CN112407308A - Carbon fiber unmanned aerial vehicle fuselage with anticollision institution - Google Patents
Carbon fiber unmanned aerial vehicle fuselage with anticollision institution Download PDFInfo
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- CN112407308A CN112407308A CN202011549700.8A CN202011549700A CN112407308A CN 112407308 A CN112407308 A CN 112407308A CN 202011549700 A CN202011549700 A CN 202011549700A CN 112407308 A CN112407308 A CN 112407308A
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- 229920000049 Carbon (fiber) Polymers 0.000 title claims abstract description 32
- 239000004917 carbon fiber Substances 0.000 title claims abstract description 32
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 title claims abstract description 32
- 230000007246 mechanism Effects 0.000 claims abstract description 34
- 230000000694 effects Effects 0.000 claims description 4
- 230000006978 adaptation Effects 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 230000008859 change Effects 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 4
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000012779 reinforcing material Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
- F16F15/08—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with rubber springs ; with springs made of rubber and metal
- F16F15/085—Use of both rubber and metal springs
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Mechanical Engineering (AREA)
- Vibration Dampers (AREA)
Abstract
The invention discloses a carbon fiber unmanned aerial vehicle body with an anti-collision mechanism, which belongs to the field of unmanned aerial vehicle protection and comprises a body, wherein the bottom of the body is fixedly connected with the anti-collision mechanism, the bottom of the anti-collision mechanism is fixedly connected with a first connecting block, the top of the first connecting block is fixedly connected with a rubber pad, one side of an inner cavity of the first connecting block is fixedly connected with a hook sleeve, one side of the hook sleeve is clamped with a barb, the bottom of the barb is fixedly connected with a moving block, the inside of the moving block is respectively and movably sleeved with a screw rod and a fixed rod, and the outside of the other end of the screw rod; through setting up anticollision institution and crashproof pad, when carbon fiber unmanned aerial vehicle was flying, utilize anticollision institution's elasticity performance to cushion the fuselage, avoided leading to carbon fiber unmanned aerial vehicle to take place the problem of damaging because of the collision of unexpected production, improved the security when carbon fiber unmanned aerial vehicle flies.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicle protection, and particularly relates to a carbon fiber unmanned aerial vehicle body with an anti-collision mechanism.
Background
Unmanned aerial vehicle is "unmanned aerial vehicle" for short, be the unmanned aerial vehicle who utilizes radio remote control equipment and the program control device manipulation of self-contained, or operate independently totally or intermittently by the on-vehicle computer, carbon-fibre composite is that present unmanned aerial vehicle uses one of more reinforcing material, however, most of carbon fiber unmanned aerial vehicle fuselages do not have anticollision institution, make carbon fiber unmanned aerial vehicle when flying, the collision because of unexpected production can lead to carbon fiber unmanned aerial vehicle to take place to damage, and carbon fiber unmanned aerial vehicle's crash pad is difficult to dismantle, long-time use can lead to the crash pad to take place to damage, for this we provide a carbon fiber unmanned aerial vehicle fuselage with anticollision institution.
Disclosure of Invention
The invention aims to provide a carbon fiber unmanned aerial vehicle body with an anti-collision mechanism, so as to solve the problems in the background technology.
In order to achieve the purpose, the invention provides the following technical scheme: a carbon fiber unmanned aerial vehicle body with an anti-collision mechanism comprises a body, wherein the bottom of the body is fixedly connected with the anti-collision mechanism, the bottom of the anti-collision mechanism is fixedly connected with a first connecting block, the top of the first connecting block is fixedly connected with a rubber pad, one side of an inner cavity of the first connecting block is fixedly connected with a hook sleeve, one side of the hook sleeve is clamped with a barb, the bottom of the barb is fixedly connected with a moving block, the inside of the moving block is respectively and movably sleeved with a screw rod and a fixed rod, the outside of the other end of the screw rod is movably sleeved with a gear box, one end of the screw rod is fixedly connected with a second gear, the top of the gear box is movably sleeved with a rotating shaft, the bottom of the rotating shaft is fixedly connected with a first gear, the outside of one end of the screw rod is movably sleeved with a first cushion block, the top of the, no. two connecting blocks of anticollision institution fixedly connected with are passed through to one side of fuselage, No. two cushion blocks are in the one end joint of No. two connecting blocks, No. two crashproof pads of one side fixedly connected with of No. two cushion blocks, No. two fixture blocks have been cup jointed in the top activity of No. two cushion blocks one side, No. two blocks of drawing of the positive fixedly connected with of No. two fixture blocks, No. three springs of the bottom fixedly connected with of No. two fixture blocks, No. one fixture block has been cup jointed in the bottom activity of No. two cushion blocks one side, No. one drawing of the positive fixedly connected with of a fixture block, No. four springs of the top fixedly connected with of a fixture block.
