CN114483374A - Solid rocket engine grain structure embedded with metal wire - Google Patents
Solid rocket engine grain structure embedded with metal wire Download PDFInfo
- Publication number
- CN114483374A CN114483374A CN202210191200.4A CN202210191200A CN114483374A CN 114483374 A CN114483374 A CN 114483374A CN 202210191200 A CN202210191200 A CN 202210191200A CN 114483374 A CN114483374 A CN 114483374A
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- Prior art keywords
- grain
- combustion
- metal wires
- central
- metal wire
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- Pending
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- 239000002184 metal Substances 0.000 title claims abstract description 48
- 239000007787 solid Substances 0.000 title claims abstract description 25
- 239000002360 explosive Substances 0.000 claims abstract description 14
- 235000013339 cereals Nutrition 0.000 claims description 55
- 239000003380 propellant Substances 0.000 claims description 9
- 235000020985 whole grains Nutrition 0.000 claims description 2
- 238000002485 combustion reaction Methods 0.000 abstract description 31
- 239000007788 liquid Substances 0.000 description 4
- 239000000126 substance Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 239000003814 drug Substances 0.000 description 2
- 229940079593 drug Drugs 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 239000004449 solid propellant Substances 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
Images
Classifications
-
- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Powder Metallurgy (AREA)
Abstract
The invention provides a solid rocket engine grain structure embedded with metal wires. The explosive column adopts an integral structure that the inner side surface and the outer side surface are combusted simultaneously, the cross sections of the inner combustion surfaces of the central explosive column and the sleeve type outer side explosive column are both star-shaped sections, and the metal wires are axially embedded in the inner side of the combustion surface of the central explosive column and the wall surface of the outer side explosive column in a perpendicular mode so as to ensure that the engine has high thrust and high maneuverability in the initial section and the tail section and has better cruising ability in the middle flying stage. In the take-off stage, the inner combustion surface, the outer combustion surface and the central charge metal wire are simultaneously combusted, so that higher thrust and good maneuverability can be obtained. In the middle stage, the central charge metal wire is burnt out, the inner combustion surface is in reduced surface combustion, the outer combustion surface is in increased surface combustion, and a stable thrust curve and high cruising ability can be obtained. In the tail flight stage, the metal wires on the wall surface are burnt, so that the thrust and the maneuverability are effectively improved. In addition, the inner combustion surface and the outer combustion surface are combusted simultaneously, so that the disturbance of airflow is enhanced, and the combustion efficiency is improved while the combustion is enhanced.
Description
Technical Field
The invention belongs to the technical field of solid rocket engines, and particularly relates to a solid rocket engine grain structure embedded with metal wires.
Background
Rocket engines are power devices which rely on changes in their system momentum to produce direct reaction forces. If the energy and working medium come from the chemical propellant stored in the system, the chemical rocket engine is called as a chemical rocket engine, and the rocket engine is divided into a solid, a liquid and a solid-liquid hybrid rocket engine according to the physical state of the chemical propellant. The solid rocket engine is a product combining the solid rocket technology and the modern industry, has the advantages of simple structure, low manufacturing cost, short preparation time, high reliability, long service life and the like compared with a liquid rocket engine, is used as a main or auxiliary power system, is widely applied to missiles and carrier rockets, and is particularly favored in the military field. In recent decades, the advent of high-energy solid propellants, advanced charge design and the use of large grain casting processes, the advent of excellent casing materials and ablation-resistant materials, and the successful research of efficient and reliable thrust vector control devices have enabled solid rocket engines to be used as power plants comparable to liquid rocket engines in the large, remote and strategic weapons fields. In the power device used by various tactical and strategic missile weapons, the solid rocket engine is in the absolute domination position.
The grain is a solid propellant with specific geometry and size, and is the energy source and working medium source of the engine. The geometrical shape and size of the grain determine the gas generation rate of the engine and the change rule thereof, and therefore, the relation between the pressure of the combustion chamber and the thrust of the engine, which changes along with time, is also determined. The design level of the explosive column greatly influences the performance of the engine and is a core part of the engine design.
