CN212243805U

CN212243805U - Unmanned aerial vehicle safety arrangement that falls

Info

Publication number: CN212243805U
Application number: CN202021040208.3U
Authority: CN
Inventors: 曹雷
Original assignee: Zhuhai Sv Tech Co ltd
Current assignee: Zhuhai Sv Tech Co ltd
Priority date: 2020-06-09
Filing date: 2020-06-09
Publication date: 2020-12-29
Anticipated expiration: 2030-06-09

Abstract

An unmanned aerial vehicle falling safety protection device comprises a support frame, a buffer mechanism and a speed reduction mechanism; the support frame is arranged at the bottom of the unmanned aerial vehicle body and used as an undercarriage of the unmanned aerial vehicle; the buffer mechanism is arranged on the support frame, and the support frame is movably connected with the unmanned aerial vehicle through the buffer mechanism; the speed reduction mechanism comprises a motor and blades, the motor is installed on the support frame and is electrically connected with a control panel of the unmanned aerial vehicle, and the blades are installed on an output shaft of the motor so as to drive the blades to rotate through the motor; when the unmanned aerial vehicle is out of control and falls, the motor drives the blades to generate airflow so as to reduce the falling speed of the unmanned aerial vehicle; after unmanned aerial vehicle landed, reduce the impact force by ground production through support frame and buffer gear, further protect unmanned aerial vehicle, reduce unmanned aerial vehicle's damaged rate.

Description

Unmanned aerial vehicle safety arrangement that falls

Technical Field

The utility model relates to an unmanned aerial vehicle protects technical field, specifically is an unmanned aerial vehicle safety arrangement that falls.

Background

The unmanned plane is an unmanned plane for short, and is an unmanned plane mainly controlled by radio remote control or self programs. The unmanned aerial vehicle gradually replaces an early warning machine and a manned machine with small volume, strong safety, flexible and convenient use and high low-altitude flight resolution, and the unmanned aerial vehicle technology is rapidly developed. Unmanned aerial vehicle is at the flight in-process, and the malfunction of any one part or link all can cause the aircraft out of control and crash to lead to the harm to organism itself and airborne equipment, and then cause huge loss of property.

In order to reduce the loss of the unmanned aerial vehicle when an accident occurs, the falling speed of the unmanned aerial vehicle when the unmanned aerial vehicle breaks down needs to be reduced; at present, a parachuting method is commonly adopted in the market, and the parachute is arranged on the unmanned aerial vehicle, so that the unmanned aerial vehicle can be automatically opened when the unmanned aerial vehicle breaks down to reduce the dropping speed of the unmanned aerial vehicle, and the unmanned aerial vehicle can slowly float down and land; but in the in-service use process discover, only protect the unmanned aerial vehicle that falls through the parachuting method, have following not enough:

one of them, unmanned aerial vehicle tenesmus in-process, the parachute receives external factor interference (air current) easily and takes place the winding and can't open completely with unmanned aerial vehicle self rotor, leads to the unable effect that exerts the deceleration of parachute.

Two, although the parachute can reduce the speed that tenesmus when unmanned aerial vehicle breaks down, nevertheless bump with ground when unmanned aerial vehicle lands, still can produce great impact force to probably cause the damage to unmanned aerial vehicle.

SUMMERY OF THE UTILITY MODEL

Technical problem to be solved

For solving above problem, the utility model provides an unmanned aerial vehicle safety arrangement that falls aims at reducing the falling speed of unmanned aerial vehicle when the air crash, and the impact force that receives after reducible unmanned aerial vehicle lands to play protection unmanned aerial vehicle's effect.

(II) technical scheme

In order to achieve the above object, the utility model provides a following technical scheme:

an unmanned aerial vehicle falling safety protection device is installed on a body of an unmanned aerial vehicle, and the unmanned aerial vehicle is internally provided with a control panel and comprises a support frame, a buffer mechanism and a speed reduction mechanism; the support frame is installed at the bottom of the unmanned aerial vehicle body and used as an undercarriage of the unmanned aerial vehicle; the buffer mechanism is mounted on the support frame, and the support frame is movably connected with the unmanned aerial vehicle through the buffer mechanism; the speed reduction mechanism comprises a motor and a paddle, the motor is installed on the support frame, and the motor is electrically connected with a control panel of the unmanned aerial vehicle; the paddle is mounted on an output shaft of the motor to be driven to rotate by the motor.

