Composite wing vertical take-off and landing aircraft with tandem wing layout

Abstract

The invention relates to the technical field of aircrafts, and particularly discloses a tandem wing layout composite wing vertical take-off and landing aircraft which comprises a plate-rod thin-wall lifting body fuselage, a front wing, a rear wing, a power system, a flight control system and a power supply module, the power system comprises a first propelling device, a second propelling device and a third propelling device; the first propelling device is fixedly arranged in front of the plate-rod thin-wall lifting body; the second propelling device is fixedly arranged on the front wing, and the third propelling device is fixedly arranged on the rear wing; the first propelling device, the second propelling device and the third propelling device are electrically connected with the flight control system; the front wings and the rear wings are fixedly connected with the plate-rod thin-wall lifting body fuselage, and the front wings and the rear wings form a tandem wing layout; the composite wing vertical take-off and landing aircraft with the tandem wing layout is more uniform in aerodynamic force distribution and smaller in wing load, and the lift force efficiency can be effectively improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a composite wing vertical take-off and landing aircraft with a tandem wing layout. Background Art

[0002] Traditional rotorcraft rely on vertical propellers to provide lift and thrust to achieve vertical take-off and landing, and have good flexibility, but their flight speed and flight time are subject to many restrictions; fixed-wing aircraft have advantages such as higher forward flight speed and cruising efficiency, but are more restricted by terrain.

[0003] In order to meet the needs of logistics transportation in complex terrain between mountainous areas, a composite wing vertical take-off and landing aircraft with a tandem wing layout was developed by combining the characteristics of rotorcraft and fixed-wing aircraft. Summary of the Invention

[0004] The purpose of the present invention is to provide a composite wing vertical take-off and landing aircraft with a tandem wing layout.

[0005] To achieve the above object, the present invention adopts the following technical solutions:

[0006] A composite wing vertical take-off and landing aircraft with a tandem wing layout comprises a plate-rod thin-wall lifting body fuselage, a front wing, a rear wing, a power system, a flight control system and a power supply module.

[0007] The power system includes a first propulsion device, a second propulsion device and a third propulsion device.

[0008] The first propulsion device is fixedly arranged in front of the fuselage of the plate-rod thin-wall lifting body, and the first propulsion device is used to provide horizontal thrust.

[0009] The second propulsion device is fixedly arranged on the front wing, and the third propulsion device is fixedly arranged on the rear wing. The second propulsion device and the third propulsion device are both used to provide vertical lift.

[0010] The third propulsion device is located directly behind the second propulsion device, and the first propulsion device and the second propulsion device are distributed in a triangle.

[0011] The first propulsion device, the second propulsion device and the third propulsion device are all electrically connected to the flight control system, and the power supply module is used to supply power to the first propulsion device, the second propulsion device, the third propulsion device and the flight control system.

[0012] The front wing and the rear wing are both fixedly connected to the plate-rod thin-wall lifting body fuselage, and the front wing and the rear wing form a tandem wing layout.

[0013] In the composite wing vertical take-off and landing aircraft with a tandem wing layout provided in at least one embodiment of the present disclosure, the plate-rod thin-wall lifting body fuselage includes: a top plate, a bottom plate, side plates and an anti-torsion and bending structure.

[0014] The top plate, the bottom plate and the side plates are constructed into a thin shell structure, and an accommodating space is formed inside the thin shell structure.

[0015] The flight control system and the power supply module are both fixedly arranged in the accommodating space.

[0016] The anti-torsion and bending structure is at least partially located in the accommodating space, and the top plate, the bottom plate and the side plates are all fixedly connected to the anti-torsion and bending structure.

[0017] The composite wing vertical take-off and landing aircraft with a tandem wing layout provided in at least one embodiment of the present disclosure further includes a landing gear.

[0018] The landing gear is fixedly connected to the base plate.

[0019] In the composite wing vertical take-off and landing aircraft with a tandem wing layout provided in at least one embodiment of the present disclosure, the anti-torsion bending structure includes: a front end plate, a rear end plate, a longitudinal main carbon tube, a front wing main carbon tube, and a rear wing main carbon tube.

