CN109282711A - The fixed temperature of missile armament melts pressure release slow-released system - Google Patents
The fixed temperature of missile armament melts pressure release slow-released system Download PDFInfo
- Publication number
- CN109282711A CN109282711A CN201811136558.7A CN201811136558A CN109282711A CN 109282711 A CN109282711 A CN 109282711A CN 201811136558 A CN201811136558 A CN 201811136558A CN 109282711 A CN109282711 A CN 109282711A
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- China
- Prior art keywords
- pressure release
- end cap
- bearing bracket
- rear end
- shell
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/34—Protection against overheating or radiation, e.g. heat shields; Additional cooling arrangements
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Radar Systems Or Details Thereof (AREA)
Abstract
The invention discloses a kind of fixed temperature of missile armament to melt pressure release slow-released system, the system is made of shell, drive end bearing bracket, pressure release module, fill, rear end cap, 4 pressure release modules are respectively provided on drive end bearing bracket and rear end cap, drive end bearing bracket and rear end cap are assemblied in the both ends of shell by threaded coaxial.The present invention can be when guided missile meets with the unexpected thermostimulation of slow cook-off, during missile armament temperature is raised, the fusible metal inlayed in the pressure release module of forward and backward end cap is mounted on gradually to soften, finally fusing forms pressure release passage, it ensure that explosive when the temperature threshold locally lighted a fire not up to occurs, liquid explosives and explosive after fusing can effectively be discharged thermally decompose the gas released, inhibit the increase of body internal pressure, making the reaction rate of explosive will not sharply increase, the slow roasting response grade for reducing warhead, promotes the slow roasting safety of ammunition.
Description
Technical field
The invention belongs to warhead security technique field, it is related to a kind of pressure relief device of warhead under thermostimulation, it is special
It is not related to a kind of safety relief slow-released system for missile armament under slow cook-off stimulation.
Background technique
Ammunition manufacture, storage, transport, military service life cycle management in all suffer from it is various it is unexpected threaten, two
The bitter lesson that accident is repeatedly revealed after prewar promotes the western countries headed by the U.S. to take the lead in proposing insensitive thinking, together
When start to work out development policies and appraisal standards, and insensitive munitions are defined as reliably to meet performance, the war of defined
The ammunition that standby state and operating technology require has an accident, and (slow cook-off, fast cook off test, projectile impact, fragmentation hit, are poly- for stimulation
Energy charge jet is hit, hot fragment and induced detonation react) when, it can be by the probability accidentally ignited and then to weapon platform, logistics system
The harm seriousness of system and personnel are reduced to minimum.NATO has worked out insensitive munitions acceptance criteria in 1984 to 1986 years；Beauty
Naval of state 2003 by Ministry of National Defence's commission is disclosed insensitive munitions army mark MIL-STD-2105C, and " risk of non-nuclear round is commented
Estimate test "；NATO has also worked out the standard STANAG 4439 of development, assessment and test insensitive munitions at the same time.It bakes at a slow speed
Combustion is the environment to heat up at a slow speed simulating ammunition and undergoing when meeting with fire accident, meets with probability in the use process of ammunition
Greatly, the extent of injury is high, has become the project that must examine of insensitive munitions examination at present, and the insensitivity research of ammunition is not only positive
Study various low rapid wear main charges, it is often more important that for the property of main charge, some let out is designed in warhead system structure
Release structures are pressed, its insensitive performance is improved.
In the Chinese invention patent " missile armament safety relief protects structure " that grant number is ZL201418005074.5
In, disclose a kind of missile armament safety relief protection structure, as shown in Figure 1, it is main include protection plug, reactive explosive and
Heat-proof device；Its principle is that warhead is in hot environment, when temperature reaches the threshold of reaction of reaction material, reaction material
Start vigorous reaction, and issue a large amount of heat in moment, so that composite material protection plug softening is fallen off from warhead drive end bearing bracket, release
Closed environment locating for warhead main charge improves the safety that warhead uses, but its existing main problem is: (1) should
Protection structure is by the aperture on warhead drive end bearing bracket, and insertion is equipped with the protection structure of reaction material, due to complex protection plug
Intensity it is not high, reduce the structural strength of warhead, in addition protect structure be embedded in main charge, occupy the body of main charge
Product, destroys the charge constitution of warhead, and then affect warhead injures performance.(2) the protection structure is to pass through environment
When temperature is increased to the threshold of reaction of reaction material, vigorous reaction occurs for reaction material, releases a large amount of heat, protects composite material
It protects plug softening, fall off, but since reaction material is also a kind of substance containing energy, and be in close contact with main charge, reactive material
The heat released when reacting more heats while passing to protection plug have been passed to main charge, increase and have been heated
The risk of vigorous reaction occurs for the main charge of stimulation.
