CN109764766A - A kind of electricity duct tail portion push type miniature missile - Google Patents
A kind of electricity duct tail portion push type miniature missile Download PDFInfo
- Publication number
- CN109764766A CN109764766A CN201910081371.XA CN201910081371A CN109764766A CN 109764766 A CN109764766 A CN 109764766A CN 201910081371 A CN201910081371 A CN 201910081371A CN 109764766 A CN109764766 A CN 109764766A
- Authority
- CN
- China
- Prior art keywords
- electric duct
- push type
- tail portion
- battery
- type miniature
- 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.)
- Pending
Links
- 230000005611 electricity Effects 0.000 title claims description 8
- 229910000838 Al alloy Inorganic materials 0.000 claims description 4
- 229910000737 Duralumin Inorganic materials 0.000 claims description 4
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 4
- 239000002131 composite material Substances 0.000 claims description 4
- 229910052744 lithium Inorganic materials 0.000 claims description 4
- 239000000843 powder Substances 0.000 abstract description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 239000000446 fuel Substances 0.000 abstract description 2
- 239000004449 solid propellant Substances 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000003814 drug Substances 0.000 description 1
- 239000003721 gunpowder Substances 0.000 description 1
- 208000020442 loss of weight Diseases 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Landscapes
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses a kind of electric duct tail portion push type miniature missile, electric duct power packages are arranged by the rear portion of control cabinet in the present invention, and electric duct power packages provide power by battery, and battery connects computer, and computer controls battery discharge and drives electric duct power packages.The present invention uses electric duct power packages to provide power for guided missile, thrust caused by electric duct power packages is much smaller than the thrust that powder burning generates, it avoids traditional fuel and promotes generated overload, therefore, the present invention can reduce the intensity requirement of missile airframe, the total weight of guided missile can not only be reduced, additionally it is possible to reduce production cost；The present invention is powered electric duct power packages using battery, and range greatly increases.
Description
Technical field
The invention belongs to guided missile fields, and in particular to a kind of electricity duct tail portion push type miniature missile.
Background technique
Guided missile plays increasingly important role as a kind of precision strike weapon in modern battlefield.It is traditional with
Fighter plane and missile truck as platform guided missile it is bulky, structure is complicated, higher cost, incidentally injures big, Zhi Nengyong
Work hits target of military importance.The target of precision target and small strike range is then to need unmanned plane carry miniature missile
Carry out precision strike.
It is to use solid propellant rocket as boosting power, otherwise be exactly no move that existing unmanned plane, which uses air-to-ground guided missile all,
The guided bomb of power.Guided bomb is because range is short, it is desirable to get to target and unmanned plane is then needed to be positioned as close to target, in this way
One carrys out the increase of arm discharge difficulty, and unmanned plane is highly susceptible to ground based threats.With solid propellant rocket as power
Guided missile is also because of its engine Shortcomings.First is that solid propellant rocket be by solid gunpowder burning generate power, production and
Storage has some potential safety problems；Second is that the thrust that powder burning generates is big, and it is high to body intensity requirement itself, it is unfavorable in this way
In use some nonmetallic materials as structural member carry out loss of weight；Third is that combustion rate of powder is fast, because mini-bomb volume and weight limits
System can not fill more medicine, so engine can only work several seconds short, limit the range of guided missile.
Summary of the invention
The purpose of the present invention is to overcome the above shortcomings and to provide a kind of electric duct tail portion push type miniature missiles, can not only
Reduce overall weight, additionally it is possible to improve the range of guided missile.
In order to achieve the above object, the present invention includes warhead, and the front of warhead is provided with seeker, warhead rear portion
It is provided with control cabinet, the rear portion of control cabinet is provided with electric duct power packages, and electric duct power packages provide power, battery by battery
Computer is connected, battery and computer are placed in control cabinet, and computer drives electric duct power packages for controlling battery discharge.
Battery is continuously electric duct power packages in the entire flight course of guided missile and provides electric power, so that guided missile is in entire flight course
It is dynamic always, effectively improve the range of guided missile.
Several rudders are provided on control cabinet, each rudder passes through corresponding steering engine and is driven, and steering engine is placed in control cabinet,
Steering engine connects computer, and computer is used to drive the angle of steering engine adjustment rudder.
It is provided with to take off on control cabinet and insert, take off and insert connection computer, computer, which passes through to take off to insert, carries out data exchange with host computer.
Electric duct power packages are fixed on the rear portion of control cabinet by duct bracket.
Duct bracket uses composite material.
