CN115258131A - High-efficiency and high-maneuverability tandem wing layout load-carrying aircraft - Google Patents

High-efficiency and high-maneuverability tandem wing layout load-carrying aircraft Download PDF

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Publication number
CN115258131A
CN115258131A CN202210950996.7A CN202210950996A CN115258131A CN 115258131 A CN115258131 A CN 115258131A CN 202210950996 A CN202210950996 A CN 202210950996A CN 115258131 A CN115258131 A CN 115258131A
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China
Prior art keywords
wing
main
vertical tail
vertical
layout
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CN202210950996.7A
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Chinese (zh)
Inventor
陈百辉
李昕亮
包圆程
郑纪源
刘璀
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Sun Yat Sen University
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Sun Yat Sen University
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Priority to CN202210950996.7A priority Critical patent/CN115258131A/en
Publication of CN115258131A publication Critical patent/CN115258131A/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/20—Integral or sandwich constructions
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C5/00—Stabilising surfaces
    • B64C5/06—Fins

Abstract

The invention discloses a high-efficiency high-maneuverability tandem wing layout heavy-duty aircraft, which comprises a main beam, a main wing and a vertical tail wing, wherein the main beam is provided with a main wing and a vertical tail wing; the main wing is arranged on the main beam; the main wing comprises a front wing and a rear wing, and the front wing and the rear wing are respectively arranged at two ends of the main beam; the two vertical tail wings are respectively and symmetrically arranged on the left ventral surface and the right ventral surface of the rear wing, and the vertical tail wings are also provided with rear landing gears; the two ends of the rear wing are provided with vertical stabilizing panels; the side surface of the vertical fixing plate is vertically connected and fixed with the length direction of the rear wing; the two unilateral front edges of the rear wing are both provided with engines, and propellers of the engines are aligned with the vertical tail wing; the rear edges of the front wing, the rear wing and the vertical tail wing are all provided with swing ailerons; the landing gear and the vertical tail wing are designed in a fusion mode, the control of the propeller slipstream enhancement rudder of an engine can be received, and the size of an aircraft can be reduced; the engine is positioned on the leading edge of the rear wing, allowing the slipstream of the propeller to enhance the control of the rudder through the ailerons.

