CN112124584A

CN112124584A - Six wing unmanned aerial vehicle of diversified scram that fall to ground

Info

Publication number: CN112124584A
Application number: CN202010982549.0A
Authority: CN
Inventors: 周光斌
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-09-17
Filing date: 2020-09-17
Publication date: 2020-12-25

Abstract

The invention belongs to the technical field of unmanned aerial vehicles, in particular to a multi-azimuth landing scram six-wing unmanned aerial vehicle, which aims at solving the problems that the existing unmanned aerial vehicle has long landing time when landing, and easily collides with other objects on the landing surface to damage parts of the unmanned aerial vehicle on landing surfaces with small areas due to overlong sliding. According to the invention, after the unmanned aerial vehicle touches the ground, the direction sensor detects the sliding direction of the unmanned aerial vehicle, so that the plurality of micro servo motors drive the rollers to roll in different directions, the force applied to the unmanned aerial vehicle in the direction opposite to the original sliding direction is increased, and the emergency stop of the unmanned aerial vehicle is realized.

Description

Six wing unmanned aerial vehicle of diversified scram that fall to ground

Technical Field

The invention relates to the technical field of unmanned aerial vehicles, in particular to a multi-azimuth landing scram six-wing unmanned aerial vehicle.

Background

The unmanned plane is called an unmanned plane for short, can complete aerial photography, reconnaissance and other affairs, and is controlled by a remote controller arranged on the ground. Generally divided into four-wing drones and six-wing drones.

The ground control station is to unmanned aerial vehicle's remote control, and the general use is the special remote controller of unmanned aerial vehicle, is provided with control center in the remote controller usually, and the operation button of user direct operation control center usually controls operations such as unmanned aerial vehicle's takeoff, landing or return journey. If the remote controller wants to control the unmanned aerial vehicle, the remote controller and the unmanned aerial vehicle must be successfully paired firstly. The popular explanation is to let the remote control and the drone know each other. In the existing pairing method of the remote controller and the unmanned aerial vehicle, a user needs to transfer the remote controller to a pairing communication channel special for pairing, then the unmanned aerial vehicle is powered on, and the unmanned aerial vehicle is transferred to the pairing communication channel same as the remote controller, so that the remote controller and the unmanned aerial vehicle enter a pairing state at the same time.

Current unmanned aerial vehicle is when falling to the ground, and the buffering effect is not good, and the impact force that receives when falling to the ground in order to reduce unmanned aerial vehicle can make it slide one section and then stop, but so can prolong unmanned aerial vehicle's the time of stopping to fall, in addition, on the less stopping and falling surface of some areas, slide the overlength then easily with stop other objects on the falling surface and bump, damage the unmanned aerial vehicle part.

Disclosure of Invention

Based on the technical problems that the existing unmanned aerial vehicle has long stopping and falling time when falling to the ground, and is easy to collide with other objects on a stopping and falling surface to damage parts of the unmanned aerial vehicle on the stopping and falling surface when the existing unmanned aerial vehicle slides too long on the stopping and falling surface with a small area, the invention provides the multi-azimuth landing scram six-wing unmanned aerial vehicle.

The invention provides a multidirectional landing scram six-wing unmanned aerial vehicle which comprises an unmanned aerial vehicle body, wherein the side end of the unmanned aerial vehicle body is uniformly connected with six propellers through a rack, an annular fixing frame is sleeved on the outer side of the unmanned aerial vehicle body, a plurality of supporting columns are fixedly connected between the annular fixing frame and the side end of the unmanned aerial vehicle body, the supporting columns are uniformly distributed on the inner side of the annular fixing frame, the lower ends of the supporting columns are fixedly connected with buffering legs, the lower ends of the buffering legs are connected with idler wheels, power mechanisms are fixedly connected onto the buffering legs, and the lower end of.

Preferably, the buffering leg includes and, upper end and support column fixed connection, sliding connection is inboard, and fixedly connected with compression spring between with, fixed connection is in the lower extreme, power unit and gyro wheel all connect in last.

