CN108016607B

CN108016607B - Unmanned aerial vehicle take-off and landing device

Info

Publication number: CN108016607B
Application number: CN201610965173.6A
Authority: CN
Inventors: 杜淼森; 赵炳根; 赵自强; 王悦
Original assignee: BYD Co Ltd
Current assignee: BYD Co Ltd
Priority date: 2016-10-31
Filing date: 2016-10-31
Publication date: 2020-03-20
Anticipated expiration: 2036-10-31
Also published as: CN108016607A

Abstract

The utility model relates to an unmanned aerial vehicle take-off and landing device, including installation frame (4000) of top open-ended cell type with fix a plurality of take-off and landing platforms (3000) in installation frame (4000), every take-off and landing platform (3000) cooperate with corresponding unmanned aerial vehicle's undercarriage respectively. Can satisfy the requirement of a large amount of unmanned aerial vehicles' take-off, descending etc., be convenient for unified protection and management.

Description

Unmanned aerial vehicle take-off and landing device

Technical Field

The utility model relates to an unmanned aerial vehicle technique field specifically relates to an unmanned aerial vehicle take off and land device.

Background

At present, many unmanned aerial vehicles have been equipped with the undercarriage for landing adaptively on the platform of taking off and landing, in the correlation technique, it is steady inadequately when unmanned aerial vehicle descends, can't make stably berth on the platform of taking off and landing, in addition, because the positioning accuracy when descending to unmanned aerial vehicle requires higher, needs the zero deviation to descend, and the operation is comparatively complicated. And the cost is higher because an intelligent control system is required to be added frequently. In addition, present unmanned aerial vehicle take-off and landing platform can only adapt to the unmanned aerial vehicle of single model, unable multiple model of adaptation to a plurality of unmanned aerial vehicles can't berth simultaneously.

Disclosure of Invention

The utility model aims at providing an unmanned aerial vehicle take off and land device to satisfy the requirement of taking off, descending of a large amount of unmanned aerial vehicles etc. be convenient for unified protection and management.

In order to achieve the above object, the present disclosure provides an unmanned aerial vehicle take-off and landing device, including the installation frame of top open-ended cell type, and fix a plurality of take-off and landing platforms in the installation frame, every take-off and landing platform cooperates with corresponding unmanned aerial vehicle's undercarriage respectively.

Optionally, at least one of the plurality of take-off and landing platforms is a different size than the other take-off and landing platforms.

Optionally, the large-sized lifting platform is arranged at the center of the mounting frame, and the small-sized lifting platform is arranged at the periphery of the large-sized lifting platform.

Optionally, the lifting platform comprises a base, the base is fixed to the bottom surface of the mounting frame, the base is formed into a regular hexagon or a regular triangle, and the edges of the bases of the plurality of lifting platforms are fitted to form a honeycomb structure.

Optionally, the take-off and landing platform includes a base and an upper platform connected above the base, the upper platform and the base are arranged at intervals in the height direction and are formed with a central hole for the landing gear of the unmanned aerial vehicle to pass through, the upper platform includes an edge portion and a guide limiting part, the guide limiting part extends from the edge portion to be inclined inwards, the inner end of the guide limiting part and the base are arranged at intervals in the height direction and are formed as a side wall of the central hole.

Optionally, the guide limiting parts are uniformly arranged along the circumferential direction, and each guide limiting part is hinged to the edge part.

Optionally, each guide limit stop is hinged to the edge by a spring hinge.

Optionally, the landing platform further comprises a support mechanism, the upper platform is formed into a regular polygon, and the regular support mechanism is supported between the corner of the upper platform and the base.

Optionally, a socket corresponding to the position of the central hole is arranged on the base.

Optionally, the lifting platform further comprises a supporting mechanism, the supporting mechanism is telescopically supported between the upper platform and the base, the supporting mechanism comprises a first sleeve assembly for driving the upper platform to lift, the first sleeve assembly comprises a first driving device fixed on the base, a lifting sleeve connected to an output end of the first driving device, and a lifting rod fixed on the upper platform, and the lifting rod is in threaded fit with the lifting sleeve.

Optionally, the support mechanism further comprises a second sleeve assembly for guiding the upper platform to ascend and descend, the second sleeve assembly comprises a guide sleeve fixed on the base and a guide rod fixed on the upper platform, the guide rod is in sliding fit with the guide sleeve, and the first sleeve assembly and the second sleeve assembly are respectively multiple and are uniformly and alternately arranged along the circumferential direction.

