CN110775277B - Unmanned aerial vehicle airborne microminiature missile throwing and separating device with synchronism - Google Patents
Unmanned aerial vehicle airborne microminiature missile throwing and separating device with synchronism Download PDFInfo
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- CN110775277B CN110775277B CN201911241383.0A CN201911241383A CN110775277B CN 110775277 B CN110775277 B CN 110775277B CN 201911241383 A CN201911241383 A CN 201911241383A CN 110775277 B CN110775277 B CN 110775277B
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- cavity
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- microminiature
- booster
- spring
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- 230000009471 action Effects 0.000 claims abstract description 7
- 238000000926 separation method Methods 0.000 claims abstract description 7
- 229910000831 Steel Inorganic materials 0.000 claims description 6
- 239000010959 steel Substances 0.000 claims description 6
- 238000000034 method Methods 0.000 abstract description 4
- 230000008569 process Effects 0.000 abstract description 4
- 230000006835 compression Effects 0.000 abstract description 2
- 238000007906 compression Methods 0.000 abstract description 2
- 230000001360 synchronised effect Effects 0.000 abstract 1
- 206010034719 Personality change Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Classifications
-
- 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 a synchronous unmanned aerial vehicle-mounted microminiature missile launching and separating device, which comprises a cross beam, a front booster, a rear booster, an upper spring, a lower spring and a microminiature missile launching front, wherein a hanging frame is connected with a hanging point structure of the microminiature missile in a hanging way, the lower ends of the front booster and the rear booster are in contact and tightly abutted with the upper surface of the microminiature missile, the upper spring is in a compression state, and the lower spring is in a stretching device; when the microminiature missile is put in, the hanging frame is separated from the hanging point structure of the microminiature missile, and the front booster and the rear booster push the microminiature missile downwards to move downwards under the rebound action of the upper spring and the lower spring; in the invention, when the missile is thrown, the cross beam is under the combined action of the upper spring and the lower spring to drive the front booster and the rear booster to synchronously boost the missile, thereby ensuring the synchronism of the front and rear throwing separating forces of the missile, avoiding the generation of head lifting or head lowering moment on the missile in the throwing separating process and improving the safety of the missile separation.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicle airborne weapons, and particularly relates to an unmanned aerial vehicle airborne microminiature missile throwing and separating device with synchronism.
Background
The unmanned aerial vehicle is thrown in the guided missile and is hit the ground target and is already becoming the main battle form of current low intensity battle. In order to avoid the problem that the unmanned aerial vehicle and the guided missile collide to generate separation unsafe due to large gesture change in the throwing separation process, the unmanned aerial vehicle generally adopts a throwing device to throw the guided missile so as to improve the relative motion relationship between the unmanned aerial vehicle and the guided missile, and the conventional throwing modes at present comprise gravity throwing, sliding rail throwing, ejection throwing and the like. The mass (less than 10 kg) and the size (less than 1 m) of the miniature missile are far less than those of the current typical unmanned aerial vehicle-mounted missile, the influence of the asynchronism of the boosting force in the throwing process on the attitude change in the separation process of the miniature missile is remarkable, the synchronism of the 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 the missile separation is caused, and the safety throwing requirement of the miniature missile is difficult to meet.
In order to solve the problems, an unmanned aerial vehicle-mounted microminiature missile throwing and separating device with synchronism is developed.
Disclosure of Invention
The invention aims to solve the problems and provide an unmanned aerial vehicle-mounted microminiature missile launching and separating device with synchronism.
