CN109404164A - A kind of charge constitution that solid propellant rocket combustibility improves - Google Patents
A kind of charge constitution that solid propellant rocket combustibility improves Download PDFInfo
- Publication number
- CN109404164A CN109404164A CN201811078933.7A CN201811078933A CN109404164A CN 109404164 A CN109404164 A CN 109404164A CN 201811078933 A CN201811078933 A CN 201811078933A CN 109404164 A CN109404164 A CN 109404164A
- Authority
- CN
- China
- Prior art keywords
- quoit
- charge
- powder
- solid propellant
- propellant rocket
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
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
- F02K9/24—Charging rocket engines with solid propellants; Methods or apparatus specially adapted for working solid propellant charges
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
- Manufacture Of Metal Powder And Suspensions Thereof (AREA)
Abstract
The present invention provides a kind of charge constitution that solid propellant rocket combustibility improves, quoit (2) are embedded in powder column when powder charge, after the powder charge (3) of grain surface is ignited, quoit (2) is heated, when the critical surface temperature of quoit (2) and hot spots reaches the ignition temperature of powder charge (3), it is close to the powder charge (3) at this to light at once, form the taper hole with quoit (2) for axle center, considerably increase burning area, to greatly increase the thrust of engine, quoit (2) is exposed to the part in flame, constantly heated by flame, when temperature reaches the fusing point of quoit, quoit (2) is melted.Technology difficulty when powder charge casting is effectively reduced, the quoit of different materials can be embedded to according to different performance requirements, to reach required performance indicator requirement.
Description
Technical field
The invention belongs to solid propellant rocket, charge constitution, especially a kind of solid propellant rocket combustibility is mentioned
High charge constitution.
Background technique
Solid propellant rocket is the power device that weaponry is widely applied, weight of the powder charge as solid propellant rocket
Component part is wanted, combustion type mainly has internal bore burning, the burning of interior exit orifice, cigarette burning etc..End-burning grain is because of the letter of its shape
Singly, the advantages that packing factor is high is widely used in continuation of the journey grade solid propellant rocket.When using end-burning grain, since end is fired
The burning area of powder column is too small, causes the thrust of such engine operation too low, and the overload that can be provided is less than normal, using being limited
System.At this moment just need to develop a kind of charge constitution for improving such solid propellant rocket combustibility.
For the thrust for improving end-burning grain engine, the propellant using high burn rate is one of approach, however, to make at present
Burn rate increases exponentially, and chemically solves merely to be very difficult from formula, and can also give propellant its
Its internal ballistics attributes brings detrimental effect, while also considerably increasing product cost.In current engineering practice, take
Measure is a certain number of wires (as shown in Figure 3) of embedment, and technique requirement when this kind of method is to casting powder charge is relatively high, real
It is bigger to apply difficulty, virtually improves cost.Furthermore wire is broken, and is embedded in and is not easy to be found in powder charge,
There is certain influence to powder charge integrality.The quoit that the present invention uses effectively reduces work when powder charge casting as shown in Figure 1
Skill difficulty can be embedded to the quoit of different materials according to different performance requirements, to reach required performance indicator requirement.
Summary of the invention
The purpose of the present invention: in order to overcome the above-mentioned deficiencies of the prior art, such solid is improved the present invention provides a kind of
The charge constitution of rocket engine combustibility.
Technical solution of the present invention:
A kind of charge constitution that solid propellant rocket combustibility improves, which is characterized in that buried in powder column when powder charge
Enter quoit 2.
The charge constitution that a kind of solid propellant rocket combustibility improves, the quoit 2 are with powder column etc.
Long and diameter is less than the cylindrical, hollow cyclic structure of powder column.
The charge constitution that a kind of solid propellant rocket combustibility improves, the diameter of the quoit 2 are medicine
2/3rds of column diameter.
The charge constitution that a kind of solid propellant rocket combustibility improves generates thrust from big according to engine
To the material sequence of small selection quoit 2 are as follows: silver-colored > copper > tungsten > aluminium > magnesium > steel.
The charge constitution that a kind of solid propellant rocket combustibility improves, the powder charge 3 of grain surface are ignited
Afterwards, quoit 2 is heated, and when the critical surface temperature of quoit 2 and hot spots reaches the ignition temperature of powder charge 3, is close at this
Powder charge 3 light at once, form the taper hole with quoit 2 for axle center, considerably increase burning area, to greatly improve
The thrust of engine, quoit 2 are exposed to the part in flame, are constantly heated by flame, when temperature reaches quoit
When fusing point, quoit 2 is melted.
