CN105371710A - Guided-missile high-speed water entering method based on reverse gas injection - Google Patents
Guided-missile high-speed water entering method based on reverse gas injection Download PDFInfo
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- CN105371710A CN105371710A CN201410442787.7A CN201410442787A CN105371710A CN 105371710 A CN105371710 A CN 105371710A CN 201410442787 A CN201410442787 A CN 201410442787A CN 105371710 A CN105371710 A CN 105371710A
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Abstract
The invention provides a guided-missile high-speed water entering method based on reverse gas injection. Protection can be provided for high-speed water entering of a guided missile, and it is avoided that the guided missile is damaged by huge impacting force generated when the high-speed guided missile enters water. A gas generator, a Laval spray tube and a long tail tube are mainly adopted in the method. The gas generator is installed inside the guided missile, and the Laval spray tube is installed at the head of the guided missile and connected with the gas generator through the long tail tube. Before the guided missile enters water, the gas generator starts to work, and a large amount of generated gas enters the Laval spray tube through the long tail tube and is accelerated to be at the supersonic speed through the Laval spray tube to be sprayed out. When entering water, the guided missile is wrapped by the gas sprayed out through the Laval spray tube and is protected. The method is simple, reliability is high, and the protective effect is good.
Description
One technical field
The present invention relates to and a kind ofly at a high speed enter water method based on oppositely jet guided missile.High-speed missile is when entering water, guided missile from air movement to water in, be an extremely complicated physical process, the flowing of this process medium fluid, hydrodynamic force load, guided missile acceleration etc. are all significant change, this may cause the damage of guided missile, comprises local damage, overall fracture and internal mechanism and damages.The present invention is a kind of based on gas generator generation gas, oppositely jet by Laval nozzle acceleration, covers body surface, enters water method to the high speed that guided missile is protected.
Two background technologies
The objects such as anti-submarine guided missle, torpedo, depth charge, submarine mine are the research topics in hydrodynamics with important military significance from passing the water surface process entered water in the air, are also the significant problems that scientific research personnel faces.Any object enters water and all experiences and hit water process, because the density contrast of air and water is very large, enter after water object touches water, originally static water particle, suddenly obtain a limited speed increment, the aqueous medium adjacent with object plane is compressed, the compressional wave that of formation is faint, propagate to all directions with the velocity of sound in water, the hydrodynamic pressure that produces of weak compressional wave is very large concerning entering water object thus.The infringement of this huge impulsive force to guided missile is very huge, the hydrodynamic force profile of guided missile may be made to be destroyed on the one hand, enter after in water, can not run by normal design operating mode; On the other hand, this impulsive force can damage the control system of engine interior, guidance system etc., makes its cisco unity malfunction.Therefore need design one to enter water method, reduce the infringement of this impulsive force to guided missile.
Three summary of the invention
The present invention utilizes gas generator to produce gas, and gas enters Laval nozzle by long-tail pipe and accelerates, and finally sprays from jet pipe with supersonic speed, covers body surface, protects the guided missile entering water.Gas generator is placed on guided missile inside, Laval nozzle is placed on nose of missile, is connected between gas generator with Laval nozzle by long-tail pipe.Guided missile is before entering water, instruction is sent to the igniter in gas generator, ignition device, gas generator is started working, produce gas through long-tail pipe because rubbing action is accelerated, be still subsonic speed when arriving long-tail pipe and Laval nozzle interface, enter Laval nozzle and continue to accelerate to supersonic speed and flow out from nozzle exit, effluent air covers high-speed single hull surface.By this device, can complete and water protection is entered to high-speed missile.
The technical solution adopted in the present invention is: produce gas by gas generator; gas, through the acceleration of long-tail pipe and Laval nozzle, sprays from nozzle exit with ultrasonic speed, covers body on the surface; prevent high-speed missile from directly striking on the water surface, reach the object of protection guided missile.
The invention has the beneficial effects as follows: utilize gas generator as the generating apparatus of gas, reliably, effectively can control the flow, pressure etc. that generate gas; Utilize Laval nozzle to accelerate the gas that gas generator produces, finally reach supersonic speed, can prevent external environment condition from having an impact to gas generator inside, ensure that gas generator normally works according to design conditions; The combustion gas body produced covers body surface, can protect on the one hand entering water process to guided missile, can reduce the resistance that water in operation led by bullet on the other hand.
Four accompanying drawing explanations
Accompanying drawing is that this enters water square law device structural representation at a high speed based on oppositely jet guided missile.
Description of symbols in figure: 1-gas generator, 2-long-tail pipe, 3-Laval nozzle, 4-missile airframe
Five detailed description of the invention
The present invention will be further described by reference to the accompanying drawings:
As shown in the figure, it is inner that gas generator (1) is placed on missile airframe (4), Laval nozzle (3) is placed on missile airframe (4) head, is connected between gas generator (1) with Laval nozzle (3) by long-tail pipe (2).Before guided missile enters water; igniter is received instruction and is lighted a fire; gas generator (1) is started working; gas is through the acceleration of long-tail pipe (2) and Laval nozzle (3); spray from nozzle exit with ultrasonic speed; cover missile airframe (4) surface, thus reach protective effect.
