CN105799948A - Catapult of flywheel-type high-speed unmanned aerial vehicle - Google Patents
Catapult of flywheel-type high-speed unmanned aerial vehicle Download PDFInfo
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- CN105799948A CN105799948A CN201610156938.1A CN201610156938A CN105799948A CN 105799948 A CN105799948 A CN 105799948A CN 201610156938 A CN201610156938 A CN 201610156938A CN 105799948 A CN105799948 A CN 105799948A
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- aerial vehicle
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- coaster
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- 238000004804 winding Methods 0.000 claims abstract description 13
- 238000005183 dynamical system Methods 0.000 claims description 13
- 230000000903 blocking effect Effects 0.000 abstract 1
- 238000004146 energy storage Methods 0.000 abstract 1
- 238000000034 method Methods 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 4
- 239000007788 liquid Substances 0.000 description 4
- 230000008569 process Effects 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000035800 maturation Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
Classifications
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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—Ground or aircraft-carrier-deck installations for launching aircraft
- B64F1/06—Ground or aircraft-carrier-deck installations for launching aircraft using catapults
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/70—Launching or landing using catapults, tracks or rails
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention relates to a launcher of an unmanned aerial vehicle, in particular to a catapult of an unmanned aerial vehicle. According to the technical scheme of the catapult of the flywheel-type high-speed unmanned aerial vehicle, the unmanned aerial vehicle is arranged on a tackle and located at a launching position before being launched, a clutch in a power system is in a disconnected state, a motor drives a flywheel to rotate, and the rotating speed is set according to launching requirements; when the unmanned aerial vehicle is launched, the clutch of the power system is connected, the flywheel drives a winding wheel to rotate, a traction rope is wound into the winding wheel and drives the tackle and the unmanned aerial vehicle to move in an accelerated mode, when the tackle moves to a tackle position sensor, the clutch is controlled to be disconnected, the tackle continues to move forwards and is blocked by a blocking device, the winding wheel stops rotating, and the unmanned aerial vehicle flies out accordingly; after launching is finished, the tackle is pulled back to the initial launching position. According to the catapult of the unmanned aerial vehicle, the flywheel serves as an energy storage element and can rapidly accelerate the unmanned aerial vehicle to a large speed on a very short track, and catapult launching of the unmanned aerial vehicle with a high speed requirement is achieved.
Description
Technical field
The present invention relates to unmanned plane discharger, particularly to a kind of unmanned aerial vehicle ejector.
Background technology
In recent years, along with the development of science and technology and military technology equipment, unmanned plane all plays more and more important effect in every field, and the unmanned plane of increasing various models is developed.Wherein, emission system is proposed new requirement by some miniature high-speeds fixed-wing unmanned plane (takeoff speed is not less than 25m/s).
Owing to the miniature high-speed usual quality of fixed-wing unmanned plane is little, carries power source limited, and takeoff speed is of a relatively high, it is impossible to accelerate to obtain takeoff speed by self, therefore generally adopt the form that other auxiliary device help it to take off.The mode of taking off that current unmanned plane is conventional has: rocket assist, and gas-liquid is launched, and combustion gas is launched, and elastic force such as launches at the mode.Rocket assist is to adopt booster rocket as power, and unmanned plane flies away from discharger under the thrust of booster rocket, have that technology maturation, thrust range be big, low cost and other advantages and property safe and out of sight poor, consumable supplies and the technical guarantee shortcoming such as costly.Gas-liquid is launched and main is adopted gas-liquid pressure energy as unmanned aerial vehicle ejecting power, has property safe and out of sight good, good economy performance, the advantages such as adaptability is good, and the shortcoming such as system complex is huge, and technical difficulty greatly, is not easily transported, relatively costly.Combustion gas is launched and is referred to and directly utilize powder gases to launch unmanned plane, unmanned plane generally has higher overload-resistant requirement, and controllability is poor.It is the elastic potential energy of flexible member (such as rubber band, spring) is converted into mechanical energy as power that elastic force launches, unmanned plane is provided to take off required speed, there is simple in construction, the advantages such as mechanism is light, but it is only applicable to SUAV, and being limited to the characteristic of elastic element, adopting elastic force to launch, to there is emission rate relatively low, launching over loading non-uniform change, the problem such as acceleration distance length.Even if adopting assembly pulley to accelerate, there is again big energy and being consumed, the problem that mechanical efficiency is low.
