CN205499331U - For military use unmanned vehicles of portable connection wing - Google Patents
For military use unmanned vehicles of portable connection wing Download PDFInfo
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- CN205499331U CN205499331U CN201521135247.0U CN201521135247U CN205499331U CN 205499331 U CN205499331 U CN 205499331U CN 201521135247 U CN201521135247 U CN 201521135247U CN 205499331 U CN205499331 U CN 205499331U
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- 238000000034 method Methods 0.000 abstract description 5
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Abstract
The utility model relates to an unmanned vehicles especially relates to a for military use unmanned vehicles of portable connection wing. Be equipped with wing reinforcement and slider on for military use unmanned vehicles of portable connection wing's the fuselage, the fuselage tail end is equipped with the propeller, is equipped with the vertical fin on the fuselage tail end, the one end of wing front wing is articulated with the wing reinforcement, and the other end of wing front wing is articulated with the one end of rear wing, the other end of rear wing is articulated with the slider, thereby the slider is close to to the fuselage to drive the wing on one side of the wing reinforcement along the tail end slip of fuselage, vertical fin and fuselage articulated, the vertical fin can be kept flat in the fuselage tail end or stood on the fuselage tail end perpendicularly. The utility model provides a for military use unmanned vehicles of portable connection wing can full play with the portable of multiaxis aircraft and the good flight performance of fixed wing aircraft. Knapsack portable is put into with the folding mode to the aircraft, demonstrates fully the portability of easily carrying. Take out from the knapsack before flight, take off through the mode that the hand was thrown, open to the state of flight at in -process wing, vertical fin bullet that the hand was thrown to descend with the form of slideing.
Description
Technical field
This utility model relates to a kind of unmanned vehicle, particularly relates to a kind of portable connection wing military unmanned aerial vehicle.
Background technology
Along with the carrying out of modern war, special force plays an increasingly important role the most day by day, and how to be dissolved in individual soldier's equipment of special force by Fixed Wing AirVehicle is original intention of the present utility model.Sometimes penetrat deep in isolation enemy's rear area in view of special force, need in strange region periphery is scouted and identification in several kilometers, or carry out some demolition dutys.Although and existing Fixed Wing AirVehicle function admirable, voyage is remote, and penetration ability is strong, but due to bulky, does not have the requirement of individual soldier's equipment；For Multi-axis aircraft, although be easy to carry about with one, but big multiple speed is relatively low, and penetration ability is poor, and voyage is little, is unsuitable for for distant reconnaissance and strike, therefore the most improper as individual reconnaissance/strike equipment.
Utility model content
This utility model provides a kind of portable connection wing military unmanned aerial vehicle for above-mentioned deficiency.
This utility model adopts the following technical scheme that
Portable connection wing military unmanned aerial vehicle described in the utility model, including fuselage, wing front wing, wing rear wing, reinforcement, slide block, propeller, vertical fin；Described fuselage is provided with wing reinforcement and slide block；Fuselage tail end is provided with propeller, and fuselage tail end is provided with vertical fin；One end of wing front wing is hinged with wing reinforcement, and the other end of wing front wing is hinged with one end of rear wing；The other end of rear wing is hinged with slide block；Slide block slides near wing reinforcement side along the tail end of fuselage thus drives wing close to fuselage；Described vertical fin is hinged with fuselage, and vertical fin can lie against fuselage tail end or vertically stand on fuselage tail end.
Portable connection wing military unmanned aerial vehicle described in the utility model, described wing is formed truss structure by front wing, rear wing；Wing front wing and rear wing connect formation at wing tip and connect wing aerodynamic arrangement.
Portable connection wing military unmanned aerial vehicle described in the utility model, described front wing includes front wing rib, wing fence, front wing front-axle beam, wing tip end plate, electric line outlets, front wing wing root rotating shaft, the front wing back rest, front wing Servo-controller, front wing rudder face, front wing wing tip shaft hole；
Described front wing rib and front wing front-axle beam, front wing back rest composition front wing framework, be provided with front wing Servo-controller in front wing framework, the tail end of wing framework is provided with front wing rudder face, is provided with eyelid covering outside front wing framework；Being provided with front wing wing root rotating shaft at the wing root of front wing framework, be provided with wing tip end plate at the wing tip of front wing framework, the tail end of wing tip end plate arranges front wing wing tip shaft hole；Wing root is provided with electric line outlets；Front wing rib is provided with wing fence.
