CN104454236B - A kind of solid engines change propulsive setting device - Google Patents
A kind of solid engines change propulsive setting device Download PDFInfo
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- CN104454236B CN104454236B CN201410674927.3A CN201410674927A CN104454236B CN 104454236 B CN104454236 B CN 104454236B CN 201410674927 A CN201410674927 A CN 201410674927A CN 104454236 B CN104454236 B CN 104454236B
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Abstract
The present invention relates to solid propellant rocket field, it relates to a kind of solid engines change propulsive setting device. The parts of resistance to ablation and ablation parts are comprised in the combustion chamber of engine, the shape of the parts of resistance to ablation is band four rounded square, four fillets are furnished with four cylinders, cylinder size is mated with the jet pipe of engine rear head, and the central authorities of square have circular hole, and the shape of ablation parts is cruciform, the central authorities of cruciform have circular hole, the parts of resistance to ablation and ablation parts are all positioned at the afterbody of combustion chamber, the ablation member supporting parts of resistance to ablation, make it with engine rear head four jet pipe isolation. The fillet limit of four rounded square of the parts of resistance to ablation is provided with positioning and guiding block, is provided with and the guide path of positioning and guiding Block-matching in combustion chamber so that four cylinders of the parts of resistance to ablation can accurately slip in four jet pipes of rear head. Present configuration is simple, safe and reliable, takies space little, cost-saving, it is achieved engine high thrust ratio.
Description
Technical field
The present invention relates to solid propellant rocket field, relate to a kind of solid engines change propulsive setting device specifically.
Background technology
Change propulsive solid propellant rocket is by changing its equivalent larynx footpath in engine working process, or the change or fast by the combustion of different propelling agents in face is fired by propelling agent, to control the change of propelling agent combustion speed and combustion chamber pressure, thus realize the object changing engine thrust in real time. Throat's diameter of the two thrust solid propellant rocket in conventional single room cannot regulate, and can not realize two stage motor high thrust ratios. In order to realize the requirement of high thrust ratio, it is necessary to throat's diameter is regulated. Throat's regulative mode has side valve type, pin hydrant, but these mode complex structures, it is necessary to space is installed relatively big, and needs servo control mechanism start.
Summary of the invention
It is an object of the invention to solve the problem, it is provided that a kind of solid engines change propulsive setting device.
In order to realize the object of the present invention, the technical solution used in the present invention is:
A kind of solid engines change propulsive setting device, the parts of resistance to ablation and ablation parts are comprised in the combustion chamber of engine, the shape of the parts of resistance to ablation is band four rounded square, four fillets are furnished with four cylinders, cylinder size is mated with the jet pipe of engine rear head, the central authorities of square have circular hole, the shape of ablation parts is cruciform, the central authorities of cruciform have circular hole, the parts of resistance to ablation and ablation parts are all positioned at the afterbody of combustion chamber, the ablation member supporting parts of resistance to ablation, make it with engine rear head four jet pipe isolation.
The fillet limit of four rounded square of the parts of resistance to ablation is provided with positioning and guiding block, is provided with and the guide path of positioning and guiding Block-matching in combustion chamber so that four cylinders of the parts of resistance to ablation can accurately slip in four jet pipes of rear head.
The material of the parts of resistance to ablation is that ablation resistant material is made, and the material of ablation parts is that the cast of solid propellant propulsion agent material is made
The useful effect of the present invention is: structure is simple, safe and reliable, takies space little, cost-saving, it is achieved engine high thrust ratio.
Accompanying drawing explanation
Fig. 1 is the parts of resistance to ablation of the present invention,
Fig. 2 is the left view of Fig. 1,
Fig. 3 is the ablation parts of the present invention,
Fig. 4 is the left view of Fig. 3,
Fig. 5 is the present invention's big larynx footpath status architecture schematic diagram when engine booster works,
Fig. 6 is the left view of Fig. 5,
Fig. 7 is the present invention's little larynx footpath status architecture schematic diagram (ablation parts have burnt rear) when level work continued a journey by engine,
Fig. 8 is the left view of Fig. 7.
Embodiment
Below in conjunction with drawings and Examples, the present invention is further described:
Embodiment: see Fig. 1 to Fig. 8.
A kind of solid engines change propulsive setting device, the parts of resistance to ablation 1 and ablation parts 2 are comprised in the combustion chamber 6 of engine, the shape of the parts of resistance to ablation 1 is band four rounded square, four fillets are furnished with four cylinders 3, cylinder 3 size is mated with the jet pipe 5 of engine rear head, the central authorities of square have circular hole, the shape of ablation parts 2 is cruciform, the central authorities of cruciform have circular hole, the parts of resistance to ablation 1 and ablation parts 2 are all positioned at the afterbody of combustion chamber 6, ablation parts 2 support the parts of resistance to ablation 1, make it with engine rear head four jet pipes 5 and isolate.