The invention realizes the above purpose through the following technical scheme:
an unmanned aerial vehicle onboard microminiature missile launching and separating device with synchronism comprises:
a cross beam;
a front booster;
A rear booster;
A spring is arranged;
A lower spring;
a first cavity, a second cavity, a third cavity, a fourth cavity and a fifth cavity are arranged in the 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 mutually communicated 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 mutually 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 miniature missile is put in, the hanging frame is hung with a hanging point structure of the miniature missile, the lower end of the front booster and the lower end of the rear booster are contacted and abutted against the upper surface of the miniature missile, the upper spring is in a compressed state, and the lower spring is in a stretching device; when the microminiature missile is put in, the hanging frame is separated from the hanging point structure of the microminiature missile, and the front booster and the rear booster push the microminiature missile downwards to move downwards under the rebound action of the upper spring and the lower spring.
Preferably, the front booster and the rear booster are both steel round bars, with a diameter phi of 10mm and a length of 50mm.
Preferably, the cross beam is a steel round bar with a diameter phi 10mm and a length 200mm.
Preferably, the effective working turns of the upper spring and the lower spring are 10, the coiling ratio is 8, the diameter of the spring wire is 2mm, and the working length is 10mm.
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 unmanned aerial vehicle-mounted microminiature missile throwing and separating device with synchronism, which comprises the following components:
When the missile is thrown, the cross beam is under the combined action of the upper spring and the lower spring to drive the front booster and the rear booster to synchronously boost the missile, so that the synchronism of the front and rear throwing separating forces of the missile is ensured, the generation of head lifting or head lowering moment on the missile in the throwing separating process is avoided, and the missile separating safety is improved.
Drawings
FIG. 1 is a cross-sectional view of the present application;
FIG. 2 is a schematic view of the structure of the cavity in 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 diagram of a microminiature missile and hanging point structure in the present application;
FIG. 5 is a schematic view of a hanging point structure according to the present application;
In the figure: 1-a hanging frame; 2-front booster; 21-a first cavity; 3-a cross beam; 31-a second cavity; 4-loading a spring; 41-a third cavity; 5-a lower spring; 51-fourth cavity; 6-hanging point structure; 7-a rear booster; 71-a fifth cavity; 8-microminiature missile.
Detailed Description
The invention is further described below with reference to the accompanying drawings:
1-5, an unmanned aerial vehicle-mounted microminiature missile 8 throwing and separating device with synchronism comprises a cross beam 3, a front booster 2, a rear booster 7, an upper spring 4 and a lower spring 5;
The first cavity 21, the second cavity 31, the third cavity 41, the fourth cavity 51 and the fifth cavity 71 are arranged in the 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 parallel;
The upper spring 4 is vertically installed in the third cavity 41; the lower spring 5 is mounted in the fourth cavity 51; the cross beam 3 is arranged in the second cavity 31; the front booster 2 is installed in the first cavity 21; the rear booster 7 is installed in the fifth cavity 71; the lower end of the upper spring 4 is connected with the upper part of the cross beam 3, the upper end of the 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 hanger 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 put in, 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 contacted and abutted 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 put in, 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 downwards to move downwards under the rebound action of the upper spring 4 and the lower spring 5.
The second cavity should have enough space to ensure the beam to move up and down in it;
In some embodiments, the front booster 2 and the rear booster 7 are both steel round bars, having a diameter Φ10mm and a length 50mm.
In some embodiments, the cross beam 3 is a steel round bar, diameter Φ10mm, length 200mm.
In some embodiments, the upper spring 4 and the lower spring 5 have an effective work turn number of 10, a winding ratio of 8, a spring wire diameter of 2mm and a work length of 10mm.
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 beam 3 at the center.
