hole, an opening of the prefabricated hole is blocked from the periphery of a partition (3), a through hole is formed in a blocking position, the excitation device penetrates through the through hole to be connected with the explosive device, two ends of the spring (12) respectively abut against a shaft shoulder of the pin (11) and the explosive device, before the explosive device acts, the spring (12) is in a compression state, after the excitation device is started to ignite the explosive device, and under the combined action of explosive shock waves and restoring force of the spring (12), the pin (11) is pushed to break the blocking cover, facing one side of the.
3. The thrust adjustable multi-stage pulse solid rocket engine according to claim 1 or 2, wherein said caps are non-metallic caps (10).
4. The thrust-modulated multistage pulse solid rocket engine of claim 2 wherein the initiating means is an electrical initiating means (13), the energizing means is an electrical energizing means (9), the electrical connection between the electrical initiating means (9) and the electrical initiating means (13) is such that the electrical energizing means (9) energizes the electrical initiating means (13) to detonate.
5. Thrust-adjustable multistage pulse solid rocket engine according to claim 1 or 2, wherein said compartments (3) are made of high-strength steel or high-strength stainless steel.
6. The thrust adjustable multi-stage pulse solid rocket engine according to claim 3, wherein the non-metallic cap (10) is made of high strength engineering plastic.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201910781302.XA CN110469425B (en) | 2019-08-23 | 2019-08-23 | Thrust-adjustable multi-stage pulse solid rocket engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910781302.XA CN110469425B (en) | 2019-08-23 | 2019-08-23 | Thrust-adjustable multi-stage pulse solid rocket engine |
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| CN110469425A CN110469425A (en) | 2019-11-19 |
| CN110469425B true CN110469425B (en) | 2020-08-18 |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111502862B (en) * | 2020-04-29 | 2023-04-07 | 内蒙动力机械研究所 | Plug-in type low pass filter |
| CN112610984B (en) * | 2020-12-14 | 2022-11-11 | 上海航天化工应用研究所 | Gas isolating device suitable for high temperature and high pressure |
| CN112464387B (en) * | 2021-01-26 | 2021-04-16 | 中国人民解放军国防科技大学 | Thrust matching design method for throat plug type variable-thrust solid engine |
| CN115523056B (en) * | 2022-10-31 | 2024-06-04 | 北京中科宇航技术有限公司 | Solid rocket engine connected by clamping ring |
| CN116464577B (en) * | 2023-04-26 | 2024-04-19 | 浙江省军工集团股份有限公司 | Double-combustion-chamber multipurpose turbine solid rocket engine |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2734025B1 (en) * | 1995-05-11 | 1997-08-01 | Europ Propulsion | PULSED LIQUID PROPERTY PULSE MOTOR |
| RU2133864C1 (en) * | 1997-09-10 | 1999-07-27 | Государственное научно-производственное предприятие "Сплав" | Solid-propellant rocket engine |
| US6532741B2 (en) * | 2001-06-29 | 2003-03-18 | United Technologies Corporation | Gas generator for producing adjustable flow |
| CN107269424B (en) * | 2017-07-25 | 2023-04-18 | 南京理工大学 | Secondary ignition structure of solid rocket engine |
| CN107781062B (en) * | 2017-09-28 | 2019-06-07 | 北京理工大学 | A kind of Double pulse solid rocket motor interstage sealing structure device |
| CN107939549B (en) * | 2017-11-08 | 2019-10-15 | 航宇救生装备有限公司 | A kind of miniature multistage pulses thrust solid propellant rocket |
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