CN210149580U - Composite wing unmanned aerial vehicle stop device - Google Patents
Composite wing unmanned aerial vehicle stop device Download PDFInfo
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- CN210149580U CN210149580U CN201921021967.2U CN201921021967U CN210149580U CN 210149580 U CN210149580 U CN 210149580U CN 201921021967 U CN201921021967 U CN 201921021967U CN 210149580 U CN210149580 U CN 210149580U
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Abstract
The utility model discloses a composite wing unmanned aerial vehicle arrester (-tor), including fixed strorage device and controller, fixed strorage device's top is provided with meteorological station and floating gate, floating gate swing joint is in fixed strorage device top, be provided with in the fixed strorage device and shut down the platform, it is connected with platform elevating gear to shut down the platform bottom, it includes position control mechanism to shut down the platform, position control mechanism is including setting up in four push rods all around of shutting down the platform, every push rod all is connected with a push rod actuating mechanism, the push rod includes horizontal push rod and vertical push rod, horizontal push rod and vertical push rod are not in same horizontal plane in vertical direction. The utility model discloses can dispose near compound wing unmanned aerial vehicle operation place for a long time, improve the ageing and the regional coverage ability of compound wing unmanned aerial vehicle emergency operation, through setting up meteorological station, receive meteorological data in real time, can judge the condition of rising and falling according to meteorological data to the model characteristics automatic adjustment angle of taking off according to compound wing unmanned aerial vehicle.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field specifically is a compound wing unmanned aerial vehicle arrester (-tor).
Background
Fixed-wing multi-rotor composite unmanned aerial vehicle is a novel aircraft different from traditional fixed-wing and rotor unmanned aerial vehicles. The multi-rotor system is additionally arranged on the fixed-wing flying platform, so that the vertical take-off and landing and hovering capabilities are obtained, and the cruise speed and range advantages of the fixed-wing unmanned aerial vehicle are achieved. Compared with other unmanned aerial vehicle systems, the composite wing unmanned aerial vehicle has obvious advantages. Compared with a helicopter, the composite wing unmanned aerial vehicle has the advantages of simple structure, low cost, high safety and long endurance time; compared with a multi-rotor wing, the composite wing unmanned aerial vehicle has long flight time, large flight range, high cruising speed and good stable flight performance under complex meteorological conditions; compared with a fixed wing, the composite wing unmanned aerial vehicle has no special runway, and is wide in application field, low in use difficulty and flexible in launching position.
The composite wing unmanned aerial vehicle is generally used for emergency operation, and is usually an area which is difficult for people to reach, and the timeliness and the area coverage capability in the operation are one of key points for ensuring the operation efficiency of the unmanned aerial vehicle. At present, because of lacking the unmanned aerial vehicle arresting gear of long-term deployment, flight each time all needs the staff to take unmanned aerial vehicle to arrive near scene and take off, has weakened the efficiency that unmanned aerial vehicle was on duty greatly. Therefore, a composite wing drone halting device is urgently needed.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a compound wing unmanned aerial vehicle stop device can arrange near operation place for a long time to improve compound wing unmanned aerial vehicle emergency operation's ageing and regional coverage ability, in addition, can judge the condition of rising and falling according to near the meteorological condition of stop device, and according to compound wing unmanned aerial vehicle's model characteristics automatic adjustment angle of taking off.
In order to achieve the purpose, the utility model provides a composite wing unmanned aerial vehicle stopping device, which comprises a fixed storage device and a controller, wherein the top of the fixed storage device is provided with a meteorological station and a movable door, the movable door is movably connected with the top of the fixed storage device, a stopping platform is arranged in the fixed storage device, the bottom of the stopping platform is connected with a platform lifting device, the meteorological station and the movable door are respectively and electrically connected with the controller,
the shutdown platform comprises a position adjusting mechanism, the position adjusting mechanism comprises four push rods arranged on the periphery of the shutdown platform, each push rod is connected with a push rod driving mechanism, the push rod driving mechanisms are electrically connected with the controller, each push rod comprises a transverse push rod and a longitudinal push rod, the transverse push rods and the longitudinal push rods are not located on the same horizontal plane in the vertical direction, the transverse push rods are prevented from colliding with the longitudinal push rods, damage is avoided, and the position adjusting mechanism moves the unmanned aerial vehicle to a target position through the push rods.
