CN109263856A - High aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangement - Google Patents
High aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangement Download PDFInfo
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- CN109263856A CN109263856A CN201811136300.7A CN201811136300A CN109263856A CN 109263856 A CN109263856 A CN 109263856A CN 201811136300 A CN201811136300 A CN 201811136300A CN 109263856 A CN109263856 A CN 109263856A
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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
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/04—Aircraft not otherwise provided for having multiple fuselages or tail booms
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Abstract
The invention discloses high aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangements, belong to aerodynamic configuration of aircraft design field.Including engine, main wing, engine linkage section, fuselage, braced wing, payload, payload linkage section, vee tail, shoe and braced wing wingtip linkage section.Braced wing is laid out and is combined with twin-fuselage configuration, the aspect ratio of main wing is greater than 35, there are two engines, a fuselage is all had immediately below each engine, a braced wing is symmetrical arranged at left and right sides of each fuselage, when fuselage is in a horizontal position, support nose of wing being overlapped length on chord length direction in the horizontal direction with main wing rear as the 0%-40% of position main wing chord length.The layout that the present invention is supported using braced wing is arranged below main wing rear, increases the rigidity of structure of main wing, reduces the unfavorable interference between braced wing and main wing, while payload that can be different with carry.
Description
Technical field
The invention belongs to aerodynamic configuration of aircraft design fields, and in particular to a kind of high aspect ratio braced wing twin fuselage
Multipurpose carrier vehicle aerodynamic arrangement.
Background technique
The wing of aircraft often carries the distributed load of aircraft total weight formation, therefore a certain amount of shape can occur
Become.The wing scale of high aspect ratio aircraft is larger, and the deformation of wing is even more serious.It is encountering prominent wind or is making pitch attitude control
When processed, this biggish high aspect ratio wing of deformation may have an impact the elastics wing of flight safety.In current material skill
The aspect ratio of the horizontal lower wing of art should not be too large.However as known by the technical knowledge, wing aspect ratio is bigger, the cruise liter of aircraft
Resistance ratio is higher, and improving aspect ratio is the threshold that improves flight vehicle aerodynamic efficiency and not can bypass.
In order to solve the Rigidity of high aspect ratio wing, industry proposes twin-fuselage configuration.Twin-fuselage configuration pass through by
The mode of wing stress point dispersion changes the distribution of force of wing, according to engineering experience common sense, using flying for twin fuselage design
Row device can be improved 4 times compared to its wing twist rigidity of single machine body aircraft.Therefore double under same structure safety standard
Fuselage aircraft can have bigger wing aspect ratio, also have higher pneumatic efficiency.
In view of the weight trim problem of aircraft, the cargo load of single machine body carrier vehicle must be placed in wing center
Namely in fuselage, the size of airframe limits the maximum volume of cargo, and to destroy fuselage whole in the channel of cargo disengaging
Body structure.And the wing center of twin fuselage aircraft has enough reserved spaces, it is not necessary that cargo to be contained in fuselage, therefore
The cargo of fuselage size, even this huge monster of carrier rocket can be much larger than with carry size.On May 31st, 2017, by
Microsoft combine founder Paul Alan invest build whole world maximum twin-fuselage aircraft Stratolaunch California, USA not
It is offline to breathe out Wei air base, the span is up to 117 meters, and can once carrying 113 tons of fuel oils, (Microsoft founder invests the maximum space flight of U.S. and flies
Machine Space Agency welcomes individual enterprise [J] space flight return and remote sensing, 2011,32 (06): 73.).It can carry and weigh between two fuselages
275 tons of rocket.Aircraft can transport the high-altitude of rocket flight to 3.5 ten thousand feet, so that rocket is detached from aircraft igniter and enter the orbit.This
Design significantly reduces the cost of rocket launching.This is basic impossible mission for single machine body aircraft.