Disclosure of Invention
The invention aims to solve the technical problem of providing a solid rocket engine grain structure embedded with metal wires, so as to meet different requirements of the solid rocket on thrust in different flight stages and improve the combustion efficiency of a propellant to a certain extent. The technology of the invention firstly provides larger thrust and extremely high maneuverability in the takeoff stage by matching larger combustion area with the combustion of the metal wire with high energy density. Along with the burnout of the inner layer metal wire, the reduced surface combustion of the central grain and the surface-increasing combustion of the outer grain, the thrust is almost kept unchanged so as to ensure long-distance cruising. Finally, the metal wires on the wall surface are combusted, certain thrust is increased for the tail flight stage, and therefore good maneuverability is kept for finding a target or avoiding an obstacle.
Technical scheme
The invention aims to provide a solid rocket engine grain structure embedded with metal wires.
The technical scheme of the invention is as follows:
the utility model provides an inlay solid rocket engine grain structure of wire which characterized in that: the whole grain main body consists of a central grain with a certain length of metal wire embedded inside and a sleeve type outer grain with a certain length of metal wire embedded close to the wall surface, and the central lines of the central grain and the outer grain are superposed; the cross section of the central grain is in a star shape similar to a flower, and the convex part is in an arc shape; the sleeve-type grain is hollow, the cross section of the hollow part is the same as that of the central grain, the cross section of the outermost side of the solid part is circular, and a gap with a certain distance is formed between the central grain and the sleeve-type grain.
The solid rocket engine grain structure embedded with the metal wire is characterized in that: the cross section of the central grain is in a star shape similar to a flower, five arc bulges similar to petals are uniformly distributed along the circumference, five groups of metal wires are embedded into the five bulge parts along the radial direction, each group of metal wires is uniformly distributed in one bulge along the axial direction, and the length of each metal wire accounts for one tenth of the radius of the grain; the inside of the convex part has no metal wire and is propellant.
The solid rocket engine grain structure embedded with the metal wire is characterized in that: the outer annular tube type grain is of a hollow structure, the cross section of the hollow part has the same shape as that of the central grain, but the shape is larger; the metal wires are positioned in the propellant close to the wall surface of the engine and are also arranged along the radial direction, five groups of metal wires are uniformly distributed along the circumference, the length of the metal wires accounts for one tenth of the radius of the explosive column, and the rest part of the metal wires is the propellant.
The invention has the following beneficial effects:
(1) the invention adopts a star-shaped structure with the inner side surface and the outer side surface simultaneously burning, thereby not only obtaining higher filling ratio, but also improving the burning efficiency to a certain extent. (2) The convex part of the star-shaped drug column is of an arc-shaped structure, so that stress concentration is avoided, and the structural integrity of the drug column in the flying process is ensured. (3) The thrust generated by combustion is greatly improved no matter in a take-off stage or a landing stage due to the addition of the metal wires, and the maneuverability of the rocket is greatly improved. (4) In the middle flight stage, the inner side grain is combusted in a surface-reducing mode, the outer side grain is combusted in a surface-increasing mode, and therefore the total thrust is almost unchanged, and the endurance is improved to a certain extent.
Drawings
FIG. 1: integral structure diagram of solid rocket engine grain structure embedded with metal wire
FIG. 2 is a schematic diagram: solid rocket engine grain structure embedded with metal wire is along grain axial top view
FIG. 3: solid rocket engine grain structure embedded with metal wires is cut along the direction of top view A-A
FIG. 4: central powder column schematic diagram of solid rocket engine powder column structure embedded with metal wires
FIG. 5: single wire structure schematic
In the figure: 1-central explosive column, 2-central explosive column metal wire, 3-outer explosive column, and 4-outer explosive column wall surface metal wire.
Detailed Description
The invention will now be further described with reference to the accompanying drawings in which:
with reference to fig. 1, the present invention provides a wire-embedded solid rocket engine grain structure with high combustion efficiency with good acceleration and maneuverability during takeoff and good maneuverability during tail flight.
During the take-off of the missile, the engine is required to provide larger thrust and has higher maneuvering capability. During the takeoff phase, a large amount of heat generated by combustion can meet the requirement. The burning direction of the grain is radial, the burning starting point is the outer surface of the star-shaped central grain 1 and the inner side surface of the outer side sleeve-type grain 3, wherein the inner surface of the central grain is embedded with a metal wire 2 with extremely high energy density. The outer surface of the central grain 1 is in reduced-area combustion, the inner surface of the outer grain 3 is in increased-area combustion, and simultaneously, the violent combustion of the metal wire is assisted to release huge energy instantaneously, so that the thrust and the maneuverability of the rocket in the takeoff stage are greatly improved. In addition, the simultaneous combustion of the inner surface of the central grain 1 and the outer surface of the outer sleeve-type grain 3 enhances the disturbance of the inner airflow, and improves the combustion efficiency and the combustion rate at this stage. Along with the combustion process, the metal wires 2 in the central explosive column 1 are burnt out, the combustion process is relatively stable, and the cruising ability of the rocket is improved. And then, the combustion enters a tail stage, the metal wire 4 on the wall surface begins to be added into the combustion process, and the thrust of the engine is increased, so that the maneuverability of the tail flight stage is improved, and the overall maneuverability of the missile is effectively enhanced.
Claims (3)
1. The utility model provides a solid rocket engine grain that inlays wire which characterized in that: the whole grain main body consists of a central grain with a certain length of metal wire embedded inside and a sleeve type outer grain with a certain length of metal wire embedded close to the wall surface, and the central lines of the central grain and the outer grain are superposed; the cross section of the central grain is in a star shape similar to a flower, and the convex part is in an arc shape; the sleeve-type grain is a hollow structure, the cross section of the sleeve-type grain is the same as that of the central grain, and a gap with a certain distance is arranged between the two parts.
2. The solid rocket engine grain embedded with metal wires of claim 1, wherein: the cross section of the central grain is in a star shape similar to a flower, five arc bulges similar to petals are uniformly distributed along the circumference, five groups of metal wires are embedded into the five bulge parts along the radial direction, each group of metal wires is uniformly distributed in each bulge along the axial direction, and the length of each metal wire accounts for one tenth of the radius of the grain; the inside of the convex explosive column has no metal wire and is propellant.
3. The solid rocket engine grain embedded with metal wires of claim 1, wherein: the outer annular tube type grain is of a hollow structure, the cross section of the hollow part has the same shape as that of the central grain, but the diameter of the hollow part is larger; the metal wires are positioned in the propellant close to the wall surface of the engine and are also arranged along the radial direction, five groups of metal wires are uniformly distributed along the circumference, the length of the metal wires accounts for one tenth of the radius of the explosive column, and the rest part of the metal wires is the propellant.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210191200.4A CN114483374A (en) | 2022-02-27 | 2022-02-27 | Solid rocket engine grain structure embedded with metal wire |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210191200.4A CN114483374A (en) | 2022-02-27 | 2022-02-27 | Solid rocket engine grain structure embedded with metal wire |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114483374A true CN114483374A (en) | 2022-05-13 |