Summary of the invention
It is an object of the invention to: be directed to the deficiencies in the prior art, it is provided that a kind of flywheel-type high-speed unmanned aerial vehicle ejector；
The technical scheme is that a kind of flywheel-type high-speed unmanned aerial vehicle ejector, it includes: supporting seat, coaster, support body, hauling rope, arrester, directive wheel, support, dynamical system and position sensor；
Supporting seat and support are for supporting frame, and making support body is that set angle tilts upward；
Coaster moves on the slideway of support body, and it is connected to high-speed unmanned aerial vehicle, and the head of coaster is provided with buffer spring；
Dynamical system provides traction power by walking around the hauling rope of directive wheel to coaster；
Position sensor and arrester are arranged on support body, when position sensor senses that coaster passes through, send stop signal to dynamical system；Arrester is for stopping the motion of coaster.Beneficial effect: 1, compared to gas liquid type launching cradle, the principle of the invention is simple, it is easy in real time, it does not have the process of inflating pressure, transmission interval is short；
2, compared to elastic force type launching cradle, the present invention has emission rate height, and acceleration distance is short, it is possible to is quickly delivered on unmanned plane by the mechanical energy of flywheel, is particularly well-suited to the transmitting of miniature high-speed unmanned plane；
3, compared to the launcher by assembly pulley speedup, intermediate transfer process of the present invention is few, and energy loss is little, and mechanical efficiency is high.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention；
Fig. 2 is the structural representation of coaster in the present invention；
Fig. 3 is the structural representation of arrester in the present invention；
Fig. 4 is the structural representation of medium power system of the present invention；
Fig. 5 is the schematic diagram that in the present invention, coaster clashes into arrester.
Detailed description of the invention
Referring to accompanying drawing, a kind of flywheel-type high-speed unmanned aerial vehicle ejector, it includes: supporting seat 1, coaster 2, support body 4, hauling rope 5, arrester 6, directive wheel 7, support 8, dynamical system 9 and position sensor 10；
Supporting seat 1 and support 8, for supporting frame 4, make support body 4 tilt upward in set angle；
Coaster 2 moves on the slideway of support body 4, and it is connected to high-speed unmanned aerial vehicle, and the head of coaster 2 is provided with buffer spring 3；
Dynamical system 9 provides traction power by walking around the hauling rope 5 of directive wheel 7 to coaster 2；
Position sensor 10 and arrester 6 are arranged on support body 4, when position sensor 10 senses that coaster 2 passes through, send stop signal to dynamical system 9；Arrester 6 is for stopping the motion of coaster 2.
Further, in such scheme, every side of coaster 2 is provided with four wheels 2-1 in rectangular layout, and upper strata wheel contacts with the slideway upper wall of support body 4, and lower floor's wheel contacts with the slideway lower wall of support body 4；The front portion of coaster 2 is provided with coaster block 2-3；The top layout of coaster 2 has the fixing device 2-2 for connecting high-speed unmanned aerial vehicle.
Arrester 6 includes: stop plate 6-3, is arranged on and stops for the bump rubber 6-2 that clash into anterior with coaster 2 on plate 6-3, and is arranged on the tripping spring 6-1 of bump rubber 6-2 both sides.
Dynamical system 9 is arranged on the bottom of support body 4, including: motor 9-1, flywheel 9-4, motor 9-1 output is transferred to the belt 9-2 of flywheel 9-4, the winding wheel 9-6 being connected by electromagnetic clutch 9-5 and flywheel 9-4, the frame 9-5 that is used for Flywheel 9-4, electromagnetic clutch 9-5, winding wheel 9-6；Winding wheel 9-6 is connected with hauling rope 5；After electromagnetic clutch 9-5 receives the stop signal of dynamical system 9, flywheel 9-4 and winding wheel 9-6 is disconnected.
The use procedure of the present invention is:
A) Display Rack open procedure is launched
Support body 4 is fixed on firm ground by supporting seat 1, support 8, and during for preventing from launching, support body 4 retreats, and can be launched by support 8 and lock.
B) preliminary procedure is launched
Coaster 2 is placed in launch initial position, is installed on by unmanned plane on coaster 2；Electromagnetic clutch 9-5 disconnects, and starts motor 9-1, motor 9-1 flywheel driven 9-4 and accelerates to rotate, can be ready to when rotating speed reaches requirement launch.
