CN110422337A - A kind of packaged type unmanned plane gas-liquid power ejection system - Google Patents
A kind of packaged type unmanned plane gas-liquid power ejection system Download PDFInfo
- Publication number
- CN110422337A CN110422337A CN201910738676.3A CN201910738676A CN110422337A CN 110422337 A CN110422337 A CN 110422337A CN 201910738676 A CN201910738676 A CN 201910738676A CN 110422337 A CN110422337 A CN 110422337A
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- slide trolley
- launcher
- flat car
- unmanned plane
- trunnion
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- 239000007788 liquid Substances 0.000 title claims abstract description 25
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 8
- 238000004146 energy storage Methods 0.000 claims description 23
- 239000007789 gas Substances 0.000 claims description 13
- 230000003028 elevating effect Effects 0.000 claims description 11
- 238000007493 shaping process Methods 0.000 claims description 11
- 238000003466 welding Methods 0.000 claims description 10
- 238000010521 absorption reaction Methods 0.000 claims description 8
- 230000001133 acceleration Effects 0.000 claims description 7
- 238000009434 installation Methods 0.000 claims description 4
- 239000011261 inert gas Substances 0.000 claims description 3
- 229910000831 Steel Inorganic materials 0.000 claims 1
- 239000010959 steel Substances 0.000 claims 1
- 239000000203 mixture Substances 0.000 abstract description 3
- 230000001141 propulsive effect Effects 0.000 abstract description 3
- 238000005516 engineering process Methods 0.000 abstract description 2
- 208000032365 Electromagnetic interference Diseases 0.000 abstract 1
- 238000006243 chemical reaction Methods 0.000 abstract 1
- 239000012530 fluid Substances 0.000 description 5
- TVEXGJYMHHTVKP-UHFFFAOYSA-N 6-oxabicyclo[3.2.1]oct-3-en-7-one Chemical compound C1C2C(=O)OC1C=CC2 TVEXGJYMHHTVKP-UHFFFAOYSA-N 0.000 description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 206010010356 Congenital anomaly Diseases 0.000 description 1
- 230000003321 amplification Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
Classifications
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Platform Screen Doors And Railroad Systems (AREA)
Abstract
The present invention relates to a kind of packaged type unmanned plane gas-liquid power ejection systems, are related to unmanned plane lift-off technology field.The present invention changes the ejection mode of unmanned plane, directly increase ejection speed using the propulsive thrust of high-pressure water jet as ejection power and by pulley, there is no energy secondary conversions, energy efficiency is high, system structure composition is simple, and speed increasing ratio is big, and maneuverability is good, the problems such as there is no electromagnetic interferences can be widely applied in various fixed-wing unmanned aerial vehicle ejecting takes off.
Description
Technical field
The present invention relates to unmanned plane lift-off technology fields, and in particular to a kind of packaged type unmanned plane gas-liquid power ejection system
System.
Background technique
Ejection launch be current fixed-wing unmanned plane pass through frequently with one kind take off mode, it can show under external force
The sliding speed for improving unmanned plane is write, take-off distance is shortened.Currently, the main ejection mode of unmanned plane includes elastic force bullet
It penetrates, the gentle hydraulic catapult of electromagnetic launch.
Wherein elastic force is launched since energy storage is limited, launches power very little；Although electromagnetic launch mechanical structure is simple, automatically controlled
Device is complicated, and there is also " congenital " defects, that is, can generate strong electromagnetic interference, influence electromechanical equipment and automatically controlled
The functional reliability of system.
Gas fluid pressure ejection is the most important ejection launch mode of current fixed-wing unmanned plane, according to used executive component
Difference, and Driven by Hydraulic Cylinder and hydraulic motor two kinds of forms of driving can be divided into, they are all using accumulator as high-pressure high-flow
Power source inserts valve group by big orifice and controls high-voltage oil liquid flow direction, and the main distinction is that hydraulic actuator is selected
Hydraulic cylinder or hydraulic motor, the Gas fluid pressure ejection system of Driven by Hydraulic Cylinder are to pass through the straight-line displacement speed of hydraulic cylinder output
After the amplification of speedup pulley blocks, unmanned plane acceleration is pulled to take off by rope；The Gas fluid pressure ejection system of hydraulic motor driving passes through
Hydraulic motor output torque drives reel and belt high-speed rotation, then pulls unmanned plane acceleration to take off by rope.However, nothing
By the Gas fluid pressure catapult-launching gear for being hydraulic cylinder or hydraulic motor driving, all there is system structure is complicated, power-weight ratio is small etc.