Portable connection wing military unmanned aerial vehicle described in the utility model, described rear wing includes rear wing front-axle beam, rear wing rib, rear wing wing tip rotating shaft, rear wing wing root rotating shaft, rear wing Servo-controller, wing flap rudder face, the rear wing back rest；
Described rear wing front-axle beam, rear wing rib form rear wing framework with the rear wing back rest, be provided with eyelid covering, be provided with rear wing Servo-controller between rear wing front-axle beam and the rear wing back rest outside framework；Rear wing framework tail end is provided with wing flap rudder face；The wing tip of rear wing is provided with rear wing wing tip rotating shaft, and the wing root of rear wing is provided with rear wing wing root rotating shaft.
Portable connection wing military unmanned aerial vehicle described in the utility model, described front wing is hinged with wing reinforcement by front wing wing root rotating shaft, and front wing is hinged with rear wing wing tip rotating shaft by front wing wing tip shaft hole；Rear wing wing root rotating shaft is hinged with slide block.
Portable connection wing military unmanned aerial vehicle described in the utility model, described slide block includes lock hole, spring, strong magnets, slide block reinforcement, manual wrench；The upper surface of described manual wrench is provided with strong magnets；The lower surface of manual wrench is provided with spring；Being respectively equipped with two pieces of slide block reinforcements before and after manual wrench at sidewall edge, slide block reinforcement is provided with hinge hole, forms the inside groove for connecting rear wing between two pieces of slide block reinforcements；It is additionally provided with lock hole on slide block reinforcement.
Portable connection wing military unmanned aerial vehicle described in the utility model, also includes that manhole, slide block reinforcement are provided with manhole.
Portable connection wing military unmanned aerial vehicle described in the utility model, described vertical fin includes vertical fin bearing member, vertical fin locking device, striker lateral pin；Vertical fin locking device is arranged in the bottom of described vertical fin bearing member；Claw is extended in the side of vertical fin locking device；Claw is connected with striker lateral pin, and claw drives striker lateral pin to lift and fall；After striker lateral pin falls, its bottom falls in lock hole.
Portable connection wing military unmanned aerial vehicle described in the utility model, described fuselage includes fuselage forward equipment bay, fuselage left plate, fuselage right plate, fuselage reinforcing frame, propeller, guide rail；Described fuselage left plate is arranged in parallel with fuselage right plate；Several fuselage reinforcing frames it are provided with between fuselage left plate and fuselage right plate；Fuselage left plate, fuselage right plate form fuselage ring structure with machine fuselage reinforcing frame, and its its top of fuselage ring structure arranges that fuselage forward equipment bay, tail end arrange propeller；Wing reinforcement is arranged in fuselage ring structure and near fuselage forward equipment bay；Fuselage ring structural base is provided with the guide rail slided for slide block.
Beneficial effect
The portable connection wing military unmanned aerial vehicle that this utility model provides, is given full play to flying quality good to the portability of Multi-axis aircraft and Fixed Wing AirVehicle.Aircraft is put in knapsack in a folded fashion and is easy to carry, and fully demonstrates the portability being easy to carry about with one.Taking out from knapsack before flight, take off by the way of hands is thrown, during hands is thrown, wing, vertical fin flick to state of flight, and to slide form landing.In whole flight course, owing to being unfolded to complete fixed wing airplane pattern, there is good flying quality and penetration ability, and have employed the aerodynamic arrangement of the connection wing, aircraft is made to have lift-drag ratio big, structural strength is high, trim resistance is little, carrying convenience, time of letting fly away are short, simple in construction, battlefield survivability advantages of higher.
Only needing a people to carry, it is desirable to portable, flexible, reliable, efficient, make every effort to simple in construction safety simultaneously, practical, cheap, cost performance is high.In folding process, the both sides of wing rotatable folding to fuselage, vertical fin is folded on fuselage, take off time quickly open to routine connect rotor aircraft configuration, taken into account portability and the flying quality of aircraft.
Accompanying drawing explanation
Fig. 1 is fuselage wing extension schematic diagram of the present utility model；
Fig. 2 is fuselage wing-folding view of the present utility model；
Fig. 3 is front wing structural representation of the present utility model；
Fig. 4 is rear wing structural representation of the present utility model；
Fig. 5 is airframe structure schematic diagram of the present utility model；
Fig. 6 is fuselage slide block structure schematic diagram of the present utility model；
Fig. 7 is that tail of the present utility model hangs down structural representation；
Fig. 8 is afterbody structural representation of the present utility model.
Detailed description of the invention
Purpose and technical scheme for making this utility model embodiment are clearer, below in conjunction with the accompanying drawing of this utility model embodiment, are clearly and completely described the technical scheme of this utility model embodiment.Obviously, described embodiment is a part of embodiment of the present utility model rather than whole embodiments.Based on described embodiment of the present utility model, the every other embodiment that those of ordinary skill in the art are obtained on the premise of without creative work, broadly fall into this utility model protection scope:
Shown in Fig. 1: illustrate aircraft view during portable connection wing military unmanned aerial vehicle flight aloft, this kind of state of flight has lift-drag ratio greatly, the advantages such as structural strength is high, trim resistance is little.
Shown in Fig. 2, illustrating the portable connection wing military unmanned aerial vehicle aircraft view when carrying process, wing-folding fell to fuselage to fuselage both sides, vertical fin.Now to have carrying convenience, time of letting fly away short for state, simple in construction, battlefield survivability advantages of higher.
Shown in Fig. 3, illustrating the version of wing before aircraft, described front wing includes front wing rib 1, wing fence 2, front wing front-axle beam 3, wing tip end plate 4, electric line outlets 5, front wing wing root rotating shaft 6, the front wing back rest 7, front wing Servo-controller 8, front wing rudder face 9, front wing wing tip shaft hole 10；
Described front wing rib 1 forms front wing framework with front wing front-axle beam 3, the front wing back rest 7, is provided with front wing Servo-controller 8 in front wing framework, and the tail end of wing framework is provided with front wing rudder face 9, is provided with eyelid covering outside front wing framework；Being provided with front wing wing root rotating shaft 6 at the wing root of front wing framework, be provided with wing tip end plate 4 at the wing tip of front wing framework, the tail end of wing tip end plate 4 arranges front wing wing tip shaft hole 10；Wing root is provided with electric line outlets 5；Front wing rib 1 is provided with wing fence 2.
When being deployed into state of flight from folded state, before wing, thriving root rotating shaft 6 rotates forward for the center of circle, and drive rear wing by front wing wing tip rotating shaft, when high-altitude flight, front wing rudder face 9 is driven to control the rolling characteristics of aircraft by front wing Servo-controller 8, when wave hopping by wing fence 2, wing tip end plate 4 for suppressing the horizontal disturbance of air-flow.
In the diagram, illustrating the version of wing after aircraft, rear wing includes rear wing front-axle beam 11, rear wing rib 12, rear wing wing tip rotating shaft 13, rear wing wing root rotating shaft 14, rear wing Servo-controller 15, wing flap rudder face 16, the rear wing back rest 17；
Described rear wing front-axle beam 11, rear wing rib 12 form rear wing framework with the rear wing back rest 17, be provided with eyelid covering, be provided with rear wing Servo-controller 15 between rear wing front-axle beam 11 and the rear wing back rest 17 outside framework；Rear wing framework tail end is provided with wing flap rudder face 16；The wing tip of rear wing is provided with rear wing wing tip rotating shaft 13, and the wing root of rear wing is provided with rear wing wing root rotating shaft 14.Eyelid covering it is covered with on rear wing.
Rear wing wing tip rotating shaft 13 is connected with front wing tip rotating shaft by bearing, rear wing wing root rotating shaft 14 is connected with fuselage slide block by bearing, and it is the most rotatable at two, when being deployed into state of flight from folded state, fuselage slide block can drive rear wing wing root rotating shaft 14 to afterbody quick sliding, drive rear wing wing tip rotating shaft 13 and front wing simultaneously, make whole wing quickly open to flight attitude.When high-altitude flight, wing flap rudder face 16 is driven to control the pitching characteristic of aircraft by rear wing Servo-controller 15.
In view 5, illustrating the version of airframe, fuselage includes fuselage forward equipment bay 26, fuselage left plate 27, fuselage right plate 28, machine fuselage reinforcing frame 29, propeller 31, guide rail 32；Described fuselage left plate 27 is arranged in parallel with fuselage right plate 28；Several fuselage reinforcing frames 29 it are provided with between fuselage left plate 27 and fuselage right plate 28；Fuselage left plate 27, fuselage right plate 28 form fuselage ring structure with machine fuselage reinforcing frame 29, and its its top of fuselage ring structure arranges that fuselage forward equipment bay 26, tail end arrange propeller 31；Wing reinforcement 30 is arranged in fuselage ring structure and near fuselage forward equipment bay 26；Fuselage ring structural base is provided with the guide rail 32 slided for slide block；Power storehouse 33, armament equipment storehouse 34 it is provided with in fuselage ring structure；
In fuselage forward equipment bay 26, equipped with high-definition camera, for shooting unfriendly target during investigation；Equipped with electrical source of power in power storehouse 33, power for propeller 31, and be that the Servo-controller on four wings is powered by wire hole.Rear portion at fuselage, armament equipment storehouse 34 is divided into several booth by fuselage reinforcing frame 29, for the payload such as explosive, electronic reconnaissance equipment, scout for aircraft and use with during explosion, base plate both sides of the edge, armament equipment storehouse 34 also serve as aircraft slide block slide rail, and it is provided with energising Magnet foremost in armament equipment storehouse 34, when folded state, fix slide block.At the afterbody of aircraft, there is the vertical fin gripper shoe 35 for fixing vertical fin respectively, it is provided that the propeller 31 of power and the wing self-locking mechanism 36 for lock slider.
In view 6, illustrating the version of fuselage slide block, slide block includes lock hole 18, spring 19, strong magnets 20, slide block reinforcement 21, manual wrench 22；The upper surface of described manual wrench 22 is provided with strong magnets 20；The lower surface of manual wrench 22 is provided with spring 19；Being respectively equipped with two pieces of slide block reinforcements 21 before and after manual wrench 22 at sidewall edge, slide block reinforcement 21 is provided with hinge hole 23, forms the inside groove for connecting rear wing between two pieces of slide block reinforcements 21；Lock hole 18 it is additionally provided with on slide block reinforcement 21.
The main bearing member of whole slide block is slide block reinforcement 21, bears moment of torsion and the moment of flexure of rear wing in aircraft flight simultaneously.Dead eye is connected with rear wing by bearing, during slide block moves, drives rear wing to move together, and rear wing and front wing also have bearing to connect at wing tip simultaneously, and the motion of rear wing also can drive front wing, thus realizes the fast folding of wing.Lock hole 18 is for when slide block is positioned at afterbody, and slide block clashes into wing self-locking mechanism 36, and striker falls in lock hole 18, so that slide block will not move forward and backward, has fixed whole wing simultaneously.Spring 19 and strong magnets 20 achieve the process of slide block rapid deployment, spring 19 it is provided with, when slide block is at fore-body, and the most whole aircraft is in folded state between afterbody and slide block, now spring 19 is in extended state, and slide block is fixed on fore-body by strong magnets 20；After strong magnets 20 power-off demagnetization, by the contraction of spring 19, the quick rearward movement of slide block to clash into wing self-locking mechanism 36 locked, if occurring card during whole, hands can stretch into manual wrench 22 auxiliary body move, and can be by checking that hole checks fault.
In view 7 and Fig. 8, illustrating the version of vertical fin, vertical fin includes vertical fin bearing member 231, vertical fin locking device 24, striker lateral pin 25；Vertical fin locking device 24 is arranged in the bottom of described vertical fin bearing member 231；Claw is extended in the side of vertical fin locking device 24；Claw is connected with striker lateral pin 25, and claw drives striker lateral pin 25 to lift and fall；After striker lateral pin 25 falls, its bottom falls in lock hole 18.
The form at airframe rear portion after slide block has clashed into striker lateral pin 25 in Fig. 8, striker lateral pin 25 fixes vertical fin by pushing down vertical fin locking device 24, and now slide block has driven wing to be expanded to offline mode.
Those skilled in the art of the present technique are appreciated that unless otherwise defined, all terms used herein (including technical term and scientific terminology) have with the those of ordinary skill in this utility model art be commonly understood by identical meaning.Should also be understood that those terms defined in such as general dictionary should be understood that have the meaning consistent with the meaning in the context of prior art, and unless defined as here, will not explain by idealization or the most formal implication.
The above; it is only this utility model preferably detailed description of the invention; but protection domain of the present utility model is not limited thereto; any those familiar with the art is in the technical scope that this utility model discloses; the change that can readily occur in or replacement, all should contain within protection domain of the present utility model.Therefore, protection domain of the present utility model should be as the criterion with scope of the claims.
Claims (9)
- The most portable connection wing military unmanned aerial vehicle, it is characterised in that: include fuselage, wing front wing, wing rear wing, reinforcement, slide block, propeller, vertical fin；Described fuselage is provided with wing reinforcement (30) and slide block；Fuselage tail end is provided with propeller, and fuselage tail end is provided with vertical fin；One end of wing front wing is hinged with wing reinforcement (30), and the other end of wing front wing is hinged with one end of rear wing；The other end of rear wing is hinged with slide block；Slide block slides near wing reinforcement (30) side along the tail end of fuselage thus drives wing close to fuselage；Described vertical fin is hinged with fuselage, and vertical fin can lie against fuselage tail end or vertically stand on fuselage tail end.
- Portable connection wing military unmanned aerial vehicle the most according to claim 1, it is characterised in that: described wing is formed truss structure by front wing, rear wing；Wing front wing and rear wing connect formation at wing tip and connect wing aerodynamic arrangement.
- Portable connection wing military unmanned aerial vehicle the most according to claim 2, it is characterized in that: described front wing includes front wing rib (1), wing fence (2), front wing front-axle beam (3), wing tip end plate (4), electric line outlets (5), front wing wing root rotating shaft (6), the front wing back rest (7), front wing Servo-controller (8), front wing rudder face (9), front wing wing tip shaft hole (10)；Described front wing rib (1) and front wing front-axle beam (3), the front wing back rest (7) composition front wing framework, be provided with front wing Servo-controller (8) in front wing framework, the tail end of wing framework is provided with front wing rudder face (9), is provided with eyelid covering outside front wing framework；Being provided with front wing wing root rotating shaft (6) at the wing root of front wing framework, be provided with wing tip end plate (4) at the wing tip of front wing framework, the tail end of wing tip end plate (4) arranges front wing wing tip shaft hole (10)；Wing root is provided with electric line outlets (5)；Front wing rib (1) is provided with wing fence (2).
- 4. according to the portable connection wing military unmanned aerial vehicle described in Claims 2 or 3, it is characterized in that: described rear wing includes rear wing front-axle beam (11), rear wing rib (12), rear wing wing tip rotating shaft (13), rear wing wing root rotating shaft (14), rear wing Servo-controller (15), wing flap rudder face (16), the rear wing back rest (17)；Described rear wing front-axle beam (11), rear wing rib (12) form rear wing framework with the rear wing back rest (17), be provided with eyelid covering, be provided with rear wing Servo-controller (15) between rear wing front-axle beam (11) and the rear wing back rest (17) outside framework；Rear wing framework tail end is provided with wing flap rudder face (16)；The wing tip of rear wing is provided with rear wing wing tip rotating shaft (13), and the wing root of rear wing is provided with rear wing wing root rotating shaft (14).
