CN110775277A - Unmanned aerial vehicle airborne microminiature missile throwing separation device with synchronism - Google Patents
Unmanned aerial vehicle airborne microminiature missile throwing separation device with synchronism Download PDFInfo
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- CN110775277A CN110775277A CN201911241383.0A CN201911241383A CN110775277A CN 110775277 A CN110775277 A CN 110775277A CN 201911241383 A CN201911241383 A CN 201911241383A CN 110775277 A CN110775277 A CN 110775277A
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- 238000000926 separation method Methods 0.000 title claims abstract description 22
- 230000009471 action Effects 0.000 claims abstract description 5
- 229910000831 Steel Inorganic materials 0.000 claims description 6
- 239000010959 steel Substances 0.000 claims description 6
- 238000004804 winding Methods 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 4
- 230000008569 process Effects 0.000 abstract description 4
- 206010034719 Personality change Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses an airborne microminiature guided missile launching separation device of an unmanned aerial vehicle with synchronism, which comprises a cross beam, a front booster, a rear booster, an upper spring, a lower spring and a microminiature guided missile launching front, wherein a hanging frame is hung and connected with a hanging point structure of the microminiature guided missile, the lower end of the front booster and the lower end of the rear booster are contacted and tightly propped against the upper surface of the microminiature guided missile, the upper spring is in a compressed state, and the lower spring is in a stretching device; when the microminiature guided missile is thrown, the hanging frame is separated from the hanging point structure of the microminiature guided missile, and the front booster and the rear booster push the microminiature guided missile to move downwards under the resilience action of the upper spring and the lower spring; in the invention, when the guided missile is thrown, the cross beam is acted by the upper spring and the lower spring together to drive the front booster and the rear booster to boost the guided missile synchronously, so that the synchronism of the separation force of the front and rear throwing of the guided missile is ensured, the guided missile is prevented from generating head-up or head-down moment in the throwing and separating processes, and the safety of separation of the guided missile and the guided missile is improved.
Description
Technical Field
The invention belongs to the technical field of airborne weapons of unmanned aerial vehicles, and particularly relates to an airborne microminiature missile launching separation device of an unmanned aerial vehicle with synchronism.
Background
The unmanned aerial vehicle launching missile striking the ground target becomes the main operation form of the current low-intensity operation. In order to avoid the problem that separation is unsafe due to the fact that a guided missile is changed in a large posture in the throwing separation process and the collision between an unmanned aerial vehicle and the guided missile is caused, the unmanned aerial vehicle usually adopts a throwing device to throw the guided missile so as to improve the relative motion relation between the unmanned aerial vehicle and the guided missile, and the conventional throwing modes comprise gravity throwing, slide rail throwing, ejection throwing and the like. The mass (less than 10kg) and the size (less than 1m) of the microminiature missile are far smaller than those of the current typical unmanned aerial vehicle airborne missile, the asynchronism of boosting force in the throwing process has obvious influence on the attitude change in the separation process, the synchronism of throwing separation force is difficult to realize in the current throwing mode, the missile is easy to generate head-up or head-down moment, the potential safety hazard of machine-missile separation is caused, and the requirement for safe throwing of the microminiature missile is difficult to meet.
In order to solve the problems, an unmanned aerial vehicle airborne microminiature missile launching separation device with synchronism is developed by the inventor.
Disclosure of Invention
The invention aims to solve the problems and provide an airborne microminiature missile launching separation device with synchronism for an unmanned aerial vehicle.