Problem is restricted by hydraulic cylinder or hydraulic motor movement velocity, attachment device complexity etc., and promoting ejection power will cause efficiency
Very fast decline.In addition, heavy duty, extreme environment frequently using be also easy to occur " run, drip, leak, pollution " the problems such as, shadow
The working efficiency and concealment of acoustic system.
Therefore, current Gas fluid pressure ejection system cannot fully meet the ejection of the especially large and medium-sized unmanned plane of unmanned plane
Mission need, how the unmanned plane gas-liquid ejection mode of Development of Novel, to overcome, existing gas-liquid ejection structure is complicated, power limited
The disadvantages of, and avoid electromagnetic launch generate strong electromagnetic the problems such as, to improve fixed-wing unmanned plane take off ability and work
Efficiency is all of great significance.
Summary of the invention
(1) technical problems to be solved
The technical problem to be solved by the present invention is how to realize that a kind of satisfaction is capable of the ejection launch need of large and medium-sized unmanned plane
The new unmanned plane gas-liquid ejection system asked the disadvantages of to overcome complicated existing gas-liquid ejection structure, power limited, and avoids electricity
The problems such as magnetic ejection generates strong electromagnetic.
(2) technical solution
In order to solve the above-mentioned technical problems, the present invention provides a kind of packaged type unmanned plane gas-liquid power ejection system,
Trunnion 2 is turned round including flat car 1, first, A-frame 3, relieving mechanism 4, the first slide trolley 5, second revolution trunnion 6, is lifted
Oil-lifting jar 7, third turn round trunnion 8, the first leading block 9, fixed pulley 10, movable pulley 11, the second slide trolley 12, energy storage tank
13, jet pipe 14, launcher 15, shoe 16, crash energy absorption equipment 17, the second leading block 18, wirerope 19, limited block
20, accelerate guide rail 21；
The first revolution trunnion 2, second is successively installed from tail end to head end and turns round trunnion in the upper surface of the flat car 1
6, the first leading block 9, fixed pulley 10, accelerate guide rail 21 and limited block 20, described in the top for accelerating guide rail 21 is placed
Second slide trolley 12, the fixed energy storage tank 13 of top installation of second slide trolley 12, second slide trolley
12 and energy storage tank 13 head end towards the limited block 20, the tail end of second slide trolley 12 installs the movable pulley
11, the tail end of the energy storage tank 13 installs the jet pipe 14；The upper surface of the launcher 15 is covered with the shoe 16, institute
First slide trolley 5 is placed in the top for stating shoe 16, and the top of first slide trolley 5 can place nobody
Machine, the tail end of the launcher 15 install the relieving mechanism 4, and the relieving mechanism 4 is used for the energy when needing to launch unmanned plane
The first slide trolley 5 is enough discharged, the head end of the launcher 15 installs the crash energy absorption equipment 17 and the second leading block 18,
The A-frame 3 is installed in the lower surface of 15 tail end of launcher and third turns round trunnion 8；The launcher 15 is located at plate
1 top of vehicle, the A-frame 3 are connected by a hinge with the first revolution trunnion 2；The elevating ram 7 is located at 15 He of launcher
Among flat car 1, described 7 one end of elevating ram is connect with the second revolution 6 hinge of trunnion, and the other end and the third are turned round
The connection of 8 hinge of trunnion；One end of the wirerope 19 is fixed on first slide trolley 5 towards the one of the second leading block 18
End, the other end, which successively bypasses the second leading block 18, the first leading block 9, movable pulley 11 and fixed pulley 10 and is fixed on, determines cunning
On wheel 10；Wherein, it is liquid reservoir close to one end of jet pipe 14 in the energy storage tank 13, is full of high pressure water inside liquid reservoir.
Preferably, the liquid reservoir and a gas cavity two parts are divided into the energy storage tank 13, wherein far from jet pipe
14 one end is gas cavity, is full of inert gas inside gas cavity.
Preferably, the bottom surface of first slide trolley 5 is equipped with idler wheel, and the first slide trolley 5 can be by idler wheel along hair
Guide rail 16 is penetrated to move forward and backward.
Preferably, the bottom surface of second slide trolley 12 is equipped with idler wheel, and the second slide trolley 12 can pass through idler wheel edge
Guide rail 21 is accelerated to move forward and backward.
Preferably, the upper surface of the flat car 1 is integrated machine-shaping with the first revolution trunnion 2 or welding forms, and puts down
The upper surface of wooden handcart 1 is integrated machine-shaping with the second revolution trunnion 6 or welding forms.
Preferably, the A-frame 3 is integrated machine-shaping with 15 tail end lower surface of launcher or welding forms.