Preferably, the power mechanism comprises a micro servo motor, the micro servo motor is fixedly connected to the outer wall, and an output shaft of the micro servo motor penetrates through and is fixedly connected with a wheel shaft of the roller.

Preferably, the power mechanism comprises a micro servo motor, a driven gear, an intermediate gear and a driving gear, the micro servo motor is fixedly connected to the inner wall, the driving gear is fixedly connected to an output shaft end of the micro servo motor, the driven gear is fixedly connected to a wheel shaft of the roller, the intermediate gear is located between the driven gear and the driving gear and is meshed with the driven gear and the driving gear, and the intermediate gear is rotatably connected with the inner wall.

Preferably, the frame is an electric telescopic rod.

Preferably, the aerial buoyancy box of unmanned aerial vehicle fuselage upper end fixedly connected with, the inboard first gasbag of fixedly connected with of aerial buoyancy box, unmanned aerial vehicle fuselage upper end fixedly connected with air pump and gravity acceleration sensor GV-sensor, and be connected with the air duct between the output of air pump and the first gasbag.

Preferably, unmanned aerial vehicle fuselage lower extreme fixedly connected with contact buffering box, and contact buffering box inboard fixedly connected with second gasbag, be connected with the air duct between the output of second gasbag and air pump equally.

Preferably, the contact buffer box and the air buoyancy box are both hinged with sealing covers, and the contact buffer box, the air buoyancy box and the sealing covers are both fixedly connected with matched magnetic force adsorption sheets.

Preferably, the first balloon has a greater modulus of elasticity than the second balloon, and the first balloon has an inflated volume that is twice the inflated volume of the second balloon at the same time.

The beneficial effects of the invention are as follows:

1. this six wing unmanned aerial vehicle of diversified scram that falls to ground, direction sensor through setting up, the buffering leg, the gyro wheel and the power unit of connecting on the gyro wheel, after touching to the ground, utilize the inside controller of taking certainly of unmanned aerial vehicle to detect unmanned aerial vehicle's slip direction according to direction sensor and control a plurality of miniature servo motor drive gyro wheels and carry out the ascending roll of equidirectional not for unmanned aerial vehicle increases it and receives the power opposite with former slip direction, thereby realizes unmanned aerial vehicle's scram.

2. This six wing unmanned aerial vehicle of diversified scram that falls to ground, through the aerial buoyancy box of fixed connection in unmanned aerial vehicle fuselage upper end, and at the first gasbag of the inboard fixed connection of aerial buoyancy box, at unmanned aerial vehicle fuselage upper end fixed connection air pump and gravity acceleration sensor, when unmanned aerial vehicle accident falls, the air pump is aerifyd in passing through the air duct to first gasbag for first gasbag is opened, and unmanned aerial vehicle can reduce the speed of falling greatly under the buoyancy effect that first gasbag falls, improves the security under the unmanned aerial vehicle condition.

3. This six wing unmanned aerial vehicle of diversified scram that falls to ground, through at unmanned aerial vehicle fuselage lower extreme fixed connection contact buffering box, and at the inboard fixed connection second gasbag of contact buffering box, when unmanned aerial vehicle accident falls, the second gasbag is opened and to be combined the buffering leg and further strengthen the buffering effect that contacts to the earth.

4. This six wing unmanned aerial vehicle of diversified scram that falls to ground sets up the elastic coefficient for being greater than the second gasbag through the elastic coefficient with first gasbag, and the inflation volume of first gasbag is the twice of the inflation volume of second gasbag at the same moment, under the state that first gasbag and second gasbag all opened, can keep this unmanned aerial vehicle vertical stability whereabouts.

5. This six wing unmanned aerial vehicle of diversified scram that falls to ground, when unmanned aerial vehicle stopped falling, the ground can produce great vibrations in the twinkling of an eye of gyro wheel, through the setting of driven gear, intermediate gear and driving gear, can reduce with miniature servo motor's direct impact, reduces the damage that causes miniature servo motor, is favorable to miniature servo motor to stabilize the function.

