CN113479340A - Unmanned aerial vehicle ejection method - Google Patents
Unmanned aerial vehicle ejection method Download PDFInfo
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- CN113479340A CN113479340A CN202110838401.4A CN202110838401A CN113479340A CN 113479340 A CN113479340 A CN 113479340A CN 202110838401 A CN202110838401 A CN 202110838401A CN 113479340 A CN113479340 A CN 113479340A
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- 238000000034 method Methods 0.000 title claims abstract description 31
- 239000007921 spray Substances 0.000 claims abstract description 5
- 238000007789 sealing Methods 0.000 claims description 7
- 230000035939 shock Effects 0.000 claims description 7
- 238000010521 absorption reaction Methods 0.000 claims description 6
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 238000010008 shearing Methods 0.000 claims 2
- 238000013016 damping Methods 0.000 description 4
- 230000003139 buffering effect Effects 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000007788 liquid 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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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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)
- Remote Sensing (AREA)
- Forklifts And Lifting Vehicles (AREA)
Abstract
The invention discloses an unmanned aerial vehicle ejection method, which comprises an unmanned aerial vehicle power ejection mechanism; the power ejection mechanism of the unmanned aerial vehicle comprises a base, an emission frame, a rotating assembly, an emission platform, a clamping unit and a power assembly; the launching platform is connected with the power assembly through a pulley block and a traction rope; the base comprises an upper base, a lower base and a lifting component; the rotating assembly comprises an electric telescopic rod, a first lifting oil cylinder and a second lifting oil cylinder; the power assembly comprises a power seat and a power tank, and a spray pipe is arranged on the left side of the power tank. The launching device realizes the catapult takeoff of the fixed wing unmanned aerial vehicle by arranging the power assembly, the launching platform, the clamping unit, the traction rope and the pulley block, does not need to adopt a runway on site, and can adjust the height and the angle of the launching frame. The invention has the advantages of relatively wider application without being limited by the runway, and less possibility of damage to take-off, thereby reducing loss.
Description
Technical Field
The invention relates to a fixed wing unmanned aerial vehicle, in particular to an unmanned aerial vehicle ejection method.
Background
Along with the development of science and technology, unmanned aerial vehicle uses more and more extensively. Unmanned aerial vehicle generally divide into fixed wing unmanned aerial vehicle and rotor unmanned aerial vehicle, thereby rotor unmanned aerial vehicle can realize VTOL because of it has a plurality of rotor groups, and it takes off and need not to use runway etc.. The fixed-wing unmanned aerial vehicle does not have a rotor set for vertical take-off and landing, and therefore the fixed-wing unmanned aerial vehicle is required to take off in a runway run-up mode.
However, if the fixed-wing unmanned aerial vehicle is used for run-up takeoff, the required runway is long, and a proper runway cannot be found for takeoff in the actual process, so that the application of the fixed-wing unmanned aerial vehicle is limited. Moreover, the fixed-wing unmanned aerial vehicle can not completely clean the runway and ensure the smoothness of the runway by running and taking off by itself, the runway is easy to collide with and the like in the taking-off process, the failure of taking off is caused, the damage can be caused seriously, and thus the great loss is brought.
Therefore, the fixed-wing unmanned aerial vehicle takes off from the runway by only depending on the fixed-wing unmanned aerial vehicle, and has the problems that the application is not wide and the taking off is easy to damage, thereby causing great loss.
Disclosure of Invention
The invention aims to provide an unmanned aerial vehicle ejection method. The fixed wing unmanned aerial vehicle catapult launching device has the advantages that the fixed wing unmanned aerial vehicle catapult launching is realized by adopting a special unmanned aerial vehicle catapult mechanism and a special unmanned aerial vehicle catapult method, the fixed wing unmanned aerial vehicle catapult launching device is not limited by a runway and is relatively wider in application, and the fixed wing unmanned aerial vehicle catapult launching device is not easy to damage during take-off so as to reduce loss.