Preferably, the support frame is integrally designed in an arc shape, a plurality of support legs designed in an arc shape are arranged on the support frame, and the support frame is in contact with the ground through the support legs.

Preferably, the supporting frame and the supporting legs are made of elastic plastic materials.

Preferably, the two deceleration mechanisms are respectively arranged at two ends of the bottom of the support frame, and the two deceleration mechanisms are respectively positioned between the supporting legs on the support frame.

Preferably, the vehicle further comprises a roller, and the roller is rotatably arranged at one end of the supporting foot, which is in contact with the ground.

Preferably, an installation rod for installing a rotor wing is arranged on the unmanned aerial vehicle body, and a sliding block is arranged on the installation rod; the buffer mechanism comprises a sleeve, a buffer part and a fixing part, and the sleeve is arranged on the support frame; one end of the sliding block penetrates through the top end of the sleeve to the interior of the sleeve, and the sleeve can slide relative to the sliding block; the fixing piece is arranged on the sleeve, and one end of the fixing piece penetrates through the bottom end of the sleeve to the interior of the sleeve; the bolster sets up inside the sleeve, just bolster one end with the slider is located the inside one end butt of sleeve, the bolster other end with the mounting is located the one end butt in the sleeve.

Preferably, the buffer part comprises a first magnetic attraction block and a second magnetic attraction block which repel each other in the same polarity, and a buffer spring; the first magnetic attraction block is arranged at one end part of the fixing piece, which is located in the sleeve, the second magnetic attraction block is slidably arranged in the sleeve, one end of the buffer spring is abutted to the second magnetic attraction block, and the other end of the buffer spring is abutted to one end, which is located in the sleeve, of the sliding block.

Preferably, the damping mechanism comprises a damping piece, a fixing bolt and a damping spring; the end part of the mounting rod is provided with a mounting block, a mounting cavity with an opening at the side edge is arranged in the mounting block, the fixing bolt is detachably mounted at the opening of the mounting cavity, the first end of the damping piece slidably penetrates through the fixing bolt to the mounting cavity, and the second end of the damping piece is positioned outside; the first end of the damping piece is provided with an upper end block, the second end of the damping piece is provided with a lower end block, the upper end block and the lower end block can respectively abut against the damping piece, the damping spring is sleeved at the second end of the damping piece, one end of the damping spring abuts against the fixed bolt, and the other end of the damping spring abuts against the lower end block.

Preferably, the shock absorber further comprises a first air bag and a second air bag, wherein a vent groove with two open ends is formed in the shock absorber, the first air bag is installed at the opening at one end of the vent groove, and the second air bag is installed at the opening at the other end of the vent groove, so that the first air bag and the second air bag are communicated with each other.

Preferably, the first air bag and the second air bag are both made of elastic rubber materials.

Preferably, a plurality of groups of guide grooves are arranged on the support frame, and each group of guide grooves comprises a first through groove and a second through groove; the first through groove is designed to be inclined to the left from bottom to top, a first air inlet and a first exhaust port are respectively arranged at the upper end and the lower end of the first through groove, and the caliber of the first air inlet is larger than that of the first exhaust port; the second through groove is designed to incline rightwards from bottom to top, a second air inlet and a second air outlet are respectively arranged at the upper end and the lower end of the second through groove, and the caliber of the second air inlet is larger than that of the second air outlet.

(III) advantageous effects

The utility model provides a falling safety protection device for unmanned aerial vehicle, when the unmanned aerial vehicle is out of control and falls, the motor drives the paddle to generate airflow so as to reduce the falling speed of the unmanned aerial vehicle; after unmanned aerial vehicle landed, reduce the impact force by ground production through support frame and buffer gear, further protect unmanned aerial vehicle, reduce unmanned aerial vehicle's damaged rate.