C) unmanned plane emission process
Engage electromagnetic clutch 9-5, flywheel 9-4 drives winding wheel 9-6 to rotate, hauling rope 5 is entangled to winding wheel 9-6, and walk around directive wheel 7 band pulley 2 accelerated motion in frame 4, when coaster 2 moves to frame 4 leading portion, when position sensor 10, speed has reached launch requirements, position sensor 10 produces control signal, controls electromagnetic clutch 9-5 and disconnects rapidly.Coaster 2 drives unmanned plane to move forward, and reduces speed now when coaster 2 bumps against arrester 6, and unmanned plane flies out under effect of inertia, completes primary emission.
D) slide trolley return stroke
After transmitting terminates, electromagnetic clutch 9-5 disconnects, and coaster 2 retracts transmitting position, repeats step B and prepares to launch next time.
Claims (4)
1. a flywheel-type high-speed unmanned aerial vehicle ejector, it is characterized in that, it includes: supporting seat (1), coaster (2), support body (4), hauling rope (5), arrester (6), directive wheel (7), support (8), dynamical system (9) and position sensor (10)；
Described supporting seat (1) and described support (8) are used for supporting described support body (4), make described support body (4) tilt upward in set angle；
Described coaster (2) moves on the slideway of described support body (4), and it is connected to high-speed unmanned aerial vehicle, and the head of described coaster (2) is provided with buffer spring (3)；
Described dynamical system (9) provides traction power by walking around the described hauling rope (5) of described directive wheel (7) to described coaster (2)；
Described position sensor (10) and described arrester (6) are arranged on described support body (4), when described position sensor (10) sense described coaster (2) by time, send stop signal to described dynamical system (9)；Described arrester (6) is used for stopping the motion of described coaster (2).
2. a kind of flywheel-type high-speed unmanned aerial vehicle ejector as claimed in claim 1, it is characterized in that, the both sides of described coaster (2) are separately installed with four wheels (2-1) in rectangular layout, upper strata wheel contacts with the slideway upper wall of described support body (4), and lower floor's wheel contacts with the slideway lower wall of described support body (4)；The front portion of described coaster (2) is provided with coaster block (2-3)；The top layout of described coaster (2) has the fixing device (2-2) for connecting high-speed unmanned aerial vehicle.
3. a kind of flywheel-type high-speed unmanned aerial vehicle ejector as claimed in claim 1 or 2, it is characterized in that, described arrester (6) including: stops plate (6-3), it is arranged on described obstruction plate (6-3) upper for the bump rubber (6-2) that clash into anterior with described coaster (2), and is arranged on the tripping spring (6-1) of described bump rubber (6-2) both sides.
4. a kind of flywheel-type high-speed unmanned aerial vehicle ejector as claimed in claim 1 or 2, it is characterized in that, described dynamical system (9) is arranged on the bottom of described support body (4), including: motor (9-1), flywheel (9-4), described motor (9-1) output is transferred to the belt (9-2) of flywheel (9-4), by the winding wheel (9-6) that electromagnetic clutch (9-5) is connected with described flywheel (9-4), for installing described flywheel (9-4), described electromagnetic clutch (9-5), the frame (9-5) of described winding wheel (9-6)；Described winding wheel (9-6) is connected with described hauling rope (5)；After described electromagnetic clutch (9-5) receives the stop signal of described dynamical system (9), described flywheel (9-4) is disconnected with described winding wheel (9-6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610156938.1A CN105799948A (en) | 2016-03-18 | 2016-03-18 | Catapult of flywheel-type high-speed unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610156938.1A CN105799948A (en) | 2016-03-18 | 2016-03-18 | Catapult of flywheel-type high-speed unmanned aerial vehicle |
