CN105539850A - Multi-angle air launching system based on aircraft - Google Patents
Multi-angle air launching system based on aircraft Download PDFInfo
- Publication number
- CN105539850A CN105539850A CN201510953471.9A CN201510953471A CN105539850A CN 105539850 A CN105539850 A CN 105539850A CN 201510953471 A CN201510953471 A CN 201510953471A CN 105539850 A CN105539850 A CN 105539850A
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- CN
- China
- Prior art keywords
- aircraft
- transmitting body
- launch system
- piston
- cylinder
- 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.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
- B64D1/04—Dropping, ejecting, or releasing articles the articles being explosive, e.g. bombs
- B64D1/06—Bomb releasing; Bombs doors
Abstract
The invention discloses a multi-angle air launching system based on an aircraft. The multi-angle air launching system based on the aircraft comprises a launching body and the aircraft, wherein the launching body is connected with the aircraft, and the aircraft controls the rotation of the launching body; when the rotation speed of the launching body reaches to a preset speed, launching bullets arranged on the launching body are launched from a plurality of directions. According to the multi-angle air launching system disclosed by the invention, the launching body can be rotated, so that objectives are stricken from a plurality of directions, and the air strike capacity of the aircraft is strengthened.
Description
Technical field
The present invention relates to aerial-launcher, particularly relate to a kind of multi-angle Launch System based on aircraft.
Background technology
Air force is the services of mainly carrying out air fighting.The basic mission of air force undertakes Homeland air defense, supports ground force, navy fight, and enemy's rear area is implemented to air strike, carried out air transport and aerial reconnaissance.And the machine of air force equipment, mainly various aircraft (such as, autogyro, fighter plane, bomber, rotor wing unmanned aerial vehicle etc.).Air attack is carried out by described aircraft.
But, when existing aircraft carries out air attack, launch bullet (such as, guided missile) from vehicle launch time, the direction of transmitting is restricted (such as, only launching from some directions), so, limit the striking capabilities that aircraft is aerial.
Summary of the invention
Main purpose of the present invention is to provide a kind of multi-angle Launch System based on aircraft, is intended to solve user when using existing aircraft to carry out air attack, launches the technical matters that the downrange of bullet is single.
For achieving the above object, the invention provides a kind of multi-angle Launch System based on aircraft, the described multi-angle Launch System based on aircraft comprises launches body and aircraft, and described transmitting body is connected with described aircraft, wherein:
Described aircraft comprises cylinder, piston, fixed link and screw rod;
Described transmitting body comprises controller and multiple transmitting bullet;
Described cylinder is arranged at the below of described aircraft, and described piston is arranged in described cylinder;
The outside of described cylinder is also connected and fixed bar, and described fixed link is also connected with described screw rod through described piston vertically downward;
Described screw rod is threaded with described transmitting body;
Described in described flying vehicles control, the air pressure of cylinder makes described piston up-down;
Described piston is connected to promote described transmitting body with described transmitting body, and described transmitting body is rotated around described screw rod; And
When the rotative speed of described transmitting body reaches pre-set velocity, described controller controls each transmitting bullet and launches along the tangential direction of described transmitting body.
Preferably, described piston comprises piston rod, cylinder part and buckle, and wherein, described cylinder part is arranged at the end of described piston rod, described cylinder part opening down, and described buckle is arranged on the edge of opening of cylinder part.
Preferably, described piston rod is arranged in described cylinder, and described piston rod is T font structure.
Preferably, described piston is connected with described transmitting body by described buckle.
Preferably, described transmitting body is a kind of cirque structure comprising inner circle and cylindrical.
Preferably, the cylindrical of described transmitting body arranges multiple transmitting bullet.
Preferably, the inner circle of described transmitting body is helicitic texture, and the screw thread of this inner circle coordinates with described screw rod and makes described screw rod through described transmitting body.
Preferably, described transmitting body also comprises speed sensor, and described speed sensor is for monitoring the rotative speed of described transmitting body.