It is fixed with several missile wings on the axial plane of warhead, is angularly arranged between adjacent missile wing.
Lifting lug is provided on the axial plane of warhead.
Lifting lug and warhead are all made of aviation-grade duralumin, hard alumin ium alloy.
Battery uses lithium battery.
Compared with prior art, electric duct power packages are arranged by the rear portion of control cabinet in the present invention, and electric duct power packages are logical
It crosses battery and power is provided, battery connects computer, and computer controls battery discharge and drives electric duct power packages.The present invention is using electricity
Duct power packages provide power for guided missile, and thrust caused by electric duct power packages is much smaller than the thrust that powder burning generates, keeps away
Traditional fuel is exempted from and has promoted generated overload, therefore, the present invention can reduce the intensity requirement of missile airframe, can not only drop
The total weight of low guided missile, additionally it is possible to reduce production cost；The present invention is powered electric duct power packages using battery, and range is big
It is big to increase.
Further, duct bracket of the invention uses composite material, can mitigate weight again while proof strength.
Further, warhead of the invention and lifting lug use aviation-grade duralumin, hard alumin ium alloy, can mitigate the weight of guided missile significantly
Amount.
Further, battery of the invention uses lithium battery, can be improved range of the invention.
Detailed description of the invention
Fig. 1 is the structural diagram of the present invention；
Wherein, 1- target seeker, 2- warhead, 3- lifting lug, 4- missile wing, 5- is de- to be inserted, 6- rudder, 7- control cabinet, 8- duct bracket,
9- electricity duct power packages.
Specific embodiment
The present invention will be further explained below with reference to the attached drawings.
Referring to Fig. 1, the present invention includes warhead 2, and lifting lug 3 and several missile wings 4 are fixed on the axial plane of warhead 2, adjacent
Missile wing 4 between be angularly arranged, the front of warhead 2 is provided with seeker 1, and 2 rear portion of warhead is provided with control cabinet 7, control
The rear portion in cabin 7 is provided with electric duct power packages 9, and electric duct power packages 9 are fixed on the rear portion of control cabinet 7, electricity by duct bracket 8
Duct power packages 9 provide power by battery, and battery connects computer, and battery and computer are placed in control cabinet 7, computer
Electric duct power packages 9 are driven for controlling battery discharge, are provided with several rudders 6 on control cabinet 7, each rudder 6 is by corresponding
Steering engine is driven, and steering engine is placed in control cabinet 7, and steering engine connects computer, and computer is used to drive the angle of steering engine adjustment rudder 6
It spends, de- slotting 5 is provided on control cabinet 7, take off slotting 5 and connect computers, computer passes through de- slotting 5 and host computer progress data exchange.
Preferably, duct bracket 8 uses composite material.
Preferably, lifting lug 3 and warhead 2 are all made of aviation-grade duralumin, hard alumin ium alloy.
Preferably, battery uses lithium battery.
In use, guided missile is fixed on required position by lifting lug 3, and it is attached by de- slotting 5 with host computer, it is upper
Machine is communicated by de- slotting 5 with the computer inside control cabinet 7, when needing to emit, and is issued to computer and is referred to accordingly
It enables, lifting lug 3 is detached from fixed position, takes off slotting 5 and is detached from from host computer junction, and computer starting battery discharge drives electric duct power
Group 9, electric duct power packages 9 provide guided missile required thrust, and computer controls steering engine, and servo driving rudder 6 is swung, and adjust
The direction of guided missile.
Claims (9)
1. a kind of electricity duct tail portion push type miniature missile, which is characterized in that including warhead (2), the front of warhead (2) is set
It is equipped with seeker (1), warhead (2) rear portion is provided with control cabinet (7), and the rear portion of control cabinet (7) is provided with electric duct power packages
(9), electric duct power packages (9) provide power by battery, and battery connects computer, and battery and computer are placed in control cabinet
(7) in, computer drives electric duct power packages (9) for controlling battery discharge.
2. a kind of electric duct tail portion push type miniature missile according to claim 1, which is characterized in that on control cabinet (7)
It is provided with several rudders (6), each rudder (6) is driven by corresponding steering engine, and steering engine is placed in control cabinet (7), and steering engine connects
Computer is connect, computer is used to drive the angle of steering engine adjustment rudder (6).
3. a kind of electric duct tail portion push type miniature missile according to claim 1, which is characterized in that on control cabinet (7)
De- slotting (5) are provided with, slotting (5) is taken off and connects computer, computer carries out data exchange by de- slotting (5) and host computer.
