CN108482700A - A kind of pneumatic ejection system of unmanned plane - Google Patents
A kind of pneumatic ejection system of unmanned plane Download PDFInfo
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- CN108482700A CN108482700A CN201810186949.3A CN201810186949A CN108482700A CN 108482700 A CN108482700 A CN 108482700A CN 201810186949 A CN201810186949 A CN 201810186949A CN 108482700 A CN108482700 A CN 108482700A
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- 229910000831 Steel Inorganic materials 0.000 claims description 8
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- 230000005611 electricity Effects 0.000 claims description 4
- 210000004209 hair Anatomy 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000003139 buffering effect Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000011017 operating method Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
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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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
A kind of pneumatic ejection system of unmanned plane, the front end of its launching trolley being placed on launcher inclined guide rails is connected with main rope one end, the main rope other end is connected in after bypassing the pulley assembly being located at below guide rail on launcher, the movable pulley f shafts of pulley assembly are connected with the piston rod of the asymmetric aerodynamic cylinder of Pneumatic assembly, the rodless cavity of the asymmetric aerodynamic cylinder is connected with launching phase solenoid directional control valve, the solenoid directional control valve is also connected with gas bomb and throttle valve respectively, the rod chamber of asymmetric aerodynamic cylinder and deceleration, backhaul solenoid directional control valve is connected, the deceleration, backhaul solenoid directional control valve is contacted with a pressure reducing valve again, the pressure reducing valve is connected with gas bomb gas outlet, above-mentioned launching phase solenoid directional control valve, pressure reducing valve and gas bomb are connected with air compressor and motor.The present invention, which is realized, to be realized transmitting using a pneumatic linear actuator, slows down, the action of three step of backhaul, be cost saved the volume and weight of the pneumatic ejection system entirety of unmanned plane and is simplified repair.
Description
Technical field
The present invention relates to a kind of pneumatic ejection systems of unmanned plane.
Background technology
Unmanned plane is a kind of not manned vehicle controlled by radar or onboard program.Be currently used primarily in information gathering,
Monitoring, as target drone, signal transfer, strike target the effects that, unmanned plane is simple to manufacture with it, at low cost, is not afraid of sacrifice, landing
Effect of the advantages that simple in recent years gradually in civilian and military field is more and more important, and country of more than 30, U.S. etc. is all to nobody
Machine field conducts in-depth research.
The mode of taking off of unmanned plane can be divided into screw wing and play boomerang, go to sliding race formula, ejection type, rocket launching formula, hand
Throwing formula, dolly takeoff formula, aerial releasing type etc..It is relatively narrow that screw wing boomerang is served only for screw wing formula unmanned plane, application range；Hand
Throwing formula is used for small drone；Sliding race formula is used for large-scale unmanned plane；Rocket launching formula will produce sound when emitting unmanned plane
The signals such as light, concealment are bad；Vehicular and aerial releasing type are restricted to transmitter site；Ejection type good concealment, primary throwing
Enter that of high cost, catapult-launching gear is more complex, is suitable for small and medium size unmanned aerial vehicles (be less than 500kg).Pneumatic ejection is gas in ejection mode
Body has the feature of environmental protection as medium, does not have to consider leakage.So that pneumatic ejection has certain use value.The scanning hawk in the U.S. without
It is man-machine just using pneumatic ejection mode.Presently, there are deceleration device to have rubber band counter pull type, pneumatic linear actuator to do shock slow
Rush device buffer gear, by spring and buffer stopper do buffer gear in the way of etc., the hair of Patent No. 200610035764.X
The deceleration device of rubber band counter pull type is utilized in injection device, this deceleration device is suitable for subtracting for small drone trigger mechanism
Speed variator, the deceleration device of the structure limit the speed of the weight and unmanned plane of transmitting unmanned plane when taking off；Patent No.
The trigger mechanism for the impact attenuation device that pneumatic linear actuator is done is used in 201220258062.9 patent, this mechanism adds hairs
Spring is utilized in the device of Patent No. 201520134411.X and slides the buffering of buffer stopper for the weight and volume of injection device
Mechanism, the mechanism structure is complicated, equally increases the weight of overall emission device；The backhaul of another aspect pneumatic linear actuator is substantially
By individual return mechanism, individual kicker cylinder and deceleration cylinder generally are installed in the piston rod extreme position of pneumatic linear actuator, in this way
Increase the weight of whole equipment to a certain extent, also becoming for system be complicated, increases transport, Operation and maintenance
Difficulty.
Invention content
The purpose of the present invention is to provide a kind of pneumatic ejection systems of unmanned plane simple in structure, light-weight.Master of the present invention
If the pneumatic linear actuator of itself carries out deceleration and backhaul, traditional, pneumatic system is solved the problems, such as.