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| CN105799948A true CN105799948A (en) | 2016-07-27 |
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| CN201610156938.1A Pending CN105799948A (en) | 2016-03-18 | 2016-03-18 | Catapult of flywheel-type high-speed unmanned aerial vehicle |
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Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428624A (en) * | 2016-08-30 | 2017-02-22 | 陕西千山航空电子有限责任公司 | Dynamic jettisoning and separation test method |
| CN106904289A (en) * | 2017-03-21 | 2017-06-30 | 张宏 | Aircraft elevation angle ejector |
| CN107089345A (en) * | 2017-04-11 | 2017-08-25 | 西安君晖航空科技有限公司 | A kind of unmanned aerial vehicle ejecting frame dolly tripping mechanism |
| CN107176310A (en) * | 2017-06-27 | 2017-09-19 | 武汉华伍航空科技有限公司 | A kind of unmanned plane launcher |
| CN107226216A (en) * | 2017-06-13 | 2017-10-03 | 司长松 | Aircraft tyre type catapult-assisted take-off technology |
| CN107600449A (en) * | 2017-09-06 | 2018-01-19 | 哈尔滨工业大学 | A kind of unmanned aerial vehicle ejecting device |
| CN107640331A (en) * | 2017-10-13 | 2018-01-30 | 国网浙江省电力公司检修分公司 | A kind of general automatic energy storage unmanned aerial vehicle ejecting device and its method of work |
| CN108082524A (en) * | 2018-01-20 | 2018-05-29 | 北京正兴弘业科技有限公司 | A kind of controllable two-stage of unmanned plane launches vehicle control syetem and catapult technique |
| CN109050961A (en) * | 2018-08-17 | 2018-12-21 | 陈霞 | A kind of multi-functional fixed-wing unmanned aerial vehicle ejector |
| CN109131924A (en) * | 2018-10-11 | 2019-01-04 | 中国船舶重工集团公司第七�三研究所 | A kind of ejector coaster brake buffer unit |
| CN109264016A (en) * | 2018-10-29 | 2019-01-25 | 河南省汇隆精密设备制造股份有限公司 | A kind of unmanned plane locking release device |
| PL422977A1 (en) * | 2017-09-26 | 2019-04-08 | Politechnika Białostocka | Kinetic launcher for unmanned aerial vehicles |
| CN109592060A (en) * | 2018-11-06 | 2019-04-09 | 江南大学 | A kind of fixed-wing unmanned plane landing system and its landing method |
| CN111196376A (en) * | 2019-12-13 | 2020-05-26 | 沈阳航空航天大学 | Collapsible independent assortment formula unmanned aerial vehicle electromagnetism catapult |
| CN112193430A (en) * | 2020-09-29 | 2021-01-08 | 浙江安防职业技术学院 | Multi-degree-of-freedom energy-saving unmanned aerial vehicle launching system |
| CN112498728A (en) * | 2020-12-09 | 2021-03-16 | 航天时代飞鸿技术有限公司 | Brushless motor driven electromagnetic catapult and method |
| CN112937898A (en) * | 2021-01-20 | 2021-06-11 | 华南理工大学 | Transmitting device based on synchronous belt |
| WO2021142970A1 (en) * | 2020-01-15 | 2021-07-22 | 南京祖航航空科技有限公司 | Quick launcher for small unmanned aerial vehicle |
| CN113815885A (en) * | 2021-10-12 | 2021-12-21 | 江西洪都航空工业股份有限公司 | Ejection launching device with propeller as power source |
| CN114435618A (en) * | 2022-03-18 | 2022-05-06 | 北京理工大学 | Aircraft traction ejection device and system and aircraft ejection control method |
| CN114537696A (en) * | 2022-03-18 | 2022-05-27 | 北京理工大学 | Aircraft engagement ejection device and system and aircraft ejection control method |
| CN109131924B (en) * | 2018-10-11 | 2024-05-24 | 中国船舶重工集团公司第七一三研究所 | Brake buffer device for ejector pulley |
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Cited By (33)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428624A (en) * | 2016-08-30 | 2017-02-22 | 陕西千山航空电子有限责任公司 | Dynamic jettisoning and separation test method |
| CN106904289A (en) * | 2017-03-21 | 2017-06-30 | 张宏 | Aircraft elevation angle ejector |
| CN107089345A (en) * | 2017-04-11 | 2017-08-25 | 西安君晖航空科技有限公司 | A kind of unmanned aerial vehicle ejecting frame dolly tripping mechanism |
| CN107089345B (en) * | 2017-04-11 | 2019-07-23 | 西安君晖航空科技有限公司 | A kind of unmanned aerial vehicle ejecting frame trolley tripping mechanism |