4. a kind of electric duct tail portion push type miniature missile according to claim 1, which is characterized in that electric duct power packages
(9) rear portion of control cabinet (7) is fixed on by duct bracket (8).
5. a kind of electric duct tail portion push type miniature missile according to claim 4, which is characterized in that duct bracket (8)
Using composite material.
6. a kind of electric duct tail portion push type miniature missile according to claim 1, which is characterized in that warhead (2)
It is fixed on axial plane several missile wings (4), adjacent missile wing is angularly arranged between (4).
7. a kind of electric duct tail portion push type miniature missile according to claim 1, which is characterized in that warhead (2)
Lifting lug (3) are provided on axial plane.
8. a kind of electric duct tail portion push type miniature missile according to claim 7, which is characterized in that lifting lug (3) and war
Pan (2) is all made of aviation-grade duralumin, hard alumin ium alloy.
9. a kind of electric duct tail portion push type miniature missile according to claim 1, which is characterized in that battery is using lithium electricity
Pond.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910081371.XA CN109764766A (en) | 2019-01-28 | 2019-01-28 | A kind of electricity duct tail portion push type miniature missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910081371.XA CN109764766A (en) | 2019-01-28 | 2019-01-28 | A kind of electricity duct tail portion push type miniature missile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109764766A true CN109764766A (en) | 2019-05-17 |
Family
ID=66454456
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910081371.XA Pending CN109764766A (en) | 2019-01-28 | 2019-01-28 | A kind of electricity duct tail portion push type miniature missile |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109764766A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112880489A (en) * | 2021-03-17 | 2021-06-01 | 西安富沃德光电科技有限公司 | Guided missile convenient to maintain |
| CN114046693A (en) * | 2021-09-22 | 2022-02-15 | 西安航天动力技术研究所 | Small rocket based on ducted engine and lifting method thereof |
| CN115016516A (en) * | 2022-06-14 | 2022-09-06 | 西安深瞳智控技术有限公司 | Steering engine control aircraft suitable for air rudder and vector rudder and test method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002151129A (en) * | 2000-11-14 | 2002-05-24 | Mitsubishi Electric Corp | Power generator for missile |
| CN106828908A (en) * | 2017-01-24 | 2017-06-13 | 北京电子工程总体研究所 | A kind of electronic single shaft shrouded propeller aircraft |
| CN206502014U (en) * | 2017-01-24 | 2017-09-19 | 浙江水利水电学院 | A kind of single duct engine |
| CN207832032U (en) * | 2018-01-29 | 2018-09-07 | 华南农业大学 | Four duct electric power rockets and its emitter |
| CN108955423A (en) * | 2018-06-27 | 2018-12-07 | 西安恒宇众科空间技术有限公司 | A kind of non-priming system guided missile with water conservancy diversion air intake structure |
| CN209689503U (en) * | 2019-01-28 | 2019-11-26 | 西安深瞳智控技术有限公司 | A kind of electricity duct tail portion push type miniature missile |
-
2019
- 2019-01-28 CN CN201910081371.XA patent/CN109764766A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002151129A (en) * | 2000-11-14 | 2002-05-24 | Mitsubishi Electric Corp | Power generator for missile |
| CN106828908A (en) * | 2017-01-24 | 2017-06-13 | 北京电子工程总体研究所 | A kind of electronic single shaft shrouded propeller aircraft |
| CN206502014U (en) * | 2017-01-24 | 2017-09-19 | 浙江水利水电学院 | A kind of single duct engine |
| CN207832032U (en) * | 2018-01-29 | 2018-09-07 | 华南农业大学 | Four duct electric power rockets and its emitter |
| CN108955423A (en) * | 2018-06-27 | 2018-12-07 | 西安恒宇众科空间技术有限公司 | A kind of non-priming system guided missile with water conservancy diversion air intake structure |
| CN209689503U (en) * | 2019-01-28 | 2019-11-26 | 西安深瞳智控技术有限公司 | A kind of electricity duct tail portion push type miniature missile |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112880489A (en) * | 2021-03-17 | 2021-06-01 | 西安富沃德光电科技有限公司 | Guided missile convenient to maintain |
| CN114046693A (en) * | 2021-09-22 | 2022-02-15 | 西安航天动力技术研究所 | Small rocket based on ducted engine and lifting method thereof |
| CN115016516A (en) * | 2022-06-14 | 2022-09-06 | 西安深瞳智控技术有限公司 | Steering engine control aircraft suitable for air rudder and vector rudder and test method |
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