The present invention is achieved by the following technical solutions：
The invention mainly comprises：Emitting module, pulley assembly and Pneumatic assembly.Wherein, emitting module includes that transmitting is small again
Vehicle and launcher, launching trolley are placed on the inclined guide rail of launcher, the front end of launching trolley (towards transmitting terminal direction) with
Main rope one end is connected, which gap and bypasses across launcher track and be located at cunning below guide rail
Wheel assembly is fixed somewhere.Pulley assembly includes 5 fixed pulleys and 1 movable pulley, and wherein fixed pulley a and b is located on guide rail, is
Main rope is oriented to, and fixed pulley c, d and e form of zigzag distribution, main rope is connected in hair after bypassing last root fixed pulley e
It penetrates on frame.Secondary steel wire rope one end is fixed on the wheel shaft of fixed pulley e, which is connected in around the movable pulley f other ends
On launcher.Asymmetrical cylinder in Pneumatic assembly can be supplied to the initial velocity and acceleration of launching trolley very little by the pulley assembly
It is amplified, reaches the initial velocity and acceleration needed for unmanned plane transmitting.The asymmetric aerodynamic of movable pulley f shafts and Pneumatic assembly
The piston rod of cylinder is connected, which is double-acting cylinder, and rodless cavity is changed with launching phase electromagnetism
It is connected to valve, which can adjust whether gas enters asymmetric aerodynamic cylinder rodless cavity, which also distinguishes
It is connected with gas bomb and throttle valve, gas bomb can give the high pressure that asymmetric aerodynamic cylinder rodless cavity provides moment, the pressure to apply
It is added on piston, completing ejection for unmanned plane provides power；Throttle valve is arranged for setting up gas in asymmetric aerodynamic cylinder rodless cavity
The speed gone out to meet the requirement in different weight unmanned plane decelerating phase, while can control return hydraulic cylinder speed again.It is asymmetric
The rod chamber of pneumatic linear actuator is connected with deceleration, backhaul solenoid directional control valve, and the deceleration, backhaul solenoid directional control valve can control in gas bomb
Whether gas enters the rod chamber of asymmetric aerodynamic cylinder, and the deceleration, backhaul solenoid directional control valve are contacted with a pressure reducing valve again, this subtracts
Pressure valve can depressurize the high pressure gas in gas bomb, which is connected with gas bomb gas outlet.The gas bomb can be given
Asymmetric aerodynamic cylinder rod chamber provides the gas of certain pressure, and the asymmetric aerodynamic the cylinder piston after transmitting unmanned plane is made to slow down and return
Journey.Above-mentioned launching phase solenoid directional control valve, pressure reducing valve and gas bomb are by preventing the check valve of gas backstreaming from being compressed with air
Machine is connected, which is connected with motor.It is equipped between air compressor and check valve and sets up overflowing for system pressure
Flow valve and the unloading valve for protecting system and system No Load Start.
The present invention has the following advantages that compared with prior art：
It realizes transmitting 1. realizing using a pneumatic linear actuator, slow down, the action of three step of backhaul, greatly saving unmanned plane gas
The volume and weight of dynamic ejection system entirety, simplifies maintenance difficulty and operating procedure.
2. utilizing a kind of novel pneumatic ejection system of unmanned plane provided by the invention that can not have to consider pneumatic linear actuator itself
Limitation of the deceleration device to cylinder moving speed further decreases the entirety of pulley blocks to increase the movement velocity of pneumatic linear actuator
Volume and weight.
Description of the drawings
Fig. 1 is simplified schematic diagram of the present invention；
In figure：1. overflow valve, 2. air compressors, 3. motors, 4. unloading valves, 5. check valves, 6. throttle valves, 7. transmitting ranks
Section solenoid directional control valve, 8. gas bombs, 9. pressure reducing valves, 10. decelerations, backhaul solenoid directional control valve, 11. asymmetric aerodynamic cylinders, 12. pulleys
Component, 13. launchers, 14. launching trolleys, a, b, c, d are fixed pulley, and e, f are movable pulley.
