CN213323665U - Emergency landing device for quad-rotor unmanned aerial vehicle - Google Patents
Emergency landing device for quad-rotor unmanned aerial vehicle Download PDFInfo
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- CN213323665U CN213323665U CN202022591084.4U CN202022591084U CN213323665U CN 213323665 U CN213323665 U CN 213323665U CN 202022591084 U CN202022591084 U CN 202022591084U CN 213323665 U CN213323665 U CN 213323665U
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- aerial vehicle
- unmanned aerial
- vehicle body
- emergency landing
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Abstract
The utility model discloses a four rotor unmanned aerial vehicle emergency landing device, including the unmanned aerial vehicle body, the side of unmanned aerial vehicle body is fixed with the cantilever, the motor is installed to the bottom of cantilever, the output shaft of motor runs through the cantilever and is connected with the rotor, the mounting groove has been seted up at the top of unmanned aerial vehicle body, the inside both ends of mounting groove are fixed with the threaded rod, mounting panel and fixture block have been cup jointed in the sliding on the threaded rod, install first spring between fixture block and the mounting groove, the guard plate is installed at the top of unmanned aerial vehicle body, the both ends of guard plate are all rotated and are connected with the pivot. The utility model discloses a setting parachute and protection foot mechanism that can launch fast, when the unmanned aerial vehicle body loses power and falls, effectively improving this internal electronic component's of unmanned aerial vehicle protection, can use again through changing guard plate, receiver and parachute after using, the convenience of use is high.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field especially relates to four rotor unmanned aerial vehicle emergency landing devices.
Background
An unmanned aircraft, abbreviated as "drone", and abbreviated in english as "UAV", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer.
Unmanned aerial vehicle is shielded because collision or signal very easily and loses power at the in-process of flight, and unmanned aerial vehicle can't hover aloft and cause the crash, carries out urgent parachute through the parachute in the prior art mostly, but parachute opening speed is slow, often does not reach and opens unmanned aerial vehicle completely and will fall to the ground and break down, uses to exist not enoughly, for this reason we propose four rotor unmanned aerial vehicle emergency landing device.
SUMMERY OF THE UTILITY MODEL
In order to solve among the prior art parachute and carry out urgent parachute, but parachute opening speed is slow, often does not reach and opens the problem that unmanned aerial vehicle will fall to the ground and break down completely, the utility model provides a four rotor unmanned aerial vehicle emergency landing device.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
the emergency landing device of the quad-rotor unmanned aerial vehicle comprises an unmanned aerial vehicle body, wherein a cantilever is fixed on the side surface of the unmanned aerial vehicle body, a motor is installed at the bottom of the cantilever, an output shaft of the motor penetrates through the cantilever and is connected with a rotor, a mounting groove is formed in the top of the unmanned aerial vehicle body, threaded rods are fixed at two ends of the inside of the mounting groove, a mounting plate and a clamping block are sleeved on the threaded rods in a sliding manner, a first spring is installed between the clamping block and the mounting groove, a protection plate is installed at the top of the unmanned aerial vehicle body, rotating shafts are rotatably connected at two ends of the protection plate, the rotating shafts penetrate through the protection plate and are connected with threaded sleeves in a sliding manner through splines, the threaded sleeves are in threaded connection with the threaded rods through threads, a, the installation cover runs through the mounting panel and inserts the inside of receiver, the internally mounted of installation cover has some firearm, protection foot mechanism is installed at the both ends of unmanned aerial vehicle body bottom, the sensor integrated board is installed to the bottom of unmanned aerial vehicle body.
Preferably, the both ends of the bottom of guard plate are fixed with the reinforcing plate, the reinforcing plate is L type mechanism, the reinforcing plate rotates with the pivot to be connected.
Preferably, a second spring is installed between the reinforcing plate and the threaded sleeve, and the second spring is sleeved on the rotating shaft.
Preferably, protection foot mechanism is including fixing the stabilizer blade in unmanned aerial vehicle body bottom, the bottom sliding connection of stabilizer blade has movable foot, the gyro wheel is installed to the bottom of activity foot, install the third spring between the top of activity foot and the stabilizer blade.
Preferably, the side of the supporting leg is rotatably connected with a first connecting rod, the side of the first connecting rod is rotatably connected with a second connecting rod, and the second connecting rod is rotatably connected with the movable leg.
Preferably, the sensor integration board is internally provided with an acceleration sensor, a height sensor, a gyroscope and a barometer.
Preferably, the parachute is internally provided with low-intensity explosive.
