CN112361880A - Bullet launching device with adjustable horizontal angle - Google Patents
Bullet launching device with adjustable horizontal angle Download PDFInfo
- Publication number
- CN112361880A CN112361880A CN202011226770.XA CN202011226770A CN112361880A CN 112361880 A CN112361880 A CN 112361880A CN 202011226770 A CN202011226770 A CN 202011226770A CN 112361880 A CN112361880 A CN 112361880A
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- China
- Prior art keywords
- slide rail
- arc
- launching
- rail
- straight
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F7/00—Launching-apparatus for projecting missiles or projectiles otherwise than from barrels, e.g. using spigots
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention provides a horizontal angle adjustable bullet shooting device, comprising: a movable slide rail (2) and a launching slide rail (3); the movable slide rail (2) comprises: a straight slide rail (4) and an arc slide rail (5); the bullet (1) is arranged on the launching slide rail (3); the straight sliding rail (4) and the arc sliding rail (5) can be folded, and when the straight sliding rail (4) and the arc sliding rail (5) are opened, a fan shape is formed; the launching slide rail (3) is arranged above the movable slide rail (2), the starting end of the launching slide rail (3) can be rotationally fixed on the aircraft body, the launching end of the launching slide rail (3) is arranged on the arc slide rail (5) and rotates along the arc slide rail (5), and an adjustable angle is provided for the launching of the bullet (1). By adopting the invention, the aircraft can capture the black flying target quickly only by finely adjusting the attitude and quickly adjusting the horizontal launching angle, and the target is not lost due to self maneuverability, thereby greatly improving the capturing performance.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to a bullet launching device with an adjustable horizontal angle.
Background
With the gradual maturity of unmanned aerial vehicle technology, various small-size commercial, civilian unmanned aerial vehicles appear in succession, and they are flying speed is fast, flexibly.
If adopt anti-unmanned aerial vehicle to carry out the net catch, because unmanned aerial vehicle compares anti-unmanned aerial vehicle size little, flexible for unmanned aerial vehicle avoids through quick motor-driven very easily, and this is just greatly reduced unmanned aerial vehicle's whole probability of catching.
An agile tracking device is needed to be designed, target can be quickly aimed and tracked, and a net capture device can be used for quick capture.
Disclosure of Invention
The purpose of the invention is as follows: the invention provides a bullet launching device with an adjustable horizontal angle, which solves the problem of low overall capture probability of the existing unmanned aerial vehicle.
The technical scheme of the invention is as follows:
the invention provides a bullet launching device with an adjustable horizontal angle, which is arranged on the upper surface of an aircraft body and is used for launching a bullet 1; the device comprises: a movable slide rail 2 and a launching slide rail 3; the movable slide rail 2 includes: a straight slide rail 4 and a circular arc slide rail 5; the bullet 1 is arranged on the launching slide rail 3;
the straight slide rail 4 and the arc slide rail 5 can be arranged on the upper surface of the aircraft body in a folding manner, and when the straight slide rail 4 and the arc slide rail 5 are opened, a fan shape is formed;
the launching slide rail 3 is arranged above the movable slide rail 2, the starting end of the launching slide rail 3 can be rotationally fixed on the aircraft body, the launching end of the launching slide rail 3 is arranged on the arc slide rail 5 and rotates along the arc slide rail 5, and an adjustable angle is provided for launching the bullet 1.
Optionally, the number of the straight slide rails 4 and the number of the arc slide rails 5 are both two;
the head ends of the two arc slide rails 5 are rotationally fixed on the upper surface of the aircraft body, and after the tail ends of the two arc slide rails 5 are respectively opened along the two sides of the aircraft body of the aircraft towards the course direction, the opened two arc slide rails 5 form an arc shape;
one end of each of the two straight slide rails 4 can be rotatably fixed on the aircraft body, and the other end of each of the two straight slide rails 4 is arranged on the two arc slide rails 5;
the length of the straight slide rail 4 is determined according to the radius of the arc slide rail 5.
Optionally, the ends of the two arc slide rails 5 are respectively provided with a locking device for locking the straight slide rail 4 and the arc slide rail 5.