Specific implementation mode
In the pneumatic ejection system simplified schematic diagram of unmanned plane shown in Fig. 1, it is inclined that launching trolley 14 is placed in launcher 13
On guide rail, the front end of launching trolley is connected (towards transmitting terminal direction) with main rope one end, which wears
It crosses gap between launcher track and is fixed on launcher around the pulley blocks 12 being located at below guide rail.Pulley assembly includes 5
A fixed pulley and 1 movable pulley, wherein fixed pulley a and b are located on guide rail, the distribution of fixed pulley c, d and e form of zigzag, main steel
Cord is connected somewhere after bypassing last root fixed pulley e.Secondary steel wire rope one end, the pair are fixed on the wheel shaft of fixed pulley e
Steel wire rope is connected in around the movable pulley f other ends on launcher.The shaft of movable pulley f and the asymmetric aerodynamic cylinder 11 of Pneumatic assembly
Piston rod be connected, which is double-acting cylinder, rodless cavity and launching phase electromagnetic switch
Valve 7 is connected, which is also connected with gas bomb 8 and throttle valve 6 respectively.The rod chamber of asymmetric aerodynamic cylinder
It is connected with deceleration, backhaul solenoid directional control valve 10, the deceleration, backhaul solenoid directional control valve are contacted with a pressure reducing valve 9 again, the pressure reducing valve
It is connected with gas bomb gas outlet.Above-mentioned launching phase solenoid directional control valve, pressure reducing valve and gas bomb pass through check valve 5 and air pressure
Contracting machine 2 is connected, which is connected with motor 3.Overflow valve 1 and off-load are equipped between air compressor and check valve
Valve 4.
The present invention the course of work approximately as：
Motor 3 is operated with engine-driven air compressor 2, is inflated to gas bomb 8,7 dead electricity of launching phase solenoid directional control valve, subtracts at this time
Speed, backhaul solenoid directional control valve 10 must be electric, when pressure reaches required value, 2 off-load of air compressor.When unmanned plane emits, electromagnetism
Reversal valve 7 obtains electric, 10 dead electricity of solenoid directional control valve, and the gas in gas bomb is entered asymmetric by launching phase solenoid directional control valve 7
The rodless cavity of pneumatic linear actuator 11, launching trolley 14 is static under the action of retaining mechanism, and it is fixed that the rope being connected at this time with trolley passes through
Pulley a, b, c, d, movable pulley e, it is static to be fixed on asymmetric aerodynamic cylinder on launcher, when obtaining firing order, asymmetric gas
Dynamic cylinder pushes piston cylinder to advance, then accelerates to launching trolley through pulley assembly 12, completes unmanned plane transmitting.Launching trolley adds
7 dead electricity of launching phase solenoid directional control valve when speed is completed is slowed down, backhaul solenoid directional control valve 10 is opened, the high pressure gas in gas bomb 8
The rod chamber for entering asymmetric aerodynamic cylinder 11 by pressure reducing valve 9 and deceleration, backhaul solenoid directional control valve 10, realizes asymmetric aerodynamic cylinder
Deceleration, trolley drives rope to be detached from fixed pulley a in moderating process, and trolley contacts by inertia belt running rope with fixed pulley b,
When speed is reduced to zero, the high pressure gas of rod chamber can push asymmetric aerodynamic the cylinder piston backhaul, trolley to be returned to by gravity
Emit starting point.
Claims (3)
1. a kind of pneumatic ejection system of unmanned plane, it is characterised in that：Launching trolley is placed on the inclined guide rail of launcher, and transmitting is small
The front end of vehicle is connected with steel wire rope one end, steel wire rope other end gap and around being located under guide rail across launcher track
It is fixed on launcher after the pulley assembly in face, the movable pulley f shafts of pulley assembly and the asymmetric aerodynamic cylinder of Pneumatic assembly
Piston rod is connected, which is double-acting cylinder, rodless cavity and launching phase solenoid directional control valve
It is connected, which is also connected with gas bomb and throttle valve respectively, rod chamber and deceleration, the backhaul electricity of asymmetric aerodynamic cylinder
Magnetic reversal valve is connected, and the deceleration, backhaul solenoid directional control valve are contacted with a pressure reducing valve again, the pressure reducing valve and gas bomb gas outlet phase
Even, above-mentioned launching phase solenoid directional control valve, pressure reducing valve and gas bomb are by preventing the check valve of gas backstreaming from being compressed with air
Machine is connected, which is connected with motor.
2. the pneumatic ejection system of unmanned plane according to claim 1, it is characterised in that：Air compressor and check valve it
Between be equipped with overflow valve and unloading valve.