Through above-mentioned technical scheme, set up a plurality of platforms that take off and land in an open-ended installation frame, the corresponding unmanned aerial vehicle undercarriage of difference adaptation can satisfy a large amount of unmanned aerial vehicle's take off, the requirement of descending etc. is convenient for unify protection and management.

Additional features and advantages of the disclosure will be set forth in the detailed description which follows.

Drawings

The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this specification, illustrate embodiments of the disclosure and together with the description serve to explain the disclosure without limiting the disclosure. In the drawings:

figure 1 is a schematic structural view of a landing gear body in an unmanned aerial vehicle landing gear according to one embodiment of the present disclosure;

fig. 2 is a schematic structural view of a locking mechanism in a landing gear of an unmanned aerial vehicle according to one embodiment of the present disclosure;

fig. 3 is a schematic structural diagram of a drone according to one embodiment of the present disclosure;

fig. 4 is a schematic structural diagram of an unmanned aerial vehicle take-off and landing platform according to an embodiment of the present disclosure;

fig. 5 is a schematic diagram of a drone in cooperation with a take-off and landing platform according to one embodiment of the present disclosure;

fig. 6 is a schematic structural diagram of a takeoff and landing device of an unmanned aerial vehicle according to an embodiment of the present disclosure;

fig. 7 is a schematic structural diagram of a takeoff and landing device of an unmanned aerial vehicle according to another embodiment of the present disclosure;

fig. 8 is a schematic structural diagram of a takeoff and landing device of an unmanned aerial vehicle according to another embodiment of the present disclosure;

FIG. 9 is a schematic structural diagram of an electric vehicle according to one embodiment of the present disclosure;

FIG. 10 is a schematic view of an application scenario of the electric vehicle in the embodiment shown in FIG. 9;

fig. 11 is a schematic structural view of an electric vehicle according to another embodiment of the present disclosure;

fig. 12 is a plan view of the electric vehicle in the embodiment shown in fig. 11;

FIG. 13 is a schematic illustration of the installation of the take-off and landing gear of the embodiment shown in FIG. 11;

fig. 14 is an application scenario diagram of the drone in the embodiment shown in fig. 11.

Description of the reference numerals

1000 unmanned plane

2000 unmanned aerial vehicle undercarriage 2100 undercarriage body

2110 guide hole 2111 guide groove

2120 mounting plate 2200 locking mechanism

2210 locking block 2211 projection

2220 guide post 2230 central shaft

2240 first link 2250 second link

2300 second driving device 2400 pressure sensor

2500 plug 3300 supporting mechanism

3000 take-off and landing platform 3100 base

3110 socket 3120 protective cover

3200 upper platform 3210 direction locating part

3220 spring hinge 3310 first driving device

3320 lifting sleeve 3330 lifting rod

3340 guide sleeve 3350 guide rod

4000 attachment frame 4100 base

5000 electric automobile 5100 vehicle charger

5200 voltage adjusting device 5300 power battery pack

5400 electric wire 5500 vehicle power system

5600

sealing ring

5700, 5800 charging port

5900 cabin cover

Detailed Description

The following detailed description of specific embodiments of the present disclosure is provided in connection with the accompanying drawings. It should be understood that the detailed description and specific examples, while indicating the present disclosure, are given by way of illustration and explanation only, not limitation.

In the present disclosure, without being stated to the contrary, the use of directional words such as "up and down" generally refers to the up and down of the drone in a steady flight condition and while landing, and "inside and outside" is with respect to the self-profile of the respective component.

The utility model provides an unmanned aerial vehicle undercarriage and with this undercarriage complex take off and land platform and take off and land device. As shown in fig. 1 to 3, the present disclosure provides an unmanned aerial vehicle landing gear 2000 including a landing gear body 2100 for being disposed at the bottom of an unmanned aerial vehicle 1000, and a locking mechanism 2200 accommodated in the landing gear body 2100, wherein a guide hole 2110 is formed in a side wall of the landing gear body 2100, and the locking mechanism 2200 includes a lock block 2210 and a driving mechanism for driving the lock block 2210 to extend out of and retract into the guide hole 2110. In this way, when the unmanned aerial vehicle 1000 is in a flight state, the locking mechanism 2200 is accommodated in the landing gear body and cannot be damaged by impact, and when the unmanned aerial vehicle 1000 lands, the locking block 2210 extends out from the side wall of the landing gear body 2100, so that the unmanned aerial vehicle 1000 can be locked on the landing platform 3000 shown in fig. 4, for example, and the stability of the unmanned aerial vehicle 1000 during parking is improved.