Compared with the prior art, the beneficial effects of the utility model are that:
when the device is used, the storage battery in the unmanned aerial vehicle body supplies power to the electronic element in the device, the output shaft of the motor rotates to drive the rotor to rotate, the rotor rotates to enable the unmanned aerial vehicle body to take off and land, the acceleration sensor, the height sensor, the gyroscope and the barometer in the sensor integrated board carry out all-round monitoring on the flight state of the unmanned aerial vehicle body, monitoring data is transmitted to the computer to judge the flight state of the unmanned aerial vehicle body, when the unmanned aerial vehicle body loses power, the data transmitted by the acceleration sensor, the height sensor, the gyroscope and the barometer are greatly fluctuated, the computer controls the igniter to be started at the moment, the igniter ignites the low-intensity explosive in the parachute, the gas generated by the explosion of the low-intensity explosive rapidly fills the parachute, the explosion of the low-intensity explosive can not generate naked fire to ignite the parachute, and the central part of the protective board which, can reduce the falling speed of unmanned aerial vehicle body fast, at the in-process that falls to the ground, the gyro wheel at first contacts ground, the gyro wheel drives movable foot afterwards and slides and compress the third spring in the landing leg, impact force when reducing the tenesmus, when the unmanned aerial vehicle body loses power and falls, effectively improves this internal electronic component's of unmanned aerial vehicle protection, can use again through changing guard plate, receiver and parachute after using, the convenience of use is high.
Drawings
Fig. 1 is a schematic structural view of an emergency landing device of a quad-rotor unmanned aerial vehicle according to the present invention;
fig. 2 is an enlarged schematic view of a portion a of the emergency landing device of a quad-rotor unmanned aerial vehicle according to the present invention;
fig. 3 is an enlarged schematic view of a part B of the emergency landing device of a quad-rotor unmanned aerial vehicle according to the present invention;
fig. 4 is the utility model provides a four rotor unmanned aerial vehicle emergency landing device's the enlarged schematic diagram of C part.
In the figure: 1 unmanned aerial vehicle body, 2 cantilevers, 3 motors, 4 rotors, 5 mounting grooves, 6 threaded rods, 7 mounting panels, 8 fixture blocks, 9 first springs, 10 guard plates, 11 reinforcing plates, 12 pivots, 13 thread bushes, 14 second springs, 15 mounting bushes, 16 igniters, 17 receivers, 18 parachute, 19 protection foot mechanism, 191 landing legs, 192 activity foot, 193 third spring, 194 gyro wheel, 195 first connecting rod, 196 second connecting rod, 20 sensor integrated board.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.
Referring to fig. 1-4, a quad-rotor unmanned aerial vehicle emergency landing device, comprising an unmanned aerial vehicle body 1, a cantilever 2 is fixed on the side surface of the unmanned aerial vehicle body 1, a motor 3 is installed at the bottom of the cantilever 2, an output shaft of the motor 3 penetrates through the cantilever 2 and is connected with a rotor 4, an installation groove 5 is formed at the top of the unmanned aerial vehicle body 1, threaded rods 6 are fixed at two ends of the interior of the installation groove 5, a mounting plate 7 and a clamping block 8 are sleeved on the threaded rods 6 in a sliding manner, a first spring 9 is installed between the clamping block 8 and the installation groove 5, a protection plate 10 is installed at the top of the unmanned aerial vehicle body 1, rotating shafts 12 are rotatably connected at two ends of the protection plate 10, the rotating shafts 12 penetrate through the protection plate 10 and are slidably connected with thread sleeves 13 through splines, the thread sleeves, installation cover 15 is installed to the bottom of mounting panel 7, and installation cover 15 runs through mounting panel 7 and inserts the inside of receiver 17, and the internally mounted of installation cover 15 has some firearm 16, and protection foot mechanism 19 is installed at the both ends of 1 bottom of unmanned aerial vehicle body, and sensor integrated board 20 is installed to the bottom of unmanned aerial vehicle body 1.
In one embodiment, the two ends of the bottom of the protection plate 10 are fixed with reinforcing plates 11, the reinforcing plates 11 are L-shaped mechanisms, and the reinforcing plates 11 are rotatably connected with the rotating shaft 12.
In one embodiment, a second spring 14 is installed between the reinforcing plate 11 and the threaded sleeve 13, and the second spring 14 is sleeved on the rotating shaft 12.
As an embodiment, the protection foot mechanism 19 includes a support leg 191 fixed at the bottom of the drone body 1, a movable foot 192 slidably connected to the bottom of the support leg 191, a roller 194 mounted at the bottom of the movable foot 192, and a third spring 193 mounted between the top of the movable foot 192 and the support leg 191.
In one embodiment, a first link 195 is rotatably connected to a side of the leg 191, a second link 196 is rotatably connected to a side of the first link 195, and the second link 196 is rotatably connected to the movable leg 192.
As an embodiment, the sensor board 20 has an acceleration sensor, a height sensor, a gyroscope, and a barometer mounted therein.
In one embodiment, the parachute 18 is provided with a low intensity explosive inside.