Summary of the invention
In order to overcome the shortcomings of that above-mentioned pressure release protecting structure and defect, the present invention provide a kind of fixed temperature melting of missile armament
Pressure release slow-released system, the pressure relief can not weaken warhead integral strength and occupy the premise of warhead charge volume
Under, in the thermostimulation of ammunition experience slow cook-off, reliable, soft formation pressure release passage reduces the slow roasting reaction of warhead
Severe degree, structure, principle are simple and reliable, can be applied to the relevant design of insensitive warhead.
Solution above-mentioned technical problem, technical solution of the invention: it is slow that a kind of fixed temperature of missile armament melts pressure release
Release system, including shell, drive end bearing bracket, pressure release module, fill, rear end cap；It is characterized in that, the shell is first-class wall thickness circle
Cylindrical sleeve has internal screw thread at the both ends of shell；The drive end bearing bracket and rear end cap are a cylindrical cover, drive end bearing bracket and rear end
Lid size is identical, is respectively front/rear end cap radius half, and the circumference coaxial with forward and backward end cap in its end face inside radius
On be evenly arranged 4 step through-holes, external screw thread on the cylinder of drive end bearing bracket and rear end cap, respectively with the internal screw thread at shell both ends end
It is coupled, when installation ensures the big one end of step bore dia inside housings；The pressure release module is a circular cylindrical projection stage body,
Grid framework is constituted by high strength titanium alloy and fusible metal that frame inner cavity is inlayed forms, pressure release module is installed tightly to front end
In the stepped hole of lid and rear end cap；The fill is to be loaded on enclosure interior by the molding cylindrical grain of founding,
Between drive end bearing bracket and rear end cap；Shell, fill, drive end bearing bracket, rear end cap are using coaxial assembly.
The fixed temperature of missile armament of the invention melts pressure release slow-released system, compared with prior art, bring technical effect
It is embodied in the following aspects:
1) the pressure release module being made of intensity frame is mounted on end cap, avoids the intensity, anti-for weakening warhead itself
Answer material occupy main charge volume and influence warhead charge structure the problem of, can guarantee warhead original design intensity and
Performance is injured not change；
2) it by embedding the design that fusible metal constitutes pressure release module in high strength frame, avoids reaction material and play occurs
When strong reaction, the heat of releasing causes main charge the risk factor of vigorous reaction occurs, and ensure that warhead is forming pressure release
The safety of main charge before channel.
Detailed description of the invention
Invention is further described in detail with reference to the accompanying drawings and detailed description.
Fig. 1 is the structural schematic diagram that grant number is ZL201418005074.5 patent.
Fig. 2 is overall structure diagram of the invention.
Fig. 3 is the schematic diagram of drive end bearing bracket in the present invention.
Fig. 4 is the schematic diagram of shell in the present invention.
Fig. 5 is the schematic diagram of pressure release module in the present invention.
Label in figure respectively indicates: 1, pressure release module, 2, drive end bearing bracket, 3, shell, 4, fill, 5, rear end cap, 1-1,
Titanium alloy grid framework, 1-2, fusible metal, 2-1, stepped hole, 2-2, external screw thread, 3-1, internal screw thread 1,3-2, internal screw thread 2.
Specific embodiment
The present invention is described in further detail with reference to the accompanying drawings and examples, it should be noted that the present invention not office
It is limited to following specific embodiments, all same transformation carried out on the basis of technical solution of the present invention are in protection scope of the present invention
It is interior.
In compliance with the above technical solution, as shown in Figure 2-5, the present embodiment provides a kind of fixed temperature melting pressure release knot of missile armament
Structure, including shell 3, drive end bearing bracket 2, pressure release module 1, fill 4, rear end cap 5；It is characterized in that, the shell 3 is first-class wall thickness
Cylindrical sleeve is highly 260mm with a thickness of 6mm, intracavity diameter 125mm, and material is LY12 duralumin, in one end of shell 3
There is internal screw thread 1, the other end has internal screw thread 2；The drive end bearing bracket 2 is a cylindrical cover, and material is LY12 duralumin, with a thickness of
12mm is to be evenly arranged 4 platforms on 2 radius half of drive end bearing bracket and the circumference coaxial with drive end bearing bracket 2 in end face inside radius
Rank through-hole is disposed with external screw thread on the cylinder of drive end bearing bracket 2, is coupled with the internal screw thread 1 of 3 one end of shell, step bore dia is big
One end inside shell 3；The rear end cap 5 is a cylindrical cover, and material is LY12 duralumin, with a thickness of 12mm, in end face
Inside radius is to be evenly arranged 4 step through-holes, rear end on 5 radius half of rear end cap and the circumference coaxial with rear end cap 5
It is disposed with external screw thread on the cylinder of lid 5, is coupled with the internal screw thread 2 of 3 one end of shell, the big one end of step bore dia is in shell
Inside 3；Shell 3, fill 4, drive end bearing bracket 2, rear end cap 5 are using coaxial assembly.