Drawings

The accompanying drawings are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention, and together with the description, do not constitute a limitation of the invention, in which:

fig. 1 shows a schematic diagram of the overall structure of the present invention;

fig. 2 shows a bottom view of the overall structure of the present invention;

FIG. 3 shows a cross-sectional view A-A of FIG. 2;

FIG. 4 shows a cross-sectional view B-B of FIG. 2;

FIG. 5 shows an enlarged schematic view at E in FIG. 4;

fig. 6 shows a front view of the overall structure of the present invention;

fig. 7 shows a top view of the overall structure of the present invention;

FIG. 8 shows a cross-sectional view C-C of FIG. 7;

FIG. 9 shows an enlarged schematic view at F in FIG. 8;

fig. 10 shows a part of the structure diagram of the invention;

fig. 11 shows a schematic diagram of a part of the structure of the present invention;

FIG. 12 shows a bottom view of FIG. 11;

FIG. 13 shows a cross-sectional view D-D of FIG. 12;

fig. 14 is a first exploded view of the overall structure of the present invention;

fig. 15 shows an exploded view of the overall structure of the present invention.

In the figure: the air bag comprises a support frame 1, a flow guide groove 10, a first through groove 101, a first air inlet 101a, a first air outlet 101b, a second through groove 102a, a second air inlet 102b, a second air outlet 102b, a supporting leg 11, a roller 12, a buffer mechanism 2, a sleeve 21, a buffer member 22, a first magnetic suction block 221, a second magnetic suction block 222, a buffer spring 223, a fixing member 23, a speed reducing mechanism 3, a motor 31, a blade 32, a damping mechanism 4, a damping member 41, a vent groove 410, an upper end block 411, a lower end block 412, a fixing bolt 42, a damping spring 43, an S mounting rod, an S1 sliding block, an S2 mounting block, an S20 mounting cavity, a first air bag Q1 and a second air bag Q2.

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. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to the attached drawings 1-15, the falling safety protection device for the unmanned aerial vehicle is installed on a body of the unmanned aerial vehicle, and the unmanned aerial vehicle is internally provided with a control panel and comprises a support frame 1, a buffer mechanism 2 and a speed reduction mechanism 3; the support frame 1 is detachably mounted at the bottom of the unmanned aerial vehicle body through bolts or buckles and used as an undercarriage of the unmanned aerial vehicle; the buffer mechanism 2 is arranged on the support frame 1, and the support frame 1 is movably connected with the unmanned aerial vehicle through the buffer mechanism 2; the deceleration mechanism 3 comprises a motor 31 and blades 32, the motor 31 is installed on the support frame 1, and the motor 31 is electrically connected with a control panel of the unmanned aerial vehicle; the paddle 32 is mounted on an output shaft of the motor 31 to rotate the paddle 32 by the motor 31.

It should be noted that, the utility model discloses a mention unmanned aerial vehicle installs wireless signal receiving module on from the control panel of taking, and the user will hold the corresponding remote control equipment in hand for the signal is transmitted to wireless signal receiving module, and is received the signal by the control panel and transmits to motor 31, and then drives motor 31 to rotate; and transmit the signal to controlling the wireless signal receiving module through the remote control equipment, and then the technique that orders about motor 31 through the control panel and start and close is known technology, and remote control fan, remote control car etc. all realize through this type of technique for example, therefore its inside detailed circuit structure and theory of operation do not do unnecessary the description in the utility model.

Specifically, when the unmanned aerial vehicle is out of control and falls in the air, a user sends a signal to the control panel through remote control, the control panel receives the signal and immediately transmits the signal to the motor 31 so as to drive the motor 31 to start and drive the paddle 32, and then upward airflow is generated, and the airflow generated by rotation of the paddle 32 is generally opposite to the falling direction of the unmanned aerial vehicle, so that the falling speed of the unmanned aerial vehicle can be reduced to a certain degree, and compared with the mode of installing a parachute on the unmanned aerial vehicle, the speed reduction mechanism 3 has stronger controllability, lower possibility of accidents caused by interference of external factors and better stability; and when unmanned aerial vehicle landed, all be under the general condition support frame 1 earlier with ground take place the contact and produce the impact force, because the effect of power is mutual, consequently ground also will produce reverse impact force reaction force, and this reverse impact force will be absorbed by support frame 1 to conduct earlier and reduce by buffer gear 2 on buffer gear 2, conduct again at last on unmanned aerial vehicle's the organism.

