CN108100287B - Unmanned aerial vehicle empty base emitter - Google Patents
Unmanned aerial vehicle empty base emitter Download PDFInfo
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- CN108100287B CN108100287B CN201711221602.XA CN201711221602A CN108100287B CN 108100287 B CN108100287 B CN 108100287B CN 201711221602 A CN201711221602 A CN 201711221602A CN 108100287 B CN108100287 B CN 108100287B
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- unmanned aerial
- aerial vehicle
- launching
- emitter
- launcher
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Launching or towing gear
- B64F1/06—Launching or towing gear using catapults
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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
- B64D5/00—Aircraft transported by aircraft, e.g. for release or reberthing during flight
Abstract
The invention discloses an unmanned aerial vehicle air-based launching device. The device comprises a slide rail, a transmitting bracket and a transmitter. Each launcher is provided with a plurality of launcher tubes, each launcher tube comprises an ejection device, and the ejection device comprises a single-double lug structure, a spring device and a steel cable and can be used for placing a plurality of swarm unmanned aerial vehicles. Before the transmission, place unmanned aerial vehicle in the launching tube earlier, then emit the transmitter through the transmission support. During the transmission, take out dead spring assembly's of lock steel cable, unblock spring assembly with the help of the thrust that spring assembly produced in the jettison device releases unmanned aerial vehicle launch canister when not damaging unmanned aerial vehicle structure and equipment, accomplishes unmanned aerial vehicle's transmission. Compared with the existing launching mode, the method has the advantages that the space utilization efficiency is high, a certain number of unmanned aerial vehicles can be launched simultaneously, and the time consumed by the unmanned aerial vehicle cluster in the launching process is shortened; the secondary preparation time of the emitter is short, and the working efficiency is high.
Description
Technical Field
The invention discloses an unmanned aerial vehicle air-based launcher with an ejection device in a launcher, and belongs to the field of unmanned aerial vehicle launching of aviation aircraft technology.
Background
Since the 30 s of the 20 th century, people begin to launch the airplane to the empty base, and the launching mode transports the child airplane to a mission area through the parent airplane with larger range and load, so that the cruising radius of the child airplane can be greatly increased, the limitation of a ground airport is eliminated, and the flexibility of taking off and landing of the child airplane is improved. However, aircraft space-based launching technology has not been well developed due to technical, risk, and cost limitations.
In recent years, with the development of unmanned aerial vehicle technology and the recent proposal of swarm unmanned aerial vehicle tactics, the air-based launching technology of the small unmanned aerial vehicle is more and more emphasized in the aviation field. Unmanned aerial vehicle systems have proven their value in battlefields, both conventional and special combat troops use unmanned aerial vehicle systems, providing point, route and environmental reconnaissance, target capture, damage assessment, and other innovative applications. The small unmanned aerial vehicle system can enhance or redefine the air combat force through the concept of changing game rules, various novel unmanned aerial vehicle combat forms are endless, and bee colony unmanned aerial vehicle tactics are one of the unmanned aerial vehicle combat forms. And the inherent disadvantage of the small unmanned aerial vehicle still restricts the tactics of the swarm unmanned aerial vehicle to the battlefield practicability. The small unmanned aerial vehicle is light in weight, and is fast low, and the time of flight is little a lot than large unmanned aerial vehicle with the voyage, and the radius of operation is limited, and the conflict capacity is poor before the operation, can not carry out long distance combat task, and the advantage of middle-size and small-size unmanned aerial vehicle colony of unable furthest performance is fought, and this has become the obstacle that restricts middle-size and small-size unmanned aerial vehicle innovation combat concept and combat task implementation. The most direct and effective method for solving the inherent disadvantages of the small unmanned aerial vehicle is to select a space-based launching and recycling mode. Utilize large-scale cargo airplane as aerial mother aircraft, take unmanned aerial vehicle to the mission segment territory on, then carry out quick aerial transmission, utilize unmanned aerial vehicle bee colony combat advantage, reconnoiter the striking to the sensitive region of target, the visible feelings of mother aircraft are retrieved swarm unmanned aerial vehicle after the task.
The existing unmanned aerial vehicle space-based rapid launching devices, such as patents CN205345355U, CN105109685A and CN205256690U, all use launching instruments to implement the launching process of the unmanned aerial vehicle. The main disadvantages of these methods are that only one drone can be launched at a time, the preparation time required for the secondary launch is long, and the launch efficiency is low. To the condition of big unmanned aerial vehicle simultaneous emission in batches, just need a large amount of transmitters, need occupy a large amount of spaces on the mother, required operating personnel is more simultaneously.
Disclosure of Invention
Aiming at the problems, the invention mainly solves the problem of rapid space-based launching of the unmanned aerial vehicle and provides an unmanned aerial vehicle space-based rapid launching device with a brand new structure.
