CN105460204A - Military unmanned aerial vehicle with portable united wings - Google Patents
Military unmanned aerial vehicle with portable united wings Download PDFInfo
- Publication number
- CN105460204A CN105460204A CN201511026382.6A CN201511026382A CN105460204A CN 105460204 A CN105460204 A CN 105460204A CN 201511026382 A CN201511026382 A CN 201511026382A CN 105460204 A CN105460204 A CN 105460204A
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- CN
- China
- Prior art keywords
- wing
- fuselage
- aerial vehicle
- unmanned aerial
- slide block
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
- B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
Abstract
The invention relates to an unmanned aerial vehicle, in particular to a military unmanned aerial vehicle with portable united wings. According to the military unmanned aerial vehicle with portable united wings, a wing stiffener and a sliding block are arranged on a fuselage, a propeller is arranged at the tail end of the fuselage, and a vertical tail is arranged at the tail end of the fuselage; one end of the front wing is hinged to the wing stiffener, and the other end of the front wing is hinged to one end of a rear wing; the other end of the rear wing is hinged to the sliding block; the sliding block slides along the tail end of the fuselage to one side close to the wing stiffener, so that the wings are driven to be close to the fuselage; the vertical tail is hinged to the fuselage, and can be levelly put at the tail end of the fuselage or perpendicular to tail end of the fuselage. According to the military unmanned aerial vehicle with portable united wings provided by the invention, the portability of a multiple-spindle aircraft and favorable flight performance of a fixed wing aircraft are fully used. The unmanned aerial vehicle is put in a knapsack after being folded, so that the unmanned aerial vehicle is convenient to carry, and the portability that the unmanned aerial vehicle is easy to carry is fully reflected. Before flight, the unmanned aerial vehicle is taken out from the knapsack, the unmanned aerial vehicle is thrown manually to fly, and in the manual throwing process, the wings and the vertical tails are ejected to be in the flight state, and land in the sliding manner.
Description
Technical field
The present invention relates to a kind of unmanned vehicle, particularly relate 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 just day by day, and how to be dissolved into by Fixed Wing AirVehicle in individual soldier's equipment of special force be original intention of the present invention.Consider that special force penetrats deep in isolation enemy's rear area sometimes, need in strange region to scout and identification in all side table kilometers, or carry out some demolition dutys.Although and existing Fixed Wing AirVehicle function admirable, voyage is far away, and penetration ability is strong, 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, large multiple speed is lower, and penetration ability is poor, and voyage is little, is all not suitable for for distant reconnaissance and strike, therefore still improper as individual reconnaissance/strike equipment.
Summary of the invention
The present invention is directed to above-mentioned deficiency and provide a kind of portable connection wing military unmanned aerial vehicle.
The present invention adopts following technical scheme:
Portable connection wing military unmanned aerial vehicle of the present invention, comprises fuselage, wing front wing, wing rear wing, reinforcement, slide block, propelling unit, vertical fin; Described fuselage is provided with wing reinforcement and slide block; Fuselage tail end is provided with propelling unit, and fuselage tail end is provided with vertical fin; One end and the wing reinforcement of wing front wing are hinged, the other end of wing front wing and one end of rear wing hinged; The other end and the slide block of rear wing are hinged; Slide block slides near wing reinforcement side along the tail end of fuselage thus drives wing close to fuselage; Described vertical fin and fuselage hinged, vertical fin can lie against fuselage tail end or vertically stand on fuselage tail end.
Portable connection wing military unmanned aerial vehicle of the present invention, described wing forms truss structure by front wing, rear wing; Wing front wing and rear wing are connected to form connection wing aerodynamic arrangement at wing tip.
Portable connection wing military unmanned aerial vehicle of the present invention, described front wing comprises front wing rib, wing fence, front wing front-axle beam, wing tip end plate, electric line outlets, the rotating shaft of front wing wing root, 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, the front wing back rest form front wing framework, are provided with front wing Servo-controller in front wing framework, and the tail end of wing framework is provided with front wing rudder face, and front wing framework outside is provided with covering; The wing root place of front wing framework is provided with the rotating shaft of front wing wing root, and the wing tip place of front wing framework is provided with wing tip end plate, and 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 of the present invention, described rear wing comprises rear wing front-axle beam, rear wing rib, the rotating shaft of rear wing wing tip, the rotating shaft of rear wing wing root, rear wing Servo-controller, wing flap rudder face, the rear wing back rest;
Described rear wing front-axle beam, rear wing rib and the rear wing back rest form rear wing framework, are provided with covering outside framework, are provided with rear wing Servo-controller between rear wing front-axle beam and the rear wing back rest; Rear wing framework tail end is provided with wing flap rudder face; The wing tip of rear wing is provided with the rotating shaft of rear wing wing tip, and the wing root of rear wing is provided with the rotating shaft of rear wing wing root.
