CN209921629U - Rotatory centrifugation of light small-size unmanned aerial vehicle takes off device with higher speed - Google Patents
Rotatory centrifugation of light small-size unmanned aerial vehicle takes off device with higher speed Download PDFInfo
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- CN209921629U CN209921629U CN201920408064.3U CN201920408064U CN209921629U CN 209921629 U CN209921629 U CN 209921629U CN 201920408064 U CN201920408064 U CN 201920408064U CN 209921629 U CN209921629 U CN 209921629U
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Abstract
The utility model discloses a rotating centrifugal accelerating take-off device of a light and small unmanned aerial vehicle, which comprises a power mechanism, a cantilever structure, a brake device and a release device, wherein one end of the cantilever structure is connected with the input end of the power mechanism, the other end of the cantilever structure is connected with the release device, and the unmanned aerial vehicle is provided with a connecting piece below and is used for being fixed on the release device; the power mechanism comprises a box-type base, a motor, a power supply, a clutch and a controller, wherein the motor is vertically arranged in the box-type base, an output shaft of the motor is connected with the clutch, the clutch is connected with a rotating shaft, and the rotating shaft is a hollow first straight pipe. The utility model discloses a rotation with higher speed of second straight tube, then take off unmanned aerial vehicle release when the outer tip linear velocity of second straight tube reaches or surpasss unmanned aerial vehicle minimum flying speed, change unmanned aerial vehicle accelerated linear motion into rotary motion, require lowly to taking off the place, can use as light unmanned aerial vehicle's the device of taking off again most of occasions, and is convenient nimble.
Description
Technical Field
The invention relates to the technical field of take-off devices of unmanned aerial vehicles, in particular to a rotary centrifugal accelerating take-off device of a light and small unmanned aerial vehicle.
Background
In recent years, unmanned aerial vehicles have developed rapidly. Unmanned aerial vehicle can divide into two main types of fixed wing unmanned aerial vehicle and rotor unmanned aerial vehicle, but rotor unmanned aerial vehicle VTOL requires lower to the place of taking off, uses in a flexible way, but generally has duration of a journey time period, flight stability shortcoming such as not good, load less. And fixed wing unmanned aerial vehicle duration is longer relatively, and the load is also bigger, and flight control is easier than rotor unmanned aerial vehicle, but fixed wing unmanned aerial vehicle needs certain speed just can take off, and is higher to taking off the place requirement.
The existing take-off mode of the fixed wing unmanned aerial vehicle is mostly running take-off, vehicle-mounted take-off, rocket boosting take-off and the like, and the modes either need a longer straight runway or a relatively wide launching site, so that a great deal of inconvenience is brought to use.
Disclosure of Invention
The invention aims to provide a rotary centrifugal accelerating take-off device of a light and small unmanned aerial vehicle, aiming at the defects of the prior art, the rotary centrifugal accelerating take-off device can be used for taking off and releasing the light and small unmanned aerial vehicle with fixed wings, can be arranged on different carriers, can change the take-off position, and is flexible and convenient to use.
The invention adopts the following technical scheme: a rotating centrifugal accelerating take-off device of a light and small unmanned aerial vehicle comprises a power mechanism, a cantilever structure, a brake device and a release device, wherein one end of the cantilever structure is connected with the output end of the power mechanism, the other end of the cantilever structure is connected with the release device, and the unmanned aerial vehicle is provided with a connecting piece below and used for being fixed on the release device;
the power mechanism comprises a box-type base, a motor, a power supply, a clutch and a controller, wherein the motor is vertically arranged in the box-type base, an output shaft of the motor is connected with the clutch, the clutch is connected with a rotating shaft, the rotating shaft is a hollow first straight pipe, a rotating connector is arranged on the first straight pipe above the clutch, and the upper end of the first straight pipe penetrates out of the box-type base to be connected with the cantilever structure;
the brake device is arranged on the box-type base and comprises a mounting seat, an electric control hydraulic brake, brake calipers and a brake disc, wherein the mounting seat is arranged on the upper end surface of the box-type base;
the cantilever structure is a hollow second straight pipe, the inner end of the second straight pipe is fixed at the upper end part of the first straight pipe, the first straight pipe is communicated with the inside of the second straight pipe, and the outer end of the second straight pipe is fixed with a release device;
the release device comprises a release seat, a V-shaped notch is formed in the upper end face of the release seat, a V-shaped groove is formed in the inner side wall of the V-shaped notch, a through hole is formed in the upper end of the release seat and is close to one side of a straight rod, a clamping lock is arranged in the through hole in a sliding mode, a pull rod is arranged close to one side of the straight rod, a plug is arranged at the left end of the through hole, the left end of the pull rod penetrates out of the plug, a spring is sleeved on the pull rod in the through hole, an elliptical ring is arranged at the other end of the pull rod, the spring can be compressed by pulling the pull rod to move the clamping lock, a;
the connecting piece is a V-shaped clamping seat arranged at the tail part of the lower end of the unmanned aerial vehicle, the V-shaped clamping seat is matched with the V-shaped groove, a bayonet is arranged at the position of the side edge of the V-shaped clamping seat corresponding to the through hole, and the bayonet is matched with the bayonet;
the inner wall of the box type base is provided with a rotating speed sensor, the rotating speed sensor is aligned to a first straight pipe, an inner stator of the rotary connector is fixed on the first straight pipe, a wiring end of the inner stator of the rotary connector is connected with a wiring end of a steering engine through a wire, a wiring end of a rotor at the outer end of the rotary connector is connected with a controller through a wire, and a motor, an electric control hydraulic brake and the rotating speed sensor are all connected with the controller through wires.