Further, as shown in fig. 1 to 3, the guide holes 2110 may be plural and arranged at intervals in the axial direction of the landing gear body 2100, and accordingly, the lock blocks 2210 may also be plural corresponding to the guide holes 2110, that is, the lock blocks 2210 of different height positions may be used to position the unmanned aerial vehicle 1000 so that the unmanned aerial vehicle 1000 may be parked at a suitable height. As shown in fig. 2, a plurality of axially aligned lock blocks 2210 may be integrally connected by means of guide posts 2220 extending in the axial direction, it being noted that, as shown in fig. 2, the guide posts 2220 are formed on the inner periphery of the main body portion of the lock block 2210, i.e., to ensure that the guide posts 2220 do not interfere with the extension and retraction of the lock block 2210.

Further, the guiding hole 2110 can be for the multiseriate that evenly arranges along circumference, and the locking piece 2210 forms into the multiseriate that corresponds for locking mechanism 2200 can be fixed a position unmanned aerial vehicle 1000 evenly along circumference, avoids unmanned aerial vehicle 1000 to berth the back and moves along radial, has improved overall structure's stability. Alternatively, in the disclosure, as shown in fig. 1 and fig. 2, the guide holes 2110 and the lock blocks 2210 may be arranged in three rows, respectively, so as to meet the requirement of circumferential positioning of the drone 1000, and the structure has high compactness, and avoid the problems of processing difficulty and mutual interference of components caused by too many rows.

In order to position the lock block 2210 in the guide hole 2110 and to slidably fit the lock block 2210 in the guide hole 2110, as shown in fig. 1, guide grooves 2111 may be formed on hole walls at both ends of the guide hole 2110, and as shown in fig. 2, protrusions 2211 slidably fit the guide grooves 2111 are protruded outward at both ends of the lock block 2210. Thus, when the lock block 2210 slides in the guide hole 2110, the projection 2211 can be in contact fit with the guide groove 2111 only, and the reduction of the service life caused by the contact abrasion of the lock block 2210 and the guide hole 2110 can be avoided.

Further, the above-described driving mechanism may include a rotatable center shaft 2230, a first link 2240 fixedly coupled to the center shaft 2230, and a second link 2250 coupled to the lock block 2210, wherein when the locking mechanism is in the form of coupling a plurality of lock blocks 2210 by guide posts 2220 as shown in fig. 2, the second link 2250 may be coupled to the guide posts 2220, and further, the first link 2240 and the second link 2250 are coupled to each other, and the lock block 2210 is at least partially received in the guide hole 2110. That is, a crank slider structure is formed between the driving mechanism, the lock block 2210 and the guide hole 2110, wherein the center shaft 2230 and the first link 2240 are cranks in the crank slider structure, the second link 2250 is a link in the crank slider structure, the lock block 2210 is a slider in the crank slider structure, and the guide hole 2110 is a frame in the crank slider structure, and thus the rotational motion of the center shaft 2230 is converted into the linear reciprocating motion of the lock block 2210, and the locking and unlocking functions of the lock block 2210 can be realized.

Further, as shown in fig. 3, a second driving device 2300 is disposed above the central shaft 2230 for driving the central shaft 2230 to rotate, and in this embodiment, the second driving device 2300 may be a first motor fixed to the bottom of the drone 1000 and accommodated in the landing gear body 2100. The first motor outputs rotary motion to drive the crank-slider structure.

Further, as shown in fig. 3 and 4, the bottom of the landing gear body 2100 may be provided with a plug 2500, where the plug 2500 is disposed at the lowest end of the landing gear body 2100, and after the unmanned aerial vehicle 1000 lands, the plug 2500 may be in plugging fit with the socket 3110 on the landing platform 3000. In order to detect the pressure condition when the plug 2500 is in contact with the take-off and landing platform 3000 (specifically, the socket 3110), the plug 2500 may be integrated with a pressure sensor 2400, so as to ensure that the pressure range of the plug 2500 after plugging is within a reasonable area, ensure that the plug 2500 and the socket 3110 are connected normally, and avoid impact damage of parts.

As shown in fig. 1, in the present disclosure, the landing gear body 2100 may be formed as a tapered structure tapering from top to bottom to facilitate the landing gear body 2100 to slide downward, and the locking mechanism 2200 may also be formed as a tapered structure with a corresponding shape after the locking block 2210 extends out of the landing gear body 2100 to facilitate the positioning of the unmanned aerial vehicle 1000 in stages, and the specific form thereof will be further explained in the following description.

In addition, this disclosure still provides an unmanned aerial vehicle, and this unmanned aerial vehicle 1000's bottom is provided with foretell unmanned aerial vehicle undercarriage 2000. Specifically, the top of undercarriage body 2100 can outwards bulge outward at an interval has mounting panel 2120, has seted up the mounting hole on the mounting panel 2120 in order to fix undercarriage body 2100 on unmanned aerial vehicle 1000 through the fastener, and locking mechanical system forms in undercarriage body 2100 and can fix the bottom at unmanned aerial vehicle 1000 through second drive device 2300.

