Compound wing aircraft

Abstract

The application relates to the technical field of aircrafts, and discloses a compound wing aircraft. The compound wing aircraft comprises a fuselage, a left wing and a right wing connected to the fuselage, at least two pairs of linear support members, each pair of linear support members being connected to the left wing and the right wing, wherein the at least two pairs of linear support members are arranged with multiple lift propellers, and the lift propellers are electrically driven, a front wing connected to the at least two pairs of linear support members, and a rear wing connected to the at least two pairs of linear support members, a front end of the at least two pairs of linear support members is provided with at least one pair of pull propellers, and the at least one pair of pull propellers are driven by an engine, and / or a rear end of the at least two pairs of linear support members is provided with at least one pair of thrust propellers, and the at least one pair of thrust propellers are driven by the engine. The compound wing aircraft realizes the carrying of a large number of passengers or goods, a long distance of voyage, and higher safety and stability.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and more particularly to a compound wing aircraft. Background Technology

[0002] While existing compound wing aircraft possess both vertical takeoff and landing (VTOL) and fixed-wing flight modes, most currently cannot provide sufficient lift in VTOL mode, and their endurance is limited. In other words, existing compound wing aircraft are limited by the number of linear support components and propellers, allowing them to carry only a few people and have limited flight distances. There has always been a need for new aircraft to meet the needs of transporting large numbers of people and / or cargo, and to achieve longer ranges, thereby achieving greater economic benefits. Summary of the Invention

[0003] The purpose of this application is to provide a compound wing aircraft that can carry a large number of passengers or cargo, have a longer range, and achieve higher safety and stability.

[0004] To address the aforementioned technical problems, this application provides a compound wing aircraft, comprising: a fuselage; a left wing and a right wing connected to the fuselage; at least two pairs of linear support members, each pair of linear support members being connected to the left wing and the right wing respectively, wherein the at least two pairs of linear support members are equipped with a plurality of lift propellers, and the lift propellers are electrically driven; a fore wing and a rear wing, the fore wing being connected to the at least two pairs of linear support members, and the rear wing being connected to the at least two pairs of linear support members; at least one pair of thrust propellers are disposed at the front end of the at least two pairs of linear support members, and the at least one pair of thrust propellers are driven by an engine; and / or, at least one pair of thrust propellers are disposed at the rear end of the at least two pairs of linear support members, and the at least one pair of thrust propellers are driven by an engine.

[0005] Optionally, the number of the at least two pairs of linear support members is three pairs, and the three pairs of linear support members are symmetrically arranged on both sides of the fuselage, with each linear support member having at least four lift propellers.

[0006] Optionally, a tension propeller is provided at the front end of each linear support member, and at least one thrust propeller is provided at the rear end of each linear support member, both of which are driven by an engine.

[0007] Optionally, the front wing and the rear wing are respectively disposed on the front and rear sides of the fuselage, wherein the front wing is connected to the three pairs of linear support members, and the rear wing is connected to the three pairs of linear support members.

[0008] Optionally, both the forewing and the aft wing are provided with multiple control surfaces for controlling the pitch of the aircraft.

[0009] Optionally, the forewing is located in front of the fuselage and is not directly connected to the fuselage, and the rear wing is located behind the fuselage and is not directly connected to the fuselage.

[0010] Optionally, the rear ends of the at least two pairs of linear support members are provided with vertical stabilizers, and the vertical stabilizers are arranged opposite to each other.

[0011] Optionally, the at least one pair of pull propellers and the at least one pair of thrust propellers can rotate at different speeds to achieve active yaw of the aircraft.

[0012] Optionally, it may also include a pod detachably attached to the fuselage for carrying passengers or cargo.

[0013] Optionally, the at least two pairs of linear support members are arranged longitudinally in parallel.

[0014] The compound wing aircraft of this application enables the transport of a large number of passengers or cargo, a longer range, and greater safety and stability. Attached Figure Description

[0015] Figure 1 The diagram shown is a structural schematic of a compound wing aircraft according to an embodiment of this application.

[0016] Figure 2 The diagram shown is a structural schematic of a compound wing aircraft according to an embodiment of this application.

[0017] Figure 3 The diagram shown is a structural schematic of a compound wing aircraft according to an embodiment of this application.

[0018] Figure 4 The diagram shown is a structural schematic of a compound wing aircraft according to an embodiment of this application.

[0019] Figure 5 The diagram shown is a structural schematic of a compound wing aircraft according to an embodiment of this application. Detailed Implementation

[0020] The following embodiments further illustrate the technical solutions of this application. It should be understood that the specific embodiments described herein are merely for explaining this application. Furthermore, it should be noted that, for ease of description, only the parts relevant to this application are shown in the accompanying drawings, not all of them.