Preferably, the power supply is a generator or a battery.
Preferentially, the middle part of the side surface of the V-shaped clamping seat is provided with a connecting sheet, and the unmanned aerial vehicle and the V-shaped clamping seat are fixed through the bolt fixing connecting sheet.
Preferentially, the outer end of the rocker arm of the steering engine is provided with a cylindrical bulge, the cylindrical bulge is arranged in the inner sliding ring of the elliptical ring, and the cylindrical bulge can slide in the elliptical ring.
Preferably, the first straight pipe is communicated with the second straight pipe, a first wiring hole is formed in the side wall of the lower end of the first straight pipe, and a second wiring hole is formed in the side wall of the outer end of the second straight pipe.
And the conducting wire connected between the stator wiring end in the rotary connector and the wiring end of the steering engine is arranged in the first straight pipe and the first straight pipe, and the two ends of the conducting wire are respectively connected with the stator wiring end through the first wiring hole and the wiring end of the steering engine through the second wiring hole.
Preferably, the first straight pipe and the second straight pipe are welded and fixed, and the second straight pipe and the releasing device are welded and fixed.
The invention has the advantages that:
(1) the unmanned aerial vehicle takes off through the accelerated rotation of the second straight pipe, and then when the linear velocity of the outer end part of the second straight pipe reaches or exceeds the minimum flight velocity of the unmanned aerial vehicle, the accelerated linear motion of the unmanned aerial vehicle is converted into rotary motion, the requirement on a take-off site is low, and the unmanned aerial vehicle can be used as a take-off device of a light and small unmanned aerial vehicle in most occasions, and is convenient and flexible.
(2) The unmanned aerial vehicle release control system controls the release of the unmanned aerial vehicle through the controller, is safe to use, simple in operation process and low in requirement on operators.
(3) The invention has simple structure, can be installed on different carriers, can quickly change the take-off position of the unmanned aerial vehicle, lightens the workload of the crew, can control the take-off direction of the unmanned aerial vehicle with the participation of the control equipment, and is convenient to use.
Drawings
FIG. 1 is a diagram of the present invention;
FIG. 2 is a schematic view of the power mechanism of FIG. 1;
FIG. 3 is a schematic view of a connection structure of a first straight pipe and a second straight pipe according to the present invention;
FIG. 4 is a top view of FIG. 1;
FIG. 5 is a schematic view of a release device according to the present invention;
FIG. 6 is a top view of FIG. 5;
FIG. 7 is a schematic structural view of the V-shaped clamping seat;
fig. 8 is a perspective view of the V-shaped cartridge.
