CN205345313U

CN205345313U - Unmanned aerial vehicle

Info

Publication number: CN205345313U
Application number: CN201521133309.4U
Authority: CN
Inventors: 刘复祥; 刘颐琳; 吴清荣; 徐贵冰; 吴国洪; 李剑
Original assignee: Nanchang Institute of Technology
Current assignee: Nanchang Institute of Technology
Priority date: 2015-12-30
Filing date: 2015-12-30
Publication date: 2016-06-29
Anticipated expiration: 2025-12-30

Abstract

The utility model provides an unmanned aerial vehicle, the reciprocating impact tunnel drilling machine comprises a machine body, first removable wall, the second removable wall, can follow the perpendicular power spare that extends of this first removable wall, locate the screw on this power spare, locate the inside subassembly of making a video recording of this fuselage, locate the inside control assembly of this fuselage, be located on this fuselage and be close to the front wing of this power spare end, be located on this fuselage and for the fin of this front wing other end, and realize that this front wing and this fin contract and the extending structure of extension, this extending structure includes the straight -bar, locate the first hinge and the A second hinge at these straight -bar both ends, locate this straight -bar center department and with this straight -bar vertically connecting rod, and locate the terminal telescopic link of this connecting rod. Owing to can control the extension of this unmanned aerial vehicle's wing through this control assembly and this extending structure and need not with the shrink to dismantle and assemble the debugging to the wing, so that relevant emergent events can in time be tackled to this unmanned aerial vehicle's bulk reduction.

Description

Unmanned vehicle

Technical field

This utility model relates to general unmanned aerial vehicle technical field, particularly to a kind of can wing shrink unmanned vehicle.

Background technology

Unmanned vehicle refers to that employing automatically controls, has self-navigation function and perform unmanned flight's equipment of special duty function.Along with the development of science and technology, unmanned vehicle is widely used in the fields such as military affairs, navigation, forest fire protection, aerial mapping, it is achieved the functions such as tracking, location, remote control, remote measurement and Digital Transmission.

Existing unmanned vehicle great majority adopt after disassembling and transport, although transportation volume reduces many, but owing to parts are scattered, needs scene to carry out assembly and adjustment before take-off, time is long, it is impossible to tackle the accident in the fields such as military affairs, navigation, forest fire protection, aerial mapping in time.

Utility model content

Based on this, it is an object of the invention to provide a kind of without dismounting, the contractile unmanned vehicle of wing.

A kind of unmanned vehicle, including fuselage, first removable wall, second removable wall, can along this vertically extending force piece of the first removable wall, it is located at the propeller on this force piece, it is located at the camera assembly of this fuselage interior, it is located at the control assembly of this fuselage interior, it is positioned on this fuselage and near the front wing of this force piece end, it is positioned on this fuselage and relative to the empennage of this front wing other end, and realize this front wing and the contraction of this empennage and the stretching structure stretched, this stretching structure includes straight-bar, it is located at the first hinge and second hinge at these straight-bar two ends, it is located at this straight-bar center and the connecting rod vertical with this straight-bar, and it is located at the expansion link between this connecting rod and this front wing.

Further, this stretching structure can rotate around this first hinge, and the rotation axis of this first hinge is vertical with the axis of this force piece, and this front wing and this empennage all pass through this stretching structure rotating middle part to this fuselage.

Further, this expansion link realizes this front wing with this empennage around the rotation of this second hinge by pneumatic mode.

Further, this force piece can shrink along the direction of this first removable wall vertical and stretch, and this force piece is provided with 3 grooves, and these 3 grooves are 120 degree of arrangements in the radial direction of this force piece.

Further, this camera assembly includes support bar and photographic head, is connected by spherical hinge between this photographic head with this support bar, and this photographic head can rotate within the scope of 120 degree of this spherical hinge cross section.

Further, this control assembly can receive the information from this camera assembly, and the wing extended configuration of this unmanned vehicle, contraction state and flare maneuver are controlled.

Further, this front wing includes the resettlement section being connected with this stretching structure and the pars contractilis being connected with this resettlement section, and the length of this pars contractilis is less than the length of this resettlement section.

Further, this empennage includes the horizontal tail empennage being connected with this stretching structure and the vee tail being connected with this horizontal tail empennage, passes through gemel connection between this horizontal tail empennage and this vee tail.

Further, the outer wall of this unmanned vehicle fuselage can be provided with nail, and this nail is connected with this fuselage by elastic component or pneumatic mode.

Above-mentioned unmanned vehicle, stretching, extension owing to can be controlled the wing of this unmanned vehicle by this control assembly and this stretching structure carries out disassembly and assembly debugging with shrinking without to wing, so that the structure of this unmanned vehicle becomes simple, volume reduces, it is possible to the accident that reply is relevant in time.

Accompanying drawing explanation

Structural representation when Fig. 1 is that in this utility model first embodiment, unmanned vehicle wing shrinks.

Structural representation when Fig. 2 is that in this utility model first embodiment, unmanned vehicle wing launches.

Fig. 3 is that in this utility model first embodiment, wing realizes shrinking the amplification schematic cross-section with deployed configuration.

Structural representation when Fig. 4 is that in this utility model the second embodiment, unmanned vehicle wing shrinks.

Detailed description of the invention

For the ease of understanding this utility model, below with reference to relevant drawings, this utility model is described more fully.Accompanying drawing gives first-selected embodiment of the present utility model.But, this utility model can realize in many different forms, however it is not limited to embodiment described herein.On the contrary, the purpose providing these embodiments is to make to disclosure of the present utility model more thoroughly comprehensively.

It should be noted that be referred to as " being fixedly arranged on " another element when element, it can directly on another element or can also there is element placed in the middle.When an element is considered as " connection " another element, it can be directly to another element or may be simultaneously present centering elements.Term as used herein " vertical ", " level ", "left", "right" and similar statement are for illustrative purposes only.

Unless otherwise defined, all of technology used herein and scientific terminology are identical with belonging to the implication that those skilled in the art of the present utility model are generally understood that.The purpose describing specific embodiment it is intended merely to herein, it is not intended that in restriction this utility model at term used in the description of the present utility model.Term as used herein " and/or " include the arbitrary and all of combination of one or more relevant Listed Items.

Refer to Fig. 1 to Fig. 3, a kind of unmanned vehicle provided in first embodiment in this utility model, including fuselage 10, first removable wall 11, second removable wall 12, can along the vertically extending force piece 13 of this first removable wall 11, it is located at the propeller 14 on this force piece 13, it is located at this camera assembly 15 within fuselage 10, it is located at this control assembly 16 within fuselage 10, it is positioned on this fuselage 10 and near the front wing 17 of this force piece 13 end, it is positioned on this fuselage 10 and relative to the empennage 18 of this front wing 17 other end, and realize this front wing 17 and the contraction of this empennage 18 and the stretching structure 19 stretched, this stretching structure 19 includes straight-bar 191, it is located at first hinge 192 and second hinge 193 at these straight-bar 191 two ends, it is located at this straight-bar 191 center and the connecting rod 194 vertical with this straight-bar 191, and it is located at the expansion link 195 between this connecting rod 192 and this front wing 17.

This first hinge 192 is connected with this fuselage 10, this stretching structure 19 can rotate around this first hinge 192, the rotation axis of this first hinge 192 is vertical with the axis of this force piece 13, and this front wing 17 all passes through this stretching structure 19 rotating middle part to this fuselage 10 with this empennage 18.This expansion link 195 realizes this front wing 17 by pneumatic mode and rotates around this second hinge 193 with this empennage 18.

Referring again to Fig. 1, when the wing (including front wing and empennage) of this unmanned vehicle is in contraction state, first removable wall 11, second removable wall 12 forms a cavity (as shown in Figure 1) with this fuselage 10, this force piece 13, this propeller 14, this camera assembly 15, this control assembly 16, this front wing 17, this empennage 18, and this stretching structure 19 all houses and this inside cavity, this fuselage 10 is provided with inner fovea part 101 near this second removable wall 12 place, it is easy to when the wing of this unmanned vehicle is in extended configuration, this front wing 17 can be embedded in this inner fovea part 101 with this empennage 17.

Referring again to Fig. 2, this force piece 13 can shrink along the direction of this first removable wall 11 vertical and stretch, this force piece 13 is provided with 3 grooves 131, these 3 grooves 131 are 120 degree of arrangements in the radial direction of this force piece 13, one end of this propeller 14 is located in this groove 131 of correspondence and away from one end of this first removable wall 11, when the wing of this unmanned vehicle is in contraction state, this propeller 14 shrinks and fits with this groove 131, when the wing of this unmanned vehicle is in extended configuration, this propeller 14 stretches and axially vertical with this force piece 13, now this force piece 13 work drives this propeller 14 to rotate, the rotative power of this force piece 13 is converted into the propulsive force of this unmanned vehicle.

This camera assembly 15 includes support bar 151 and photographic head 152, it is internal and can along flexible that this support bar 151 is vertical at this fuselage 10, it is connected by spherical hinge (not shown) between this photographic head 152 with this support bar 151, this photographic head 152 can rotate within the scope of 120 degree of this spherical hinge cross section, the environment of surrounding is shot, this camera assembly 15 is provided with 4 altogether, it is possible to the carrying out around this unmanned vehicle is shot without dead angle.

This control assembly 16 can receive the information from this camera assembly 15, and the wing extended configuration to this unmanned vehicle, contraction state and flare maneuver are controlled, thus realizing following the tracks of, location, remote control, the function such as remote measurement and Digital Transmission, intelligent terminal's (not shown) can also be transmitted information to simultaneously, this intelligent terminal is the hand-held or portable unit that user is easy to that operation controls, as: hands machine, flat board, laptop computer, intelligent watch, and other can send and the wearable mobile equipment receiving information, this intelligent terminal is by App application program and these control assembly 16 wireless connections, and issue instructions to this control assembly 16.

This front wing 17 includes the resettlement section 171 being connected with this stretching structure 19 and the pars contractilis 172 being connected with this resettlement section 171, and the length of this pars contractilis 172 is less than the length of this resettlement section 171.When the wing of this unmanned vehicle is in contraction state, it is internal that this pars contractilis 172 is contained in this resettlement section 171, when the wing of this unmanned vehicle is in extended configuration, this resettlement section 171 is vertical with the axis of this support member 151 in this camera assembly 15, and this resettlement section 171 is embedded in this inner fovea part 101.It is provided with pneumatic member (not shown) in this resettlement section 171, and this control assembly 16 realizes the retracted position of this pars contractilis 172 by controlling this pneumatic member.

This empennage 18 includes the horizontal tail empennage 181 being connected with this stretching structure 19 and the vee tail 182 being connected with this horizontal tail empennage 181, by gemel connection 183 between this horizontal tail empennage 181 and this vee tail 182.

It should be understood that the unmanned vehicle in the present embodiment is except being used for the fields such as military affairs, navigation, forest fire protection, aerial mapping, it is possible to use as kids toys, improve child's interest to aviation field.

Refer to Fig. 4, structural representation when shrinking for unmanned vehicle wing in this utility model the second embodiment, unmanned vehicle in the present embodiment is more or less the same with the unmanned vehicle in first embodiment, it is different in that the unmanned vehicle in the present embodiment is on the basis of first embodiment, outer wall (removing the first removable wall and the second removable wall) at described unmanned vehicle fuselage is provided with nail 20, this nail 20 is connected with this fuselage 10 by elastic component or pneumatic mode, thus this control assembly 16 can control this nail 20 and shrink in the outer wall of this fuselage 10.Unmanned vehicle in this embodiment after landing can milling train, padding machine or roll people, be the sharp weapon to the block of vacant lot, enemy airport.

To sum up, in this utility model above-described embodiment, owing to this unmanned vehicle being provided with this control assembly and this stretching structure, the stretching, extension of the wing that can control this unmanned vehicle carries out disassembly and assembly debugging with shrinking without to wing, the structure making this unmanned vehicle becomes simple, volume reduces, it is possible to the accident that reply is relevant in time.

Embodiment described above only have expressed several embodiments of the present utility model, and it describes comparatively concrete and detailed, but therefore can not be interpreted as the restriction to this utility model the scope of the claims.It should be pointed out that, for the person of ordinary skill of the art, without departing from the concept of the premise utility, it is also possible to make some deformation and improvement, these broadly fall into protection domain of the present utility model.Therefore, the protection domain of this utility model patent should be as the criterion with claims.

Claims

1. a unmanned vehicle, including fuselage, first removable wall, second removable wall, can along this vertically extending force piece of the first removable wall, it is located at the propeller on this force piece, it is located at the camera assembly of this fuselage interior, it is located at the control assembly of this fuselage interior, it is positioned on this fuselage and near the front wing of this force piece end, it is positioned on this fuselage and relative to the empennage of this front wing other end, and realize this front wing and the contraction of this empennage and the stretching structure stretched, it is characterized in that: this stretching structure includes straight-bar, it is located at the first hinge and second hinge at these straight-bar two ends, it is located at this straight-bar center and the connecting rod vertical with this straight-bar, and it is located at the expansion link of this connecting rod end.

2. unmanned vehicle according to claim 1, it is characterized in that, this stretching structure can rotate around this first hinge, and the rotation axis of this first hinge is vertical with the axis of this force piece, and this front wing and this empennage all pass through this stretching structure rotating middle part to this fuselage.

3. unmanned vehicle according to claim 1, it is characterised in that this expansion link realizes this front wing by pneumatic mode and rotates around this second hinge with this empennage.

4. unmanned vehicle according to claim 1, it is characterised in that this force piece can shrink along the direction of this first removable wall vertical and stretch, and this force piece is provided with 3 grooves, and these 3 grooves are 120 degree of arrangements in the radial direction of this force piece.

5. unmanned vehicle according to claim 1, it is characterised in that this camera assembly includes support bar and photographic head, is connected by spherical hinge between this photographic head with this support bar, and this photographic head can rotate within the scope of 120 degree of this spherical hinge cross section.

6. unmanned vehicle according to claim 1, it is characterised in that this control assembly can receive the information from this camera assembly, and the wing extended configuration of this unmanned vehicle, contraction state and flare maneuver are controlled.

7. unmanned vehicle according to claim 1, it is characterised in that this front wing includes the resettlement section being connected with this stretching structure and the pars contractilis being connected with this resettlement section, and the length of this pars contractilis is less than the length of this resettlement section.

8. unmanned vehicle according to claim 1, it is characterised in that this empennage includes the horizontal tail empennage being connected with this stretching structure and the vee tail being connected with this horizontal tail empennage, passes through gemel connection between this horizontal tail empennage and this vee tail.

9. unmanned vehicle according to claim 1, it is characterised in that the outer wall of this unmanned vehicle fuselage can be provided with nail, this nail is connected with this fuselage by elastic component or pneumatic mode.