Preferably, described fixed link is hollow structure.
Preferably, comprise cable in described fixed link, this cable, for connecting described aircraft and controller, makes described aircraft control described controller by described cable.
Compared to prior art, multi-angle Launch System based on aircraft of the present invention have employed technique scheme, reach following technique effect: described emission coefficient rotates launches body, the multiple transmitting bullets launched on body are launched from multiple directions, achieve aircraft and carry out multi-angle air attack aloft, enhance the air attack ability of aircraft, improve fighting capacity.
Accompanying drawing explanation
Fig. 1 is the planar structure schematic diagram of the multi-angle Launch System preferred embodiment that the present invention is based on aircraft;
Fig. 2 is the planar structure schematic diagram of the preferred embodiment of piston in the multi-angle Launch System that the present invention is based on aircraft;
Fig. 3 is the planar structure schematic diagram launching the preferred embodiment of body in the multi-angle Launch System that the present invention is based on aircraft.
The realization of the object of the invention, functional characteristics and advantage will in conjunction with the embodiments, are described further with reference to accompanying drawing.
Detailed description of the invention
For further setting forth the present invention for the technological means reaching above-mentioned purpose and take and effect, below in conjunction with accompanying drawing and preferred embodiment, the specific embodiment of the present invention, structure, feature and effect thereof are described in detail.Should be appreciated that specific embodiment described in the invention only in order to explain the present invention, be not intended to limit the present invention.
As shown in Figure 1, Fig. 1 is the planar structure schematic diagram of the multi-angle Launch System preferred embodiment that the present invention is based on aircraft.In the present embodiment, the described multi-angle Launch System based on aircraft includes, but not limited to launch body 5 and aircraft 8.Described transmitting body 5 is connected with described aircraft 8.
Described aircraft 8 includes, but not limited to cylinder 1, piston 2, fixed link 3 and screw rod 4.
Described transmitting body 5 comprises multiple transmitting bullet 6 and multiple control unit 7, and wherein, corresponding one of each control unit 7 launches bullet 6 to control this transmitting bullet 6.In other embodiments, described control unit 7 also can be one, and namely a control unit 7 controls all transmitting bullets 6.
Described cylinder 1 is arranged at the below of described aircraft 8, arranges piston 2 in described cylinder 1, described piston 2 up-and-down movement in cylinder 1.
As shown in Figure 2, Fig. 2 is the planar structure schematic diagram of the preferred embodiment of piston in the multi-angle Launch System that the present invention is based on aircraft.
Described piston 2 comprises piston rod 20, cylinder part 22 and buckle 24, and described piston rod 20 is arranged in described cylinder 1, and described piston rod 20 is T font structure.Described cylinder part 22 is arranged at the end of described piston rod 20, described cylinder part 22 opening down.Described buckle 24 is arranged on the edge of opening of described cylinder part 22.
Further, as shown in Figure 1, described piston 2 is connected with described transmitting body 5, for promoting described transmitting body 5 up-and-down movement.Specifically, described piston 2 is connected with described transmitting body 5 by described buckle 24.Described transmitting body 5 blocks described buckle 24, and described piston 2 is connected with described transmitting body 5.
The outside of described cylinder 1 also connects described fixed link 3, and described fixed link 3 is also connected with described screw rod 4 through described piston 2 vertically downward.
Described screw rod 4 is threaded with described transmitting body 5, and described transmitting body 5 is rotated around described screw rod 4, thus described transmitting body 5 is moved up and down along described screw rod 4.
As shown in Figure 3, Fig. 3 is the planar structure schematic diagram launching the preferred embodiment of body in the multi-angle Launch System that the present invention is based on aircraft.