[0021] The terms used in this specification to describe the various embodiments are to be understood not only in their commonly defined meanings, but also, by their specific definitions in this specification, to include structures, materials, or actions that extend beyond their commonly defined meanings. Therefore, if an element is to be understood in the context of this specification to include more than one meaning, its use in the claims must be understood to apply universally to all possible meanings supported by the specification and by its own terminology.

[0022] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature being directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0023] The term "aircraft" is defined as an air transport system of any size having at least one lift propeller as its propulsion source. The term "aircraft" can include both "manned" and "unmanned" air transport systems. A manned aircraft can mean an air transport system carrying one or more human passengers, none of whom have control over the aircraft. A manned aircraft can also mean an air transport system carrying one or more human passengers, some of whom, or one of whom, has partial or full control over the aircraft. An unmanned aircraft can mean an air transport system that does not carry any human passengers and flies autonomously or is remotely controlled by someone at a distance.

[0024] The term "compound wing aircraft" is defined as an air transport system of any size that has at least one propeller as its propulsion source. The term "compound wing aircraft" can include both "manned" and "unmanned" air transport systems. A manned compound wing aircraft can refer to an air transport system carrying one or more human passengers, none of whom have control over the compound wing aircraft. A manned compound wing aircraft can also refer to an air transport system carrying one or more human passengers, some of whom, or one of whom, has partial or full control over the compound wing aircraft. An unmanned compound wing aircraft can refer to an air transport system that does not carry any human passengers and flies autonomously or is remotely controlled by someone at a distance.

[0025] The term "fixed wing" is defined as a non-rotating wing on an aircraft that generates lift due to the forward airspeed of the aircraft and the shape of the fixed wing.

[0026] The accompanying drawings illustrate various embodiments of the compound wing aircraft. It should be noted, in particular, that other types of aircraft are envisioned to implement many of the inventive features described herein, in addition to those shown in the drawings.

[0027] like Figure 1 As shown, this application provides a compound wing aircraft 100, including: a fuselage 110, a left wing 121 and a right wing 122 connected to the fuselage 110, three pairs of linear support members 130, and a canard wing 141 and a rear wing 142. The left wing 121 and the right wing 122 are symmetrically arranged on both sides of the fuselage 110 along the longitudinal axis of the fuselage 110. The left wing 121 and the right wing 122 are non-rotatable relative to the fuselage 110 and provide lift for the aircraft during level flight. Each pair of linear support members 130 is symmetrically arranged on both sides of the fuselage 110 and is respectively connected to the left wing 121 and the right wing 122. Each linear support member 130 is equipped with four lift propellers 140, all of which are driven by electric motors, and each motor is independently powered by a rechargeable battery.

[0028] The canard 141 connects to the front end of three pairs of linear support members 130, and the aft 142 connects to the rear end of the three pairs of linear support members 130. A thrust propeller 241, driven by an engine, is located at the front end of each linear support member 130; a thrust propeller 242, also driven by an engine, is located at the rear end of each linear support member 130. The engine is powered by fossil fuels, allowing for a greater flight range compared to electric propulsion while carrying the same weight of batteries.

[0029] In some embodiments, the motors of the thrust propeller 241 and the push propeller 242 may also be partially electrically driven.

[0030] In some embodiments, such as Figure 1 As shown, a pod 220 can also be detachably attached to the fuselage 110. The pod 220 is used for carrying passengers or cargo, and can also carry other functions, such as installing other recording devices, deployment devices, or other instruments and equipment. It is conceivable that in some embodiments, a thrust propeller 242 is also provided at the rear of the pod 220 to increase the cruising thrust.

[0031] The linear support 130 can house motors (not shown in the figure), each driving a corresponding lift propeller 140. The four lift propellers on each linear support are spaced apart, and a total of 24 lift propellers can be arranged on the three pairs of linear supports. This provides more lift to carry larger and heavier pods 220, enabling the compound wing aircraft of this application to become a so-called "air bus," for example, capable of carrying 30 passengers at a time. Furthermore, each lift propeller 140 can be independently powered, and the larger number of lift propellers 140 significantly improves the resistance to partial failure risks, enhancing the flight safety of the compound wing aircraft.

[0032] In one embodiment, the motors of 24 lift propellers are combined to form a 6x4 motor matrix array, which integrates the control of each motor into a unified motor matrix control system. Under the control system of artificial intelligence, control efficiency can be improved and control costs can be simplified.

[0033] In one embodiment, each linear support 130 is provided with more lift propellers 140, such as six or more, to increase load capacity.

[0034] In one embodiment, the fuselage 110 is detachably connected to the left wing 121 and the right wing 122, facilitating maintenance and replacement. In another embodiment, the fuselage 110 is integrally formed with the left wing 121 and the right wing 122, which improves structural integrity.