Advantages of the present invention:
The thrust that can be improved continuation of the journey grade end combustion solid propellant rocket engine operation, to meet weaponry to hair
The requirement of motivation overload.
Detailed description of the invention:
Fig. 1 is embedment quoit powder charge sectional view；
Fig. 2 is powder charge combustion process figure around quoit；
Fig. 3 is embedment wire powder charge sectional view.
Specific embodiment:
The invention will be described in further detail with reference to the accompanying drawing.
As shown in Fig. 2, being close to should when the critical surface temperature of quoit 2 and hot spots reaches the ignition temperature of powder charge 3
The powder charge 3 at place is lighted at once, is formd the taper hole 1 with quoit 2 for axle center, is considerably increased burning area, thus greatly
Improve the thrust of engine.As interface constantly elapses, quoit 2 is gradually exposed in flame, constantly for added by flame
Heat when the temperature in somewhere reaches the fusing point of quoit 2, and is melted at once.Therefore, go deep into 2 phase of quoit in flame
When in a heat absorption column, it constantly absorbs heat, and heat is passed to the quoit 2 inside powder column, and be constantly melted
Fall.
Before buried metal circle, cleaning appropriate should be carried out to quoit surface, to guarantee that powder charge can be pasted with quoit
It closes, and then guarantees that powder charge medicine can be ignited in time.During carrying out end-burning grain filling, first pasted in combustion chamber shell body
Heat insulation layer and lining, then carry out the casting of powder charge.During casting, arrange that required quoit is embedded into powder charge.
It is different as brought by the quoit of arrangement different metal material along quoit burn rate motor power, work
In journey implementation process, the quoit of different materials can be selected according to weaponry to the different demands of motor power, to obtain
Different size of thrust.For increasing along quoit burn rate and then improving the ability of thrust, common several metal material effects
Fruit sequence is as follows: silver-colored > copper > tungsten > aluminium > magnesium > steel.
Claims (5)
1. the charge constitution that a kind of solid propellant rocket combustibility improves, which is characterized in that be embedded in powder column when powder charge
Quoit (2).
2. the charge constitution that a kind of solid propellant rocket combustibility according to claim 1 improves, which is characterized in that
The quoit (2) is the cylindrical, hollow cyclic structure that and diameter isometric with powder column is less than powder column.
3. the charge constitution that a kind of solid propellant rocket combustibility according to claim 2 improves, which is characterized in that
The diameter of the quoit (2) is 2/3rds of powder column diameter.
4. the charge constitution that a kind of solid propellant rocket combustibility according to claim 2 improves, which is characterized in that
The material sequence that thrust selects quoit (2) from big to small is generated according to engine are as follows: silver-colored > copper > tungsten > aluminium > magnesium > steel.
5. the charge constitution that a kind of solid propellant rocket combustibility according to claim 2 improves, which is characterized in that
After the powder charge (3) of grain surface is ignited, quoit (2) is heated, and quoit (2) and the critical surface temperature of hot spots reach
When the ignition temperature of powder charge (3), it is close to the powder charge (3) at this and lights at once, forms the taper hole with quoit (2) for axle center,
Burning area is considerably increased, to greatly increase the thrust of engine, quoit (2) is exposed to the part in flame,
It is constantly heated by flame, when temperature reaches the fusing point of quoit, quoit (2) is melted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811078933.7A CN109404164B (en) | 2018-09-17 | 2018-09-17 | Charge structure for improving combustion performance of solid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811078933.7A CN109404164B (en) | 2018-09-17 | 2018-09-17 | Charge structure for improving combustion performance of solid rocket engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109404164A true CN109404164A (en) | 2019-03-01 |
| CN109404164B CN109404164B (en) | 2021-08-03 |
Family
ID=65464823
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811078933.7A Active CN109404164B (en) | 2018-09-17 | 2018-09-17 | Charge structure for improving combustion performance of solid rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109404164B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109973245A (en) * | 2019-03-07 | 2019-07-05 | 北京灵动飞天动力科技有限公司 | A kind of embedding clad metal wire end combustion powder charge |
