CN110146295B - Fragment impact generator of solid rocket engine - Google Patents
Fragment impact generator of solid rocket engine Download PDFInfo
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- CN110146295B CN110146295B CN201910370270.4A CN201910370270A CN110146295B CN 110146295 B CN110146295 B CN 110146295B CN 201910370270 A CN201910370270 A CN 201910370270A CN 110146295 B CN110146295 B CN 110146295B
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- rocket engine
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
Abstract
The invention relates to a fragment impact generator of a solid rocket engine, which comprises an annular base, wherein a fragment is fixed at the bottom end of the annular base, a driving explosive which drives the fragment to fly through detonation is fixed at the top end of the annular base, the fragment is in a spherical crown shape, and a concave part matched with the fragment is arranged at the bottom end of the driving explosive; the top end of the driving powder is fixed with booster powder, the top end of the booster powder is fixed with a positioning ring, and the positioning ring is internally fixed with a detonator. The fragment speed generated by the invention is 2300m/s +/-200 m/s, the effective impact fragment mass is 17.0g +/-2.0 g, and the generator has a simple structure and is convenient to operate, thereby meeting the requirements of American military standard and European military standard.
Description
Technical Field
The invention relates to a fragment impact generator of a solid rocket engine, which is applied to fragment impact evaluation of the solid rocket engine and is a key part for evaluating and evaluating the insensitive characteristic and the low vulnerability of the solid rocket engine.
Background
In modern wars, various weapons are equipped on combat platforms such as warplanes, naval vessels, aircraft carriers and the like, in order to improve the combat capability, the energy and power of weapon models are higher and higher, and the deterioration of safety performance follows, particularly, combustion or explosion accidents caused by external stimulation such as accidental falling, fire and the like in the processes of transportation, hoisting, combat and the like not only cause damage to own weapons and equipment, but also cause a large amount of casualties and huge economic loss. The above unexpected safety accidents directly cause damage to weaponry and platforms such as aircraft carriers, warships, fighters and ammunition depots, and the fighting capacity of the own party is seriously weakened. To this end, specialized solid rocket engines of low vulnerability and insensitivity characteristics methods and apparatus have been established in the united states and european countries. Among them, the fragment impact test is one of the key tests. However, because the related research on the low vulnerability and the insensitive characteristic of the domestic solid rocket engine is started later, the research on the fragment impact of the solid rocket engine is just started, and the research on the generator is blank.
Along with the continuous enhancement of the national defense strength of China and the increase of unstable factors of the surrounding environment, a test device and a method for evaluating the low vulnerability and the insensitive characteristic of a solid rocket engine are urgently needed to be established by design units and military. Unfortunately, so far, no test device for solid rocket engines exists in China.
Disclosure of Invention
The invention aims to provide a generator suitable for fragment impact of a solid rocket engine, and results of repeated calculation and multiple tests prove that the generator is stable to use, simple to operate and consistent in test results with foreign results, and meets the requirements of American military standards and European standards.
In order to achieve the purpose, the invention provides the following technical scheme:
a fragment impact generator of a solid rocket engine comprises an annular base, wherein a fragment is fixed at the bottom end of the annular base, a driving powder for driving the fragment to fly through detonation is fixed at the top end of the annular base, the fragment is in a spherical crown shape, and a concave part matched with the fragment is arranged at the bottom end of the driving powder; the top end of the driving powder is fixed with booster powder, the top end of the booster powder is fixed with a positioning ring, and the positioning ring is internally fixed with a detonator.
Preferably, the propellant is formed by pressing explosive with detonation velocity not lower than 7000 m/s.
Preferably, the propellant powder is a cylinder with the diameter of 37.0mm +/-0.1 mm, the height of 60.0mm +/-0.1 mm and the radius of 32.50mm +/-0.05 mm of the concave part.
Preferably, the booster explosive is formed by pressing poly black-14.
Preferably, the booster explosive is a cylinder with the diameter of 20.0mm +/-0.1 mm and the height of 10.0mm +/-0.1 mm.
Preferably, the diameter of the fragments is 38.0(0, -0.01) mm, the thickness is 2mm, and the radius of the sphere is 32.50mm + -0.05 mm.
Preferably, the positioning ring is machined from aluminum alloy.
Preferably, the positioning ring has an inner diameter of 8.0mm, an outer diameter of 12.0mm and a height of 10.0 mm.
Preferably, the annular base is machined from 45# steel.
Preferably, the annular base has an inner diameter of 38.0(0.03, 0) mm, an outer diameter of 46.0mm and a height of 40.0 mm.
Compared with the prior art, the invention has the beneficial effects that:
1. the fragment impact generator of the solid rocket engine can generate fragments with the mass of 17.0g +/-2.0 g.