[0035] In some embodiments, such as Figure 1 As shown, three pairs of linear support members 130 are arranged parallel to the fuselage 110 and symmetrically on both sides of the fuselage 110. The length of each of the three pairs of linear support members 130 is greater than the length of the fuselage 110. The three pairs of linear support members are arranged longitudinally parallel to each other.

[0036] The forewing 141 connects the front ends of three pairs of linear support members 130, with the connection point between the forewing 141 and the linear support members 130 close to the front thrust propeller 241. In one embodiment, all linear support members 130 extend forward beyond the forewing 141, facilitating the installation of the thrust propeller 241 in the extended portion. The rearwing 142 connects the rear ends of the three pairs of linear support members 130. In one embodiment, all linear support members 130 extend rearward beyond the rearwing 142, facilitating the installation of the thrust propeller 242 in the extended portion. In this manner, the forewing 141 and rearwing 142 connect the front and rear ends of the linear support members 130 respectively, improving the structural integrity of the aircraft 100, increasing structural strength, and enhancing safety and reliability. In another embodiment, the connection point between the forewing 141 and the linear support members 130 can also be far away from the thrust propeller 241, and the connection point between the rearwing 142 and the linear support members 130 can also be far away from the thrust propeller 242.

[0037] Additionally, the canard 141 is located in front of the fuselage 110 and is not connected to the fuselage 110. The rear wing 142 is located behind the fuselage 110 and is not connected to the fuselage 110. In one embodiment, for example... Figure 2 and Figure 3 As shown, the forewing 141 and the rearwing 142 can be composed of two separate parts, each of which is connected only to three linear support members 130 on one side of the fuselage 110. While ensuring structural strength, this can reduce the processing cost of the forewing 141 or the rearwing 142 and also achieve weight reduction.

[0038] In some embodiments, the location and orientation of the motor are not limited. In this embodiment, the lift propellers 140 are all disposed on the top of the linear support 130; in one embodiment, they may also be disposed on the bottom of the linear support 130.

[0039] Both the fore wing 141 and the rear wing 142 are provided with multiple control surfaces 150 for controlling the pitch of the aircraft 100. The control surfaces 150 are disposed between the inner linear support members 130. In one embodiment, the fore wing 141 includes five control surfaces 150. The rear wing 142 includes five control surfaces 150. The control surfaces 150 are used to control the pitch of the aircraft 100. The five control surfaces 150 at both ends can improve the maneuverability of the aircraft, increase control redundancy, and enhance safety and reliability.

[0040] In one embodiment, such as Figure 1 As shown, vertical stabilizers 310 are provided at the rear ends of the three pairs of linear support members 130, and the six vertical stabilizers 310 are arranged in parallel relative to each other. Each of the six vertical stabilizers is provided with a steering surface, which can serve as a control unit for steering. The six control units also increase control redundancy and improve safety and reliability. In one embodiment, the six vertical stabilizers extend downwards. In another embodiment, the vertical stabilizers can also be configured to extend upwards.

[0041] In one embodiment, the 10 control surfaces 150 of the forewing 141 and the aft 142 and the 6 steering surfaces of the six vertical stabilizers 310 together constitute a three-dimensional control system. Under the control system of artificial intelligence, control costs can be simplified, control efficiency can be improved, and control stability can be enhanced.

[0042] In one embodiment, the linear support 130 consists of two pairs. For example... Figure 4As shown, the compound wing aircraft 100 includes: a fuselage 110, a left wing 121 and a right wing 122 connected to the fuselage 110, two pairs of linear support members 130, and a canard wing 141 and a rear wing 142. The left wing 121 and the right wing 122 are symmetrically arranged on both sides of the fuselage 110 along the longitudinal axis of the fuselage 110. The left wing 121 and the right wing 122 are non-rotatable relative to the fuselage 110 and provide lift for the aircraft during level flight. Each pair of linear support members 130 is symmetrically arranged on both sides of the fuselage 110 and is connected to the left wing 121 and the right wing 122 respectively. Each linear support member 130 is equipped with four lift propellers 140, all of which are driven by electric motors, each of which is independently powered by a rechargeable battery.

[0043] In one embodiment, for example Figure 5 As shown, the rear wing 142 can be composed of two separate parts, each of which is connected to two linear support members 130 on one side of the fuselage 110. While ensuring structural strength, this reduces the processing cost of the rear wing 142 and also achieves a weight reduction effect.

[0044] The fuselage of the aircraft provided in this application is preferably made of carbon fiber material, which has a certain degree of ductility and toughness. While enhancing the strength of the fuselage, carbon fiber material itself has a certain degree of toughness and ductility, which can be used to resist some of the torque and air resistance applied to the fuselage during flight.