Optionally, the locking device comprises an electromagnetic locking mechanism 8;
the electromagnetic locking mechanism 8 is connected with a controller on the aircraft through a lead laid at the bottom of the arc slide rail 5, and the controller is used for sending an opening/closing instruction to the electromagnetic locking mechanism 8.
Optionally, the electromagnetic locking mechanism 8 includes a relay and a magnet;
and when the relay receives an opening/closing instruction, the magnet is controlled to release/adsorb the straight slide rail 4.
Optionally, the head ends of the two arc slide rails 5 rotate around a rotating shaft arranged in a front fixing hole 6 in the front of the aircraft body of the aircraft;
the two arc slide rails 5 are positioned in the same plane.
Optionally, the launching slide rail 3 and the two arc slide rails 5 both rotate around a rotating shaft arranged in a rear fixing hole 7 at the rear part of the aircraft body.
Alternatively, when the straight slide rail 4 and the arc slide rail 5 are folded at the upper part of the machine body,
the emission slide rail 3, the straight slide rail 4 and the arc slide rail 5 are sequentially arranged from top to bottom.
The invention has the advantages that:
the invention provides a bullet launching device with an adjustable horizontal angle, which is arranged on the upper surface of an aircraft body and is used for launching a bullet 1; the device comprises: a movable slide rail 2 and a launching slide rail 3; the movable slide rail 2 includes: a straight slide rail 4 and a circular arc slide rail 5; the bullet 1 is arranged on the launching slide rail 3; the straight slide rail 4 and the arc slide rail 5 can be arranged on the upper surface of the aircraft body in a folding manner, and form a fan shape when the straight slide rail 4 and the arc slide rail 5 are opened; the launching slide rail 3 is arranged above the movable slide rail 2, the starting end of the launching slide rail 3 can be rotationally fixed on the aircraft body, the launching end of the launching slide rail 3 is arranged on the arc slide rail 5 and rotates along the arc slide rail 5, and an adjustable angle is provided for the launching of the bullet 1. By adopting the invention, the aircraft can capture the black flying target quickly only by finely adjusting the attitude and quickly adjusting the horizontal launching angle, and the target is not lost due to self maneuverability, thereby greatly improving the capturing performance.
Drawings
Fig. 1 is a top view of a horizontally angularly adjustable bullet-firing device provided by the present invention;
figure 2 is a side view of the horizontally angularly adjustable bullet-firing device provided by the present invention;
fig. 3 is a front view of the horizontally angularly adjustable bullet-shooting device provided in the present invention;
figure 4 is a first top view of the horizontally angularly adjustable bullet-launching device of the present invention in an open position;
FIG. 5 is a second top view of the bullet-launching device of the present invention in an open position;
description of reference numerals:
1-a bullet; 2, moving the sliding rail; 3-launching the sliding rail;
4-a straight slide rail; 5-arc slide rail; 6-front fixing hole;
7-rear fixing hole; 8-electromagnetic locking mechanism.
Detailed Description
The present invention is described in further detail below with reference to the attached drawings.
Referring to fig. 1 to 5, the horizontally angularly adjustable bullet-shooting device of the present invention is provided on the upper surface of the body of an aircraft for loading bullets 1.
The device mainly comprises a launching slide rail 3 and a movable slide rail. The bullet shooting device comprises a shooting slide rail 3, a bullet 1, a movable slide rail 2, an arc slide rail 5 and a straight slide rail 4, wherein the shooting slide rail 3 is installed on the back of the aircraft, the bullet 1 is installed at the tail of the shooting slide rail 3, the movable slide rail 2 is installed on the lower portion of the shooting slide rail 3 in parallel, the arc slide rail 5 and the straight slide rail 4 can be folded or rotate along a fixing hole position 67, the arc slide rail 5 is used for providing shooting angle selection for the bullet 1, and the straight. The shooting slide rail 3 can slide along the arc slide rail 5 to adjust the shooting angle of the bullet 1.