As shown in fig. 4, the present disclosure provides a landing platform 3000 including a base 3100 and an upper platform 3200 attached above the base 3100, the upper platform 3200 being spaced apart from the base 3100 in a height direction and formed with a center hole for passing an unmanned landing gear 2000 therethrough, that is, the unmanned landing gear 2000 passes through the center hole, and a lock block 2210 passes through a guide hole 2110 in a landing gear body 2100, so that the unmanned aerial vehicle 1000 can be fixed to the landing platform 3000. The upper stage 3200 includes an edge portion and a guiding position-limiting member 3210, wherein the edge portion of the upper stage 3200 is an outer frame of the upper stage 3200. As shown in fig. 4 and 5, in the present embodiment, the guide stopper 3210 is a plate-shaped structure, and the locking form between the landing gear 2000 of the unmanned aerial vehicle and the landing platform 3000 is such that the guide stopper 3210 is clamped by a lock block 2210 to position the unmanned aerial vehicle 1000 in height. Wherein, the locking block 2210 may be formed with a groove so that the guide stopper 3210 may be inserted into the groove; alternatively, the guide limit pieces 3210 may be inserted between two adjacent axially arranged locking blocks 2210, i.e., in the embodiment shown in fig. 1 to 3, the drone 1000 may also be positioned in height.

Further, direction locating part 3210 follows limit portion's leanin downwardly extending, and like this, unmanned aerial vehicle 1000 can carry out primary localization through this inclined plane structure when descending, and unmanned aerial vehicle undercarriage 2000 is under the effect of the direction locating part 3210 of slope, and the central zone of landing platform 3000 is landing to subsequent accurate positioning gradually. When the initial positioning, the unmanned aerial vehicle 1000 only needs to be located above the landing platform 3000 region, and the accurate positioning can be performed through the inclined guide limit part 3210. Further, as shown in fig. 4 and 5, the inner end of the guide stopper 3210 is spaced apart from the base 3100 in the height direction and is formed as a side wall of the above-described center hole, so that the unmanned landing gear 2000 is formed between the base 3100 and the upper deck 3200.

Specifically, the direction locating part 3210 is a plurality of along evenly laying of circumference, and every direction locating part 3210 articulates respectively in limit portion for the size of centre bore can change along with the rotation of direction locating part 3210, and like this, its impact force can drive the rotation of direction locating part 3210 when passing the centre bore of unmanned aerial vehicle undercarriage 2000, avoids the limit portion rigid connection of direction locating part 3210 and upper platform 3200 to lead to the impact destruction. Optionally, the direction locating part 3210 has a smaller rotatable range, that is, the hinge joint between the direction locating part 3210 and the upper platform 3200 is provided with a limiting structure, so that the direction locating part 3210 can support the dead weight of the unmanned aerial vehicle 1000, and the unmanned aerial vehicle 1000 is prevented from directly impacting the base 3100 after landing. Further, each guiding position-limiting member 3210 may be hinged to an edge portion by a spring hinge 3220, respectively, so that the guiding position-limiting member 3210 may automatically return to a natural state after the unmanned aerial vehicle 1000 is separated from the landing platform 3000. It should be noted that the spring hinge 3220 itself is a structure known to those skilled in the art, and it is equivalent to adding a torsion spring at the hinge joint of the ordinary hinge, so that the spring hinge can return under the elastic action after being forced to rotate, for example, a hinge on a door capable of being pushed and pulled bilaterally. It should be noted here that the spring hinge 3220 has a relatively high strength, that is, the guide limiting member 3210 can be ensured to support the self weight of the drone 1000, and the drone 1000 is prevented from continuously sinking to impact the base 3100 after landing due to the self weight.

Further, the upper platform 3200 may be formed as a regular polygon, which ensures that the upper platform 3200 has a central symmetrical structure, such as a regular quadrilateral or a regular hexagon structure as shown in the drawings, and has high stability and convenient processing. This regular polygon's bight passes through supporting mechanism 3300 to be supported on base 3100, guarantees the holistic homogeneity of platform 3000 that takes off and land promptly, and each part can receive even impact force when unmanned aerial vehicle 1000 descends in platform 3000 that takes off and land.