Furthermore, hemispherical bulges are distributed on the surface of the shutdown platform.
Further, the relation between the diameter D of the hemispherical protrusion and the width L of the support part of the composite wing unmanned aerial vehicle is as follows: d is less than or equal to L. Wherein, the supporting part of the composite wing unmanned aerial vehicle is usually a roller or a supporting rod, and here, the width L of the supporting part is the width of the roller or the width of the supporting rod. When the push rod promotes unmanned aerial vehicle, for the stability when guaranteeing unmanned aerial vehicle and removing, avoid unmanned aerial vehicle's supporting part can not block in the recess between the hemisphere type arch, or because of the recess between the hemisphere type arch takes place to shake or slope, the bellied diameter D of hemisphere type and compound wing unmanned aerial vehicle's supporting part width L must satisfy D and be less than or equal to L.
Further, the surface of the shutdown platform is fully paved with the balls, and of course, the relationship between the diameter D 'of the balls and the width L of the support part of the composite wing unmanned aerial vehicle also needs to satisfy D' less than L.
When the advancing direction of push rod is inconsistent with the roll direction of unmanned aerial vehicle supporting part, the supporting part of unmanned aerial vehicle takes place violent friction with the platform surface of shutting down easily, cause the damage to unmanned aerial vehicle, therefore, the surface of shutting down the platform is covered with the hemisphere arch or is covered with the ball, can effectively reduce unmanned aerial vehicle and the frictional force of shutting down the platform surface, make position control mechanism remove unmanned aerial vehicle to the target location more easily, avoided the problem that the unmanned aerial vehicle supporting part and shut down the platform surface and take place violent friction and cause the damage.
Further, the meteorological station comprises a wind direction sensor, a wind force sensor, a rain and snow sensor, a humidity sensor and an air pressure sensor. The weather station transmits weather data such as wind direction, wind power, wind speed, humidity and air pressure to the controller in real time, and the controller judges whether the composite wing unmanned aerial vehicle can take off and land according to preset take-off and landing conditions.
Further, platform elevating gear includes lift platform, lift base, base cylinder and is located the crane between lift platform and the lift base, the crane is two mutual articulated connecting rods, lift platform's bottom surface is provided with first slide, the top sliding connection of connecting rod is in first slide, lift base's top surface is provided with the second slide, the bottom sliding connection of connecting rod is in the second slide, the base cylinder sets up the top surface at lift base, the output and the at least one of base cylinder the bottom of connecting rod is connected.
Further, the push rod driving mechanism is at least one push rod cylinder.
Furthermore, the length of the push rod is the same as the side length of the shutdown platform where the push rod is located, so that the action range of the push rod can cover the whole shutdown platform.
Further, what shut down the platform is provided with a plurality of cameras that shut down the platform center towards all around, the camera is connected with the controller electricity, when shutting down the completion back, carries out visual inspection through the camera to composite wing unmanned aerial vehicle's exterior structure, looks over whether have the bad part.
Further, the shutdown platform further comprises an angle adjusting mechanism, the angle adjusting mechanism comprises a rotating disk and a rotating disk driving mechanism, the rotating disk is arranged at the center of the surface of the shutdown platform, the rotating disk driving mechanism is arranged inside the shutdown platform, the rotating disk driving mechanism is electrically connected with the controller, and the rotating disk driving mechanism drives the rotating disk to rotate on the shutdown platform. The rotary disk driving mechanism is a prior art, and the specific structure thereof is not described in detail herein.
Further, the shutdown platform further comprises a charging system, and the charging system is electrically connected with the controller.
