CN113482798B - Free-packed grain pressing structure of solid rocket engine and use method - Google Patents
Free-packed grain pressing structure of solid rocket engine and use method Download PDFInfo
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- CN113482798B CN113482798B CN202110690244.7A CN202110690244A CN113482798B CN 113482798 B CN113482798 B CN 113482798B CN 202110690244 A CN202110690244 A CN 202110690244A CN 113482798 B CN113482798 B CN 113482798B
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- pipe
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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
- F02K9/24—Charging rocket engines with solid propellants; Methods or apparatus specially adapted for working solid propellant charges
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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
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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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Medicines That Contain Protein Lipid Enzymes And Other Medicines (AREA)
Abstract
The invention provides a free-loading explosive column pressing structure of a solid rocket engine and a using method thereof, which solve the problem of inner trajectory abnormity caused by falling off of a spring in the working process of the engine in the prior art. The utility model provides a solid rocket engine freely loads powder column and presses medicine structure, includes the combustion chamber, from left to right is equipped with blanking cover, pipe, powder column clamp ring and freely loads the powder column in proper order in the combustion chamber, is equipped with the pressure medicine spring in the pipe, pipe one end and blanking cover threaded connection, the other end and powder column clamp ring sliding connection. By using the freely-filled grain pressing structure of the solid rocket engine, the pressing spring can tightly press the freely-filled grain through the grain pressing ring; and the area of the powder pressing surface of the powder column pressing ring is large enough, so that the freely filled powder column cannot be damaged. Because the pressure charge spring is fixed in the pressure charge spring guide pipe, the pressure charge spring can not be taken out of the engine by gas in the working process of the engine to cause the internal ballistic trajectory abnormality of the engine.
Description
Technical Field
The invention relates to the technical field of solid rocket engine explosive loading, in particular to a free-loading explosive column pressing structure of a solid rocket engine and a using method.
Background
In a solid rocket engine with freely filled grains, the grains are in a free state in the engine. Therefore, the explosive column must be fixed at the front end and the rear end of the explosive column, the length change of the explosive column at high and low temperatures is considered, a rigid explosive blocking structure is generally fixed at the rear end, and an elastic supporting structure is mostly adopted at the front end to adapt to the thermal expansion stress of the explosive column at high and low temperatures. The elastic element of the front end elastic supporting structure mostly adopts a spring, but the spring is easy to break and fall off in the working process of the engine, and the falling off process can cause the abnormality of the ballistic curve in the engine and cause the eccentricity of thrust.
Disclosure of Invention
The invention provides a free charge and explosive pressing structure of a solid rocket engine and a using method thereof, which solve the problem of internal ballistic abnormality caused by falling off of a spring in the working process of the engine in the prior art.
The technical scheme of the invention is realized as follows:
the utility model provides a solid rocket engine freely loads grain and presses medicine structure, includes the combustion chamber, from left to right is equipped with blanking cover, pipe, grain clamp collar in proper order and freely loads the grain in the combustion chamber, is equipped with the pressure medicine spring in the pipe, pipe one end and blanking cover threaded connection, the other end and grain clamp collar sliding connection.
Further, the right-hand member of pipe is equipped with the external screw thread, and the left end of powder column clamp ring is equipped with the internal thread with external screw thread fit, and the inner wall of powder column clamp ring on internal thread right side is the smooth surface.
Furthermore, the side wall of the guide pipe is provided with a plurality of first vent holes, the first vent holes are communicated with the inner cavity of the blocking cover, the right end face and the side wall of the explosive column pressing ring are provided with a plurality of second vent holes, and the outer surface of the explosive column pressing ring is provided with a powder pressing surface used for pressing freely filled explosive columns.
Further, the thickness of the medicine pressing surface is 2-4 mm, and a plurality of through holes are formed in the medicine pressing surface.
Furthermore, a cushion pad is arranged between the grain pressing ring and the freely filled grain.
Further, the plug cover is in threaded connection with the combustion chamber.
Further, the material of the pressing spring is 65 Mn.
A use method of a free-filling grain explosive-pressing structure of a solid rocket engine comprises the following steps:
s1) placing the pressing spring in the catheter, pressing the pressing spring by using a medicine column pressing ring, and installing the medicine column pressing ring on the catheter to enable the medicine column pressing ring to freely move outside the catheter;
s2) screwing the guide tube onto the central thread of the cap, and finally fixing the cap to the front end of the combustion chamber of the engine which is filled with the freely filled charge.
Further, on the external screw thread with the internal thread screw in pipe of medicine post clamping ring in step 1, continue rotatory medicine post clamping ring and make the internal thread release from the external screw thread, make the smooth surface and the external screw thread department of medicine post clamping ring corresponding, medicine post clamping ring cover can freely remove outside the pipe.
The beneficial effect that this technical scheme can produce: by using the free-filling grain pressing structure of the solid rocket engine, the pressing spring can tightly press the free-filling grain through the grain pressing ring; and the area of the powder pressing surface of the powder column pressing ring is large enough, so that the freely filled powder column is not damaged. Because the charge pressing spring is fixed in the guide pipe, the charge pressing spring is not carried out of the engine by gas in the working process of the engine to cause ballistic abnormality in the engine. The invention has simple structure, the spring is not easy to fall off in the working process of the engine, and the assembly and the disassembly are convenient.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic plan view of the present invention;
FIG. 2 is a perspective view of a catheter;
fig. 3 is a schematic perspective view of a grain clamp ring.
In the figure: pipe 1, pressure medicine spring 2, powder column clamping ring 3, blanking cover 4, combustion chamber 5, blotter 6 freely loads powder column 7, presses the powder face 8.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without inventive effort based on the embodiments of the present invention, are within the scope of the present invention.
The left and right in the present invention are relative to the position shown in fig. 1.
Example 1
As shown in fig. 1-3, this embodiment provides a solid rocket engine freely loads grain and presses medicine structure, including combustion chamber 5, be equipped with blanking cover 4, pipe 1, grain clamp ring 3 and freely load grain 7 from left to right in proper order in the combustion chamber 5, be equipped with in the pipe 1 and press medicine spring 2, pipe 1 one end and 4 threaded connection of blanking cover, the other end and 3 sliding connection of grain clamp ring.
The use process of the invention is as follows:
the drug pressing spring 2 is placed in the catheter 1, the drug column pressing ring 3 is used for pressing the drug pressing spring 2, and the drug column pressing ring 3 is screwed into the catheter 1 until the drug column pressing ring 3 is sleeved outside the catheter 1 and moves freely. The catheter 1 is then screwed onto the central thread of the cap 4. Finally, the plug cover 4 is fixed with the front end of the engine combustion chamber 5 which is filled with the freely filled grain 7.
Example 2
The right-hand member of pipe 1 is equipped with the external screw thread, and the left end of powder column clamp ring 3 is equipped with the internal thread with external screw thread fit, and the inner wall of powder column clamp ring 3 on internal thread right side is the smooth surface.
After the medicine column pressing ring 3 is screwed into the external thread of the guide pipe 1, the medicine column pressing ring can be sleeved on the guide pipe 1 to move freely, and meanwhile, the medicine column pressing ring cannot fall off due to the resisting effect of the thread. This has also guaranteed that the powder column clamp ring 3 is along with pressing the deformation of medicine spring 2 and powder column and freely removes and have the requirement of certain pretightning force.
Other structures of this embodiment are the same as those of embodiment 1.
Example 3
The lateral wall of pipe 1 is equipped with a plurality of first air vents, and first air vent communicates with each other with the inner chamber of blanking cover 4, and the right-hand member face and the lateral wall of powder column clamp ring 3 all are equipped with a plurality of second air vents, and 3 surfaces of powder column clamp ring are equipped with the face 8 of pressing medicine that is used for compressing tightly freely filling powder column 7 specially. The first vent hole is communicated with the second vent hole, and the second vent hole is communicated with the freely filled grain 7.
The first vent hole and the second vent hole are provided mainly for facilitating the gas circulation.
Other structures of this embodiment are the same as those of embodiment 1.
Example 4
The thickness of the powder pressing surface 8 is 2-4 mm, and a plurality of through holes are formed in the powder pressing surface 8.
The thickness of the medicine pressing surface 8 is 2-4 mm, the medicine pressing surface is too thin, the strength is not enough, ablation resistance cannot be realized, and the quality is increased when the medicine pressing surface is too thick. The function of the multiple through holes on the powder pressing surface 8 is to make the gas flow smoothly.
Other structures of this embodiment are the same as those of embodiment 3.
Example 5
And a cushion pad 6 is arranged between the grain pressing ring 3 and the freely-filled grain 7. And the cushion pad 6 is fixed on the powder pressing surface 8 of the powder column pressing ring 3 by glue.
The buffer pad 6 is used for buffering the impact force between the grain pressing ring 3 and the freely-filled grain 7, and the material is industrial felt.
Other structures of this embodiment are the same as those of embodiment 1.
Example 6
The plug cover 4 is in threaded connection with the combustion chamber 5. The blocking cover 4 is fixedly connected with the combustion chamber 5 and plays a role in sealing the gas in the combustion chamber 5.
Other structures of this embodiment are the same as those of embodiment 1.
Example 7
The material of the pressing spring 2 is 65 Mn.
The 65Mn material has good elasticity and ablation resistance. The specification of the drug pressing spring 2 is designed according to the size of specific drug pressing force, such as the spring pitch diameter, the wire diameter, the length and the like.
Other structures of this embodiment are the same as those of embodiment 1.
A use method of a free-filling grain explosive-pressing structure of a solid rocket engine comprises the following steps:
s1) placing the drug pressing spring 2 in the catheter 1, pressing the drug pressing spring 2 by the drug column pressing ring 3, and installing the drug column pressing ring 3 on the catheter 1 to enable the drug column pressing ring 3 to move freely outside the catheter 1;
s2) screwing the guide tube 1 onto the central thread of the cap 4, and finally fixing the cap 4 to the front end of the engine combustion chamber 5 in which the freely packed grains 7 have been loaded.
Further, on the external screw thread with the internal thread screw in pipe 1 of medicine post clamping ring 3 in step 1, continue rotatory medicine post clamping ring 3 and make the internal thread release from the external screw thread, make the smooth surface of medicine post clamping ring 3 corresponding with external screw thread department, 3 covers of medicine post clamping ring can freely remove outside pipe 1.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (6)
1. The utility model provides a solid rocket engine freely loads grain and presses medicine structure which characterized in that: including combustion chamber (5), from left to right be equipped with blanking cover (4) in proper order in combustion chamber (5), pipe (1), powder column clamp ring (3) and freely load powder column (7), be equipped with in pipe (1) and press powder spring (2), pipe (1) one end and blanking cover (4) threaded connection, the other end and powder column clamp ring (3) sliding connection, the right-hand member of pipe (1) is equipped with the external screw thread, the left end of powder column clamp ring (3) be equipped with external screw thread fit's internal thread, the inner wall of powder column clamp ring (3) on internal thread right side is the smooth surface.
2. The free-loading charge pressing structure of a solid rocket engine according to claim 1, wherein: and a buffer pad (6) is arranged between the grain pressing ring (3) and the freely-filled grain (7).
3. The free-loading charge pressing structure of a solid rocket engine according to claim 1, wherein: the blocking cover (4) is in threaded connection with the combustion chamber (5).
4. The free-loading charge pressing structure of a solid rocket engine according to claim 1, wherein: the material of the pressing spring (2) is 65 Mn.
