CN112211749A - Small solid rocket engine - Google Patents
Small solid rocket engine Download PDFInfo
- Publication number
- CN112211749A CN112211749A CN202010982883.6A CN202010982883A CN112211749A CN 112211749 A CN112211749 A CN 112211749A CN 202010982883 A CN202010982883 A CN 202010982883A CN 112211749 A CN112211749 A CN 112211749A
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- China
- Prior art keywords
- oxidant
- gunpowder
- layer
- combustion
- combustion chamber
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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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/10—Shape or structure of solid propellant charges
- F02K9/18—Shape or structure of solid propellant charges of the internal-burning type having a star or like shaped internal cavity
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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
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
- F02K9/346—Liners, e.g. inhibitors
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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
- F02K9/97—Rocket nozzles
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
The invention provides a small solid rocket engine, and relates to the technical field of rocket engines. The invention improves the explosive column and the spray pipe in the combustion chamber. Divide into oxidant layer and powder layer with the powder column, let in gas channel through oxidant hole and powder hole, can effectively prevent the unstable insecurity key element of mixing the powder column, set up the oxidant layer simultaneously and play certain heat protection effect to the combustion chamber casing, be spiral align to grid with oxidant hole and powder hole, can effectively control the combustion process, realize fractional combustion and complete combustion, promote the combustion chamber combustion performance. In addition, the engine spray pipe is designed into a rotatable flexible joint and a single-side expansion type spray pipe, so that the radial direction speed can be effectively controlled while the airtightness and the rotational stability of the spray pipe are ensured, the vector control of the engine is realized, and the control on the emission range and the direction of the engine is promoted.
Description
Technical Field
The invention belongs to the technical field of rocket engines, and particularly relates to a small solid rocket engine.
Background
The solid rocket engine belongs to the chemical rocket engine, and uses solid matter (energy source and working medium) as propellant. The solid propellant is ignited and then burnt in the combustion chamber to generate high-temperature and high-pressure fuel gas, namely chemical energy is converted into heat energy; the gas expands and accelerates through the jet pipe, the heat energy is converted into kinetic energy, and the kinetic energy is discharged from the jet pipe at an extremely high speed so as to generate thrust to fly forwards. The solid rocket engine is a power device of various weapons, and has wide application in the field of aerospace. The device has the advantages of simple structure, maneuverability, reliability and easy maintenance, and greatly meets the requirements of modern wars and aerospace career.
However, the solid propellant is affected by various loading effects and temperature and humidity changes, so that physical or chemical property changes may occur, the structural integrity of the solid rocket engine may be damaged, and other defects may be caused. The defects of the traditional solid rocket engine include combustion chamber defects and nozzle defects. These two defects can generate an 'ultra' combustion surface when the powder fuel is combusted, which can cause a great threat, so that the optimization of the structure of the powder fuel column in the combustion chamber and the improvement of the performance of the spray pipe are necessary for the performance and the development of the solid rocket engine.
The invention improves the grain structure and the spray pipe structure of the small solid rocket engine, can make up the defects caused by design to a certain extent, improves the performance of the small solid rocket engine, and can also be designed into the structure of a common solid rocket engine.
Disclosure of Invention
The invention aims to solve the technical problem of providing a small solid rocket engine. Compared with the prior art, the invention has the advantages that the explosive column in the combustion chamber is divided into the oxidant layer and the explosive layer, the oxidant layer has the function of easier volatilization, the fuel gas channel is introduced through the oxidant hole and the explosive hole, and the premixed combustion is not carried out, so that the unstable and unsafe factors of the mixed explosive column can be effectively prevented. Meanwhile, the oxidant layer is close to the combustion chamber shell, the gunpowder layer is close to the gas channel, and the existence of the gunpowder column oxidant layer plays a certain heat insulation role for the combustion chamber shell. The oxidant holes and the gunpowder holes are spirally and uniformly arranged to realize staged combustion. In addition, the connecting part of the throat part and the expansion section of the engine spray pipe adopts a rotatable flexible joint, so that the rotating stability of the spray pipe is ensured. The expansion section of the spray pipe adopts a single-side expansion type spray pipe design, and the vector control of the engine is realized.
Technical scheme
The invention aims to provide a small solid rocket engine which can effectively control the combustion process of the engine, obtain radial speed and realize vector control of the engine.