The invention realizes the purpose through the following technical scheme:
an unmanned aerial vehicle machine carries microminiature guided missile and puts in separator with synchronism includes:
a cross beam;
a front booster;
a rear booster;
an upper spring;
a lower spring;
a first cavity, a second cavity, a third cavity, a fourth cavity and a fifth cavity are arranged in a hanger of the unmanned aerial vehicle, the second cavity is transversely arranged, the first cavity, the third cavity, the fourth cavity and the fifth cavity are vertically arranged, the third cavity and the fourth cavity are communicated with each other and are on the same straight line, the joint of the third cavity and the fourth cavity is positioned on the second cavity, two ends of the second cavity are respectively communicated with the first cavity and the fifth cavity, and the first cavity, the fourth cavity and the fifth cavity are arranged in parallel;
the upper spring is vertically arranged in the third cavity; the lower spring is arranged in the fourth cavity; the cross beam is arranged in the second cavity; the front booster is arranged in the first cavity; the rear booster is arranged in the fifth cavity; the lower end of the upper spring is connected with the upper part of the cross beam, the upper end of the lower spring is connected with the lower part of the cross beam, the lower end of the lower spring is connected with the hanging frame, and the two ends of the cross beam are respectively connected with the upper end of the front booster and the upper end of the rear booster;
before the micro guided missile is thrown, the hanging frame is hung and connected with a hanging point structure of the micro guided missile, the lower end of the front booster and the lower end of the rear booster are contacted and tightly propped against the upper surface of the micro guided missile, the upper spring is in a compressed state, and the lower spring is in a stretching device; when the microminiature guided missile is thrown, the hanging frame is separated from the hanging point structure of the microminiature guided missile, and the front booster and the rear booster push the microminiature guided missile to move downwards under the resilience action of the upper spring and the lower spring.
Preferably, the front booster and the rear booster are steel round rods, the diameter phi of each round rod is 10mm, and the length of each round rod is 50 mm.
Preferably, the cross beam is a steel round rod with the diameter phi of 10mm and the length of 200 mm.
Preferably, the effective working turns of the upper spring and the lower spring are 10, the winding ratio is 8, the diameter of the spring wire is 2mm, and the working length is 10 mm.
Specifically, the lower end of the upper spring and the upper end of the lower spring are both connected with the center of the cross beam.
The invention has the beneficial effects that:
the invention relates to an airborne microminiature missile launching separation device of an unmanned aerial vehicle with synchronism, which comprises the following components:
when the guided missile is thrown, the cross beam is acted by the upper spring and the lower spring to drive the front booster and the rear booster to boost the guided missile synchronously, so that the synchronism of the separation force of the guided missile in front and rear throwing is ensured, the guided missile is prevented from generating head-up or head-down moment in the throwing and separating process, and the separation safety of the guided missile is improved.
Drawings
FIG. 1 is a cross-sectional view of the present application;
FIG. 2 is a schematic structural view of a chamber according to the present application;
FIG. 3 is a schematic view of the mounting structure of the front booster, the cross beam structure, the upper spring, the lower spring, and the rear booster in the present application;
FIG. 4 is a schematic structural view of a microminiature missile and a hanging point structure in the present application;
FIG. 5 is a schematic view of a hanging point configuration of the present application;
in the figure: 1, a hanging rack; 2-front booster; 21-a first cavity; 3, a cross beam; 31-a second cavity; 4, spring mounting; 41-third cavity; 5-lower spring; 51-a fourth cavity; 6-hanging point structure; 7-rear booster; 71-fifth cavity; 8-microminiature missile.
Detailed Description
The invention will be further described with reference to the accompanying drawings in which:
as shown in fig. 1-5, an airborne microminiature missile 8 launching separation device of an unmanned aerial vehicle with synchronism comprises a cross beam 3, a front booster 2, a rear booster 7, an upper spring 4 and a lower spring 5;
a first cavity 21, a second cavity 31, a third cavity 41, a fourth cavity 51 and a fifth cavity 71 are arranged in a hanger 1 of the unmanned aerial vehicle, the second cavity 31 is transversely arranged, the first cavity 21, the third cavity 41, the fourth cavity 51 and the fifth cavity 71 are vertically arranged, the third cavity 41 and the fourth cavity 51 are mutually communicated and are on the same straight line, the joint of the third cavity 41 and the fourth cavity 51 is positioned on the second cavity 31, two ends of the second cavity 31 are respectively communicated with the first cavity 21 and the fifth cavity 71, and the first cavity 21, the fourth cavity 51 and the fifth cavity 71 are mutually arranged in parallel;
the upper spring 4 is vertically arranged in the third cavity 41; the lower spring 5 is arranged in the fourth cavity 51; the beam 3 is mounted in the second cavity 31; the front booster 2 is arranged in the first cavity 21; the rear booster 7 is arranged in the fifth cavity 71; the lower end of an upper spring 4 is connected with the upper part of the cross beam 3, the upper end of a lower spring 5 is connected with the lower part of the cross beam 3, the lower end of the lower spring 5 is connected with the hanging rack 1, and the two ends of the cross beam 3 are respectively connected with the upper end of the front booster 2 and the upper end of the rear booster 7;
before the microminiature missile 8 is thrown, the hanging frame 1 is hung with a hanging point structure 6 of the microminiature missile 8, the lower end of the front booster 2 and the lower end of the rear booster 7 are both contacted and tightly propped against the upper surface of the microminiature missile 8, the upper spring 4 is in a compressed state, and the lower spring 5 is in a stretching device; when the microminiature missile 8 is thrown, the hanging frame 1 is separated from the hanging point structure 6 of the microminiature missile 8, and the front booster 2 and the rear booster 7 push the microminiature missile 8 to move downwards under the resilience action of the upper spring 4 and the lower spring 5.
