CN109141144A - A kind of infrared guidance guided missile breaking type casts cover aside - Google Patents
A kind of infrared guidance guided missile breaking type casts cover aside Download PDFInfo
- Publication number
- CN109141144A CN109141144A CN201811154720.8A CN201811154720A CN109141144A CN 109141144 A CN109141144 A CN 109141144A CN 201811154720 A CN201811154720 A CN 201811154720A CN 109141144 A CN109141144 A CN 109141144A
- Authority
- CN
- China
- Prior art keywords
- shield
- frangible
- infrared
- drag reduction
- reduction head
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 230000001681 protective effect Effects 0.000 claims abstract description 21
- 229920001971 elastomer Polymers 0.000 claims abstract description 18
- 239000004033 plastic Substances 0.000 claims abstract description 15
- 229920003023 plastic Polymers 0.000 claims abstract description 15
- 239000003999 initiator Substances 0.000 claims abstract description 10
- 239000000463 material Substances 0.000 claims description 19
- 238000009413 insulation Methods 0.000 claims description 5
- 229920002635 polyurethane Polymers 0.000 claims description 5
- 239000004814 polyurethane Substances 0.000 claims description 5
- 229910000851 Alloy steel Inorganic materials 0.000 claims description 3
- 229920000297 Rayon Polymers 0.000 claims description 3
- 238000002955 isolation Methods 0.000 claims description 3
- 238000005192 partition Methods 0.000 claims description 3
- 238000004080 punching Methods 0.000 claims description 3
- 239000000919 ceramic Substances 0.000 claims description 2
- 239000011521 glass Substances 0.000 claims description 2
- 229910021426 porous silicon Inorganic materials 0.000 claims description 2
- HQVNEWCFYHHQES-UHFFFAOYSA-N silicon nitride Chemical compound N12[Si]34N5[Si]62N3[Si]51N64 HQVNEWCFYHHQES-UHFFFAOYSA-N 0.000 claims description 2
- 241000209202 Bromus secalinus Species 0.000 claims 1
- 230000003111 delayed effect Effects 0.000 claims 1
- 230000011218 segmentation Effects 0.000 claims 1
- 238000005474 detonation Methods 0.000 abstract description 12
- 230000000977 initiatory effect Effects 0.000 abstract description 7
- 238000012360 testing method Methods 0.000 abstract description 7
- 238000013461 design Methods 0.000 abstract description 6
- 230000000694 effects Effects 0.000 abstract description 6
- 238000002474 experimental method Methods 0.000 abstract description 6
- 230000002411 adverse Effects 0.000 abstract description 4
- 238000010438 heat treatment Methods 0.000 abstract description 4
- 238000005266 casting Methods 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 7
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000003139 buffering effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 238000003384 imaging method Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 230000017260 vegetative to reproductive phase transition of meristem Effects 0.000 description 1
Classifications
-
- 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
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
- F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/72—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material
- F42B12/76—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material of the casing
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid Mechanics (AREA)
- Thermal Sciences (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
A kind of infrared guidance guided missile breaking type casts cover aside comprising: frangible drag reduction head-shield, connection ring, cushion collar, primacord, electric initiator, protective case, infrared dome；It uses frangible drag reduction head-shield to provide excellent aerodynamic configuration for the autonomous high-speed flight of guided missile, solves the problems, such as infrared dome Aerodynamic Heating blinding and the loss of big drag power；Variable diameters, the design of varying pitch primacord, ensure that frangible drag reduction head-shield is crushed uniformly when casting aside in infrared guidance missile flight latter stage, while reducing influence of the detonation wave to infrared dome；It is designed using cushion collar and protective case duplicate protection, detonation wave will not generate adverse effect to the transparent infrared window of infrared dome when ensure that fuse arming test experiment initiation；Using soft rubber ring and rigid plastics ring double shielding, when ensure that fuse arming test experiment initiation detonation wave will not the rectification cover body to infrared dome generate adverse effect.
Description
Technical field
The present invention relates to a kind of infrared guidance guided missile head-shields to cast technology aside, and in particular to a kind of infrared guidance guided missile breaking type
Cast cover aside.