To sum up, when unmanned aerial vehicle is out of control and falls, this unmanned aerial vehicle safety arrangement that falls reduces unmanned aerial vehicle's speed of tenesmus through deceleration mechanism 3, after unmanned aerial vehicle lands, reduces the impact force by ground production through support frame 1 and buffer gear 2, further protects unmanned aerial vehicle, reduces unmanned aerial vehicle's damage rate.

Referring to the attached drawings 1-5, the support frame 1 is designed to be arc-shaped as a whole, a plurality of supporting legs 11 designed to be arc-shaped are arranged on the support frame 1, the support frame 1 is in contact with the ground through the supporting legs 11, and one end of each supporting leg 11 in contact with the ground is also rotatably provided with a roller 12.

Specifically, when the unmanned aerial vehicle falls and lands, the unmanned aerial vehicle is arranged on the supporting legs 11 and contacts with the ground firstly, and the reverse impact force generated by the ground is transmitted to the supporting frame 1 through the supporting legs 11; and because the whole support frame 1 and the supporting legs 11 are all designed in a circular arc shape and are influenced by reverse impact force, the whole support frame 1 and the supporting legs 11 are bent to a certain degree to buffer, the process can indirectly reduce the force of the reverse impact force, and the process is the first-stage buffering.

On the other hand, because the supporting frame 1 and the supporting legs 11 are subjected to the bending deformation caused by the reverse impact force of the ground, in order to avoid the supporting frame 1 and the supporting legs 11 from being broken in the process of the bending deformation, in the utility model, the supporting frame 1 and the supporting legs 11 are both made of elastic materials with the recovery capability; such as elastic plastic and elastic steel; and consider unmanned aerial vehicle's bearing problem, the utility model discloses well support frame 1 and supporting legs 11 choose for use the elastic plastic material for support frame 1 and supporting legs 11 all possess certain resilience and toughness, and then difficult fracture when receiving the reverse impact force on ground has prolonged the life of support frame 1 and supporting legs 11.

In addition, considering that the supporting legs 11 are easy to wear when in contact with the ground, the roller 12 is arranged at one end of each supporting leg 11, which is in contact with the ground, when the unmanned aerial vehicle lands, the roller 12 is firstly in contact with the ground, so that the supporting legs 11 can be prevented from directly contacting with the ground to wear; because the roller 12 is installed on each supporting foot 11, when the roller 12 contacts the ground, under the influence of gravity of the unmanned aerial vehicle, the roller 12 will slide on the ground, and further will drive the whole unmanned aerial vehicle to slide a certain distance on the ground, according to the law of conservation of energy, under the condition that the total energy is not changed, because the unmanned aerial vehicle slides on the ground is a process of doing work, a part of energy will be consumed, namely, when the roller 12 contacts the ground, part of reverse impact force generated by the ground can be guided to the roller 12 to do work due to the movement of the unmanned aerial vehicle, so as to reduce the total amount of reverse impact force transmitted to the supporting foot 11, and further reduce the strength of the reverse impact force transmitted to the supporting foot 11, and further reduce the possibility that the supporting foot 11 breaks when receiving the ground reverse impact force.

Referring to fig. 1 to 5, two deceleration mechanisms 3 are provided and respectively installed at two ends of the bottom of the support frame 1, and the two deceleration mechanisms 3 are located between the support legs 11 on the support frame 1.

Specifically, the deceleration mechanism 3 is installed between each supporting leg 11 on the support frame 1, and when the unmanned aerial vehicle lands, the paddle 32 of the deceleration mechanism 3 is in contact with the ground, so that the paddle 32 is prevented from being damaged.

On the other hand, considering that when the unmanned aerial vehicle falls, the unmanned aerial vehicle may not land on the support frame 1 due to the uneven stress at the two ends of the unmanned aerial vehicle, the two deceleration mechanisms 3 are respectively installed at the two ends of the bottom of the support frame 1, and thus air flows can be generated at the two ends of the unmanned aerial vehicle at the same time, so that the stress balance at the two ends of the unmanned aerial vehicle can be ensured, the unmanned aerial vehicle can be more stable when falling, and the possibility that the unmanned aerial vehicle lands on the support frame 1 is improved; the strength of the total airflow can be increased, and the falling speed of the unmanned aerial vehicle is further reduced.