Further, as shown in fig. 4, a socket 3110 corresponding to the position of the central hole may be further disposed on the base 3100, and the socket 3110 is disposed right below the central hole to be in plug-in fit with the plug 2500 on the landing gear body 2100. Further, a protective cover 3120 is provided at the outer circumference of the socket 3110, and the protective cover 3120 is provided at intervals at the outer circumference of the socket 3110 to prevent the socket 3110 from being damaged by an impact from an external device.

Further, as shown in fig. 4, the upper stage 3200 is supported on the base 3100 by a support mechanism 3300, and the support mechanism 3300 may be a telescopic column structure, so that the height of the upper stage 3200 can be adjusted. Like this, the height after unmanned aerial vehicle 1000 is falling can be adjusted to the one side, and on the other hand can adjust as above plug 2500 and socket 3110 grafting cooperation, guarantees to connect stably.

Specifically, the supporting mechanism 3300 may include a first sleeve assembly for driving the upper platform 3200 to ascend and descend, the first sleeve assembly including a first driving means 3310 fixed on the base 3100, an ascending and descending sleeve 3320 connected to an output end of the first driving means 3310, and an ascending and descending rod 3330 fixed on the upper platform 3200, the ascending and descending rod 3330 being sleeved in the ascending and descending sleeve 3320 and threadedly engaged with the ascending and descending sleeve 3320. Specifically, the first driving device 3310 may be a second motor, and the second motor outputs a rotational motion to drive the lifting sleeve 3320 to rotate, and since the lifting rod 3330 is in threaded fit with the lifting sleeve 3320, and the height of the lifting sleeve 3320 is kept constant, the lifting rod 3330 moves in height under the action of the threaded pair, so as to drive the upper platform 3200 to move up and down. In order to stably support the upper deck 3200, the first sleeve assemblies are uniformly arranged in the circumferential direction of the lifting deck 3000.

Further, the supporting mechanism 3300 further includes a second sleeve assembly for guiding the upper platform 3200 to be lifted and lowered, the second sleeve assembly including a guide sleeve 3340 fixed on the base 3100 and a guide rod 3350 fixed on the upper platform 3200, the guide rod 3350 being slidably fitted with the guide sleeve 3340. That is, the second sleeve assembly plays a guiding role only when the upper stage 3200 moves up and down, so that the upper stage 3200 can stably move.

Further, the first sleeve component and the second sleeve component are respectively multiple and are uniformly and alternately arranged along the circumferential direction, sufficient driving force is guaranteed to drive the upper platform 3200, the second sleeve component which is only in sliding fit is arranged, thread fit is not needed, and cost is greatly reduced.

The landing and takeoff process of the drone 1000 in one embodiment of the present disclosure is briefly described below with reference to fig. 1 to 5.

In the flight state of the drone 1000, the locking mechanism 2200 is completely housed in the landing gear body 2100, i.e. the locking mechanism 2200 is in the unlocked state.

After the unmanned aerial vehicle 1000 receives the landing instruction, the unmanned aerial vehicle is firstly initially positioned above the take-off and landing platform 3000, and specifically, initially positioned above the guide limit part 3210. At this time, the first motor is controlled to drive the rotary shaft 2230 to rotate by a certain angle, and the locking block 2210 protrudes from the guide hole 2110 by using the principle of the crank slider structure. Meanwhile, under the slope guiding action of the guiding limit part 3210, the unmanned aerial vehicle 1000 further descends until reaching the central hole of the upper platform 3200. In this embodiment, the lock block 2210 is provided in plural numbers arranged in the axial direction, and the locking mechanism 2200 is formed in a tapered structure after the lock block 2210 protrudes out of the landing gear body 2100. In this way, the locking blocks 2210 at different heights form outer diameters of different sizes, the outer diameter of the locking block 2210 at least one height is larger than the diameter of the central hole, and under the action of gravity or driving force of the unmanned aerial vehicle 1000, the locking block 2210 at that height impacts the guide limiting member 3210 and passes through the central hole, so that the guide limiting member 3210 can be clamped between two adjacent locking blocks 2210, or between the locking block 2210 at the top and the bottom of the body of the unmanned aerial vehicle 1000. According to the different impact force of unmanned aerial vehicle 1000 to leading locating part 3210 to and the different external diameters that the lock piece 2210 formed, unmanned aerial vehicle 1000 can be fixed a position in the height department of difference. At this moment, unmanned aerial vehicle's accurate positioning has been realized. Further, the removal of control second motor drive first sleeve subassembly realization upper mounting platform 3200 ascending direction of height, upper mounting platform 3200 can drive the unmanned aerial vehicle 1000 removal that has fixed a position to make the plug 2500 of unmanned aerial vehicle 1000 bottom and the socket 3110 cooperation of pegging graft on the base 3100 of platform 3000 that takes off and land. It should be noted that the initial positioning of the unmanned aerial vehicle 1000 may be performed by manual remote control, or may be performed by a positioning system of the unmanned aerial vehicle 1000 itself, which is not specifically limited herein, depending on the specific use environment.