As shown in figure 5, the pressure release module 1 is a circular cylindrical projection stage body, grid framework 1-1 is made of high strength titanium alloy
The fusible metal 1-2 composition inlayed with frame inner cavity, pressure release module 1 fit closely the step for being installed on drive end bearing bracket 2 Yu rear end cap 5
In hole, in the present embodiment, it is Ti-6Al-4V alloy, fusible metal 1-2 material that high strength titanium alloy, which constitutes grid framework 1-1 material,
Material is Bi-Sn alloy；
The fill 4 is the cylindrical grain made of founding, and diameter is identical as 3 internal diameter of shell, is loaded on
Inside shell 3, between drive end bearing bracket 2 and rear end cap 5, in the present embodiment, fill 4 is a kind of the fried containing aluminium of TNT base HMX
Medicine, the 1.82g/cm of density3。
The gross area of the drive end bearing bracket 2 and 4 stepped holes in 5 end face of rear end cap accounts for drive end bearing bracket and rear end cap area respectively
20%~28%, in the present embodiment, the big one end diameter of step bore dia is 38mm, and the small one end diameter of diameter is 30mm, preceding
The small end cross-sectional area summation of 4 step bore dias accounts for drive end bearing bracket and rear end cap end face face respectively in end cap 2 and 5 end face of rear end cap
Long-pending 23%；
The stepped hole of the drive end bearing bracket 2 and rear end cap 5, the big one end depth of diameter are 5 thickness of drive end bearing bracket 2 or rear end cap
One third, in the present embodiment, the stepped hole of drive end bearing bracket 2 and rear end cap 5, the big one end depth of diameter is 4mm；
In the present embodiment, pilot system includes electrical heating oven, thermocouple, temperature control instrument, screen monitoring, the heating of oven
Power is 3000W, and 0~300 DEG C of temperature controller temperature control range, expeimental cartridge is put in oven, is added with the heating rate of 1 DEG C/min to it
Heat, test result show, when temperature is to 112 DEG C, fusible metal starts to soften, outwardly convex, meltable when temperature is to 136 DEG C
Metal molten flows out together along with liquid explosives, and by 47 minutes 2 hours, combustion reaction was had occurred in expeimental cartridge, and end cap is rushed
Out, structural integrity, it can be seen that the fixed temperature of missile armament, which melts slow-released system, reduces the slow roasting response grade of expeimental cartridge.
Working principle of the invention is as follows: when the prominent unexpected thermostimulation for meeting slow cook-off of missile armament, missile armament
In the constantly raised environment of temperature, during temperature is raised, the fusible metal inlayed in pressure release module gradually softens,
When temperature is increased to certain value, fusible metal starts to melt, soft forms pressure release passage, due to the fusible metal of selection
Liquidus curve is generally 130 DEG C or so, when melting, and the temperature threshold locally lighted a fire also not up to occurs for explosive, therefore is formed
Pressure release passage can effectively be discharged fusing after liquid explosives and explosive decompose reaction release gas, to slow down
The increase of body internal pressure, increase the reaction rate of explosive will not sharply, reduce the slow roasting response grade of warhead,
Improve the slow roasting safety of ammunition.
Claims (5)
1. a kind of fixed temperature of missile armament melts pressure release slow-released system, characterized by comprising: shell (3), is let out drive end bearing bracket (2)
Die block (1), fill (4), rear end cap (5)；The shell (3) is first-class wall thickness cylindrical barrel, in one end of shell (3)
Have internal screw thread 1 (3-1), the other end has internal screw thread 2 (3-2)；The drive end bearing bracket (2) is a cylindrical cover, the radius on end face
4 step through-holes, drive end bearing bracket have been evenly arranged for drive end bearing bracket (2) radius half and on the circumference coaxial with drive end bearing bracket (2)
(2) there is external screw thread on cylinder, be coupled with the internal screw thread 1 (3-1) of shell (3) one end, the big one end of step bore dia exists
Shell (3) is internal；The pressure release module (1) is a circular cylindrical projection stage body, constitutes grid framework and frame by high strength titanium alloy
The fusible metal composition that inner cavity is inlayed, pressure release module (1) are coupled in the stepped hole of drive end bearing bracket (2) and rear end cap (5)；Institute
Stating rear end cap (5) is a cylindrical cover, and in end face, inside radius is for rear end cap (5) radius half and same with rear end cap (5)
It has been evenly arranged 4 step through-holes on the circumference of axis, has been disposed with external screw thread on the cylinder of rear end cap (5), with shell (3) one end
Internal screw thread 2 (3-2) is coupled, and the big one end of step bore dia is internal in shell (3)；The fill (4) is to pass through founding
Cylindrical grain made of technique, diameter is identical as shell (3) internal diameter, and it is internal to be loaded on shell (3), be located at drive end bearing bracket (2) with
Between rear end cap (5).