Referring to fig. 6 to 10, an installation rod S for installing a rotor is arranged on the unmanned aerial vehicle body, and a sliding block S1 is arranged on the installation rod S; the buffer mechanism 2 comprises a sleeve 21, a buffer piece 22 and a fixing piece 23, wherein the sleeve 21 is arranged on the support frame 1; one end of the slide block S1 penetrates through the top end of the sleeve 21 to the interior of the sleeve 21, and the sleeve 21 can slide relative to the slide block S1; the fixing piece 23 is installed on the sleeve 21, and one end of the fixing piece 23 penetrates through the bottom end of the sleeve 21 to the inside of the sleeve 21; the cushion member 22 is disposed inside the sleeve 21, one end of the cushion member 22 abuts against one end of the slider S1 inside the sleeve 21, and the other end of the cushion member 22 abuts against one end of the fixing member 23 inside the sleeve 21.

Specifically, when the unmanned aerial vehicle lands, a reverse impact force generated by the ground is transmitted to the supporting legs 11, the supporting legs 11 are subjected to bending deformation to drive the sleeve 21 to move, and because the fixing piece 23 is installed at the bottom end of the sleeve 21, and one end of the fixing piece 23 abuts against the buffer piece 22 installed in the sleeve 21, when the fixing piece 23 moves along with the sleeve 21 and extrudes the buffer piece 22, the reverse impact force transmitted to the supporting legs 11 is transmitted to the buffer piece 22; bolster 22 possesses the cushioning effect, and the decay takes place for reverse impact force in the transmission process, and consequently reducible reverse impact force is to the damage that unmanned aerial vehicle caused.

It should be noted that, in the embodiment of the utility model, supporting legs 11 are equipped with four, and buffer gear 2 corresponds supporting legs 11 and is equipped with four, and installation pole S also corresponds buffer gear 2 and is equipped with four to make unmanned aerial vehicle atress even.

Further, the buffer 22 includes a first magnetic block 221 and a second magnetic block 222 with like poles repelling each other, and a buffer spring 223; the first magnetic block 221 is mounted at one end of the fixing member 23 inside the sleeve 21, the second magnetic block 222 is slidably mounted inside the sleeve 21, one end of the buffer spring 223 abuts against the second magnetic block 222, and the other end of the buffer spring 223 abuts against one end of the sliding block S1 inside the sleeve 21.

Specifically, in the initial state, the distance between the first magnetic attraction block 221 and the second magnetic attraction block 222 is large, the repulsive force is small, and the buffer spring 223 is in a normal state; when the supporting leg 11 is forced to bend and drive the sleeve 21 and the fixing member 23 to move, the first magnetic attraction block 221 will rapidly approach the second magnetic attraction block 222, so that the repulsive force between the first magnetic attraction block 221 and the second magnetic attraction is increased to form a second-stage buffer; in the process that the first magnetic block 221 approaches the second magnetic block 222, the second magnetic block 222 moves along the sliding block S1 under the influence of the repulsive force of the first magnetic block 221 to press the buffer spring 223, so that the buffer spring 223 is compressed and stored, and the buffer spring 223 is designed to form a third-stage buffer.

In conclusion, unmanned aerial vehicle is after landing, possesses tertiary buffering at least, and the first order is inhaled piece 221 and second magnetism by support frame 1 and supporting legs 11 and is inhaled the piece and provide by first magnetism, and the third level is inhaled piece 222 and is provided by buffer spring 223 by first magnetism to make unmanned aerial vehicle weigh down the reverse impact force stratum layer that ground produced and decrease, reduce the damaged rate behind the unmanned aerial vehicle weighs down.