Specifically, described transmitting body 5 is a kind of cirque structure comprising inner circle and cylindrical, and the cylindrical of described transmitting body 5 arranges multiple transmitting bullet 6.Specifically, described cylindrical arranges one every default circumferential angle and launches bullet 6, and such as, described transmitting body 5 arranges one every 24 degree at described cylindrical and launches bullet, the annulus of described transmitting body 5 is arranged 15 and launches bullet.The inner circle of described transmitting body 5 is helicitic texture, and the screw thread of this inner circle coordinates with described screw rod 4 and makes described screw rod 4 through described transmitting body 5, and described transmitting body 5 can move up and down along described screw rod 4.
Further, as shown in Figure 1, the air pressure that described aircraft 8 controls described cylinder 1 makes described piston 2 up-and-down movement.Specifically, if when the gas in described cylinder 1 increases, the air pressure in described cylinder 1 increases, and described piston 2 moves downward, if when the gas in described cylinder 1 reduces, the air pressure in described cylinder 1 reduces, described piston 2 upward movement.
Described piston 2, for promoting described transmitting body 5, makes described transmitting body 5 by the mode around described screw rod 4 rotation along described screw rod 4 up-and-down movement.
Described controller 7 is for when the rotative speed of described transmitting body 5 reaches pre-set velocity, and described controller 7 controls described multiple transmitting bullet 6 and launches along the tangential direction of described transmitting body 5.Described transmitting body 5 also comprises speed sensor (not shown in figure 1), and described speed sensor is for monitoring the rotative speed of described transmitting body 5.Such as, arrange 15 in Fig. 2 and launch bullet 6, the corresponding tangential direction of each transmitting bullet 6, then launch bullet 6 simultaneously from 15 directions transmittings for 15.
In addition, described fixed link 3 is hollow structure, cable (not shown) is comprised in this fixed link 3, this cable is for connecting described aircraft 8 and controller 7, make described aircraft 8 can control described controller 7 by described cable, such as, control described controller 7 and send instruction to described transmitting bullet 6, this instruction is for controlling the transmitting of described transmitting bullet 6.
Described transmitting bullet 6 may be, but not limited to, guided missile, shell, paintball, candle bomb or other body.
Described aircraft 8 may be, but not limited to, autogyro, fighter plane, bomber, rotor wing unmanned aerial vehicle or other device that can aloft fly.
The principle of work of the described multi-angle Launch System based on aircraft is as follows:
Described aircraft 8 controls described piston 2 up-and-down movement by the gas in described cylinder 1.
Due to described piston 2 and the annexation of described transmitting body 5, described piston 2 up-and-down movement drives described transmitting body 5 up-and-down movement.
Because described transmitting body 5 is arranged on described screw rod 4, described transmitting body 5 up-and-down movement, drives described transmitting body 5 to rotate.
When the rotative speed (obtaining rotative speed by described speed sensor) of described transmitting body 5 arrives pre-set velocity, described controller 7 controls described transmitting bullet 6 and launches.In the present embodiment, because described transmitting body 5 rotates, under the effect of rotary centrifugal force, described transmitting bullet 6 is launched from the tangential direction of the cylindrical of described transmitting body 5.In other embodiments, described aircraft 8 can send instruction by described cable to described controller 7, and this instruction is for controlling the transmitting of described transmitting bullet 6.
These are only the preferred embodiments of the present invention; not thereby the scope of the claims of the present invention is limited; every utilize specification sheets of the present invention and accompanying drawing content to do equivalent structure or equivalent function conversion; or be directly or indirectly used in other relevant technical fields, be all in like manner included in scope of patent protection of the present invention.
Claims (10)
1. based on a multi-angle Launch System for aircraft, it is characterized in that, the described multi-angle Launch System based on aircraft comprises launches body and aircraft, and described transmitting body is connected with described aircraft, wherein:
Described aircraft comprises cylinder, piston, fixed link and screw rod;
Described transmitting body comprises controller and multiple transmitting bullet;
Described cylinder is arranged at the below of described aircraft, and described piston is arranged in described cylinder;
The outside of described cylinder is also connected and fixed bar, and described fixed link is also connected with described screw rod through described piston vertically downward;
Described screw rod is threaded with described transmitting body;
Described in described flying vehicles control, the air pressure of cylinder makes described piston up-down;
Described piston is connected to promote described transmitting body with described transmitting body, and described transmitting body is rotated around described screw rod; And
When the rotative speed of described transmitting body reaches pre-set velocity, described controller controls each transmitting bullet and launches along the tangential direction of described transmitting body.
