A blended wing body aircraft

Abstract

The utility model relates to the field of aircraft technology discloses a kind of wing-body fusion aircraft, including wing-body fusion body of fuselage and wing fusion, multiple rotor propellers and propelling propeller, the end of wing is provided with winglet, the tail of wing-body fusion body is equipped with flat tail on both sides, tail top middle is equipped with vertical tail;Multiple rotor propellers include two front rotor propellers embedded in two mounting holes of wing and two rear rotor propellers symmetrically arranged at the front end of flat tail, two rear rotor propeller outer is equipped with surrounding baffle ring;Propelling propeller includes two propeller blades coaxially arranged in front and back and motor for driving two propeller blades to rotate respectively, and the rotating direction of two propeller blades is opposite to offset counter torque.The utility model uses wing-body fusion body, rotor propeller, the aerodynamic layout of double-shaft common propeller reverse-rotation type propelling propeller, reduces air resistance, improves aerodynamic efficiency, improves flight stability.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, specifically to a blended wing-body aircraft. Background Technology

[0002] Unmanned aerial vehicles (UAVs) are a general term for unmanned aerial vehicles. With the development of technology, UAVs have experienced explosive growth in both military and civilian fields. UAVs include rotary-wing UAVs, fixed-wing UAVs, and compound-wing UAVs. Fixed-wing UAVs rely on their wings to generate lift, similar to traditional aircraft. They require a certain speed to maintain flight and are typically powered by propellers or jet engines. They lack vertical takeoff and landing (VTOL) capabilities and require runways or catapults for takeoff and landing via taxiing or parachute. Fixed-wing UAVs are the most widely used due to their advantages of long flight time, high payload capacity, and high speed. Rotary-wing UAVs directly provide lift through multiple rotors (usually 4-8), supporting VTOL. They use motors to drive propellers, adjusting rotation speed to control attitude and position, offering advantages such as high flexibility, convenient takeoff and landing, and simple operation. However, they have significant limitations in payload, flight time, speed, and range. Compound-wing UAVs combine the advantages of fixed-wing and multi-rotor systems, enabling VTOL in multi-rotor mode and efficient cruise in fixed-wing mode. However, the aerodynamic layout of existing compound-wing UAVs still has shortcomings, and aerodynamic efficiency needs further optimization. Utility Model Content

[0003] The purpose of this invention is to address the aforementioned problems by providing a blended wing-body aircraft, thus resolving the issues in the background technology.

[0004] To achieve the above objectives, the technical solution adopted by this utility model is as follows: A blended wing-body aircraft, comprising:

[0005] A blended wing-body fuselage, wherein the fuselage and wings are integrated, and the wings are provided with winglets at their tips; the blended wing-body fuselage has horizontal tails on both sides of its tail and a vertical tail in the middle of the top of its tail.

[0006] Multiple rotors are used to provide vertical lift power, including two front rotors and two rear rotors. The wing of the blended wing-body body is symmetrically provided with mounting holes for embedding the two front rotors. The two rear rotors are symmetrically arranged on both sides of the front end of the horizontal stabilizer. The two rear rotors are surrounded by retaining rings.

[0007] The propulsion propeller is located at the tail of the blended wing-body and is used to provide the thrust required for level flight. The propulsion propeller includes two propeller blades arranged coaxially and a motor for driving the two propeller blades to rotate respectively. The two propeller blades rotate in opposite directions and cancel out the counter-torque by rotating in opposite directions.

[0008] Furthermore, the wing has a relative thickness of 3% to 4%, a tip-to-root ratio of 0.2 to 0.3, a leading-edge sweep angle of 45° to 50°, and a trailing-edge sweep angle of 5° to 8°.

[0009] Furthermore, the relative thickness of the flat tail is 10% to 12%, the tip-to-root ratio is 0.5 to 0.6, the leading edge sweep angle is 5° to 10°, and the trailing edge sweep angle is 0° to 3°.

[0010] Furthermore, the single-side span of the horizontal stabilizer is 40% to 50% of the single-side span of the wing.

[0011] Furthermore, the relative thickness of the vertical tail is 5% to 6%.

[0012] Furthermore, the wingtip has a relative thickness of 1% to 2% and an outward cant angle of 16°.

[0013] Furthermore, the mounting hole is located on the wing-body blended body near the junction of the fuselage and the wing.

[0014] Furthermore, the front rotor propeller and the rear rotor propeller are arranged symmetrically front to back.

[0015] Furthermore, a wheeled landing gear is installed on the bottom surface of the blended wing-body.