Referring to fig. 1-4, because the rotor of the drone is generally installed at the end of the mounting rod S, considering that when the drone falls down, the portion of the drone not protected by the support frame 1 is prone to toppling, for example, the rotor on the four mounting rods S and the mounting rod S is prone to contact with the ground, resulting in damage to the rotor; on the other hand, because four installation pole S rotors are not protected by special, often receive vibrations and break off easily when unmanned aerial vehicle weighs down. Therefore, the utility model also comprises a damping mechanism 4, wherein the damping mechanism 4 comprises a damping piece 41, a fixing bolt 42 and a damping spring 43; the end part of the mounting rod S is provided with a mounting block S2, a mounting cavity S20 with an opening at the side edge is arranged in the mounting block S2, the fixing bolt 42 is detachably mounted at the opening of the mounting cavity S20, the first end of the shock absorbing piece 41 slidably penetrates through the fixing bolt 42 to the mounting cavity S20, and the second end of the shock absorbing piece 41 is positioned outside; the first end of the damping member 41 is provided with an upper end block 411, the second end of the damping member 41 is provided with a lower end block 412, the upper end block 411 and the lower end block 412 can respectively abut against the damping member 41, the damping spring 43 is sleeved at the second end of the damping member 41, one end of the damping spring 43 abuts against the fixed bolt 42, and the other end of the damping spring abuts against the lower end block 412.

Specifically, when the unmanned aerial vehicle lands on the ground, the lower end block 412 at the second end of the shock absorbing member 41 is affected by the reverse impact force generated by the ground, so that the whole shock absorbing member 41 moves along the installation cavity S20, and the upper end block 411 at the first end of the shock absorbing member 41 gradually approaches the installation rod S; in the process, the damping spring 43 sleeved at the second end of the damping member 41 is compressed by the lower end block 412 to form a fourth-stage buffer, so as to weaken the strength of the reverse impact force transmitted to the end of the mounting rod S.

It should be noted that, in the embodiment of the present invention, the fixing bolt 42 is screwed to the mounting block S2, so that the user can mount the damping mechanism 4 or dismount the damping mechanism 4 to repair each part.

Further, in order to improve the cushioning effect of damper 41, and avoid damper 41 direct and ground contact impaired, the utility model discloses in still include first gasbag Q1 and second gasbag Q2, damper 41 is inside to be equipped with both ends open-ended air channel 410, first gasbag Q1 is installed at the opening part of air channel 410 one end, and the opening part at the air channel 410 other end is installed to second gasbag Q2, so that first gasbag Q1 and second gasbag Q2 put through each other, and first gasbag Q1 and second gasbag Q2 are elastic rubber material.

It should be noted that the first airbag Q1 and the second airbag Q2 are both designed in an accordion shape, the accommodating volumes of the first airbag Q1 and the second airbag Q2 are equal, and the air in the first airbag Q1 and the second airbag Q2 is only enough to completely fill one airbag; in a normal state, the gas in the first air bag Q1 and the second air bag Q2 is in an even distribution state.

Specifically, when the unmanned aerial vehicle lands and the support leg 11 contacts with the ground, the first air bag Q1 contacts with the ground first and is squeezed by the reverse impact force generated by the ground, and is gradually folded and contracted, and the gas in the first air bag Q1 gradually flows into the second air bag Q2 through the vent groove 410 until the lower end block 412 at the second end of the shock absorbing member 41 contacts with the ground, and all the gas in the first air bag Q1 flows into the second air bag Q2, so that the second air bag Q2 expands; at this time, the shock absorbing member 41 is continuously driven by the reverse impact force, so as to drive the upper end block 411 at the first end of the shock absorbing member 41 to extrude the second air bag Q2, the second air bag Q2 is stressed to be folded and contracted, and the gas in the second air bag Q2 is gradually extruded into the first air bag Q1 through the vent groove 410; in the whole process, the gas in the first air bag Q1 and the second air bag Q2 is transferred once to form the fifth-stage buffer, and no matter the gas in the first air bag Q1 is transferred to the second air bag Q2 or the gas in the second air bag Q2 is transferred to the first air bag Q1, energy is consumed, so that the energy is generated by applying work through reverse impact force, and the effect of reducing the impact strength of the reverse impact force on the supporting legs 11 is achieved.

The first air bag Q1 and the second air bag Q2 are made of elastic rubber materials and have certain elasticity and recovery capability and stronger toughness, namely the first air bag Q1 and the second air bag Q2 are guaranteed to have good impact resistance capability, and the first air bag Q1 and the second air bag Q2 are guaranteed to bear high-degree impact.