The takeoff process and the landing process of the drone 1000 are reverse operation processes, and only a simple description is given here. After unmanned aerial vehicle 1000 received the signal of taking off, at first make upper platform 3200 rise under the effect of second motor, plug 2500 and socket 3110 separation, rise to sufficient height after upper platform 3200, during landing gear body 2100 is withdrawed to lock block 2210, carry out the unblock operation promptly, unmanned aerial vehicle can take off this moment, and unmanned aerial vehicle takes off the back, and direction locating part 3210 can return to initial position under the effect of spring hinge.

As shown in fig. 6-8, the present disclosure also provides an unmanned aerial vehicle take-off and landing device, comprising a mounting frame 4000 of a trough type with an open top, and a plurality of take-off and landing platforms 3000 fixed in the mounting frame 4000, wherein the take-off and landing platforms 3000 may be the take-off and landing platforms 3000 described in detail above, for cooperating with landing gears of the respective unmanned aerial vehicle 1000. Especially, when last platform 3200 can reciprocate, unmanned aerial vehicle 1000 can be parked simultaneously to two adjacent platforms 3000 that take off and land, through high staggered arrangement for two unmanned aerial vehicle 1000 can not influence each other.

Further, at least one of these a plurality of take-off and landing platforms is different with other take-off and landing platform sizes, and this take-off and landing device can cooperate the unmanned aerial vehicle 1000 and the unmanned aerial vehicle undercarriage 2000 of multiple different models simultaneously like this.

Specifically, the lifting platform 3000 is fixed to the bottom surface of the mounting frame 4000 through the base 3100, and in order to stably support other components by the base 3100 and facilitate the mounting of the plurality of lifting platforms 3000, in one lifting platform 3000, the outer contour of the base 3100 may be the outer contour of the whole lifting platform 3000, so that when the lifting platform 3000 is mounted, only the cooperation between the plurality of bases 3100 needs to be considered, and interference is avoided. Further, the base 3100 may be fixed in the mounting frame 4000 in the form of bolts or snaps, and a specific fixing form thereof is not particularly limited herein.

In one embodiment, as shown in fig. 6 and 7, the base 3100 may be formed in a regular hexagon, with the edges of the base 3100 of the plurality of landing platforms 3000 being arranged in close proximity to form a honeycomb structure. In the embodiment shown in fig. 8, the base 3100 is formed in a rectangular shape, and edges of the base 3100 of the plurality of the lifting platforms 3000 are closely arranged to form a matrix structure, and both of the structures can make the structure of the lifting device compact. In other embodiments, the base 3100 may have other shapes, such as a regular triangle. It should be noted that, since the landing platforms 3000 may have different sizes, the honeycomb structure may be an approximate honeycomb structure, and the matrix structure may be an approximate matrix structure, for example, in fig. 7, three sizes of landing platforms are provided in this embodiment, and the pedestals 3100 are formed into an approximate honeycomb structure.

Further, in order to improve space utilization, the large-sized landing platform 3000 is disposed at the center of the mounting frame 4000, and the small-sized landing platform 3000 is disposed at the outer periphery of the large-sized landing platform 3000, that is, the small-sized landing platform 3000 is disposed in a smaller area of the edge portion of the mounting frame 4000, for example, in the embodiment shown in fig. 7, the small-sized landing platforms are disposed in four corners of the mounting frame 4000.

Further, the bottom of the mounting frame 4000 is provided with a base 4100 to be mounted on an external platform through the base 4100, wherein the mounting platform may be a moving vehicle, a ship, or a fixed base, etc. In other embodiments, a vehicle, a ship, or a base may be used as the base 4100.

The utility model discloses an electric automobile, as shown in fig. 9 and 11, electric automobile is provided with unmanned aerial vehicle take-off and landing platform 3000 including passing through on-vehicle charger 5100, voltage adjusting device 5200, power battery group 5300 and whole car driving system 5400 that electric wire 5500 connects in proper order on 5000 of electric automobile to make unmanned aerial vehicle can descend to electric automobile 5000, realize that electric automobile 5000 is in the unmanned aerial vehicle's of static, low-speed condition take-off and landing. Here, the take-off and landing platform 3000 may be the unmanned aerial vehicle take-off and landing platform 3000 described above. That is, electric automobile can regard as unmanned aerial vehicle 1000's base, and unmanned aerial vehicle 1000 can descend automatically to electric automobile 5000 on, and it is stable to stop. It should be noted that the voltage adjustment device 5200 may include a transformation device commonly used in electric vehicles such as a distribution box and a transformer, and the power system 5400 of the whole vehicle includes a power and control system, a corresponding transmission mechanism and an auxiliary system, which are all structures of a common electric vehicle, and are well known to those skilled in the art, and are not limited herein.