2. The speed of the fragment generated by the fragment impact generator of the solid rocket engine is within 2300m/s +/-200 m/s.
3. The driving explosive for the solid rocket engine fragment impact generator is composed of explosives with the detonation velocity of more than 7000m/s, and the selection range is wide.
4. The fragment impact generator of the solid rocket engine is a one-time-use device and has the characteristics of convenience in use, low cost and the like.
5. The fragment of the solid rocket engine fragment impact generator can meet the standards of the American and European fragment impact tests.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic cross-sectional view of the present invention;
FIG. 3 is an end view of the annular base;
FIG. 4 is a schematic top view of the propellant charge;
FIG. 5 is a top schematic view of a booster;
FIG. 6 is an end view of the retaining ring;
fig. 7 is a top schematic view of a fragment.
Reference numerals: 1-detonator, 2-positioning ring, 3-booster, 4-driving powder, 5-annular base and 6-fragment.
Detailed Description
The invention is further described with reference to the following drawings and specific embodiments.
Example 1
Referring to fig. 1 and 2, the solid rocket engine fragment impact generator comprises an annular base 5, fragments 6 are fixed at the bottom end of the annular base, a driving explosive 4 for driving the fragments to fly through detonation is fixed at the top end of the annular base, the driving explosive provides energy for driving the fragments after explosion, the fragments are spherical crown-shaped, and concave portions matched with the fragments are arranged at the bottom end of the driving explosive; the top end of the driving powder is fixed with an explosion transfer powder 3, the driving powder is detonated after the explosion transfer powder is detonated, the top end of the explosion transfer powder is fixed with a positioning ring 2, a detonator 1 is fixed in the positioning ring, and the detonator is used for detonating the explosion transfer powder. The fragment is a core component of a fragment impact test, is driven by explosive driving of a driving agent to fly out at a certain speed, impacts a solid rocket engine and examines the safety of the solid rocket engine.
Referring to fig. 1, 2 and 4, in the present embodiment, the propellant is formed by compression molding an explosive having a detonation velocity of not less than 7000 m/s. The driving powder is a cylinder with the diameter of 37.0mm plus or minus 0.1mm, the height of 60.0mm plus or minus 0.1mm and the radius of 32.50mm plus or minus 0.05mm of a concave part. And (4) pressing and molding by adopting a special mold, and standing for 24 hours for later use.
Referring to fig. 1 and 5, in the present embodiment, the booster is formed by pressing poly black-14. The booster explosive is a cylinder with the diameter of 20.0mm plus or minus 0.1mm and the height of 10.0mm plus or minus 0.1 mm. And (4) pressing and molding by adopting a special mold, and standing for 24 hours for later use.
Referring to fig. 1, 2 and 7, in this example, 45# steel was used to process the fragments with a diameter of 38.0(0, -0.01) mm, a thickness of 2mm and a sphere radius of 32.50mm ± 0.05 mm.
The broken pieces are designed into a spherical crown shape, so that the energy gathering effect can be achieved, and the impact precision of the broken pieces can be ensured. The flying speed of the fragments is mainly determined by the mass of the driving agent and the mass of the fragments, and the flying speed of the fragments can be adjusted by changing the mass of the driving agent and the mass of the fragments so as to meet different test requirements.
Referring to fig. 1 and 6, in the present embodiment, the positioning ring is machined from an aluminum alloy. The inner diameter of the positioning ring is 8.0mm, the outer diameter of the positioning ring is 12.0mm, and the height of the positioning ring is 10.0 mm.
Referring to fig. 1 and 3, in the present embodiment, the annular base is machined from 45# steel. The annular base has an inner diameter of 38.0(0.03, 0) mm, an outer diameter of 46.0mm and a height of 40.0 mm. And (5) deburring for later use. The annular base is used for fixing the driving powder and the fragments. The annular base has a gain effect on the flight speed of the fragments.
In the present embodiment, the 8# electric detonator is used as the detonator.
The solid rocket engine fragment impact generator is assembled as follows: firstly, mounting the broken piece 6 at the bottom end of the annular base 5, then slowly loading the pressed black-2-gathering driving powder 4 from the top end of the annular base 5 to ensure that the concave part of the black-2-gathering driving powder is completely contacted with the spherical crown of the broken piece 6, then fixing the pressed black-14-gathering booster 3 at the top end of the driving powder 4, fixing the positioning ring 2 at the top end of the booster 3, inserting the detonator 1 into the positioning ring for fixing, wherein all the components are concentric in the assembly process, fixing the components by using AB glue or similar quick-drying glue or adhesive tape and the like, and using the components after the quick-drying glue or adhesive tape is solidified.
The speed of the splits was measured by electrical measurement and the results are shown in table 1.