The technical scheme adopted by the invention is as follows:
an unmanned aerial vehicle space based launcher, the space based launcher comprising: the device comprises a slide rail, a telescopic emitter support and emitters, wherein a plurality of emitters are mounted on the slide rail, so that one emitter can be conveniently switched with the next emitter after completing an emission task;
one end of the telescopic emitter support is arranged on the sliding rail and can slide along the sliding rail; the other end is connected with the emitter; one end of the transmitter support can rotate around the root hinge, and the alignment direction of the transmitter can be adjusted according to different transmitting angle requirements, so that the small unmanned aerial vehicle can transmit horizontally, vertically or at any angle; the launcher is a many launcher, and it includes a plurality of launchers, every place a small-size unmanned aerial vehicle who is in folding storage state in the launch canister, every set up an ejection device in the launch canister.
Preferably, the ejection device comprises a single-double lug structure, a spring device and a steel cable, one end of the spring device is connected with the ejection barrel, and the other end of the spring device is connected with the small unmanned aerial vehicle in a folded state through the single-double lug structure; the steel cable penetrates through the single-double lug structure to lock the spring device.
Preferably, the transmitter support is provided with a plurality of sets.
Preferably, the slide rail is installed and fixed on a floor in the main machine body.
Preferably, the slide rail is a double-rail slide rail structure.
Preferably, during the transmission, take out the steel cable of locking spring assembly, unblock spring assembly, the effort that produces when releasing through spring assembly sends out the launch canister with unmanned aerial vehicle, accomplishes unmanned aerial vehicle's transmission.
Preferably, when the small unmanned aerial vehicle is in a folding storage state, the small unmanned aerial vehicle keeps the direction of vertical emission stored in the main body of the small unmanned aerial vehicle.
Preferably, the emitter support is driven by a driving device to slide on the slide rail. The driving means may employ servo motors, pulleys, and the like, which are well known in the art.
The invention has the advantages that:
(1) the unmanned aerial vehicle can be simultaneously launched in batches through one set of launching equipment, and the efficiency of space-based launching is improved.
(2) The launching support can control and adjust the launching direction of the unmanned aerial vehicle, and the unmanned aerial vehicle can be launched at any angle at any time.
(3) The operation is simple, and less participators exist in the operation process;
(4) a plurality of emitters can be configured in one master machine, and other emitters can be used for continuing to emit in the preparation process after one emitter is finished, so that a large amount of time can be saved.
Drawings
Fig. 1 is a schematic diagram of the positions of the transmitters and the components thereof when the unmanned aerial vehicle air-based transmitting device horizontally transmits.
Fig. 2 is a schematic diagram of the positions of the transmitters and the components thereof when the unmanned aerial vehicle air-based transmitting device vertically transmits.
Fig. 3 is a schematic diagram of the state of the unmanned aerial vehicle space-based launcher stored in the mother aircraft in the folded storage state.
Fig. 4 is a schematic diagram of the operation of a plurality of emitters in the unmanned aerial vehicle space-based emitter device in the main body of the invention in a slide rail.
Fig. 5 is a schematic diagram of the state of the unmanned aerial vehicle air-based launcher in the launch canister before launching.
Fig. 6 is a composition structure diagram of the ejection device in the ejection barrel of the unmanned aerial vehicle air-based launching device.
Fig. 7 is a schematic diagram of the unmanned aerial vehicle space-based launching device after being released when the unmanned aerial vehicle space-based launching device executes a horizontal launching task.
Wherein, 1 is the master, 2 are the slide rail, 3 are the transmitter support, 4 are the transmitter, 5 are the launch canister, 6 are unmanned aerial vehicle under the folding storage state, 7 are unmanned aerial vehicle under the expansion state, 8 are spring assembly, 9 are single-two ears piece structure, 10 are the steel cable, 11 are drive arrangement.
Detailed Description
As shown in figure 1, a carrier-8 is taken as a mother machine 1, an unmanned aerial vehicle air-based launching device is carried in the mother machine 1, and a small folding unmanned aerial vehicle with the weight of 10kg and the voyage of 150km is transported to a task place beyond 600 km. This unmanned aerial vehicle empty base emitter, it includes: the device comprises a sliding rail 2 with a double-rail sliding rail structure, a telescopic emitter support 3 and three emitters 4, wherein the three emitters 4 are mounted on the sliding rail 2, so that one emitter 4 can be conveniently switched with the next emitter 4 after completing an emitting task; the slide rail 2 is fixedly arranged on a floor in the machine body of the mother machine 1; one end of the telescopic emitter bracket 3 is arranged on the slide rail 2 and can slide along the slide rail 2; the other end is connected with the emitter 4; one end of the emitter support 3 can rotate around the root hinge, and the alignment direction of the emitter 4 can be adjusted according to different emission angle requirements, so that the small unmanned aerial vehicle 6 can emit horizontally, vertically or at any angle; the launcher 4 comprises 10 launch barrels 5, a small unmanned aerial vehicle 6 in a folding storage state is placed in each launch barrel 5, and an ejection device is arranged in each launch barrel 5;
the ejection device comprises a single-double lug structure 9, a spring device 8 and a steel cable 10, wherein one end of the spring device 8 is connected with the ejection barrel 5, and the other end of the spring device 8 is connected with the small unmanned aerial vehicle 6 in a folded state through the single-double lug structure 9; the steel cable 10 passes through the single-double lug structure 9 to lock the spring device 8.