Claims (4)
1. enter a water method at a high speed based on oppositely jet guided missile, it is characterized in that, comprising:
One gas generator, for generation of the gas covering body surface; One Laval nozzle, the gas for being produced by gas generator accelerates to supersonic speed ejection, covers body surface; One long-tail pipe, for connecting gas generator and Laval nozzle, can make gas generator be placed on guided missile inside, ensures that the change of guided missile position of centre of gravity is as far as possible little.
2. at a high speed enter water method according to according to claim 1 based on oppositely jet guided missile, it is characterized in that: gas generator has reliable igniter, when receiving firing command, can safety, reliably light a fire.
3. enter water method according to according to claim 1 at a high speed based on oppositely jet guided missile, it is characterized in that: Laval nozzle outlet has a blanking cover, when gas generator does not work, when preventing guided missile from running, extraneous gas enters wherein, during gas generator work, after setting up pressure, blanking cover can be blown off.
4. at a high speed enter water method according to according to claim 1 based on oppositely jet guided missile, it is characterized in that: long-tail pipe and gas generator and Laval nozzle compact siro spinning technology, the sealing of guarantee whole system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410442787.7A CN105371710A (en) | 2014-09-02 | 2014-09-02 | Guided-missile high-speed water entering method based on reverse gas injection |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410442787.7A CN105371710A (en) | 2014-09-02 | 2014-09-02 | Guided-missile high-speed water entering method based on reverse gas injection |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105371710A true CN105371710A (en) | 2016-03-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410442787.7A Pending CN105371710A (en) | 2014-09-02 | 2014-09-02 | Guided-missile high-speed water entering method based on reverse gas injection |
Country Status (1)
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| CN (1) | CN105371710A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109341443A (en) * | 2018-09-01 | 2019-02-15 | 哈尔滨工程大学 | A kind of reversed jet bubbling crystallzation assists high speed to enter water to lower shock loading mechanism |
| CN109387122A (en) * | 2018-09-01 | 2019-02-26 | 哈尔滨工程大学 | The reversed water spray bubbling crystallzation of one kind assists high speed to enter water attenuating shock loading mechanism |
| CN111829402A (en) * | 2020-06-10 | 2020-10-27 | 中山大学 | Method for assisting high-speed water entry by forward water spraying, air spraying and air ventilating cavitation |
| CN111846160A (en) * | 2020-06-10 | 2020-10-30 | 中山大学 | Water spraying, air jetting and ventilating forward cavitation-assisted high-speed water inlet mechanism |
| CN113932663A (en) * | 2021-10-29 | 2022-01-14 | 大连理工大学 | Reverse air injection load-reducing device |
| US20220065597A1 (en) * | 2018-12-19 | 2022-03-03 | Bae Systems Plc | Munitions and projectiles |
| CN115031588A (en) * | 2022-06-17 | 2022-09-09 | 中山大学 | Supercavitation navigation body capable of jetting forward |
-
2014
- 2014-09-02 CN CN201410442787.7A patent/CN105371710A/en active Pending
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109341443A (en) * | 2018-09-01 | 2019-02-15 | 哈尔滨工程大学 | A kind of reversed jet bubbling crystallzation assists high speed to enter water to lower shock loading mechanism |
| CN109387122A (en) * | 2018-09-01 | 2019-02-26 | 哈尔滨工程大学 | The reversed water spray bubbling crystallzation of one kind assists high speed to enter water attenuating shock loading mechanism |
| US20220065597A1 (en) * | 2018-12-19 | 2022-03-03 | Bae Systems Plc | Munitions and projectiles |
| CN111829402A (en) * | 2020-06-10 | 2020-10-27 | 中山大学 | Method for assisting high-speed water entry by forward water spraying, air spraying and air ventilating cavitation |
| CN111846160A (en) * | 2020-06-10 | 2020-10-30 | 中山大学 | Water spraying, air jetting and ventilating forward cavitation-assisted high-speed water inlet mechanism |
| CN113932663A (en) * | 2021-10-29 | 2022-01-14 | 大连理工大学 | Reverse air injection load-reducing device |
| CN113932663B (en) * | 2021-10-29 | 2022-12-09 | 大连理工大学 | Reverse air injection load-reducing device |
| CN115031588A (en) * | 2022-06-17 | 2022-09-09 | 中山大学 | Supercavitation navigation body capable of jetting forward |
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| PB01 | Publication | ||
| DD01 | Delivery of document by public notice |
Addressee: Liu Jianing Document name: Notification of Publication of the Application for Invention |
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| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160302 |