[0020] The front end plate and the rear end plate are both fixedly connected to the longitudinal main carbon tube, and the front end plate and the rear end plate are both perpendicular to the longitudinal main carbon tube.

[0021] The front end plate and the rear end plate are both fixedly connected to the top plate, and the front end plate and the rear end plate are both fixedly connected to the bottom plate.

[0022] A first connecting frame and a second connecting frame are fixedly arranged on the longitudinal main carbon tube.

[0023] The front wing main carbon tube and the rear wing main carbon tube are fixedly connected to the first connecting frame and the second connecting frame respectively, and the front wing main carbon tube and the rear wing main carbon tube are both perpendicular to the front wing main carbon tube.

[0024] The front wing main carbon tube is inserted into the front wing, and the front wing main carbon tube is fixedly connected to the front wing.

[0025] The rear wing main carbon tube is inserted into the rear wing, and the rear wing main carbon tube is fixedly connected to the rear wing.

[0026] In the composite wing vertical take-off and landing aircraft with a tandem wing layout provided in at least one embodiment of the present disclosure, a third connecting frame is fixedly provided at the head end of the longitudinal main carbon tube.

[0027] The first propulsion device is fixedly connected to the third connecting frame.

[0028] In the composite wing vertical take-off and landing aircraft with a tandem wing layout provided in at least one embodiment of the present disclosure, the side panels are hollowed out.

[0029] In the composite wing vertical take-off and landing aircraft with a tandem wing layout provided by at least one embodiment of the present disclosure, both the front wing and the rear wing have ailerons and a drive device.

[0030] The driving device is connected to the aileron, and is used to drive the aileron to swing.

[0031] In the composite wing vertical take-off and landing aircraft with a tandem wing layout provided in at least one embodiment of the present disclosure, the plate-rod thin-wall lifting body fuselage has a vertical tail.

[0032] In the composite wing vertical take-off and landing aircraft with a tandem wing layout provided in at least one embodiment of the present disclosure, a rudder is provided on the vertical tail.

[0033] The rudder is electrically connected to the flight control system.

[0034] The beneficial effects of this invention include: combining the advantages of tandem configuration, lifting body configuration, and composite wing technology, achieving high lift coefficient, high lift-to-drag ratio, and large payload capacity. Furthermore, the aircraft's lifting body fuselage design significantly reduces interference drag and provides ample cargo space. Furthermore, the four wing control surfaces of the tandem wing can adopt hybrid control logic, whereby the four control surfaces and the propellers simultaneously control the aircraft's lift and roll, making the aircraft more flexible to control. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0036] Figure 1 The figure is a schematic diagram of the overall structure of a composite wing vertical take-off and landing aircraft with a tandem wing layout according to the present invention.

[0037] Figure 2 This is a block diagram of the connections of some components of a composite wing vertical take-off and landing aircraft with a tandem wing layout according to the present invention.

[0038] Figure 3 Schematic diagram of the structure of the torsion-resistant structure.

[0039] Figure 4 This is a side view of the plate-rod thin-walled lifting body fuselage.

[0040] In the picture:

[0041] 10. Plate-rod thin-wall lifting body fuselage; 11. Top plate; 12. Bottom plate; 13. Side plate; 14. Anti-torsion bending structure; 15. Vertical tail; 16. Rudder; 141. Front end plate; 142. Rear end plate; 143. Longitudinal main carbon tube; 144. Front wing main carbon tube; 145. Rear wing main carbon tube; 146. First connecting frame; 147. Second connecting frame; 148. Third connecting frame;

[0042] 20. Front wing; 21. Aileron; 22. Drive unit;

[0043] 30. Rear wing;

[0044] 40. Power system; 41. First propulsion device; 42. Second propulsion device; 43. Third propulsion device;

[0045] 50. Flight control system;

[0046] 60. Power supply module;

[0047] 70. Landing gear. DETAILED DESCRIPTION

[0048] The technical solutions in the embodiments will be described clearly and completely below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments, rather than all the embodiments.