The technical scheme of the invention is as follows: the unmanned aerial vehicle ejection method comprises an unmanned aerial vehicle power ejection mechanism; the unmanned aerial vehicle power ejection mechanism comprises a base, a launching frame arranged on the base, a rotating assembly arranged on the base and rotatably connected with the bottom of the launching frame, a launching platform movably arranged on the launching frame, a clamping unit arranged at the bottom end of the launching frame and connected with the launching platform, and a power assembly movably arranged on the base and connected with the launching platform; the launching platform is connected with the power assembly through a pulley block and a traction rope penetrating through the pulley block; the base comprises an upper base, a lower base arranged below the upper base and a lifting assembly arranged between the upper base and the lower base; the launching rack is provided with a launching chute corresponding to the launching platform, and the middle lower part of the launching platform is clamped in the launching chute; the top end of the launching chute is provided with an elastic buffer unit; the pulley block comprises a first pulley arranged at the top of the launching frame, a second pulley arranged above the upper base, a third pulley arranged on the right side of the second pulley and a fourth pulley arranged on the left side of the power assembly; the second pulley, the third pulley and the fourth pulley are all positioned at the same horizontal height; one end of the traction rope is connected with the launching platform, the other end of the traction rope is sequentially connected with the first pulley, the second pulley, the third pulley and the fourth pulley, and the other end of the traction rope is fixedly connected to the third pulley; the rotating assembly comprises an electric telescopic rod, a first lifting oil cylinder and two second lifting oil cylinders, wherein the electric telescopic rod is arranged at the left end of the upper base and is rotatably connected with the bottom end of the launching frame; the power assembly comprises a power seat movably arranged at the right part above the upper base and a power tank arranged above the power seat, and a spray pipe is arranged at the left side of the power tank; the fourth pulley is arranged at the left end of the power seat.
In the unmanned aerial vehicle ejection method, the power tank is a liquid power tank, and the interior of the power tank is filled with high-pressure water.
In the unmanned aerial vehicle ejection method, the lifting assembly comprises three groups of uniformly arranged scissor lifting frames and a plurality of hydraulic telescopic rods uniformly arranged between adjacent scissor lifting frames.
In the unmanned aerial vehicle ejection method, a plurality of roller groups are uniformly arranged below the lower base; each roller group is connected with the lower base through a rotating platform.
In the unmanned aerial vehicle ejection method, a clamping arm clamped with the launching platform is arranged at the top of the right side of the clamping unit; the clamping arm can realize clamping and releasing of the launching pad.
In the unmanned aerial vehicle ejection method, a power sliding groove corresponding to the power seat is formed in the right part of the upper base, and the lower part of the power seat and the roller thereof are both positioned in the power sliding groove; the right-hand member of going up the base is equipped with the stopper, No. two lift cylinder's bottom is rotated and is connected in the top of stopper.
In the unmanned aerial vehicle ejection method, the power seat is provided with a mounting seat corresponding to the power tank; a lower damping filling layer corresponding to the power tank is arranged below the inner part of the mounting seat, an opening corresponding to the power tank and used for dismounting the power tank is arranged at the top of the mounting seat, a sealing cover is arranged at the opening, and an upper damping filling layer is arranged between the sealing cover and the power tank; the upper shock absorption filling layer is detachably arranged in the mounting seat.
In the unmanned aerial vehicle ejection method, a push-back assembly for resetting the power seat is arranged in the bottom of the limiting block; the push-back assembly comprises a horizontal telescopic rod and a driving motor for driving the horizontal telescopic rod to stretch; the horizontal telescopic rod is located in the limiting block when completely contracted, and the horizontal telescopic rod penetrates through the left side of the limiting block and extends out to reset the power seat.
In the unmanned aerial vehicle ejection method, the launching platform is provided with a mounting rack corresponding to the fixed-wing unmanned aerial vehicle and used for fixing and separating the fixed-wing unmanned aerial vehicle.
