CN209126968U - A kind of twin fuselage unmanned plane with divided wing - Google Patents
A kind of twin fuselage unmanned plane with divided wing Download PDFInfo
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- CN209126968U CN209126968U CN201821744887.5U CN201821744887U CN209126968U CN 209126968 U CN209126968 U CN 209126968U CN 201821744887 U CN201821744887 U CN 201821744887U CN 209126968 U CN209126968 U CN 209126968U
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- high lift
- lift device
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Abstract
The utility model discloses a kind of twin fuselage unmanned plane with divided wing, including wing and fuselage, the horizontal tail may also be arranged on afterbody, the fuselage includes with the symmetrically arranged left fuselage of the plane of symmetry of wing and right fuselage, and the wing includes the left outside wing being successively detachably connected from left to right, left central wing, center the connection wing, the right median wing, starboard outboard；The left fuselage is arranged below left central wing, and the right fuselage is arranged below the right median wing；The carrying structure for carrying is provided on the center connection wing.The beneficial effects of the utility model are: the utility model can adjust the entire length of wing and the spacing of left fuselage and right fuselage according to specifically needing to select the center connection wing of different length, to meet various sizes of carrying object to the size requirement of mounting space between left fuselage and right fuselage, it avoids mounting space from wasting, can preferably adapt to different task by selecting different length center to connect the wing.
Description
Technical field
The utility model relates to air vehicle technique field, specifically a kind of twin fuselage unmanned plane with divided wing.
Background technique
Development of UAV is very fast in recent years, a kind of large size unmanned plane, as global hawk unmanned plane, predator's unmanned plane,
Pterosaur unmanned plane, rainbow unmanned plane and heron unmanned plane etc., endurance is long, can carry multiple-task load and weapon, executes more
Kind task, so that deep favored by various countries user.However for the cargo gondola, mission payload, large aerospace weapon of some large sizes,
Or other larger aircrafts for needing to launch in the air, still lack the unmanned plane that can be carried at present.
Utility model patent the 201720275100.4th disclosed on January 5th, 2018 discloses twenty formula of one kind and is laid out nobody
Machine has biggish mounting space, can carry large-sized object unmanned plane.But the unmanned plane that the utility model is announced or so fuselage
Spacing is fixed, and have much difficulty in healing weighing apparatus between task compatibility and flight efficiency.For example, when carrying cargo gondola execution freight transport task, goods
The width of object gondola is smaller, not high to the pitch requirements of left and right fuselage, not high to flight cruise requirement for height, and require compared with
Fast flying speed and lower kilometer oil consumption rate, wish that left and right fuselage spacing is smaller when executing this interior task, wing area is smaller,
To improve cruise efficiency；When carrying object is the large scale aircraft launched in the air, it is desirable to which left and right fuselage spacing is greatly a bit to guarantee
Loading space, wingspan length higher are launched with improving lift resistance ratio and then can fly to greatly in the air a bit.
Utility model content
In order to overcome the deficiencies of the prior art, the utility model provides a kind of twin fuselage unmanned plane with divided wing,
For adjusting the spacing of left and right fuselage to meet the space requirement of different carrying objects.
The technical scheme in the invention for solving the above technical problem is: a kind of twin fuselage with divided wing nobody
Machine, including being in the wing of symmetrical structure, the fuselage of side, the vertical fin that afterbody is arranged in, setting under the wings of an airplane being arranged in vertical fin
On horizontal tail, the horizontal tail may also be arranged on afterbody, and the fuselage includes symmetrical as the plane of symmetry using the plane of symmetry of wing
The left fuselage and right fuselage being arranged, the wing include the left outside wing being successively detachably connected from left to right, left central wing, in
Centre the connection wing, the right median wing, starboard outboard；The left fuselage is arranged below left central wing, and the right fuselage is arranged in the right side
It entreats below the wing；The carrying structure for carrying is provided on the center connection wing.
Beneficial effect acquired by this programme is: so that wing segmentation detachably can need to select difference according to specific
The center of length connects the wing to adjust the entire length of wing and the spacing of left fuselage and right fuselage, to meet different sizes
Carrying object to the size requirement of mounting space between left fuselage and right fuselage, avoid mounting space from wasting, reduce use cost.
In addition, by selecting different length center to connect the wing preferably to adapt to different task, the connection wing in brachymedial centre makes wing area
It is small, reduce flight resistance, and then improve flying speed, the task suitable for fast transportation shipping；The long center connection wing makes machine
Wing aspect ratio is big, so that lift resistance ratio is high, and then enables to flying height higher, is suitable for high-altitude and launches task.
Further, it in order to preferably realize the utility model, is provided with below the left outside wing and starboard outboard several
A power device symmetrical as the plane of symmetry using the plane of symmetry of wing.
It is using beneficial effect acquired by above-mentioned further technical solution: keeps power device symmetrical convenient for keeping
The balance of unmanned plane, and avoid power device from occupying the mounting space of left and right inboard and influence the carrying function of unmanned plane
Energy.
Further, in order to preferably realize that the utility model, the rear of the left outside wing are provided with the left outside wing rear of A
High lift device and the left outside wing rear high lift device of B, the rear of the starboard outboard are provided with A starboard outboard rear high lift device and B
Starboard outboard rear high lift device；The left outside wing rear high lift device of the A and A starboard outboard rear high lift device are symmetrical arranged, institute
The left outside wing rear high lift device of the B stated and B starboard outboard rear high lift device are symmetrical arranged.
It is using beneficial effect acquired by above-mentioned further technical solution: in take-off and landing stage and other needs
In the case where increase lift.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of this programme；
Fig. 2 is the bottom view of UAV flight A carrying object；
Fig. 3 is the bottom view of UAV flight B carrying object.
Wherein: 1- fuselage, 2- wing, the left outside wing of 21-, 22- starboard outboard, the left central wing of 23-, the 24- right median wing, in 25-
The centre connection wing, 3- vertical fin, 31- rudder, 4- horizontal tail, 41- elevator, 5- power device, 6- nose-gear, 7- main landing gear,
81-A carrying object, 82-B carrying object, the left outside wing rear high lift device of 211-A, the left outside wing rear high lift device of 212-B, 213- are left
Aileron, 221-A starboard outboard rear high lift device, 222-B starboard outboard rear high lift device, 223- starboard aileron.
Specific embodiment
Below with reference to examples and drawings, the utility model is described in further detail, but the reality of the utility model
It is without being limited thereto to apply mode.
Embodiment 1:
As shown in Figure 1, in the present embodiment, a kind of twin fuselage unmanned plane with divided wing, including in symmetrical structure
Wing 2, the fuselage 1 being arranged in below wing 2, the vertical fin 3 that 1 tail portion of fuselage is set, the horizontal tail 4 being arranged on vertical fin 3, it is described
Fuselage 1 include using the plane of symmetry of wing 2 as the symmetrically arranged left fuselage of the plane of symmetry and right fuselage, the wing 2 include from
The left outside wing 21, left central wing 23, center the connection wing 25, the right median wing 24, starboard outboard 22 being successively detachably connected from left to right；Institute
Left 23 lower section of central wing is arranged in the left fuselage stated, and the right fuselage is arranged below the right median wing 24；The center connection
The carrying structure for carrying is provided on the wing 25.The control system for realizing control is provided in fuselage 1.
The center connection wing 25 is symmetrical structure, and left central wing 23 connect the plane of symmetry pair of the wing 25 with the right median wing 24 with center
Claim distribution.The plane of symmetry that the left outside wing 21 connect the wing 25 with starboard outboard 22 with center is symmetrical.
Using twin fuselage unmanned plane convenient for article is carried and transported by plug-in mode, by article be mounted on left fuselage with
Between right fuselage, integrally keep balancing convenient for unmanned plane.The size of carrying object has difference according to specific circumstances, if left fuselage
It is smaller with the spacing of right fuselage, be unable to satisfy the installation requirement of large scale carrying object, need using another size nobody
Machine is carried, and the use cost of unmanned plane is increased.If the spacing of left fuselage and right fuselage is larger, although can satisfy small ruler
The installation requirement of very little carrying object, but will cause the waste of space and resource.
By the way that wing 2 to be segmented, and each section is set to be detachably connected, it can be according to the selection of dimension suitable dimension of carrying object
The center connection wing 25 adjust the spacing of left fuselage Yu right fuselage, to play the function of adjusting mounting space.
As shown in Figure 2 and Figure 3, since the width dimensions of A carrying object 81 are less than the width dimensions of B carrying object 82, thus A takes
Mounting space needed for loading 81 is less than the mounting space of B carrying object 82, is transporting the two carryings using the same unmanned plane
When object, it is only necessary to which the connection wing 25 in replacement center without replacing entire unmanned plane, thus reduces use cost, avoids
The wasting of resources.
When needing a collection of unmanned plane while transporting the different cargo of a collection of size, can also according to it is specific need to choose close
The suitable center connection wing 25 meets different requirements to adjust left fuselage from the spacing of right fuselage.
Further, it is additionally provided with power device 5 on unmanned plane, different number can be used, can be set on wing,
It can be set on fuselage, be the common knowledge and customary means of those skilled in the art, herein without repeating.
It is additionally provided with operation rudder face in each aerofoil, for example, the rear in vertical fin 3 is provided with rudder, after horizontal tail 4
Edge is provided with elevator, symmetrical aileron is arranged on wing 2.Flight using operation rudder face control aircraft is this field
The common knowledge and customary means of technical staff, specific structure and working principle not as this programme improvement, herein
The specific structure and working principle of operation rudder face are not repeated.
The nose-gear 6 that the lower section of the fuselage 1 is provided with and the main landing gear 7 positioned at 6 rear of nose-gear, it is described
Nose-gear 6 and main landing gear 7 can be with folding and unfoldings.Nose-gear 6 and main landing gear 7 slide for unmanned aerial vehicle, take off and
It alightings run, is the common knowledge and customary means of those skilled in the art, specific structure and working principle are not as this
The improvement of scheme does not repeat nose-gear 6 and the specific structure and working principle of main landing gear 7 herein.
Embodiment 2:
On the basis of the above embodiments, in the present embodiment, the lower section of the left outside wing 21 and starboard outboard 22 is provided with
Several power devices 5 symmetrical as the plane of symmetry using the plane of symmetry of wing 2.
Power is provided for the flight of unmanned plane using power device 5, specific structure and working principle are not as this programme
Improvement, the specific structure of power device 5 is not defined and is repeated with working principle herein.
Make the symmetrical unmanned plane that is conducive to of power device 5 integrally keep balancing, avoids any one lateral deviation weight in the left and right sides
And influence the flight of unmanned plane.The quantity of the power device 5 is even number, and convenient for distribution.Power device 5 is distributed in machine
The outside of body 1, i.e. setting are in the left outside wing 21 and the carrying sky on starboard outboard 22, avoiding the occupancy left and right inboard of power device 5
Between.
Embodiment 3:
On the basis of the above embodiments, in the present embodiment, the rear of the left outside wing 21 is provided with the left outside wing rear of A
High lift device 211 and the left outside wing rear high lift device 212 of B, the rear of the starboard outboard 22 are provided with A starboard outboard rear lift-rising
Device 221 and B starboard outboard rear high lift device 222；The left outside wing rear high lift device 211 of the A and A starboard outboard rear lift-rising
Device 221 is symmetrical arranged, and the left outside wing rear high lift device 212 of the B is symmetrical arranged with B starboard outboard rear high lift device 222.
Utilize the left outside wing rear high lift device 211 of A, A starboard outboard rear high lift device 221, the left outside wing rear high lift device of B
212 wait high lift devices with B starboard outboard rear high lift device 222, convenient in the case where take-off and landing stage and other needs
The lift for increasing unmanned plane, is conducive to make unmanned plane also can be compared with low velocity take-off and landing, Huo Zhe when carrying cargo
When dispensing, speed is reduced by increasing lift in order to be launched.The specific structure and working principle of high lift device are this
The customary means of field technical staff, and not as the improvement of this programme, herein not to the specific structure of high lift device and
Working principle is defined and repeats.
It is above-described, it is only the preferred embodiment of the utility model, any form not is made to the utility model
On limitation, according to the technical essence of the utility model, within the spirit and principles of the present invention, to above embodiments institute
Any simple modifications, equivalent substitutions and improvements etc. made, within the protection scope for still falling within technical solutions of the utility model.
Claims (3)
1. a kind of twin fuselage unmanned plane with divided wing including the wing (2) in symmetrical structure and is arranged under wing (2)
The fuselage (1) of side, the fuselage (1) includes using the plane of symmetry of wing (2) as the symmetrically arranged left fuselage of the plane of symmetry and right machine
Body, it is characterised in that: the wing (2) includes the left outside wing (21) being successively detachably connected from left to right, left central wing
(23), center the connection wing (25), the right median wing (24), starboard outboard (22)；The left fuselage is arranged below left central wing (23),
The right fuselage setting is below the right median wing (24)；The carrying for carrying is provided in the center connection wing (25)
Structure.
2. a kind of twin fuselage unmanned plane with divided wing according to claim 1, it is characterised in that: described is left outside
Several are provided with below the wing (21) and starboard outboard (22) to fill using the plane of symmetry of wing (2) power symmetrical as the plane of symmetry
Set (5).
3. a kind of twin fuselage unmanned plane with divided wing according to claim 1 or 2, it is characterised in that: described
The rear of the left outside wing (21) is provided with the left outside wing rear high lift device (211) of A and the left outside wing rear high lift device (212) of B, described
The rear of starboard outboard (22) be provided with A starboard outboard rear high lift device (221) and B starboard outboard rear high lift device (222)；Institute
The left outside wing rear high lift device (211) of the A stated and A starboard outboard rear high lift device (221) are symmetrical arranged, the left outside wing of the B
Rear high lift device (212) and B starboard outboard rear high lift device (222) are symmetrical arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821744887.5U CN209126968U (en) | 2018-10-26 | 2018-10-26 | A kind of twin fuselage unmanned plane with divided wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821744887.5U CN209126968U (en) | 2018-10-26 | 2018-10-26 | A kind of twin fuselage unmanned plane with divided wing |
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| Publication Number | Publication Date |
|---|---|
| CN209126968U true CN209126968U (en) | 2019-07-19 |
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|---|---|---|---|
| CN201821744887.5U Active CN209126968U (en) | 2018-10-26 | 2018-10-26 | A kind of twin fuselage unmanned plane with divided wing |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111017185A (en) * | 2019-12-19 | 2020-04-17 | 中国航空工业集团公司西安飞机设计研究所 | Laminar flow technology verification machine |
| CN112977879A (en) * | 2021-04-01 | 2021-06-18 | 中国航天空气动力技术研究院 | Aeroelastic test platform |
| CN113335517A (en) * | 2021-08-09 | 2021-09-03 | 中国空气动力研究与发展中心空天技术研究所 | Double-fuselage tandem rotor wing composite wing aircraft layout |
-
2018
- 2018-10-26 CN CN201821744887.5U patent/CN209126968U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111017185A (en) * | 2019-12-19 | 2020-04-17 | 中国航空工业集团公司西安飞机设计研究所 | Laminar flow technology verification machine |
| CN112977879A (en) * | 2021-04-01 | 2021-06-18 | 中国航天空气动力技术研究院 | Aeroelastic test platform |
| CN113335517A (en) * | 2021-08-09 | 2021-09-03 | 中国空气动力研究与发展中心空天技术研究所 | Double-fuselage tandem rotor wing composite wing aircraft layout |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Double-fuselage unmanned aerial vehicle with segmented wings Effective date of registration: 20191227 Granted publication date: 20190719 Pledgee: Agricultural Bank of China Co.,Ltd. Chengdu Tianfu New Area Branch Pledgor: SICHUAN TENGDUN TECHNOLOGY Co.,Ltd. Registration number: Y2019510000082 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20231026 Granted publication date: 20190719 Pledgee: Agricultural Bank of China Co.,Ltd. Chengdu Tianfu New Area Branch Pledgor: SICHUAN TENGDUN TECHNOLOGY Co.,Ltd. Registration number: Y2019510000082 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right |