Compared with the prior art, the beneficial effects of the utility model are that: the utility model can be deployed near the operation site of the composite wing unmanned aerial vehicle for a long time, and the timeliness and the area coverage capability of the emergency operation of the composite wing unmanned aerial vehicle are improved; the utility model discloses a set up meteorological station, real-time reception meteorological data can judge the condition of rising and falling according to meteorological data to according to compound wing unmanned aerial vehicle's model characteristics automatic adjustment angle of taking off, make compound wing unmanned aerial vehicle also can take off at strong wind weather.
Drawings
Fig. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic structural view of the intermediate shutdown platform of the present invention (the hemispherical protrusion is not shown);
FIG. 3 is a schematic structural view of a hemispherical protrusion of the present invention;
fig. 4 is a schematic structural view of the middle platform lifting device of the present invention;
fig. 5 is an electrical connection block diagram of the present invention;
in the figure: 100. fixing the storage device; 200. a controller; 300. a weather station; 400. a movable door; 500. a shutdown platform; 510. a push rod; 520. a push rod drive mechanism; 530. a hemispherical bulge; 540. a camera; 600. a platform lifting device; 610. a lifting platform; 611. a first slideway; 612. a second slideway; 620. a lifting base; 630. a base cylinder; 640. a connecting rod; 710. rotating the disc; 720. a rotating disk drive mechanism; 800. provided is a charging system.
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 fig. 1-5, a composite wing unmanned aerial vehicle stopping device comprises a fixed storage device 100 and a controller 200, a weather station 300 and a movable door 400 are arranged on the top of the fixed storage device 100, the movable door 400 is movably connected to the top of the fixed storage device 100, a stopping platform 500 is arranged in the fixed storage device 100, a platform lifting device 600 is connected to the bottom of the stopping platform 500, the weather station 300 and the movable door 400 are respectively electrically connected with the controller 200,
as shown in fig. 2, the shutdown platform 500 includes a position adjusting mechanism, the position adjusting mechanism includes four push rods 510 arranged around the shutdown platform 500, each push rod 510 is connected with a push rod driving mechanism 520, the push rod driving mechanism 520 is electrically connected with the controller 200, the push rod driving mechanism 520 is at least one push rod cylinder, the push rods 510 include a transverse push rod and a longitudinal push rod, the transverse push rod and the longitudinal push rod are not in the same horizontal plane in the vertical direction, the transverse push rod is prevented from colliding with the longitudinal push rod to cause damage, and the position adjusting mechanism moves the unmanned aerial vehicle to a target position through the push rods 510. The length of the push rod 510 is the same as the side length of the shutdown platform 500 where the push rod 510 is located, so that the action range of the push rod 510 can cover the whole shutdown platform 500.
When the propulsion direction of push rod 510 is inconsistent with the roll/moving direction of unmanned aerial vehicle supporting part, the supporting part of unmanned aerial vehicle takes place violent friction with stopping platform 500 surface easily, causes the damage to unmanned aerial vehicle, consequently, as shown in fig. 3, the surface of stopping platform 500 is covered with hemisphere type arch 530, or is covered with the ball. Wherein, the relation of the diameter D of the hemispherical bulge 530 and the width L of the support part of the composite wing unmanned aerial vehicle is as follows: d is less than or equal to L. The support part of the composite wing drone is usually a roller or a support rod, where the support part width L is the width of the roller or the width of the support rod. When push rod 510 promoted unmanned aerial vehicle, for the stability when guaranteeing unmanned aerial vehicle and removing, avoid unmanned aerial vehicle's supporting part can not block in the recess between the protruding 530 of hemisphere, or take place to shake or slope because of the recess between the protruding 530 of hemisphere, the diameter D of the protruding 530 of hemisphere and compound wing unmanned aerial vehicle's supporting part width L must satisfy D and be less than or equal to L. Of course, the relationship between the diameter D 'of the balls and the width L of the support portion of the compound wing drone should also satisfy D' ≦ L.