2. the fixed temperature of missile armament as described in claim 1 melts pressure release slow-released system, it is characterised in that: the pressure release module
(1) the embedded fusible metal of grid framework is the alloy that Bi, Sn fusible metal of the fusing point lower than 200 DEG C is constituted.
3. the fixed temperature of missile armament as described in claim 1 melts pressure release slow-released system, it is characterised in that: the drive end bearing bracket (2)
The 20%~28% of front/rear end cap sectional area is accounted for the aperture gross area of 4 stepped holes in rear end cap (5) end face.
4. the fixed temperature of missile armament as claimed in claim 3 melts pressure release slow-released system, it is characterised in that: the drive end bearing bracket (2)
The 23% of front/rear end cap sectional area is accounted for the aperture gross area of 4 stepped holes in rear end cap (5) end face.
5. leading the fixed temperature of missile armament as described in claim 1 melts pressure release slow-released system, it is characterised in that: the drive end bearing bracket
(2) with the stepped hole of rear end cap (5), the big one end depth of diameter is the one third of drive end bearing bracket (2) or rear end cap (5) thickness.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811136558.7A CN109282711A (en) | 2018-09-28 | 2018-09-28 | The fixed temperature of missile armament melts pressure release slow-released system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811136558.7A CN109282711A (en) | 2018-09-28 | 2018-09-28 | The fixed temperature of missile armament melts pressure release slow-released system |
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| Publication Number | Publication Date |
|---|---|
| CN109282711A true CN109282711A (en) | 2019-01-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811136558.7A Pending CN109282711A (en) | 2018-09-28 | 2018-09-28 | The fixed temperature of missile armament melts pressure release slow-released system |
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| CN (1) | CN109282711A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110987456A (en) * | 2019-11-18 | 2020-04-10 | 上海新力动力设备研究所 | Engine simulation device for ignition device test |
| CN112747639A (en) * | 2021-01-15 | 2021-05-04 | 中国工程物理研究院总体工程研究所 | A alleviate structure for release of thick casing ammunition pressure |
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| US20050235861A1 (en) * | 2004-04-08 | 2005-10-27 | Nico-Pyrotechnik Hanns-Juergen Diederichs Gmbh & Co. Kg, A Large Entity | Cartridge munition, particularly one of medium caliber |
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| US8505458B1 (en) * | 2012-01-27 | 2013-08-13 | The United States Of America As Represented By The Secretary Of The Navy | Venting cap system |
| US8550004B1 (en) * | 2009-10-21 | 2013-10-08 | The United States Of America As Represented By The Secretary Of The Army | Riveted cartridge venting |
| CN105043172A (en) * | 2015-06-04 | 2015-11-11 | 西安近代化学研究所 | Internal stress release device for liquid-phase charging payload |
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2018
- 2018-09-28 CN CN201811136558.7A patent/CN109282711A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN1258347A (en) * | 1998-03-17 | 2000-06-28 | 蒂姆萨弗派克艾卡尔斯库加股份公司 | Safety packaging |
| US20050235861A1 (en) * | 2004-04-08 | 2005-10-27 | Nico-Pyrotechnik Hanns-Juergen Diederichs Gmbh & Co. Kg, A Large Entity | Cartridge munition, particularly one of medium caliber |
| CN2852037Y (en) * | 2005-12-30 | 2006-12-27 | 中国北方工业公司 | Package drum for modular charge |
| US8550004B1 (en) * | 2009-10-21 | 2013-10-08 | The United States Of America As Represented By The Secretary Of The Army | Riveted cartridge venting |
| US8505458B1 (en) * | 2012-01-27 | 2013-08-13 | The United States Of America As Represented By The Secretary Of The Navy | Venting cap system |
| CN105043172A (en) * | 2015-06-04 | 2015-11-11 | 西安近代化学研究所 | Internal stress release device for liquid-phase charging payload |
Non-Patent Citations (1)
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110987456A (en) * | 2019-11-18 | 2020-04-10 | 上海新力动力设备研究所 | Engine simulation device for ignition device test |
| CN112747639A (en) * | 2021-01-15 | 2021-05-04 | 中国工程物理研究院总体工程研究所 | A alleviate structure for release of thick casing ammunition pressure |
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Application publication date: 20190129 |