Background technique
Infrared guidance guided missile have many advantages, such as passive detection, not vulnerable to after electronic interferences, transmitting regardless of, imaging identification,
Have the function of can not be substituted under the information-based strongly disturbing environmental condition of modern war.But meanwhile more with missile flight speed
Fast and flying distance is farther, and infrared guidance guided missile is faced with Aerodynamic Heating blinding and big drag power loss problem, how to solve this
A little problems, which become the research and development of new infrared seeker, to be solved the problems, such as.
Summary of the invention
The purpose of the present invention is to provide a kind of infrared guidance guided missile breaking types to cast cover aside, i.e., in infrared guidance nose of missile
Increase separable head-shield, to solve initial flying stage frictional heat and commutation issue；In giving for infrared guidance missile flight latter stage
Moment again separates separable head-shield, and infrared seeker starts to work normally, and solves infrared guidance guided missile with the method and faces
Aerodynamic Heating blinding and big drag power problem is lost.
For achieving the above object, the present invention adopts the following technical scheme:
A kind of infrared guidance guided missile breaking type casts cover aside, it is characterized in that: include frangible drag reduction head-shield, connection ring, cushion collar,
Primacord, electric initiator, protective case, infrared dome；The frangible drag reduction head-shield material be porous silicon nitride ceramic be sintered and
At shape is coniform thin walled shell, and shape is to be rotated to be formed around rotary shaft by karman curve, and purpose is to reduce missile flight initial stage
There are connection ring in air drag during high-speed flight, tail portion, and frangible drag reduction head-shield and connection ring are bonded together with viscose；
The cushion collar is put together by more valve polyurethane foamed materials of even partition in the axial direction, and material has good slow
Punching performance, shape is identical as the inner wall shape of frangible drag reduction head-shield, and contoured surface has helical groove, be embedded in groove lead it is quick-fried
There are bald coniform convolution cavity in rope, tail portion, have pit on cushion collar divisional plane, electric initiator, electric initiating are disposed in pit
Device connects electric connector by conducting wire, and cushion collar is arranged on the inside of frangible drag reduction head-shield, and shape is bonded with frangible drag reduction head-shield；Institute
It states protective case to be put together by more valve polyurethane foamed materials of even partition in the axial direction, material has good buffering
Performance, shape is identical as the bald coniform convolution first half shape of cavity of cushion collar tail portion, and there is approximate sphericity in tail portion
Cavity, protective case are arranged in the front end of cushion collar tail portion cavity, and shape is bonded with the front end of cushion collar tail portion cavity, protective case
The splicing seams of splicing seams and cushion collar dislocation arrangement；The infrared dome includes the transparent infrared window and tail portion radome fairing on head
Ontology, infrared dome are arranged in the cavity being made of frangible drag reduction head-shield, cushion collar, protective case, shape and frangible drag reduction
The cavity that head-shield, cushion collar, protective case form is bonded substantially, and infrared dome and frangible drag reduction head-shield pass through connection ring screw
It links together.
For improved technology scheme, further: frangible drag reduction head-shield material also can be used devitrified glass and be sintered.
It is further: to have arranged stacked between frangible drag reduction head-shield tail portion and infrared dome for improved technology scheme
Soft rubber ring, the isolation of rigid plastics ring, soft rubber ring and rigid plastics ring are that sheet, split-type are spliced, soft rubber
The splicing seams of rubber ring and the splicing seams of rigid plastics ring misplace and arrange, soft rubber ring is contacted with frangible drag reduction head-shield, hard modeling
Material ring is contacted with infrared dome, by the soft rubber ring of arranged stacked, rigid plastics ring, can be reduced quick-fried when fuse arming test experiment initiation
Hong influence of the wave to infrared dome.
Further for improved technology scheme: the material of connection ring is low-expansion alloy steel, to guarantee to connect under thermal environment
Connect the matching of ring and frangible drag reduction head-shield material expansion between the two.
For improved technology scheme, further: connection ring outer side covering has heat insulation loop, when reducing guided missile high-speed flight
The temperature of connection ring further improves the matching of connection ring and frangible drag reduction head-shield material expansion between the two.
It is further for improved technology scheme: being bonded there are certain gap between frangible drag reduction head-shield and connection ring,
Further improve the matching of connection ring and frangible drag reduction head-shield material expansion between the two.
For improved technology scheme, further: the diameter of primacord designs for variable diameters, and the screw pitch of primacord is varying pitch
Design, frangible drag reduction head-shield is broken uniformly when guaranteeing fuse arming test experiment initiation, while influence of the detonation wave to infrared dome is minimum.
