CN114671022A - Unmanned aerial vehicle with descending buffer device - Google Patents
Unmanned aerial vehicle with descending buffer device Download PDFInfo
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- CN114671022A CN114671022A CN202210339336.5A CN202210339336A CN114671022A CN 114671022 A CN114671022 A CN 114671022A CN 202210339336 A CN202210339336 A CN 202210339336A CN 114671022 A CN114671022 A CN 114671022A
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- unmanned aerial
- aerial vehicle
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- 238000009434 installation Methods 0.000 claims abstract description 31
- 230000001133 acceleration Effects 0.000 claims abstract description 17
- 230000003139 buffering effect Effects 0.000 claims description 10
- 235000017166 Bambusa arundinacea Nutrition 0.000 description 8
- 235000017491 Bambusa tulda Nutrition 0.000 description 8
- 241001330002 Bambuseae Species 0.000 description 8
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 8
- 239000011425 bamboo Substances 0.000 description 8
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 5
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000008602 contraction Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 238000013016 damping Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- 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
- B64D17/00—Parachutes
- B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
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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
- B64U70/80—Vertical take-off or landing, e.g. using rockets
- B64U70/83—Vertical take-off or landing, e.g. using rockets using parachutes, balloons or the like
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle with a landing buffer device, wherein a high-pressure gas storage tank is fixedly connected with the bottom of an unmanned aerial vehicle body, two trigger units are fixedly arranged on two opposite sides of the high-pressure gas storage tank respectively, each trigger unit comprises an installation cylinder, a first piston block and a parachute, a cavity is formed in the installation cylinder, one end of the installation cylinder is open, the other end of the installation cylinder is fixedly connected with the high-pressure gas storage tank, the other end of the installation cylinder is communicated with a gas outlet pipe of the high-pressure gas storage tank through an electric control valve, the first piston block is arranged in the installation cylinder in a sliding mode, the parachute is arranged in the cavity and is fixedly connected with one side of the first piston block, a microprocessor and an acceleration sensor are fixedly arranged on the high-pressure gas storage tank, and the microprocessor is electrically connected with the acceleration sensor and the electric control valve respectively. The problem of current unmanned aerial vehicle electric energy exhaust or receive when striking, unmanned aerial vehicle easily falls and damages from the high altitude is solved.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle with a landing buffer device.
Background
A drone is an unmanned aircraft that is operated with a radio remote control device and self-contained program control, or is operated autonomously, either completely or intermittently, by an onboard computer.
In current patent application No. 201710646471.3's patent document, a scalable comprehensive protection device of unmanned aerial vehicle is disclosed, and specifically disclose including flight control computer and frame, including a motor, an end cap, a controller, and a cover plate, the rotor, the flight control computer is rectangular structure, all be provided with the frame on four vertical edges of flight control computer, the tip of frame is provided with the motor, the top of motor is provided with the rotor, shell outside surface intermediate position be provided with the fender rod, flight control settlement machine top intermediate position is provided with the fender rod, the bottom and the motor of fender rod, the shell of flight control computer can be dismantled and be connected, the top lateral surface of fender rod is provided with the screw thread, the top of fender rod is provided with the link, the link is the type structure of falling T, set up connecting screw hole on the intermediate side surface of link, connecting screw hole and fender rod top threaded connection.
Through the above scheme, can reduce unmanned aerial vehicle and receive the striking and the degree of damaging at the flight in-process, but, when the electric energy in the unmanned aerial vehicle exhausts, the unmanned aerial vehicle chance is free falling body motion and falls, scalable comprehensive protection device just loses the guard action, and unmanned aerial vehicle easily falls and damages, reduces unmanned aerial vehicle's life.
Disclosure of Invention
In view of this, it is necessary to provide an unmanned aerial vehicle with a landing buffer device, so as to solve the problem that the existing unmanned aerial vehicle is easy to fall from high altitude and be damaged when the electric energy of the unmanned aerial vehicle is exhausted or the unmanned aerial vehicle is impacted.