TABLE 1 fragmentation generator quality and speed test results
| Item | Mass, g | Speed, m/s | Remarks for note |
| Results | 18.1 | 2353 |
The content of the embodiment is only a part of the embodiment of the present invention, not all embodiments, but the protection scope of the present invention is not limited thereto, and any other embodiments obtained by a person of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.
Claims (6)
1. A fragment impact generator of a solid rocket engine is characterized in that: the explosive-free blasting device comprises an annular base (5), wherein a fragment (6) is fixed at the bottom end of the annular base, a driving explosive (4) which drives the fragment to fly through detonation is fixed at the top end of the annular base, the fragment is in a spherical crown shape, and a concave part matched with the fragment is arranged at the bottom end of the driving explosive; the top end of the driving powder is fixed with booster powder (3), the top end of the booster powder is fixed with a positioning ring (2), and a detonator (1) is fixed in the positioning ring; the driving explosive (4) is formed by pressing explosive with the detonation velocity not lower than 7000m/s into a cylinder with the diameter of 37.0mm +/-0.1 mm, the height of 60.0mm +/-0.1 mm and the radius of 32.50mm +/-0.05 mm; the booster explosive (3) is formed by pressing poly black-14 into a cylinder with the diameter of 20.0mm +/-0.1 mm and the height of 10.0mm +/-0.1 mm.
2. A solid-rocket engine fragment impact generator as defined in claim 1, wherein: the diameter of the fragment (6) is 38.0(0, -0.01) mm, the thickness is 2mm, and the radius of the sphere is 32.50mm +/-0.05 mm.
3. A solid-rocket engine fragment impact generator as defined in claim 1, wherein: the positioning ring (2) is processed by aluminum alloy.
4. A solid-rocket engine fragment impact generator as defined in claim 1, wherein: the inner diameter of the positioning ring (2) is 8.0mm, the outer diameter is 12.0mm, and the height is 10.0 mm.
5. A solid-rocket engine fragment impact generator as defined in claim 1, wherein: the annular base (5) is machined from 45# steel.
6. A solid-rocket engine fragment impact generator as defined in claim 1, wherein: the inner diameter of the annular base (5) is 38.0(0.03, 0) mm, the outer diameter is 46.0mm, and the height is 40.0 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910370270.4A CN110146295B (en) | 2019-05-06 | 2019-05-06 | Fragment impact generator of solid rocket engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910370270.4A CN110146295B (en) | 2019-05-06 | 2019-05-06 | Fragment impact generator of solid rocket engine |
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| CN110146295A CN110146295A (en) | 2019-08-20 |
| CN110146295B true CN110146295B (en) | 2021-03-23 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN203501904U (en) * | 2013-05-20 | 2014-03-26 | 湖北航天化学技术研究所 | Fragment launcher |
| CN108061489A (en) * | 2017-11-27 | 2018-05-22 | 北京理工大学 | One kind is used for standard fragmentation bump test explosive detonation drive-type emitter |
| CN108088335A (en) * | 2017-11-27 | 2018-05-29 | 北京理工大学 | A kind of design method for high speed fragments bump test series transmitting device |
| JP2018159492A (en) * | 2017-03-22 | 2018-10-11 | 日油株式会社 | Flying body ejecting device and method for fragment impact test using the same |
| CN109540965A (en) * | 2018-11-15 | 2019-03-29 | 中国工程物理研究院化工材料研究所 | Explosive fragmentation driving capability evaluating apparatus and method |
-
2019
- 2019-05-06 CN CN201910370270.4A patent/CN110146295B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203501904U (en) * | 2013-05-20 | 2014-03-26 | 湖北航天化学技术研究所 | Fragment launcher |
| JP2018159492A (en) * | 2017-03-22 | 2018-10-11 | 日油株式会社 | Flying body ejecting device and method for fragment impact test using the same |
| CN108061489A (en) * | 2017-11-27 | 2018-05-22 | 北京理工大学 | One kind is used for standard fragmentation bump test explosive detonation drive-type emitter |
| CN108088335A (en) * | 2017-11-27 | 2018-05-29 | 北京理工大学 | A kind of design method for high speed fragments bump test series transmitting device |
| CN109540965A (en) * | 2018-11-15 | 2019-03-29 | 中国工程物理研究院化工材料研究所 | Explosive fragmentation driving capability evaluating apparatus and method |
Non-Patent Citations (2)
| Title |
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| 《固体火箭发动机破片冲击起爆阈值计算》;杨琨 等;《固体火箭技术》;20181031;第41卷(第5期);第566-573页 * |
| 《破片对固体推进剂装药安全性影响研究进展》;宋柳芳 等;《飞航导弹》;20190131(第1期);第92-96页 * |
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