In the figure: 1. the automatic brake device comprises an unmanned aerial vehicle, 2 parts of a release device, 4 parts of a second straight pipe, 5 parts of a rotary connector, 6 parts of a clutch, 7 parts of a brake disc, 9 parts of a mounting seat, 10 parts of a brake cable, 11 parts of an electric control hydraulic brake, 12 parts of brake pincers, 13 parts of a controller, 14 parts of a motor, 15 parts of a battery, 16 parts of a lead, 17 parts of a rotating speed sensor, 18 parts of a box type base, 19 parts of a release seat, 20 parts of a steering engine, 21 parts of an elliptical ring, 22 parts of a pull rod, 23 parts of a spring, 24 parts of a clamping lock, 25 parts of a V-shaped notch, 27 parts of a V-shaped groove, 28 parts of a connecting piece, 29 parts of a V-shaped clamping seat, 30 parts of a clamping opening, 31 parts of a first straight pipe, 32 parts of a cylindrical protrusion, 33 parts of a rocker.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
As shown in fig. 1 to 8, the rotating centrifugal accelerating takeoff device of a light and small unmanned aerial vehicle comprises a power mechanism, a cantilever structure, a brake device and a release device 2, wherein one end of the cantilever structure is connected with the output end of the power mechanism, the other end of the cantilever structure is connected with the release device 2, and the unmanned aerial vehicle 1 is provided with a connecting piece below and is fixed on the release device 2.
The power mechanism comprises a box type base 18, a motor 14, a power supply, a clutch 6 and a controller 13, wherein the motor 14 is vertically arranged in the box type base 18, and an output shaft of the motor 14 is connected with the clutch 6. The clutch 6 is connected with a rotating shaft, the rotating shaft is a hollow first straight pipe 31, a rotary connector 5 is arranged on the first straight pipe 31 above the clutch 6, the upper end of the first straight pipe 31 penetrates out of the box-type base 18 to be connected with a cantilever structure, a power supply adopts a generator or a battery 15, and the battery 15 is adopted in the embodiment.
The brake device is arranged on the box-type base 18 and comprises a mounting seat 9, an electric control hydraulic brake 11, brake calipers 12 and a brake disc 7, wherein the mounting seat 9, the electric control hydraulic brake 11, the brake calipers 12 and the brake disc 7 are arranged on the upper end face of the box-type base 18, the brake calipers 12 are arranged in the mounting seat 9, the brake disc 7 is arranged on a first straight pipe 31, the brake disc 7 is clamped between the two brake calipers 12, and the electric control hydraulic brake 11 is connected with the brake calipers 12 through a brake cable 10.
The cantilever structure is a hollow second straight pipe 4, the inner end of the second straight pipe 4 is fixed at the upper end part of the first straight pipe 31, the first straight pipe 31 is communicated with the inner part of the second straight pipe 4, and the outer end of the second straight pipe 4 is fixed with the release device 2.
The release device 2 comprises a release seat 19, a V-shaped notch 25 is formed in the upper end face of the release seat 19, a V-shaped groove 27 is formed in the inner side wall of the V-shaped notch 25, a through hole is formed in one side, close to a straight rod, of the upper end of the release seat 19, a clamping lock 24 is arranged in the through hole in a sliding mode, a pull rod 22 is arranged on one side, close to the straight rod, of the clamping lock 24, a plug is arranged at the left end of the through hole, the left end of the pull rod 22 penetrates out of the plug, a spring 23 is sleeved on the pull rod 22 in the through hole, an elliptical ring 21 is arranged at the other end of the pull rod 22, the spring 23 can be compressed by pulling the pull rod 22 to move the clamping lock 24, a steering engine 20;
the connecting piece is a V-shaped clamping seat 29 arranged at the tail of the lower end of the unmanned aerial vehicle 1, the V-shaped clamping seat 29 is matched with the V-shaped groove 27, a bayonet 30 is arranged at the position, corresponding to the through hole, of the side edge of the V-shaped clamping seat 29, and the bayonet 24 is matched with the bayonet 30;
the inner wall of the box-type base 18 is provided with a rotating speed sensor 17, the rotating speed sensor 17 is aligned to the first straight pipe 31, a stator 37 inside the rotary connector 5 is fixed on the first straight pipe 31, a terminal of the stator 37 inside the rotary connector 5 is connected with a terminal of the steering engine 20 through a lead 16, a terminal of a rotor 36 at the outer end of the rotary connector 5 is connected with the controller 13 through the lead 16, and the motor 14, the electric control hydraulic brake 11 and the rotating speed sensor 17 are also connected with the controller 13 through the lead 16.
In the second embodiment, a connecting piece 28 is arranged in the middle of the side surface of the V-shaped clamping seat 29, and the unmanned aerial vehicle 1 and the V-shaped clamping seat 29 are fixed by fixing the connecting piece 28 through bolts.
In the third embodiment, a cylindrical protrusion 32 is arranged at the outer end of a rocker arm 33 of the steering engine 20, the cylindrical protrusion 32 is arranged in the sliding inner ring of the elliptical ring 21, and the cylindrical protrusion 32 can slide in the sliding inner ring of the elliptical ring 21.