Portable connection wing military unmanned aerial vehicle of the present invention, described front wing is hinged by the rotating shaft of front wing wing root and wing reinforcement, front wing pass through front wing wing tip shaft hole and the rotating shaft of rear wing wing tip hinged; The rotating shaft of rear wing wing root and slide block hinged.
Portable connection wing military unmanned aerial vehicle of the present invention, described slide block comprises 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; The front-rear side walls edge of manual wrench is respectively equipped with two pieces of slide block reinforcements, and slide block reinforcement is provided with hinge hole, forms the inside groove for connecting rear wing between two pieces of slide block reinforcements; Slide block reinforcement is also provided with lock hole.
Portable connection wing military unmanned aerial vehicle of the present invention, also comprises access opening, and access opening is arranged on slide block reinforcement.
Portable connection wing military unmanned aerial vehicle of the present invention, described vertical fin comprises vertical fin bearing member, vertical fin blocking device, striker lateral pin; Vertical fin blocking device is arranged in the bottom of described vertical fin bearing member; Claw is extended in the side of vertical fin blocking 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 of the present invention, described fuselage comprises fuselage forward equipment bay, fuselage left side board, fuselage right side board, machine fuselage reinforcing frame, propelling unit, guide rail; Described fuselage left side board and fuselage right side board are arranged in parallel; Several fuselage reinforcing frames are provided with between fuselage left side board and fuselage right side board; Fuselage left side board, fuselage right side board and machine fuselage reinforcing frame form fuselage framed structure, and its its top of fuselage ring structure arranges that fuselage forward equipment bay, tail end arrange propelling unit; Wing reinforcement to be arranged in fuselage ring structure and near fuselage forward equipment bay; Fuselage ring structural base is provided with the guide rail for skid.
Beneficial effect
Portable connection wing military unmanned aerial vehicle provided by the invention, is given full play to the portability of Multi-axis aircraft and the good airworthiness of Fixed Wing AirVehicle.Aircraft is put into knapsack in a folded fashion and is easy to carry, and fully demonstrates the portability be easy to carry about with one.Take out from knapsack before flight, the mode of being thrown by hand is taken off, and in the process that hand 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 aircraft pattern, there is good airworthiness and penetration ability, and have employed the aerodynamic arrangement of the connection wing, aircraft is made to have 1ift-drag ratio large, structural strength is high, trim resistance is little, carrying convenience, time of letting fly away are short, and structure is simple, battlefield survivability advantages of higher.
Only need a people to carry, require portable, flexible, reliable, efficient, to make every effort to structure simple and safe, practical, cheap simultaneously, and cost performance is high.In folding process, wing rotatable folding is to the both sides of fuselage, and vertical fin is folded on fuselage, take off time open to conventional connection rotor aircraft configuration fast, taken into account portability and the airworthiness of aircraft.
Accompanying drawing explanation
Fig. 1 is fuselage wing extension schematic diagram of the present invention;
Fig. 2 is fuselage wing-folding view of the present invention;
Fig. 3 is front wing structural representation of the present invention;
Fig. 4 is rear wing structural representation of the present invention;
Fig. 5 is airframe structure schematic diagram of the present invention;
Fig. 6 is fuselage slide block structure schematic diagram of the present invention;
Fig. 7 is that tail of the present invention hangs down structural representation;
Fig. 8 is afterbody structural representation of the present invention.
Detailed description of the invention
For making the object of the embodiment of the present invention and technical scheme clearly, below in conjunction with the accompanying drawing of the embodiment of the present invention, the technical scheme of the embodiment of the present invention is clearly and completely described.Obviously, described embodiment is a part of embodiment of the present invention, instead of whole embodiments.Based on described embodiments of the invention, the every other embodiment that those of ordinary skill in the art obtain under without the need to the prerequisite of creative work, all belongs to the scope of protection of the invention:
Shown in Fig. 1: illustrate aircraft view when portable connection wing military unmanned aerial vehicle flies aloft, this kind of state of flight has 1ift-drag ratio greatly, the advantages such as structural strength is high, trim resistance is little.
Shown in Fig. 2, illustrate the aircraft view of portable connection wing military unmanned aerial vehicle when carrying process, wing-folding is to fuselage both sides, and vertical fin fell on fuselage.Now state has carrying convenience, the time of letting fly away is short, and structure is simple, battlefield survivability advantages of higher.