[0045] Each linear support component can be made of suitable materials to withstand the physical demands of flight and resist the torsion caused by various pressures generated during flight. Such materials include natural and synthetic polymers, various metals and metal alloys, natural materials, textile fibers, glass, and ceramic materials.

[0046] In the aircraft provided in this application, each linear support is parallel to the longitudinal axis of the fuselage 110, so that the propellers arranged on each linear support are parallel to each other, thereby providing optimal stability and redundancy. When a propeller on a linear support fails, it is only necessary to shut down the corresponding propeller on the other linear support opposite the failed propeller, so that the remaining working propellers can be kept in balance, allowing the aircraft to remain in the air.

[0047] In one embodiment, such as Figure 1 As shown, an airspeed meter 400 is installed at the forward-facing end of the canard 141. In addition, an airspeed meter (not shown in the figure) can also be installed at the front of the linear support 130. Multiple airspeed meters can ensure system redundancy and improve safety and reliability.

[0048] The multiple thrust and pull propellers arranged in the three pairs of linear support members of this application embodiment can provide more powerful thrust, enabling the compound wing aircraft of this design to become a so-called "air bus" that can carry dozens of people at a time. Furthermore, the multiple thrust and pull propellers provide different thrust ratios to generate asymmetrical thrust. The asymmetrical thrust can control the aircraft to actively yaw, thereby adding another yaw control channel. When the lift motor yaw control cannot be guaranteed, it can be achieved through multiple thrust and pull propellers, which increases control redundancy and improves safety and reliability.

[0049] The above embodiments are merely illustrative of the principles and effects of this application. Any person skilled in the art can modify or alter the above embodiments without departing from the purpose of this application. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the purpose disclosed in this application should still be covered by the claims of this application.

Claims

1. A compound wing aircraft, characterized in that, include: Fuselage (110); left wing (121) and right wing (122) connected to said fuselage (110); At least two pairs of linear support members (130), each pair of linear support members (130) being connected to the left wing (121) and the right wing (122) respectively, wherein the at least two pairs of linear support members (130) are provided with a plurality of lifting propellers (140), and the lifting propellers (140) are electrically driven; A front wing (141) and a rear wing (142), wherein the front wing (141) is connected to the at least two pairs of linear support members (130) and the rear wing (142) is connected to the at least two pairs of linear support members (130); At least one pair of thrust propellers (241) are provided at the front end of the at least two pairs of linear support members (130), and the at least one pair of thrust propellers (241) are driven by an engine; and / or, at least one pair of thrust propellers (242) are provided at the rear end of the at least two pairs of linear support members (130), and the at least one pair of thrust propellers (242) are driven by an engine.

2. The compound wing aircraft according to claim 1, characterized in that, The number of the at least two pairs of linear support members (130) is three pairs, and the three pairs of linear support members (130) are symmetrically arranged on both sides of the fuselage (110), and each linear support member (130) is provided with at least four lift propellers (140).

3. The compound wing aircraft according to claim 2, characterized in that, Each linear support (130) has a tension propeller (241) at its front end and at least one thrust propeller (242) at its rear end. Both the tension propeller (241) and the thrust propeller (242) are driven by an engine.

4. The compound wing aircraft according to claim 2, characterized in that, The forewing (141) and the rearwing (142) are respectively disposed on the front and rear sides of the fuselage (110), wherein the forewing (141) is connected to the three pairs of linear support members (130), and the rearwing (142) is connected to the three pairs of linear support members (130).

5. The compound wing aircraft according to claim 1, characterized in that, Both the fore wing (141) and the rear wing (142) are provided with multiple control surfaces (150) for controlling the pitch of the aircraft.

6. The compound wing aircraft according to claim 1, characterized in that, The forewing (141) is located in front of the fuselage (110) and is not directly connected to the fuselage (110). The rearwing (142) is located behind the fuselage (110) and is not directly connected to the fuselage (110).

7. The compound wing aircraft according to claim 1, characterized in that, Vertical stabilizers (310) are provided at the rear ends of the at least two pairs of linear support members (130), and each of the vertical stabilizers (310) is arranged opposite to each other.

8. The compound wing aircraft according to claim 1, characterized in that, The at least one pair of pull propellers (241) and the at least one pair of thrust propellers (242) can rotate at different speeds to enable active yaw of the aircraft.

9. The compound wing aircraft according to claim 1, characterized in that, It also includes a pod (220) that can be detachably attached to the fuselage (110) for carrying passengers or cargo.

10. The compound wing aircraft according to claim 1, characterized in that, The at least two pairs of linear support members (130) are arranged in parallel longitudinally.

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