CN110254720A - A kind of Flying-wing's solar energy unmanned plane - Google Patents
A kind of Flying-wing's solar energy unmanned plane Download PDFInfo
- Publication number
- CN110254720A CN110254720A CN201910471292.XA CN201910471292A CN110254720A CN 110254720 A CN110254720 A CN 110254720A CN 201910471292 A CN201910471292 A CN 201910471292A CN 110254720 A CN110254720 A CN 110254720A
- Authority
- CN
- China
- Prior art keywords
- wing
- flying
- unmanned plane
- vertical fin
- solar energy
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000005484 gravity Effects 0.000 claims description 5
- 230000005611 electricity Effects 0.000 claims 1
- 238000010276 construction Methods 0.000 abstract description 5
- 238000000034 method Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 239000000654 additive Substances 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000002386 leaching Methods 0.000 description 1
- 230000006855 networking Effects 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
Classifications
-
- 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
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
-
- B64D27/353—
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/02—Power-plant nacelles, fairings, or cowlings associated with wings
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
Abstract
The invention discloses a kind of Flying-wing's solar energy unmanned planes, comprising: wing, vertical fin, power gondola, non-retractable formula undercarriage, control surface and solar battery array；Wherein, control surface, comprising: aileron, rudder and flying tail；Vertical fin uses trapezoidal shape, is arranged in wing two sides wingtip；Flying tail uses rectangular profile, is arranged in segment trailer in wing；Aileron is arranged in trailing edge；Rudder is arranged in vertical fin rear；Power gondola is hung below wing；Solar battery array is laid on upper surface of the airfoil；Non-retractable formula undercarriage is arranged in below complete machine.The present invention can reduce the scale of unmanned plane by high pneumatic lift resistance ratio and light construction weight, enhance the wind loading rating of unmanned plane by high flying speed.
Description
Technical field
The invention belongs to unmanned plane overall design technique field more particularly to a kind of Flying-wing's solar energy unmanned planes.
Background technique
Solar energy unmanned plane is the Electric aircraft using solar radiation as the energy, is Aeronautics and new energy technology
The product combined.The solar energy unmanned plane cruise time is long, flying height is high, overlay area is wide, use cost is low, to environment without
Pollution, the multiple-tasks such as communication relay, electronic reconnaissance, mobile networking can be executed, be orbiter, unmanned plane powered by conventional energy,
The important supplement of the flying platforms such as high altitude airship, by extensive concern both domestic and external.
Domestic and international existing solar energy unmanned plane mostly uses greatly the normal arrangement of " wing+fuselage+empennage ", with Britain
" Zephyr " series of QinetiQ company, " Solara " of Google company, the U.S. are representative.Normal arrangement solar energy unmanned plane
Have the disadvantage that (1) lift coefficient is big, the flying speed under the conditions of the same wing carries is low, and leading to unmanned plane, wind resistance is weak；
(2) what fuselage increased full machine soaks area, and full machine lift resistance ratio is caused to reduce；(3) fuselage increases the construction weight of full machine, from
The longer-distance empennage of wing increases the cable weight of full machine, and unmanned plane scale is caused to become larger.
Summary of the invention
Technology of the invention solves the problems, such as: a kind of Flying-wing's solar energy unmanned plane is overcome the deficiencies of the prior art and provide,
The scale that unmanned plane can be reduced by high pneumatic lift resistance ratio and light construction weight, enhances unmanned plane by high flying speed
Wind loading rating.
In order to solve the above-mentioned technical problem, the invention discloses a kind of Flying-wing's solar energy unmanned planes, comprising: wing,
Vertical fin, power gondola, non-retractable formula undercarriage, control surface and solar battery array；Wherein, control surface, comprising: aileron, direction
Rudder and flying tail；
Vertical fin uses trapezoidal shape, is arranged in wing two sides wingtip；
Flying tail uses rectangular profile, is arranged in segment trailer in wing；
Aileron is arranged in trailing edge；
Rudder is arranged in vertical fin rear；
Power gondola is hung below wing；
Solar battery array is laid on upper surface of the airfoil；
Non-retractable formula undercarriage is arranged in below complete machine.
In above-mentioned Flying-wing's solar energy unmanned plane, wing, comprising: intermediate wing panel and be symmetricly set on the intermediate wing
The left outside wing panel and starboard outboard section of the section left and right sides；
The flat shape of left outside wing panel, intermediate wing panel and starboard outboard section is trapezoidal；
Flying tail is arranged in intermediate wing panel tail portion.
In above-mentioned Flying-wing's solar energy unmanned plane,
Wing uses high aspect ratio low sweep angle aerodynamic arrangement；Wherein, intermediate wing panel is using conventional airfoil with high ratio of lift over drag；It is left
Outer panel and starboard outboard section use recurvation aerofoil profile；
In above-mentioned Flying-wing's solar energy unmanned plane, power gondola shares four groups；Wherein, two groups of power gondolas are hung on
Below left outside wing panel, another two groups of power gondolas are hung below starboard outboard section, and, it is hung on two below left outside wing panel groups of power and hangs
Cabin is symmetrical about intermediate wing panel middle line with two groups of power gondolas being hung below starboard outboard section.
In above-mentioned Flying-wing's solar energy unmanned plane, further includes: four groups of propellers；Wherein, four groups of propellers are pacified respectively
Mounted in the front of four groups of power gondolas.
In above-mentioned Flying-wing's solar energy unmanned plane, motor and battery, power gondola are installed inside power gondola
Entirety, with the full machine center of gravity of trim, made full machine longitudinal direction static-stability before the leading edge of a wing.
In above-mentioned Flying-wing's solar energy unmanned plane, 30% or more of battery weight Zhan Quanji gross weight.
In above-mentioned Flying-wing's solar energy unmanned plane, airborne equipment is installed inside wing.
In above-mentioned Flying-wing's solar energy unmanned plane, non-retractable formula undercarriage uses preceding two o'clock and rear two point form cloth
Office；Wherein, preceding two o'clock is two main wheels, is partly embedded in two groups of insides power gondola lower part respectively；Two o'clock is two tail wheels afterwards, respectively
Partly it is embedded in the two vertical fin lower parts in left and right.
In above-mentioned Flying-wing's solar energy unmanned plane,
Vertical fin includes symmetrically arranged left vertical fin and right vertical fin, and left vertical fin and right vertical fin are separately positioned on left outside wing panel wingtip
With starboard outboard section wingtip；
Aileron includes symmetrically arranged port aileron and starboard aileron, and port aileron and starboard aileron are separately positioned on left outside wing panel rear
With starboard outboard section rear；
Rudder includes symmetrically arranged left direction rudder and right direction rudder, and left direction rudder and right direction rudder are separately positioned on a left side
Vertical fin rear and right vertical fin rear.
The invention has the following advantages that
(1) Flying-wing's solar energy unmanned plane lift resistance ratio of the invention is high.Flying-wing's shape is clean, and additives is few, leaching
Wetted surface is small, and zero lift drag is small, can be high with lift resistance ratio.
(2) Flying-wing's solar energy unmanned plane lightweight construction of the invention.On the one hand it due to eliminating fuselage, can save
Construction weight can reduce wing on the other hand as eliminating lumped mass caused by fuselage and empennage to a certain extent
Weight.
(3) Flying-wing's solar energy unmanned plane wind loading rating of the invention is strong.Since cruise lift coefficient is small, cruising speed
Increase, the wind loading rating in flight course is strong.
(4) Flying-wing's solar energy unmanned plane propulsive efficiency of the invention is high.Since cruise lift coefficient is small, cruising speed
Increase, 30% or so can be higher by through entry evaluation Reynolds number, so that propeller design difficulty reduces, propulsion system is comprehensive
It can improve.
Detailed description of the invention
Fig. 1 is a kind of overall effect figure of Flying-wing's solar energy unmanned plane in the embodiment of the present invention；
Fig. 2 is a kind of top view of Flying-wing's solar energy unmanned plane in the embodiment of the present invention；
Fig. 3 is a kind of main view of Flying-wing's solar energy unmanned plane in the embodiment of the present invention；
Fig. 4 is a kind of side view of Flying-wing's solar energy unmanned plane in the embodiment of the present invention；
Wherein: 1- wing, 2- vertical fin, 3- power gondola, the non-retractable formula undercarriage of 4-, 5- solar battery array, 6- aileron,
7- rudder, 8- flying tail, the left outside wing panel of 101-, the centre 102- wing panel, 103- starboard outboard section, the left vertical fin of 201-, 202- are right
Vertical fin, 301- power gondola I, 302- power gondola II, 303- power gondola III, 304- power gondola IV, 401- main wheel I,
402- main wheel II, 403- tail wheel I, 404- tail wheel II, 601- port aileron, 602- starboard aileron, 701- left direction rudder, 702- right direction
Rudder, 801- propeller I, 802- propeller II, 803- propeller III, 804- propeller IV.
Specific embodiment
To make the object, technical solutions and advantages of the present invention clearer, below in conjunction with attached drawing to disclosed by the invention
Embodiment is described in further detail.
Such as Fig. 1~4, in the present embodiment, Flying-wing's solar energy unmanned plane, comprising: wing 1, vertical fin 2, power are hung
Cabin 3, non-retractable formula undercarriage 4, control surface and solar battery array 5, wherein, control surface can specifically include: aileron 6, direction
Rudder 7 and flying tail 8.Wherein, vertical fin 2 uses trapezoidal shape, is arranged in 1 two sides wingtip of wing；Flying tail 8 is using outside rectangle
Shape is arranged in segment trailer in wing 1；Aileron 6 is arranged in 1 rear of wing；Rudder 7 is arranged in 2 rear of vertical fin；Power gondola 3
It is hung on 1 lower section of wing；Solar battery array 5 is laid on 1 upper surface of wing；Non-retractable formula undercarriage 4 is arranged in below complete machine.
Preferably, wing 1 can specifically include: intermediate wing panel 102 and be symmetricly set at left and right sides of intermediate wing panel
Left outside wing panel 101 and starboard outboard section 103.Wherein, left outside wing panel 101, the planar shaped of intermediate wing panel 102 and starboard outboard section 103
Shape is trapezoidal；Flying tail 8 is arranged in intermediate 102 tail portion of wing panel.
Preferably, wing 1 uses high aspect ratio low sweep angle aerodynamic arrangement.Wherein, intermediate wing panel 102 is using conventional promotion
Aerofoil profile is compared in resistance；Left outside wing panel 101 and starboard outboard section 103 use recurvation aerofoil profile.
Preferably, power gondola 3 shares four groups of (e.g., power gondolas I 301 shown in Fig. 2, power gondola II 302, dynamic
Power gondola III 303 and power gondola IV are 304).Wherein, two groups of power gondola (power gondola I 301, power gondola II 302) hangings
In left outside 101 lower section of wing panel, another two groups of power gondolas (power gondola III 303 and power gondola IV 304) are hung on starboard outboard section
103 lower sections, and, two groups of power gondolas for being hung on left outside 101 lower section of wing panel are hung with two groups of power for being hung on 103 lower section of starboard outboard section
Cabin is symmetrical about intermediate wing panel middle line.Further, which can also include: four groups of propellers
(e.g., propeller I 801 shown in Fig. 2, propeller II 802, propeller III 803 and propeller IV be 804).Wherein, four groups of spirals
Paddle is separately mounted to the front of four groups of power gondolas.
Preferably, non-retractable formula undercarriage 4 is laid out using preceding two o'clock and rear two point form.Wherein, preceding two o'clock is two masters
(e.g., 402) main wheel I 401 and main wheel II shown in Fig. 4, are partly embedded in two groups of inside power gondola (power gondolas II to wheel respectively
302, the 303) lower part of power gondola III；Two o'clock is that (e.g., 404) tail wheel I 403 and tail wheel II shown in Fig. 4, divide two tail wheels afterwards
It is not embedded in the two vertical fin lower parts in left and right partly.
Preferably, vertical fin 2 includes symmetrically arranged left vertical fin 201 and right vertical fin 202, and left vertical fin 201 and right vertical fin 202 divide
It She Zhi not be in left outside 101 wingtip of wing panel and 103 wingtip of starboard outboard section.Aileron 6 includes symmetrically arranged port aileron 601 and starboard aileron
602, port aileron 601 and starboard aileron 602 are separately positioned on left outside 101 rear of wing panel and 103 rear of starboard outboard section.Rudder 7 wraps
Symmetrically arranged left direction rudder 701 and right direction rudder 702 are included, left direction rudder 701 and right direction rudder 702 are separately positioned on left vertical fin
202 rear of 201 rears and right vertical fin.
Preferably, motor and battery are installed inside power gondola 3, power gondola is whole before the leading edge of a wing, with
The full machine center of gravity of trim, makes full machine longitudinal direction static-stability.Wherein, 30% or more of battery weight Zhan Quanji gross weight.
Preferably, airborne equipment is installed inside wing 1.
From upper description:
Wing: as the prevailing lift face of unmanned plane, using high aspect ratio low sweep angle aerodynamic arrangement, wherein great Zhan string
Full machine lift resistance ratio can be improved than aerodynamic arrangement, reduce the energy consumption in flight course；Low sweep angle aerodynamic arrangement can increase
Big control surface control arm, and make full machine retrofocus, by the preposition installation of the lumped masses such as battery, by gravity allocation focus
Before, make full machine longitudinal direction static-stability.Further, intermediate wing panel uses recurvation using conventional airfoil with high ratio of lift over drag, left/right outer panel
Aerofoil profile, to improve full machine lift coefficient, and by longitudinal moment trim.
Flying tail: it using dynamic form entirely, on the one hand provides part longitudinal trim torque, on the other hand does pitch control
Face reduces the coupling of horizontal course and nonlinear problem when longitudinal attitude control.
Vertical fin: as unmanned plane fixed fin and also serve as winglet, on the one hand make full machine course static-stability, it is another
Aspect improves full machine lift resistance ratio.
Power gondola: as the filling structure of unmanned plane dynamical system, sharing four groups, and extension is hung under wing respectively
Side, inside are equipped with motor and battery, and front is equipped with propeller.30% or more of battery weight Zhan Quanji gross weight moves
Power gondola is whole before the leading edge of a wing, with the full machine center of gravity of trim.
Control surface: as the control surface of unmanned plane, including being located at the aileron of outer panel rear and positioned at the side of vertical fin rear
To rudder, the horizontal directional control to full machine, each two panels of aileron and rudder left and right, to improve the remaining of control surface are realized.
Non-retractable formula undercarriage: for non-retractable formula structure, main wheel is located at below the power gondola of inside, and tail wheel, which is located at, to hang down
Below tail.
Various embodiments are described in a progressive manner in this explanation, the highlights of each of the examples are with its
The difference of his embodiment, the same or similar parts between the embodiments can be referred to each other.
The above, optimal specific embodiment only of the invention, but scope of protection of the present invention is not limited thereto,
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by anyone skilled in the art,
It should be covered by the protection scope of the present invention.
The content that description in the present invention is not described in detail belongs to the well-known technique of professional and technical personnel in the field.
Claims (10)
1. a kind of Flying-wing's solar energy unmanned plane characterized by comprising wing, vertical fin, power gondola, non-retractable formula
Undercarriage, control surface and solar battery array；Wherein, control surface, comprising: aileron, rudder and flying tail；
Vertical fin uses trapezoidal shape, is arranged in wing two sides wingtip；
Flying tail uses rectangular profile, is arranged in segment trailer in wing；
Aileron is arranged in trailing edge；
Rudder is arranged in vertical fin rear；
Power gondola is hung below wing；
Solar battery array is laid on upper surface of the airfoil；
Non-retractable formula undercarriage is arranged in below complete machine.
2. Flying-wing's solar energy unmanned plane according to claim 1, which is characterized in that wing, comprising: intermediate wing panel,
And it is symmetricly set on left outside wing panel and starboard outboard section at left and right sides of intermediate wing panel；
The flat shape of left outside wing panel, intermediate wing panel and starboard outboard section is trapezoidal；
Flying tail is arranged in intermediate wing panel tail portion.
3. Flying-wing's solar energy unmanned plane according to claim 2, which is characterized in that
Wing uses high aspect ratio low sweep angle aerodynamic arrangement；Wherein, intermediate wing panel is using conventional airfoil with high ratio of lift over drag；The left outside wing
Section and starboard outboard section use recurvation aerofoil profile.
4. Flying-wing's solar energy unmanned plane according to claim 2, which is characterized in that power gondola shares four groups；Its
In, two groups of power gondolas are hung below left outside wing panel, and another two groups of power gondolas are hung below starboard outboard section, and, it is hung on a left side
Two groups of power gondolas below outer panel and two groups of power gondolas being hung below starboard outboard section are symmetrical about intermediate wing panel middle line.
5. Flying-wing's solar energy unmanned plane according to claim 4, which is characterized in that further include: four groups of propellers；Its
In, four groups of propellers are separately mounted to the front of four groups of power gondolas.
6. Flying-wing's solar energy unmanned plane according to claim 1, which is characterized in that be equipped with electricity inside power gondola
Machine and battery, power gondola is whole before the leading edge of a wing, with the full machine center of gravity of trim, makes full machine longitudinal direction static-stability.
7. Flying-wing's solar energy unmanned plane according to claim 6, which is characterized in that battery weight Zhan Quanji gross weight
30% or more.
8. Flying-wing's solar energy unmanned plane according to claim 1, which is characterized in that be equipped with airborne set inside wing
It is standby.
9. Flying-wing's solar energy unmanned plane according to claim 3, which is characterized in that non-retractable formula undercarriage uses
Preceding two o'clock and rear two point form layout；Wherein, preceding two o'clock is two main wheels, is partly embedded in two groups of insides power gondola lower part respectively；Afterwards
Two o'clock is two tail wheels, is partly embedded in the two vertical fin lower parts in left and right respectively.
10. Flying-wing's solar energy unmanned plane according to claim 2, which is characterized in that
Vertical fin includes symmetrically arranged left vertical fin and right vertical fin, and left vertical fin and right vertical fin are separately positioned on left outside wing panel wingtip and the right side
Outer panel wingtip；
Aileron includes symmetrically arranged port aileron and starboard aileron, and port aileron and starboard aileron are separately positioned on left outside wing panel rear and the right side
Outer panel rear；
Rudder includes symmetrically arranged left direction rudder and right direction rudder, and left direction rudder and right direction rudder are separately positioned on left vertical fin
Rear and right vertical fin rear.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910471292.XA CN110254720A (en) | 2019-05-31 | 2019-05-31 | A kind of Flying-wing's solar energy unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910471292.XA CN110254720A (en) | 2019-05-31 | 2019-05-31 | A kind of Flying-wing's solar energy unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110254720A true CN110254720A (en) | 2019-09-20 |
Family
ID=67916299
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910471292.XA Pending CN110254720A (en) | 2019-05-31 | 2019-05-31 | A kind of Flying-wing's solar energy unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110254720A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110576965A (en) * | 2019-09-23 | 2019-12-17 | 西北工业大学 | Unmanned aerial vehicle layout with least control surface configuration and control method thereof |
| CN110816806A (en) * | 2019-10-28 | 2020-02-21 | 西北工业大学 | Cluster type bionic solar unmanned aerial vehicle |
| CN110979635A (en) * | 2019-12-25 | 2020-04-10 | 西北工业大学 | Winged unmanned aerial vehicle with wingtip winglet provided with vertical control surface |
| CN112776979A (en) * | 2021-04-02 | 2021-05-11 | 中国航天空气动力技术研究院 | Detachable auxiliary support structure and method for solar unmanned aerial vehicle |
| CN113665838A (en) * | 2021-10-21 | 2021-11-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Full-motion horizontal tail layout optimization method and device for widening gravity center envelope of helicopter |
| CN113682471A (en) * | 2021-10-26 | 2021-11-23 | 中国航天空气动力技术研究院 | Rotor solar energy unmanned aerial vehicle verts |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104890859A (en) * | 2015-06-23 | 2015-09-09 | 中国航空工业集团公司西安飞机设计研究所 | Solar drone |
| CN204846384U (en) * | 2015-07-13 | 2015-12-09 | 北京汉能创昱科技有限公司 | Solar drive unmanned aerial vehicle |
| CN105416587A (en) * | 2015-12-02 | 2016-03-23 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Aerodynamic layout of aircraft with blended wing body |
| CN106218887A (en) * | 2016-08-22 | 2016-12-14 | 杭州迅蚁网络科技有限公司 | A kind of vertically taking off and landing flyer of distributed-power device layout |
| CN106628115A (en) * | 2016-11-25 | 2017-05-10 | 烟台南山学院 | Four-duct flying-wing type unmanned aerial vehicle |
| CN107512394A (en) * | 2017-08-28 | 2017-12-26 | 郗杰 | A kind of tail sitting posture VUAV and flight control method |
| CN207931972U (en) * | 2018-02-11 | 2018-10-02 | 中国航天空气动力技术研究院 | A kind of solar energy unmanned plane |
| CN109703758A (en) * | 2019-01-14 | 2019-05-03 | 北京空天技术研究所 | Two-way all-wing aircraft flight vehicle aerodynamic shape and design method |
| CN210284611U (en) * | 2019-05-31 | 2020-04-10 | 中国航天空气动力技术研究院 | Flying wing layout solar unmanned aerial vehicle |
-
2019
- 2019-05-31 CN CN201910471292.XA patent/CN110254720A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104890859A (en) * | 2015-06-23 | 2015-09-09 | 中国航空工业集团公司西安飞机设计研究所 | Solar drone |
| CN204846384U (en) * | 2015-07-13 | 2015-12-09 | 北京汉能创昱科技有限公司 | Solar drive unmanned aerial vehicle |
| CN105416587A (en) * | 2015-12-02 | 2016-03-23 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Aerodynamic layout of aircraft with blended wing body |
| CN106218887A (en) * | 2016-08-22 | 2016-12-14 | 杭州迅蚁网络科技有限公司 | A kind of vertically taking off and landing flyer of distributed-power device layout |
| CN106628115A (en) * | 2016-11-25 | 2017-05-10 | 烟台南山学院 | Four-duct flying-wing type unmanned aerial vehicle |
| CN107512394A (en) * | 2017-08-28 | 2017-12-26 | 郗杰 | A kind of tail sitting posture VUAV and flight control method |
| CN207931972U (en) * | 2018-02-11 | 2018-10-02 | 中国航天空气动力技术研究院 | A kind of solar energy unmanned plane |
| CN109703758A (en) * | 2019-01-14 | 2019-05-03 | 北京空天技术研究所 | Two-way all-wing aircraft flight vehicle aerodynamic shape and design method |
| CN210284611U (en) * | 2019-05-31 | 2020-04-10 | 中国航天空气动力技术研究院 | Flying wing layout solar unmanned aerial vehicle |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110576965A (en) * | 2019-09-23 | 2019-12-17 | 西北工业大学 | Unmanned aerial vehicle layout with least control surface configuration and control method thereof |
| CN110816806A (en) * | 2019-10-28 | 2020-02-21 | 西北工业大学 | Cluster type bionic solar unmanned aerial vehicle |
| CN110979635A (en) * | 2019-12-25 | 2020-04-10 | 西北工业大学 | Winged unmanned aerial vehicle with wingtip winglet provided with vertical control surface |
| CN112776979A (en) * | 2021-04-02 | 2021-05-11 | 中国航天空气动力技术研究院 | Detachable auxiliary support structure and method for solar unmanned aerial vehicle |
| CN112776979B (en) * | 2021-04-02 | 2021-08-10 | 中国航天空气动力技术研究院 | Detachable auxiliary support structure and method for solar unmanned aerial vehicle |
| CN113665838A (en) * | 2021-10-21 | 2021-11-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Full-motion horizontal tail layout optimization method and device for widening gravity center envelope of helicopter |
| CN113665838B (en) * | 2021-10-21 | 2021-12-21 | 中国空气动力研究与发展中心低速空气动力研究所 | Full-motion horizontal tail layout optimization method and device for widening gravity center envelope of helicopter |
| CN113682471A (en) * | 2021-10-26 | 2021-11-23 | 中国航天空气动力技术研究院 | Rotor solar energy unmanned aerial vehicle verts |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110254720A (en) | A kind of Flying-wing's solar energy unmanned plane | |
| CN107176286B (en) | Double-duct fan power system-based foldable fixed wing vertical take-off and landing unmanned aerial vehicle | |
| CN104890859B (en) | A kind of solar energy unmanned plane | |
| CN103552682B (en) | A kind of all-wing aircraft and buzzard-type wing connection wing airplane | |
| CN106184737B (en) | Combined type is laid out vertically taking off and landing flyer and VTOL flying method | |
| CN204846384U (en) | Solar drive unmanned aerial vehicle | |
| CN103496305A (en) | Hovercar | |
| CN108128453A (en) | A kind of air-sea dual-purpose solar unmanned plane and its control method | |
| CN102730183A (en) | Novel solar airplane | |
| CN108557081A (en) | A kind of solar united wing unmanned plane and its control method | |
| CN109774916B (en) | Solar aircraft adopting three-dimensional layout design | |
| CN207208447U (en) | Folding fixed-wing vertical take-off and landing unmanned aerial vehicle based on double ducted fan dynamical systems | |
| CN208053611U (en) | Efficient electric gliding unmanned plane | |
| CN105270620A (en) | Integrated general-purpose vertical take-off and landing aircraft based on lifting and floating force | |
| CN110816806B (en) | Cluster type bionic solar unmanned aerial vehicle | |
| CN207931972U (en) | A kind of solar energy unmanned plane | |
| CN113371175A (en) | Fixed wing scouting and hitting integrated unmanned aerial vehicle model and design method thereof | |
| CN206068150U (en) | Combined type layout vertically taking off and landing flyer | |
| CN103287569B (en) | Lifting-pushing type large-scale solar-powered unmanned aerial vehicle capable of taking off and landing in non-runway field and hovering | |
| CN210284611U (en) | Flying wing layout solar unmanned aerial vehicle | |
| CN205738056U (en) | A kind of aerodynamic arrangement of the big aircraft of strategy | |
| CN205602117U (en) | Novel high lift VTOL aircraft | |
| CN211364907U (en) | Pneumatic overall arrangement of low-speed unmanned aerial vehicle | |
| CN204871605U (en) | Gyroplane can vert | |
| CN112644686A (en) | Tandem wing overall arrangement solar energy unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |