CN106516074B - A kind of floating integrated flight vehicle aerodynamic shape of deformable liter - Google Patents
A kind of floating integrated flight vehicle aerodynamic shape of deformable liter Download PDFInfo
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- CN106516074B CN106516074B CN201610925534.4A CN201610925534A CN106516074B CN 106516074 B CN106516074 B CN 106516074B CN 201610925534 A CN201610925534 A CN 201610925534A CN 106516074 B CN106516074 B CN 106516074B
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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
-
- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
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- 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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Abstract
The invention discloses a kind of floating integrated flight vehicle aerodynamic shapes of deformable liter, belong to Aircraft Design technical field.The aerodynamic configuration is single machine body, the tandem wing, without horizontal tail layout, and twin vertical fin flare certain angle, wing is located at back, front and back wing same design；Fuselage can produce radial deformation, fuselage be divided into before in after three sections, the deformation of three sections of fuselages carries out respectively.The introducing of dynamic lift of the present invention keeps the aircraft altitude higher than dirigible, and flying speed is bigger, and wind resistance and mobility are stronger；The introducing of uplift makes the aircraft load-carrying ability be significantly larger than conventional High Altitude UAV, and structure height intensity is higher；During vertical ascent and decline, fuselage can produce corresponding deformation and change body volume guarantee fuselage buoyancy and aircraft weight balance, it does not need conventional dirigible and rises the balloonet and attendant equipment in floating integrated aircraft, aircraft weight can be reduced, reduce aircraft ground and park volume.
Description
Technical field
The invention belongs to Aircraft Design technical fields, are related to a kind of floating integrated flight vehicle aerodynamic shape of deformable liter,
Specifically refer to a kind of flight vehicle aerodynamic shape for comprehensively utilizing dynamic lift and uplift and fuselage can be deformed adaptively.
Background technique
Close to space vehicle platform is with a wide range of applications, for this high altitude long time aircraft platforms, high-altitude
Dirigible, solar powered aircraft and the floating integrated aircraft of liter are to study more direction at present.But these types of aircraft also has it obvious
The shortcomings that: the volume of high altitude airship 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.For solar powered aircraft due to being limited by solar power, the weight of aircraft must be very light, greatly limits it and takes
Ability with load, and housing construction has to sacrifice intensity and toughness due to pursuing light-weight, to pursue high pneumatic efficiency
Wing mostly uses high aspect ratio configuration, causes wing flexibility larger, and wing deformation is serious when flight, is easy to appear flight safety and asks
Topic.Rising floating integrated aircraft uplift component at present is mostly semi-rigid dirigible structure, and shape is immutable, and inside must have huge
Balloonet adjust aircraft weight to store air, bulky is parked on ground, and must have intake and exhaust pump etc. equipment come
Balloonet is adjusted, structure is complicated, and impost is big.
To overcome the disadvantage of above several aircraft respectively, it is necessary to design that a kind of load-carrying ability is strong, and the rigidity of structure is big, gas
The high near space vehicle aerodynamic configuration of efficiency of movement, to meet the needs of Altitude Long Endurance Unmanned Air Vehicle design.
Summary of the invention
To solve deficiency existing near space vehicle in the prior art, the present invention proposes a kind of deformable liter floating one
Body flight vehicle aerodynamic shape.The present invention is mainly characterized in that aircraft lift is made of uplift and dynamic lift two parts, uplift
I.e. buoyancy is generated by fuselage, and dynamic lift is generated by wing, and fuselage can adaptively be deformed with flying height, and aerodynamic configuration is single machine
Body, the tandem wing are laid out without horizontal tail, and twin vertical fin flare certain angle, wing is located at back, front and back wing same design, individually
Wing is high aspect ratio straight wing, and fuselage cross-section is the combination of two semiellipses.Fuselage can produce radial deformation, and fuselage is divided into
Before in after three sections, the deformation of three sections of fuselages carries out respectively, and wherein the deformation of middle section fuselage is primary deformable.
The floating integrated flight vehicle aerodynamic shape of deformable liter provided by the invention, 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.
The deformable rigid backbone includes that front and back wing spar, frame deflection truss, fuselage dimension shape frame and fuselage are vertical
Beam, wherein body longeron has two, is connected to A, B two o'clock with front wing spar, is connected to C, D two o'clock with rear wing spar；The machine
The both ends of body stringer reach fuselage head and tail position, support as fuselage longitudinal framework；The frame deflection truss has
It two, connect with front spar in A, B two o'clock, is connect with rear wing spar in C, D two o'clock respectively；The both ends of the fuselage dimension shape frame
Connect by two revolute pairs with two body longerons, before fuselage in after three sections, each section of fuselage all at least one
A fuselage ties up shape frame, plane where fuselage ties up shape frame there is distressed structure identical with frame deflection truss, fuselage to tie up shape frame and
Plane where frame deflection truss vertically and body longeron, in fuselage maximum unfolded state, stressed-skin construction shape and design machine
Body contour is consistent.
The frame deflection truss and fuselage dimension shape frame include five truss and six revolute pairs, with frame deflection purlin
Frame is connected on front wing spar for A, B two o'clock, and the frame deflection truss includes the first truss~the 5th truss, described
First truss~the 5th truss structure is arc-shaped shape, when maximum unfolded state, on frame deflection truss skin shape with
Design fuselage appearance is consistent, fuselage surface continual curvature, and transition junction is smooth；One end of truss and truss passes through rotation respectively
Pair is connected to A, B two o'clock, and revolute pair is sequentially passed through between the first truss and the 5th truss and connects the second truss, third truss and the
Four truss；Exterior fuselage skin is connected on the first truss~the 5th truss, is deformed together with the first truss~the 5th truss.
The invention has the following advantages:
(1) introducing of dynamic lift keeps the aircraft altitude higher than dirigible, and flying speed is bigger, wind resistance and motor-driven
Property is stronger.
(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) since fuselage can produce part uplift, VTOL can be realized using fuselage uplift in low latitude, reduced
Requirement of the aircraft to airport is able to achieve hovering, achievable various Fixed Point Operation tasks in high-level a certain altitude range.
(4) during vertical ascent and decline, fuselage can produce corresponding deformation change body volume and guarantee that fuselage is floating
Power and aircraft weight balance, and do not need conventional dirigible and rise the balloonet and attendant equipment in floating integrated aircraft, can reduce
Aircraft weight reduces aircraft ground and parks volume.
Detailed description of the invention
Figure 1A~1D is the floating integrated 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 schematic diagram.
Fig. 4 is frame deflection structural schematic diagram.
In figure:
1- fuselage；2- front wing；3- rear wing；4- empennage；5- engine；
6- solar battery；7- cross sectional shape A；8- cross sectional shape B；9- cross sectional shape C；10- wing spar；
11- frame deflection truss；12- revolute pair；13- body longeron；14- fuselage ties up shape frame.
Specific embodiment
The present invention will be described in further detail with reference to the accompanying drawings and examples.
The floating integrated flight vehicle aerodynamic shape of deformable liter proposed by the present invention, as shown in Figure 1A~1D, the aircraft gas
Dynamic shape includes fuselage 1, front wing 2, rear wing 3 and empennage 4, and the fuselage 1 is deformable fuselage, the front wing 2 and 3 groups of rear wing
At tandem wing, front wing 2, rear wing 3 are high aspect ratio configuration, are located at 1 front and rear part of fuselage, since rear wing 3 is located at
There are 3 °~6 ° differential seat angles in the wake flow of front wing 2, therefore between front wing 2 and rear wing 3, to guarantee pneumatic efficiency with higher, institute
Empennage 4 is stated using rudder-vator, is located at 1 rear portion of fuselage.It is promoted using propeller, four engines 5 are respectively placed in front and back wing or so
Two sides, power supply are combined using solar battery 6 with fuel cell by the way of power supply.As shown in Figure 1B~1D, network is indicated
Solar battery 6, the solar battery 6 are layed in fuselage 1 and front wing 2,3 upper surface of rear wing.
In conjunction with Fig. 1, aircraft provided by the invention is single machine body, and fuselage uses half hard structure, and having inside fuselage 1 can
Deform rigid backbone, the outer film laying covering of skeleton, fuselage 1 divides be before in after three sections, such as Figure 1B, leading portion is semielliptical forming head
Portion, middle section are to wait straight sections, and back segment is tail portion contraction section, and the deformation of three sections of fuselages carries out respectively, and the wherein deformation of middle section fuselage is
Primary deformable.
The flying method of the floating integrated aircraft of the deformable liter: at ground, the fuselage 1 of aircraft is state of ground machine
Body cross sectional shape A7, volume is minimum, and uplift and weight are in a basic balance.Low latitude deforms ascent stage, generates by engine 5
Thrust flies before resistance to overcome, and front wing 2 and rear wing 3, which generate aerodynamic lift, makes aircraft climb, ambient atmosphere pressure and big airtight
Degree reduces, and 1 internal pressure of fuselage is greater than external pressure, the pressure difference of formation drive the servo-actuated variation of deformable rigid backbone without
Additional energy is paid, 1 volume of fuselage adaptively increases, and the moment keeps 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 expansion completely
Shape C9, aircraft reach maximum hovering height, and the body volume of aircraft no longer changes.If aircraft also needs further to climb
It rises, is then pushed by engine 5 and generate enough flying speeds, front wing 2 and rear wing 3 generate aerodynamic lift, dynamic lift and buoyancy
Resultant force be greater than aircraft gravity, aircraft, which continues to climb, eventually arrives at scheduled cruising altitude.Decline stage is substantially dynamic
The inverse process of lift climb and deformation ascent stage.Aircraft whole energy is provided by solar battery 6, and solar battery 6 exists
Daytime directly provides energy, and electrolysis water for engine 5 and airborne equipment and payload, stores energy for fuel cell.
Night energy is provided by fuel cell completely.
Illustrate the specific embodiment of the deformable rigid backbone of fuselage interior in conjunction with Fig. 2, Fig. 3 and Fig. 4: such as Fig. 3, fuselage
Internal deformable rigid backbone includes front and back 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 A, B two o'clock with front wing spar 10, is connected to C, D two o'clock with rear wing spar 10,
And it is supported as fuselage longitudinal framework.There are two the frame deflection truss 11, connect respectively with front and back wing spar 10.
The frame deflection truss 11 is reinforcement structure, and for realizing frame deflection, the both ends that fuselage ties up shape frame 14 are turned by two
Dynamic pair connect with two body longerons 13, be laid out before fuselage respectively in three sections afterwards, fuselage, which ties up shape frame 14, to be had and machine
Body deforms the identical distressed structure of truss 11, and fuselage ties up 14 place plane of shape frame and 11 place plane of frame deflection truss is vertical
Guarantee that outer skin construction profile is consistent with design fuselage appearance in fuselage maximum unfolded state with body longeron.Due to fuselage
Distressed structure space scale is very big, in order to meet the requirement of deformation stability, reduction quality is taken into account, using plane bar structure structure
Shape frame 14 is tieed up at frame deflection truss 11 and fuselage.By taking frame deflection truss 11 as an example, the frame deflection truss 11, which divides, is
The truss structure of five parts: the first truss H5 of truss H1~the 5th, five truss structures are arc-shaped shape.Such as Fig. 4,
One truss H1 and the 5th H5 is connect by revolute pair 12 with wing spar 10, between the first truss H1 and the second truss H2, second
Between truss H2 and third truss H3, between third truss H3 and the 4th truss H4, between the 4th truss H4 and the 5th truss H5
It is connected respectively by a revolute pair 12.Exterior fuselage skin uses thin-film material, is layed on frame deflection truss 11, with first
The truss H5 of truss H1~the 5th is deformed together, then the deformable outer surface of waist is divided into five pieces, and each piece relatively independent, each
Block itself does not deform, and shape is relatively fixed with curvature, so that guaranteeing is 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 is sent out
The driving force for the shape that changes is from fuselage skin internal and external pressure difference without paying additional energy.When deforming complete, revolute pair 12
Locking, to meet the requirement on load.
When aircraft docks at ground, fuselage is cross sectional shape A7, as shown in Fig. 2, the first truss H1 and the 5th purlin at this time
Frame H5 is opened to fuselage two sides, and third truss H3 is moved to uppermost position in fig-ure, at this time 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 revolute pair 12 is locked, and body volume is most at this time
Small, lateral dimension is minimum.Aircraft deforms in uphill process, and fuselage is cross sectional shape B8, and fuselage skin is inside and outside to generate pressure difference,
Frame deflection truss 11 and fuselage dimension shape frame 14 is pushed to deform, revolute pair 12 unlocks at this time, the first truss H1 and the 5th purlin
Frame H5 is rotated around revolute pair 12 and is opened to fuselage two sides, and third truss H3 is translated downwards, the second truss H2 and the 4th truss H4
It is rotated down around revolute pair 12, by sub-controlling unit in deformation process, guarantees aircraft bilateral symmetry, with the liter of height
Height, aircraft fuselage volume are gradually increased.When aircraft fuselage volume increases to maximum rating, fuselage is cross sectional shape C9,
Third truss H3 is moved to extreme lower position, and each revolute pair 12 is locked, the first truss H1 and the second truss H2, the second truss H2 and
Guarantee tangent, exterior skin mistake between third truss H3, third truss H3 and the 4th truss H4, the 4th truss H4 and the 5th truss H5
It crosses smooth.
Embodiment:
Rise the floating integrated hovering of Flight Vehicle Design maximum height h=15km, maximum volume V=140000m3, fuselage largest body
Long-pending ratio K=6.3 with minimum volume.
The chord length of each truss is calculated by the geometrical relationship between deformation truss: setting two rotations on wing spar 10
The distance between pair 12 is a, and the first truss H1 and the 5th truss H5 chord length are 1.11a, third truss H3 and the 4th truss H4 string
A length of 0.94a, third truss H3 chord length are 0.85a.If the angle of the first truss H1 and vertical direction is θ, aircraft is on ground
θ=28.4 ° when parking, aircraft deform in uphill process, and when flying height is 11km, θ reaches 51.6 ° of maximum value, at this time
Truss H2, H3 and H4 are in horizontal position, and when flying height reaches maximum hovering height 15km, θ=30.4 ° have been deformed
At.
Claims (4)
1. a kind of floating integrated flight vehicle aerodynamic shape of deformable liter, including fuselage, front wing, rear wing and empennage, it is characterised in that:
The fuselage is deformable fuselage, and fuselage interior has deformable rigid backbone, external fuselage film laying material covering；Institute
The deformable rigid backbone stated includes front and back wing spar, frame deflection truss, fuselage dimension shape frame and body longeron, middle fuselage
Stringer has two, is connected to A, B two o'clock with front wing spar, is connected to C, D two o'clock with rear wing spar；The both ends of the body longeron
Fuselage head and tail position are reached, is supported as fuselage longitudinal framework；There are two the frame deflection truss, respectively with it is preceding
Spar is connected in A, B two o'clock, is connect with rear wing spar in C, D two o'clock；The both ends of the fuselage dimension shape frame pass through two rotations
It is secondary to be connect with two body longerons, before fuselage in after three sections, each section of fuselage all at least one fuselage tie up shape frame,
Fuselage, which ties up shape frame, has distressed structure identical with frame deflection truss, and fuselage ties up shape frame place plane and frame deflection truss institute
Plane vertically and body longeron, in fuselage maximum unfolded state, stressed-skin construction shape is consistent with design fuselage appearance；It is described
Frame deflection truss and fuselage dimension shape frame include five truss and six revolute pairs, be connected to A, B two o'clock on front wing spar
Frame deflection truss include the first truss~the 5th truss, first truss~the 5th truss structure is arc-shaped outer
Shape, when maximum unfolded state, skin shape is consistent with design fuselage appearance on frame deflection truss, fuselage surface continual curvature,
Transition junction is smooth；One end of first truss and the 5th truss passes through revolute pair respectively and is connected to A, B two o'clock, the first truss and
Revolute pair is sequentially passed through between 5th truss connects the second truss, third truss and the 4th truss；Exterior fuselage skin is connected to
On one truss~the 5th truss, deformed together with the first truss~the 5th truss.
2. a kind of floating integrated flight vehicle aerodynamic shape of deformable liter according to claim 1, it is characterised in that: described
The planform of first truss and the 5th truss is identical with size；The planform and size phase of second truss and the 4th truss
Together.
3. a kind of floating integrated flight vehicle aerodynamic shape of deformable liter according to claim 1, it is characterised in that: aircraft
When docking at ground, fuselage is that cross sectional shape A, at this time the first truss and the 5th truss are opened to fuselage two sides, and third truss is flat
Uppermost position in fig-ure is moved to, the distance between third truss and wing spar are minimum at this time；Second truss and the 4th truss are in fuselage
Inside, each revolute pair is locked, and body volume is minimum at this time, and lateral dimension is minimum；Aircraft deforms in uphill process, and fuselage is
Cross sectional shape B, fuselage skin is inside and outside to generate pressure difference, pushes frame deflection truss and fuselage dimension shape frame to deform, turns at this time
Dynamic secondary unlock, the first truss and the 5th truss are rotated around revolute pair and are opened to fuselage two sides, and third truss translates downwards, and second
Truss is rotated down with the 4th truss around revolute pair, and aircraft fuselage volume is gradually increased；When aircraft fuselage volume increases to
When maximum rating, fuselage is cross sectional shape C, and third truss is moved to extreme lower position, and each revolute pair is locked, the first truss and the
Guarantee between two truss, the second truss and third truss, third truss and the 4th truss, the 4th truss and the 5th truss it is tangent,
Exterior skin transition is smooth.
4. a kind of floating integrated flight vehicle aerodynamic shape of deformable liter according to claim 1, it is characterised in that: described
In aircraft, front wing and rear wing form tandem wing, and front wing, rear wing are high aspect ratio configuration, before being located at fuselage
Rear portion is located in the wake flow of front wing due to rear wing, there is 3 °~6 ° differential seat angles between front wing and rear wing, and the empennage uses V
T tail is located at fuselage afterbody；It is promoted using propeller, two engines is each provided at left and right sides of the wing of front and back, power supply uses
Solar battery combines the mode of power supply with fuel cell.
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| 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 |
| CN108121855B (en) * | 2017-12-06 | 2021-04-09 | 北京理工大学 | Flight dynamics optimization method of small unmanned aerial vehicle based on bionic flexible wing |
| 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 |
| CN110834711A (en) * | 2019-11-12 | 2020-02-25 | 上海智御动力技术有限公司 | Near space volume variable suspension platform 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 |
| CN112158323B (en) * | 2020-10-24 | 2024-06-21 | 西安航空学院 | Unmanned aerial vehicle fuselage-heat dissipation intake duct 3D additive integrated skin structure |
| CN113022846B (en) * | 2021-05-27 | 2021-08-03 | 北京航空航天大学 | Mixed mode aircraft |
| CN114347737B (en) * | 2021-12-29 | 2024-03-12 | 北京国家新能源汽车技术创新中心有限公司 | Deformable low-resistance flying car body structure and car |
| CN116702331B (en) * | 2023-06-27 | 2024-07-12 | 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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