Beneficial effect
Due to the adoption of the technical scheme as described above, the invention has the following beneficial effects:
It uses frangible drag reduction head-shield to provide excellent aerodynamic configuration for the autonomous high-speed flight of guided missile, solves infrared dome
Problem is lost in Aerodynamic Heating blinding and big drag power；Variable diameters, the design of varying pitch primacord, ensure that frangible drag reduction head-shield red
It is crushed uniformly when outer seeker flight latter stage casts aside, while reducing influence of the detonation wave to infrared dome；Using cushion collar
It is designed with protective case duplicate protection, detonation wave will not generate the transparent infrared window of infrared dome when ensure that fuse arming test experiment initiation
Adverse effect；Using soft rubber ring and rigid plastics ring double shielding, detonation wave will not be to red when ensure that fuse arming test experiment initiation
The rectification cover body of outer radome fairing generates adverse effect；Using heat insulation loop, low-expansion alloy steel connection ring and frangible drag reduction head
Gap design Nian Jie with connection ring is covered, guarantees of frangible drag reduction head-shield and connection ring material expansion between the two under thermal environment
With property, the reliability that frangible drag reduction head-shield is connected with hot conditions flowering structure of the connection ring in guided missile high-speed flight is improved.
It designs through the above structure, perfection realizes frangible drag reduction head-shield and casts safe and reliable protection with guided missile aside, has
Flight resistance is small, disturbance is small, small feature is influenced on body sensitive structure, and the technical solution is made to have maximum universality, can
To provide a kind of feasible solution for all kinds of remote infrared type tactical missiles.
Detailed description of the invention
Fig. 1 is that a kind of infrared guidance guided missile breaking type casts cover schematic diagram aside；
Fig. 2 is that a kind of infrared guidance guided missile breaking type casts cover assembling schematic diagram aside.
In figure: 1, frangible drag reduction head-shield, 2, primacord, 3, electric initiator, 4, cushion collar, 5, protective case, 6, soft rubber
Ring, 7, rigid plastics ring, 8, connection ring, 9, heat insulation loop, 10, conducting wire, 11, infrared dome, 12, electric connector.
Specific embodiment
The present invention can be explained in more detail by the following examples, the open purpose of the present invention is intended to protect the present invention
All changes and improvements in range, the invention is not limited to the following examples:
A kind of infrared guidance guided missile breaking type casts cover aside comprising: frangible drag reduction head-shield 1, cushion collar 4, is led connection ring 8
Quick-fried rope 2, electric initiator 3, protective case 5, infrared dome 11；Frangible drag reduction head-shield 1 is bonded together with connection ring 8 with viscose；
Cushion collar 4 is arranged in 1 inside of frangible drag reduction head-shield, is embedded with primacord 2 in 4 contoured surface groove of cushion collar, in divisional plane pit
It is disposed with electric initiator 3, electric initiator 3 connects electric connector 12 by conducting wire 10；Protective case 5 is arranged in 4 tail portion of cushion collar sky
The front end of chamber, the splicing seams of protective case 5 and the splicing seams of cushion collar 4 misplace and arrange；Infrared dome 11 is arranged in be subtracted by frangible
It hinders in the cavity that head-shield 1, cushion collar 4, protective case 5 form, is connected to one with screw by connection ring 8 with frangible drag reduction head-shield 1
It rises；Soft rubber ring 6, rigid plastics ring 7 are arranged between frangible 1 tail portion of drag reduction head-shield and infrared dome ontology；Heat insulation loop 9
It is covered on the outer surface of connection ring 8.