The technical scheme of the invention is as follows:
the utility model provides a small-size solid rocket engine, includes ignition, combustion chamber casing, powder column, abnormal shape spray tube, its characterized in that: based on the structure and the effect of the traditional small solid rocket engine, the invention carries out layered filling and staged combustion on the explosive columns in the combustion chamber, and effectively controls the combustion process; the expansion section of the spray pipe is designed into a rotatable spray pipe, the section of an outlet is set to be an inclined plane, a single-side expansion spray pipe is formed, radial speed is generated, and vector control is achieved.
The explosive column in the combustion chamber is characterized in that: the fuel gas burner is divided into an oxidant layer and a gunpowder layer, the oxidant layer and the gunpowder layer are uniformly matched to ensure that the oxidant and the gunpowder are completely combusted at the same time, the oxidant layer is close to a combustion chamber shell, the gunpowder layer is close to a fuel gas channel, the oxidant layer and the gunpowder layer are separated by a heat insulation layer, and the oxidant layer and the gunpowder layer are respectively connected with the fuel gas channel through an oxidant hole and a gunpowder hole. The oxidant holes and the gunpowder holes are arranged in an inclined opposite impact manner, the oxidant holes are provided with throttling plugs for preventing backfire, the oxidant holes and the fuel gas channel form an angle of 45 degrees, the oxidant holes and the gunpowder holes in the whole fuel gas channel are spirally and uniformly arranged to form 8 groups of oxidant holes and gunpowder holes, each group rotates 90 degrees and is spirally arranged for 2 circles, and the oxidant and the gunpowder form staged combustion along the combustion channel.
The engine nozzle is characterized in that: the designed nozzle has a convergence half angle of 45 degrees, an expansion half angle of 15 degrees, a convergence section connected with the combustion chamber by bolts, and a connection part of a throat part and an expansion section by a rotatable flexible joint, so that the normal direction of an outlet of the oblique section is controlled while the airtightness of the nozzle is ensured.
The invention has the following beneficial effects:
compared with the traditional solid rocket engine, the small solid rocket engine is more optimized in structure. The combustion chamber grain design can guarantee that the combustion chamber is inside to burn steadily, can not cause the explosion danger, and the oxidant layer is close to the combustion chamber shell, can regard as the insulating layer, prevents that the high temperature from resulting in the combustion chamber shell to receive thermal deformation in the gas channel, has increased the life of casing. The oxidant layer and the gunpowder layer are uniformly matched, and the combustion process can be effectively controlled due to the existence of the gunpowder hole and the throttling plug. The oxidant holes and the gunpowder holes can be arranged in a mode that the oxidant and the gunpowder in the gunpowder column can be fully combusted, waste of the gunpowder and the oxidant is avoided, meanwhile, the oxidant and the gunpowder can be controlled to be combusted in a grading mode through the evenly arranged gunpowder holes and the throttle plugs, front flame is combusted firstly, the front flame gradually extends towards the rear portion, and combustion performance of an engine is improved.
The rotatable flexible joint is designed at the engine spray pipe, so that on one hand, the airtightness of the spray pipe can be ensured, and on the other hand, the rotation stability of the spray pipe is ensured. The expansion section of the spray pipe is designed into an oblique section to form a single-side expansion type spray pipe, the speed in the radial direction can be effectively controlled, the structure is simpler compared with a complex vector nozzle, the same vector control effect can be achieved, and the performance of an engine is guaranteed.
Drawings
FIG. 1: small solid rocket engine semi-section
FIG. 2: small solid rocket engine 3/4 sectional view
FIG. 3: small solid rocket engine head section schematic diagram
FIG. 4: overall structure schematic diagram of small solid rocket engine
In the figure: 1-igniter, 2-shell heat insulation layer, 3-oxidant layer, 4-gunpowder layer, 5-pre-ignition fuel, 6-oxidant hole, 7-gunpowder hole, 8-throttling plug, 9-gas channel, 10-brake screw, 11-rotatable flexible joint and 12-oblique section of nozzle outlet.
Detailed Description
The invention will now be further described with reference to the accompanying drawings in which:
with reference to fig. 1, 2, 3 and 4, the invention is a small solid rocket engine. Fig. 1 is a half sectional view of a small solid rocket engine, fig. 2 is a sectional view of the small solid rocket engine 3/4, fig. 3 is a sectional view of a head of the small solid rocket engine, and fig. 4 is a schematic view of an overall structure of the small solid rocket engine.