The second cavity has enough space for the beam to move up and down;
in some embodiments, the front booster 2 and the rear booster 7 are steel round rods, with a diameter of Φ 10mm and a length of 50 mm.
In some embodiments, the beam 3 is a steel round bar with a diameter of 10mm and a length of 200 mm.
In some embodiments, the upper spring 4 and the lower spring 5 have an effective number of turns of 10, a turn ratio of 8, a wire diameter of 2mm, and a working length of 10 mm.
In some embodiments, the lower end of the upper spring 4 and the upper end of the lower spring 5 are both connected to the center of the cross beam 3.
Before the microminiature missile 8 is thrown, the point hanging structure 6 of the microminiature missile 8 is in a locking state, at the moment, the microminiature missile 8 is kept in a connection state with the hanging frame 1, the upper spring 4 is in a compression state, the lower spring 5 is in a tension state, and downward acting force is generated on the cross beam 3, and because the cross beam 3 is fixedly connected with the front booster 2 and the rear booster 7, the lower end surfaces of the front booster 2 and the rear booster 7 are kept in downward pre-tightening contact with the upper surfaces of the front end and the rear end of the missile; when the guided missile is thrown, the hanging point structure 6 is unlocked, the connection relation between the microminiature guided missile 8 and the hanging frame 1 is released, the cross beam 3 moves downwards under the combined action of the resilience forces of the upper spring 4 and the lower spring 5, the front booster 2 and the rear booster 7 move downwards simultaneously due to the fixed connection of the cross beam 3, the front booster 2 and the rear booster 7 synchronously push the guided missile to move downwards at the positions which are equidistant from the front and the rear of the center of mass of the guided missile, the synchronism of the separating force of the front and the rear thrown guided missile is ensured, the downward acting force is ensured to be generated only on the guided missile without generating the moment around the center of mass of the guided missile, the condition that the guided missile generates head-lifting or head-lowering moment in the throwing and separating process is avoided, and the separation safety of the.
The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (5)
1. The utility model provides an unmanned aerial vehicle machine carries microminiature guided missile and puts in separator with synchronism which characterized in that includes:
a cross beam;
a front booster;
a rear booster;
an upper spring;
a lower spring;
a first cavity, a second cavity, a third cavity, a fourth cavity and a fifth cavity are arranged in a hanger of the unmanned aerial vehicle, the second cavity is transversely arranged, the first cavity, the third cavity, the fourth cavity and the fifth cavity are vertically arranged, the third cavity and the fourth cavity are communicated with each other and are on the same straight line, the joint of the third cavity and the fourth cavity is positioned on the second cavity, two ends of the second cavity are respectively communicated with the first cavity and the fifth cavity, and the first cavity, the fourth cavity and the fifth cavity are arranged in parallel;
the upper spring is vertically arranged in the third cavity; the lower spring is arranged in the fourth cavity; the cross beam is arranged in the second cavity; the front booster is arranged in the first cavity; the rear booster is arranged in the fifth cavity; the lower end of the upper spring is connected with the upper part of the cross beam, the upper end of the lower spring is connected with the lower part of the cross beam, the lower end of the lower spring is connected with the hanging frame, and the two ends of the cross beam are respectively connected with the upper end of the front booster and the upper end of the rear booster;
before the micro guided missile is thrown, the hanging frame is hung and connected with a hanging point structure of the micro guided missile, the lower end of the front booster and the lower end of the rear booster are contacted and tightly propped against the upper surface of the micro guided missile, the upper spring is in a compressed state, and the lower spring is in a stretching device; when the microminiature guided missile is thrown, the hanging frame is separated from the hanging point structure of the microminiature guided missile, and the front booster and the rear booster push the microminiature guided missile to move downwards under the resilience action of the upper spring and the lower spring.