In addition, the position that electric wire 5500 passed electric automobile 5000's inside panel beating is equipped with sealing washer 5600 respectively in the cover, can stabilize the pencil on the one hand, and on the other hand can avoid each part to receive impurity influence.

In one embodiment of the present disclosure, as shown in fig. 9 and 10, the on-vehicle charger 5100, the voltage regulator 5200, and the take-off and landing platform 3000 are provided in a front compartment of the electric vehicle, the power battery pack 5300 is provided below a floor of a vehicle body of the electric vehicle, and the entire vehicle power system 5400 is provided in a rear compartment of the electric vehicle. To save storage space in the trunk compartment, the entire vehicle powertrain 5400 can be disposed below the trunk deck. As is well known to those skilled in the art, an electric vehicle is provided with a charging port at which an external charging device charges a power battery pack through an on-board charger. In the present embodiment, since the in-vehicle charger 5100 is disposed in the front compartment, the charging port 5700 of the electric vehicle may be disposed at a front grill of the electric vehicle, reducing a distance from the charging port 5700 to the in-vehicle charger 5100, thereby improving space utilization.

When the take-off and landing platform 3000 is installed in the front cabin, the base 3100 may be provided with an installation hole, and the base 3100 may be fixed in the front cabin by means of a threaded fastener, so as to achieve detachability of the take-off and landing platform 300. In addition, the landing platform 3000 may be integrated with the electric vehicle 5000, that is, the front deck bulkhead may be used as the base 3100 of the landing platform 3000.

Further, as shown in fig. 9, in the present embodiment, a nacelle cover 5900 of the front nacelle is hinged to the front end of the nacelle body of the front nacelle. Thus, as shown in fig. 10, in the process of landing or taking off the unmanned aerial vehicle, the canopy 5900 is turned up forward, and an operator can control the ascending and descending of the unmanned aerial vehicle in the vehicle. Specifically, unmanned aerial vehicle is in the region of two lines of vision, and operating personnel can observe unmanned aerial vehicle 1000's flight state better to control unmanned aerial vehicle 1000. After the landing or taking-off step is completed, the cabin cover 5900 is closed, and the normal running of the electric automobile 5000 is not influenced. For example, after unmanned aerial vehicle 1000 lands to the front deck, cabin cover 5900 closes, and the front deck can protect unmanned aerial vehicle 1000 as unmanned aerial vehicle 1000's accommodation space.

In one embodiment of the present disclosure, as shown in fig. 11 and 12, the entire vehicle power system 5400 may be provided in a front compartment of an electric vehicle, the power battery pack 5300 is provided below a floor panel of the electric vehicle, the on-board charger 5100 and the voltage adjustment device 5200 are provided below a trunk lid of a rear compartment of the electric vehicle, and the landing platform 3000 is mounted above the electric vehicle. In this embodiment, since the landing platform 3000 is provided outside the vehicle body, the utilization ratio of the space in the vehicle, particularly the storage space of the rear compartment, can be improved. In this case, as shown in fig. 11, since the in-vehicle charger 5100 is provided in the rear compartment, the charging port 5800 of the electric vehicle may be provided at a position close to the in-vehicle charger 5100 of the side wall metal plate of the electric vehicle 5000, and the distance from the charging port 5800 to the in-vehicle charger 5100 is reduced, thereby improving space efficiency.

Because the space of the roof is abundant, the landing platform 3000 of the present disclosure may include a plurality of landing platforms, which are fixed in the mounting frame 4000, that is, the unmanned aerial vehicle landing apparatus described above is disposed on the roof of the electric vehicle 5000. Specifically, mounting holes are opened at both sides of the mounting frame 4000 to be fastened to the top of the electric vehicle by fastening means such as bolts, as shown in fig. 13, a circled in the figure is a mounting point of the mounting frame 4000 to the roof, and the mounting frame 4000 may share one mounting point with the roof rack. In addition, if need not dismantle, take-off and landing platform 3000 can also carry out the integrated design with electric automobile 5000, for example, can install a plurality of take-off and landing platforms 3000 in installation frame 4000, form foretell unmanned aerial vehicle take-off and landing device, the bottom of take-off and landing device is fixed at the roof. This embodiment can realize that many unmanned aerial vehicles provide the reconnaissance task for the vehicle. In addition, unmanned aerial vehicle 1000 can also play the effect of extending the field of vision for the driver, specifically, can be provided with image monitoring equipment on unmanned aerial vehicle 1000, for example fig. 14 shows, after unmanned aerial vehicle 1000 takes off, can fly around electric automobile 5000, can real-time all-round control the condition around the electric automobile, solve the problem of field of vision blind area.