In actual work, fly the stage in the ground stage of guided missile, extension and autonomous flight stage, frangible drag reduction head-shield 1 undertake
The test of the various mechanical environments, thermal environment condition of guided missile, and excellent drag reduction aerodynamic configuration is provided for guided missile；In frangible drag reduction
When head-shield 1 is cast aside, primacord 2 is according to commanding detonation, and under the action of detonation wave, frangible 1 Integral-crushing of drag reduction head-shield is simultaneously cast aside,
Detonation wave after cushion collar 4 and protective case 5 detonate to primacord 2 is buffered and is absorbed, and plays buffer action to detonation residue；
When frangible drag reduction head-shield 1 is crushed, fragment is uniform, small-sized, and very light in weight and bomb body relative velocity are very low, there is no and
The risk of bomb body other structures generation severe crash and damage；After frangible drag reduction head-shield 1 is broken casts aside, cushion collar 4 and protection
More valve structures of set 5 lose outer layer support, fall off naturally under the stripping effect of pneumatic incoming flow, simultaneously because cushion collar 4 and guarantor
Sheath 5 is made of polyurethane foamed material, and relative velocity is not high, even if colliding after stripping with bomb body other structures
It will not be caused to damage；The soft or hard protection that soft rubber ring 6 and rigid plastics ring 7 form is combined to 11 tail of infrared dome
The radome fairing body part in portion realizes isolation and protection, so that it is guaranteed that detonation wave is while broken outer layer frangible drag reduction head-shield 1
The rectification cover body of 11 tail portion of infrared dome will not be had an impact；After frangible drag reduction head-shield 1 is broken casts aside, soft rubber
Ring 6 and rigid plastics ring 7 lose the support of outer layer, realize under the stripping effect of pneumatic incoming flow and cast aside automatically, while soft rubber
The Material Strength and hardness of rubber ring 6 and rigid plastics ring 7 be not high, and size is smaller, and opposite missile velocity is not high, even if after stripping
Colliding with bomb body other structures will not cause to damage to it.
Claims (7)
1. a kind of infrared guidance guided missile breaking type casts cover aside, it is characterized in that: including frangible drag reduction head-shield (1), connection ring (8), delaying
Punching set (4), primacord (2), electric initiator (3), protective case (5), infrared dome (11)；Frangible drag reduction head-shield (1) material
Matter is that porous silicon nitride ceramic is sintered, and shape is coniform thin walled shell, and shape is by karman curve around rotary shaft rotary
At tail portion has connection ring (8), and frangible drag reduction head-shield (1) is Nian Jie with connection ring (8) viscose；The cushion collar (4) is by along axis
More valve polyurethane foamed materials of even partition are put together, and shape is identical as the inner wall shape of frangible drag reduction head-shield (1), outside
There is helical groove on shape surface, is embedded in groove primacord (2), and there is bald coniform convolution cavity in tail portion, has on divisional plane recessed
It cheats, is disposed with electric initiator (3) in pit, electric initiator (3) passes through conducting wire (10) connection electric connector (12), cushion collar (4)
It is arranged on the inside of frangible drag reduction head-shield (1), shape is bonded with frangible drag reduction head-shield (1)；The protective case (5) is by uniform along axis
More valve polyurethane foamed materials of segmentation are put together, before the bald coniform convolution cavity of shape and cushion collar (4) tail portion
Half part shape is identical, and there is the cavity of approximate sphericity in tail portion, and the splicing seams of protective case (5) and the splicing seams of cushion collar (4) misplace
Arrangement, protective case (5) are arranged in the front end of cushion collar (4) tail portion cavity, the front end patch of shape and cushion collar (4) tail portion cavity
It closes；The infrared dome (11) includes the transparent infrared window and tail portion rectification cover body on head, infrared dome (11) arrangement
In the cavity being made of frangible drag reduction head-shield (1), cushion collar (4), protective case (5), shape and frangible drag reduction head-shield (1) are delayed
The cavity that punching set (4), protective case (5) form is bonded substantially, and infrared dome (11) and frangible drag reduction head-shield (1) pass through connection ring
(8) it is linked together with screw.
2. a kind of infrared guidance guided missile breaking type casts cover aside according to claim 1, it is characterized in that: frangible drag reduction head-shield (1)
Material is that devitrified glass is sintered.
3. a kind of infrared guidance guided missile breaking type casts cover aside according to claim 1, it is characterized in that: frangible drag reduction head-shield (1)
There are soft rubber ring (6), the rigid plastics ring (7) of arranged stacked between tail portion and infrared dome (11) tail portion rectification cover body
Isolation, soft rubber ring (6) and rigid plastics ring (7) are sheet, split-type is spliced, the splicing seams of soft rubber ring (6)
It misplaces and arranges with the splicing seams of rigid plastics ring (7), soft rubber ring (6) is contacted with frangible drag reduction head-shield (1), rigid plastics ring
(7) it is contacted with infrared dome (11).
4. a kind of infrared guidance guided missile breaking type casts cover aside according to claim 1, it is characterized in that: the material of connection ring (8)
For low-expansion alloy steel.
