CN218431808U

CN218431808U - Collapsible portable unmanned aerial vehicle

Info

Publication number: CN218431808U
Application number: CN202222837491.8U
Authority: CN
Inventors: 罗俊达; 罗俊杰; 许可; 万耿栋
Original assignee: Guangzhou Walkera Technology Co ltd
Current assignee: Guangzhou Walkera Technology Co ltd
Priority date: 2022-10-26
Filing date: 2022-10-26
Publication date: 2023-02-03
Anticipated expiration: 2032-10-26

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a foldable portable unmanned aerial vehicle, which comprises a vehicle body, a rotor arm, a power device, a rotor and a rotor protective cover, wherein at least part of one end of the rotor arm is inwards concave and accommodated in a folding groove on the side surface of the vehicle body and is arranged on the side surface of the vehicle body; the fuselage comprises first half and latter half, and first half's width is greater than latter half's width, and first half and latter half's width is poor to be formed and to accomodate the space of folding rotor arm for unmanned aerial vehicle's whole portability obtains the promotion of certain degree, simultaneously, to the improvement of rotor safety cover and rotor arm design, also is favorable to reducing unmanned aerial vehicle's weight, improves unmanned aerial vehicle's flexibility.

Description

Collapsible portable unmanned aerial vehicle

Technical Field

The utility model belongs to the technical field of the unmanned air vehicle technique and specifically relates to a collapsible portable unmanned aerial vehicle is related to.

Background

An unmanned aircraft, abbreviated as "drone", and abbreviated in english as "UAV", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer. Unmanned aerial vehicles are in fact a general term for unmanned aerial vehicles, and can be defined from a technical perspective as follows: unmanned fixed wing aircraft, unmanned VTOL aircraft, unmanned airship, unmanned helicopter, unmanned multi-rotor aircraft, unmanned paravane, etc. Compared with manned aircraft, it has the advantages of small volume, low cost, convenient use, low requirement on the operational environment, strong battlefield viability and the like. Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. In the civil aspect, the unmanned aerial vehicle + the industrial application are really just needed by the unmanned aerial vehicle; the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and developed countries actively expand the industrial application and develop the unmanned aerial vehicle technology. To foretell all kinds of unmanned aerial vehicles, often there is the weight of emphasis among the prior unmanned aerial vehicle technique big, and the flexibility is lower and the relatively poor technical drawback of whole portability, for this reason, we propose a collapsible portable unmanned aerial vehicle to solve above-mentioned technical problem to a certain extent at least.

SUMMERY OF THE UTILITY MODEL

The utility model discloses an overcome the shortcoming and not enough that exist among the prior art, provide a collapsible portable unmanned aerial vehicle to the realization reduces unmanned aerial vehicle weight, improves the unmanned aerial vehicle flexibility and improves the technological effect of unmanned aerial vehicle portability.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

a foldable portable unmanned aerial vehicle comprises a body, a rotor arm, a power device, a rotor and a rotor protective cover, wherein at least part of one end of the rotor arm is accommodated in a folding groove in the side face of the body in a concave manner and is arranged on the side face of the body; the fuselage comprises half and the back half, and the width of half is greater than the width of back half before, and the difference in width of half and back half forms the space of accomodating folding rotor arm.

Wherein, rotor arm one end is passed through slewing mechanism collapsible connection in the side of fuselage, is equipped with power device on the rotor arm other end, the rotor install in directly over power device.

Preferably, the other end of the rotor arm is provided with a rotor wing protection cover, the rotor wing protection cover is of a fan-shaped structure, the angle range of the rotor wing protection cover is controlled to be 120-160 degrees, the center of the rotor wing protection cover coincides with the center of the rotor wing, and the rotor wing protection cover is detachably connected with the other end of the rotor wing arm through a lock catch structure. Rotor safety cover adopts fan-shaped structure can further reduce the overall dimension of rotor safety cover, is favorable to reducing unmanned aerial vehicle's whole weight to a greater extent, can be not more than 249g with unmanned aerial vehicle's whole weight control, also is favorable to reducing the mutual interference effect between adjacent rotor and the rotor safety cover simultaneously.

Wherein, rotor arm safety cover lower surface is the arc, adopts the arc structure to be favorable to improving shock resistance to a certain extent. The rotor safety cover comprises radial support and hoop support, the radial support intersects outer net and the inlayer net of formation with the hoop support, the proportional control of outer net quantity and inlayer net quantity is at 2:1, thereby forming one or more core supports penetrating the inner layer grids and the outer layer grids and connecting the inner layer grids and the outer layer grids into a whole. Outer net quantity is greater than inlayer net quantity, can guarantee the intensity of outer net and crashproof ability on the one hand, and on the other hand can minimize inlayer net and block the rotor and rotate the air current of in-process, is favorable to gaseous outflow.