Referring to fig. 10-13, when the unmanned aerial vehicle falls, the unmanned aerial vehicle moves to the ground quickly under the action of gravity, and in order to further reduce the falling speed of the unmanned aerial vehicle, the support frame 1 of the present invention is provided with a plurality of sets of guiding gutters 10, each set of guiding gutters 10 includes a first through groove 101 and a second through groove 102; the first through groove 101 is designed to be inclined to the left from bottom to top, a first air inlet 101a and a first exhaust port 101b are respectively arranged at the upper end and the lower end of the first through groove 101, and the caliber of the first air inlet 101a is larger than that of the first exhaust port 101 b; the second through groove 102 is inclined from bottom to top to right, and a second air inlet 102a and a second air outlet 102b are respectively arranged at the upper end and the lower end of the second through groove 102, and the aperture of the second air inlet 102a is larger than that of the second air outlet 102 b.

In particular, the quick tenesmus in-process of unmanned aerial vehicle can bear the impact of ascending air current, and general unmanned aerial vehicle is owing to do not have the design of guide air current, therefore the air current flows through from unmanned aerial vehicle's organism easily, and the design of guiding gutter 10 is then through guiding this air current and reach the mesh that reduces unmanned aerial vehicle's tenesmus speed.

Specifically, when upward airflow impacts the bottom of the body of the unmanned aerial vehicle, the upward airflow passes through the first through groove 101 and the second through groove 102 on the support frame 1, and due to the design that the first through groove 101 is inclined from bottom to top to left, the design can block the airflow flowing through the first through groove 101, so that the airflow in the first through groove 101 can stay for a certain time; and the bore of first air inlet 101a is greater than the bore of first exhaust port 101b, can make the speed that the air current got into first logical groove 101 in faster, and the speed of flowing out in first logical groove 101 is slower, also can prolong the dwell time of air current in first logical groove 101, and the dwell time of air current in first logical groove 101 is longer, then the influence to support frame 1 is big more, consequently can utilize the air current to reduce unmanned aerial vehicle's tenesmus speed to a great extent.

On the other hand, in the utility model, first logical groove 101 is the same with the design of second logical groove 102, to opposite when its incline direction, its effect is that the guide air current is kept away from after first logical groove 101 and second logical groove 102 gradually relatively, make the air current that leads to groove 102 through first logical groove 101 and second can follow the different positions and the not equidirectional outflow of support frame 1, avoid the air current that leads to groove 101 and second logical groove 102 to concentrate together, thereby the ascending air current of reinforcing in the at utmost is to the effort of support frame 1, in order to reach the mesh that reduces unmanned aerial vehicle tenesmus speed.

In addition, because guiding gutter 10 is equipped with the multiunit, and the equipartition is in 1 both sides of support frame, consequently also can get up the effect of balanced support frame 1 and unmanned aerial vehicle for unmanned aerial vehicle stable tenesmus, the increase is installed and is contacted the possibility on ground earlier at unmanned aerial vehicle's organism support frame 1.

It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.

Claims

1. An unmanned aerial vehicle falling safety protection device is installed on a body of an unmanned aerial vehicle, and a control panel is arranged in the unmanned aerial vehicle, and is characterized by comprising a support frame (1), a buffer mechanism (2) and a deceleration mechanism (3);

the support frame (1) is installed at the bottom of the unmanned aerial vehicle body and used as an undercarriage of the unmanned aerial vehicle;

the buffer mechanism (2) is installed on the support frame (1), and the support frame (1) is movably connected with the unmanned aerial vehicle through the buffer mechanism (2);

the deceleration mechanism (3) comprises a motor (31) and blades (32), the motor (31) is installed on the support frame (1), and the motor (31) is electrically connected with a control board of the unmanned aerial vehicle; the blades (32) are mounted on an output shaft of the motor (31) to be driven in rotation by the motor (31) to the blades (32).

2. The unmanned aerial vehicle falling safety protection device of claim 1, wherein the support frame (1) is designed in a circular arc shape as a whole, a plurality of supporting feet (11) in a circular arc shape are arranged on the support frame (1), and the support frame (1) is in contact with the ground through the supporting feet (11); the support frame (1) and the supporting legs (11) are both made of elastic materials with recovery capability.

3. The unmanned aerial vehicle falling safety device according to claim 2, wherein two deceleration mechanisms (3) are provided and respectively installed at two ends of the bottom of the support frame (1), and the two deceleration mechanisms (3) are located between the support feet (11) on the support frame (1).