Preferably, the lower surface of third revolution trunnion 8 and 15 tail end of launcher be integrated machine-shaping or welding and
At.
Preferably, first slide trolley 5 is equipped with shifting block or hook for connecting unmanned plane.
Preferably, 4 to 6 group idler wheels are installed in 1 bottom surface of flat car, and flat car 1 can realize braking or front and back by idler wheel
Side-to-side movement.
Preferably, 6 groups of idler wheels are installed in 1 bottom surface of flat car, and flat car 1 can realize braking or all around by idler wheel
Movement.
(3) beneficial effect
The present invention changes the ejection mode of unmanned plane, directly simultaneously using the propulsive thrust of high-pressure water jet as ejection power
Increase ejection speed by pulley, there is no energy secondaries to convert, and energy efficiency is high, and system structure composition is simple, and speed increasing ratio is big,
The problems such as maneuverability is good, and electromagnetic interference is not present, can be widely applied in various fixed-wing unmanned aerial vehicle ejecting takes off.
Detailed description of the invention
Fig. 1 is the working principle of the invention figure；
Fig. 2 is the structural schematic diagram of energy storage tank in the present invention.
Wherein, 1- flat car, 2- first turn round trunnion, 3- A-frame, 4- relieving mechanism, the first slide trolley of 5-, 6-
Second revolution trunnion, 7- elevating ram, 8- third turn round trunnion, the first leading block of 9-, 10- fixed pulley, 11- movable pulley, 12-
Second slide trolley, 13- energy storage tank, 14- jet pipe, 15- launcher, 16- shoe, 17- crash energy absorption equipment, 18- first
Leading block, 19- wirerope, 20- limited block, 21- accelerate guide rail.
Specific embodiment
To keep the purpose of the present invention, content and advantage clearer, with reference to the accompanying drawings and examples, to of the invention
Specific embodiment is described in further detail.
The present invention provides a kind of packaged type unmanned plane gas-liquid power ejection system, is a kind of bullet relevant to Fluid-transmission
Injection device, as shown in Figure 1, the system includes that flat car 1, first turns round trunnion 2, A-frame 3, relieving mechanism 4, first slides
Trolley 5, second turn round trunnion 6, elevating ram 7, third revolution trunnion 8, the first leading block 9, fixed pulley 10, movable pulley 11,
Second slide trolley 12, energy storage tank 13, jet pipe 14, launcher 15, shoe 16, the guiding of crash energy absorption equipment 17, second are slided
Wheel 18, limited block 20, accelerates guide rail 21 at wirerope 19；
The first revolution trunnion 2, second is successively installed from tail end to head end and turns round trunnion in the upper surface of the flat car 1
6, the first leading block 9, fixed pulley 10, accelerate guide rail 21 and limited block 20, described in the top for accelerating guide rail 21 is placed
Second slide trolley 12, the fixed energy storage tank 13 of top installation of second slide trolley 12, second slide trolley
12 and energy storage tank 13 head end towards the limited block 20, the tail end of second slide trolley 12 installs the movable pulley
11, the tail end of the energy storage tank 13 installs the jet pipe 14；The upper surface of the launcher 15 is covered with the shoe 16, institute
First slide trolley 5 is placed in the top for stating shoe 16, and the top of first slide trolley 5 can place nobody
Machine, the tail end of the launcher 15 install the relieving mechanism 4, and the relieving mechanism 4 is used for the energy when needing to launch unmanned plane
The first slide trolley 5 is enough discharged, the head end of the launcher 15 installs the crash energy absorption equipment 17 and the second leading block 18,
The A-frame 3 is installed in the lower surface of 15 tail end of launcher and third turns round trunnion 8；The launcher 15 is located at plate
1 top of vehicle, the A-frame 3 are connected by a hinge with the first revolution trunnion 2；The elevating ram 7 is located at 15 He of launcher
Among flat car 1, described 7 one end of elevating ram is connect with the second revolution 6 hinge of trunnion, and the other end and the third are turned round
The connection of 8 hinge of trunnion；One end of the wirerope 19 is fixed on first slide trolley 5 towards the one of the second leading block 18
End, the other end, which successively bypasses the second leading block 18, the first leading block 9, movable pulley 11 and fixed pulley 10 and is fixed on, determines cunning
On wheel 10；
As shown in Fig. 2, being divided into liquid reservoir and gas cavity two parts in the energy storage tank 13, wherein close to jet pipe 14
One end is liquid reservoir, and high pressure water is full of inside liquid reservoir, is full of high pressure nitrogen or other inside the gas cavity of the other end
Inert gas；
The bottom surface of first slide trolley 5 is equipped with idler wheel, and the first slide trolley 5 can be by idler wheel along shoe 16
It moves forward and backward；The bottom surface of second slide trolley 12 is equipped with idler wheel, and the second slide trolley 12 can be by idler wheel along acceleration guide rail 21
It moves forward and backward；
The upper surface of the flat car 1 is integrated machine-shaping with the first revolution trunnion 2 or welding forms, flat car 1
Upper surface is integrated machine-shaping with the second revolution trunnion 6 or welding forms；A-frame 3 is with 15 tail end lower surface of launcher
It is integrally machined molding or welding forms, the lower surface of third revolution trunnion 8 and 15 tail end of launcher is integrated machine-shaping or spelling
It welds；
The packaged type unmanned plane gas-liquid power ejection system when in use, between unmanned plane and the first slide trolley 5
Pass through shifting block or hook connection；4-6 group idler wheel is installed in 1 bottom surface of flat car, and flat car 1 can realize that braking or front and back are left by idler wheel
Right movement.
The packaged type unmanned plane gas-liquid power ejection system course of work of the invention is as follows: the piston rod of elevating ram 7
It stretches out, launcher 15 is rotated by the first revolution trunnion 2, is elevated launcher 15 simultaneously close to one end of the second leading block 18
It forms an angle with ground shape, the high pressure water inside the liquid reservoir of energy storage tank 13 generates that jet stream is counter pushes away from 14 high speed ejection of jet pipe
Power drives energy storage tank 13, the second slide trolley 12 and movable pulley 11 to accelerate to travel forward together, since one end of wirerope 19 is tight
Gu motionless on fixed pulley 10, the wirerope 19 being wrapped on movable pulley 11 is pulled, and relieving mechanism 4 discharges the first slide trolley
5, pulled under the guiding role of the first leading block 9 and the second leading block 18 first slide trolley 5 along shoe 16 to
Preacceleration campaign, to drive the unmanned plane acceleration on the first slide trolley 5 to travel forward, when the first slide trolley 5 is along transmitting
The movement of guide rail 16 is slowed down and is braked when encountering crash energy absorption equipment 17, while unmanned plane is detached from the first slide trolley 5 and takes off, thus
Complete the ejection launch task of unmanned plane.
It can be seen that a kind of packaged type unmanned plane gas-liquid power ejection system provided by the invention, when needing to launch,
Elevating ram pushes launcher to form certain transmitting inclination angle, and the high pressure water in energy storage tank is anti-from jet pipe high speed ejection formation jet stream
Thrust after the first slide trolley is by wirerope and pulley speedup, pulls guide rail of second slide trolley on launcher to accelerate
Movement, unmanned plane realization is taken off after reaching certain speed.The system realizes a kind of new ejection mode of unmanned plane, straight
It connects using the propulsive thrust of high-pressure water jet as ejection power and increases ejection speed by pulley, there is no energy secondaries to turn
The problems such as change, energy efficiency is high, and system structure composition is simple, and speed increasing ratio is big, and maneuverability is good, and electromagnetic interference is not present, can
It is widely applied in various fixed-wing unmanned aerial vehicle ejecting takes off.
The above is only a preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, without departing from the technical principles of the invention, several improvement and deformations can also be made, these improvement and deformations
Also it should be regarded as protection scope of the present invention.
Claims (10)
1. a kind of packaged type unmanned plane gas-liquid power ejection system, which is characterized in that including flat car (1), the first revolution branch
Ear (2), A-frame (3), relieving mechanism (4), the first slide trolley (5), the second revolution trunnion (6), elevating ram (7), the
Three revolution trunnion (8), the first leading block (9), fixed pulley (10), movable pulley (11), the second slide trolley (12), energy storage tank
(13), jet pipe (14), launcher (15), shoe (16), crash energy absorption equipment (17), the second leading block (18), steel wire
It restricts (19), limited block (20), accelerate guide rail (21)；
The upper surface of the flat car (1) is successively installed by first revolution trunnion (2), the second revolution trunnion from tail end to head end
(6), the first leading block (9), fixed pulley (10), acceleration guide rail (21) and limited block (20), acceleration guide rail (21)
Place second slide trolley (12), the fixed energy storage tank of top installation of second slide trolley (12) in top
(13), the head end of second slide trolley (12) and energy storage tank (13) is sliding towards the limited block (20), described second
The tail end of row trolley (12) installs the movable pulley (11), and the tail end of the energy storage tank (13) installs the jet pipe (14)；It is described
The upper surface of launcher (15) is covered with the shoe (16), and the top of the shoe (16) is placed described first and slided
Trolley (5), the top of first slide trolley (5) can place unmanned plane, described in the tail end installation of the launcher (15)
Relieving mechanism (4), the relieving mechanism (4) are described for that can discharge when needing to launch unmanned plane the first slide trolley (5)
The head end of launcher (15) installs the crash energy absorption equipment (17) and the second leading block (18), launcher (15) tail end
Lower surface the A-frame (3) is installed and third turns round trunnion (8)；The launcher (15) is located above flat car (1),
The A-frame (3) is connected by a hinge with the first revolution trunnion (2)；The elevating ram (7) be located at launcher (15) and
Flat car (1) is intermediate, and described elevating ram (7) one end is connect with described second revolution trunnion (6) hinge, the other end and described the
Three revolution trunnion (8) hinge connections；One end of the wirerope (19) is fixed on first slide trolley (5) and leads towards second
To one end of pulley (18), the other end successively bypass the second leading block (18), the first leading block (9), movable pulley (11) and
Fixed pulley (10) is simultaneously fixed on fixed pulley (10)；Wherein, one end in the energy storage tank (13) close to jet pipe (14) is liquid
Cavity, liquid reservoir inside are full of high pressure water.