The parts which are not involved in the device are the same as or can be realized by adopting the prior art, and the invention can lead the plurality of micro servo motors to drive the rollers to roll in different directions according to the sliding direction of the unmanned aerial vehicle detected by the direction sensor after the unmanned aerial vehicle contacts the ground, thereby leading the unmanned aerial vehicle to increase the force which is opposite to the original sliding direction and further realizing the emergency stop of the unmanned aerial vehicle.

Drawings

Fig. 1 is a schematic structural view of a multi-azimuth landing scram six-wing unmanned aerial vehicle provided by the invention in a normal flight state;

fig. 2 is a schematic structural diagram of an early stage of the multi-azimuth landing scram six-wing unmanned aerial vehicle in an out-of-control state, according to the invention;

fig. 3 is a schematic structural diagram of a later stage of the multi-azimuth landing scram six-wing unmanned aerial vehicle in an out-of-control state, according to the invention;

fig. 4 is a schematic structural view of a buffering leg of the multi-azimuth landing scram six-wing drone provided by the invention;

fig. 5 is an exploded view of the buffering legs of the multi-azimuth landing scram six-wing drone provided by the invention.

In the figure: the unmanned aerial vehicle comprises an unmanned aerial vehicle body 1, a machine frame 2, a propeller 3, a 4-ring-shaped fixing frame, a supporting column 5, a buffering leg 6, a wheel frame 61, a buffering rod 62, a buffering sleeve 63, a roller 7, a contact buffering box 8, an aerial buoyancy box 9, a first air bag 10, a second air bag 11, a magnetic adsorption sheet 12, a sealing cover 13, an air pump 14, an air duct 15, a miniature servo motor 16, a driven gear 17, an intermediate gear 18, a driving gear 19, a compression spring 20 and a gravity acceleration sensor 21.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.

Example 1

Referring to fig. 1-3, a six wing unmanned aerial vehicle of diversified scram that fall to ground, including the unmanned aerial vehicle fuselage 1 that the side has six screws 3 through frame 2 evenly connected, 1 outside cover of unmanned aerial vehicle fuselage is equipped with annular mount 4, a plurality of support columns 5 of fixedly connected with between annular mount 4 and the 1 side of unmanned aerial vehicle fuselage, and a plurality of support columns 5 evenly distributed is 4 inboards in annular mount, support column 5 lower extreme fixed connection buffering leg 6, and the 6 lower extremes of buffering leg are connected with gyro wheel 7, fixedly connected with power unit on the

buffering leg

6, 1 lower extreme of unmanned aerial vehicle fuselage is connected with directional sensor.

According to the invention, the buffering legs 6 comprise 61, 62 and 63, the upper ends of 63 are fixedly connected with the supporting

columns

5, 61 is slidably connected to the inner side of 63, compression springs 20 are fixedly connected between 62 and 61, 61 is fixedly connected to the lower end of 62, and the power mechanism and the rollers 7 are connected to 61.

The power mechanism comprises a micro servo motor 16, the micro servo motor 16 is fixedly connected to the outer wall of the roller 61, and an output shaft of the micro servo motor 16 penetrates through the roller 61 and is fixedly connected with a wheel shaft of the roller 7.

Wherein, frame 2 is electric telescopic handle, is convenient for accomodate screw 3 when idle, reduces whole unmanned aerial vehicle's area, and is difficult for the rupture when the transportation.

Wherein, the aerial buoyancy box 9 of 1 upper end fixedly connected with of unmanned aerial vehicle fuselage, the first gasbag 10 of the inboard fixedly connected with of

aerial buoyancy box

9, 1 upper end fixedly connected with air pump 14 of unmanned aerial vehicle fuselage and acceleration of gravity sensor 21, GV-sensor can be chooseed for use to acceleration of gravity sensor 21, be connected with air duct 15 between the output of air pump 14 and the first gasbag 10, when unmanned aerial vehicle accident falls, air pump 14 aerifys in to first gasbag 10 through air duct 15, make first gasbag 10 open, unmanned aerial vehicle can reduce the speed of falling greatly under the buoyancy of first gasbag 10, improve the security under the unmanned aerial vehicle condition of falling.