[0049] Conventional aerodynamic configurations offer advantages in terms of cargo transport, including simple control methods, extensive analytical experience, and mature theories. However, conventionally designed aircraft have a wingspan approaching 3 meters, placing significant demands on wing strength. This significantly increases the difficulty of structural weight reduction and wing fabrication. Furthermore, the counterweight of conventionally designed aircraft limits the location and space for cargo holds. Furthermore, underwing cargo holds generate significant interference drag, impacting the overall aerodynamic configuration of the aircraft.

[0050] To this end, embodiments provide a composite wing vertical takeoff and landing aircraft with a tandem wing layout. Combining the advantages of a tandem configuration with a lifting body configuration and composite wing technology, the aircraft achieves a range of technical advantages, including a high lift coefficient, a high lift-to-drag ratio, and a large payload capacity. Furthermore, the aircraft utilizes a wide lifting body fuselage design, significantly reducing interference drag and providing ample cargo space. Furthermore, the four wing control surfaces of the tandem wing can utilize hybrid control logic, meaning that the four control surfaces and the propellers simultaneously control the aircraft's lift and roll, making aircraft control more flexible.

[0051] Example

[0052] like Figures 1 to 4As shown, this embodiment provides a composite wing vertical take-off and landing aircraft with a tandem wing layout, including a plate-rod thin-wall lifting body fuselage 10, a front wing 20, a rear wing 30, a power system 40, a flight control system 50, a power supply module 60 and a landing gear 70.

[0053] Specifically, the power system 40 includes a first propulsion device 41, a second propulsion device 42, and a third propulsion device 43. The first propulsion device 41 is fixedly mounted in front of the thin-walled lifting body 10 and is used to provide horizontal thrust. The second propulsion device 42 is fixedly mounted on the front wing 20, and the third propulsion device 43 is fixedly mounted on the rear wing 30. Both the second propulsion device 42 and the third propulsion device 43 are used to provide vertical lift. The third propulsion device 43 is located directly behind the second propulsion device 42, forming a triangular arrangement between the first and second propulsion devices 41 and 42.

[0054] Specifically, the front wing 20 and the rear wing 30 each have ailerons 21 and a drive device 22. The drive device 22 is connected to the ailerons 21 and is used to drive the ailerons 21 to swing. The plate-bar thin-walled lifting body fuselage 10 has a vertical tail 15. The vertical tail 15 is provided with a rudder 16.

[0055] Exemplarily, the driving device 22 is a steering gear, and the aileron 21 is fixedly connected to the output shaft of the steering gear.

[0056] In terms of wing structure, the front and rear wings use a basswood carbon fiber wing spar-carbon tube-EPP foam filling composite structure to resist the lift load and torsional load of the wing; the wing-body fusion transition surface has a complex curved shape and mainly bears torsional loads, so a new lightweight PLA material is used and produced using a 3D printing process; the wingtip adopts a 3D printing foam material process because of its twisted geometric shape and complex force.

[0057] In this embodiment, the first propulsion device 41, the second propulsion device 42, the third propulsion device 43, the drive device 22 and the rudder 16 are all electrically connected to the flight control system 50, and the power supply module 60 is used to supply power to the first propulsion device 41, the second propulsion device 42, the third propulsion device 43, the drive device 22, the rudder 16 and the flight control system 50.

[0058] In this embodiment, the front wing 20 and the rear wing 30 are both fixedly connected to the plate-bar thin-wall lifting body fuselage 10, and the front wing 20 and the rear wing 30 form a tandem wing layout. The landing gear 70 is fixedly connected to the bottom plate 12.

[0059] The structure of the plate-rod thin-wall lifting body fuselage 10 will be further disclosed below with reference to the accompanying drawings.

[0060] like Figure 4As shown, the plate-and-stem thin-walled lifting body fuselage 10 utilizes a KT-plate thin-walled structure. It comprises a top panel 11, a bottom panel 12, side panels 13, and a torsional bending structure 14. These panels form a thin shell structure, enhancing the fuselage's torsional rigidity. The shell also defines a storage space within the structure.

[0061] Specifically, the top plate 11 and the bottom plate 12 are both KT plates; two side plates 13 are configured, and the side plates 13 are made of PLA material.