In the fourth embodiment, the first straight pipe 31 is communicated with the second straight pipe 4, the side wall of the lower end part of the first straight pipe 31 is provided with a first wiring hole 40, and the side wall of the outer end part of the second straight pipe 4 is provided with a second wiring hole 41.
The conducting wire 16 connected between the terminal of the stator 37 in the rotary connector 5 and the terminal of the steering engine 20 is arranged in the first straight pipe 31 and the first straight pipe 31, two ends of the conducting wire are respectively connected with the terminal of the stator 37 through the first wire feeding hole 40, and the second wire feeding hole 41 is connected with the terminal of the steering engine 20.
In the fifth embodiment, the first straight pipe 31 and the second straight pipe 4 are welded and fixed, and the second straight pipe 4 and the releasing device 2 are welded and fixed.
The working principle is as follows: the lower end face of the tail of the unmanned aerial vehicle 1 is fixedly provided with a V-shaped clamping seat 29, the unmanned aerial vehicle 1 is fixed in a V-shaped groove 27 of the release seat 19 through the V-shaped clamping seat 29, and the clamping lock 24 is clamped into a clamping opening 30 of the V-shaped clamping seat 29 under the action of the spring 23 to fix the V-shaped clamping seat 29; controller 13 control motor 14 rotates, 14 output shafts of motor pass through clutch 6 and drive first straight tube 31 and rotate, thereby drive unmanned aerial vehicle 1 through second straight tube 4 and rotate, speed sensor 17 detects the rotational speed of first straight tube 31, feed back to controller 13, when the outer tip linear velocity of second straight tube 4 reaches or surpasss unmanned aerial vehicle 1 minimum flying speed, controller 13 control steering wheel 20 rotates rocking arm 33, make pull rod 22 inward movement, make kayser 24 take out from bayonet 30, thereby take off with the release of unmanned aerial vehicle 1.
(1) According to the invention, the unmanned aerial vehicle 1 is released to take off through the accelerated rotation of the second straight pipe 4, and then when the linear velocity of the outer end part of the second straight pipe 4 reaches or exceeds the minimum flight velocity of the unmanned aerial vehicle 1, the accelerated linear motion of the unmanned aerial vehicle 1 is converted into rotary motion, the requirement on a take-off site is low, and the device can be used as a take-off device of the light and small unmanned aerial vehicle 1 in most occasions, and is convenient and flexible.
(2) The controller 13 controls the release of the unmanned aerial vehicle 1, so that the unmanned aerial vehicle is safe to use, simple in operation process and low in requirement on operators.
(3) The invention can be installed on different vehicles, can quickly change the takeoff position of the unmanned aerial vehicle 1, reduces the workload of the crew, can control the takeoff direction of the unmanned aerial vehicle 1 with the participation of the control equipment, and is convenient to use.
Although the present invention has been described in detail with reference to the preferred embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted without departing from the spirit and scope of the invention. Those skilled in the art can also make other changes and the like in the design of the present invention within the spirit of the present invention as long as they do not depart from the technical effects of the present invention. Such variations are intended to be included within the scope of the invention as claimed.