2. The unmanned aerial vehicle airborne microminiature missile launching separation device with synchronism as claimed in claim 1, wherein: the front booster and the rear booster are steel round rods, the diameter phi is 10mm, and the length is 50 mm.
3. The unmanned aerial vehicle airborne microminiature missile launching separation device with synchronism as claimed in claim 1, wherein: the beam is a steel round bar with the diameter phi of 10mm and the length of 200 mm.
4. The unmanned aerial vehicle airborne microminiature missile launching separation device with synchronism as claimed in claim 1, wherein: the effective working turns of the upper spring and the lower spring are 10, the winding ratio is 8, the diameter of the spring wire is 2mm, and the working length is 10 mm.
5. The unmanned aerial vehicle airborne microminiature missile launch separation device with synchronism as recited in any one of claims 1 to 4, wherein: the lower end of the upper spring and the upper end of the lower spring are both connected with the center of the cross beam.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911241383.0A CN110775277B (en) | 2019-12-06 | 2019-12-06 | Unmanned aerial vehicle airborne microminiature missile throwing and separating device with synchronism |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911241383.0A CN110775277B (en) | 2019-12-06 | 2019-12-06 | Unmanned aerial vehicle airborne microminiature missile throwing and separating device with synchronism |
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| CN110775277A true CN110775277A (en) | 2020-02-11 |
| CN110775277B CN110775277B (en) | 2024-04-19 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112432555A (en) * | 2020-11-11 | 2021-03-02 | 河南北方红阳机电有限公司 | Ground throwing device for simulating airborne projectile launching |
| CN112520031A (en) * | 2020-12-17 | 2021-03-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Aircraft object throwing separation device |
Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB394018A (en) * | 1930-05-30 | 1931-08-13 | Blackburn Aeroplane & Motor Co | Improvements in means for carrying and releasing torpedoes or other elongated bodies from aircraft |
| US3840201A (en) * | 1972-06-09 | 1974-10-08 | Alkan R & Cie | Device for steadying loads suspended from aircrafts |
| DE3622173A1 (en) * | 1986-07-02 | 1988-01-14 | Messerschmitt Boelkow Blohm | Load locking mechanism for helicopters |
| US4750404A (en) * | 1987-04-06 | 1988-06-14 | Varo, Inc. | Aircraft missile launcher snubber apparatus |
| EP0759532A2 (en) * | 1995-08-19 | 1997-02-26 | Bodenseewerk Gerätetechnik GmbH | Device for receiving and holding missiles in a launching device |
| EP0908696A1 (en) * | 1997-09-16 | 1999-04-14 | AEROSPATIALE Société Nationale Industrielle | Automatic control device of at least a mobile element such as a ventral fin of a missile |
| EP2312256A2 (en) * | 2009-10-14 | 2011-04-20 | Diehl BGT Defence GmbH & Co.KG | Missile launching device |
| US20110265637A1 (en) * | 2010-04-29 | 2011-11-03 | United States Of America As Represented By The Secretary Of The Army | Missile Secure-Release Mechanism Having Wheel Lock Detent |
| JP3187212U (en) * | 2013-09-04 | 2013-11-14 | 昌弘 小山田 | Aircraft disaster prevention launcher and aircraft |
| CN105115357A (en) * | 2015-09-08 | 2015-12-02 | 中国工程物理研究院总体工程研究所 | Portable multi-functional pneumatic emitter |
| WO2016070930A1 (en) * | 2014-11-07 | 2016-05-12 | Kongsberg Defence & Aerospace As | Method and system for protecting folding wings on a missile while in their stowed state |
