CN110228590A - A kind of detachable cargo hold connection wing twin fuselage logistics unmanned plane - Google Patents
A kind of detachable cargo hold connection wing twin fuselage logistics unmanned plane Download PDFInfo
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- CN110228590A CN110228590A CN201910582228.9A CN201910582228A CN110228590A CN 110228590 A CN110228590 A CN 110228590A CN 201910582228 A CN201910582228 A CN 201910582228A CN 110228590 A CN110228590 A CN 110228590A
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- wing
- cargo hold
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- part host
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 12
- 239000000463 material Substances 0.000 claims description 6
- 230000009467 reduction Effects 0.000 claims description 5
- 239000002131 composite material Substances 0.000 claims description 3
- 230000005484 gravity Effects 0.000 claims description 3
- 238000013461 design Methods 0.000 description 7
- 238000005516 engineering process Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 239000002657 fibrous material Substances 0.000 description 2
- 230000004927 fusion Effects 0.000 description 2
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
- 240000002853 Nelumbo nucifera Species 0.000 description 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 1
- 238000007792 addition Methods 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
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- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/10—All-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D9/00—Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C2009/005—Ailerons
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of detachable cargo holds to connect wing twin fuselage logistics unmanned plane, and the detachable cargo hold connection wing twin fuselage logistics unmanned plane includes blended wing-body formula twin fuselage, lower part host wing, upper secondary wing, propulsion device, modular removable formula cargo hold, flight control system and vertical tail；The blended wing-body formula twin fuselage and lower part host wing are seamlessly transitted using curved surface, lower part host wing and upper secondary wing constitute connection wing structure, modular removable formula cargo hold is located in the middle part of lower part host wing, and flight control system includes aileron, the elevator and rudder on upper secondary wing of wing flap on the inside of the host wing of lower part, outside.Twin fuselage logistics unmanned plane load loading space with higher of the invention, outstanding aeroperformance have better airport adaptability, excellent economy and higher cargo efficiency of loading.
Description
Technical field
The present invention relates to unmanned aerial vehicle designs and manufacturing field, connect the logistics of wing twin fuselage more particularly to detachable cargo hold
Unmanned plane.
Background technique
With e-commerce, the fast development of air harbor regional economy, logistic industry to unmanned plane since it is more and more brighter
It is aobvious, long-range, medium-long range, intermediate range, short range, the logistics system of end are formed, end and short range logistics distribution generally use someone
Lorry express delivery or multi-rotor unmanned aerial vehicle are realized, enterprise's railway, highway and large-scale visitor remotely can be used and change the completion of goods someone's aircraft, but is right
Medium-long range, intermediate range logistics transportation, the increase of cost can be brought using above method, be badly in need of a kind of for medium-long range or intermediate range logistics
The air transportation mode of transport.The very big cost of voyage defect and long-range someone's cargo aircraft in view of more rotors of short range, in
Type, relatively large fixed-wing shipping unmanned plane are one of the effective means realized.
Technical problem of the invention is current medium-long range logistics unmanned aerial vehicle design, and there are following critical issues:
(1) unmanned plane payload is smaller；(2) adaptability on the especially general airport in airport is poor；(3) economy and efficiency of loading compared with
It is low.To limit the universal of logistics unmanned plane.
In order to solve the above problem, the present invention uses following key technology approach: (1) removable using twin fuselage binding modulesization
Formula cargo hold is unloaded, unmanned plane payload can greatly improve 50 ~ 80%；(2) to improve airport adaptability, using even wing formula structure, drop
The low span 30 ~ 50%, so that the unmanned plane of same level take-off weight can be adapted for airport of opening the navigation or air flight；(3) connecting wing body fusion type is set
Meter, the modular removable formula cargo hold of drag reduction streamline shape, connection wing structure design, reduce flight resistance 10% or so, simultaneously
With preferable structural strength and lower construction weight, voyage is effectively increased；(4) fusion type twin fuselage, modularization are used
Removable discharge compartment is designed in conjunction, can greatly improve cargo handling speed, alleviates the logistics pressure that future airport faces.
Summary of the invention
Regarding the issue above, the present invention provides one kind greatly improves payload, improves Air Logistics economy
Property, improve airport adaptability wing twin fuselage logistics unmanned plane is connected with the detachable cargo hold of cargo handling speed.
In order to achieve the above objectives, present invention employs following technical proposals: a kind of detachable cargo hold connection of the invention
Wing twin fuselage logistics unmanned plane, the detachable cargo hold connection wing twin fuselage logistics unmanned plane includes blended wing-body formula two-shipper
Body, lower part host wing, upper secondary wing, propulsion device, modular removable formula cargo hold, flight control system and vertical tail；
The blended wing-body formula twin fuselage and lower part host wing are seamlessly transitted using curved surface, the lower part host wing and top slave
The wing constitutes connection wing structure, and the blended wing-body formula twin fuselage are located at lower part host wing away from 0.2 ~ 0.6 sesquialter length position of wing root
Set, the upper secondary wing be connected to lower part host wing wingtip position formed connection wing structure, the propulsion device and
Vertical tail is respectively positioned on the tail portion of blended wing-body formula twin fuselage, and the vertical tail is connected with upper secondary wing, the company of raising
Wing structure intensity is connect, and improves unmanned plane directional stability.The modular removable formula cargo hold is connected with lower part host wing
It connects, wing flap, aileron, the elevator of the flight control system are respectively placed in modular removable formula cargo hold and blended wing-body formula
Between twin fuselage, the rear of the outside rear of lower part host wing, upper secondary wing.
Further, the lower part host wing uses Low Speed Airfoil or laminar flow airfoil, after the lower part host wing
Sweep angle is 0 ~ 30 degree, and flight stability is improved at 0 ~ 3 degree of the upper counterangle of the lower part host wing.
Further, the upper secondary wing is Low Speed Airfoil or laminar flow airfoil, the sweepforward of the lower part host wing
Angle is 5 ~ 35 degree.
Further, the shape of the modular removable formula cargo hold is drag reduction streamline shape, by inserting mode fastly
Be connected to the wing root position of lower part host wing, keep center of gravity generally within 0.25 times of chord length of wing root at.
Further, the propulsion device is double hair propulsion systems, and the propulsion device is battery or helical turbine
Paddle motor driving.
Further, the flight control system includes wing flap, aileron, elevator and rudder, the wing flap position
Between modular removable formula cargo hold and blended wing-body formula twin fuselage, the lift-rising dress of lift is improved when taking off for unmanned plane
It sets；The aileron is located at the outside rear of lower part host wing, can be extended according to mission requirements to extending in the host wing of lower part
Side, roll guidance and control for unmanned plane；Elevator is located at the posterior border position of upper secondary wing, realizes unmanned plane pitching behaviour
Make, and assists realizing tumbling action；Rudder is located at the rear section of vertical tail.
Further, the upper secondary wing is away from 0 ~ 0.3 sesquialter length of wingtip,
Further, the material of the blended wing-body formula twin fuselage, lower part host wing and upper secondary wing be composite material or
Other light-weight high-strength materials.
The utility model has the advantages that the present invention is based on twin fuselage designs, connection wing structure, modular removable formula cargo hold, blended wing-body
And airflow design, the comprehensive air transportation ability for improving the logistics unmanned plane.In conjunction with twin fuselage, modular removable formula goods
Cabin, payload can greatly improve 50 ~ 80%；Using the modular removable formula cargo hold of blended wing-body technology, drag reduction streamline shape
And connection wing structure, reduce flight resistance 10%；With outstanding navigation airport adaptability, with the substantially increasing on navigation airport
Add, higher convenience will be provided for logistics unmanned plane, and the adaptability on airport of opening the navigation or air flight will become the important restrictions of logistics unmanned plane；
Binding modules design for disassembly thinking can greatly improve unmanned plane cargo handling efficiency, improve logistics speed.
With existing compared with task unmanned plane, the present invention has the advantage that
(1) twin fuselage are designed and are connected the wing and effectively combine by the present invention, are solved between heavy load and airport adaptability
Contradiction, make it possible open the navigation or air flight airport landing medium-long range logistics unmanned plane；
(2) load load mode of the present invention is flexible, (carries to the task of some more difficult disassemblies in conjunction with the traditional type load mode of fuselage
Lotus) and modular removable formula transloading mode (being mainly directed towards routinely logistics goods), substantially increase cargo handling efficiency.
(3) blended wing-body of the invention design, reduces flight resistance, is conducive to improve unmanned plane aerodynamic characteristic and structure is special
Property.
Detailed description of the invention
Fig. 1 is oblique view of the invention；
Fig. 2 is top view of the invention；
Fig. 3 is side view of the invention；
Wherein, 1 blended wing-body formula twin fuselage, 2 lower part host wings, 3 upper secondary wings, 4 propulsion devices, 5 modular removable formulas
Cargo hold, 6 flight control systems, 61 wing flaps, 62 ailerons, 63 elevators, 64 rudders, 7 vertical tails.
Specific embodiment
Following embodiment only exists in illustrative purpose, limits the scope of the invention without being intended to.
Embodiment 1
A kind of detachable cargo hold of the invention connects wing twin fuselage logistics unmanned plane, and the detachable cargo hold connection wing is double
Fuselage logistics unmanned plane includes blended wing-body formula twin fuselage 1, lower part host wing 2, upper secondary wing 3, propulsion device 4, modularization
Detachable cargo hold 5, flight control system 6 and vertical tail 7.
The blended wing-body formula twin fuselage 1 and lower part host wing 2 are seamlessly transitted using curved surface, lower part host wing 2 and upper
Portion's slave wing constitutes connection wing structure.Blended wing-body formula twin fuselage 1 are located at lower part host wing 2 away from 0.2 sesquialter length position of wing root.
The lower part host wing 2 uses Low Speed Airfoil, and angle of sweep is 10 degree, and flight stability is improved at 0 ~ 3 degree of the upper counterangle
Property.The upper secondary wing 3 is connected to the wingtip position of lower part host wing 2, away from 0.1 sesquialter length of wingtip, forms the connection wing
Structure, the upper secondary wing 3 are Low Speed Airfoil or laminar flow airfoil, and sweepforward angle is 18 degree.
Blended wing-body formula twin fuselage 1, lower part host wing 2 and the upper secondary wing 3 be composite material or its
Its light-weight high-strength material.
The modular removable formula cargo hold 5 is drag reduction streamline shape, is connected to lower part host wing 2 by inserting mode fastly
Wing root position, keep center of gravity generally within 0.25 times of chord length of wing root at.
The propulsion device 4 is located at the tail portion of blended wing-body formula twin fuselage 1, and for double hair propulsion systems, battery can be used
Or turboprop driving.
The flight control system 6 includes wing flap 61, aileron 62, elevator 63 and rudder 64；Wing flap 61 is located at mould
Between the detachable cargo hold 5 of blockization and blended wing-body formula twin fuselage 1, the high lift device of lift is improved when taking off for unmanned plane；
Aileron 62 is located at the outside rear of lower part host wing 2, can be extended to 2 inside of lower part host wing is extended to, be used according to mission requirements
In the roll guidance and control of unmanned plane；Elevator 63 is located at the posterior border position of upper secondary wing 3, realizes unmanned plane pitching behaviour
Make, and assists realizing tumbling action；Rudder 64 is located at the rear section of vertical tail 7.
The vertical tail 7 is located at the tail portion of blended wing-body formula twin fuselage 1, and is connected with upper secondary wing 3, improves
Wing structure intensity is connected, and improves unmanned plane directional stability.
Embodiment 2
Embodiment 2 the difference from embodiment 1 is that:
The blended wing-body formula twin fuselage 1 are located at lower part host wing 2 away from 0.3 sesquialter length position of wing root；
The lower part host wing 2 uses Low Speed Airfoil, and angle of sweep is 15 degree, 1 degree of the upper counterangle；
The upper secondary wing 3 is connected to the wingtip position of lower part host wing 2, away from 0.15 sesquialter length of wingtip, forms connection
Wing structure, the upper secondary wing 3 are Low Speed Airfoil, and sweepforward angle is 25 degree.
Blended wing-body formula twin fuselage 1, lower part host wing 2 and the upper secondary wing 3 is for almag and again
Condensation material.
Embodiment 3
The blended wing-body formula twin fuselage 1 are located at lower part host wing 2 away from 0.4 sesquialter length position of wing root；
The lower part host wing 2 uses laminar flow airfoil, and angle of sweep is 20 degree, 1 degree of the upper counterangle；
The upper secondary wing 3 is connected to the wingtip position of lower part host wing 2, away from 0.25 sesquialter length of wingtip, forms connection
Wing structure, the upper secondary wing 3 are laminar flow airfoil, and sweepforward angle is 35 degree.
Blended wing-body formula twin fuselage 1, lower part host wing 2 and the upper secondary wing 3 is almag and carbon
Fibrous material.
Embodiment 4
Embodiment 4 the difference from embodiment 1 is that:
The blended wing-body formula twin fuselage 1 are located at lower part host wing 2 away from 0.5 sesquialter length position of wing root；
The lower part host wing 2 uses laminar flow airfoil, and angle of sweep is 25 degree, 1.5 degree of the upper counterangle；
The upper secondary wing 3 is connected to the wingtip position of lower part host wing 2, away from 0.3 sesquialter length of wingtip, forms the connection wing
Structure, the upper secondary wing 3 are laminar flow airfoil, and sweepforward angle is 30 degree.
Blended wing-body formula twin fuselage 1, lower part host wing 2 and the upper secondary wing 3 is almag and carbon
Fibrous material.
Embodiment 5
Embodiment 5 the difference from embodiment 1 is that: the blended wing-body formula twin fuselage (1) are located at lower part host wing (2) away from the wing
0.2 sesquialter length position of root, the lower part host wing 2 use laminar flow airfoil, and angle of sweep is 30 degree, 0 degree of the upper counterangle；Described
Upper secondary wing 3 is laminar flow airfoil, and sweepforward angle is 35 degree.
Embodiment 6
Embodiment 6 the difference from embodiment 1 is that: the blended wing-body formula twin fuselage (1) are located at lower part host wing (2) away from the wing
0.6 sesquialter length position of root, the lower part host wing 2 use laminar flow airfoil, and angle of sweep is 0 degree, 3 degree of the upper counterangle；Described
Upper secondary wing 3 is laminar flow airfoil, and sweepforward angle is 5 degree.
Specific embodiment described herein is only an example for the spirit of the invention.The neck of technology belonging to the present invention
The technical staff in domain can make various modifications or additions to the described embodiments or replace by a similar method
In generation, however, it does not deviate from the spirit of the invention or beyond the scope of the appended claims.
Although 1 blended wing-body formula twin fuselage, 2 lower part host wings, 3 upper secondary wings, 4 propulsion dresses are used more herein
It sets, 5 modular removable formula cargo holds, 6 flight control systems, 61 wing flaps, 62 ailerons, 63 elevators, 64 rudders, 7 vertical ends
The terms such as the wing, but it does not exclude the possibility of using other terms.The use of these items is only for more easily describing and
Explain essence of the invention；Being construed as any additional limitation is disagreed with spirit of that invention.
Claims (8)
1. a kind of detachable cargo hold connects wing twin fuselage logistics unmanned plane, it is characterised in that: the detachable cargo hold connects
Wing twin fuselage logistics unmanned plane is connect to include blended wing-body formula twin fuselage (1), lower part host wing (2), upper secondary wing (3), promote
Device (4), modular removable formula cargo hold (5), flight control system (6) and vertical tail (7), the blended wing-body formula are double
Fuselage (1) and lower part host wing (2) are seamlessly transitted using curved surface, and the lower part host wing (2) and upper secondary wing (3) are constituted
Wing structure is connected, the blended wing-body formula twin fuselage (1) are located at lower part host wing (2) away from 0.2 ~ 0.6 sesquialter length position of wing root
It sets, the wingtip position that the upper secondary wing (3) is connected to lower part host wing (2) forms connection wing structure, the propulsion
Device (4) and vertical tail (7) are respectively positioned on the tail portion of blended wing-body formula twin fuselage (1), the vertical tail (7) and upper secondary
Wing (3) is connected, and the modular removable formula cargo hold (5) is connected with lower part host wing (2), the flight control
Wing flap (61), aileron (62), the elevator (63) of system (6) are respectively placed in modular removable formula cargo hold (5) and blended wing-body
Between formula twin fuselage (1), the rear of the outside rear of lower part host wing (2), upper secondary wing (3).
2. detachable cargo hold according to claim 1 connects wing twin fuselage logistics unmanned plane, it is characterised in that: described
Lower part host wing (2) uses Low Speed Airfoil or laminar flow airfoil, and the angle of sweep of the lower part host wing (2) is 0 ~ 30 degree, described
Lower part host wing (2) 0 ~ 3 degree of the upper counterangle.
3. detachable cargo hold according to claim 2 connects wing twin fuselage logistics unmanned plane, it is characterised in that: described
Upper secondary wing (3) is Low Speed Airfoil or laminar flow airfoil, and the sweepforward angle of the lower part host wing (2) is 5 ~ 35 degree.
4. detachable cargo hold according to claim 1 connects wing twin fuselage logistics unmanned plane, it is characterised in that: described
The shape of modular removable formula cargo hold (5) is drag reduction streamline shape, the wing for being connected to lower part host wing (2) by inserting mode fastly
Root position, keep center of gravity generally within 0.25 times of chord length of wing root at.
5. detachable cargo hold according to claim 1 connects wing twin fuselage logistics unmanned plane, it is characterised in that: described
Propulsion device (4) is double hair propulsion systems, and the propulsion device (4) is that battery or turboprop drive.
6. detachable cargo hold according to claim 1 connects wing twin fuselage logistics unmanned plane, it is characterised in that: described
Flight control system (6) includes wing flap (61), aileron (62), elevator (63) and rudder (64), the wing flap (61) position
Between modular removable formula cargo hold (5) and blended wing-body formula twin fuselage (1), the aileron (62) is located at lower part host wing
(2) outside rear, the aileron (62) are extended to extending on the inside of lower part host wing (2), and elevator (63) is located at top
The posterior border position of the slave wing (3), rudder (64) are located at the rear section of vertical tail (7).
7. detachable cargo hold according to claim 1 connects wing twin fuselage logistics unmanned plane, it is characterised in that: described
Upper secondary wing (3) is away from 0 ~ 0.3 sesquialter length of wingtip.
8. detachable cargo hold according to claim 1 connects wing twin fuselage logistics unmanned plane, it is characterised in that: described
The material of blended wing-body formula twin fuselage (1), lower part host wing (2) and upper secondary wing (3) is that composite material or other lightweights are high
Strong material.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910582228.9A CN110228590A (en) | 2019-06-30 | 2019-06-30 | A kind of detachable cargo hold connection wing twin fuselage logistics unmanned plane |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910582228.9A CN110228590A (en) | 2019-06-30 | 2019-06-30 | A kind of detachable cargo hold connection wing twin fuselage logistics unmanned plane |
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| CN110228590A true CN110228590A (en) | 2019-09-13 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113460282A (en) * | 2021-06-28 | 2021-10-01 | 航天时代飞鸿技术有限公司 | Pneumatic layout of unmanned aerial vehicle |
| CN115884923A (en) * | 2020-08-25 | 2023-03-31 | 以色列航空工业有限公司 | Aircraft with external upper cargo module |
| CN116062205A (en) * | 2023-03-07 | 2023-05-05 | 四川腾盾科技有限公司 | Unmanned aerial vehicle with integral fuselage cargo hold throwing and recycling device and throwing method |
Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5007875A (en) * | 1987-10-02 | 1991-04-16 | Madhava Dasa | Multiple configuration model aircraft |
| CA1314035C (en) * | 1988-11-23 | 1993-03-02 | Georges C.A. Armand | Airplanes and hydroplanes with multiple fuselages with three support surfaces |
| US20020003190A1 (en) * | 2000-06-29 | 2002-01-10 | Sankrithi Mithra M.K.V. | Blended wing and multiple-body airplane configuration |
| CN103171766A (en) * | 2011-12-20 | 2013-06-26 | 北京航空航天大学 | Short distance rising and landing unmanned all-wing aircraft |
| DE102012023821A1 (en) * | 2012-12-05 | 2014-06-05 | Airbus Operations Gmbh | Airplane with at least two fuselages and two main wings |
| CN203698646U (en) * | 2014-01-16 | 2014-07-09 | 江苏中科遥感信息技术有限公司 | Flying wing imitating rapidly ascending unmanned plane |
| DE102014201040A1 (en) * | 2014-01-21 | 2015-07-23 | Airbus Operations Gmbh | aircraft |
| CN104875885A (en) * | 2015-06-17 | 2015-09-02 | 沈阳飞机工业（集团）有限公司 | Composite aircraft |
| CN107521695A (en) * | 2017-08-04 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of blended wing-body connects wing aircraft |
| CN206841718U (en) * | 2017-03-21 | 2018-01-05 | 四川腾盾科技有限公司 | A kind of twenty formula layout unmanned plane |
| CN107985597A (en) * | 2017-11-03 | 2018-05-04 | 西北工业大学 | A kind of shipping unmanned plane with modularization cargo hold |
| CN108058830A (en) * | 2017-12-14 | 2018-05-22 | 彩虹无人机科技有限公司 | A kind of unmanned logistics transportation machine of binary |
| CN207450215U (en) * | 2017-09-20 | 2018-06-05 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of change sweepforward twin-fuselage configuration aircraft |
| CN108557081A (en) * | 2018-03-23 | 2018-09-21 | 西北工业大学 | A kind of solar united wing unmanned plane and its control method |
| CN108569399A (en) * | 2018-04-10 | 2018-09-25 | 西北工业大学 | A kind of short take-off and landing unmanned plane using distributed duct power |
| CN109305375A (en) * | 2018-10-29 | 2019-02-05 | 四川腾盾科技有限公司 | A kind of twin-fuselage aircraft |
| CN109398705A (en) * | 2018-03-15 | 2019-03-01 | 吴大卫 | A kind of airfreighter |
| CN109774916A (en) * | 2019-01-14 | 2019-05-21 | 北京航空航天大学 | A kind of Helios using three-dimensional layout designs |
| CN211766301U (en) * | 2019-06-30 | 2020-10-27 | 郑州航空工业管理学院 | Double-body logistics unmanned aerial vehicle with detachable cargo compartment connecting wings |
-
2019
- 2019-06-30 CN CN201910582228.9A patent/CN110228590A/en active Pending
Patent Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5007875A (en) * | 1987-10-02 | 1991-04-16 | Madhava Dasa | Multiple configuration model aircraft |
| CA1314035C (en) * | 1988-11-23 | 1993-03-02 | Georges C.A. Armand | Airplanes and hydroplanes with multiple fuselages with three support surfaces |
| US20020003190A1 (en) * | 2000-06-29 | 2002-01-10 | Sankrithi Mithra M.K.V. | Blended wing and multiple-body airplane configuration |
| CN103171766A (en) * | 2011-12-20 | 2013-06-26 | 北京航空航天大学 | Short distance rising and landing unmanned all-wing aircraft |
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