Claims (7)
1. A rotating centrifugal accelerating take-off device of a light and small unmanned aerial vehicle is characterized by comprising a power mechanism, a cantilever structure, a brake device and a release device, wherein one end of the cantilever structure is connected with the transmission end of the power mechanism, the other end of the cantilever structure is connected with the release device, and the unmanned aerial vehicle is provided with a connecting piece below and used for being fixed on the release device;
the power mechanism comprises a box-type base, a motor, a power supply, a clutch and a controller, wherein the motor is vertically arranged in the box-type base, an output shaft of the motor is connected with the clutch, the clutch is connected with a rotating shaft, the rotating shaft is a hollow first straight pipe, a rotating connector is arranged on the first straight pipe above the clutch, and the upper end of the first straight pipe penetrates out of the box-type base to be connected with the cantilever structure;
the brake device is arranged on the box-type base and comprises a mounting seat, an electric control hydraulic brake, brake calipers and a brake disc, wherein the mounting seat is arranged on the upper end surface of the box-type base;
the cantilever structure is a hollow second straight pipe, the inner end of the second straight pipe is fixed at the upper end part of the first straight pipe, the first straight pipe is communicated with the inside of the second straight pipe, and the outer end of the second straight pipe is fixed with a release device;
the release device comprises a release seat, a V-shaped notch is formed in the upper end face of the release seat, a V-shaped groove is formed in the inner side wall of the V-shaped notch, a through hole is formed in the upper end of the release seat and is close to one side of a straight rod, a clamping lock is arranged in the through hole in a sliding mode, a pull rod is arranged close to one side of the straight rod, a plug is arranged at the left end of the through hole, the left end of the pull rod penetrates out of the plug, a spring is sleeved on the pull rod in the through hole, an elliptical ring is arranged at the other end of the pull rod, the spring can be compressed by pulling the pull rod to move the clamping lock, a;
the connecting piece is a V-shaped clamping seat arranged at the tail part of the lower end of the unmanned aerial vehicle, the V-shaped clamping seat is matched with the V-shaped groove, a bayonet is arranged at the position of the side edge of the V-shaped clamping seat corresponding to the through hole, and the bayonet is matched with the bayonet;
the inner wall of the box type base is provided with a rotating speed sensor, the rotating speed sensor is aligned to a first straight pipe, an inner stator of the rotary connector is fixed on the first straight pipe, a wiring end of the inner stator of the rotary connector is connected with a wiring end of a steering engine through a wire, a wiring end of a rotor at the outer end of the rotary connector is connected with a controller through a wire, and a motor, an electric control hydraulic brake and the rotating speed sensor are all connected with the controller through wires.
2. The rotating centrifugal accelerating takeoff device of the light and small unmanned aerial vehicle as claimed in claim 1, characterized in that: the power supply adopts a generator or a battery.
3. The rotating centrifugal accelerating takeoff device of the light and small unmanned aerial vehicle as claimed in claim 1, characterized in that: the middle part of the side face of the V-shaped clamping seat is provided with a connecting sheet, and the unmanned aerial vehicle and the V-shaped clamping seat are fixed through the bolt fixing connecting sheet.
4. The rotating centrifugal accelerating takeoff device of the light and small unmanned aerial vehicle as claimed in claim 1, characterized in that: the outer end of the rocker arm of the steering engine is provided with a cylindrical bulge, the cylindrical bulge is arranged in the elliptical ring sliding inner ring, and the cylindrical bulge can slide in the elliptical ring sliding inner ring.
5. The rotating centrifugal accelerating takeoff device of the light and small unmanned aerial vehicle as claimed in claim 1, characterized in that: the first straight pipe is communicated with the second straight pipe, a first wiring hole is formed in the side wall of the lower end portion of the first straight pipe, and a second wiring hole is formed in the side wall of the outer end portion of the second straight pipe.
6. The rotating centrifugal accelerating takeoff device of the light and small unmanned aerial vehicle as claimed in claim 5, wherein: and the conducting wire connected between the stator wiring end in the rotary connector and the wiring end of the steering engine is arranged in the first straight pipe and the first straight pipe, and the two ends of the conducting wire are respectively connected with the stator wiring end through the first wiring hole and the wiring end of the steering engine through the second wiring hole.
7. The rotating centrifugal accelerating takeoff device of the light and small unmanned aerial vehicle as claimed in claim 1, characterized in that: the first straight pipe and the second straight pipe are welded and fixed, and the second straight pipe and the release device are welded and fixed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920408064.3U CN209921629U (en) | 2019-03-28 | 2019-03-28 | Rotatory centrifugation of light small-size unmanned aerial vehicle takes off device with higher speed |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920408064.3U CN209921629U (en) | 2019-03-28 | 2019-03-28 | Rotatory centrifugation of light small-size unmanned aerial vehicle takes off device with higher speed |
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| Publication Number | Publication Date |
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| CN209921629U true CN209921629U (en) | 2020-01-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201920408064.3U Active CN209921629U (en) | 2019-03-28 | 2019-03-28 | Rotatory centrifugation of light small-size unmanned aerial vehicle takes off device with higher speed |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109850176A (en) * | 2019-03-28 | 2019-06-07 | 河南机电职业学院 | A kind of small-sized unmanned plane rotating centrifugal acceleration launching apparatus |
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2019
- 2019-03-28 CN CN201920408064.3U patent/CN209921629U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109850176A (en) * | 2019-03-28 | 2019-06-07 | 河南机电职业学院 | A kind of small-sized unmanned plane rotating centrifugal acceleration launching apparatus |
| CN109850176B (en) * | 2019-03-28 | 2023-12-22 | 河南机电职业学院 | Rotary centrifugal acceleration take-off device of light unmanned aerial vehicle |
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