The invention provides an unmanned aerial vehicle with a landing buffer device, which comprises
The unmanned aerial vehicle comprises an unmanned aerial vehicle body, and a high-pressure gas storage tank fixedly connected with the bottom of the unmanned aerial vehicle body;
the trigger units are respectively fixedly arranged on two opposite sides of the high-pressure gas storage box and comprise an installation cylinder, a first piston block and a parachute, wherein a cavity is formed in the installation cylinder, one end of the installation cylinder is opened, the other end of the installation cylinder is fixedly connected with the high-pressure gas storage box, the other end of the installation cylinder is communicated with a gas outlet pipe of the high-pressure gas storage box through an electric control valve, the first piston block is arranged in the installation cylinder in a sliding mode, and the parachute is arranged in the cavity and is fixedly connected with one side, close to the opening end, of the first piston block;
the control unit comprises a microprocessor and an acceleration sensor which are fixedly arranged on the high-pressure gas storage box, the microprocessor is electrically connected with the acceleration sensor and the electric control valve respectively, and the microprocessor controls the electric control valve to be opened so that gas in the high-pressure gas storage box is conveyed to the mounting cylinder to push the first piston block to pop up the parachute.
Specifically, a first elastic piece is arranged in the mounting cylinder, one end of each first elastic piece is fixedly connected with the inner wall of the other end of the mounting cylinder, and the other end of each first elastic piece is fixedly connected with the other side of the first piston block.
Specifically, the inner wall of the mounting cylinder is provided with a limit ring block correspondingly blocked with one side of the first piston block.
Specifically, a vent hole is formed in the middle of the first piston block, and the inner diameter of the vent hole is 1-2 mm.
Specifically, the bottom of high pressure gas storage box is provided with two support frames that are used for reducing unmanned aerial vehicle body and ground striking symmetrically.
Specifically, the device also comprises at least one buffer unit which is fixedly arranged at the bottom of the high-pressure air storage box and is positioned between the two support frames.
Specifically, the buffer unit includes the buffer cylinder with high-pressure gas receiver bottom fixed connection, slides second piston piece, piston rod and the second elastic component that sets up in the buffer cylinder, the one end of piston rod extend to in the buffer cylinder with one side fixed connection of second piston piece, it is a plurality of the second elastic component sets up in the buffer cylinder, and is a plurality of the one end of second elastic component and the interior roof fixed connection of buffer cylinder, the other end with the opposite side fixed connection of second piston piece, through the other end and the ground contact compression of piston rod are a plurality of the second elastic component carries out the damping.
Specifically, the other end of the piston rod is provided with a buffer air bag.
Specifically, the buffer unit further comprises a driving motor arranged at the bottom of the high-pressure air storage box, and an output shaft of the driving motor is fixedly arranged on the rotating blade.
Specifically, high pressure gas receiver is via connecting piece and unmanned aerial vehicle body fixed connection, the connecting piece includes the connecting rod and sets firmly in the connecting block at the relative both ends of connecting rod, wherein, one the bottom fixed connection of connecting block and unmanned aerial vehicle body, another connecting block and high pressure gas receiver fixed connection.
The beneficial effects of the invention are:
(1) the invention provides an unmanned aerial vehicle with a landing buffer device, wherein the triggering units are arranged on two opposite sides of a high-pressure gas storage tank, an acceleration sensor converts the acceleration of the unmanned aerial vehicle during falling into an electric signal and transmits the electric signal to a microprocessor, the microprocessor controls the opening of an electric control valve, high-pressure gas in the high-pressure gas storage tank enters a mounting cylinder to push a first piston block to slide, and the first piston block can push a parachute out of the mounting cylinder instantly, so that the falling speed of the unmanned aerial vehicle is reduced, the unmanned aerial vehicle is prevented from falling from high altitude and being damaged, and the service life of the unmanned aerial vehicle is prolonged.
(2) The invention provides an unmanned aerial vehicle with a landing buffer device, when a trigger unit is not used, a parachute is arranged in an installation cylinder in a contraction state, the flight resistance of the unmanned aerial vehicle can be reduced, and the consumption of electric energy is reduced.
Drawings
The invention is further illustrated with reference to the following figures and examples.
Fig. 1 is a schematic structural view of an unmanned aerial vehicle with a landing buffer device according to the present invention;
figure 2 is a front view of an unmanned aerial vehicle having a landing gear of the present invention;
fig. 3 is a reference view of a state of use of an unmanned aerial vehicle having a landing buffer device according to the present invention;
FIG. 4 is an enlarged schematic view of A in FIG. 3;
fig. 5 is a schematic view of the installation of the buffer unit of the present invention.
Detailed Description
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate preferred embodiments of the invention and together with the description, serve to explain the principles of the invention and not to limit the scope of the invention.
The invention provides an unmanned aerial vehicle with a landing buffer device, which comprises an unmanned aerial vehicle body 1, a trigger unit 2 and a control unit 3, wherein the trigger unit 2 and the control unit 3 are both arranged on the unmanned aerial vehicle body 1, when the unmanned aerial vehicle body 1 falls from high altitude due to the exhaustion of electric energy or impact and the like, the control unit 3 can control the trigger unit 2 to be started, so that the falling speed of the unmanned aerial vehicle body 1 can be reduced, and the damage of the unmanned aerial vehicle body 1 can be prevented as much as possible.
More specifically, in this embodiment, the high pressure gas tank 11 is fixedly connected to the bottom of the unmanned aerial vehicle body 1, wherein the high pressure gas tank 11 is fixedly connected to the unmanned aerial vehicle body 1 via a connecting member 13, the connecting member 13 includes a connecting rod 131 and connecting blocks 132 fixedly disposed at two opposite ends of the connecting rod 131, one of the connecting blocks 132 is fixedly connected to the bottom of the unmanned aerial vehicle body 1, the other connecting block 132 is fixedly connected to the high pressure gas tank 11, and the high pressure gas tank 11 is filled with high pressure gas.
The two trigger units 2 are respectively and fixedly arranged on two opposite sides of the high-pressure gas storage tank 11, and the two trigger units 2 are symmetrically arranged on two opposite sides of the high-pressure gas storage tank 11, so that the flight balance of the unmanned aerial vehicle body 1 is ensured.
It should be noted that, trigger unit 2 includes that inside has a cavity and one end open-ended installation section of thick bamboo 21, first piston block 22 and parachute 23, the other end and the 11 fixed connection of high-pressure gas storage tank of installation section of thick bamboo 21, just the other end of installation section of thick bamboo 21 is linked together via the outlet duct of automatically controlled valve and high-pressure gas storage tank 11, first piston block 22 slides and sets up in installation section of thick bamboo 21, parachute 23 sets up in the cavity and is close to one side fixed connection of open end with first piston block 22, at this moment, parachute 23 is the contraction state, and small can not increase unmanned aerial vehicle body 1's flight resistance.
In this embodiment, the control unit 3 includes microprocessor 31 and acceleration sensor 32 that set firmly on high-pressure gas storage tank 11, microprocessor 31 respectively with acceleration sensor 32 and electric control valve electric connection, still be provided with independent electric power unit on the outer wall of high-pressure gas storage tank 11, electric power unit is used for supplying power to microprocessor 31 and acceleration sensor 32, when acceleration sensor receives the speed that descends and is 5m/S, through the opening of microprocessor 31 control electric control valve, supply in the gas in high-pressure gas storage tank 11 is carried to installation section of thick bamboo 21 and is pushed first piston piece 22 in order to pop out parachute 23, wherein microprocessor 31 'S signal is STM8S208C8T6, and acceleration sensor 32' S model is ADXL 345.
On the basis of the above scheme, be provided with first elastic component 24 in the installation section of thick bamboo 21, a plurality of the one end of first elastic component 24 and the inner wall fixed connection of the installation section of thick bamboo 21 other end, the other end with the opposite side fixed connection of first piston piece 22, first elastic component 24 is compression spring, first piston piece 22 can slide to initial position under the effect of first elastic component 24, is convenient for retrieve parachute 23 in installation section of thick bamboo 21.
In order to prevent the first piston block from falling out of the mounting cylinder, more specifically, the inner wall of the mounting cylinder 21 is provided with a limit ring block 211 which is blocked correspondingly to one side of the first piston block 22.
On the basis of the above scheme, a push rod is arranged in the middle of the first piston block 22, one end of the parachute is fixedly connected with the push rod, the parachute 23 can be pushed out of the installation barrel 21 by the first piston block 22 through the push rod, at least one vent hole is arranged on the first piston block 22, the inner diameter of the vent hole is 1-2mm, in the present embodiment, the inner diameter of the vent hole is 1mm, and after the parachute 23 is pushed out by the first piston block 22, high-pressure gas escapes from the vent hole, so that the first piston block 22 returns to the initial position under the action of the first elastic member 24. Since the rope of the parachute 23 is long enough, the first piston block 22 does not affect the parachute 23 during the drawing back of the first elastic member 24.
In order to reduce the impact that receives when the unmanned aerial vehicle body contacts ground, the bottom symmetry of high pressure gas tank 11 is provided with two support frames 12 that supply in reducing unmanned aerial vehicle body 1 and ground striking. Further, the device also comprises at least one buffer unit 4 which is fixedly arranged at the bottom of the high-pressure air storage tank 11 and is positioned between the two support frames 12.
In this embodiment, the buffer unit 4 includes a buffer cylinder 41 fixedly connected to the bottom of the high pressure gas storage tank 11, a second piston block 42, a piston rod 43 and a second elastic member 44 slidably disposed in the buffer cylinder 41, one end of the piston rod 43 extends into the buffer cylinder 41 and is fixedly connected to one side of the second piston block 42, and is a plurality of the second elastic member 44 is disposed in the buffer cylinder 41, and is a plurality of one end of the second elastic member 44 is fixedly connected to the inner top wall of the buffer cylinder 41, and the other end is fixedly connected to the other side of the second piston block 42, and the second elastic member 44 is compressed by the other end of the piston rod 43 in contact with the ground to reduce the vibration.
In order to further reduce the impact that receives when the unmanned aerial vehicle body contacts ground, the other end of piston rod 43 is provided with buffering gasbag 45, furtherly, buffer unit 4 still includes the driving motor 46 who sets up in high-pressure gas storage tank 11 bottom, set firmly in rotating vane on driving motor 46's the output shaft. When the unmanned aerial vehicle body descends, the rotating blades rotate, so that the descending speed of the unmanned aerial vehicle body 1 can be further reduced by the airflow from the upstream to the upstream, and the impact on the unmanned aerial vehicle body 1 when the unmanned aerial vehicle body contacts the ground can be reduced.
In the using process, when the unmanned aerial vehicle body 1 falls, the acceleration sensor 32 converts the acceleration of the unmanned aerial vehicle when falling into an electric signal and transmits the electric signal to the microprocessor 31, the microprocessor 31 controls the opening of the electric control valve, high-pressure gas in the high-pressure gas storage tank 11 enters the mounting cylinder 21 to push the first piston block 22 to slide, the first piston block 22 can instantly push the parachute 23 out of the mounting cylinder 21, and the falling speed of the unmanned aerial vehicle body 1 is reduced under the action of the two parachutes 23; when the unmanned aerial vehicle body 1 is to be in contact with the ground, the driving motor 46 drives the rotating blades to rotate, so that the airflow from the upstream to the top can further reduce the descending speed of the unmanned aerial vehicle body 1, at the moment, the buffering air bag 45 is in contact with the ground, so that the piston rod 43 pushes the second piston block 42 to compress the second elastic piece 44 for vibration reduction, and the two supporting frames 12 are ensured to stably fall on the ground.
The beneficial effects of the invention are:
the invention provides an unmanned aerial vehicle with a landing buffer device, wherein the triggering units are arranged on two opposite sides of a high-pressure gas storage tank, an acceleration sensor converts the acceleration of the unmanned aerial vehicle during falling into an electric signal and transmits the electric signal to a microprocessor, the microprocessor controls the opening of an electric control valve, high-pressure gas in the high-pressure gas storage tank enters a mounting cylinder to push a first piston block to slide, and the first piston block can push a parachute out of the mounting cylinder instantly, so that the falling speed of the unmanned aerial vehicle is reduced, the unmanned aerial vehicle body is prevented from falling from high altitude and being damaged, and the service life of the unmanned aerial vehicle is prolonged.
While the invention has been described with reference to specific preferred embodiments, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention as defined in the following claims.
Claims (10)
1. Unmanned aerial vehicle with descending buffer device, which is characterized by comprising
The unmanned aerial vehicle comprises an unmanned aerial vehicle body, and a high-pressure gas storage tank fixedly connected with the bottom of the unmanned aerial vehicle body;
the trigger units are respectively fixedly arranged on two opposite sides of the high-pressure gas storage box and comprise an installation cylinder, a first piston block and a parachute, wherein a cavity is formed in the installation cylinder, one end of the installation cylinder is opened, the other end of the installation cylinder is fixedly connected with the high-pressure gas storage box, the other end of the installation cylinder is communicated with a gas outlet pipe of the high-pressure gas storage box through an electric control valve, the first piston block is arranged in the installation cylinder in a sliding mode, and the parachute is arranged in the cavity and is fixedly connected with one side, close to the opening end, of the first piston block;
the control unit comprises a microprocessor and an acceleration sensor which are fixedly arranged on the high-pressure gas storage box, the microprocessor is electrically connected with the acceleration sensor and the electric control valve respectively, and the microprocessor controls the electric control valve to be opened so that gas in the high-pressure gas storage box is conveyed to the mounting cylinder to push the first piston block to pop up the parachute.
2. An unmanned aerial vehicle with a landing buffering device according to claim 1, wherein a first elastic part is arranged in the installation cylinder, one end of the first elastic parts is fixedly connected with the inner wall of the other end of the installation cylinder, and the other end of the first elastic parts is fixedly connected with the other side of the first piston block.
3. An unmanned aerial vehicle with a landing buffering device as claimed in claim 1, wherein the inner wall of the mounting cylinder is provided with a stop ring block correspondingly blocked with one side of the first piston block.
4. An unmanned aerial vehicle with a landing buffering device as claimed in claim 1, wherein a vent hole is arranged in the middle of the first piston block, and the inner diameter of the vent hole is 1-2 mm.
5. An unmanned aerial vehicle with landing buffer device as claimed in claim 1, wherein the bottom of the high pressure gas storage tank is symmetrically provided with two support frames for reducing the impact between the unmanned aerial vehicle body and the ground.
6. An unmanned aerial vehicle with landing buffer device as claimed in claim 5, further comprising at least one buffer unit fixed to the bottom of the high pressure gas storage tank and located between the two support frames.
7. The unmanned aerial vehicle with landing buffer device of claim 6, wherein the buffer unit comprises a buffer cylinder fixedly connected with the bottom of the high-pressure air tank, a second piston block, a piston rod and a second elastic part, the second piston block, the piston rod and the second elastic part are slidably arranged in the buffer cylinder, one end of the piston rod extends into the buffer cylinder and is fixedly connected with one side of the second piston block, the second elastic part is arranged in the buffer cylinder and is a plurality of, one end of the second elastic part is fixedly connected with the inner top wall of the buffer cylinder, the other end of the second elastic part is fixedly connected with the other side of the second piston block, and the second elastic part is subjected to vibration reduction by compressing the other end of the piston rod with the ground.
8. An unmanned aerial vehicle with landing buffering device as claimed in claim 7, wherein the other end of the piston rod is provided with a buffering air bag.
9. The unmanned aerial vehicle with the landing buffering device as claimed in claim 6, wherein the buffering unit further comprises a driving motor disposed at the bottom of the high-pressure air tank, and an output shaft of the driving motor is fixedly disposed on the rotating blade.
10. The unmanned aerial vehicle with the landing buffering device as claimed in claim 1, wherein the high-pressure gas tank is fixedly connected with the unmanned aerial vehicle body through a connecting piece, the connecting piece comprises a connecting rod and connecting blocks fixedly arranged at two opposite ends of the connecting rod, one of the connecting blocks is fixedly connected with the bottom of the unmanned aerial vehicle body, and the other connecting block is fixedly connected with the high-pressure gas tank.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210339336.5A CN114671022A (en) | 2022-04-01 | 2022-04-01 | Unmanned aerial vehicle with descending buffer device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210339336.5A CN114671022A (en) | 2022-04-01 | 2022-04-01 | Unmanned aerial vehicle with descending buffer device |
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| Publication Number | Publication Date |
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| CN114671022A true CN114671022A (en) | 2022-06-28 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210339336.5A Pending CN114671022A (en) | 2022-04-01 | 2022-04-01 | Unmanned aerial vehicle with descending buffer device |
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| CN110171561A (en) * | 2019-06-24 | 2019-08-27 | 焦佳敏 | A kind of unmanned plane pushing stable landing based on reversed air pressure |
| CN210364381U (en) * | 2019-07-02 | 2020-04-21 | 詹恭强 | Security protection unmanned aerial vehicle |
| CN211364949U (en) * | 2019-12-17 | 2020-08-28 | 广东中东测绘科技有限公司 | Laser radar aerial survey aircraft |
| CN113453983A (en) * | 2019-02-19 | 2021-09-28 | 美蓓亚三美株式会社 | Parachute device, flying device, and flying body launching mechanism |
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2022
- 2022-04-01 CN CN202210339336.5A patent/CN114671022A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104118564A (en) * | 2014-07-21 | 2014-10-29 | 张行晔 | Safety protection system of aircraft with multiple rotor wings |
| CN207157553U (en) * | 2017-06-27 | 2018-03-30 | 中国人民解放军第三军医大学 | A kind of automatic-opening parachute assembly |
| CN108177782A (en) * | 2018-02-05 | 2018-06-19 | 天津曙光天成科技有限公司 | Unmanned helicopter parachute trigger mechanism and unmanned helicopter |
| CN108891217A (en) * | 2018-07-04 | 2018-11-27 | 天津超算科技有限公司 | Automobile aerocraft |
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