[0016] By adopting the above technical solution, this utility model has the following beneficial effects:

[0017] The aircraft of this utility model adopts an aerodynamic layout of a blended wing-body structure in which the fuselage and wings are integrated. There is no clear dividing line between the fuselage and wings. Both the fuselage and wings can generate lift. The blended wing-body structure can significantly reduce the wetted area and induced drag, increase the lifting surface and thus improve the lift-drag ratio. In addition, with the horizontal and vertical tails, the maximum lift coefficient is increased and the flight stability is improved.

[0018] The aircraft of this utility model adopts a fixed-wing and rotor propeller take-off and landing layout, which has both vertical take-off and landing function and the performance of fixed-wing aircraft. It can play a dual flight mode function and achieve a highly efficient aerodynamic layout. Of the four rotor propellers, the first two rotor propellers are located in the middle of the wing, and the last two rotor propellers are surrounded by a design. This design ensures that the airflow under the rotor propellers will not hit the wing when the aircraft is in flight, reducing airflow resistance and greatly improving the aerodynamic efficiency of the motor. It has higher aerodynamic efficiency.

[0019] The tail propeller of this invention uses a coaxial dual-propeller design. The two propellers rotate in opposite directions to cancel out the counter-torque, thereby achieving a more stable and safer flight operation. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the structure of a blended wing-body aircraft according to the present invention;

[0021] Figure 2 This is a top view of a blended wing-body aircraft according to the present invention;

[0022] Figure 3 This is a front view of a blended wing-body aircraft according to the present invention;

[0023] Figure 4 This is a left view of a blended wing-body aircraft according to the present invention;

[0024] In the diagram: 1-Blended wing-body, 2-Winglet, 3-Horizontal stabilizer, 4-Vertical stabilizer, 5-Propeller, 6-Mounting hole, 7-Rotor propeller, 8-Enclosure ring, 9-Wheel landing gear. Detailed Implementation

[0025] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the art to which the present invention pertains. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the present invention. The terms "first," "second," etc., in the specification, claims, and accompanying drawings of the present invention are used to distinguish different objects and not to describe a particular order. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or device that includes a series of steps or units is not limited to the listed steps or units, but may optionally include steps or units not listed, or may optionally include other steps or units inherent to these processes, methods, products, or devices.

[0026] In this document, the term "embodiment" means that a particular feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of the present invention. The appearance of this phrase in various places throughout the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described herein can be combined with other embodiments.

[0027] like Figures 1-4 As shown, a blended wing-body aircraft includes a blended wing-body 1, multiple rotor propellers 77, and a propulsion propeller 5.

[0028] The fuselage and wings of the blended wing-body 1 are integrated, and the wingtips are provided with winglets 2 at the ends of the wings; horizontal tails 3 are provided on both sides of the tail of the blended wing-body 1, and vertical tail 4 is provided in the middle of the top of the tail of the blended wing-body 1.

[0029] Multiple rotors 7 provide vertical lift power, including two front rotors 7 and two rear rotors 7. The wing of the blended wing-body 1 has symmetrically arranged mounting holes 6 for embedding the two front rotors 7, and the two rear rotors 7 are symmetrically arranged on both sides of the front end of the horizontal stabilizer 3. The two rear rotors 7 are surrounded by retaining rings 8. In this embodiment, the mounting holes 6 are located on the blended wing-body 1 near the junction of the fuselage and wing. The front and rear rotors 7 are symmetrically arranged. Each rotor 7 includes rotor blades and a motor for driving the rotor blades.

[0030] Of the four rotors 7, the first two are positioned between the wings, while the latter two are arranged in a surrounding design. This design prevents airflow below the rotors 7 from hitting the wings during flight, reducing air resistance and significantly improving the aerodynamic efficiency of the motors. The surrounding design of the rotors also protects the aircraft's safety while achieving a highly efficient aerodynamic layout. The design of the rotors 7 and wings combines vertical takeoff and landing capabilities with the performance of a fixed-wing aircraft, enabling dual flight modes and providing more safe flight options.

[0031] The propulsion propeller 5, located at the tail of the blended wing-body 1, provides the thrust required for level flight. The propulsion propeller 5 includes two coaxially arranged propeller blades and motors that drive each blade. The two propeller blades rotate in opposite directions, canceling out counter-torque through this counter-rotation. Using coaxial dual propellers as the aircraft's forward propulsion, and utilizing their counter-rotation to counteract counter-torque, achieves a more stable and safer flight operation.