As a preferred embodiment, anticollision institution includes connecting rod, a spring, fixed cover and No. two springs, the outside and the fixed top activity of cover of connecting rod bottom cup joint, the bottom of fixed cover and the top fixed connection of a connecting block, the bottom of fuselage is through the top fixed connection of a spring and a connecting block, the bottom of connecting rod is through the top fixed connection of No. two springs and a connecting block.
As a preferred embodiment, the number of the anti-collision mechanisms is six, four of the six anti-collision mechanisms are symmetrically distributed at the top and the bottom of the fuselage in pairs, and the other two anti-collision mechanisms are symmetrically distributed at two sides of the fuselage.
In a preferred embodiment, the top of the first connecting block is matched with the bottom of the machine body, and the machine body is positioned above the first connecting block.
As a preferred embodiment, the first gear and the second gear are located inside the gear box, one side of the first gear is matched with the top of the second gear, and the outside of the screw is provided with external threads in two directions.
In a preferred embodiment, the bottom of the third spring is fixedly connected with a fixing plate, the fixing plate is fixedly connected with the inner part of one side of the second cushion block, and the bottom of the fixing plate is fixedly connected with the top end of the fourth spring.
Compared with the prior art, the invention has the beneficial effects that:
according to the carbon fiber unmanned aerial vehicle body with the anti-collision mechanism, due to the arrangement of the anti-collision mechanism and the anti-collision pad, when the carbon fiber unmanned aerial vehicle flies, the body is buffered by using the elastic performance of the anti-collision mechanism, so that the problem that the carbon fiber unmanned aerial vehicle is damaged due to collision caused by accidents is avoided, and the flying safety of the carbon fiber unmanned aerial vehicle is improved;
this carbon fiber unmanned aerial vehicle fuselage with anticollision institution, through setting up the barb, the hook housing, the movable block, the screw rod, the dead lever, a cushion, the rotation axis, the gear box, a gear and No. two gears, can dismantle the crashproof pad of fuselage top and bottom, through setting up No. two connecting blocks, No. three springs, a fixture block, No. one draw the piece, No. four springs, No. two fixture blocks, No. two draw piece and No. two cushions, can dismantle the crashproof pad of fuselage both sides, avoided the long-time use of crashproof pad and lead to the crashproof pad to take place the problem of damaging, the change of crashproof pad has brought the facility.
Drawings
FIG. 1 is a schematic front view of the structure of the present invention;
FIG. 2 is an enlarged view of the position A in the present invention;
FIG. 3 is an enlarged view of the position B in the present invention;
fig. 4 is a side view of the first block of the present invention.
In the figure: 1. a body; 2. a connecting rod; 3. a first spring; 4. fixing a sleeve; 5. a second spring; 6. a first connecting block; 7. a barb; 8. hooking; 9. a moving block; 10. a screw; 11. fixing the rod; 12. a first cushion block; 13. a rotating shaft; 14. a gear box; 15. a first gear; 16. a second gear; 17. a first anti-collision pad; 18. a rubber pad; 19. a movable groove; 20. a second connecting block; 21. a third spring; 22. a first clamping block; 23. a first pull block; 24. a fourth spring; 25. a second clamping block; 26. pulling the block II; 27. a second cushion block; 28. no. two crash pads.
Detailed Description
The present invention will be further described with reference to the following examples.
The following examples are intended to illustrate the invention but are not intended to limit the scope of the invention. The conditions in the embodiments can be further adjusted according to specific conditions, and simple modifications of the method of the present invention based on the concept of the present invention are within the scope of the claimed invention.