The igniter 1 is fixed at the front inlet end of the gas channel 9, the igniter 1 is started to ignite firstly, the pre-ignition fuel 5 is ignited, high-temperature gas generated by fuel combustion is introduced into the oxidant hole 6 and the gunpowder hole 7, the oxidant layer 3 and the gunpowder layer 4 are heated to volatilize, and then the oxidant hole 6 and the gunpowder hole 7 are injected into the gas channel 9, the oxidant hole 6 and the gunpowder hole 7 are arranged in an inclined opposite punching mode, so that the oxidant and the gunpowder are mixed fully, and the combustion is more complete. The front oxidant and gunpowder are volatilized in the gunpowder column firstly, and gradually volatilize to the rear end under the action of the spiral arrangement, so that the staged layered combustion is formed. The volatilized oxidant layer is acted by the throttling plug 8, fuel gas cannot rush into a cavity of the oxidant layer, and the cavity and the shell heat-insulating layer 2 jointly form a thick heat-insulating area to prevent the shell from being deformed and damaged due to high temperature. The oxidant is more volatile than gunpowder, and the oxidant and the gunpowder are completely combusted in a proper proportion, so that energy loss is reduced. The high-temperature and high-speed airflow after combustion firstly enters a convergent section of the Laval nozzle, rapid expansion and pressurization are carried out in the convergent section, the front part of the convergent section is fixed with a combustion chamber shell through a brake screw 10, good stability is achieved, and no energy loss of the airflow in the convergent section is guaranteed. Then the airflow enters the expansion section through the throat part, the speed of the airflow is increased sharply, supersonic airflow is formed, and strong thrust is generated. Under the action of the rotatable flexible joint 11 and the oblique section 12 of the outlet of the spray pipe, the radial direction speed can be generated while the air tightness of the spray pipe is ensured, the speed direction of the high-temperature high-speed gas outlet is controlled, and the emission range and the direction of an engine are effectively controlled.
Claims (4)
1. The utility model provides a small-size solid rocket engine, includes ignition, combustion chamber casing, powder column, abnormal shape spray tube, its characterized in that: based on the structure and the effect of the traditional small solid rocket engine, the invention carries out layered filling and staged combustion on the explosive columns in the combustion chamber, and effectively controls the combustion process; the expansion section of the spray pipe is designed into a rotatable spray pipe, the section of an outlet is set into an inclined plane, a single-side expansion spray pipe is formed, and radial speed control is achieved.
2. A small solid-rocket engine according to claim 1 wherein: the designed combustion chamber has a charge column divided into an oxidant layer and a gunpowder layer, the oxidant layer and the gunpowder layer are uniformly matched, the oxidant layer is close to a combustion chamber shell, the gunpowder layer is close to a gas channel, the oxidant layer and the gunpowder layer are separated by a heat insulation layer, and the oxidant layer and the gunpowder layer are respectively connected with the gas channel through an oxidant hole and a gunpowder hole.
3. A small solid rocket engine according to claim 1 and claim 2 wherein: the oxidant holes and the gunpowder holes are arranged in an inclined opposite impact manner, the oxidant holes are provided with throttling plugs for preventing backfire, the oxidant holes and the fuel gas channel form an angle of 45 degrees, the oxidant holes and the gunpowder holes in the whole fuel gas channel are spirally and uniformly arranged to form 8 groups of oxidant holes and gunpowder holes, each group rotates 90 degrees and is spirally arranged for 2 circles, and the oxidant and the gunpowder form staged combustion along the combustion channel.