This emitter includes three transmitters 4, and transmitter length 760mm, wide 300mm, the launching tube degree of depth are 1100mm, and the design has 10 pieces of launching tubes 5 on the device, can launch 10 unmanned aerial vehicle 6 simultaneously. In the flying process of the mother aircraft 1, the three transmitters 4 are in a storage state and are mounted on the slide rails 2, as shown in fig. 3; upon arrival at the task site, an operator sends an instruction requesting that horizontal launch be performed. After receiving the instruction, the program controls to release the transmitter 4 to extend to the outside of the body of the main machine 1, and the transmitter support 3 adjusts the transmitter 4 to a horizontal transmitting angle according to the instruction, as shown in the state of fig. 1. Treat the transmitter 4 back of taking one's place, operating personnel assigns the transmission instruction, takes out steel cable 10, triggers spring assembly 8, releases transmitter 4 with unmanned aerial vehicle 6 in the launch canister 5, accomplishes unmanned aerial vehicle 6's transmission.
Those skilled in the art will appreciate that the invention may be practiced without these specific details. The above-described embodiments of the present invention are illustrative of the scheme and are not intended to limit the present invention, and any changes within the meaning and range equivalent to the protection range of the present invention should be considered to be included in the protection range of the present invention.
Claims (7)
1. An unmanned aerial vehicle space-based transmitting device, its characterized in that, this space-based transmitting device includes: the device comprises a sliding rail (2), a telescopic emitter support (3) and emitters (4), wherein a plurality of emitters (4) are mounted on the sliding rail (2), so that one emitter (4) can be conveniently switched with the next emitter (4) after completing an emission task;
one end of the telescopic emitter support (3) is arranged on the sliding rail (2) and can slide along the sliding rail (2); the other end is connected with the emitter (4); one end of the emitter support (3) can rotate around the root hinge, and the alignment direction of the emitter (4) can be adjusted according to different emission angle requirements, so that the small unmanned aerial vehicle (6) can emit at any angle, such as horizontal, vertical or other angles; the launcher (4) is a multi-barrel launching device and comprises a plurality of launching barrels (5), a small unmanned aerial vehicle (6) in a folding storage state is placed in each launching barrel (5), and an ejection device is arranged in each launching barrel (5);
the ejection device comprises a single-double lug plate structure (9), a spring device (8) and a steel cable (10), one end of the spring device (8) is connected with the launch barrel (5), and the other end of the spring device is connected with the small unmanned aerial vehicle (6) in a folded state through the single-double lug plate structure (9); the steel cable (10) passes through the single-double lug structure (9) to lock the spring device (8).
2. An unmanned aerial vehicle airborne launcher according to claim 1, wherein said launcher support (3) is a plurality of sets.
3. An unmanned aerial vehicle air base launcher according to claim 1, wherein the slide rail (2) is installed and fixed on the floor in the main body of the main machine (1).
4. An unmanned aerial vehicle airborne launcher according to claim 1, wherein said sliding track (2) is a double track slideway structure.
5. An unmanned aerial vehicle air base launcher according to claim 1, wherein during launching, the steel cable (10) of the locking spring device (8) is pulled out, the spring device (8) is unlocked, and the unmanned aerial vehicle is sent out of the launch canister (5) by the acting force generated when the spring device (8) is released, so that the unmanned aerial vehicle is launched.
6. An unmanned aerial vehicle airborne launcher according to claim 1, wherein the small unmanned aerial vehicle when in a folded storage state maintains the orientation of vertical launch stored within the body of the parent machine (1).