Referring to fig. 1-4, the invention provides a carbon fiber unmanned aerial vehicle body with an anti-collision mechanism, which comprises a body 1, and is characterized in that: the anti-collision device comprises a machine body 1, wherein the bottom of the machine body 1 is fixedly connected with an anti-collision mechanism, the bottom of the anti-collision mechanism is fixedly connected with a first connecting block 6, the top of the first connecting block 6 is fixedly connected with a rubber pad 18, one side of the inner cavity of the first connecting block 6 is fixedly connected with a hook sleeve 8, one side of the hook sleeve 8 is clamped with a barb 7, the bottom of the barb 7 is fixedly connected with a moving block 9, the inside of the moving block 9 is respectively and movably sleeved with a screw rod 10 and a fixed rod 11, the outside of the other end of the screw rod 10 is movably sleeved with a gear box 14, one end of the screw rod 10 is fixedly connected with a second gear 16, the top of the gear box 14 is movably sleeved with a rotating shaft 13, the bottom end of the rotating shaft 13 is fixedly connected with a first gear 15, the outside of one end of the screw rod 10 is movably sleeved with a first cushion block 12, a second cushion block 27 is clamped at one end of the second connecting block 20, a second anti-collision pad 28 is fixedly connected to one side of the second cushion block 27, a second clamping block 25 is movably sleeved at the top of one side of the second cushion block 27, a second pull block 26 is fixedly connected to the front of the second clamping block 25, a third spring 21 is fixedly connected to the bottom of the second clamping block 25, a first clamping block 22 is movably sleeved at the bottom of one side of the second cushion block 27, a first pull block 23 is fixedly connected to the front of the first clamping block 22, and a fourth spring 24 is fixedly connected to the top of the first clamping block 22; through setting up barb 7, the hook cover 8, the movable block 9, the screw rod 10, the dead lever 11, cushion 12, rotation axis 13, gear box 14, gear 15 and No. two gears 16, can dismantle the crash pad of fuselage 1 top and bottom, through setting up No. two connecting blocks 20, No. three spring 21, fixture block 22, draw a 23, No. four spring 24, No. two fixture block 25, draw a 26 and No. two cushion 27 No. two, can dismantle the crash pad of fuselage 1 both sides, avoided the long-time use of crash pad and leaded to the crash pad problem of taking place to damage, brought the facility for the change of crash pad.
The anti-collision mechanism comprises a connecting rod 2, a first spring 3, a fixed sleeve 4 and a second spring 5, the outer part of the bottom end of the connecting rod 2 is movably sleeved with the top of the fixed sleeve 4, the bottom of the fixed sleeve 4 is fixedly connected with the top of a first connecting block 6, the bottom of the machine body 1 is fixedly connected with the top of the first connecting block 6 through the first spring 3, and the bottom end of the connecting rod 2 is fixedly connected with the top of the first connecting block 6 through the second spring 5; when unmanned aerial vehicle collides because of the accident on the way flying, the bump-on-the-road produces and exerts pressure to No. one crash pad 17 or No. two crash pads 28, No. one crash pad 17 or No. two crash pads 28 generate pressure to anticollision institution, No. one spring 3 and No. two springs 5 take place compression deformation because of pressure among the anticollision institution, the pressure that the collision produced has been offset, utilize anticollision institution's elasticity performance to cushion fuselage 1, the problem of carbon fiber unmanned aerial vehicle emergence damage has been avoided, the security when having improved carbon fiber unmanned aerial vehicle flies.
The number of the anti-collision mechanisms is six, four of the six anti-collision mechanisms are symmetrically distributed at the top and the bottom of the machine body 1 in pairs, and the other two anti-collision mechanisms are symmetrically distributed at two sides of the machine body 1; because of the collision is uncertain factor, six anticollision institution make carbon fiber unmanned aerial vehicle can three hundred sixty degrees anticollision.
The top of the first connecting block 6 is matched with the bottom of the machine body 1, and the machine body 1 is positioned above the first connecting block 6; when unmanned aerial vehicle bumps, the rubber pad 18 at 6 tops of a connecting block prevents that 6 tops of a connecting block from striking unmanned aerial vehicle's bottom, has improved unmanned aerial vehicle because of the security of unexpected bottom when bumping on the way in flight.
The first gear 15 and the second gear 16 are positioned inside the gear box 14, one side of the first gear 15 is matched with the top of the second gear 16, and external threads in two directions are arranged outside the screw 10; when the crash pad 17 of fuselage 1 top and bottom need be dismantled, rotatory rotation axis 13, rotation axis 13 drives a gear 15 and rotates, a gear 15 drives No. two gears 16 and rotates, No. two gears 16 drive screw rod 10 and rotate, screw rod 10 drives two movable blocks 9 through the external screw thread of equidirectional two and removes to screw rod 10 middle part, movable block 9 drives barb 7 and breaks away from the shackle 8, and then dismantle the crash pad 17 of fuselage 1 top and bottom, avoided the long-time use of crash pad 17 and leaded to the problem that crash pad 17 takes place to damage, brought the facility for the change of crash pad 17.