Description

High-efficiency and high-maneuverability tandem wing layout load-carrying aircraft
Technical Field
The invention relates to the field of aircrafts, in particular to a serial wing layout load-carrying aircraft with high efficiency and high maneuverability.
Background
The unmanned aerial vehicle has the characteristics of low operation cost, high maneuverability, convenience and high efficiency in use and the like, and is successfully applied to the logistics industry at present. However, under the circumstances that energy is increasingly tensed, the price of petroleum is increasingly rising, and the load-carrying aircraft is small in carrying capacity, limited in carrying goods, low in operation efficiency, high in energy consumption of large unmanned aircraft, and limited in urban flight area, the demand of the load-carrying aircraft is increasing, which is small in size, strong in control performance, and high in load-carrying efficiency.
A conventional layout small-sized load-carrying unmanned aerial vehicle usually adopts a high-aspect-ratio design to achieve the purposes of lift-increasing and drag reduction, but has higher design requirements on structural strength and rigidity due to a longer wingspan.
The front wing and the rear wing of the tandem wing layout aircraft are main sources of lift force of the aircraft, and compared with the conventional layout aircraft, the tandem wing layout aircraft can effectively reduce the wingspan of the front wing and the rear wing and reduce the rigidity requirement of a wing structure.
Therefore, a technical scheme capable of improving the loading efficiency of the unmanned aerial vehicle is urgently needed.
Disclosure of Invention
The invention aims to provide a serial wing layout load-carrying aircraft with high efficiency and high maneuverability, and aims to solve the problems that the existing conventional layout aircraft is large in size and low in load-carrying efficiency.
In order to solve the technical problem, the invention provides a high-efficiency high-maneuverability tandem wing layout heavy-duty aircraft, which comprises a main beam, a main wing and a vertical tail wing; the main wings are arranged on the main beam; the main wing comprises a front wing and a rear wing, and the front wing and the rear wing are respectively installed at two ends of the main beam; the two vertical tail wings are respectively and symmetrically arranged on the left ventral surface and the right ventral surface of the rear wing, and the vertical tail wings are also provided with rear landing gears; the two ends of the rear wing are provided with vertical stabilizing panels; the side surface of the vertical fixing plate is vertically connected and fixed with the length direction of the rear wing; the two unilateral front edges of the rear wing are both provided with engines, and propellers of the engines are aligned with the vertical tail wing; and the rear edges of the front wing, the rear wing and the vertical tail wing are all provided with swing ailerons.
In one embodiment, the main beam is mounted between a ventral surface of the front wing and a dorsal surface of the rear wing.
In one embodiment, the main beam is mounted between the back surface of the front wing and the ventral surface of the rear wing.
In one embodiment, the wing differential angle of the front wing and the rear wing is 0.5-3 degrees; the height difference of the front edge point of the front wing and the rear wing is 4-10% of the wingspan of the rear wing; the difference of the wingspan of the front wing and the rear wing is 40-46% of the wingspan of the rear wing.
In one embodiment, the front wing and the rear wing are both straight wings.
In one embodiment, the wing area of the main wing is 0.3m 2 -1m 2 (ii) a The wing area of the vertical tail wing is 0.03m 2 -0.1m 2 。
In one embodiment, the mounting angle of the front wing is 2-5 degrees, the mounting angle of the rear wing is 2-5 degrees, and the mounting angle of the vertical tail wing is 0 degree; the aspect ratio of the front wing, the rear wing and the vertical tail wing is 2-3, 2.5-3.5 and 0.5-1 respectively; the tip-to-root ratios of the front wing, the rear wing and the vertical tail are 0.3-0.8, 0.2-0.6 and 0.4-0.8, respectively.
In one embodiment, the vertical distance between the chord line of the vertical tail wing and the main girder is 36-40% of the unilateral wing span.
In one embodiment, the wing of the main wing comprises a spar and a skin; a plurality of wing ribs are uniformly arranged on the wing beam in the length direction; the skin wraps the spar and the wing rib; at the leading edge of the main wing, the spar, the wing rib and the skin form a closed D-box; the main wing is provided with a lug piece at the center in the length direction of the main wing, and the lug piece is fixedly connected with the main beam; the rear edge of the main wing is provided with an auxiliary wing beam, the auxiliary wing beam is fixedly connected with the wing rib of the wing, and the auxiliary wing beam is rotatably provided with the auxiliary wing; an engine compartment is arranged on the rear wing, the engine compartment is fixedly connected with the wing beam, and the engine is mounted on the engine compartment.
In one embodiment, the rear landing gear includes a rear wheel and a rear strut; the vertical tail comprises an auxiliary wing plate and a vertical wing rib; the rear wheel is rotatably connected with one end of the rear supporting rod, and the other end of the rear supporting rod is fixedly connected with the engine compartment; a plurality of vertical wing ribs are arranged along the length direction of the rear supporting rod; the auxiliary wing plate is arranged at the rear edge of the vertical tail wing, and the auxiliary wing plate is fixedly connected with the vertical wing rib; the skin wraps the auxiliary wing plate and the vertical wing rib; the aileron plate is rotatably provided with the aileron; the main beam is also provided with a nose landing gear which is arranged below the nose wing; the nose landing gear comprises a nose wheel and a front support bar; the front wheel is rotatably connected with one end of the front supporting rod, and the other end of the front supporting rod is fixedly connected with the main beam.
The invention has the following beneficial effects:
1. the invention adopts the layout of the tandem wings, simplifies the structural design and improves the structural compactness by reducing the aspect ratio and the extension length of the airplane and fusing the undercarriage and the vertical tail wing on the premise of not reducing the lift-drag ratio and the load capacity of the airplane.
2. The center of gravity of the aircraft is arranged between the front wing and the rear wing, and the span is reduced to achieve the purpose of reducing the structural rigidity and strength requirements in the design and manufacturing process of the aircraft, so that the structural weight is reduced.
3. The vertical tail wing is designed and installed behind and below a propeller of the engine, the propeller is installed on the front edge of the rear wing, and the ailerons of the vertical tail wing and the ailerons of the rear wing receive propeller accelerated airflow so as to increase the rudder effect under the conditions of low speed and stall.
4. According to the tandem wing load-carrying aircraft, the configuration that airflow of the front wing and the rear wing is favorably interfered is designed, so that the aircraft is trimmed under the condition that the optimal installation angle of the main wing is not changed, the lift-drag ratio and the load capacity of the aircraft are improved, and the requirements of long-range high-efficiency cruise on environmental protection and energy conservation are met.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
Figure 1 is a side view of an aircraft according to a first embodiment of the invention;
FIG. 2 is a schematic structural view of an aircraft in accordance with a first embodiment of the invention;
FIG. 3 is a top plan view of the aircraft of the first embodiment of the present invention;
FIG. 4 is an isometric view of an aircraft in accordance with a first embodiment of the invention;
FIG. 5 is a schematic illustration of a second embodiment of the aircraft with a load carrying compartment according to the present invention;
FIG. 6 is a schematic structural view of an aircraft frame of a second embodiment of the invention;
FIG. 7 is a side view of an aircraft frame of a second embodiment of the invention;
FIG. 8 is a pressure cloud plot of the results of a CFD simulation of the wing set and vertical tail of an aircraft of the present invention.
The reference numbers are as follows:
1. a main beam; 11. a load carrying compartment;
2. a main wing; 21. a front wing; 22. a rear wing; 221. a vertical stabilizing panel; 222. an engine; 23. A vertical tail; 231. a secondary wing plate; 232. a vertical wing rib;
24. a spar; 241. a front wing spar; 242. a rear wing spar;
25. covering a skin; 251. a front wing skin; 252. a rear wing skin;
26. a wing rib; 261. a front wing rib; 262. a rear wing rib;
27. a secondary spar; 271. a front wing spar; 272. a rear wing spar;
28. a tab; 29. an engine compartment;
3. an aileron; 31. a front wing aileron; 32. a rear wing aileron; 33. a vertical tail aileron;
4. a rear landing gear; 41. a rear wheel; 42. a rear support bar;
5. a nose landing gear; 51. a front wheel; 52. a front support bar;
6. a leading edge;
7. a trailing edge;
8. ventral surface;
9. and a back surface.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention.
One embodiment of a tandem wing arrangement heavy-duty vehicle is shown in fig. 1-4, and includes a main beam 1, main wings 2, and a vertical tail 23; the main wing 2 is arranged on the main beam 1; the main wing 2 comprises a front wing 21 and a rear wing 22, and the front wing 21 and the rear wing 22 are respectively installed at two ends of the main girder 1; the two vertical tail wings 23 are respectively and symmetrically arranged on the left ventral surface 8 and the right ventral surface 8 of the rear wing 22, and the rear landing gear 4 is also arranged on the vertical tail wings 23; vertical stabilizing panels 221 are mounted at both ends of the rear wing 22; the side surface of the vertical fixing plate is vertically connected and fixed with the length direction of the rear wing 22; the two single-sided leading edges 6 of the rear wing 22 are each provided with an engine 222, and the propellers of the engines 222 are aligned with the vertical tail fin 23; the rear edges 7 of the front wing 21, the rear wing 22 and the vertical tail 23 are all provided with swing ailerons 3.
In particular, the line of tension of the motor 222 coincides with the chord line of the vertical tail 23;
with regard to the above terminology, it is to be interpreted that:
tension line: the engine drives the propeller to rotate to generate a propelling force, and an auxiliary line passing through a propelling force action point and pointing to an action direction is a tension line.
Chord line: in the airfoil shape of the cross section of the airfoil, an auxiliary line connecting the most leading edge point and the most trailing edge point of the airfoil profile is a chord line.
Regarding the above-described mounting manner of the main beam 1 and the front wing 21 and the rear wing 22, in this embodiment, as shown in fig. 1, 3 and 4, the main beam 1 is mounted between the ventral surface 8 of the front wing 21 and the dorsal surface 9 of the rear wing 22.
When the integrated wing is applied, the front wing 21 and the rear wing 22 are all integrated wings, the ventral surface 8 of the front wing 21 and the back surface 9 of the rear wing 22 are directly connected and fixed with the main beam 1, and the front wing 21, the main beam 1 and the rear wing 22 are sequentially arranged from top to bottom in the vertical direction. The wing layout mode is a tandem front and rear wing layout design, namely a tandem wing layout.
It should be noted that, in the above, the ventral surface 8, the dorsal surface 9, the leading edge 6 and, hereinafter, the trailing edge 7 are specifically positioned as indicated in fig. 3 and 4, the ventral surface 8 is the underside of the front wing 21 and the rear wing 22, and the dorsal surface 9 is the upper side of the front wing 21 and the rear wing 22; the front edge 6 is the front ends of the front wing 21, the rear wing 22 and the vertical tail 23, and the rear edge 7 is the rear ends of the front wing 21, the rear wing 22 and the vertical tail 23; the two single sides of the rear wing 22 are divided into a left single side and a right single side by taking a midline of the wing in the length direction as a boundary, and the main beam 1 can also be taken as a boundary.
A second embodiment of the invention, which is substantially identical to the first embodiment, differs from the first embodiment in that the spar 1, the front wing 21 and the rear wing 22 are mounted in different positions, this embodiment being shown in fig. 7 with the spar 1 mounted between the rear face 9 of the front wing 21 and the ventral face 8 of the rear wing 22.
When the integrated wing is applied, the front wing 21 and the rear wing 22 are all integrated wings, the back surface 9 of the front wing 21 and the ventral surface 8 of the rear wing 22 are directly connected and fixed with the main beam 1, and the front wing 21, the main beam 1 and the rear wing 22 are sequentially arranged from bottom to top in the vertical direction. The wing layout mode is also a tandem front wing layout design, the design of a load carrying cabin 11 is additionally added in the wing layout mode, and the load carrying space is utilized to the maximum extent through the load carrying layout shown in the figure.
As shown in fig. 5 to 7, the vertical stabilizer panel 221 of the rear wing 22 is not shown for the convenience of showing the internal structure of the wing.
In relation to the arrangement of the main wing 2 described above, as shown in fig. 1, 2, 5 and 6 for this embodiment, the wing of the main wing 2 comprises a spar 24 and a skin 25; a plurality of wing ribs 26 are uniformly arranged on the spar 24 in the length direction; skin 25 wraps spar 24 and wing ribs 26; at the leading edge 6 of the main wing 2, the spars 24, wing ribs 26 and skin 25 form a closed D-box; in the center of the main wing 2 in the length direction, the main wing 2 is provided with a lug 28, and the lug 28 is fixedly connected with the main beam 1; the rear edge 7 of the main wing 2 is provided with an auxiliary wing beam 27, the auxiliary wing beam 27 is fixedly connected with a wing rib 26, and the auxiliary wing 3 is rotatably arranged on the auxiliary wing beam 27; the rear wing 22 is provided with an engine compartment 29, the engine compartment 29 is fixedly connected with the wing beam 24, and the engine 222 is mounted on the engine compartment 29.
Specifically, spar 24 includes a front wing spar 241 and a rear wing spar 242; skin 25 includes a forward wing skin 251 and an aft wing skin 252; wing ribs 26 include a forward wing rib 261 and an aft wing rib 262; the secondary spar 27 comprises a front wing secondary spar 271 and a rear wing secondary spar 272;
in particular, the wing ribs 26 and tabs 28 are of a lightweight design, and a plurality of weight-reducing slots are provided in the wing ribs 26 and tabs 28.
1. The front wing 21 adopts a front wing spar 241, a front wing skin 251, a front wing rib 261 and a front wing auxiliary spar 271, and the front wing 21 is combined in the connection mode.
2. The rear wing 22 is formed by combining the rear wing spar 242, the rear wing skin 252, the rear wing rib 262 and the rear wing auxiliary spar 272 in the above-mentioned connection mode, wherein the engine room 29 is fixedly connected with the rear wing spar 242.
3. As shown in the figure, the nacelle 29 is rectangular, and has a short-side end face on one side connected and fixed to the rear wing spar 242 and an engine 222 mounted on the short-side end face on the other side; the panels that make up the engine compartment 29 are also provided with a plurality of weight-reducing slots.
With respect to the above described landing gear arrangement, this embodiment is shown in figures 1, 2, 5 and 6, the rear landing gear 4 comprises a rear wheel 41 and a rear strut 42; the vertical rear wing 23 includes a aileron 231 and a vertical wing rib 232; the rear wheel 41 is rotatably connected with one end of the rear supporting rod 42, and the other end of the rear supporting rod 42 is fixedly connected with the engine compartment 29; a plurality of vertical ribs 232 are installed along the length direction of the rear support bar 42; the aileron 231 is mounted on the rear edge 7 of the vertical tail fin 23, and the aileron 231 is fixedly connected with the vertical fin rib 232; the skin 25 wraps the aileron plate 231 and the tab rib 232; the aileron plate 231 is rotatably provided with an aileron 3; the main beam 1 is also provided with a nose landing gear 5, and the nose landing gear 5 is arranged below the nose wing 21; the nose landing gear 5 includes a nose wheel 51 and a front stay 52; the front wheel 51 is rotatably connected with one end of a front support rod 52, and the other end of the front support rod 52 is fixedly connected with the main beam 1.
When the device is used, the rear support rod 42 is inserted into the engine compartment 29, and the rear support rod 42 is fixedly connected with the engine compartment 29; the vertical tail 23 is fused with the rear landing gear 4;
the beneficial effects brought are as follows: the vertical tail 23 and the rear landing gear 4 are designed in a fusion mode, the function of a vertical stabilizer can be shared, the structural redundancy is reduced, the requirements for the structural strength and rigidity of the aircraft are lowered, the structural weight and the cost of the aircraft are reduced, and the load ratio is improved.
In particular, the rear edges 7 of the front wing 21, the rear wing 22 and the vertical tail 23 are all provided with swing ailerons 3, and the ailerons 3 comprise a front wing aileron 31, a rear wing aileron 32 and a vertical tail aileron 33; therefore, the front wing 21 is correspondingly provided with a front wing aileron 31, the rear wing 22 is correspondingly provided with a rear wing aileron 32, and the vertical tail 23 is correspondingly provided with a vertical tail aileron 33;
the front wing ailerons 31 and the rear wing ailerons 32 are provided with link mechanisms, the front wing ailerons 31 and the rear wing ailerons 32 are respectively and rotatably connected with the front wing aileron beams 271 and the rear wing aileron beams 272 through the link mechanisms, and the link mechanisms are driven by installing steering engines on the front wings 21 and the rear wings 22, so that the front wing ailerons 31 and the rear wing ailerons 32 are driven to swing.
The vertical tail aileron 33 has a link mechanism, the vertical tail aileron 33 is rotatably connected to the aileron plate 231 via the link mechanism, and the vertical tail 23 is provided with a steering gear to drive the link mechanism, thereby driving the vertical tail aileron 33 to swing.
The beneficial effects brought are that: as the engine 222 is arranged at the front edge 6 of the rear wing 22, the vertical tail 23 is positioned below the rear wing 22 to receive the slipstream of the propeller of the engine 222, the control effect of the rudder is enhanced, the vertical stable panel 221 penetrating through the upper surface and the lower surface of the rear wing 22 inhibits the tip vortex to reduce the induced resistance, the control surfaces of the front wing 21 and the rear wing 22 are comprehensively used to realize mixed control, and the control effect and the lateral stability and the shape fixing performance of the aircraft are enhanced.
Design parameters relating to the front wing 21, the rear wing 22, and the vertical rear wing 23 described above:
1. the wing difference angle of the front wing 21 and the rear wing 22 is 0.5-3 degrees;
2. the height difference of the front edge 6 point of the front wing 21 and the rear wing 22 is 4-10% of the wingspan of the rear wing 22;
3. the difference of the wingspan of the front wing 21 and the rear wing 22 is 40-46% of the wingspan of the rear wing 22;
4. the front wing 21 and the rear wing 22 are both straight wings;
5. wing area of the main wing 2 is 0.3m 2 -1m 2 ；
6. Wing area of the vertical tail 23 is 0.03m 2 -0.1m 2 ；
7. The mounting angle of the front wing 21 is 2-5 degrees, the mounting angle of the rear wing 22 is 2-5 degrees, and the mounting angle of the vertical tail wing 23 is 0 degree;
8. the aspect ratio of the front wing 21, the rear wing 22 and the vertical tail 23 is 2-3, 2.5-3.5 and 0.5-1 respectively;
9. the tip-root ratios of the front wing 21, the rear wing 22 and the vertical tail 23 are respectively 0.3-0.8, 0.2-0.6 and 0.4-0.8;
10. the vertical distance between the chord line of the vertical tail 23 and the main beam 1 is 36-40% of the single-side span.
It should be noted that, in the following description,
when in application, the aircraft actually manufactured by the scheme selects the optimal parameters,
1.1, the wing differential angle of the front wing 21 and the rear wing 22 is 1 degree;
2.1, the height difference of the front edge 6 point of the front wing 21 and the rear wing 22 is 7 percent of the wingspan of the rear wing 22;
3.1, the difference of the wingspans of the front wing 21 and the rear wing 22 is 43.3 percent of the wingspan of the rear wing 22;
5.1 wing area of main wing 2 0.6m 2 ；
6.1, wing area of vertical tail 23 0.06m 2 ；
7.1, the mounting angle of the front wing 21 is 4 degrees, the mounting angle of the rear wing 22 is 3 degrees, and the mounting angle of the vertical tail wing 23 is 0 degree;
8.1, front wing 21, rear wing 22 and vertical tail 23 have aspect ratios of 2.79, 3.1 and 0.87, respectively;
9.1, front wing 21, rear wing 22 and vertical tail 23 have tip to root ratios of 0.6, 0.44 and 0.65, respectively;
10.1, the vertical distance between the chord line of the vertical tail wing 23 and the main beam 1 is 38 percent of the single-side span.
For the interpretation of nouns:
wing difference angle: the serial layout aircraft design index refers to the difference value of the erection angles of the front wing and the rear wing, and is that the erection angle of the front wing is larger than that of the rear wing at the front tail of the aircraft.
Height difference of front edge points: the design index of the tandem layout aircraft refers to the projection of the distance between the most front edge points of the wing root planing surfaces of the front wing and the rear wing in the vertical direction of the aircraft, and represents the relative height of the front wing and the rear wing, and if the height difference is positive, the front wing is higher than the rear wing.
Span difference: and (3) serially arranging aircraft design indexes, representing the wingspan size of the front wing and the rear wing, and being the wingspan difference value of the front wing and the rear wing.
Flat wing: wings without sweep angle, this type of wing has a planar projection shape that is symmetrical along the wing centerline.
Mounting angles: the aerodynamic design index of the aircraft refers to the included angle between the chord line of the wing root of the aircraft wing and the central axis of the aircraft body, namely the front edge of the wing tilts upwards of the aircraft.
Aspect ratio: the aerodynamic design index of the aircraft is the ratio of the wingspan of the aircraft wing to the average chord length, and the larger the aspect ratio is, the more slender the fuselage is.
The ratio of the root to the tip: the aerodynamic design index of the aircraft is the ratio of the chord length of the wing tip of the aircraft wing to the chord length of the wing root.
Chord line: in the airfoil shape of the cross section of the airfoil, an auxiliary line connecting the most front edge point and the most rear edge point of the airfoil profile is a chord line.
Has the advantages that:
(1) By utilizing the tandem wing layout, the loading center of gravity of the aircraft is controlled between the front wing 21 and the rear wing 22, the loading point position of the aircraft is widened, the fuselage space is fully utilized, the requirement of large volume and high loading freight is met, and the problem of low loading efficiency of the existing loading aircraft is effectively solved; meanwhile, by controlling the parameters, the aspect ratio and the extension length of the airplane are reduced on the premise of not reducing the lift-drag ratio and the load capacity of the airplane.
(2) The existing tandem wing layout load-carrying aircraft can reduce the lift force of the rear wing 22 due to the downwash airflow action of the front wing 21.
By means of the design, the front wing 21 and the rear wing 22 are favorable for the spatial position of airflow interference, the lift force of the aircraft is improved, and the problem of low loading efficiency of the existing load-carrying aircraft is effectively solved.
(3) The existing tandem wing layout aircraft usually adopts a structural design that the rear landing gear 4 and the vertical tail wing 23 are independent, and the structure is complex.
According to the invention, the vertical tail wings 23 on two sides and the rear landing gear 4 are designed in a fusion manner, the vertical tail wings 23 are arranged at the rear lower part of the engine cabin 29, and the vertical tail wings 23 and the rear landing gear 4 are designed in a fusion manner, so that the propeller slipstream of the engine 222 is received, the rudder control effect is enhanced, and meanwhile, the rudder can be used as a buffer mechanism, the damage of impact on the structure of the aircraft body in the landing stage is reduced, the structure weight is greatly reduced, and the problems of the existing heavy structure and insufficient structure strength of the load-carrying aircraft can be effectively solved.
(4) The existing tandem wing layout aircraft realizes aircraft trim through a front wing and rear wing differential angle, and the final installation angle of the wing is not in a state of being capable of providing lift to the maximum extent due to the trim requirement.
The invention realizes zero lift moment balancing of the airplane by utilizing the spatial position configuration of the front wing 21 and the rear wing 22, greatly reduces balancing resistance, does not change the optimal mounting angle of the front wing 21 and the rear wing 22, and does not reduce the lift-drag ratio of the whole airplane.
In addition, the invention was experimentally validated for flight and aerodynamic simulation analysis was performed using fluid analysis software prior to experimental flight.
The optimum stagger angle of the front and rear airfoils 22 is obtained by software analysis. The relative spatial positions of the front wing 21 and the rear wing 22 are adjusted without changing the optimal mounting angle of the wings, and the trim is verified through software.
Software calculation and verification: as shown in fig. 8, it can be seen that the upper surfaces of the front wing 21 and the rear wing 22 are low-pressure areas, which are blue in color and generate suction, and the lower surfaces are red, which are high-pressure areas and generate pressure, which act together to generate the lift force of the aircraft;
more drastic color change is generated near the front edge 6 of the upper surface of the front wing 21, the eye span directions of the blue area are uniformly distributed, and the color change of the front edge 6 of the upper surface of the rear wing 22 is not obvious, so that the phenomenon that the downwash of the front wing 21 inhibits the upper surface of the rear wing 22, the pressure is increased, the lift force of the rear wing 22 is reduced, and the effect of reducing the low head moment trim is achieved; the rear wing 22 presents a distinct blue area near the tip of the wing, which is caused by the high energy vortex blowing accelerating airflow for the tip vortex effect of the front wing 21. Software calculation verifies that the designed tandem wing layout of the spatial installation positions of the front wing 21 and the rear wing 22 has an obvious effect on improving the wing lift force.
Test flight verification: the test flight results are successful, and the aircraft smoothly finishes takeoff, conventional flight line flight, special flight, low-altitude traffic field and landing. The flight performance of the aircraft is overall normal, the flight attitude is stable, and the aircraft can cruise according to the flight line, so that the aircraft balancing scheme can be realized, and the result calculated by the fluid analysis software is basically correct. The horizontal side direction posture of the aircraft basically has no special condition, and the verification wingtip winglet can improve the horizontal side stability. The landing success can also prove that the design strength of the landing gear and the vertical fin of the aircraft meet the actual requirements.
The foregoing is a preferred embodiment of the present invention, and it should be noted that modifications and embellishments could be made by those skilled in the art without departing from the principle of the present invention, and these modifications and embellishments are also regarded as the scope of the present invention.

Claims (10)

1. A high-efficiency high-maneuverability tandem wing layout heavy-duty aircraft, which is characterized in that,
comprises a main beam, a main wing and a vertical tail wing;
the main wings are arranged on the main beam;
the main wing comprises a front wing and a rear wing, and the front wing and the rear wing are respectively installed at two ends of the main beam;
the two vertical tail wings are respectively and symmetrically arranged on the left ventral surface and the right ventral surface of the rear wing, and the vertical tail wings are also provided with rear landing gears;
the two ends of the rear wing are provided with vertical stable panels; the side surface of the vertical fixing plate is vertically connected and fixed with the length direction of the rear wing;
the two unilateral front edges of the rear wing are both provided with engines, and propellers of the engines are aligned with the vertical tail wing;
and the rear edges of the front wing, the rear wing and the vertical tail wing are all provided with swing ailerons.
2. The tandem wing layout heavy-duty vehicle of claim 1,
the main beam is arranged between the ventral surface of the front wing and the back surface of the rear wing.
3. The tandem wing layout payload vehicle of claim 1,
the main beam is arranged between the back surface of the front wing and the ventral surface of the rear wing.
4. The tandem wing layout heavy-duty vehicle of any one of claims 2 to 3,
the wing difference angle between the front wing and the rear wing is 0.5-3 degrees;
the height difference of the front edge point of the front wing and the rear wing is 4-10% of the wingspan of the rear wing;
the difference of the wingspan of the front wing and the rear wing is 40-46% of the wingspan of the rear wing.
5. The tandem wing layout heavy-duty vehicle of claim 4,
the front wing and the rear wing are both straight wings.
6. The tandem wing layout payload vehicle of claim 4,
the wing area of the main wing is 0.3m 2 -1m 2 ；
The wing area of the vertical tail wing is 0.03m 2 -0.1m 2 。
7. The tandem wing layout payload vehicle of claim 6,
the mounting angle of the front wing is 2-5 degrees, the mounting angle of the rear wing is 2-5 degrees, and the mounting angle of the vertical tail wing is 0 degree;
the aspect ratio of the front wing, the rear wing and the vertical tail wing is 2-3, 2.5-3.5 and 0.5-1 respectively;
the tip-root ratios of the front wing, the rear wing and the vertical tail wing are respectively 0.3-0.8, 0.2-0.6 and 0.4-0.8.
8. The tandem wing layout heavy-duty vehicle of claim 1,
the vertical distance between the chord line of the vertical tail wing and the main beam is 36-40% of the single-side span.
9. The tandem wing layout heavy-duty vehicle of claim 1,
the wing of the main wing comprises a wing spar and a skin;
a plurality of wing ribs are uniformly arranged on the wing beam in the length direction;
the skin wraps the spar and the wing rib;
at the leading edge of the main wing, the spar, the wing rib and the skin form a closed D-box;
the main wing is provided with a lug piece at the center in the length direction of the main wing, and the lug piece is fixedly connected with the main beam;
the rear edge of the main wing is provided with an auxiliary wing beam, the auxiliary wing beam is fixedly connected with the wing rib of the wing, and the auxiliary wing beam is rotatably provided with the auxiliary wing;
an engine compartment is arranged on the rear wing, the engine compartment is fixedly connected with the wing beam, and the engine is mounted on the engine compartment.
10. The tandem wing layout heavy-duty vehicle of claim 9,
the rear landing gear comprises a rear wheel and a rear supporting rod; the vertical tail comprises an auxiliary wing plate and a vertical wing rib;
the rear wheel is rotatably connected with one end of the rear supporting rod, and the other end of the rear supporting rod is fixedly connected with the engine compartment;
a plurality of vertical wing ribs are arranged along the length direction of the rear supporting rod; the auxiliary wing plate is arranged at the rear edge of the vertical tail wing, and the auxiliary wing plate is fixedly connected with the vertical wing rib; the skin wraps the auxiliary wing plate and the vertical wing rib; the aileron plate is rotatably provided with the aileron;
the main beam is also provided with a nose landing gear which is arranged below the nose wing;
the nose landing gear comprises a nose wheel and a front support bar;
the front wheel is rotatably connected with one end of the front supporting rod, and the other end of the front supporting rod is fixedly connected with the main beam.
CN202210950996.7A 2022-08-09 2022-08-09 High-efficiency and high-maneuverability tandem wing layout load-carrying aircraft Pending CN115258131A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210950996.7A CN115258131A (en) 2022-08-09 2022-08-09 High-efficiency and high-maneuverability tandem wing layout load-carrying aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210950996.7A CN115258131A (en) 2022-08-09 2022-08-09 High-efficiency and high-maneuverability tandem wing layout load-carrying aircraft

Publications (1)

Publication Number Publication Date
CN115258131A true CN115258131A (en) 2022-11-01

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Family Applications (1)

Application Number Title Priority Date Filing Date
CN202210950996.7A Pending CN115258131A (en) 2022-08-09 2022-08-09 High-efficiency and high-maneuverability tandem wing layout load-carrying aircraft

Country Status (1)

Country Link
CN (1) CN115258131A (en)

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