7. An unmanned aerial vehicle air-based launcher according to claim 1, wherein said launcher support (3) is driven by a driving device to slide on a sliding rail.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711221602.XA CN108100287B (en) | 2017-11-23 | 2017-11-23 | Unmanned aerial vehicle empty base emitter |
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| CN201711221602.XA CN108100287B (en) | 2017-11-23 | 2017-11-23 | Unmanned aerial vehicle empty base emitter |
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| CN108100287A CN108100287A (en) | 2018-06-01 |
| CN108100287B true CN108100287B (en) | 2020-06-26 |
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Families Citing this family (19)
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| CN109436364B (en) * | 2018-10-22 | 2021-10-15 | 南京航空航天大学 | Device and method for continuous launching of unmanned aerial vehicle |
| CN109229410A (en) * | 2018-10-23 | 2019-01-18 | 西北工业大学 | A kind of rotary unmanned plane air-launching method and device |
| CN109263996A (en) * | 2018-10-23 | 2019-01-25 | 西北工业大学 | A kind of bee colony unmanned plane aerial-launcher |
| CN109334982A (en) * | 2018-11-28 | 2019-02-15 | 贵州电网有限责任公司 | A kind of unmanned plane goes out bee device |
| CN111348191A (en) * | 2018-12-20 | 2020-06-30 | 中国航空工业集团公司西安飞机设计研究所 | Backward ejection type unmanned aerial vehicle launching method |
| CN109747828B (en) * | 2018-12-27 | 2022-05-17 | 中国航空工业集团公司西安飞机设计研究所 | Single-group wheel slide rail type unmanned aerial vehicle launching device and launching method |
| CN109747831B (en) * | 2018-12-27 | 2022-04-19 | 中国航空工业集团公司西安飞机设计研究所 | Tail sliding cable type air-based unmanned aerial vehicle launching device and launching method |
| CN109747829B (en) * | 2018-12-27 | 2022-04-19 | 中国航空工业集团公司西安飞机设计研究所 | Single-group rectangular slide rail type unmanned aerial vehicle launching device and launching method |
| CN109941422A (en) * | 2019-03-22 | 2019-06-28 | 北京理工大学 | A kind of the aerodynamic configuration structure and control method of folding wings missile-borne unmanned plane |
| CN110260718B (en) * | 2019-06-26 | 2024-02-27 | 刘峰 | Anti-unmanned aerial vehicle is with small-size general vertical emission device |
| CN110435894B (en) * | 2019-07-03 | 2022-12-27 | 江汉大学 | Aerial takeoff system for solar unmanned aerial vehicle |
| CN110562462A (en) * | 2019-10-09 | 2019-12-13 | 北京中航智科技有限公司 | Throwing type unmanned vehicles and a protection section of thick bamboo thereof |
| CN110920892A (en) * | 2019-11-29 | 2020-03-27 | 西北工业大学 | Device is scattered to whole small-size cluster unmanned aerial vehicle of puting in |
| CN112249333A (en) * | 2020-09-23 | 2021-01-22 | 北京特种机械研究所 | Microminiature aerial scattering type unmanned aerial vehicle system |
| CN112607031B (en) * | 2020-12-22 | 2022-02-22 | 西安羚控电子科技有限公司 | Modular unmanned aerial vehicle cluster aerial rapid delivery system |
| CN113200146A (en) * | 2021-05-18 | 2021-08-03 | 重庆交通大学 | Missile type folding cluster unmanned aerial vehicle control method, system, medium and unmanned aerial vehicle |
| CN113120251B (en) * | 2021-05-24 | 2023-01-31 | 中国人民解放军国防科技大学 | Air-jet unmanned aerial vehicle launching tube |
| CN113501125B (en) * | 2021-07-07 | 2023-02-28 | 广东空天科技研究院 | Blooming type openable nacelle for launching and recovering unmanned aerial vehicle in air |
| CN113501131B (en) * | 2021-07-07 | 2023-04-07 | 广东空天科技研究院 | Honeycomb type aerial unmanned aerial vehicle launching and recycling device, unmanned aerial vehicle and aerial aircraft carrier |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7147188B2 (en) * | 2004-08-26 | 2006-12-12 | The Boeing Company | Aircraft store ejector rack systems and methods |
| CN102887227A (en) * | 2012-10-31 | 2013-01-23 | 无锡同春新能源科技有限公司 | Projectile bombing unmanned aerial vehicle for killing mosquito |
| CN203727655U (en) * | 2013-11-11 | 2014-07-23 | 北京理工大学 | Flexible wing unmanned aerial vehicle launching cylinder |
| CN103693207B (en) * | 2013-12-12 | 2016-03-16 | 桂林航龙科讯电子技术有限公司 | A kind of SUAV (small unmanned aerial vehicle) ejector |
| CN205675255U (en) * | 2016-06-20 | 2016-11-09 | 杨志超 | Unmanned plane launcher |
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Application publication date: 20180601 Assignee: Beijing northern sky long hawk UAV Technology Co.,Ltd. Assignor: BEIHANG University Contract record no.: X2021990000039 Denomination of invention: An air based launcher for UAV Granted publication date: 20200626 License type: Exclusive License Record date: 20210119 |
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