Shown in Fig. 3, illustrate the version of wing before aircraft, described front wing comprises 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, and front wing framework outside is provided with covering; The wing root place of front wing framework is provided with front wing wing root rotating shaft 6, and the wing tip place of front wing framework is provided with wing tip end plate 4, and 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, wing in the past thriving root rotating shaft 6 rotates forward for the center of circle, and drive rear wing by the rotating shaft of front wing wing tip, when high-altitude flight, drive front wing rudder face 9 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, illustrate the version of wing after aircraft, rear wing comprises 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 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.Rear wing is covered with covering.
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 two places are all rotatable, 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 open to flight attitude fast.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, illustrate the version of airframe, fuselage comprises fuselage forward equipment bay 26, fuselage left side board 27, fuselage right side board 28, machine fuselage reinforcing frame 29, propelling unit 31, guide rail 32; Described fuselage left side board 27 is arranged in parallel with fuselage right side board 28; Several fuselage reinforcing frames 29 are provided with between fuselage left side board 27 and fuselage right side board 28; Fuselage left side board 27, fuselage right side board 28 form fuselage framed 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 propelling unit 31; Wing reinforcement 30 to be arranged in fuselage ring structure and near fuselage forward equipment bay 26; Fuselage ring structural base is provided with the guide rail 32 for skid; Power storehouse 33, armament equipment storehouse 34 is provided with in fuselage ring structure;
In fuselage forward equipment bay 26, high-definition camera is housed, for taking unfriendly target in investigation process; In power storehouse 33, electrical source of power being housed, for propelling unit 31 is powered, and is that Servo-controller on four wings is powered by wire hole.At the rear portion of fuselage, armament equipment storehouse 34 is divided into several booth by fuselage reinforcing frame 29, for the capacity weight such as explosive, electronic reconnaissance equipment, use for when aircraft scouting and explosion, base plate both sides of the edge, armament equipment storehouse 34 are also as aircraft slide block slide rail, and be provided with energising magnet foremost in armament equipment storehouse 34, fix slide block for during folded state.At the afterbody of aircraft, there is the vertical fin stay bearing plate 35 for fixing vertical fin respectively, the propelling unit 31 of power and the wing self-locking mechanism 36 for lock slider are provided.
In view 6, illustrate the version of fuselage slide block, slide block comprises 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; The front-rear side walls edge of manual wrench 22 is respectively equipped with two pieces of slide block reinforcements 21, and 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; Slide block reinforcement 21 is also provided with lock hole 18.
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.Bearing hole is connected with rear wing by bearing, and in the process of slide block movement, drive rear wing to move together, rear wing also has bearing to be connected with front wing at wing tip place 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, thus slide block can not be moved forward and backward, and has fixed whole wing simultaneously.Spring 19 and strong magnets 20 achieve the process of slide block rapid deployment, spring 19 is provided with, when slide block is at forebody, when namely whole aircraft is in folded state between afterbody and slide block, now spring 19 is in extended state, and slide block is fixed on forebody by strong magnets 20; After strong magnets 20 power-off demagnetization, by the contraction of spring 19, slide block moves fast backward and to clash into wing self-locking mechanism 36 locked, if there is card in whole process, hand can be stretched into manual wrench 22 auxiliary mechanism to move, and check fault by sighthole.
In view 7 and Fig. 8, illustrate the version of vertical fin, vertical fin comprises vertical fin bearing member 231, vertical fin blocking device 24, striker lateral pin 25; Vertical fin blocking device 24 is arranged in the bottom of described vertical fin bearing member 231; Claw is extended in the side of vertical fin blocking 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.
In Fig. 8, slide block has clashed into the form at the rear airframe rear portion of striker lateral pin 25, and striker lateral pin 25 fixes vertical fin by pushing down vertical fin blocking 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, and all terms used herein (comprising technical term and scientific terminology) have the meaning identical with the general understanding of the those of ordinary skill in field belonging to the present invention.Should also be understood that those terms defined in such as general dictionary should be understood to have the meaning consistent with the meaning in the context of prior art, unless and define as here, can not explain by idealized or too formal implication.
The above; be only the present invention's preferably detailed description of the invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; the change that can expect easily or replacement, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of claim.
Claims (9)
1. portable connection wing military unmanned aerial vehicle, is characterized in that: comprise fuselage, wing front wing, wing rear wing, reinforcement, slide block, propelling unit, vertical fin; Described fuselage is provided with wing reinforcement (30) and slide block; Fuselage tail end is provided with propelling unit, and fuselage tail end is provided with vertical fin; One end and the wing reinforcement (30) of wing front wing are hinged, the other end of wing front wing and one end of rear wing hinged; The other end and the slide block of rear wing are hinged; Slide block slides near wing reinforcement (30) side along the tail end of fuselage thus drives wing close to fuselage; Described vertical fin and fuselage hinged, vertical fin can lie against fuselage tail end or vertically stand on fuselage tail end.