4. An unmanned aerial vehicle fall safety device according to claim 2, further comprising a roller (12), wherein the roller (12) is rotatably mounted at one end of the support foot (11) contacting the ground.

5. The unmanned aerial vehicle falling safety protection device of claim 2, wherein a mounting rod (S) for mounting a rotor wing is arranged on the unmanned aerial vehicle body, and a sliding block (S1) is arranged on the mounting rod (S); the buffer mechanism (2) comprises a sleeve (21), a buffer part (22) and a fixing part (23), and the sleeve (21) is arranged on the support frame (1); one end of the sliding block (S1) penetrates through the top end of the sleeve (21) to the inside of the sleeve (21), and the sleeve (21) can slide relative to the sliding block (S1); the fixing piece (23) is arranged on the sleeve (21), and one end of the fixing piece (23) penetrates through the bottom end of the sleeve (21) to the inside of the sleeve (21); the buffer piece (22) is arranged in the sleeve (21), one end of the buffer piece (22) is abutted to one end, located in the sleeve (21), of the sliding block (S1), and the other end of the buffer piece (22) is abutted to one end, located in the sleeve (21), of the fixing piece (23).

6. The unmanned aerial vehicle fall safety device of claim 5, wherein the buffer member (22) comprises a first magnetic block (221) and a second magnetic block (222) which are repellent to each other in like polarity, and a buffer spring (223); the first magnetic suction block (221) is installed at one end portion, located in the sleeve (21), of the fixing piece (23), the second magnetic suction block (222) is installed inside the sleeve (21) in a sliding mode, one end of the buffer spring (223) is abutted to the second magnetic suction block (222), and the other end of the buffer spring (223) is abutted to one end, located in the sleeve (21), of the sliding block (S1).

7. An unmanned aerial vehicle fall safety device according to claim 5, further comprising a shock absorbing mechanism (4), the shock absorbing mechanism (4) comprising a shock absorbing member (41), a fixing bolt (42) and a shock absorbing spring (43); the end part of the mounting rod (S) is provided with a mounting block (S2), a mounting cavity (S20) with an opening on the side is arranged in the mounting block (S2), the fixing bolt (42) is detachably mounted at the opening of the mounting cavity (S20), the first end of the shock absorbing piece (41) slidably penetrates through the fixing bolt (42) to the mounting cavity (S20), and the second end of the shock absorbing piece (41) is located outside; an upper end block (411) is arranged at the first end of the damping piece (41), a lower end block (412) is arranged at the second end of the damping piece (41), the upper end block (411) and the lower end block (412) can be abutted against the damping piece (41) respectively, the damping spring (43) is sleeved at the second end of the damping piece (41), one end of the damping spring (43) is abutted against the fixing bolt (42), and the other end of the damping spring is abutted against the lower end block (412).

8. The unmanned aerial vehicle falling safety protection device of claim 7, further comprising a first air bag (Q1) and a second air bag (Q2), wherein the shock absorption piece (41) is internally provided with a vent groove (410) with two open ends, the first air bag (Q1) is installed at the opening of one end of the vent groove (410), and the second air bag (Q2) is installed at the opening of the other end of the vent groove (410), so that the first air bag (Q1) and the second air bag (Q2) are communicated with each other.

9. The crash safety apparatus of unmanned aerial vehicle as claimed in claim 8, wherein the first and second air bags (Q1, Q2) are made of elastic rubber.

10. The unmanned aerial vehicle fall safety device of claim 1, wherein a plurality of groups of guiding grooves (10) are formed in the support frame (1), and each group of guiding grooves (10) comprises a first through groove (101) and a second through groove (102); the first through groove (101) is designed to be inclined to the left from bottom to top, a first air inlet (101a) and a first exhaust port (101b) are respectively arranged at the upper end and the lower end of the first through groove (101), and the caliber of the first air inlet (101a) is larger than that of the first exhaust port (101 b); the second through groove (102) is designed to be inclined to the right from bottom to top, a second air inlet (102a) and a second air outlet (102b) are respectively arranged at the upper end and the lower end of the second through groove (102), and the caliber of the second air inlet (102a) is larger than that of the second air outlet (102 b).