The unmanned aerial vehicle ejection method comprises the following steps:
A. the fixed wing unmanned aerial vehicle is arranged on the launching platform through the mounting frame;
B. the height of the launching frame is adjusted by adjusting the hydraulic telescopic rod, so that the launching frame meets the required projection height;
C. the angle of the launching frame is adjusted by sequentially adjusting the electric telescopic rod, the first lifting oil cylinder and the second lifting oil cylinder, so that the required projection angle is met;
D. opening the power tank, and simultaneously releasing the clamping arm of the clamping unit to fix the launching platform;
E. when the launching pad moved to the launching cradle top and contacted with the elastic buffer unit, the mounting bracket on the launching pad released, and the fixed wing unmanned aerial vehicle takes off after breaking away from the launching pad.
Compared with the prior art, the launching mechanism has the advantages that the power seat and the power tank are arranged as power components of the launching power, the fixed-wing unmanned aerial vehicle is fixed by the launching platform, the launching platform is fixed by the clamping unit and then is connected by the pulley block comprising the traction rope and the pulleys, so that the launching of the fixed-wing unmanned aerial vehicle is realized, a runway on site is not needed, the unmanned aerial vehicle can be launched by the power launching mechanism of the unmanned aerial vehicle no matter where the unmanned aerial vehicle is applied, the application is not limited by the environment, and the application is relatively wide; the fixed wing unmanned aerial vehicle takes off by adopting the launching device disclosed by the invention, so that the fixed wing unmanned aerial vehicle can be prevented from being influenced by a field runway, and the height and the angle of the launching frame can be adjusted according to actual conditions, thereby ensuring that the fixed wing unmanned aerial vehicle does not collide with the external environment in the taking off and primary flying processes, reducing the damage and reducing the loss of the fixed wing unmanned aerial vehicle.
Therefore, the fixed wing unmanned aerial vehicle catapult launching device has the advantages that the fixed wing unmanned aerial vehicle catapult launching is realized by adopting the special unmanned aerial vehicle catapult mechanism and the special unmanned aerial vehicle catapult launching method, the fixed wing unmanned aerial vehicle catapult launching device is not limited by a runway and is relatively wider in application, and the fixed wing unmanned aerial vehicle catapult launching device is not easy to damage during take-off so as to reduce loss.
Furthermore, the roller groups with the rotating table are arranged below the lower base, so that the mechanism is convenient to move and rotate and use.
Through set up the mount pad that corresponds with the power jar on the power seat, and the mount pad upper wall opening is equipped with sealed lid, and its inside filling layer that has the cushioning effect that is equipped with, the power jar can be more steady in quick replacement and the use.
The retractable push-back assembly is arranged at the bottom of the limiting block, so that the power seat can be pushed back to reset, the reset fixation of the mechanism is realized, and the continuous use is convenient.
Run through No. two pulleys, No. three pulleys and No. four pulleys in proper order through the haulage rope and fix again on No. three pulleys, move the messenger when No. four pulleys and remove, can drive the pulling rope twice pulling to improve the translation rate of launch pad, improved fixed wing unmanned aerial vehicle's ejection speed.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is an enlarged view at A in FIG. 1;
fig. 3 is an enlarged view at B in fig. 1.
Reference numerals: 11-lower base, 12-upper base, 121-power sliding chute, 13-scissor lifting frame, 14-hydraulic telescopic rod, 15-roller group, 16-limiting block, 2-launching frame, 21-launching sliding chute, 3-launching platform, 4-clamping unit, 41-clamping arm, 51-electric telescopic rod, 52-lifting oil cylinder, 53-lifting oil cylinder II, 6-power base, 7-traction rope, 71-pulley I, 72-pulley II, 73-pulley III, 74-pulley IV, 8-mounting base, 81-sealing cover, 82-upper shock absorption filling layer, 83-lower shock absorption filling layer, 9-power tank and 91-spray pipe.
The invention is further described with reference to the following figures and detailed description.
Detailed Description
The embodiment of the invention comprises the following steps: the unmanned aerial vehicle ejection method is shown in figures 1-3 and comprises an unmanned aerial vehicle power ejection mechanism; the power ejection mechanism of the unmanned aerial vehicle comprises a base, an emission frame 2 which is arranged on the base and is used as a runway, a rotating assembly which is arranged on the base and is rotatably connected with the bottom of the emission frame 2 to realize angle adjustment, an emission platform 3 which is movably arranged on the emission frame 2 and is used as a fixed wing unmanned aerial vehicle to bear, a clamping unit 4 which is arranged at the bottom end of the emission frame 2 and is connected with the emission platform 3, and a power assembly which is movably arranged on the base and is connected with the emission platform 3 and is used for providing power; the launching platform 3 is connected with the power assembly through a pulley block and a traction rope 7 penetrating through the pulley block; the base comprises an upper base 12, a lifting assembly and a lower base 11 which are arranged in sequence from top to bottom; the launching frame 2 is provided with a launching chute 21 for the launching platform 3 to slide; the top end of the launching chute 21 is provided with an elastic buffering unit for buffering and decelerating; the pulley block comprises a first pulley 71 arranged at the top of the launching frame 2, a second pulley 72 arranged above the upper base 12, a third pulley 73 arranged on the right side of the second pulley 72 and a fourth pulley 74 arranged on the left side of the power assembly; the second pulley 72, the third pulley 73 and the fourth pulley 74 are all located at the same horizontal height; one end of the traction rope 7 is connected with the launching platform 3, the other end of the traction rope is sequentially connected with a first pulley 71, a second pulley 72, a third pulley 73 and a fourth pulley 74, and the other end of the traction rope is fixedly connected to the third pulley 73; the rotating assembly comprises an electric telescopic rod 51 which is arranged at the left end of the upper base 12 and is rotatably connected with the bottom end of the launching frame 2, a first lifting oil cylinder 52 which is arranged between the electric telescopic rod 51 and the second pulley 72 and is rotatably connected with the bottom of the launching frame 2, and two second lifting oil cylinders 53 which are arranged at the right end of the upper base 12 and are connected with the two sides of the top end of the launching frame 2; the power assembly comprises a power seat 6 movably arranged at the right part above the upper base 12 and a power tank 9 arranged above the power seat 6, and a spray pipe 91 is arranged at the left side of the power tank 9; the fourth pulley 74 is arranged at the left end of the power seat 6.
The power tank 9 is a hydrodynamic tank, and the interior thereof is filled with high-pressure water, which is ejected from the nozzle 91 to generate thrust.
The lifting assembly comprises three groups of lifting scissors lifting frames 13 and four hydraulic telescopic rods 14 mainly used for supporting lifting.
Five pairs of roller groups 15 are uniformly arranged below the lower base 11; each roller group 15 is connected with the lower base 11 through a rotating platform, so that rotation can be realized.
And a clamping arm 41 capable of realizing clamping and releasing of the launching platform 3 is arranged at the top of the right side of the clamping unit 4.
The right part of the upper base 12 is provided with a power sliding chute 121 for the power seat 6 to slide; the right end of the upper base 12 is provided with a limiting block 16, and the bottom of the second lifting oil cylinder 53 is rotatably connected to the top of the limiting block 16.
The power seat 6 is provided with a mounting seat 8 corresponding to the power tank 9; a lower damping filling layer 83 corresponding to the power tank 9 is arranged below the inner part of the mounting seat 8, an opening corresponding to the power tank 9 and used for dismounting the power tank 9 is arranged at the top of the mounting seat, a sealing cover 81 is arranged at the opening, and an upper damping filling layer 82 is arranged between the sealing cover 81 and the power tank 9; the upper shock absorbing filling layer 82 is detachably arranged in the mounting seat 8.
A push-back component for resetting the power seat 6 is arranged in the bottom of the limiting block 16; the push-back assembly comprises a horizontal telescopic rod and a driving motor for driving the horizontal telescopic rod to stretch; the horizontal telescopic rod is located in the limiting block 16 when completely contracting, and the horizontal telescopic rod penetrates and extends out from the left side of the limiting block 16 to reset the power seat 6.
And the launching platform 3 is provided with a mounting rack which corresponds to the fixed-wing unmanned aerial vehicle and is used for fixing and separating the fixed-wing unmanned aerial vehicle.
The unmanned aerial vehicle ejection method comprises the following steps:
A. the fixed wing unmanned aerial vehicle is arranged on the launching platform 3 through a mounting frame;
B. the height of the launching frame 2 is adjusted by adjusting the hydraulic telescopic rod 14, so that the required projection height is met;
C. the angle of the launching frame 2 is adjusted by sequentially adjusting the electric telescopic rod 51, the first lifting oil cylinder 52 and the second lifting oil cylinder 53, so that the required projection angle is met;
D. the power tank 9 is opened, and meanwhile, the clamping arm 41 of the clamping unit 4 releases the fixation of the launching platform 3;
E. when launching pad 3 removed 2 tops of launching cradle and contacted with the elastic buffer unit, the mounting bracket release on launching pad 3, and fixed wing unmanned aerial vehicle breaks away from 3 backs of launching pad and takes off.
Claims (9)
1. The unmanned aerial vehicle ejection method comprises an unmanned aerial vehicle power ejection mechanism, and is characterized in that: the unmanned aerial vehicle power ejection mechanism comprises a base, a launching frame (2) arranged on the base, a rotating assembly arranged on the base and rotatably connected with the bottom of the launching frame (2), a launching platform (3) movably arranged on the launching frame (2), a clamping unit (4) arranged at the bottom end of the launching frame (2) and connected with the launching platform (3), and a power assembly movably arranged on the base and connected with the launching platform (3); the launching platform (3) is connected with the power assembly through a pulley block and a traction rope (7) penetrating through the pulley block; the base comprises an upper base (12), a lower base (11) arranged below the upper base (12) and a lifting assembly arranged between the upper base (12) and the lower base (11); the launching rack (2) is provided with a launching chute (21) corresponding to the launching platform (3), and the middle lower part of the launching platform (3) is clamped in the launching chute (21); the top end of the launching chute (21) is provided with an elastic buffer unit; the pulley block comprises a first pulley (71) arranged at the top of the launching frame (2), a second pulley (72) arranged above the upper base (12), a third pulley (73) arranged on the right side of the second pulley (72) and a fourth pulley (74) arranged on the left side of the power assembly; the second pulley (72), the third pulley (73) and the fourth pulley (74) are all positioned at the same horizontal height; one end of the traction rope (7) is connected with the launching platform (3), and the other end of the traction rope is sequentially connected with a first pulley (71), a second pulley (72), a third pulley (73) and a fourth pulley (74) and fixedly connected to the third pulley (73); the rotating assembly comprises an electric telescopic rod (51) which is arranged at the left end of the upper base (12) and is rotatably connected with the bottom end of the launching frame (2), a first lifting oil cylinder (52) which is arranged between the electric telescopic rod (51) and the second pulley (72) and is rotatably connected with the bottom of the launching frame (2), and two second lifting oil cylinders (53) which are arranged at the right end of the upper base (12) and are connected with the two sides of the top end of the launching frame (2); the power assembly comprises a power seat (6) movably arranged on the right part above the upper base (12) and a power tank (9) arranged above the power seat (6), and a spray pipe (91) is arranged on the left side of the power tank (9); the fourth pulley (74) is arranged at the left end of the power seat (6).