Family
ID=81484768
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210191200.4A Pending CN114483374A (en) | 2022-02-27 | 2022-02-27 | Solid rocket engine grain structure embedded with metal wire |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114483374A (en) |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1325929A (en) * | 1962-05-07 | 1963-05-03 | Atlantic Res Corp | Semi-solid monopropellant and rocket engine combustion process based on this process |
| FR1336958A (en) * | 1962-09-05 | 1963-09-06 | Du Pont | Ignition device for solid propellants |
| GB1168657A (en) * | 1966-02-02 | 1969-10-29 | Zeebrugge Forges Sa | Rocket Propellent Blocks. |
| GB1172221A (en) * | 1960-06-09 | 1969-11-26 | Atlantic Res Corp | Improvements in or relating to Propellent Grains |
| DE1526837A1 (en) * | 1966-03-19 | 1969-12-18 | Nitrochemie Gmbh | Solid rocket system |
| EP0089476A2 (en) * | 1982-03-23 | 1983-09-28 | Bayern-Chemie Gesellschaft für flugchemische Antriebe mit beschränkter Haftung | Composite propellant and process for its manufacture |
| FR2835571A1 (en) * | 2002-02-01 | 2003-08-08 | Celerg | Free pyrotechnic charge e.g. for rocket motor has channel of starshaped cross-section to limit residual pyrotechnic material |
| RU2241846C1 (en) * | 2003-04-02 | 2004-12-10 | Федеральное государственное унитарное предприятие "Научно-исследовательский институт полимерных материалов" | Rocket engine telescopic solid-propellant charge |
| CN106870206A (en) * | 2017-03-29 | 2017-06-20 | 北京航空航天大学 | A kind of quick response solid-liquid rocket combines powder column |
| CN109404164A (en) * | 2018-09-17 | 2019-03-01 | 江西洪都航空工业集团有限责任公司 | A kind of charge constitution that solid propellant rocket combustibility improves |
| CN112392629A (en) * | 2021-01-04 | 2021-02-23 | 北京航空航天大学 | Solid-liquid-solid co-combustion chamber combined power rocket engine and aircraft |
-
2022
- 2022-02-27 CN CN202210191200.4A patent/CN114483374A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1172221A (en) * | 1960-06-09 | 1969-11-26 | Atlantic Res Corp | Improvements in or relating to Propellent Grains |
| FR1325929A (en) * | 1962-05-07 | 1963-05-03 | Atlantic Res Corp | Semi-solid monopropellant and rocket engine combustion process based on this process |
| FR1336958A (en) * | 1962-09-05 | 1963-09-06 | Du Pont | Ignition device for solid propellants |
| GB1168657A (en) * | 1966-02-02 | 1969-10-29 | Zeebrugge Forges Sa | Rocket Propellent Blocks. |
| DE1526837A1 (en) * | 1966-03-19 | 1969-12-18 | Nitrochemie Gmbh | Solid rocket system |
| EP0089476A2 (en) * | 1982-03-23 | 1983-09-28 | Bayern-Chemie Gesellschaft für flugchemische Antriebe mit beschränkter Haftung | Composite propellant and process for its manufacture |
| FR2835571A1 (en) * | 2002-02-01 | 2003-08-08 | Celerg | Free pyrotechnic charge e.g. for rocket motor has channel of starshaped cross-section to limit residual pyrotechnic material |
| RU2241846C1 (en) * | 2003-04-02 | 2004-12-10 | Федеральное государственное унитарное предприятие "Научно-исследовательский институт полимерных материалов" | Rocket engine telescopic solid-propellant charge |
| CN106870206A (en) * | 2017-03-29 | 2017-06-20 | 北京航空航天大学 | A kind of quick response solid-liquid rocket combines powder column |
| CN109404164A (en) * | 2018-09-17 | 2019-03-01 | 江西洪都航空工业集团有限责任公司 | A kind of charge constitution that solid propellant rocket combustibility improves |
| CN112392629A (en) * | 2021-01-04 | 2021-02-23 | 北京航空航天大学 | Solid-liquid-solid co-combustion chamber combined power rocket engine and aircraft |
Non-Patent Citations (2)
| Title |
|---|
| 于洋: "一种自由装填式组合药柱的低温三维结构完整性分析", 固体火箭技术, vol. 30, no. 1, pages 34 - 38 * |
| 詹君彪: "减面燃烧规律的药柱选用准则", 弹箭与制导学报, vol. 35, no. 5, pages 85 - 91 * |
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| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20220513 |