In order to accomodate better unmanned aerial vehicle's rotor arm and rotor reach the mesh that improves unmanned aerial vehicle's whole portability, there is a smooth transition district between fuselage first half and the latter half, with be located the folded slot that the rotor arm of fuselage first half is connected set up in smooth transition district, with be located the folded slot that the rotor arm of fuselage latter half is connected set up in the afterbody of fuselage.

Preferably, the folding groove of the front half part of the fuselage is formed by the inward concave front half part of the fuselage, the folding groove of the rear half part of the fuselage is formed by the outward convex upper and lower folding groove walls of the tail part of the fuselage, and the folding groove is used for folding and containing the rotor arm part therein.

In order to facilitate the rotor arm to be folded and stored in the side face of the machine body, the rotor arm is guaranteed to have better strength, one end part of the rotor arm is concave downwards to form an avoiding space, an inclined convex variable surface exists on one side, facing the other end of the rotor arm, of the avoiding space, the thickness of the cross section of the rotor arm is gradually reduced from the convex variable surface to the other end of the rotor arm, and the gradient of a slope formed by the thickness of the cross section of the rotor arm from large to small is controlled to be 5% -10%.

Wherein, set up in the interaxial distance of a pair of rotor of fuselage first half is less than set up in the interaxial distance of a pair of rotor of fuselage second half, and the distance difference between the two is not more than 1cm, is favorable to improving the holistic flexibility of unmanned aerial vehicle.

Preferably, the other ends of the pair of rotor arms arranged on the front half part of the fuselage are inclined forwards by a certain angle, the inclination angle is controlled to be 5-15 degrees, the distance between the rotor on the front half part of the fuselage and the rotor on the rear half part of the fuselage can be properly increased, and the mutual interference of the front and rear adjacent rotors in the operation process can be reduced to a certain extent.

In order to further improve the flexibility of the unmanned aerial vehicle and ensure the folding and containing space of the rotor arms, a certain horizontal height difference exists between a pair of rotor arms arranged at the front half part of the machine body and a pair of rotor arms arranged at the rear half part of the machine body, and the horizontal height difference is controlled to be 5 to 10cm.

Compared with the prior art, the beneficial effects of the utility model are that:

one end of the rotor arm can be at least partially accommodated in a folding groove on the side surface of the machine body in a concave manner and is arranged on the side surface of the machine body; the fuselage comprises first half and latter half, and first half's width is greater than latter half's width, and first half and latter half's width difference form the space that can accomodate folding rotor arm for unmanned aerial vehicle's whole portability obtains the promotion of certain degree, simultaneously, to the improvement of rotor safety cover and rotor arm design, also is favorable to reducing unmanned aerial vehicle's weight, improves unmanned aerial vehicle's flexibility.

Drawings

Fig. 1 is the utility model discloses unmanned aerial vehicle's expansion state's structural schematic diagram.

Fig. 2 is the utility model discloses unmanned aerial vehicle's the structure inside view of expansion state.

Fig. 3 is the utility model discloses unmanned aerial vehicle's expansion state's structure front view.

Fig. 4 is the utility model discloses unmanned aerial vehicle's the structure schematic diagram of the state of packing up.

Fig. 5 is the utility model discloses unmanned aerial vehicle's the structure inside view of packing up the state.

The reference numerals include:

1-fuselage 2-rotor arm 3-power plant

4-rotor 5-rotor protective cover 6-folding groove (front)

7-folding groove (rear) 8-avoiding space 9-convex surface

Detailed Description

The present invention will be further described with reference to the following examples and accompanying drawings.

Referring to fig. 1-5, the foldable portable unmanned aerial vehicle comprises a vehicle body 1, a rotor arm 2, a power device 3, a rotor 4 and a rotor protective cover 5, wherein at least part of one end of the rotor arm 2 is accommodated in a folding groove (front) 6 and a folding groove (rear) 7 on the side surface of the vehicle body in a concave manner and is arranged on the side surface of the vehicle body 1; the fuselage 1 is composed of a front half and a rear half, the width of the front half is larger than that of the rear half, and the difference in width between the front half and the rear half forms a space for accommodating the folding rotor arm 2. One end part of the rotor arm 2 is concave downwards to form an avoiding space 8, and one side of the avoiding space 8 facing the other end of the rotor arm 2 is provided with an inclined convex surface 9.

Further, referring to fig. 1-3, one end of the rotor arm 2 is foldably connected to the side surface of the fuselage 1 through a rotating mechanism, the other end is provided with a power device 3, the rotor 4 is arranged right above the power device 3, and the power device 3 is used for controlling the starting rotation and the stopping rotation of the rotor 4.

Further, referring to fig. 1-3, the other end of the rotor arm 2 is provided with a rotor protection cover 5, the rotor protection cover 5 is of a fan-shaped structure, the angle range of the rotor protection cover 5 is controlled to be 120-160 degrees, the center of the rotor protection cover 5 coincides with the center of the rotor 4, the rotor protection cover 5 adopts a lock catch structure to be detachably connected with the other end of the rotor arm 2, when the unmanned aerial vehicle is not used, the lock catch structure can be unlocked, the rotor protection cover 5 is detached from the rotor arm 2, and then the rotor 4 and the rotor arm 2 are folded and stored. Rotor safety cover 5 adopts fan-shaped structure can further reduce rotor safety cover 5's overall dimension, is favorable to reducing unmanned aerial vehicle's whole weight to the bigger degree, can be not more than 249g with unmanned aerial vehicle's whole weight control, also is favorable to reducing the mutual interference effect between adjacent rotor 4 and the rotor safety cover 5 simultaneously.

Further, referring to fig. 1-3, 5 lower surfaces of rotor arm safety cover are the arc, adopt the arc structure to be favorable to improving shock resistance to a certain extent, guarantee the organism integrity of unmanned aerial vehicle when the collision condition takes place better. Rotor safety cover 5 supports with the hoop by radial support and constitutes, radial support and the hoop support intersect and form outer net and inlayer net, the proportional control of outer net quantity and inlayer net quantity is at 2:1, thereby forming one or more core supports penetrating the inner layer grids and the outer layer grids and connecting the inner layer grids and the outer layer grids into a whole. Outer net quantity is greater than inlayer net quantity, can guarantee the intensity of outer net and crashproof ability on the one hand, and on the other hand can minimize inlayer net and rotate the air current of in-process to the rotor and block, is favorable to gaseous outflow, can further improve unmanned aerial vehicle at the whole flexibility of flight in-process.

Further, referring to fig. 1 to 5, a smooth transition area exists between the front half part and the rear half part of the fuselage 1, the folding slot (front) 6 connected with the rotor arm 2 located at the front half part of the fuselage is arranged in the smooth transition area, and the folding slot (rear) 7 connected with the rotor arm 2 located at the rear half part of the fuselage 1 is arranged at the tail part of the fuselage 1. The collapsible trough (preceding) 6 of fuselage 1 first half by the first half of fuselage is inwards sunken to form, the collapsible trough (back) 7 of fuselage 1 second half by the outside convex upper and lower folding cell wall of afterbody of fuselage 1 forms, when the parking unmanned aerial vehicle, can fold rotor 4 and rotor arm 2 and accomodate in collapsible trough (preceding) 6 and collapsible trough (back) 7, and rotor 4 is folded and is accomodate the back, holds and locates in the width difference that fuselage 1 first half and second half formed, can reach the purpose in practice thrift the space, improves the holistic portability of unmanned aerial vehicle.

Further, referring to fig. 3, one end of the rotor arm 2 is partially recessed to form an avoidance space 8, one side of the avoidance space 8 facing the other end of the rotor arm 2 is provided with an inclined convex surface 9, the thickness of the cross section of the rotor arm 2 is gradually reduced from the convex surface 9 to the other end of the rotor arm 2, and the slope gradient formed by the thickness of the cross section of the rotor arm 2 from large to small is controlled to be 5% -10%.

Further, referring to fig. 1-3, set up in the interaxial distance of a pair of rotor 4 of fuselage 1 first half is less than set up in the interaxial distance of a pair of rotor 4 of fuselage 1 second half, and the distance difference between the two is not more than 1cm, is favorable to improving unmanned aerial vehicle at the flexibility of flight in-process.

Further, referring to fig. 1-2, the other ends of the pair of rotor arms 2 disposed at the front half of the fuselage 1 are inclined forward by a certain angle, and the inclination angle is controlled to be 5 ° to 15 °, so that the distance between the rotor 4 at the front half of the fuselage 1 and the rotor 4 at the rear half of the fuselage 1 can be increased appropriately, and the above improved design of the rotor arms 2 is beneficial to reduce the mutual interference effect of the airflows of the front and rear adjacent rotors during the operation process to a certain extent.

Further, referring to fig. 3, a certain horizontal height difference exists between a pair of rotor arms 2 arranged at the front half part of the airframe 1 and a pair of rotor arms 2 arranged at the rear half part of the airframe 1, the horizontal height difference is controlled to be 5-10cm, and the design of the horizontal height difference between the rotor arms 2 can further improve the flexibility of the unmanned aerial vehicle in the flying process, and can ensure a more sufficient folding storage space for the rotor arms 2 and improve the portability of the unmanned aerial vehicle after being folded and stored.