The working principle is as follows: when the device is used, a storage battery in the unmanned aerial vehicle body 1 supplies power to electronic elements in the device, an output shaft of a motor 3 rotates to drive a rotor 4 to rotate, the rotor 4 rotates to enable the unmanned aerial vehicle body 1 to take off and land, an acceleration sensor, a height sensor, a gyroscope and a barometer in a sensor integrated board 20 carry out all-directional monitoring on the flight state of the unmanned aerial vehicle body 1, monitoring data are transmitted to a computer to judge the flight state of the unmanned aerial vehicle body 1, when the unmanned aerial vehicle body 1 loses power, the data transmitted by the acceleration sensor, the height sensor, the gyroscope and the barometer fluctuate greatly, the computer controls an igniter 16 to start, the igniter 16 ignites low-intensity explosives in a parachute 18, gases generated by low-intensity explosive explosion rapidly fill the parachute 18, the low-intensity explosives cannot generate naked flames to ignite the parachute 18, parachute 18 breaks through the central part of guard plate 10 and expands immediately, can reduce the falling speed of unmanned aerial vehicle body 1 fast, at the in-process that falls to the ground, gyro wheel 194 at first contacts ground, gyro wheel 194 drives movable foot 192 and slides and compress third spring 193 in landing leg 191 afterwards, impact force when reducing the tenesmus, when unmanned aerial vehicle body 1 loses power and falls, effectively improve the protection to the electronic component in unmanned aerial vehicle body 1, through changing guard plate 10 after the use, receiver 17 and parachute 18 can use again, the convenience of use is high.
The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.
Claims (7)
1. Four rotor unmanned aerial vehicle emergency landing device, including unmanned aerial vehicle body (1), its characterized in that, cantilever (2) are fixed with to the side of unmanned aerial vehicle body (1), motor (3) are installed to the bottom of cantilever (2), the output shaft of motor (3) runs through cantilever (2) and is connected with rotor (4), mounting groove (5) have been seted up at the top of unmanned aerial vehicle body (1), threaded rod (6) are fixed at the both ends of the inside of mounting groove (5), sliding sleeve has been cup jointed mounting panel (7) and fixture block (8) on threaded rod (6), install first spring (9) between fixture block (8) and mounting groove (5), guard plate (10) is installed at the top of unmanned aerial vehicle body (1), the both ends of guard plate (10) all rotate and are connected with pivot (12), pivot (12) run through guard plate (10) and have thread bush (13) through spline sliding connection, threaded sleeve (13) pass through screw thread and threaded rod (6) threaded connection, the top of mounting panel (7) is fixed with receiver (17), the internally mounted of receiver (17) has parachute (18), installation cover (15) are installed to the bottom of mounting panel (7), installation cover (15) run through mounting panel (7) and insert the inside of receiver (17), the internally mounted of installation cover (15) has some firearm (16), protection foot mechanism (19) are installed at the both ends of unmanned aerial vehicle body (1) bottom, sensor integrated board (20) are installed to the bottom of unmanned aerial vehicle body (1).
2. The emergency landing device of a quad-rotor unmanned aerial vehicle according to claim 1, wherein reinforcing plates (11) are fixed to two ends of the bottom of the protection plate (10), the reinforcing plates (11) are L-shaped mechanisms, and the reinforcing plates (11) are rotatably connected to the rotating shaft (12).
3. The emergency landing device of a quad-rotor unmanned aerial vehicle according to claim 2, wherein a second spring (14) is installed between the reinforcing plate (11) and the thread bush (13), and the second spring (14) is sleeved on the rotating shaft (12).
4. The emergency landing device of a quad-rotor Unmanned Aerial Vehicle (UAV) according to claim 1, wherein the protection leg mechanism (19) comprises a leg (191) fixed to the bottom of the UAV body (1), a movable leg (192) is slidably connected to the bottom of the leg (191), a roller (194) is installed on the bottom of the movable leg (192), and a third spring (193) is installed between the top of the movable leg (192) and the leg (191).
5. Emergency landing gear of a quad-rotor unmanned aerial vehicle according to claim 4, wherein a first link (195) is rotatably connected to the side of the leg (191), a second link (196) is rotatably connected to the side of the first link (195), and the second link (196) is rotatably connected to the movable leg (192).
6. Quad-rotor unmanned aerial vehicle emergency landing device according to claim 1, wherein the sensor board (20) has acceleration sensors, altitude sensors, gyroscopes and barometers mounted inside.
7. A quad-rotor unmanned aerial vehicle emergency landing gear according to claim 1, wherein the parachute (18) is internally provided with low-intensity explosive.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022591084.4U CN213323665U (en) | 2020-11-11 | 2020-11-11 | Emergency landing device for quad-rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022591084.4U CN213323665U (en) | 2020-11-11 | 2020-11-11 | Emergency landing device for quad-rotor unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN213323665U true CN213323665U (en) | 2021-06-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202022591084.4U Expired - Fee Related CN213323665U (en) | 2020-11-11 | 2020-11-11 | Emergency landing device for quad-rotor unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117885934A (en) * | 2024-03-15 | 2024-04-16 | 中飞艾维航空科技(苏州)有限公司 | Unmanned aerial vehicle power loss emergency equipment |
-
2020
- 2020-11-11 CN CN202022591084.4U patent/CN213323665U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117885934A (en) * | 2024-03-15 | 2024-04-16 | 中飞艾维航空科技(苏州)有限公司 | Unmanned aerial vehicle power loss emergency equipment |
| CN117885934B (en) * | 2024-03-15 | 2024-05-17 | 中飞艾维航空科技(苏州)有限公司 | Unmanned aerial vehicle power loss emergency equipment |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20210601 Termination date: 20211111 |
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| CF01 | Termination of patent right due to non-payment of annual fee |