The circular arc slide rail 5 is divided into a front section of rail and a rear section of rail, the front rail is used for the launching slide rail 3 to slide and adjust the launching angle, and the rear rail is used for the straight slide rail 4 to slide to the tail end of the circular arc slide rail 5. The front and rear tracks are divided simultaneously to ensure that the arc slide rail 5, the straight slide rail 4 and the launching slide rail 3 do not interfere with each other when being folded.
When the horizontal angle-adjustable bullet launching device is used, after the aircraft takes off from the ground, the bullet launching device flies to a target area through manual guidance, a black flying unmanned aerial vehicle is detected, and positioning is carried out through interference and binocular vision. After the interference is effective, the flying attitude of the aircraft is kept unchanged or finely adjusted, the two sections of arc slide rails 5 simultaneously rotate to the maximum angle along the heading, and the straight slide rail 4 slides to the extreme end of the slide rail along the arc slide rails 5 and is fixed by the electromagnetic locking mechanism 8. The launching guide rail 3 slides on the movable slide rail, the horizontal launching angle is adjusted according to the target position, and the bullet 1 is ignited on the rail and quickly flies to the target for net capture. Even if the interference is invalid, the target can be maneuvered and locked by the simple attitude adjustment of the aircraft and the horizontal movement of the launching orbit, and the target is not lost due to the fact that the aircraft does not need to carry out large turning radius adjustment. After the bullet 1 is launched, the launching slide rail 3 slides on the movable slide rail until the in-situ launched missile is parallel to the body shaft, the straight slide rail 4 slides along the arc slide rail 5 to be folded, the arc slide rail 5 rotates to be folded, and the ground of the aircraft is recovered.
Finally, it should be noted that the above examples are only illustrative of the implementation of the present invention and are not limiting. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical proposal described in the embodiments can be modified, or some technical features can be equally replaced; such modifications and substitutions do not substantially depart from the spirit and scope of the present invention, and are intended to be included within the scope of the appended claims.
Claims (8)
1. A horizontal angle adjustable bullet shooting device is characterized in that the bullet shooting device is arranged on the upper surface of a body of an aircraft and is used for shooting bullets (1); the device comprises: a movable slide rail (2) and a launching slide rail (3); the mobile slide rail (2) comprises: a straight slide rail (4) and an arc slide rail (5); the bullet (1) is arranged on the launching slide rail (3);
the straight sliding rail (4) and the arc sliding rail (5) are arranged on the upper surface of the aircraft body in a foldable mode, and when the straight sliding rail (4) and the arc sliding rail (5) are opened, a fan shape is formed;
the bullet shooting device is characterized in that the shooting slide rail (3) is arranged above the movable slide rail (2), the starting end of the shooting slide rail (3) can be rotationally fixed on the aircraft body, the shooting end of the shooting slide rail (3) is arranged on the arc slide rail (5) and rotates along the arc slide rail (5), and an adjustable angle is provided for shooting of bullets (1).
2. The device according to claim 1, characterized in that the number of said straight sliding tracks (4) and said circular arc sliding tracks (5) is two;
the head ends of the two arc slide rails (5) are rotationally fixed on the upper surface of the aircraft body, the tail ends of the two arc slide rails (5) are respectively opened towards the course direction along the two sides of the aircraft body, and the opened two arc slide rails (5) form an arc shape;
one end of each of the two straight sliding rails (4) can be rotatably fixed on the aircraft body, and the other end of each of the two straight sliding rails is arranged on the two arc sliding rails (5);
the length of the straight slide rail (4) is determined according to the radius of the arc slide rail (5).
3. The device according to claim 1, characterized in that the ends of the two circular arc slide rails (5) are respectively provided with a locking device for locking the straight slide rail (4) and the circular arc slide rails (5).
4. A device according to claim 3, characterized in that the locking device comprises an electromagnetic locking mechanism (8);
the electromagnetic locking mechanism (8) is connected with a controller on the aircraft through a lead laid at the bottom of the arc slide rail (5), and the controller is used for sending an opening/closing instruction to the electromagnetic locking mechanism (8).
5. The device according to claim 4, characterized in that the electromagnetic locking mechanism (8) comprises a relay and a magnet;
and when the relay receives an opening/closing instruction, the magnet is controlled to release/adsorb the straight sliding rail (4).