Before the microminiature missile 8 is put in, the hanging point structure 6 of the microminiature missile 8 is in a locking state, at the moment, the microminiature missile 8 is 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, downward acting force is generated on the cross beam 3, and the cross beam 3 is fixedly connected with the front booster 2 and the rear booster 7, so that the lower end surfaces of the front booster 2 and the rear booster 7 are in downward pre-tightening contact with the upper surfaces of the front end and the rear end of the missile; when the missile is thrown, the hanging point structure 6 is unlocked, the connection relation between the microminiature missile 8 and the hanging frame 1 is released, the cross beam 3 moves downwards under the combined action of the resilience force of the upper spring 4 and the lower spring 5, and the front booster 2 and the rear booster 7 move downwards simultaneously due to the fact that the cross beam 3 is fixedly connected with the front booster 2 and the rear booster 7, and the front booster 2 and the rear booster 7 synchronously push the missile downwards at the front and rear equidistant positions of the center of mass of the missile, so that the synchronism of the front and rear throwing separating force of the missile is ensured, downward acting force is only ensured to the missile, moment around the center of mass of the missile is not generated, head lifting or head lowering moment generated by the missile in the throwing separating process is avoided, and the missile separating safety is improved.
The foregoing has shown and described the basic principles, principal features and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present invention, and various changes and modifications may be made without departing from the spirit and scope of the invention, which is defined in the appended claims. The scope of the invention is defined by the appended claims and their equivalents.
Claims (5)
1. An unmanned aerial vehicle onboard microminiature missile input separation device with synchronism is characterized by comprising:
a cross beam;
a front booster;
A rear booster;
A spring is arranged;
A lower spring;
a first cavity, a second cavity, a third cavity, a fourth cavity and a fifth cavity are arranged in the 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 mutually communicated 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 mutually 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 miniature missile is put in, the hanging frame is hung with a hanging point structure of the miniature missile, the lower end of the front booster and the lower end of the rear booster are contacted and abutted against the upper surface of the miniature missile, the upper spring is in a compressed state, and the lower spring is in a stretched state; when the microminiature missile is put in, the hanging frame is separated from the hanging point structure of the microminiature missile, and the front booster and the rear booster push the microminiature missile downwards to move downwards under the rebound action of the upper spring and the lower spring.
2. The unmanned aerial vehicle-mounted microminiature missile launching and separating device with synchronism according to claim 1, wherein the device is characterized in that: the front booster and the rear booster are both steel round rods, the diameter phi is 10mm, and the length is 50mm.
3. The unmanned aerial vehicle-mounted microminiature missile launching and separating device with synchronism according to claim 1, wherein the device is characterized in that: the cross beam is a steel round rod with the diameter phi of 10mm and the length of 200mm.
4. The unmanned aerial vehicle-mounted microminiature missile launching and separating device with synchronism according to claim 1, wherein the device is characterized in that: the effective working turns of the upper spring and the lower spring are 10, the coiling ratio is 8, the diameter of the spring wire is 2mm, and the working length is 10mm.
5. The unmanned aerial vehicle-mounted microminiature missile launching and separating device with synchronism according to any one of claims 1 to 4, wherein the device is characterized in that: the lower end of the upper spring and the upper end of the lower spring are 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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| Publication Number | Publication Date |
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| CN110775277A CN110775277A (en) | 2020-02-11 |
| CN110775277B true CN110775277B (en) | 2024-04-19 |
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| CN201911241383.0A Active CN110775277B (en) | 2019-12-06 | 2019-12-06 | Unmanned aerial vehicle airborne microminiature missile throwing and separating device with synchronism |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Citations (14)
| 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 |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8091460B2 (en) * | 2010-04-29 | 2012-01-10 | The United States Of America As Represented By The Secretary Of The Army | Missile secure-release mechanism having wheel lock detent |
-
2019
- 2019-12-06 CN CN201911241383.0A patent/CN110775277B/en active Active
Patent Citations (14)
| 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 |
| 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 |
|---|
| 巡飞器载重能力与装载火箭弹间匹配关系研究;李永泽;孙传杰;卢永刚;飞行力学;20131022;36(6);第570-573页 * |
| 无人机机载导弹分离轨迹的数值仿真;沈琼;余雄庆;;弹箭与制导学报;20091015(05);第99-102页 * |
| 空空导弹发射装置安全性设计浅析;李伟军;科技信息;20130525;第73-74页 * |
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