The bottom of the third spring 21 is fixedly connected with a fixing plate, the fixing plate is fixedly connected with the inner part of one side of the second cushion block 27, and the bottom of the fixing plate is fixedly connected with the top end of the fourth spring 24; no. two crash pads 28 of fuselage 1 both sides need be dismantled, pull-push No. one No. 23 and No. two pull blocks 26 to the direction of fixed plate, pull-push No. one No. 23 and No. two pull blocks 26 drive a fixture block 22 and No. two fixture blocks 25 and move to the direction of fixed plate, and then drive 21 No. three springs and No. four springs 24 and take place compression deformation, a fixture block 22 and No. two fixture blocks 25 break away from the inside draw-in groove of No. two connecting blocks 20, and then dismantle No. two crash pads 28 of fuselage 1 both sides, avoided No. two crash pads 28 long-time use and leaded to No. one crash pad 17 to take place the problem of damaging, brought the facility for No. two crash pads 28's change.
The working principle and the using process of the invention are as follows: firstly, when the unmanned aerial vehicle collides by accident in the flying process, the collision object applies pressure to the first or second anti-collision pad 17 or 28, the first or second anti-collision pad 17 or 28 applies pressure to the anti-collision mechanism, the first and second springs 3 and 5 in the anti-collision mechanism compress and deform due to the pressure, the pressure generated by collision is counteracted, the problem of damage of the carbon fiber unmanned aerial vehicle is avoided, the safety of the carbon fiber unmanned aerial vehicle in the flying process is improved, then, the carbon fiber unmanned aerial vehicle can be prevented from collision by three hundred and sixty degrees due to the collision as uncertain factors, the rubber pad 18 at the top of the first connecting block 6 prevents the top of the first connecting block 6 from colliding with the bottom of the unmanned aerial vehicle, the safety of the unmanned aerial vehicle head when the unmanned aerial vehicle collides by accident in the flying process is improved, and finally, when the first anti-collision pad 17 at the top and the bottom of the body 1 needs to be disassembled, the rotating shaft 13 is rotated, the rotating shaft 13 drives the first gear 15 to rotate, the first gear 15 drives the second gear 16 to rotate, the second gear 16 drives the screw rod 10 to rotate, the screw rod 10 drives the two moving blocks 9 to move towards the middle of the screw rod 10 through external threads in two directions, the moving blocks 9 drive the barbs 7 to be separated from the hook sleeves 8, and then the first anti-collision pads 17 at the top and the bottom of the machine body 1 are disassembled, so that the problem that the first anti-collision pads 17 are damaged due to long-time use of the first anti-collision pads 17 is avoided, convenience is brought to replacement of the first anti-collision pads 17, when the second anti-collision pads 28 at two sides of the machine body 1 need to be disassembled, the first pull block 23 and the second pull block 26 are pushed and pulled towards the direction of the fixing plate, the first pull block 23 and the second pull block 26 drive the first fixture block 22 and the second fixture block 25 to move towards the direction of the fixing plate, and further drive the third, no. one fixture block 22 and No. two fixture blocks 25 break away from the inside draw-in groove of No. two connecting blocks 20, and then dismantle No. two crash pads 28 of fuselage 1 both sides, have avoided No. two crash pads 28 long-time uses and lead to No. one crash pad 17 to take place the problem of damaging, have brought the facility for No. two crash pads 28's change.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (6)
1. The utility model provides a carbon fiber unmanned aerial vehicle fuselage with anticollision institution, includes fuselage (1), its characterized in that: the anti-collision device comprises a machine body (1), wherein the bottom of the machine body (1) is fixedly connected with an anti-collision mechanism, the bottom of the anti-collision mechanism is fixedly connected with a first connecting block (6), the top of the first connecting block (6) is fixedly connected with a rubber pad (18), one side of an inner cavity of the first connecting block (6) is fixedly connected with a hook sleeve (8), one side of the hook sleeve (8) is clamped with a barb (7), the bottom of the barb (7) is fixedly connected with a moving block (9), the inside of the moving block (9) is respectively and movably sleeved with a screw rod (10) and a fixed rod (11), the outside of the other end of the screw rod (10) is movably sleeved with a gear box (14), one end of the screw rod (10) is fixedly connected with a second gear (16), the top of the gear box (14) is movably sleeved with a rotating shaft, a first cushion block (12) is movably sleeved outside one end of the screw (10), a movable groove (19) is formed in the top of the first cushion block (12), a first anti-collision pad (17) is fixedly connected to the bottom of the first cushion block (12), a second connecting block (20) is fixedly connected to one side of the machine body (1) through an anti-collision mechanism, a second cushion block (27) is clamped to one end of the second connecting block (20), a second anti-collision pad (28) is fixedly connected to one side of the second cushion block (27), a second clamping block (25) is movably sleeved on the top of one side of the second cushion block (27), a second pull block (26) is fixedly connected to the front of the second clamping block (25), a third spring (21) is fixedly connected to the bottom of the second clamping block (25), and a first clamping block (22) is movably sleeved on the bottom of one side of the second cushion block (27), the front surface of the first clamping block (22) is fixedly connected with a first pulling block (23), and the top of the first clamping block (22) is fixedly connected with a fourth spring (24).