The fillet limit of four rounded square of the parts of resistance to ablation 1 is provided with positioning and guiding block 4, is provided with and the guide path that positioning and guiding block 4 mates in combustion chamber 6 so that four cylinders 3 of the parts of resistance to ablation 1 can accurately slip in four jet pipes 5 of rear head.
The parts of resistance to ablation 1 are made for ablation resistant material, and ablation parts 2 are made for the cast of solid propellant propulsion agent material.
Principle of work of the present invention illustrates: adopts ablation resistant material to process the center drilling of the parts of resistance to ablation 1, has enough blast tubes when ensureing engine operation. Adopt solid propellant to pour into ablation parts 2, ablation parts 2 are placed between rear head and the parts of resistance to ablation 1. When engine booster works, ablation parts 2 support the parts of resistance to ablation 1, form relatively wide arc gap therebetween, and 4 cylinders of the parts of resistance to ablation 1 can not block four jet pipes 5 of engine rear head, and as shown in Figure 5, engine is in big larynx footpath state. After thruster work terminates, ablation parts 2 also just burn completely. Now, the parts of resistance to ablation 1 are moved backward by guide path under the effect of engine gas, and four jet pipes 5 around engine rear head blocked by four cylinders, leave the passage of intermediate tube, as shown in Figure 7, become little larynx footpath state, and engine realizes low thrust.
Embodiments of the invention announce be one of preferred embodiment also; but it is not limited thereto; the those of ordinary skill of this area; very easily according to above-described embodiment; understand the spirit of the present invention; and make different amplifications and change, but as long as not departing from the spirit of the present invention, all in protection scope of the present invention.
Claims (3)
1. a solid engines change propulsive setting device, the parts of resistance to ablation and ablation parts are comprised in the combustion chamber of engine, it is characterized in that: the shape of the parts of resistance to ablation is band four rounded square, four fillets are furnished with four cylinders, cylinder size is mated with the jet pipe of engine rear head, the central authorities of square have circular hole, the shape of ablation parts is cruciform, the central authorities of cruciform have circular hole, the parts of resistance to ablation and ablation parts are all positioned at the afterbody of combustion chamber, the ablation member supporting parts of resistance to ablation, make it with engine rear head four jet pipe isolation.
2. a kind of solid engines change propulsive setting device according to claim 1, it is characterized in that: the fillet limit of four rounded square of the parts of resistance to ablation is provided with positioning and guiding block, it is provided with in combustion chamber and the guide path of positioning and guiding Block-matching so that four cylinders of the parts of resistance to ablation can accurately slip in four jet pipes of rear head.
3. a kind of solid engines change propulsive setting device according to claim 2, it is characterised in that: the parts of resistance to ablation are that ablation resistant material is made, and ablation parts are that the cast of solid propellant propulsion agent material is made.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410674927.3A CN104454236B (en) | 2014-11-24 | 2014-11-24 | A kind of solid engines change propulsive setting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410674927.3A CN104454236B (en) | 2014-11-24 | 2014-11-24 | A kind of solid engines change propulsive setting device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104454236A CN104454236A (en) | 2015-03-25 |
| CN104454236B true CN104454236B (en) | 2016-06-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410674927.3A Active CN104454236B (en) | 2014-11-24 | 2014-11-24 | A kind of solid engines change propulsive setting device |
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| CN (1) | CN104454236B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107725217B (en) * | 2017-11-20 | 2019-06-21 | 西安航天动力测控技术研究所 | Solid propellant rocket is without hood gas scragging system |
| CN109900478B (en) * | 2019-03-18 | 2020-09-25 | 西安爱生技术集团公司 | Device and method for testing rocket thrust of small and medium-sized unmanned aerial vehicles |
| CN113653571B (en) * | 2021-08-16 | 2022-11-08 | 北京机械设备研究所 | Solid propellant combustion flow stabilizer and solid engine combustion generator |
| CN116044617A (en) * | 2023-03-01 | 2023-05-02 | 北京星河动力装备科技有限公司 | Nozzle and rocket engine |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5898644A (en) * | 1981-12-07 | 1983-06-11 | Nissan Motor Co Ltd | Rocket motor |
| US7958718B1 (en) * | 1989-07-07 | 2011-06-14 | Alliant Techsystems Inc. | Precision controlled variable thrust solid propellant rocket motor |
| JP3916285B2 (en) * | 1997-03-05 | 2007-05-16 | 旭化成ケミカルズ株式会社 | A perforated plate and a short rocket motor using the perforated plate |
| US7966805B2 (en) * | 2007-05-15 | 2011-06-28 | Raytheon Company | Hydroxyl amine based staged combustion hybrid rocket motor |
| CN201925048U (en) * | 2010-10-09 | 2011-08-10 | 南京理工大学 | Multi-powder-chamber variable thruster |
| CN204253210U (en) * | 2014-11-24 | 2015-04-08 | 江西洪都航空工业集团有限责任公司 | A kind of solid engines change propulsive controlling device |
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| CN104454236A (en) | 2015-03-25 |
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