5. A use method of the free-loading grain pressing structure of the solid rocket engine as claimed in any one of claims 1 to 4, wherein:
s1), placing the drug pressing spring (2) in the catheter (1), pressing the drug pressing spring (2) by using the drug column pressing ring (3), installing the drug column pressing ring (3) on the catheter (1), and enabling the drug column pressing ring (3) to freely move outside the catheter (1);
s2) the guide pipe (1) is screwed into the central thread of the blocking cover (4), and finally the blocking cover (4) is fixed with the front end of the engine combustion chamber (5) which is filled with the freely-filled grain (7).
6. Use according to claim 5, characterized in that: in the step 1, the internal thread of the explosive column pressing ring (3) is screwed into the external thread of the guide pipe (1), the explosive column pressing ring (3) is continuously rotated to enable the internal thread to be disengaged from the external thread, the smooth surface of the explosive column pressing ring (3) corresponds to the external thread, and the explosive column pressing ring (3) is sleeved outside the guide pipe (1) and can freely move.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110690244.7A CN113482798B (en) | 2021-06-22 | 2021-06-22 | Free-packed grain pressing structure of solid rocket engine and use method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110690244.7A CN113482798B (en) | 2021-06-22 | 2021-06-22 | Free-packed grain pressing structure of solid rocket engine and use method |
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| Publication Number | Publication Date |
|---|---|
| CN113482798A CN113482798A (en) | 2021-10-08 |
| CN113482798B true CN113482798B (en) | 2022-07-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110690244.7A Active CN113482798B (en) | 2021-06-22 | 2021-06-22 | Free-packed grain pressing structure of solid rocket engine and use method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115163335B (en) * | 2022-07-01 | 2023-01-13 | 星河动力(北京)空间科技有限公司 | Combustion chamber grain for test and simulated engine combustion chamber |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1267718A (en) * | 1968-11-28 | 1972-03-22 | Messerschmitt Boelkow Blohm | A rocket propulsion unit |
| US5817968A (en) * | 1987-08-03 | 1998-10-06 | The United States Of America As Represented By The Secretary Of The Air Force | Gas generation with high pressure sensitivity exponent propellant |
| CN106121862A (en) * | 2016-08-11 | 2016-11-16 | 西北工业大学 | A kind of solid rocket motor grain fixing device |
| CN107269424A (en) * | 2017-07-25 | 2017-10-20 | 南京理工大学 | A kind of solid propellant rocket regnition structure |
| CN107642435A (en) * | 2016-12-16 | 2018-01-30 | 湖北航天化学技术研究所 | A kind of adjustable thrust, it can repeatedly start automatically controlled solid engine |
| CN110714855A (en) * | 2018-07-12 | 2020-01-21 | 南京理工大学 | Electric control power device with real-time controllable thrust and capable of repeatedly igniting and extinguishing |
-
2021
- 2021-06-22 CN CN202110690244.7A patent/CN113482798B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1267718A (en) * | 1968-11-28 | 1972-03-22 | Messerschmitt Boelkow Blohm | A rocket propulsion unit |
| US5817968A (en) * | 1987-08-03 | 1998-10-06 | The United States Of America As Represented By The Secretary Of The Air Force | Gas generation with high pressure sensitivity exponent propellant |
| CN106121862A (en) * | 2016-08-11 | 2016-11-16 | 西北工业大学 | A kind of solid rocket motor grain fixing device |
| CN107642435A (en) * | 2016-12-16 | 2018-01-30 | 湖北航天化学技术研究所 | A kind of adjustable thrust, it can repeatedly start automatically controlled solid engine |
| CN107269424A (en) * | 2017-07-25 | 2017-10-20 | 南京理工大学 | A kind of solid propellant rocket regnition structure |
| CN110714855A (en) * | 2018-07-12 | 2020-01-21 | 南京理工大学 | Electric control power device with real-time controllable thrust and capable of repeatedly igniting and extinguishing |
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| CN113482798A (en) | 2021-10-08 |
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