3. the pneumatic ejection system of unmanned plane according to claim 1, it is characterised in that：Pulley assembly includes 5 fixed pulleys
With 1 movable pulley, wherein fixed pulley a and b is located on guide rail, and fixed pulley c, d and e form of zigzag distribution, main rope bypasses
It is connected on launcher after last root fixed pulley e, secondary steel wire rope one end is fixed on the wheel shaft of fixed pulley e, the pair steel wire
Rope is connected in around the movable pulley f other ends on launcher.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810186949.3A CN108482700A (en) | 2018-03-07 | 2018-03-07 | A kind of pneumatic ejection system of unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810186949.3A CN108482700A (en) | 2018-03-07 | 2018-03-07 | A kind of pneumatic ejection system of unmanned plane |
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| Publication Number | Publication Date |
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| CN108482700A true CN108482700A (en) | 2018-09-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201810186949.3A Pending CN108482700A (en) | 2018-03-07 | 2018-03-07 | A kind of pneumatic ejection system of unmanned plane |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109573087A (en) * | 2019-01-29 | 2019-04-05 | 航天神舟飞行器有限公司 | It is a kind of for emitting the wedge-shaped Pneumatic ejection device of unmanned plane |
| CN111038724A (en) * | 2019-12-27 | 2020-04-21 | 航天神舟飞行器有限公司 | Mechanism for launching unmanned aerial vehicle on airship |
| CN113815882A (en) * | 2021-11-22 | 2021-12-21 | 辽宁美托科技股份有限公司 | Ground inflation guarantee air source equipment for ground blowing, rotating and launching of unmanned aerial vehicle |
| CN114524107A (en) * | 2022-01-14 | 2022-05-24 | 成都飞机工业（集团）有限责任公司 | Unmanned aerial vehicle pneumatic ejection system and method based on rodless cylinder vacuum differential pressure |
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| CN102485596A (en) * | 2009-11-24 | 2012-06-06 | 刘华 | Aircraft catapult of aircraft carrier |
| RU2497725C1 (en) * | 2012-06-05 | 2013-11-10 | Открытое акционерное общество "Завод им. В.А. Дегтярева" | Aircraft launching catapult |
| CN203453160U (en) * | 2013-05-08 | 2014-02-26 | 燕山大学 | Pneumatic-hydraulic system of low-impact UAV ejector |
| CN105460230A (en) * | 2015-12-11 | 2016-04-06 | 陕西飞机工业（集团）有限公司 | Pneumatic catapult-assisted take-off device and method used for unmanned plane |
| CN107097968A (en) * | 2017-05-03 | 2017-08-29 | 西安伺动科技有限公司 | A kind of pneumatic unmanned plane emitter |
-
2018
- 2018-03-07 CN CN201810186949.3A patent/CN108482700A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102485596A (en) * | 2009-11-24 | 2012-06-06 | 刘华 | Aircraft catapult of aircraft carrier |
| RU2497725C1 (en) * | 2012-06-05 | 2013-11-10 | Открытое акционерное общество "Завод им. В.А. Дегтярева" | Aircraft launching catapult |
| CN203453160U (en) * | 2013-05-08 | 2014-02-26 | 燕山大学 | Pneumatic-hydraulic system of low-impact UAV ejector |
| CN105460230A (en) * | 2015-12-11 | 2016-04-06 | 陕西飞机工业（集团）有限公司 | Pneumatic catapult-assisted take-off device and method used for unmanned plane |
| CN107097968A (en) * | 2017-05-03 | 2017-08-29 | 西安伺动科技有限公司 | A kind of pneumatic unmanned plane emitter |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109573087A (en) * | 2019-01-29 | 2019-04-05 | 航天神舟飞行器有限公司 | It is a kind of for emitting the wedge-shaped Pneumatic ejection device of unmanned plane |
| CN109573087B (en) * | 2019-01-29 | 2023-09-22 | 航天神舟飞行器有限公司 | Wedge-shaped air pressure ejection device for launching unmanned aerial vehicle |
| CN111038724A (en) * | 2019-12-27 | 2020-04-21 | 航天神舟飞行器有限公司 | Mechanism for launching unmanned aerial vehicle on airship |
| CN113815882A (en) * | 2021-11-22 | 2021-12-21 | 辽宁美托科技股份有限公司 | Ground inflation guarantee air source equipment for ground blowing, rotating and launching of unmanned aerial vehicle |
| CN113815882B (en) * | 2021-11-22 | 2022-03-29 | 辽宁美托科技股份有限公司 | Ground inflation guarantee air source equipment for ground blowing, rotating and launching of unmanned aerial vehicle |
| CN114524107A (en) * | 2022-01-14 | 2022-05-24 | 成都飞机工业（集团）有限责任公司 | Unmanned aerial vehicle pneumatic ejection system and method based on rodless cylinder vacuum differential pressure |
| CN114524107B (en) * | 2022-01-14 | 2023-09-19 | 成都飞机工业（集团）有限责任公司 | Pneumatic ejection system and method for unmanned aerial vehicle based on rodless cylinder vacuum differential pressure |
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