The surface of stopping platform 500 is covered with hemispherical bulges 530 or is covered with balls, so that the friction force between the unmanned aerial vehicle and the surface of stopping platform 500 can be effectively reduced, the position adjusting mechanism can move the unmanned aerial vehicle to a target position more easily, and the problem that the damage is caused by severe friction between the supporting part of the unmanned aerial vehicle and the surface of stopping platform 500 is avoided.
Specifically, the weather station 300 includes a wind direction sensor, a wind force sensor, a rain and snow sensor, a humidity sensor, and an air pressure sensor. The meteorological station 300 transmits meteorological data such as wind direction, wind power, wind speed, humidity, air pressure and the like to the controller 200 in real time, and the controller 200 judges whether the composite wing unmanned aerial vehicle can take off and land according to preset take-off and landing conditions.
Specifically, as shown in fig. 4, the platform lifting device 600 includes a lifting platform 610, a lifting base 620, a base cylinder 630, and a lifting frame located between the lifting platform 610 and the lifting base 620, the lifting frame is two mutually hinged connecting rods 640, a first slide rail 611 is provided on the bottom surface of the lifting platform 610, the top end of the connecting rod 640 is slidably connected in the first slide rail 611, a second slide rail 612 is provided on the top surface of the lifting base 620, the bottom end of the connecting rod 640 is slidably connected in the second slide rail 612, the base cylinder 630 is provided on the top surface of the lifting base 620, and the output end of the base cylinder 630 is connected with the bottom end of at least one connecting rod 640.
Shut down platform 500 be provided with a plurality of cameras 540 that shut down the platform center towards all around, camera 540 is connected with controller electricity 200, when shutting down the completion back, carries out visual inspection through camera 540 to composite wing unmanned aerial vehicle's exterior structure, checks whether there is the damage part.
The shutdown platform 500 further comprises an angle adjusting mechanism, the angle adjusting mechanism comprises a rotating disk 710 and a rotating disk driving mechanism 720, the rotating disk 710 is arranged in the center position of the surface of the shutdown platform 500, the rotating disk driving mechanism 720 is arranged inside the shutdown platform 500, the rotating disk driving mechanism 720 is electrically connected with the controller 200, and the rotating disk driving mechanism 720 drives the rotating disk 710 to rotate on the shutdown platform 500. The rotary disk driving mechanism 720 is a conventional one, and the specific structure thereof will not be described in detail herein.
The docking station 500 further includes a charging system 800, the charging system 800 being connected to the controller electronics 200.
The working principle is as follows:
the weather station 300 transmits weather data such as wind direction, wind power, wind speed, humidity and air pressure to the controller 200 in real time, the controller 200 judges whether the composite wing unmanned aerial vehicle can take off and land according to preset take-off and landing conditions, when the weather data meet the preset take-off conditions and the controller 200 receives a take-off instruction, the controller 200 opens the movable door 400 at the top of the fixed storage device 100, the platform lifting device 600 ascends to shut down the platform 500, the angle adjusting mechanism turns the nose of the composite wing unmanned aerial vehicle to the windward direction, and the composite wing unmanned aerial vehicle can be ready to take off;
when meteorological data satisfies predetermined descending condition and controller 200 receives the descending instruction, controller 200 opens fixed strorage device top 100's floating gate 400, platform elevating gear 600 rises and shuts down platform 500, compound wing unmanned aerial vehicle descends to shutting down platform 500 on, position control mechanism's push rod 410 resets after pushing away compound wing unmanned aerial vehicle to the target location, this target location is the central point that shuts down platform 500 usually, later angle adjusting mechanism drives compound wing unmanned aerial vehicle rotatory, orientation and the target orientation unanimous to compound wing unmanned aerial vehicle, the orientation of adjustment compound wing unmanned aerial vehicle and the unanimous aim at of target orientation: visual inspection is facilitated through the camera 540, and the charging system 800 is also facilitated to charge the composite wing unmanned aerial vehicle.