4. A small solid-rocket engine according to claim 1 wherein: the designed nozzle has a convergence half angle of 45 degrees and an expansion half angle of 15 degrees, the convergence section is connected with the combustion chamber by bolts, and the connecting part of the throat part and the expansion section adopts a rotatable flexible joint to control the normal direction of an outlet of the oblique section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010982883.6A CN112211749A (en) | 2020-09-18 | 2020-09-18 | Small solid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010982883.6A CN112211749A (en) | 2020-09-18 | 2020-09-18 | Small solid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112211749A true CN112211749A (en) | 2021-01-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010982883.6A Pending CN112211749A (en) | 2020-09-18 | 2020-09-18 | Small solid rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112211749A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112983676A (en) * | 2021-03-31 | 2021-06-18 | 西北工业大学 | Novel solid rocket engine combustion chamber grain |
| CN113153580A (en) * | 2021-03-31 | 2021-07-23 | 西北工业大学 | Combined spray pipe of solid rocket engine |
| CN113494386A (en) * | 2021-07-26 | 2021-10-12 | 江西新明机械有限公司 | Miniaturized multifunctional rocket engine |
| CN114857620A (en) * | 2022-04-28 | 2022-08-05 | 湖北航天技术研究院总体设计所 | Solid vector thrust device of large gas quantity gas supply mode |
| CN114922746A (en) * | 2022-06-21 | 2022-08-19 | 西北工业大学 | Solid rocket engine and thrust adjusting method thereof |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB941620A (en) * | 1960-11-23 | 1963-11-13 | Thiokol Chemical Corp | Steering device for rocket powered vehicles |
| US3442084A (en) * | 1966-07-22 | 1969-05-06 | Dynamit Nobel Ag | Multistage solid fuel rocket propulsion unit for the placing of depth charges |
| US5714711A (en) * | 1990-12-31 | 1998-02-03 | Mei Corporation | Encapsulated propellant grain composition, method of preparation, article fabricated therefrom and method of fabrication |
| CN102251879A (en) * | 2011-06-09 | 2011-11-23 | 北京航空航天大学 | Differential adjustable unilateral expansion nozzle |
| CN106837608A (en) * | 2017-04-01 | 2017-06-13 | 北京航空航天大学 | Fire change propulsive solid-liquid rocket structure in a kind of decking end |
| CN108488004A (en) * | 2018-01-25 | 2018-09-04 | 南京航空航天大学 | It is a kind of based on variable inclined wedge angle stay determine detonation engine |
| CN111365144A (en) * | 2020-02-28 | 2020-07-03 | 上海新力动力设备研究所 | Flexible joint and solid rocket engine jet pipe adopting same |
-
2020
- 2020-09-18 CN CN202010982883.6A patent/CN112211749A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB941620A (en) * | 1960-11-23 | 1963-11-13 | Thiokol Chemical Corp | Steering device for rocket powered vehicles |
| US3442084A (en) * | 1966-07-22 | 1969-05-06 | Dynamit Nobel Ag | Multistage solid fuel rocket propulsion unit for the placing of depth charges |
| US5714711A (en) * | 1990-12-31 | 1998-02-03 | Mei Corporation | Encapsulated propellant grain composition, method of preparation, article fabricated therefrom and method of fabrication |
| CN102251879A (en) * | 2011-06-09 | 2011-11-23 | 北京航空航天大学 | Differential adjustable unilateral expansion nozzle |
| CN106837608A (en) * | 2017-04-01 | 2017-06-13 | 北京航空航天大学 | Fire change propulsive solid-liquid rocket structure in a kind of decking end |
| CN108488004A (en) * | 2018-01-25 | 2018-09-04 | 南京航空航天大学 | It is a kind of based on variable inclined wedge angle stay determine detonation engine |
| CN111365144A (en) * | 2020-02-28 | 2020-07-03 | 上海新力动力设备研究所 | Flexible joint and solid rocket engine jet pipe adopting same |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112983676A (en) * | 2021-03-31 | 2021-06-18 | 西北工业大学 | Novel solid rocket engine combustion chamber grain |
| CN113153580A (en) * | 2021-03-31 | 2021-07-23 | 西北工业大学 | Combined spray pipe of solid rocket engine |
| CN113153580B (en) * | 2021-03-31 | 2022-08-16 | 西北工业大学 | Combined spray pipe of solid rocket engine |
| CN112983676B (en) * | 2021-03-31 | 2023-06-13 | 西北工业大学 | Solid rocket engine combustion chamber grain |
| CN113494386A (en) * | 2021-07-26 | 2021-10-12 | 江西新明机械有限公司 | Miniaturized multifunctional rocket engine |
| CN114857620A (en) * | 2022-04-28 | 2022-08-05 | 湖北航天技术研究院总体设计所 | Solid vector thrust device of large gas quantity gas supply mode |
| CN114857620B (en) * | 2022-04-28 | 2023-06-20 | 湖北航天技术研究院总体设计所 | Solid vector thrust device of large-gas-quantity gas supply mode |
| CN114922746A (en) * | 2022-06-21 | 2022-08-19 | 西北工业大学 | Solid rocket engine and thrust adjusting method thereof |
| CN114922746B (en) * | 2022-06-21 | 2024-04-12 | 西北工业大学 | Solid rocket engine and thrust adjusting method thereof |
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Application publication date: 20210112 |
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