5. a kind of infrared guidance guided missile breaking type casts cover aside according to claim 1, it is characterized in that: being covered on the outside of connection ring (8)
It is stamped heat insulation loop (9).
6. a kind of infrared guidance guided missile breaking type casts cover aside according to claim 1, it is characterized in that: frangible drag reduction head-shield (1)
Bonding gap is provided between connection ring (8).
7. a kind of infrared guidance guided missile breaking type casts cover aside according to claim 1, it is characterized in that: the diameter of primacord (2)
To straighten gauge structure；The screw pitch of primacord (2) is varying pitch structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811154720.8A CN109141144B (en) | 2018-09-29 | 2018-09-29 | Infrared guided missile crushing type throwing separation cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811154720.8A CN109141144B (en) | 2018-09-29 | 2018-09-29 | Infrared guided missile crushing type throwing separation cover |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109141144A true CN109141144A (en) | 2019-01-04 |
| CN109141144B CN109141144B (en) | 2024-02-09 |
Family
ID=64813917
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811154720.8A Active CN109141144B (en) | 2018-09-29 | 2018-09-29 | Infrared guided missile crushing type throwing separation cover |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109141144B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114829868A (en) * | 2019-12-04 | 2022-07-29 | Bae系统信息和电子系统集成有限公司 | Ammunition front cone |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5003883A (en) * | 1990-07-23 | 1991-04-02 | The United States Of America As Represented By The Secretary Of The Army | Lightweight blast shield |
| CN1961194A (en) * | 2004-05-27 | 2007-05-09 | Mbda法国公司 | Flying weapon for observing the ground |
| CN202024690U (en) * | 2010-11-20 | 2011-11-02 | 王先全 | Missile with vacuum shell |
| KR20120056123A (en) * | 2010-11-24 | 2012-06-01 | 국방과학연구소 | Protective cover of missile, missile having the same and impact relief method of missile |
| RU2010150397A (en) * | 2010-12-08 | 2012-06-20 | Федеральное государственное унитарное предприятие "Обнинское научно-производственное предприятие "Технология" (RU) | ROCKET HEAD |
| CN105277227A (en) * | 2015-10-13 | 2016-01-27 | 北京航天长征飞行器研究所 | Infrared protective cover with integrated dual-layer structure for heat insulation and force bearing |
| US20170131076A1 (en) * | 2014-06-25 | 2017-05-11 | Mbda France | Missile provided with a separable protective fairing |
| CN209027376U (en) * | 2018-09-29 | 2019-06-25 | 中国空空导弹研究院 | A kind of infrared guidance guided missile breaking type casts cover aside |
-
2018
- 2018-09-29 CN CN201811154720.8A patent/CN109141144B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5003883A (en) * | 1990-07-23 | 1991-04-02 | The United States Of America As Represented By The Secretary Of The Army | Lightweight blast shield |
| CN1961194A (en) * | 2004-05-27 | 2007-05-09 | Mbda法国公司 | Flying weapon for observing the ground |
| CN202024690U (en) * | 2010-11-20 | 2011-11-02 | 王先全 | Missile with vacuum shell |
| KR20120056123A (en) * | 2010-11-24 | 2012-06-01 | 국방과학연구소 | Protective cover of missile, missile having the same and impact relief method of missile |
| RU2010150397A (en) * | 2010-12-08 | 2012-06-20 | Федеральное государственное унитарное предприятие "Обнинское научно-производственное предприятие "Технология" (RU) | ROCKET HEAD |
| US20170131076A1 (en) * | 2014-06-25 | 2017-05-11 | Mbda France | Missile provided with a separable protective fairing |
| CN105277227A (en) * | 2015-10-13 | 2016-01-27 | 北京航天长征飞行器研究所 | Infrared protective cover with integrated dual-layer structure for heat insulation and force bearing |
| CN209027376U (en) * | 2018-09-29 | 2019-06-25 | 中国空空导弹研究院 | A kind of infrared guidance guided missile breaking type casts cover aside |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114829868A (en) * | 2019-12-04 | 2022-07-29 | Bae系统信息和电子系统集成有限公司 | Ammunition front cone |
| CN114829868B (en) * | 2019-12-04 | 2023-10-20 | Bae系统信息和电子系统集成有限公司 | Ammunition front cone |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109141144B (en) | 2024-02-09 |
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