| CN107226216A (en) * | 2017-06-13 | 2017-10-03 | 司长松 | Aircraft tyre type catapult-assisted take-off technology |
| CN107176310B (en) * | 2017-06-27 | 2023-09-15 | 安徽国援智能科技有限公司 | Unmanned aerial vehicle launching cradle |
| CN107176310A (en) * | 2017-06-27 | 2017-09-19 | 武汉华伍航空科技有限公司 | A kind of unmanned plane launcher |
| CN107600449A (en) * | 2017-09-06 | 2018-01-19 | 哈尔滨工业大学 | A kind of unmanned aerial vehicle ejecting device |
| PL422977A1 (en) * | 2017-09-26 | 2019-04-08 | Politechnika Białostocka | Kinetic launcher for unmanned aerial vehicles |
| CN107640331A (en) * | 2017-10-13 | 2018-01-30 | 国网浙江省电力公司检修分公司 | A kind of general automatic energy storage unmanned aerial vehicle ejecting device and its method of work |
| CN107640331B (en) * | 2017-10-13 | 2024-05-03 | 国网浙江省电力公司检修分公司 | Universal automatic energy storage unmanned aerial vehicle ejection device and working method thereof |
| CN108082524A (en) * | 2018-01-20 | 2018-05-29 | 北京正兴弘业科技有限公司 | A kind of controllable two-stage of unmanned plane launches vehicle control syetem and catapult technique |
| CN108082524B (en) * | 2018-01-20 | 2023-10-10 | 沈观清 | Unmanned plane controllable two-stage ejection vehicle-mounted control system and ejection method |
| CN109050961A (en) * | 2018-08-17 | 2018-12-21 | 陈霞 | A kind of multi-functional fixed-wing unmanned aerial vehicle ejector |
| CN109050961B (en) * | 2018-08-17 | 2021-07-16 | 山东航拍网络科技有限公司 | Multifunctional fixed-wing unmanned aerial vehicle ejector |
| CN109131924B (en) * | 2018-10-11 | 2024-05-24 | 中国船舶重工集团公司第七一三研究所 | Brake buffer device for ejector pulley |
| CN109131924A (en) * | 2018-10-11 | 2019-01-04 | 中国船舶重工集团公司第七�三研究所 | A kind of ejector coaster brake buffer unit |
| CN109264016B (en) * | 2018-10-29 | 2024-05-14 | 河南省汇隆精密设备制造股份有限公司 | Unmanned aerial vehicle locking release |
| CN109264016A (en) * | 2018-10-29 | 2019-01-25 | 河南省汇隆精密设备制造股份有限公司 | A kind of unmanned plane locking release device |
| CN109592060B (en) * | 2018-11-06 | 2023-04-18 | 江南大学 | Fixed-wing unmanned aerial vehicle take-off and landing system and take-off and landing method thereof |
| CN109592060A (en) * | 2018-11-06 | 2019-04-09 | 江南大学 | A kind of fixed-wing unmanned plane landing system and its landing method |
| CN111196376A (en) * | 2019-12-13 | 2020-05-26 | 沈阳航空航天大学 | Collapsible independent assortment formula unmanned aerial vehicle electromagnetism catapult |
| WO2021142970A1 (en) * | 2020-01-15 | 2021-07-22 | 南京祖航航空科技有限公司 | Quick launcher for small unmanned aerial vehicle |
| CN112193430A (en) * | 2020-09-29 | 2021-01-08 | 浙江安防职业技术学院 | Multi-degree-of-freedom energy-saving unmanned aerial vehicle launching system |
| CN112193430B (en) * | 2020-09-29 | 2022-06-03 | 浙江安防职业技术学院 | Multi-degree-of-freedom energy-saving unmanned aerial vehicle launching system |
| CN112498728A (en) * | 2020-12-09 | 2021-03-16 | 航天时代飞鸿技术有限公司 | Brushless motor driven electromagnetic catapult and method |
| CN112937898B (en) * | 2021-01-20 | 2024-04-09 | 华南理工大学 | Transmitting device based on synchronous belt |
| CN112937898A (en) * | 2021-01-20 | 2021-06-11 | 华南理工大学 | Transmitting device based on synchronous belt |
| CN113815885A (en) * | 2021-10-12 | 2021-12-21 | 江西洪都航空工业股份有限公司 | Ejection launching device with propeller as power source |
| CN114435618B (en) * | 2022-03-18 | 2024-03-05 | 北京理工大学 | Aircraft traction ejection device, system and aircraft ejection control method |
| CN114537696B (en) * | 2022-03-18 | 2024-03-08 | 北京理工大学 | Aircraft engagement ejection device, system and aircraft ejection control method |
| CN114537696A (en) * | 2022-03-18 | 2022-05-27 | 北京理工大学 | Aircraft engagement ejection device and system and aircraft ejection control method |
| CN114435618A (en) * | 2022-03-18 | 2022-05-06 | 北京理工大学 | Aircraft traction ejection device and system and aircraft ejection control method |
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