2. The unmanned aerial vehicle ejection method of claim 1, wherein: the lifting component comprises three groups of shearing fork lifting frames (13) which are uniformly arranged and a plurality of hydraulic telescopic rods (14) which are uniformly arranged between the adjacent shearing fork lifting frames (13).
3. The unmanned aerial vehicle ejection method of claim 1, wherein: a plurality of roller groups (15) are uniformly arranged below the lower base (11); each roller group (15) is connected with the lower base (11) through a rotating table.
4. The unmanned aerial vehicle ejection method of claim 1, wherein: the top of the right side of the clamping unit (4) is provided with a clamping arm (41) clamped with the launching platform (3); the clamping arm (41) can realize clamping and releasing of the launching platform (3).
5. The unmanned aerial vehicle ejection method of claim 1, wherein: the right part of the upper base (12) is provided with a power sliding groove (121) corresponding to the power seat (6), and the lower part of the power seat (6) and the roller thereof are positioned in the power sliding groove (121); the right end of the upper base (12) is provided with a limiting block (16), and the bottom of the second lifting oil cylinder (53) is rotatably connected to the top of the limiting block (16).
6. The unmanned aerial vehicle ejection method of claim 1, wherein: the power seat (6) is provided with a mounting seat (8) corresponding to the power tank (9); a lower shock absorption filling layer (83) corresponding to the power tank (9) is arranged below the inner part of the mounting seat (8), an opening corresponding to the power tank (9) and used for dismounting the power tank (9) is arranged at the top of the mounting seat, a sealing cover (81) is arranged at the opening, and an upper shock absorption filling layer (82) is arranged between the sealing cover (81) and the power tank (9); the upper shock absorption filling layer (82) is detachably arranged in the mounting seat (8).
7. The unmanned aerial vehicle ejection method of claim 5, wherein: a push-back component used for resetting the power seat (6) is arranged in the bottom of the limiting block (16); the push-back assembly comprises a horizontal telescopic rod and a driving motor for driving the horizontal telescopic rod to stretch; the horizontal telescopic rod is located in the limiting block (16) when completely contracted, and the horizontal telescopic rod penetrates and extends out from the left side of the limiting block (16) to reset the power seat (6).
8. The unmanned aerial vehicle ejection method of claim 1, wherein: and the launching platform (3) is provided with a mounting rack which corresponds to the fixed-wing unmanned aerial vehicle and is used for fixing and separating the fixed-wing unmanned aerial vehicle.
9. A method of ejection by a drone according to any one of claims 1 to 8, characterized by the steps of:
A. the fixed wing unmanned aerial vehicle is arranged on a launching platform (3) through a mounting frame;
B. the height of the launching frame (2) is adjusted by adjusting the hydraulic telescopic rod (14) to meet the required projection height;
C. the angle of the launching frame (2) is adjusted by sequentially adjusting the electric telescopic rod (51), the first lifting oil cylinder (52) and the second lifting oil cylinder (53), so that the required projection angle is met;
D. opening the power tank (9), and simultaneously releasing the clamping arm (41) of the clamping unit (4) from fixing the launching platform (3);
E. when launching pad (3) remove to launching cradle (2) top and contact with the elasticity buffer unit, the mounting bracket release on launching pad (3), take off behind the fixed wing unmanned aerial vehicle breaks away from launching pad (3).
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| CN202110838401.4A CN113479340A (en) | 2021-07-23 | 2021-07-23 | Unmanned aerial vehicle ejection method |
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| CN202110838401.4A CN113479340A (en) | 2021-07-23 | 2021-07-23 | Unmanned aerial vehicle ejection method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN117429651A (en) * | 2023-11-17 | 2024-01-23 | 广州天海翔航空科技有限公司 | Unmanned aerial vehicle catapulting device suitable for marine environment |
| CN117429651B (en) * | 2023-11-17 | 2024-03-19 | 广州天海翔航空科技有限公司 | Unmanned aerial vehicle catapulting device suitable for marine environment |
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Application publication date: 20211008 |