It is obvious to a person skilled in the art that the invention is not restricted to details of the above-described exemplary embodiments, but that it can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (10)
1. A composite wing unmanned aerial vehicle stopping device is characterized by comprising a fixed storage device and a controller, wherein a meteorological station and a movable door are arranged at the top of the fixed storage device, the movable door is movably connected to the top of the fixed storage device, a stopping platform is arranged in the fixed storage device, a platform lifting device is connected to the bottom of the stopping platform, the meteorological station and the movable door are respectively and electrically connected with the controller,
the shutdown platform comprises a position adjusting mechanism, the position adjusting mechanism comprises four push rods arranged on the periphery of the shutdown platform, each push rod is connected with a push rod driving mechanism, the push rod driving mechanisms are electrically connected with the controller, each push rod comprises a transverse push rod and a longitudinal push rod, and the transverse push rods and the longitudinal push rods are not in the same horizontal plane in the vertical direction.
2. The compound wing drone arrester of claim 1, wherein the surface of the arrester platform is covered with hemispherical bumps.
3. The stop device of claim 2, wherein the diameter D of the hemispherical protrusion and the width L of the support portion of the composite wing drone are in the following relationship: d is less than or equal to L.
4. The compound wing drone arrester of claim 1, wherein the surface of the arrester platform is flooded with balls.
5. The compound wing drone arrester of claim 1, wherein the weather station includes a wind direction sensor, a wind sensor, a rain and snow sensor, a humidity sensor, and an air pressure sensor.
6. The stop device of a compound wing unmanned aerial vehicle according to claim 1, wherein the platform lifting device comprises a lifting platform, a lifting base, a base cylinder and a lifting frame between the lifting platform and the lifting base, the lifting frame is two mutually hinged connecting rods, the bottom surface of the lifting platform is provided with a first slide way, the top end sliding connection of the connecting rods is in the first slide way, the top surface of the lifting base is provided with a second slide way, the bottom end sliding connection of the connecting rods is in the second slide way, the base cylinder is arranged on the top surface of the lifting base, and the output end of the base cylinder is connected with at least one of the bottom ends of the connecting rods.
7. The compound wing drone arresting device of claim 1, wherein the pushrod drive mechanism is at least one pushrod cylinder.
8. The compound wing drone arresting device of claim 1, wherein a plurality of cameras are disposed around the platform toward the center of the platform, the cameras being electrically connected to the controller.
9. The compound wing drone arrester of claim 1, wherein the arrester platform further comprises an angle adjustment mechanism, the angle adjustment mechanism comprising a rotating disk and a rotating disk drive mechanism, the rotating disk being disposed centrally on the surface of the arrester platform, the rotating disk drive mechanism being disposed within the arrester platform, the rotating disk drive mechanism being electrically connected to the controller, the rotating disk drive mechanism driving the rotating disk to rotate on the arrester platform.
10. The compound wing drone arresting device of claim 1, wherein the arresting platform further comprises a charging system electrically connected with the controller.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201921021967.2U CN210149580U (en) | 2019-07-03 | 2019-07-03 | Composite wing unmanned aerial vehicle stop device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201921021967.2U CN210149580U (en) | 2019-07-03 | 2019-07-03 | Composite wing unmanned aerial vehicle stop device |
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| CN210149580U true CN210149580U (en) | 2020-03-17 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114003049A (en) * | 2020-07-28 | 2022-02-01 | 丰田自动车株式会社 | Flying object takeoff control system |
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2019
- 2019-07-03 CN CN201921021967.2U patent/CN210149580U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114003049A (en) * | 2020-07-28 | 2022-02-01 | 丰田自动车株式会社 | Flying object takeoff control system |
| CN114003049B (en) * | 2020-07-28 | 2024-04-26 | 丰田自动车株式会社 | Flying object take-off control system |
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