2. as claimed in claim 1 based on the multi-angle Launch System of aircraft, it is characterized in that, described piston comprises piston rod, cylinder part and buckle, wherein, described cylinder part is arranged at the end of described piston rod, described cylinder part opening down, and described buckle is arranged on the edge of opening of cylinder part.
3., as claimed in claim 2 based on the multi-angle Launch System of aircraft, it is characterized in that, described piston rod is arranged in described cylinder, and described piston rod is T font structure.
4., as claimed in claim 2 based on the multi-angle Launch System of aircraft, it is characterized in that, described piston is connected with described transmitting body by described buckle.
5., as claimed in claim 1 based on the multi-angle Launch System of aircraft, it is characterized in that, described transmitting body is a kind of cirque structure comprising inner circle and cylindrical.
6., as claimed in claim 5 based on the multi-angle Launch System of aircraft, it is characterized in that, the cylindrical of described transmitting body arranges multiple transmitting bullet.
7. as claimed in claim 5 based on the multi-angle Launch System of aircraft, it is characterized in that, the inner circle of described transmitting body is helicitic texture, and the screw thread of this inner circle coordinates with described screw rod and makes described screw rod pass described transmitting body.
8. the multi-angle Launch System based on aircraft as described in any one of claim 1 to 7, is characterized in that, described transmitting body also comprises speed sensor, and described speed sensor is for monitoring the rotative speed of described transmitting body.
9., as claimed in claim 1 based on the multi-angle Launch System of aircraft, it is characterized in that, described fixed link is hollow structure.
10., as claimed in claim 9 based on the multi-angle Launch System of aircraft, it is characterized in that, comprise cable in described fixed link, this cable, for connecting described aircraft and controller, makes described aircraft control described controller by described cable.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510953471.9A CN105539850A (en) | 2015-12-18 | 2015-12-18 | Multi-angle air launching system based on aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510953471.9A CN105539850A (en) | 2015-12-18 | 2015-12-18 | Multi-angle air launching system based on aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105539850A true CN105539850A (en) | 2016-05-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510953471.9A Pending CN105539850A (en) | 2015-12-18 | 2015-12-18 | Multi-angle air launching system based on aircraft |
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| CN (1) | CN105539850A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105905286A (en) * | 2016-05-10 | 2016-08-31 | 深圳市旋翼捷科技有限公司 | Unmanned aerial vehicle with thrust line variable device |
| CN106742000A (en) * | 2017-03-13 | 2017-05-31 | 芜湖博高光电科技股份有限公司 | A kind of passive location homing device |
| CN107021224A (en) * | 2017-04-28 | 2017-08-08 | 深圳市轻准科技有限公司 | Hang down and throw howitzer unmanned plane |
-
2015
- 2015-12-18 CN CN201510953471.9A patent/CN105539850A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105905286A (en) * | 2016-05-10 | 2016-08-31 | 深圳市旋翼捷科技有限公司 | Unmanned aerial vehicle with thrust line variable device |
| CN105905286B (en) * | 2016-05-10 | 2018-02-27 | 深圳市旋翼捷科技有限公司 | Unmanned plane with thrust line variset |
| CN106742000A (en) * | 2017-03-13 | 2017-05-31 | 芜湖博高光电科技股份有限公司 | A kind of passive location homing device |
| CN107021224A (en) * | 2017-04-28 | 2017-08-08 | 深圳市轻准科技有限公司 | Hang down and throw howitzer unmanned plane |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160504 |
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| WD01 | Invention patent application deemed withdrawn after publication |