2. the system as claimed in claim 1, which is characterized in that be divided into the liquid reservoir and a gas in the energy storage tank (13)
Body cavity two parts are full of inert gas inside gas cavity wherein one end far from jet pipe (14) is gas cavity.
3. the system as claimed in claim 1, which is characterized in that the bottom surface of first slide trolley (5) is equipped with idler wheel, the
One slide trolley (5) can be moved forward and backward by idler wheel along shoe (16).
4. the system as claimed in claim 1, which is characterized in that the bottom surface of second slide trolley (12) is equipped with idler wheel,
Second slide trolley (12) can be moved forward and backward by idler wheel along acceleration guide rail (21).
5. the system as claimed in claim 1, which is characterized in that the upper surface of the flat car (1) and the first revolution trunnion (2)
It is integrated machine-shaping or welding forms, the upper surface of flat car (1) is integrated machine-shaping or spelling with the second revolution trunnion (6)
It welds.
6. the system as claimed in claim 1, which is characterized in that the A-frame (3) and launcher (15) tail end lower surface
It is integrated machine-shaping or welding forms.
7. the system as claimed in claim 1, which is characterized in that third revolution trunnion (8) and launcher (15) tail end
Lower surface is integrated machine-shaping or welding forms.
8. the system as claimed in claim 1, which is characterized in that first slide trolley (5) is equipped with for connecting nobody
The shifting block or hook of machine.
9. the system as claimed in claim 1, which is characterized in that install 4 to 6 group idler wheels, flat car in flat car (1) bottom surface
(1) braking can be realized by idler wheel or all around move.
10. system as claimed in claim 9, which is characterized in that install 6 groups of idler wheels, flat car in flat car (1) bottom surface
(1) braking can be realized by idler wheel or all around move.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910738676.3A CN110422337A (en) | 2019-08-12 | 2019-08-12 | A kind of packaged type unmanned plane gas-liquid power ejection system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910738676.3A CN110422337A (en) | 2019-08-12 | 2019-08-12 | A kind of packaged type unmanned plane gas-liquid power ejection system |
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| CN110422337A true CN110422337A (en) | 2019-11-08 |
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| CN201910738676.3A Pending CN110422337A (en) | 2019-08-12 | 2019-08-12 | A kind of packaged type unmanned plane gas-liquid power ejection system |
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Cited By (7)
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| CN111096706A (en) * | 2019-12-31 | 2020-05-05 | 四川京航天程科技发展有限公司 | Self-wiping glass aerial work platform |
| CN111717408A (en) * | 2020-06-29 | 2020-09-29 | 山东科技大学 | An offshore launch platform that can carry multiple UAVs |
| CN111924123A (en) * | 2020-06-24 | 2020-11-13 | 耿新利 | Agricultural thing networking fixed wing unmanned aerial vehicle jettison device |
| CN113148217A (en) * | 2021-06-09 | 2021-07-23 | 中国科学院工程热物理研究所 | Launch auxiliary power unit |
| CN113398603A (en) * | 2020-03-16 | 2021-09-17 | 广东彩珀科教文化股份有限公司 | Novel push type ejection toy car is from gyration track |
| CN113479340A (en) * | 2021-07-23 | 2021-10-08 | 航天时代飞鹏有限公司 | Unmanned aerial vehicle ejection method |
| CN119262381A (en) * | 2024-11-14 | 2025-01-07 | 北京航天试验技术研究所 | A medium and large unmanned aerial vehicle ejection device and ejection method |
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Application publication date: 20191108 |