| CN105865743A (en) * | 2016-06-24 | 2016-08-17 | 中国航天空气动力技术研究院 | High-speed wind tunnel ejection throwing testing mechanism |
| KR101701975B1 (en) * | 2016-04-08 | 2017-02-13 | 유효선 | Vertical free falling apparatus for dropping objects airdrop |
| EP3412903A1 (en) * | 2017-06-06 | 2018-12-12 | MBDA UK Limited | Air intake cover |
| CN210942266U (en) * | 2019-12-06 | 2020-07-07 | 中国工程物理研究院总体工程研究所 | Unmanned aerial vehicle airborne microminiature missile throwing separation device with synchronism |
-
2019
- 2019-12-06 CN CN201911241383.0A patent/CN110775277B/en active Active
Patent Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB394018A (en) * | 1930-05-30 | 1931-08-13 | Blackburn Aeroplane & Motor Co | Improvements in means for carrying and releasing torpedoes or other elongated bodies from aircraft |
| US3840201A (en) * | 1972-06-09 | 1974-10-08 | Alkan R & Cie | Device for steadying loads suspended from aircrafts |
| DE3622173A1 (en) * | 1986-07-02 | 1988-01-14 | Messerschmitt Boelkow Blohm | Load locking mechanism for helicopters |
| US4750404A (en) * | 1987-04-06 | 1988-06-14 | Varo, Inc. | Aircraft missile launcher snubber apparatus |
| EP0759532A2 (en) * | 1995-08-19 | 1997-02-26 | Bodenseewerk Gerätetechnik GmbH | Device for receiving and holding missiles in a launching device |
| EP0908696A1 (en) * | 1997-09-16 | 1999-04-14 | AEROSPATIALE Société Nationale Industrielle | Automatic control device of at least a mobile element such as a ventral fin of a missile |
| EP2312256A2 (en) * | 2009-10-14 | 2011-04-20 | Diehl BGT Defence GmbH & Co.KG | Missile launching device |
| US20110265637A1 (en) * | 2010-04-29 | 2011-11-03 | United States Of America As Represented By The Secretary Of The Army | Missile Secure-Release Mechanism Having Wheel Lock Detent |
| JP3187212U (en) * | 2013-09-04 | 2013-11-14 | 昌弘 小山田 | Aircraft disaster prevention launcher and aircraft |
| WO2016070930A1 (en) * | 2014-11-07 | 2016-05-12 | Kongsberg Defence & Aerospace As | Method and system for protecting folding wings on a missile while in their stowed state |
| CN105115357A (en) * | 2015-09-08 | 2015-12-02 | 中国工程物理研究院总体工程研究所 | Portable multi-functional pneumatic emitter |
| KR101701975B1 (en) * | 2016-04-08 | 2017-02-13 | 유효선 | Vertical free falling apparatus for dropping objects airdrop |
| CN105865743A (en) * | 2016-06-24 | 2016-08-17 | 中国航天空气动力技术研究院 | High-speed wind tunnel ejection throwing testing mechanism |
| EP3412903A1 (en) * | 2017-06-06 | 2018-12-12 | MBDA UK Limited | Air intake cover |
| CN210942266U (en) * | 2019-12-06 | 2020-07-07 | 中国工程物理研究院总体工程研究所 | Unmanned aerial vehicle airborne microminiature missile throwing separation device with synchronism |
Non-Patent Citations (3)
| Title |
|---|
| 李伟军: "空空导弹发射装置安全性设计浅析", 科技信息, 25 May 2013 (2013-05-25), pages 73 - 74 * |
| 李永泽;孙传杰;卢永刚: "巡飞器载重能力与装载火箭弹间匹配关系研究", 飞行力学, vol. 36, no. 6, 22 October 2013 (2013-10-22), pages 570 - 573 * |
| 沈琼;余雄庆;: "无人机机载导弹分离轨迹的数值仿真", 弹箭与制导学报, no. 05, 15 October 2009 (2009-10-15), pages 99 - 102 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112432555A (en) * | 2020-11-11 | 2021-03-02 | 河南北方红阳机电有限公司 | Ground throwing device for simulating airborne projectile launching |
| CN112432555B (en) * | 2020-11-11 | 2023-10-13 | 河南北方红阳机电有限公司 | Ground throwing device for simulating airborne projectile launching |
| CN112520031A (en) * | 2020-12-17 | 2021-03-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Aircraft object throwing separation device |
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