[0032] The wing has a relative thickness of 3%–4%, a tip-to-root ratio of 0.2–0.3, a leading-edge sweep angle of 45°–50°, and a trailing-edge sweep angle of 5°–8°. Leading-edge sweep reduces shock wave drag, while trailing-edge sweep increases the wing chord length and wing area, ensuring sufficient lift.

[0033] The horizontal stabilizer 3 has a relative thickness of 10%–12%, a tip-to-root ratio of 0.5–0.6, a leading-edge sweep angle of 5°–10°, and a trailing-edge sweep angle of 0°–3°. The single-side span of the horizontal stabilizer 3 is 40%–50% of the single-side span of the wing.

[0034] The relative thickness of the vertical tail 4 is 5% to 6%.

[0035] Among them, the winglet 2 has a relative thickness of 1% to 2% and an outward cant angle of 16° to 20°.

[0036] In this embodiment, a wheeled landing gear 9 is mounted on the bottom surface of the blended wing-body 1. The wheeled landing gear 9 consists of one front wheel and two rear wheels. The front wheel controls the direction of the vehicle when taxiing on the ground, while the rear wheels bear the main weight and control the braking. Preferably, the wheeled landing gear 9 is a shock-absorbing spring-loaded wheeled landing gear.

[0037] This utility model adopts an aerodynamic layout of a wing-body blended body 1, which integrates the fuselage and wings, and can significantly reduce the wetted area and induced drag, increase the lifting surface and thus improve the lift-to-drag ratio; it adopts a take-off and landing layout with fixed wings and rotor propellers 7, which has both vertical take-off and landing capabilities and the performance of a fixed-wing aircraft, and can achieve dual flight mode functionality, thus achieving a highly efficient aerodynamic layout; the propulsion propeller at the tail of the aircraft adopts a coaxial dual propeller as the forward propulsion of the aircraft, and the two propellers rotate in opposite directions to cancel out the anti-torque.

[0038] The above description is a detailed explanation and illustration of the preferred embodiments of the present utility model. However, these descriptions are not intended to limit the scope of protection claimed by the present utility model. All equivalent changes or modifications made under the technical teachings of the present utility model shall fall within the patent protection scope covered by the present utility model.

Claims

1. A blended wing-body aircraft, characterized in that, include: A blended wing-body fuselage, wherein the fuselage and wings are integrated, and the wings are provided with winglets at their tips; the blended wing-body fuselage has horizontal tails on both sides of its tail and a vertical tail in the middle of the top of its tail. Multiple rotors are used to provide vertical lift power, including two front rotors and two rear rotors. The wing of the blended wing-body body is symmetrically provided with mounting holes for embedding the two front rotors. The two rear rotors are symmetrically arranged on both sides of the front end of the horizontal stabilizer. The two rear rotors are surrounded by retaining rings. The propulsion propeller is located at the tail of the blended wing-body and is used to provide the thrust required for level flight. The propulsion propeller includes two propeller blades arranged coaxially at the front and rear and a motor for driving the two propeller blades to rotate respectively. The two propeller blades rotate in opposite directions to counteract the counter torque.

2. The blended wing-body aircraft according to claim 1, characterized in that: The wing has a relative thickness of 3% to 4%, a tip-to-root ratio of 0.2 to 0.3, a leading-edge sweep angle of 45° to 50°, and a trailing-edge sweep angle of 5° to 8°.

3. A blended wing-body aircraft according to claim 1, characterized in that: The flat tail has a relative thickness of 10% to 12%, a tip-to-root ratio of 0.5 to 0.6, a leading edge sweep angle of 5° to 10°, and a trailing edge sweep angle of 0° to 3°.

4. A blended wing-body aircraft according to claim 1 or 3, characterized in that: The horizontal stabilizer has a single-side span of 40% to 50% of the wing's single-side span.

5. A blended wing-body aircraft according to claim 1, characterized in that: The relative thickness of the vertical tail is 5% to 6%.

6. A blended wing-body aircraft according to claim 1, characterized in that: The winglet has a relative thickness of 1% to 2% and an outward cant angle of 16° to 20°.

7. A blended wing-body aircraft according to claim 1, characterized in that: The mounting holes are located on the blended wing-body near the junction of the fuselage and the wing.

8. A blended wing-body aircraft according to claim 1, characterized in that: The front rotor and rear rotor are symmetrically arranged front and rear.

9. A blended wing-body aircraft according to claim 1, characterized in that: The bottom surface of the blended wing-body is equipped with wheeled landing gear.

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