- Portable connection wing military unmanned aerial vehicle the most according to claim 4, it is characterized in that: described front wing is hinged with wing reinforcement (30) by front wing wing root rotating shaft (6), front wing is hinged with rear wing wing tip rotating shaft (13) by front wing wing tip shaft hole (10)；Rear wing wing root rotating shaft (14) is hinged with slide block.
- Portable connection wing military unmanned aerial vehicle the most according to claim 4, it is characterised in that: described slide block includes lock hole (18), spring (19), strong magnets (20), slide block reinforcement (21), manual wrench (22)；The upper surface of described manual wrench (22) is provided with strong magnets (20)；The lower surface of manual wrench (22) is provided with spring (19)；Being respectively equipped with two pieces of slide block reinforcements (21) before and after manual wrench (22) at sidewall edge, slide block reinforcement (21) is provided with hinge hole (23), forms the inside groove for connecting rear wing between two pieces of slide block reinforcements (21)；Lock hole (18) it is additionally provided with on slide block reinforcement (21).
- Portable connection wing military unmanned aerial vehicle the most according to claim 6, it is characterised in that: also include that manhole (37), slide block reinforcement (21) are provided with manhole (37).
- 8. according to the portable connection wing military unmanned aerial vehicle described in claim 1 or 6, it is characterised in that: described vertical fin includes vertical fin bearing member (231), vertical fin locking device (24), striker lateral pin (25)；Vertical fin locking device (24) is arranged in the bottom of described vertical fin bearing member (231)；Claw is extended in the side of vertical fin locking device (24)；Claw is connected with striker lateral pin (25), and claw drives striker lateral pin (25) to lift and fall；After striker lateral pin (25) falls, its bottom falls in lock hole (18).
- Portable connection wing military unmanned aerial vehicle the most according to claim 1, it is characterised in that: described fuselage includes fuselage forward equipment bay (26), fuselage left plate (27), fuselage right plate (28), fuselage reinforcing frame (29), propeller (31), guide rail (32)；Described fuselage left plate (27) is arranged in parallel with fuselage right plate (28)；Several fuselage reinforcing frames (29) it are provided with between fuselage left plate (27) and fuselage right plate (28)；Fuselage left plate (27), fuselage right plate (28) form fuselage ring structure with machine fuselage reinforcing frame (29), and its its top of fuselage ring structure arranges that fuselage forward equipment bay (26), tail end arrange propeller (31)；Wing reinforcement (30) is arranged in fuselage ring structure and near fuselage forward equipment bay (26)；Fuselage ring structural base is provided with the guide rail (32) slided for slide block.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521135247.0U CN205499331U (en) | 2015-12-31 | 2015-12-31 | For military use unmanned vehicles of portable connection wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521135247.0U CN205499331U (en) | 2015-12-31 | 2015-12-31 | For military use unmanned vehicles of portable connection wing |
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| Publication Number | Publication Date |
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| CN205499331U true CN205499331U (en) | 2016-08-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521135247.0U Expired - Fee Related CN205499331U (en) | 2015-12-31 | 2015-12-31 | For military use unmanned vehicles of portable connection wing |
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| CN (1) | CN205499331U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105460204A (en) * | 2015-12-31 | 2016-04-06 | 南京航空航天大学 | Military unmanned aerial vehicle with portable united wings |
| CN112265631A (en) * | 2020-10-16 | 2021-01-26 | 中国空气动力研究与发展中心 | Box-type folding wing unmanned aerial vehicle layout capable of realizing modular assembly with variable aspect ratio |
-
2015
- 2015-12-31 CN CN201521135247.0U patent/CN205499331U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105460204A (en) * | 2015-12-31 | 2016-04-06 | 南京航空航天大学 | Military unmanned aerial vehicle with portable united wings |
| CN112265631A (en) * | 2020-10-16 | 2021-01-26 | 中国空气动力研究与发展中心 | Box-type folding wing unmanned aerial vehicle layout capable of realizing modular assembly with variable aspect ratio |
| CN112265631B (en) * | 2020-10-16 | 2022-07-12 | 中国空气动力研究与发展中心 | Box-type folding wing unmanned aerial vehicle layout capable of realizing modular assembly with variable aspect ratio |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160824 Termination date: 20181231 |