The preferred embodiments of the present disclosure are described in detail with reference to the accompanying drawings, however, the present disclosure is not limited to the specific details of the above embodiments, and various simple modifications may be made to the technical solution of the present disclosure within the technical idea of the present disclosure, and these simple modifications all belong to the protection scope of the present disclosure. It should be noted that, in the foregoing embodiments, various features described in the above embodiments may be combined in any suitable manner, and in order to avoid unnecessary repetition, various combinations that are possible in the present disclosure are not described again. In addition, any combination of the various embodiments of the present disclosure may be made, and the same should be considered as the disclosure of the present invention, as long as the combination does not depart from the spirit of the present disclosure.

Claims

1. An unmanned aerial vehicle take-off and landing device, comprising a groove-shaped mounting frame (4000) with an opening at the upper part and a plurality of take-off and landing platforms (3000) fixed in the mounting frame (4000), wherein each of the take-off and landing platforms (3000) is respectively matched with a landing gear of a corresponding unmanned aerial vehicle, the take-off and landing platform (3000) comprises a base (3100) and an upper platform (3200) connected above the base (3100), the upper platform (3200) and the base (3100) are arranged at intervals along the height direction and are formed with a central hole for enabling the landing gear (2000) of the unmanned aerial vehicle to pass through, the upper platform (3200) comprises an edge part and a guide limiting part (3210), the guide limiting part (3210) extends downwards from the edge part in an inclined manner, the inner end of the guide limiting part (3210) and the base (3100) are arranged at intervals along the height direction and are formed as a side wall, the guide limit parts (3210) are uniformly arranged along the circumferential direction, and each guide limit part (3210) is hinged to the side part.

2. The unmanned aerial vehicle take-off and landing apparatus of claim 1, wherein at least one of the plurality of take-off and landing platforms is a different size than the other take-off and landing platforms.

3. Unmanned aerial vehicle take-off and landing arrangement according to claim 2, characterized in that the large size take-off and landing platform (3000) is arranged in the center of the mounting frame (4000) and the small size take-off and landing platform (3000) is arranged at the periphery of the large size take-off and landing platform (3000).

4. The unmanned aerial vehicle take-off and landing device according to any one of claims 1 to 3, wherein the take-off and landing platform (3000) comprises a base (3100), the base (3100) is fixed to the bottom surface of the mounting frame (4000), the base (3100) is formed in a regular hexagon or regular triangle, and edges of the bases (3100) of the plurality of take-off and landing platforms (3000) are fitted to form a honeycomb structure.

5. The unmanned aerial vehicle take-off and landing device of claim 1, wherein each guide limit (3210) is hinged to the edge portion by a spring hinge (3220).

6. The unmanned aerial vehicle take-off and landing device of claim 1, wherein the take-off and landing platform further comprises a support mechanism (3300), the upper platform (3200) is formed as a regular polygon, and the support mechanism (3300) is supported between a corner of the upper platform (3200) and the base (3100).

7. The unmanned aerial vehicle take-off and landing device of claim 1, wherein a socket (3110) corresponding to the central hole is provided on the base (3100).

8. The unmanned aerial vehicle take-off and landing device of claim 1, wherein the take-off and landing platform further comprises a support mechanism (3300), the support mechanism (3300) is telescopically supported between the upper platform (3200) and a base (3100), the support mechanism (3300) comprises a first sleeve assembly for driving the upper platform (3200) to ascend and descend, the first sleeve assembly comprises a first driving device (3310) fixed on the base (3100), a lifting sleeve (3320) connected to an output end of the first driving device (3310), and a lifting rod (3330) fixed on the upper platform (3200), and the lifting rod (3330) is in threaded engagement with the lifting sleeve (3320).

9. The unmanned aerial vehicle take-off and landing device of claim 8, wherein the supporting mechanism (3300) further comprises a second sleeve assembly for guiding the upper platform (3200) to ascend and descend, the second sleeve assembly comprises a guide sleeve (3340) fixed on the base (3100), and a guide rod (3350) fixed on the upper platform (3200), the guide rod (3350) is slidably fitted with the guide sleeve (3340), and the first sleeve assembly and the second sleeve assembly are respectively multiple and are uniformly and alternately arranged along the circumferential direction.