| CN110145411A (en) * | 2019-05-27 | 2019-08-20 | 上海新力动力设备研究所 | A kind of solid propellant rocket inner hole cast charge constitution and method with inner cavity partition |
| CN114483374A (en) * | 2022-02-27 | 2022-05-13 | 西北工业大学 | Solid rocket engine grain structure embedded with metal wire |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201269719Y (en) * | 2008-09-09 | 2009-07-08 | 陈卓斌 | Miniature solid rocket apparatus |
| DE202011103297U1 (en) * | 2011-06-30 | 2012-02-03 | Mgtu N.E. Baumana | Device for igniting a sample of rocket solid |
| EP2503135A2 (en) * | 2011-03-23 | 2012-09-26 | ROXEL France | Dual-pulse and multi-pulse thrust generators |
| US20130031888A1 (en) * | 2011-08-01 | 2013-02-07 | The Aerospace Corporation | Systems, Methods, and Apparatus for Providing a Multi-Fuel Hybrid Rocket Motor |
| CN106121862A (en) * | 2016-08-11 | 2016-11-16 | 西北工业大学 | A kind of solid rocket motor grain fixing device |
| US20180169937A1 (en) * | 2007-03-22 | 2018-06-21 | Ronald D. Jones | Additive manufactured thermoplastic-nanocomposite aluminum hybrid rocket fuel grain and method of manufacturing same |
-
2018
- 2018-09-17 CN CN201811078933.7A patent/CN109404164B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20180169937A1 (en) * | 2007-03-22 | 2018-06-21 | Ronald D. Jones | Additive manufactured thermoplastic-nanocomposite aluminum hybrid rocket fuel grain and method of manufacturing same |
| CN201269719Y (en) * | 2008-09-09 | 2009-07-08 | 陈卓斌 | Miniature solid rocket apparatus |
| EP2503135A2 (en) * | 2011-03-23 | 2012-09-26 | ROXEL France | Dual-pulse and multi-pulse thrust generators |
| DE202011103297U1 (en) * | 2011-06-30 | 2012-02-03 | Mgtu N.E. Baumana | Device for igniting a sample of rocket solid |
| US20130031888A1 (en) * | 2011-08-01 | 2013-02-07 | The Aerospace Corporation | Systems, Methods, and Apparatus for Providing a Multi-Fuel Hybrid Rocket Motor |
| CN106121862A (en) * | 2016-08-11 | 2016-11-16 | 西北工业大学 | A kind of solid rocket motor grain fixing device |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109973245A (en) * | 2019-03-07 | 2019-07-05 | 北京灵动飞天动力科技有限公司 | A kind of embedding clad metal wire end combustion powder charge |
| CN110145411A (en) * | 2019-05-27 | 2019-08-20 | 上海新力动力设备研究所 | A kind of solid propellant rocket inner hole cast charge constitution and method with inner cavity partition |
| CN110145411B (en) * | 2019-05-27 | 2020-09-18 | 上海新力动力设备研究所 | Solid rocket engine inner hole tubular charging structure with inner cavity partition plate and method |
| CN114483374A (en) * | 2022-02-27 | 2022-05-13 | 西北工业大学 | Solid rocket engine grain structure embedded with metal wire |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109404164B (en) | 2021-08-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109404164A (en) | A kind of charge constitution that solid propellant rocket combustibility improves | |
| US1376316A (en) | Projectile | |
| CN107620652B (en) | Multi-pulse thrust-adjustable solid propeller | |
| JP3649251B2 (en) | Serial arc plasma injector | |
| KR101249772B1 (en) | Projectile with high explosive | |
| US8650921B2 (en) | Method and device for explosion forming | |
| US5997667A (en) | Fire starting flare | |
| CN107925222A (en) | Ignition plug for I. C. engine | |
| GB2257498A (en) | Hollow charges | |
| US2972948A (en) | Shaped charge projectile | |
| US6237494B1 (en) | Ignition component for a pyrotechnic composition or propellant charge | |
| US4907487A (en) | Apparatus for and method of accelerating a projectile through a capillary passage and projectile therefor | |
| SE533046C2 (en) | Methods for electric over-ignition and combustion of propellant charge, as well as divarge and ammunition shot accordingly | |
| US8245640B1 (en) | Melted metal dispersal warhead | |
| US2447200A (en) | Exhaust nozzle for rocket motors | |
| FR2526154A1 (en) | FLAT BODY FOR FRAGMENTABLE PROJECTILES AND BLEEDED COMBAT HEADS | |
| JP2000055597A (en) | Launching powder | |
| US5431105A (en) | Electrothermal chemical cartridge | |
| CA1261202A (en) | Electric detonator | |
| US4727639A (en) | Method of manufacturing subcaliber segmented sabot projectile | |
| US20020195017A1 (en) | Reverse ignition cartridge | |
| US2419371A (en) | Cartridge | |
| CN105492113A (en) | Gas generator | |
| EP1444478B1 (en) | Transverse plasma injector ignitor | |
| CN113624079B (en) | Electric ignition device for multipoint ignition in large-caliber gun bore and assembling method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |