CN106516074A - Deformable lift and buoyancy integrated aircraft aerodynamic configuration - Google Patents
Deformable lift and buoyancy integrated aircraft aerodynamic configuration Download PDFInfo
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- CN106516074A CN106516074A CN201610925534.4A CN201610925534A CN106516074A CN 106516074 A CN106516074 A CN 106516074A CN 201610925534 A CN201610925534 A CN 201610925534A CN 106516074 A CN106516074 A CN 106516074A
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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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
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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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/064—Stringers; Longerons
-
- 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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/065—Spars
-
- 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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Aviation & Aerospace Engineering (AREA)
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Abstract
Belonging to the technical field of aircraft design, the invention discloses a deformable lift and buoyancy integrated aircraft aerodynamic configuration. The aerodynamic configuration has a single-fuselage, tandem wing and horizontal tail-free layout, double vertical tails tilt outward certain angle, wings are located at the upper part of the fuselage, front wings and back wings have the same design. The fuselage can produce radial deformation, the fuselage is divided into a front section, a middle section and a back section, and the three sections of the fuselage deform respectively. Because of the introduction of dynamic lift, the aircraft has higher flight height than an airship, greater flight speed, and stronger wind resistant performance and maneuverability; and due to the introduction of static lift, the aircraft has loading capacity far higher than that of conventional high-altitude unmanned aerial vehicles, and has higher structural height and strength. In the process of vertical rising and fall, the fuselage can produce corresponding deformation to change the fuselage volume so as to guarantee the fuselage lift and the aircraft weight balance. With no need for ballonet and ancillary equipment in conventional airships and lift and buoyancy integrated aircrafts, the deformable lift and buoyancy integrated aircraft aerodynamic configuration provided by the invention can reduce the aircraft weight and decrease the ground parking volume of the aircraft.
Description
Technical field
The invention belongs to Aircraft Design technical field, is related to a kind of floating one flight vehicle aerodynamic profile of deformable liter,
Specifically refer to a kind of comprehensive utilization dynamic lift and uplift and fuselage can self adaptation deformation flight vehicle aerodynamic profile.
Background technology
Close to space vehicle platform is with a wide range of applications, for this HAE aircraft platforms, high-altitude
The floating one aircraft of dirigible, solar powered aircraft and liter is to study more direction at present.But this several aircraft also has which obvious
Shortcoming：The volume of HAA is excessively huge, and flying speed is low, and mobility is poor, and wind resistance is poor, transport, storage and maintenance
Cost is very high., due to being limited by solar power, the weight of aircraft must be very light, greatly limit which and takes for solar powered aircraft
Ability with load, and housing construction has to sacrifice intensity and toughness due to pursuing lightweight, is to pursue high pneumatic efficiency
Adopt high aspect ratio configuration more wing, cause wing flexibility larger, wing deformation is serious during flight, flight safety easily occurs and asks
Topic.Floating one aircraft uplift part being risen at present and mostly being semi-rigid dirigible structure, its profile is immutable, and inside must have huge
Balloonet adjust aircraft weight to store air, bulky is parked on ground, and must have the equipment such as intake and exhaust pump
Balloonet is adjusted, complex structure, impost are big.
To overcome the respective shortcoming of several aircraft of the above, it is necessary to design a kind of load-carrying ability by force, the rigidity of structure is big, gas
The high near space vehicle aerodynamic configuration of efficiency of movement, to meet the demand of Altitude Long Endurance Unmanned Air Vehicle design.
The content of the invention
To solve the deficiency that near space vehicle is present in prior art, the present invention proposes a kind of deformable liter floating
Body flight vehicle aerodynamic profile.The present invention is mainly characterized in that aircraft lift is made up of uplift and dynamic lift two parts, uplift
I.e. buoyancy is produced by fuselage, and dynamic lift is produced by wing, and fuselage can deform with flying height self adaptation, and aerodynamic configuration is unit
Body, the tandem wing, without horizontal tail layout, twin vertical fin flare certain angle, wing are located at back, and wing same design, single in front and back
Wing is high aspect ratio straight wing, and fuselage cross-section is two semielliptical combinations.Fuselage can produce radial deformation, and fuselage is divided into
Before in after three sections, the deformation of three sections of fuselages is carried out respectively, and the deformation of wherein stage casing fuselage is primary deformable.
The floating one flight vehicle aerodynamic profile of deformable liter that the present invention is provided, including fuselage, front wing, rear wing and empennage, institute
The fuselage stated is deformable fuselage, and fuselage interior has deformable rigid backbone, external fuselage film laying material covering.
Described deformable rigid backbone includes that before and after's wing spar, frame deflection truss, fuselage dimension shape frame and fuselage are vertical
Beam, wherein body longeron have two, are connected to 2 points of A, B with front wing spar, are connected to 2 points of C, D with rear wing spar；The machine
The two ends of body longeron reach fuselage head and tail position, support as fuselage longitudinal framework；Described frame deflection truss has
Two, it is connected for 2 points in A, B with front spar respectively, is connected for 2 points in C, D with rear wing spar；Described fuselage ties up the two ends of shape frame
By two rotate it is secondary be connected with two described body longerons, before fuselage in three sections afterwards, each section of fuselage all at least
Individual fuselage ties up shape frame, fuselage tie up shape frame with frame deflection truss identical distressed structure, fuselage dimension shape frame place plane and
Frame deflection truss place plane vertically and body longeron, in fuselage maximum deployed condition, stressed-skin construction profile and design machine
Body contour is consistent.
Described frame deflection truss and fuselage dimension shape frame include that five truss and six rotations are secondary, with frame deflection purlin
Frame is connected on front wing spar as a example by 2 points of A, B, and described frame deflection truss includes the first truss～the 5th truss, described
First truss～the 5th truss structure is circular arc profile, during maximum deployed condition, on frame deflection truss skin shape with
Design fuselage appearance is consistent, and fuselage surface continual curvature, transition junction are smooth；One end of truss and truss is respectively by rotating
Pair is connected to 2 points of A, B, and rotation the second truss of secondary connection, the 3rd truss and the are sequentially passed through between the first truss and the 5th truss
Four truss；Exterior fuselage skin is connected on the first truss～the 5th truss, is together deformed with the first truss～the 5th truss.
The invention has the advantages that：
(1) introducing of dynamic lift makes that the aircraft altitude is higher than dirigible, and flying speed is bigger, wind resistance and motor-driven
Property is higher.
(2) introducing of uplift makes the aircraft load-carrying ability be significantly larger than conventional High Altitude UAV, structure height intensity
It is higher.
(3) as fuselage can produce part uplift, VTOL can be realized using fuselage uplift in low latitude, is reduced
Hovering is realized in requirement of the aircraft to airport, high-level a certain altitude range interior energy, can complete various Fixed Point Operation tasks.
(4) during vertical ascent and decline, fuselage can produce corresponding deformation change body volume and ensure that fuselage is floated
Power is balanced with aircraft weight, it is not necessary to the balloonet and attendant equipment in conventional dirigible and the floating one aircraft of liter, it is possible to decrease
Aircraft weight, reduces aircraft ground and parks volume.
Description of the drawings
Figure 1A～1D is the floating one flight vehicle aerodynamic appearance schematic diagram of deformable liter.
Fig. 2 is that low latitude deforms uphill process middle fuselage radial deformation schematic diagram.
Fig. 3 is full machine structural representation.
Fig. 4 is frame deflection structural representation.
In figure：
1- fuselages；2- front wings；3- rear wings；4- empennages；5- engines；
6- solar cells；7- cross sectional shape A；8- cross sectional shape B；9- cross sectional shape C；10- wing spars；
11- frame deflection truss；12- rotates secondary；13- body longerons；14- fuselages tie up shape frame.
Specific embodiment
The present invention will be described in further detail with reference to the accompanying drawings and examples.
The floating one flight vehicle aerodynamic profile of deformable liter proposed by the present invention, as shown in Figure 1A～1D, the aircraft gas
Dynamic profile includes fuselage 1, front wing 2, rear wing 3 and empennage 4, and described fuselage 1 is 3 groups of deformable fuselage, the front wing 2 and rear wing
Into tandem wing, front wing 2, rear wing 3 are high aspect ratio configuration, respectively positioned at 1 front and rear part of fuselage, as rear wing 3 is located at
In the wake flow of front wing 2, therefore between front wing 2 and rear wing 3, there are 3 °～6 ° differential seat angles, to ensure with higher pneumatic efficiency, institute
State empennage 4 and adopt rudder-vator, positioned at 1 rear portion of fuselage.Advanced using propeller, four engines 5 are respectively placed in before and after's wing or so
Both sides, power by the way of solar cell 6 combines power supply with fuel cell.As shown in Figure 1B～1D, network is represented
Solar cell 6, the solar cell 6 are layed in fuselage 1 and front wing 2,3 upper surface of rear wing.
With reference to Fig. 1, the aircraft that the present invention is provided is unit body, and, using half hard structure, having inside fuselage 1 can for fuselage
Deformation rigid backbone, the outer film laying covering of skeleton, for three sections after in front, such as Figure 1B, leading portion are semielliptical forming head for 1 point of fuselage
Portion, to wait straight section, back segment is afterbody contraction section, and the deformation of three sections of fuselages carried out respectively, and the deformation of wherein stage casing fuselage is in stage casing
Primary deformable.
The flying method of the floating one aircraft of the deformable liter：At ground, the fuselage 1 of aircraft is state of ground machine
Body cross sectional shape A7, volume are minimum, and its uplift and weight are in a basic balance.Low latitude deforms ascent stage, produces by engine 5
Thrust fly before resistance to overcome, and front wing 2 and rear wing 3 produce aerodynamic lift and make aircraft climb, and ambient atmosphere pressure is airtight with big
Degree reduces, and 1 internal pressure of fuselage is more than external pressure, the pressure differential of formation drive the servo-actuated change of deformable rigid backbone without
Additional energy to be paid, the increase of 1 volume self adaptation of fuselage, moment keep gravity and buoyancy of substantially equal, during fuselage cross-section is in
Between state fuselage cross sectional shape B8.When the volume of fuselage 1 increases to maximum, deformation terminates, section when fuselage 1 is to expand completely
Shape C9, aircraft reach maximum hovering height, and the body volume of aircraft no longer changes.If aircraft also needs further to climb
Rising, then promoting that enough flying speeds are produced by engine 5, front wing 2 and rear wing 3 produce aerodynamic lift, dynamic lift and buoyancy
With joint efforts more than aircraft gravity, aircraft continues to climb and eventually arrives at predetermined cruising altitude.Decline stage is substantially dynamic
Lift climb and the inverse process of deformation ascent stage.Aircraft whole energy is provided by solar cell 6, and solar cell 6 exists
Daytime directly provides energy, and electrolysis water with airborne equipment and payload for engine 5, is fuel cell storage energy.
Night energy is provided by fuel cell completely.
The specific embodiment of the deformable rigid backbone of fuselage interior is illustrated with reference to Fig. 2, Fig. 3 and Fig. 4：Such as Fig. 3, fuselage
Internal deformable rigid backbone includes before and after's wing spar 10, frame deflection truss 11, fuselage dimension shape frame 14 and body longeron
13.Wherein body longeron 13 has two, is connected to 2 points of A, B with front wing spar 10, is connected to 2 points of C, D with rear wing spar 10,
And support as fuselage longitudinal framework.Described frame deflection truss 11 has two, is connected with front and back wing spar 10 respectively.
Described frame deflection truss 11 is reinforcement structure, and for realizing frame deflection, the two ends of fuselage dimension shape frame 14 are turned by two
It is dynamic it is secondary be connected with two described body longerons 13, during layout is before fuselage respectively after three sections, fuselage dimension shape frame 14 has and machine
Body deforms 11 identical distressed structure of truss, and 14 place plane of fuselage dimension shape frame and 11 place plane of frame deflection truss are vertical
With body longeron, fuselage maximum deployed condition, it is ensured that outer skin construction profile with design fuselage appearance it is consistent.Due to fuselage
Distressed structure space scale is very big, in order to meet the requirement of deformation stability, takes into account reduction quality, using plane bar structure structure
Into frame deflection truss 11 and fuselage dimension shape frame 14.By taking frame deflection truss 11 as an example, 11 points described of frame deflection truss is
The truss structure of five parts：First truss H1～the 5th truss H5, five truss structures are circular arc profile.Such as Fig. 4, the
One truss H1 and the 5th H5 is connected with wing spar 10 by rotating secondary 12, between the first truss H1 and the second truss H2, second
Between truss H2 and the 3rd truss H3, between the 3rd truss H3 and the 4th truss H4, between the 4th truss H4 and the 5th truss H5
Secondary 12 are rotated by one respectively to connect.Exterior fuselage skin adopts thin-film material, is layed on frame deflection truss 11, with first
Truss H1～the 5th truss H5 together deforms, then the deformable outer surface of waist is divided into five pieces, and each block is relatively independent, each
Block itself does not deform, and shape is relatively fixed with curvature, so as to ensure to be not in big buckling phenomena in deformation process,
And reach be badly deformed when, it is ensured that fuselage surface continual curvature, transition junction are smooth.Frame deflection truss 11
The driving force of the shape that changes need not pay additional energy from fuselage skin external and internal pressure difference.When deforming complete, secondary 12 are rotated
Locking, to meet the requirement on load.
When aircraft docks at ground, fuselage is cross sectional shape A7, as shown in Fig. 2 now the first truss H1 and the 5th purlin
Frame H5 is opened to fuselage both sides, and the 3rd truss H3 moves to uppermost position in fig-ure, now between the 4th truss H3 and wing spar 10
Distance is minimum；Second truss H2 and the 4th truss H4 is in inboard, and each rotates secondary 12 locked, and now body volume is most
Little, lateral dimension is minimum.In aircraft deformation uphill process, fuselage is cross sectional shape B8, and fuselage skin is inside and outside to produce pressure difference,
Promote frame deflection truss 11 and fuselage dimension shape frame 14 to deform, now rotate secondary 12 unblock, the first truss H1 and the 5th purlin
Frame H5 is rotated and is opened to fuselage both sides around rotating secondary 12, and the 3rd truss H3 is translated downwards, the second truss H2 and the 4th truss H4
Rotate down around rotating secondary 12, pass through sub-controlling unit in deformation process, it is ensured that aircraft is symmetrical, with the liter of height
Height, aircraft fuselage volume gradually increase.When aircraft fuselage volume increases to maximum rating, fuselage is cross sectional shape C9,
3rd truss H3 moves to extreme lower position, and each rotates secondary 12 locked, the first truss H1 and the second truss H2, the second truss H2 and
3rd truss H3, between the 3rd truss H3 and the 4th truss H4, the 4th truss H4 and the 5th truss H5, ensure tangent, exterior skin mistake
Cross smooth.
Embodiment：
Rise the maximum hovering height h=15km, maximum volume V=140000m of floating one Flight Vehicle Design3, fuselage largest body
Ratio K=6.3 of product and minimum volume.
The chord length of each truss is calculated by the geometrical relationship between deformation truss：If two rotations on wing spar 10
The distance between secondary 12 is a, and the first truss H1 and the 5th truss H5 chord lengths are 1.11a, the 3rd truss H3 and the 4th truss H4 strings
A length of 0.94a, the 3rd truss H3 chord lengths are 0.85a.If the first truss H1 is θ with the angle of vertical direction, aircraft is on ground
θ=28.4 ° when parking, in aircraft deformation uphill process, when flying height is 11km, θ reaches 51.6 ° of maximum, now
Truss H2, H3 and H4 are in horizontal level, and when flying height reaches maximum hovering height 15km, θ=30.4 ° have deformed
Into.
Claims (5)
1. a kind of deformable liter floats one flight vehicle aerodynamic profile, including fuselage, front wing, rear wing and empennage, it is characterised in that：
Described fuselage is deformable fuselage, and fuselage interior has deformable rigid backbone, external fuselage film laying material covering；Institute
The deformable rigid backbone stated includes before and after's wing spar, frame deflection truss, fuselage dimension shape frame and body longeron, its middle fuselage
Longeron has two, is connected to 2 points of A, B with front wing spar, is connected to 2 points of C, D with rear wing spar；The two ends of the body longeron
Fuselage head and tail position are reached, is supported as fuselage longitudinal framework；Described frame deflection truss has two, respectively with it is front
Spar is connected for 2 points in C, D with rear wing spar in 2 points of connections of A, B；The two ends of described fuselage dimension shape frame are rotated by two
It is secondary to be connected with two described body longerons, before fuselage in after three sections, each section of fuselage all at least one fuselages tie up shape frame,
Fuselage tie up shape frame with frame deflection truss identical distressed structure, fuselage dimension shape frame place plane and frame deflection truss institute
In plane vertically and body longeron, in fuselage maximum deployed condition, stressed-skin construction profile is consistent with fuselage appearance is designed.
2. a kind of deformable liter according to claim 1 floats one flight vehicle aerodynamic profile, it is characterised in that：Described
Frame deflection truss and fuselage dimension shape frame include that five truss and six rotations are secondary, before being connected to frame deflection truss cautiously
On beam as a example by 2 points of A, B, described frame deflection truss includes the first truss～the 5th truss, described the first truss～5th
Truss structure is circular arc profile, during maximum deployed condition, skin shape and design fuselage appearance one on frame deflection truss
Cause, fuselage surface continual curvature, transition junction are smooth；One end of first truss and the 5th truss is respectively by rotating secondary connection
In A, B, rotation the second truss of secondary connection, the 3rd truss and the 4th purlin between the first truss and the 5th truss, are sequentially passed through at 2 points
Frame；Exterior fuselage skin is connected on the first truss～the 5th truss, is together deformed with the first truss～the 5th truss.
3. a kind of deformable liter according to claim 2 floats one flight vehicle aerodynamic profile, it is characterised in that：Described
The planform of the first truss and the 5th truss and equivalently-sized；The planform and size phase of the second truss and the 4th truss
Together.
4. a kind of deformable liter according to claim 2 floats one flight vehicle aerodynamic profile, it is characterised in that：Aircraft
When docking at ground, fuselage is cross sectional shape A, and now the first truss and the 5th truss are opened to fuselage both sides, and the 3rd truss is put down
Uppermost position in fig-ure is moved to, now the distance between the 3rd truss and wing spar minimum；Second truss and the 4th truss are in fuselage
Inner side, each rotates secondary locked, and now body volume is minimum, and lateral dimension is minimum；In aircraft deformation uphill process, fuselage is
Cross sectional shape B, fuselage skin is inside and outside to produce pressure difference, promotes frame deflection truss and fuselage dimension shape frame to deform, now turns
Dynamic secondary unblock, the first truss and the 5th truss are rotated and are opened to fuselage both sides around pair is rotated, and the 3rd truss is translated downwards, truss
Second is rotated down around pair is rotated with the 4th truss, and aircraft fuselage volume gradually increases；When aircraft fuselage volume is increased to
During maximum rating, fuselage is cross sectional shape C, and the 3rd truss moves to extreme lower position, and each rotates secondary locked, the first truss and the
Two truss, the second truss and the 3rd truss, the 3rd truss and the 4th truss, between the 4th truss and the 5th truss, ensure tangent,
Exterior skin transition is smooth.
5. a kind of deformable liter according to claim 1 floats one flight vehicle aerodynamic profile, it is characterised in that：Described
In aircraft, front wing and rear wing constitute tandem wing, and front wing, rear wing are high aspect ratio configuration, respectively before fuselage
, as rear wing is located in the wake flow of front wing, therefore there are 3 °～6 ° differential seat angles at rear portion between front wing and rear wing, the empennage adopts V
T tail, positioned at fuselage afterbody；Advanced using propeller, four engines are respectively placed in before and after's wing left and right sides, power supply is adopted
Solar cell combines the mode of power supply with fuel cell.
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|---|---|---|---|
| CN201610925534.4A CN106516074B (en) | 2016-10-24 | 2016-10-24 | A kind of floating integrated flight vehicle aerodynamic shape of deformable liter |
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| CN201610925534.4A CN106516074B (en) | 2016-10-24 | 2016-10-24 | A kind of floating integrated flight vehicle aerodynamic shape of deformable liter |
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| CN106516074B CN106516074B (en) | 2019-01-22 |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106892083A (en) * | 2017-04-12 | 2017-06-27 | 北京建中数字科技有限公司 | A kind of bionical frame for intersecting twin-rotor helicopter |
| CN108121855A (en) * | 2017-12-06 | 2018-06-05 | 北京理工大学 | Small-sized unmanned aircraft flight dynamics optimization method based on Bionic flexible wing |
| CN108216679A (en) * | 2017-12-26 | 2018-06-29 | 中国航天空气动力技术研究院 | A kind of solar energy unmanned plane population parameter determines method and system |
| CN111409821A (en) * | 2020-04-26 | 2020-07-14 | 北京航空航天大学合肥创新研究院 | Solar unmanned aerial vehicle with tilting wings |
| CN112158323A (en) * | 2020-10-24 | 2021-01-01 | 西安航空学院 | 3D material increase integration skin structure of unmanned aerial vehicle fuselage-heat dissipation intake duct |
| CN113022846A (en) * | 2021-05-27 | 2021-06-25 | 北京航空航天大学 | Mixed mode aircraft |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106892083A (en) * | 2017-04-12 | 2017-06-27 | 北京建中数字科技有限公司 | A kind of bionical frame for intersecting twin-rotor helicopter |
| CN106892083B (en) * | 2017-04-12 | 2023-11-21 | 北京清航紫荆装备科技有限公司 | Bionic rack of crossed double-rotor helicopter |
| CN108121855A (en) * | 2017-12-06 | 2018-06-05 | 北京理工大学 | Small-sized unmanned aircraft flight dynamics optimization method based on Bionic flexible wing |
| CN108216679A (en) * | 2017-12-26 | 2018-06-29 | 中国航天空气动力技术研究院 | A kind of solar energy unmanned plane population parameter determines method and system |
| CN108216679B (en) * | 2017-12-26 | 2020-03-24 | 中国航天空气动力技术研究院 | Solar unmanned aerial vehicle overall parameter determination method and system |
| CN111409821A (en) * | 2020-04-26 | 2020-07-14 | 北京航空航天大学合肥创新研究院 | Solar unmanned aerial vehicle with tilting wings |
| CN112158323A (en) * | 2020-10-24 | 2021-01-01 | 西安航空学院 | 3D material increase integration skin structure of unmanned aerial vehicle fuselage-heat dissipation intake duct |
| CN113022846A (en) * | 2021-05-27 | 2021-06-25 | 北京航空航天大学 | Mixed mode aircraft |
| CN113022846B (en) * | 2021-05-27 | 2021-08-03 | 北京航空航天大学 | Mixed mode aircraft |
| WO2023124094A1 (en) * | 2021-12-29 | 2023-07-06 | 北京国家新能源汽车技术创新中心有限公司 | Vehicle body structure of transformable low-resistance flying vehicle, and vehicle |
| CN116702331A (en) * | 2023-06-27 | 2023-09-05 | 成都飞机工业（集团）有限责任公司 | Airship comprehensive optimization method based on neural network |
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