The wing aspect ratio of previously mentioned aircraft is bigger, and cruise lift resistance ratio is higher.Industry proposed another solve greatly
The distribution form of aspect ratio wing Rigidity, i.e., install braced wing immediately below wing, with the structure type for being similar to bridge
It reinforces wing and increases aspect ratio.1996 to 2001, Virginia Polytechnic Institute and State University was under the subsidy of NASA, using multidisciplinary excellent
Change method has carried out extensive, system feasibility study (Zhu Ziqiang, Wang Xiaolu, Wu Zong to transonic speed braced wing layout aircraft
At waiting Multidisciplinary Optimization [J] aviation journal of support wing transonic speed civil aircraft, 2009,30 (1): 1-11.).As a result table
Bright, braced wing layout allows wing to further increase length under the premise of not increasing weight and thickness, reduces induced drag.But
Braced wing and wing, which will form the unfavorable aerodynamic interference of double-vane, reduces pneumatic efficiency, as can reducing unfavorable aerodynamic interference, lift resistance ratio
It can be further up.It is necessary to use the supporting form for being different from the traditional support wing to reduce unfavorable interference thus., it is obvious that
The wing structure rigidity for the aircraft being laid out simultaneously using twin-fuselage configuration and braced wing is compared with single machine body conventional aircraft
It is advantageous.It is necessary to explore a kind of twin fuselage support rotor aircraft layout of higher pneumatic efficiency.
Summary of the invention
The present invention proposes a kind of using high aspect ratio braced wing twin fuselage multipurpose from pneumatic and structure design angle
Braced wing is laid out and combines with twin-fuselage configuration, improves the rigidity of structure of aircraft wing by carrier vehicle aerodynamic arrangement, increases
The aspect ratio for adding wing, by the way that braced wing is arranged in below main wing rear, reduce between braced wing and main wing caused by not
Benefit interference meets the rigidity of structure for increasing main wing and increases flight vehicle aerodynamic efficiency, that is, damping ratio dual requirements.
High aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangement provided by the present invention, including start
Machine, main wing, engine linkage section, fuselage, braced wing, payload, payload linkage section, vee tail, shoe and support
Thriving tip linkage section.The aspect ratio of the main wing is greater than 35, and there are two engines, is located at two that main wing extends length direction
At trisection point, and it is fixedly connected on main wing lower surface.One is all had immediately below each engine to be arranged in parallel with engine
Fuselage, engine is between fuselage and main wing, and the fuselage is connected with corresponding engine by engine linkage section, often
A braced wing is symmetrical arranged at left and right sides of a fuselage, braced wing is connected between fuselage and main wing, plays support main wing
Effect improves the lift resistance ratio of main wing while increasing the aspect ratio of main wing.The wing root of the braced wing is respectively with fuselage or so
Connection, the wingtip of braced wing are connected by braced wing wingtip linkage section with main wing rear, the length of braced wing wingtip linkage section
It is the 0.2%~2% of main span length, the chord length of braced wing wingtip linkage section is equal with the wing tip chord of braced wing length, wherein is located at
The wingtip of braced wing on the left of the fuselage of left end is connected at the A point of main wing rear by a braced wing wingtip linkage section, and A point arrives
The offset distance of six Along ent of the main wing leftmost side is not more than the 5% of main wing length, one section of braced wing on the right side of the fuselage of left end
Wingtip be connected at the B point of main wing rear by another braced wing wingtip linkage section, B point is located at the right side of main wing point of bisection
Side, the layout of the braced wing of the layout and left end fuselage two sides of the braced wing of right end fuselage two sides is about main wing point of bisection or so
Symmetrically.Payload is located at the underface at main wing point of bisection, is connect by payload linkage section with main wing, each fuselage
Rear portion passes through shoe and is fixedly connected with a rudder-vator, and the upper counterangle size of rudder-vator is to guarantee that empennage avoids engines tail
Stream, main wing, engine linkage section, payload linkage section, braced wing wingtip linkage section and braced wing section be aerofoil profile.
When fuselage is in a horizontal position, in extending into section for main wing, support nose of wing and main wing rear in level
Coincidence length of the direction on chord length direction is the 0%-40% of position main wing chord length；Braced wing is located at the rear of main wing
Lower section, front/rear sweep angle is identical as the rear line of main wing, guarantees in each section along the vertical direction of main wing, both wings leading edge point
Horizontal distance and section in main wing chord length ratio be a fixed value it is constant.Each engine is arranged in corresponding fuselage
Top, avoid engine spray wake flow to rudder-vator generate aerodynamic interference.
The present invention has the advantages that
1, the present invention is used to increase the rigidity of structure of wing using twin-fuselage configuration, and the aspect ratio of main wing is enable to be greater than
35。
2, the layout that the present invention is supported using braced wing is arranged below main wing rear, it is rigid in the structure for increasing main wing
The unfavorable interference between braced wing and main wing is reduced while spending, and helps to increase flight vehicle aerodynamic efficiency.
3, the present invention is enhanced to cargo aircraft in the twin-fuselage configuration of main wing center carry payload to not androgynous
The adaptability of product payload is conducive to carry out a variety of different transport tasks.
Detailed description of the invention
Fig. 1 is the top view of high aspect ratio braced wing twin fuselage multipurpose carrier vehicle of the invention；
Fig. 2 is the main view of high aspect ratio braced wing twin fuselage multipurpose carrier vehicle of the present invention；
Fig. 3 is the side view of high aspect ratio braced wing twin fuselage multipurpose carrier vehicle of the present invention；
Fig. 4 is that high aspect ratio braced wing twin fuselage multipurpose carrier vehicle of the present invention replaces the vertical view after payload
Figure；
Fig. 5 is that high aspect ratio braced wing twin fuselage multipurpose carrier vehicle of the present invention replaces the main view after payload
Figure；
Fig. 6 is the side view of braced wing of the present invention and main wing；
Fig. 7 a be the present invention support nose of wing and main wing leading edge horizontal direction horizontal distance s be -0.1 when, braced wing with
The flow pressure cloud atlas of main wing；
When Fig. 7 b is present invention support nose of wing and the horizontal distance s of main wing leading edge horizontal direction is 0.5, braced wing and master
The flow pressure cloud atlas of the wing；
When Fig. 7 c is present invention support nose of wing and the horizontal distance s of main wing leading edge horizontal direction is 0.9, braced wing and master
The flow pressure cloud atlas of the wing；
Fig. 8 a is the horizontal distance s respectively -0.1,0.1,0.3,0.5,0.7 of braced wing of the present invention and main wing horizontal direction
When with 0.9, the change curve of the lift coefficient of aircraft；
Fig. 8 b is the horizontal distance s respectively -0.1,0.1,0.3,0.5,0.7 of braced wing of the present invention and main wing horizontal direction
When with 0.9, the change curve of the lift resistance ratio of aircraft；
In figure:
1, engine；2, main wing；3, engine linkage section；4, fuselage；5, braced wing；
6, payload；7, payload linkage section；8, rudder-vator；9, shoe；10, braced wing wingtip linkage section.
Specific embodiment
The present invention will be described in further detail with reference to the accompanying drawing.
The present invention proposes a kind of using high aspect ratio braced wing twin fuselage multipurpose from pneumatic and structure design angle
Braced wing is laid out and combines with twin-fuselage configuration by carrier vehicle aerodynamic arrangement, improves the rigidity of structure of aircraft main wing, increases
The aspect ratio of main wing is added to be used to increase the lift resistance ratio of aircraft；It is supported by the way that braced wing 5 to be arranged in reduce below 2 rear of main wing
Generated unfavorable interference between the wing 5 and main wing 2 meets the rigidity of structure for increasing main wing 2 and increases flight vehicle aerodynamic efficiency
Dual requirements.
High aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangement provided by the present invention, in conjunction with Fig. 1, figure
Shown in 2 and Fig. 3, including engine 1, main wing 2, engine linkage section 3, fuselage 4, braced wing 5, payload 6, payload connect
Connect section 7, vee tail 8, shoe 9 and braced wing wingtip linkage section 10.The aspect ratio of the main wing 2 is greater than 35, and engine 1 has
It two, is located at main wing 2 and extends at two trisection points of length direction, and be fixedly connected on 2 lower surface of main wing.Each start
The fuselage 4 being arranged in parallel with engine 1 is all had immediately below machine 1, engine 1 is described between fuselage 4 and main wing 2
Fuselage 4 is connected by engine linkage section 3 with corresponding engine 1.Each 4 left and right sides of fuselage is symmetrical arranged a support
The wing 5, braced wing 5 are connected between fuselage 4 and main wing 2, play the role of supporting main wing 2, are increasing the same of the aspect ratio of main wing 2
The lift resistance ratio of Shi Tigao main wing 2.The wing root of the braced wing 5 is connected at left and right sides of fuselage 4 respectively, and the wingtip of braced wing 5 is logical
Braced wing wingtip linkage section 10 is crossed to be connected with 2 rear of main wing.The length of braced wing wingtip linkage section 10 is 2 length of main wing
0.2%~2%, the chord length of braced wing wingtip linkage section 10 is equal with the wing tip chord of braced wing 5 length, with 4 left side of left end fuselage
For the connection of one section of braced wing 5, the wingtip of braced wing 5 is connected to the A point of 2 rear of main wing by braced wing wingtip linkage section 10
Place, the offset distance of A point to 2 leftmost side of main wing, six Along ent are not more than the 5% of 2 length of main wing.Positioned at 4 right side of left end fuselage
The wingtip of one section of braced wing 5 is connected at the B point of 2 rear of main wing by braced wing wingtip linkage section 10, and B point is located at main wing 2 two
The right side of Along ent, specifically, in the feelings for guaranteeing that one section of braced wing 5 on 4 right side of left end fuselage is not in contact with payload 6
Under condition, increase B point as far as possible crosses to the right the distance of 2 point of bisection of main wing, and guarantees the monosymmetric basic demand of fuselage 4.Such as
Shown in Fig. 2, due to braced wing 5 and main wing 2 be in preceding apparent direction it is straight, pass through the phase at one end of braced wing wingtip linkage section 10
Even, and braced wing 5 is connected to the fuselage 4 of bottom, and fuselage 4 is connected to main wing 2 by engine linkage section 3 and engine 1, overall
On form triangle geometry relationship in Front view 2, therefore the vertical range of fuselage 4 and main wing 2 actually determines in layout
The vertical range of braced wing 5 and main wing 2, therefore fuselage 4 should be greater than corresponding engine 1 and main wing 2 with the vertical range of main wing 2
The 300% of 2 chord length of junction main wing.The braced wing 5 of the layout and 4 two sides of left end fuselage of the braced wing 5 of 4 two sides of right end fuselage
It is laid out the point of bisection bilateral symmetry about main wing 2.Payload 6 is located at the underface at 2 point of bisection of main wing, by effective
Load linkage section 7 is connect with main wing 2, and each 4 rear portion of fuselage passes through shoe 9 and is fixedly connected with a rudder-vator 8, rudder-vator 8
Upper counterangle size be guarantee rudder-vator 8 avoid 1 wake flow of engine.Main wing 2, engine linkage section 3, payload linkage section
7, the section of braced wing wingtip linkage section 10 and braced wing 5 is aerofoil profile, and specific aerofoil profile is according to Flight Vehicle Design use demand
It is individually determined.
It is different from the layout that braced wing 5 is arranged in 2 underface of main wing by conventional support wing layout, as shown in Figure 1, Figure 2 and Fig. 3 institute
Show, when fuselage 4 is in a horizontal position, in extending into section for main wing, 5 leading edge of braced wing and 2 rear of main wing are along chord length side
Upward coincidence length is the 0%-40% of 2 chord length of position main wing, and 2 leading edge of main wing and 5 leading edge of braced wing are in Vertical Square
To vertical range and braced wing 5 upper counterangle combine the height of fuselage 4 and the length of engine linkage section 3 to determine, and fuselage 4
The design use demand of the length combination aircraft itself of height and engine linkage section 3 determines that (aircraft center is hung as guaranteed
The payload 6 of load cannot contact to earth)；Braced wing 5 is located at below the rear of main wing 2, and front/rear sweep angle is identical as main wing 2, design
When need to guarantee in each section along the vertical direction of main wing 2,2 chord length of main wing in the horizontal distance and section of both wings leading edge point
Ratio is that a fixed value is constant.Each engine 1 is arranged in the top of corresponding fuselage 4, and engine 1 is avoided to spray wake flow
Aerodynamic interference is generated to rudder-vator 8.
High aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangement proposed by the present invention, central carry
Payload 6 can be replaced according to different task demand.Wherein, payload 6 is with 7 carry of payload linkage section in master
The carry mode of the lower section of the wing 2, the degree of modularity is higher, to the limitation of 6 volume of payload than conventional single machine body carrier vehicle
It is small, multipurpose transport capacity can be better achieved, should be noted that in carry makes the center of gravity of payload 6 be in payload connection
7 place vertical planes of section guarantee that aircraft can carry out trim, latent with biggish application in fields such as earthquake relief work, branch road transportations
Power.In addition to this, payload 6 can be cargo or the mission payload with certain specific function, such as large-scale early warning radar,
Electronic jamming equipment, large-scale communication trunking etc..As shown in Figure 1, Figure 2 and Fig. 3 in, payload 6 be cargo, as Fig. 4 with
In Fig. 5, payload 6 is large-scale early warning radar, can serve as multipurpose special type fortune using the aircraft of aerodynamic arrangement of the present invention
Carry aircraft.
Main wing 2 and the specific relative position aeroperformance integrated therewith of braced wing 5 are closely related, need according to pneumatic design
Requirement be determined.In live flying environment, there is wingtip vortex at wing wingtip in three-dimensional main wing 2 and braced wing 5
Effect, the pressure gradient that wingtip vortex generates make air-flow produce flowing in wingspan length direction, but due to the exhibition string of main wing 2
Aspect ratio than being greater than 35, super large makes wingtip vortex very little for the relatively entire wing area in the influence area of wing, therefore
Flow strength in wingspan length direction is much smaller relative to the flow strength for flowing to direction (fuselage direction), therefore wing exhibition
The flow strength of length direction can be ignored relative to the flow strength for flowing to direction (fuselage direction), and main wing 2 and braced wing 5 are opposite
Position determines that control parameter is 2 leading edge of main wing and 5 leading edge of braced wing water in the horizontal direction after being analyzed according to two-dimensional case
The vertical range of flat distance and vertical direction.
As shown in fig. 6, in the section along spanwise direction of main wing 2,5 leading edge of braced wing and 2 leading vertical direction of main wing
Vertical range be g, the horizontal distance of 5 leading edge of braced wing and 2 leading edge horizontal direction of main wing is based on the unit of measurement of s, g and s
The multiple of 2 chord length of the wing, such as " g=1.0 " represent the vertical range in 5 leading edge of braced wing and 2 leading vertical direction of main wing as 2 string of main wing
Long 1.0 times, and braced wing 5 is located at 2 lower section of main wing；S, which is positive, represents the rear that braced wing 5 is located at main wing 2, and s, which is negative, represents branch
The support wing 5 is located at the front of main wing 2, is located at 2 rear of main wing and before 5 leading edge of braced wing and main wing 2 as " s=1.0 " represents braced wing 5
The horizontal distance of edge horizontal direction is 1.0 times of 2 chord length of main wing.
Embodiment 1:
The aerofoil profile of main wing 2 and braced wing 5 is RAE2822, and speed of incoming flow 100m/s, the incoming flow angle of attack is 2 °, and A point is located at master
At 2 leftmost side of the wing, six Along ent, the upper counterangle of rudder-vator is 30 °~60 °, and the upper counterangle of braced wing is 10 °~25 °, braced wing
Front/rear sweep angle be 5 °~10 °.In the section along spanwise direction of main wing 2, before taking different 5 leading edge of braced wing and main wing 2
The horizontal distance s (respectively -0.1,0.5,0.9) of edge horizontal direction, taking vertical range g is 0.3, obtained braced wing 5 and master
The flow pressure cloud atlas of the wing 2 is as shown in Fig. 7 a, 7b, 7c.It can be seen that braced wing 5 in main wing leading edge from Fig. 7 a, braced wing 5
Upper surface air-flow acceleration make the air-flow below 2 leading edge of main wing by accelerate influence, destroy the suction peak of main wing 2, lead
Cause drop in lift；It can be seen that from Fig. 7 b and form local jet pipe effect between main wing 2 and braced wing 5,5 lift of main wing is same
It is destroyed；When can be seen that braced wing 5 from Fig. 7 c and being located at below main wing 2 rear, according to scholar Koffsky rear condition, main wing 2
The air velocity of rear and itself upper surface are close, even if thus braced wing 5 generates acceleration to 2 lower surface of main wing at this time,
It remains unchanged very little to the lift effect of main wing 2.
Fig. 8 a illustrates the variation of lift coefficient when horizontal distance s is respectively -0.1,0.1,0.3,0.5,0.7,0.9, shows
Lift is worst when right visible braced wing 5 is located at 2 underface of main wing, and lift when positioned at 2 rear of main wing, which is significantly better than, is located at main wing 2
Leading edge.Fig. 8 b illustrates the variation of lift resistance ratio when horizontal distance s is respectively -0.1,0.1,0.3,0.5,0.7,0.9, it is seen that support
Lift resistance ratio is minimum when the wing 5 is located at 2 underface of main wing, and lift resistance ratio when positioned at 2 rear of main wing is apparently higher than positioned at 2 leading edge of main wing,
Prove that rear edge support is conducive to improve flight vehicle aerodynamic efficiency.
In conclusion aerodynamic arrangement of the present invention increases high aspect ratio using the distribution form that twin fuselage and braced wing combine
The rigidity of structure of wing, the level by improving aspect ratio to 35 or more increase the lift resistance ratio of aircraft, the design of twin fuselage
More conducively carry large size payload.This aerodynamic arrangement is that one kind effectively may be used for the design of multipurpose carrier vehicle
Select scheme.
As known by the technical knowledge, the present invention can not depart from the embodiment party of its theoretical essence or essential feature by others
Case is realized.Therefore, above-mentioned all embodiments are all merely illustrative, not the only.Each component in the present invention
Size, cross sectional shape and relative position are determined according to design requirement, and are suitable for the aerodynamic arrangement of the aircraft of any size
Design, it is all within the scope of the invention as claimed or the change that is equal in protection scope of the present invention is sent out by this
It is bright to include.
Claims (9)
1. a kind of high aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangement, including engine, main wing, fuselage, V
Type tail and shoe；It is characterized in that, further including braced wing, braced wing wingtip linkage section and engine linkage section；Engine
There are two, it is located at main wing and extends at two trisection points of length direction, and be fixedly connected on main wing lower surface；Each start
The fuselage of one with engine parallel arrangement are all had immediately below machine, for engine between fuselage and main wing, the fuselage is logical
It crosses engine linkage section to connect with corresponding engine, a braced wing, braced wing is symmetrical arranged at left and right sides of each fuselage
It is connected between fuselage and main wing, the wing root of the braced wing is connect with fuselage or so respectively, and the wingtip of braced wing passes through support
Thriving tip linkage section is connected with main wing rear；Wherein, the wingtip of the braced wing on the left of the fuselage of left end passes through a support
Thriving tip linkage section is connected at the A point of main wing rear, and the wingtip of one section of braced wing on the right side of the fuselage of left end passes through another
A braced wing wingtip linkage section is connected at the B point of main wing rear, the layout and left end fuselage of the braced wing of right end fuselage two sides
The layout of the braced wing of two sides is about main wing point of bisection bilateral symmetry.
2. a kind of high aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangement as described in claim 1, special
Sign is, the length of braced wing wingtip linkage section is long 0.2%~2% of the main span, the chord length of braced wing wingtip linkage section with
The wing tip chord length of braced wing is equal.
3. a kind of high aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangement as described in claim 1, special
Sign is that the offset distance of A point to six Along ent of the main wing leftmost side is located at main wing bisection no more than 5%, the B point of main wing length
The right side of point.
4. a kind of high aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangement as claimed in claim 3, special
Sign is that A point is located at six Along ent of the main wing leftmost side.
5. a kind of high aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangement as described in claim 1, special
Sign is that the section of engine linkage section, braced wing wingtip linkage section and braced wing is aerofoil profile.
6. a kind of high aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangement as described in claim 1, special
Sign is that the aspect ratio of the main wing is greater than 35.
7. a kind of high aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangement as described in claim 1, special
Sign is, when fuselage is in a horizontal position, support nose of wing and main wing rear being overlapped on chord length direction in the horizontal direction
Length is the 0%~40% of position main wing chord length.
8. a kind of high aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangement as described in claim 1, special
Sign is that the upper counterangle of braced wing is 10 °~45 °, and the front/rear sweep angle of braced wing is 0 °~10 °, and the upper counterangle of rudder-vator is
30 °~60 °.
9. a kind of high aspect ratio braced wing twin fuselage multipurpose carrier vehicle aerodynamic arrangement as described in claim 1, special
Sign is, for cargo, large-scale early warning radar, electronic jamming equipment or the large-scale delivery for communicating trunking.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111337211A (en) * | 2020-03-05 | 2020-06-26 | 中国航天空气动力技术研究院 | Double-body model four-point supporting and fixing device |
| CN114160214A (en) * | 2021-11-10 | 2022-03-11 | 中国空气动力研究与发展中心空天技术研究所 | Unmanned aerial vehicle extreme environment simulation laboratory |
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| CN111337211A (en) * | 2020-03-05 | 2020-06-26 | 中国航天空气动力技术研究院 | Double-body model four-point supporting and fixing device |
| CN111337211B (en) * | 2020-03-05 | 2022-01-04 | 中国航天空气动力技术研究院 | Double-body model four-point supporting and fixing device |
| CN114160214A (en) * | 2021-11-10 | 2022-03-11 | 中国空气动力研究与发展中心空天技术研究所 | Unmanned aerial vehicle extreme environment simulation laboratory |
| CN114160214B (en) * | 2021-11-10 | 2023-10-27 | 中国空气动力研究与发展中心空天技术研究所 | Unmanned aerial vehicle extreme environment simulation laboratory |
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