CN209689505U - A kind of coaxial double-oar tail portion push type miniature missile - Google Patents
A kind of coaxial double-oar tail portion push type miniature missile Download PDFInfo
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- CN209689505U CN209689505U CN201920145874.4U CN201920145874U CN209689505U CN 209689505 U CN209689505 U CN 209689505U CN 201920145874 U CN201920145874 U CN 201920145874U CN 209689505 U CN209689505 U CN 209689505U
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- missile
- coaxial double
- oar
- tail portion
- paddle
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Abstract
The utility model discloses a kind of coaxial double-oar tail portion push type miniature missiles, coaxial double-oar power packages are arranged in the tail portion of control cabinet in the utility model, coaxial double-oar power packages pass through positive rotating motor and the reversion motor positive paddle of coaxial driving and anti-paddle, power is provided to guided missile, and positive rotating motor and reversion motor pass through battery and driven.The utility model can greatly reduce the weight of power packages, the quality of warhead can be made to increase, to have the function that improve guided missile power by substituting traditional power with coaxial double-oar power packages.The coaxial double-oar power packages of the utility model are driven by positive paddle and anti-paddle, driving power is stablized, guided missile will not be made to generate compared with big overload, so the requirement to structural strength can be loosened, light material is used to achieve the purpose that mitigate construction weight, and the cost of missile propulsive plant can be substantially reduced.
Description
Technical field
The utility model belongs to guided missile field, and in particular to a kind of coaxial double-oar 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.
Utility model content
Purpose of the utility model is to overcome the above-mentioned shortcomings and provide a kind of coaxial double-oar tail portion push type miniature missile,
Without using existing solid propellant rocket, weight can reduce, improve range.
In order to achieve the above object, the utility model includes warhead, and the front of warhead is provided with seeker, warhead
Rear portion be provided with control cabinet, control cabinet tail portion is provided with coaxial double-oar power packages, and coaxial double-oar power packages pass through battery and carry out
Driving, battery are placed in control cabinet；
Coaxial double-oar power packages include that the positive rotating motor of coaxial setting and reversion motor, positive rotating motor are connected with reversion motor
Battery, positive rotating motor and the reversion motor positive paddle of coaxial driving and anti-paddle.
Lifting lug is provided in warhead, lifting lug is welded in warhead.
Warhead and lifting lug are all made of aviation-grade duralumin, hard alumin ium alloy.
Missile wing is fixed in warhead, missile wing is fixed by screws in warhead.
It is provided with rudder on control cabinet, steering engine is provided in control cabinet, rudder connects steering engine by steering wheel, and steering engine connects battery.
Steering engine connects missile-borne computer with battery, and missile-borne computer is placed in control cabinet, and missile-borne computer is for driving rudder
The position of machine control flaps.
Positive rotating motor and reversion motor are all connected with missile-borne computer, and missile-borne computer is for controlling positive rotating motor and reversion electricity
The revolving speed of machine.
Be provided on control cabinet it is de- insert, take off and insert connection missile-borne computer, it is de- to insert for the logical of missile-borne computer and host computer
News.
It is provided with level-one paddle cover on anti-paddle, second level paddle cover is provided on positive paddle.
Battery uses lithium battery.
Compared with prior art, coaxial double-oar power packages are arranged in the tail portion of control cabinet in the utility model, and coaxial double-oar is dynamic
Power group provides power by positive rotating motor and the reversion motor positive paddle of coaxial driving and anti-paddle, to guided missile, and positive rotating motor and instead
Rotating motor passes through battery and is driven.The utility model, can be significantly by substituting traditional power with coaxial double-oar power packages
The weight for reducing power packages, can be such that the quality of warhead increases, to have the function that improve guided missile power, and coaxial double-oar
Two propeller positive and negative rotations can cancel out each other torsion, avoid unnecessary vibration.The coaxial double-oar power packages of the utility model
It is driven by positive paddle and anti-paddle, driving power is stablized, and guided missile will not be made to generate compared with big overload, so wanting to structural strength
Asking can loosen, use light material with achieve the purpose that mitigate construction weight, and can substantially reduce missile propulsive plant at
This.