[0062] Specifically, the flight control system 50 and the power supply module 60 are fixedly disposed in the accommodation space. The anti-torsion structure 14 is partially located in the accommodation space, and the top plate 11 , the bottom plate 12 and the side plates 13 are fixedly connected to the anti-torsion structure 14 .

[0063] Specifically, the side panels 13 adopt a hollow design to further reduce the weight of the fuselage.

[0064] The structure of the anti-torsion structure 14 will be further disclosed below with reference to the accompanying drawings.

[0065] like Figure 3 As shown, the anti-torsion structure 14 includes: a front end plate 141 , a rear end plate 142 , longitudinal main carbon tubes 143 , front wing main carbon tubes 144 and rear wing main carbon tubes 145 .

[0066] Specifically, the front end plate 141 and the rear end plate 142 are both fixedly connected to the longitudinal main carbon tube 143, and the front end plate 141 and the rear end plate 142 are both perpendicular to the longitudinal main carbon tube 143. The front end plate 141 and the rear end plate 142 are both fixedly connected to the top plate 11; similarly, the front end plate 141 and the rear end plate 142 are both fixedly connected to the bottom plate 12.

[0067] Specifically, a first connecting frame 146 and a second connecting frame 147 are fixedly mounted on longitudinal main carbon tubes 143. Front wing main carbon tubes 144 and rear wing main carbon tubes 145 are fixedly connected to first connecting frame 146 and second connecting frame 147, respectively. Front wing main carbon tubes 144 and rear wing main carbon tubes 145 are both perpendicular to front wing main carbon tubes 144.

[0068] Furthermore, the front wing main carbon tube 144 is inserted into the front wing 20 and fixedly connected to the front wing 20 ; the rear wing main carbon tube 145 is inserted into the rear wing 30 and fixedly connected to the rear wing 30 .

[0069] Furthermore, a third connecting frame 148 is fixedly provided at the head end of the longitudinal main carbon tube 143 ; the first propulsion device 41 is fixedly connected to the third connecting frame 148 .

[0070] The power scheme of the composite wing vertical take-off and landing aircraft with a tandem wing layout will be disclosed below.

[0071] According to the requirements of aerodynamic design indicators for the geometric dimensions of the aircraft, the maximum wingspan of the aircraft is defined as 2.4m and the length is 1.3m; from the perspective of aircraft load configuration, center of gravity allocation and balance design; on the one hand, considering that the main available load volume of the fuselage is in the front middle part, the rear space is relatively narrow and the aircraft power group is placed in the front of the aircraft, the position of the aircraft's lift center should be in the front middle of the fuselage to achieve maximum cargo hold space; the aircraft's external dimensions and lift center position diagram are shown in the appendix.

[0072] Due to the flow field disturbances between the front and rear wings, the lift of the rear wing is reduced, and its effective lift area is essentially equal to that of the front wing. Therefore, the aircraft's wingset design features a smaller front wing and a larger rear wing. The front wing is positioned near the nose of the slat-and-stem thin-walled lifting body fuselage, while the rear wing is positioned at the tail. To provide ample cargo space, the lift section width of the slat-and-stem thin-walled lifting body fuselage is set at 540mm. The wing design adopts a trapezoidal geometry to achieve optimal low-speed aerodynamic efficiency, reduce induced drag caused by spanwise flow, and facilitate manufacturing.

[0073] A composite wing vertical take-off and landing scheme was adopted in which a propeller was added to the front side of the wing to provide lift. Considering that the lift during the cruising flight phase and the vertical take-off phase should be greater than the sum of the body weight and the air resistance, that is,

[0074] T≥mg+F 阻 ;

[0075] The total lift is provided by four propellers, take F 阻 = 0.2mg, and the lift provided by a single propeller should be no less than 2.2kg. The motor selected is an X3520 motor, KV1250, and the propeller size is selected as 10*6.

[0076] Although the embodiments of the present application have been shown and described above, the scope of protection of the present invention is not limited thereto, and any changes or substitutions that are not conceivable through creative work should be included in the scope of protection of the present invention; unless expressly stated, any elements, actions or instructions used in this document should not be interpreted as critical or necessary.

Claims

1. A composite wing vertical take-off and landing aircraft with a tandem wing layout, characterized in that: include: Plate-rod thin-wall lifting body fuselage, front wing, rear wing, power system, flight control system and power supply module; The power system includes a first propulsion device, a second propulsion device and a third propulsion device; The first propulsion device is fixedly arranged in front of the fuselage of the plate-rod thin-wall lifting body, and the first propulsion device is used to provide horizontal thrust; The second propulsion device is fixedly arranged on the front wing, and the third propulsion device is fixedly arranged on the rear wing, and the second propulsion device and the third propulsion device are both used to provide vertical lift; The third propulsion device is located directly behind the second propulsion device, and the first propulsion device and the second propulsion device are distributed in a triangle; The first propulsion device, the second propulsion device, and the third propulsion device are all electrically connected to the flight control system, and the power supply module is used to supply power to the first propulsion device, the second propulsion device, the third propulsion device, and the flight control system; The front wing and the rear wing are both fixedly connected to the plate-rod thin-wall lifting body fuselage, and the front wing and the rear wing form a tandem wing layout.

2. The tandem wing layout composite wing vertical take-off and landing aircraft according to claim 1, characterized in that: The plate-rod thin-wall lifting body fuselage comprises: Top plate, bottom plate, side plate and anti-torsion bending structure; The top plate, bottom plate and side plates are constructed into a thin shell structure, and a receiving space is formed inside the thin shell structure; The flight control system and the power supply module are both fixedly arranged in the accommodation space; The anti-torsion and bending structure is at least partially located in the accommodating space, and the top plate, the bottom plate and the side plates are all fixedly connected to the anti-torsion and bending structure.

3. The composite wing vertical take-off and landing aircraft with a tandem wing layout according to claim 2, characterized in that: Also includes landing gear; The landing gear is fixedly connected to the base plate.

4. The composite wing vertical take-off and landing aircraft with a tandem wing layout according to claim 2, characterized in that: The anti-torsion bending structure comprises: Front end plate, rear end plate, longitudinal main carbon tube, front wing main carbon tube and rear wing main carbon tube; The front end plate and the rear end plate are both fixedly connected to the longitudinal main carbon tube, and the front end plate and the rear end plate are both perpendicular to the longitudinal main carbon tube; The front end plate and the rear end plate are both fixedly connected to the top plate, and the front end plate and the rear end plate are both fixedly connected to the bottom plate; A first connecting frame and a second connecting frame are fixedly provided on the longitudinal main carbon tube; The front wing main carbon tube and the rear wing main carbon tube are fixedly connected to the first connecting frame and the second connecting frame respectively, and the front wing main carbon tube and the rear wing main carbon tube are both perpendicular to the front wing main carbon tube; The front wing main carbon tube is inserted into the front wing, and the front wing main carbon tube is fixedly connected to the front wing; The rear wing main carbon tube is inserted into the rear wing, and the rear wing main carbon tube is fixedly connected to the rear wing.

5. The composite wing vertical take-off and landing aircraft with a tandem wing layout according to claim 4, characterized in that: A third connecting frame is fixedly provided at the head end of the longitudinal main carbon tube; The first propulsion device is fixedly connected to the third connecting frame.

6. The composite wing vertical take-off and landing aircraft with a tandem wing layout according to claim 2, characterized in that: The side panels are hollowed out.

7. The composite wing vertical take-off and landing aircraft with a tandem wing layout according to claim 1, characterized in that: The front wing and the rear wing both have ailerons and drive devices; The driving device is connected to the aileron, and is used to drive the aileron to swing.

8. The composite wing vertical take-off and landing aircraft with a tandem wing layout according to claim 1, characterized in that: The plate-rod thin-wall lifting body fuselage is provided with a vertical tail.

9. The composite wing vertical take-off and landing aircraft with a tandem wing layout according to claim 8, characterized in that: The vertical tail is provided with a rudder; The rudder is electrically connected to the flight control system.

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