Wherein, 1 lower extreme fixedly connected with contact buffering box 8 of unmanned aerial vehicle fuselage, and the inboard fixedly connected with second gasbag 11 of contact buffering box 8, be connected with air duct 15 between the output of second gasbag 11 and air pump 14 equally, when unmanned aerial vehicle accident falls, second gasbag 11 is opened and to be combined buffering leg 6 and further strengthen the buffering effect of touching to the ground.

Wherein, all articulated on contact buffer box 8 and the aerial buoyancy box 9 have sealed lid 13, avoid external dust and impurity to get into in contact buffer box 8 and the aerial buoyancy box 9, contact buffer box 8 and aerial buoyancy box 9 and sealed lid 13 go up equal fixedly connected with assorted magnetic force adsorption piece 12, can keep sealed lid 13 stable seal, be difficult for receiving external resistance accident to open.

Wherein, the elastic coefficient of first gasbag 10 is greater than the elastic coefficient of second gasbag 11, and the inflation volume of first gasbag 10 is twice of the inflation volume of second gasbag 11 at the same moment, under the state that first gasbag 10 and second gasbag 11 are all opened, can keep this unmanned aerial vehicle vertical stability whereabouts.

The working principle is as follows: when the unmanned aerial vehicle accidentally falls, the gravity acceleration sensor 21 detects that the falling speed exceeds a manual preset threshold value, at the moment, the air pump 14 is controlled to be opened through the unmanned aerial vehicle internal controller, the air pump 14 inflates air into the first air bag 10 through the air duct 15, so that the first air bag 10 is opened, the falling speed of the unmanned aerial vehicle can be greatly reduced under the buoyancy action of the first air bag 10, the safety of the unmanned aerial vehicle in the falling condition is improved, meanwhile, the air pump 14 inflates air into the second air bag 11 through the air duct 15, the buffering leg 6 can play a good buffering effect when the unmanned aerial vehicle contacts the ground, and the second air bag 11 is opened, so that the grounding buffering effect can be further enhanced by combining the buffering; after touchdown, the controller controls a plurality of miniature servo motors 16 to drive the rollers 7 to roll in different directions according to the sliding direction of the unmanned aerial vehicle detected by the direction sensor, so that the unmanned aerial vehicle is increased to be subjected to a force opposite to the original sliding direction, and the emergency stop of the unmanned aerial vehicle is realized.

Example 2

Referring to fig. 4-5, a six wing unmanned aerial vehicle of diversified scram, this embodiment compares in embodiment 1, and power unit includes miniature servo motor 16, driven gear 17, intermediate gear 18 and driving gear 19, and miniature servo motor 16 is fixed connection on 61 inner walls, and driving gear 19 is fixed connection in miniature servo motor 16's output axle head, and driven gear 17 is fixed connection on the shaft of gyro wheel 7, and intermediate gear 18 is located between driven gear 17 and driving gear 19 and meshes with driven gear 17 and driving gear 19 mutually, and intermediate gear 18 rotates with 61 inner walls and is connected.

The working principle is as follows: when unmanned aerial vehicle stops falling, can produce great vibrations in the twinkling of an eye on gyro wheel 7 ground, through driven gear 17, intermediate gear 18 and driving gear 19's setting, can reduce with miniature servo motor 16's direct impact, reduce the damage that causes miniature servo motor 16, be favorable to miniature servo motor 16 to stabilize the function.

It should be further noted that the electrical control method used in this document is automatically controlled by a controller and powered by an external power source, and the control circuit of the controller can be implemented by simple programming by those skilled in the art, which belongs to the common knowledge in the art, and this application mainly serves to protect the mechanical device, so the control method and the circuit connection are not explained in detail in this application.

The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.

Claims

1. The utility model provides a six wing unmanned aerial vehicle of diversified scram, includes unmanned aerial vehicle fuselage (1) that the side passes through frame (2) evenly connected with six screws (3), its characterized in that, unmanned aerial vehicle fuselage (1) outside cover is equipped with annular mount (4), a plurality of support columns of fixedly connected with (5) between annular mount (4) and unmanned aerial vehicle fuselage (1) side, and a plurality of support columns (5) evenly distributed are inboard in annular mount (4), support column (5) lower extreme fixed connection buffering leg (6), and buffering leg (6) lower extreme is connected with gyro wheel (7), fixedly connected with power unit on buffering leg (6), unmanned aerial vehicle fuselage (1) lower extreme is connected with directional sensor.

2. The multi-azimuth landing scram six-wing unmanned aerial vehicle of claim 1, wherein the buffering leg (6) comprises (61), (62) and (63), the upper end of the (63) is fixedly connected with the supporting column (5), the (61) is slidably connected to the inner side of the (63), a compression spring (20) is fixedly connected between the (62) and the (61), the (61) is fixedly connected to the lower end of the (62), and the power mechanism and the roller (7) are both connected to the (61).

3. The multi-azimuth landing scram six-wing unmanned aerial vehicle of claim 2, wherein the power mechanism comprises a micro servo motor (16), the micro servo motor (16) is fixedly connected to the outer wall of the wheel (61), and an output shaft of the micro servo motor (16) penetrates through the wheel (61) and is fixedly connected with an axle of the wheel (7).

4. The multi-azimuth landing scram six-wing unmanned aerial vehicle of claim 2, wherein the power mechanism comprises a micro servo motor (16), a driven gear (17), an intermediate gear (18) and a driving gear (19), the micro servo motor (16) is fixedly connected to the inner wall of the wing (61), the driving gear (19) is fixedly connected to the output shaft end of the micro servo motor (16), the driven gear (17) is fixedly connected to the wheel shaft of the roller (7), the intermediate gear (18) is located between the driven gear (17) and the driving gear (19) and meshed with the driven gear (17) and the driving gear (19), and the intermediate gear (18) is rotatably connected to the inner wall of the wing (61).

5. The multi-azimuth landing scram six-wing drone according to claim 1, characterized in that the frame (2) is an electric telescopic pole.

6. The six-wing multi-azimuth landing scram unmanned aerial vehicle as claimed in claim 1, wherein the unmanned aerial vehicle body (1) is fixedly connected with an aerial buoyancy box (9) at the upper end thereof, a first air bag (10) is fixedly connected to the inner side of the aerial buoyancy box (9), an air pump (14) and a gravitational acceleration sensor (21) GV-sensor are fixedly connected to the upper end of the unmanned aerial vehicle body (1), and an air duct (15) is connected between the output end of the air pump (14) and the first air bag (10).

7. The six-wing multi-azimuth landing scram unmanned aerial vehicle as claimed in claim 6, wherein the lower end of the unmanned aerial vehicle body (1) is fixedly connected with a contact buffer box (8), a second air bag (11) is fixedly connected to the inner side of the contact buffer box (8), and an air duct (15) is also connected between the second air bag (11) and the output end of the air pump (14).

8. The multi-azimuth landing scram six-wing unmanned aerial vehicle as claimed in claim 7, wherein the contact buffer box (8) and the air buoyancy box (9) are hinged with sealing covers (13), and the contact buffer box (8), the air buoyancy box (9) and the sealing covers (13) are fixedly connected with matched magnetic adsorption sheets (12).

9. The six-wing multi-azimuth landing scram unmanned aerial vehicle of claim 8, wherein the elastic coefficient of the first air bag (10) is greater than that of the second air bag (11), and the expansion volume of the first air bag (10) is twice as large as that of the second air bag (11) at the same time.