Further, the explosive assembly casing of the utility model and lifting lug use aviation-grade duralumin, hard alumin ium alloy, can mitigate significantly
The weight of guided missile.
Further, the positive rotating motor of the utility model and reversion motor are controlled by missile-borne computer, Neng Goushi
When adjust positive rotating motor and invert motor revolving speed, preferably adjust missile attitude.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the utility model；
Fig. 2 is the structural schematic diagram of the utility model weight coaxial double-oar power packages；
Wherein, 1- target seeker, 2- warhead, 3- lifting lug, 4- missile wing, 5- is de- to be inserted, 6- control cabinet, 7- rudder, 8- coaxial double-oar
Power packages, 9- invert motor, the positive rotating motor of 10-, the anti-paddle of 11-, 12- level-one paddle cover, the positive paddle of 13-, 14- second level paddle cover.
Specific embodiment
The utility model is described further with reference to the accompanying drawing.
Referring to Fig. 1, the utility model includes warhead 2, and the front of warhead 2 is provided with seeker 1, after warhead 2
Portion is provided with control cabinet 6, and 6 tail portion of control cabinet is provided with coaxial double-oar power packages 8, and coaxial double-oar power packages 8 are carried out by battery
Driving, battery are placed in control cabinet 6；Lifting lug 3 is provided in warhead 2, lifting lug 3 is welded in warhead 2.It is solid in warhead 2
Surely there is missile wing 4, missile wing 4 is fixed by screws in warhead 2, and rudder 7 is provided on control cabinet 6, is provided with rudder in control cabinet 6
Machine, rudder 7 connect steering engine by steering wheel, and steering engine connects battery, and steering engine connects missile-borne computer with battery, and missile-borne computer is placed in control
In cabin 6 processed, missile-borne computer is used to drive the position of steering engine control flaps 7, and de- slotting 5 are provided on control cabinet 6, takes off and inserts 5 connection bullets
Computer is carried, takes off and inserts 5 communications for being used for missile-borne computer and host computer.
Referring to fig. 2, coaxial double-oar power packages 8 include the positive rotating motor 10 and reversion motor 9 of coaxial setting, positive rotating motor 10
Battery, positive rotating motor 10 and the positive paddle 13 of the coaxial driving of reversion motor 9 and anti-paddle 11, positive 10 He of rotating motor are connected with reversion motor 9
Reversion motor 9 is all connected with missile-borne computer, and missile-borne computer is used to control the revolving speed of positive rotating motor 10 and reversion motor 9, anti-paddle
It is provided with level-one paddle cover 12 on 11, second level paddle cover 14 is provided on positive paddle 13.
Preferably, warhead 2 and lifting lug 3 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 missile-borne computer inside control cabinet 6, is issued when needing to emit, and to missile-borne computer
Corresponding to instruct, lifting lug 3 is detached from fixed position, takes off and inserts 5 from the disengaging of host computer junction, missile-borne computer starts positive rotating motor 10
With reversion motor 9, positive rotating motor 10 and reversion motor 9 drive positive paddle 13 and anti-paddle 11 to be rotated respectively, provide institute to guided missile
The thrust needed, missile-borne computer control steering engine, and servo driving rudder 7 is swung, so as to adjust the direction of guided missile.
The reason of not having to single propeller using coaxial double-oar is because two propeller positive and negative rotations of coaxial double-oar can be with
It cancels out each other torsion, acts on the just only remaining thrust on body.Single propeller rotation can generate twisting force on body,
Have an adverse effect to missile flight.