2. portable connection wing military unmanned aerial vehicle according to claim 1, is characterized in that: described wing forms truss structure by front wing, rear wing; Wing front wing and rear wing are connected to form connection wing aerodynamic arrangement at wing tip.
3. portable connection wing military unmanned aerial vehicle according to claim 2, it is characterized in that: described front wing comprises 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) form front wing framework, and 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), and front wing framework outside is provided with covering; The wing root place of front wing framework is provided with front wing wing root rotating shaft (6), and the wing tip place of front wing framework is provided with wing tip end plate (4), and 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. the portable connection wing military unmanned aerial vehicle according to Claims 2 or 3, it is characterized in that: described rear wing comprises 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) and the rear wing back rest (17) form rear wing framework, be provided with 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).
5. the portable connection wing military unmanned aerial vehicle according to claim 1 or 4, it is characterized in that: described front wing is hinged by front wing wing root rotating shaft (6) and wing reinforcement (30), front wing is hinged by front wing wing tip shaft hole (10) and rear wing wing tip rotating shaft (13); Rear wing wing root rotating shaft (14) is hinged with slide block.
6. portable connection wing military unmanned aerial vehicle according to claim 4, is characterized in that: described slide block comprises 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); The front-rear side walls edge of manual wrench (22) is respectively equipped with two pieces of slide block reinforcements (21), and 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); Slide block reinforcement (21) is also provided with lock hole (18).
7. portable connection wing military unmanned aerial vehicle according to claim 6, is characterized in that: also comprise access opening (37), and access opening (37) is arranged on slide block reinforcement (21).
8. the portable connection wing military unmanned aerial vehicle according to claim 1 or 6, is characterized in that: described vertical fin comprises vertical fin bearing member (231), vertical fin blocking device (24), striker lateral pin (25); Vertical fin blocking device (24) is arranged in the bottom of described vertical fin bearing member (231); Claw is extended in the side of vertical fin blocking 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).
9. portable connection wing military unmanned aerial vehicle according to claim 1, is characterized in that: described fuselage comprises fuselage forward equipment bay (26), fuselage left side board (27), fuselage right side board (28), machine fuselage reinforcing frame (29), propelling unit (31), guide rail (32); Described fuselage left side board (27) and fuselage right side board (28) are arranged in parallel; Several fuselage reinforcing frames (29) are provided with between fuselage left side board (27) and fuselage right side board (28); Fuselage left side board (27), fuselage right side board (28) and machine fuselage reinforcing frame (29) form fuselage framed structure, and its its top of fuselage ring structure arranges that fuselage forward equipment bay (26), tail end arrange propelling unit (31); Wing reinforcement (30) to be arranged in fuselage ring structure and near fuselage forward equipment bay (26); Fuselage ring structural base is provided with the guide rail (32) for skid.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201511026382.6A CN105460204B (en) | 2015-12-31 | 2015-12-31 | Portable connection wing military unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201511026382.6A CN105460204B (en) | 2015-12-31 | 2015-12-31 | Portable connection wing military unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN105460204A true CN105460204A (en) | 2016-04-06 |
| CN105460204B CN105460204B (en) | 2017-09-29 |
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| CN201511026382.6A Expired - Fee Related CN105460204B (en) | 2015-12-31 | 2015-12-31 | Portable connection wing military unmanned aerial vehicle |
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| CN112407238A (en) * | 2020-11-24 | 2021-02-26 | 哈尔滨工业大学 | Aircraft telescopic wing based on stroke amplification mechanism |
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| CN112407238A (en) * | 2020-11-24 | 2021-02-26 | 哈尔滨工业大学 | Aircraft telescopic wing based on stroke amplification mechanism |
| CN112937834A (en) * | 2021-04-14 | 2021-06-11 | 北京航空航天大学 | Adopt small-size unmanned aerial vehicle of ally oneself with pneumatic overall arrangement of wing formula |
| CN112937834B (en) * | 2021-04-14 | 2022-06-28 | 北京航空航天大学 | Adopt small-size unmanned aerial vehicle of antithetical couplet wing formula aerodynamic configuration |
| CN113044200A (en) * | 2021-04-20 | 2021-06-29 | 西北工业大学 | Novel solar unmanned aerial vehicle layout with connection wings close to space |
| CN113044200B (en) * | 2021-04-20 | 2023-10-27 | 西北工业大学 | Solar unmanned aerial vehicle layout in adjacent space of connecting wing |
| CN113859516A (en) * | 2021-10-22 | 2021-12-31 | 哈尔滨工业大学 | Deformation wing parallel guide rail distributed type driving telescopic mechanism |
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| CN105460204B (en) | 2017-09-29 |
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