6. The device according to claim 2, characterized in that the head ends of the two circular arc slide rails (5) rotate around a rotating shaft arranged in a front fixing hole (6) at the front part of the aircraft body;
the two arc slide rails (5) are positioned in the same plane.
7. The device according to claim 2, characterized in that the launch slide (3) and the two circular arc slides (5) both rotate around a rotation axis arranged in a rear fixing hole (7) at the rear of the fuselage of the aircraft.
8. The device according to claim 7, characterized in that when the straight sliding rail (4) and the circular arc sliding rail (5) are folded on the upper part of the machine body,
the launching slide rail (3), the straight slide rail (4) and the arc slide rail (5) are sequentially arranged from top to bottom.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011226770.XA CN112361880B (en) | 2020-11-05 | 2020-11-05 | Bullet launching device with adjustable horizontal angle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011226770.XA CN112361880B (en) | 2020-11-05 | 2020-11-05 | Bullet launching device with adjustable horizontal angle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112361880A true CN112361880A (en) | 2021-02-12 |
| CN112361880B CN112361880B (en) | 2022-10-14 |
Family
ID=74509574
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011226770.XA Active CN112361880B (en) | 2020-11-05 | 2020-11-05 | Bullet launching device with adjustable horizontal angle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112361880B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH548898A (en) * | 1972-03-08 | 1974-05-15 | Egger Hermann | METHOD FOR ADJUSTING THE FELT OF A SAILBOAT JIB AND DEVICE FOR IMPLEMENTING THIS PROCESS. |
| CN106275478A (en) * | 2016-09-08 | 2017-01-04 | 四川建筑职业技术学院 | A kind of slide rail type three-axis stabilization The Cloud Terrace |
| CN106672234A (en) * | 2016-11-06 | 2017-05-17 | 合肥齐飞信息技术有限公司 | Wing adjustable type underwater unmanned aerial vehicle convenient to operate |
| CN207060407U (en) * | 2017-08-22 | 2018-03-02 | 浙江同创无人机科技有限公司 | A kind of aerial mapping three-dimensional modeling unmanned plane |
| US20190367169A1 (en) * | 2018-05-25 | 2019-12-05 | Bryan Patrick O'Leary | Unmanned flying grenade launcher |
| CN110553548A (en) * | 2019-08-30 | 2019-12-10 | 江西洪都航空工业集团有限责任公司 | anti-unmanned aerial vehicle system based on fixed wing platform |
| CN211824532U (en) * | 2020-01-19 | 2020-10-30 | 广西交通科学研究院有限公司 | Rock quality high slope remote information acquisition equipment based on unmanned aerial vehicle |
-
2020
- 2020-11-05 CN CN202011226770.XA patent/CN112361880B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH548898A (en) * | 1972-03-08 | 1974-05-15 | Egger Hermann | METHOD FOR ADJUSTING THE FELT OF A SAILBOAT JIB AND DEVICE FOR IMPLEMENTING THIS PROCESS. |
| CN106275478A (en) * | 2016-09-08 | 2017-01-04 | 四川建筑职业技术学院 | A kind of slide rail type three-axis stabilization The Cloud Terrace |
| CN106672234A (en) * | 2016-11-06 | 2017-05-17 | 合肥齐飞信息技术有限公司 | Wing adjustable type underwater unmanned aerial vehicle convenient to operate |
| CN207060407U (en) * | 2017-08-22 | 2018-03-02 | 浙江同创无人机科技有限公司 | A kind of aerial mapping three-dimensional modeling unmanned plane |
| US20190367169A1 (en) * | 2018-05-25 | 2019-12-05 | Bryan Patrick O'Leary | Unmanned flying grenade launcher |
| CN110553548A (en) * | 2019-08-30 | 2019-12-10 | 江西洪都航空工业集团有限责任公司 | anti-unmanned aerial vehicle system based on fixed wing platform |
| CN211824532U (en) * | 2020-01-19 | 2020-10-30 | 广西交通科学研究院有限公司 | Rock quality high slope remote information acquisition equipment based on unmanned aerial vehicle |
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| Publication number | Publication date |
|---|---|
| CN112361880B (en) | 2022-10-14 |
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