Claims (10)
1. a kind of coaxial double-oar tail portion push type miniature missile, which is characterized in that including warhead (2), the front of warhead (2)
It is provided with seeker (1), the rear portion of warhead (2) is provided with control cabinet (6), and it is dynamic that control cabinet (6) tail portion is provided with coaxial double-oar
Power group (8), coaxial double-oar power packages (8) are driven by battery, and battery is placed in control cabinet (6)；
Coaxial double-oar power packages (8) include coaxial setting positive rotating motor (10) and reversion motor (9), positive rotating motor (10) and instead
Rotating motor (9) connects battery, positive rotating motor (10) and reversion motor (9) positive paddle (13) of coaxial driving and anti-paddle (11).
2. a kind of coaxial double-oar tail portion push type miniature missile according to claim 1, which is characterized in that warhead (2)
On be provided with lifting lug (3), lifting lug (3) is welded on warhead (2).
3. a kind of coaxial double-oar tail portion push type miniature missile according to claim 2, which is characterized in that warhead (2)
Aviation-grade duralumin, hard alumin ium alloy is all made of with lifting lug (3).
4. a kind of coaxial double-oar tail portion push type miniature missile according to claim 1, which is characterized in that warhead (2)
On be fixed with missile wing (4), missile wing (4) is fixed by screws on warhead (2).
5. a kind of coaxial double-oar tail portion push type miniature missile according to claim 1, which is characterized in that control cabinet (6)
On be provided with rudder (7), steering engine is provided in control cabinet (6), rudder (7) connects steering engine, steering engine connection missile-borne computer by steering wheel.
6. a kind of coaxial double-oar tail portion push type miniature missile according to claim 5, which is characterized in that steering engine and battery
Missile-borne computer is connected, missile-borne computer is placed in control cabinet (6), and missile-borne computer is used to drive the position of steering engine control flaps (7)
It sets.
7. a kind of coaxial double-oar tail portion push type miniature missile according to claim 1, which is characterized in that positive rotating motor
(10) and reversion motor (9) is all connected with missile-borne computer, and missile-borne computer is for controlling positive rotating motor (10) and reversion motor (9)
Revolving speed.
8. a kind of coaxial double-oar tail portion push type miniature missile according to claim 1, which is characterized in that control cabinet (6)
On be provided with de- slotting (5), take off slotting (5) and connect missile-borne computer, take off communication that slotting (5) are used for missile-borne computer and host computer.
9. a kind of coaxial double-oar tail portion push type miniature missile according to claim 1, which is characterized in that on anti-paddle (11)
It is provided with level-one paddle cover (12), is provided with second level paddle cover (14) on positive paddle (13).
10. a kind of coaxial double-oar tail portion push type miniature missile according to claim 1, which is characterized in that battery uses
Lithium battery.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920145874.4U CN209689505U (en) | 2019-01-28 | 2019-01-28 | A kind of coaxial double-oar tail portion push type miniature missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920145874.4U CN209689505U (en) | 2019-01-28 | 2019-01-28 | A kind of coaxial double-oar tail portion push type miniature missile |
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| Publication Number | Publication Date |
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| CN209689505U true CN209689505U (en) | 2019-11-26 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201920145874.4U Active CN209689505U (en) | 2019-01-28 | 2019-01-28 | A kind of coaxial double-oar tail portion push type miniature missile |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109708535A (en) * | 2019-01-28 | 2019-05-03 | 西安深瞳智控技术有限公司 | A kind of coaxial double-oar tail portion push type miniature missile |
| CN114894042A (en) * | 2022-04-29 | 2022-08-12 | 西北工业大学 | Modularized general synergetic microminiature missile based on boosting separation |
-
2019
- 2019-01-28 CN CN201920145874.4U patent/CN209689505U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109708535A (en) * | 2019-01-28 | 2019-05-03 | 西安深瞳智控技术有限公司 | A kind of coaxial double-oar tail portion push type miniature missile |
| CN114894042A (en) * | 2022-04-29 | 2022-08-12 | 西北工业大学 | Modularized general synergetic microminiature missile based on boosting separation |
| CN114894042B (en) * | 2022-04-29 | 2023-06-30 | 西北工业大学 | Modularized general type collaborative microminiature missile based on boosting separation |
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