2. The carbon fiber unmanned aerial vehicle fuselage with anticollision mechanism of claim 1, characterized in that: anticollision institution includes connecting rod (2), spring (3), fixed cover (4) and No. two spring (5), the outside and the fixed top of cover (4) activity of connecting rod (2) bottom are cup jointed, the bottom of fixed cover (4) and the top fixed connection of connecting block (6), the bottom of fuselage (1) is through the top fixed connection of spring (3) and connecting block (6), the bottom of connecting rod (2) is through the top fixed connection of No. two spring (5) and connecting block (6).
3. The carbon fiber unmanned aerial vehicle fuselage with anticollision mechanism of claim 1, characterized in that: the number of the anti-collision mechanisms is six, four of the anti-collision mechanisms are symmetrically distributed at the top and the bottom of the machine body (1), and the other two anti-collision mechanisms are symmetrically distributed at two sides of the machine body (1).
4. The carbon fiber unmanned aerial vehicle fuselage with anticollision mechanism of claim 1, characterized in that: the top of the first connecting block (6) is matched with the bottom of the machine body (1), and the machine body (1) is located above the first connecting block (6).
5. The carbon fiber unmanned aerial vehicle fuselage with anticollision mechanism of claim 1, characterized in that: a gear (15) and No. two gears (16) are located inside gear box (14), one side of a gear (15) and the top looks adaptation of No. two gears (16), the outside of screw rod (10) is equipped with the external screw thread of two kinds of directions.
6. The carbon fiber unmanned aerial vehicle fuselage with anticollision mechanism of claim 1, characterized in that: the bottom fixed connection fixed plate of No. three spring (21), the fixed plate is with the inside fixed connection of No. two cushion (27) one side, the bottom of fixed plate and the top fixed connection of No. four spring (24).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011549700.8A CN112407308A (en) | 2020-12-24 | 2020-12-24 | Carbon fiber unmanned aerial vehicle fuselage with anticollision institution |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011549700.8A CN112407308A (en) | 2020-12-24 | 2020-12-24 | Carbon fiber unmanned aerial vehicle fuselage with anticollision institution |
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| CN112407308A true CN112407308A (en) | 2021-02-26 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011549700.8A Pending CN112407308A (en) | 2020-12-24 | 2020-12-24 | Carbon fiber unmanned aerial vehicle fuselage with anticollision institution |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113148162A (en) * | 2021-05-12 | 2021-07-23 | 黄河水利职业技术学院 | Many rotor unmanned aerial vehicle mapping device |
| CN113559528A (en) * | 2021-09-26 | 2021-10-29 | 深圳市鼎峰无限电子有限公司 | Remote control helicopter with anti-falling device |
| US20220396369A1 (en) * | 2016-05-17 | 2022-12-15 | Espheric, Llc | Multi Sensor Support Structure |
-
2020
- 2020-12-24 CN CN202011549700.8A patent/CN112407308A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20220396369A1 (en) * | 2016-05-17 | 2022-12-15 | Espheric, Llc | Multi Sensor Support Structure |
| US11975864B2 (en) * | 2016-05-17 | 2024-05-07 | Espheric, Llc | Multi sensor support structure |
| CN113148162A (en) * | 2021-05-12 | 2021-07-23 | 黄河水利职业技术学院 | Many rotor unmanned aerial vehicle mapping device |
| CN113559528A (en) * | 2021-09-26 | 2021-10-29 | 深圳市鼎峰无限电子有限公司 | Remote control helicopter with anti-falling device |
| CN113559528B (en) * | 2021-09-26 | 2021-12-10 | 深圳市鼎峰无限电子有限公司 | Remote control helicopter with anti-falling device |
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