In the use process of the foldable portable unmanned aerial vehicle, a technician can take out and unfold the rotor arm 2 and the rotor 4 from the side of the vehicle body in the folding groove (front) 6 and the folding groove (rear) 7 through the rotating mechanism, and install the rotor protecting cover 5 at the other end of the rotor arm 2 through the locking structure, so that the unmanned aerial vehicle can be used; when finishing unmanned aerial vehicle's use, the technical staff at first can untie the hasp structure on the rotor safety cover 5, dismantle rotor safety cover 5 from rotor arm 2 other end, then accomodate rotor 4 and rotor arm 2 part are folding in folding groove (preceding) 6 and folding groove (back) 7, rotor 4 packs up the back, hold and locate 1 first half of fuselage and the width difference that latter half formed, can reach the purpose in saving space, and then improve the portability after unmanned aerial vehicle packs up.

It is obvious that the above embodiments of the present invention are only examples for clearly illustrating the technical solutions of the present invention, and are not limitations to the specific embodiments of the present invention. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

In the present invention, unless stated to the contrary, the terms "upper, lower, left, right, front, back, inner, outer, vertical and horizontal" and the like contained in the terms "are used to represent the orientation of the terms in the conventional use state, or are colloquially understood by those skilled in the art, and should not be construed as limiting the terms, meanwhile, the numerical terms" first "," second "and" third "do not represent the specific number and order, but are used for the distinction of names, and the terms" include "," include "or any other variants thereof are intended to cover the non-exclusive inclusion, so that the process, method, article or apparatus including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes the elements inherent to such process, method, article or apparatus.

Claims

1. The utility model provides a collapsible portable unmanned aerial vehicle, includes fuselage, rotor arm, power device, rotor and rotor safety cover, its characterized in that: one end of the rotor arm is at least partially recessed in a folding groove on the side surface of the machine body and arranged on the side surface of the machine body; the fuselage comprises half and the back half, and the width of half is greater than the width of back half before, and the difference in width of half and back half forms the space of accomodating folding rotor arm.

2. The foldable portable drone according to claim 1, characterized in that: rotatable folding connection in fuselage side of rotor arm one end is equipped with power device on the other end, the rotor sets up power device is directly over.

3. The foldable portable drone of claim 2, characterized in that: the other end of the rotor wing arm is provided with a rotor wing protection cover, the rotor wing protection cover is of a fan-shaped structure, the angle range of the rotor wing protection cover is controlled to be 120-160 degrees, the center of the rotor wing protection cover coincides with the center of the rotor wing, and the rotor wing protection cover is detachably connected with the other end of the rotor wing arm through a lock catch structure.

4. A foldable portable drone according to claim 3, characterised in that: the rotor arm protection cover lower surface is the arc, comprises radial support and hoop support, the crossing outer net and the inlayer net that form of radial support and hoop support, the proportional control of outer net quantity and inlayer net quantity is at 2:1, thereby forming one or more core supports penetrating the inner layer grids and the outer layer grids and connecting the inner layer grids and the outer layer grids into a whole.

5. The foldable portable drone according to claim 1, characterized in that: there is a smooth transition district between fuselage first half and the latter half, with be located the folding tank that fuselage first half's rotor arm is connected set up in smooth transition district, with be located the folding tank that fuselage latter half's rotor arm is connected set up in the afterbody of fuselage.

6. A foldable portable drone according to claim 5, characterised in that: the folding groove of the front half part of the machine body is formed by inwards recessing the front half part of the machine body, and the folding groove of the rear half part of the machine body is formed by upper and lower folding groove walls protruding outwards from the tail part of the machine body.

7. A foldable portable unmanned aerial vehicle according to any one of claims 1 to 6, wherein: one end part of the rotor arm is concave downwards to form an avoiding space, the avoiding space faces to one side of the other end of the rotor arm, an inclined convex surface is arranged on one side of the other end of the rotor arm, the convex surface reaches the other end of the rotor arm, and the thickness of the cross section of the rotor arm is gradually reduced.

8. A foldable portable unmanned aerial vehicle according to any one of claims 1 to 6, wherein: the center distance between the pair of rotary wings arranged at the front half part of the machine body is smaller than that between the pair of rotary wings arranged at the rear half part of the machine body, and the distance difference between the two parts is not larger than 1cm.

9. A foldable portable unmanned aerial vehicle according to any one of claims 1 to 6, wherein: the other ends of a pair of rotor arms arranged at the front half part of the aircraft body are inclined forwards at a certain angle, and the inclination angle is controlled to be 5-15 degrees.

10. A foldable portable unmanned aerial vehicle according to any one of claims 1 to 6, wherein: a certain horizontal height difference exists between a pair of rotor arms arranged at the front half part of the machine body and a pair of rotor arms arranged at the rear half part of the machine body, and the horizontal height difference is controlled to be 5-10cm.