A tandem wing vertical take-off and landing aircraft

Abstract

The application discloses a tandem wing type vertical take-off and landing aircraft, which comprises a fuselage, wings, lifting wings and landing gears. The fuselage is the main structure of the aircraft and adopts a streamline structure. The fuselage is internally provided with an aircraft cabin, an electric propulsion device cabin and a power system. The main wings and the lifting wings are arranged on the two sides of the front end and the rear end of the fuselage in a tandem wing layout, the length of the lifting wings is longer than that of the main wings, and the lifting wings are horizontally stretched, and a plurality of groups of propellers are arranged. The trailing edge of the wing tip of the main wing is provided with an aileron. The rolling moment generated by the differential deflection of the left and right ailerons can make the aircraft make lateral maneuvering. The landing gears are located at the bottom of the fuselage and comprise front landing gears and rear landing gears, which are used for supporting the aircraft when the aircraft is parked and slid on the ground. The aircraft has optimized lift distribution and aerodynamic coupling effect, improves the lift efficiency and stability, and enhances the safety and vertical take-off and landing capability. The load distribution of the aircraft is flexible and can adapt to various task requirements.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, in particular to a tandem wing vertical take-off and landing aircraft. BACKGROUND

[0002] With the accelerated development of urbanization, traffic congestion and environmental pollution have become global challenges. As an important solution for future urban air transportation, the tandem wing vertical take-off and landing aircraft has unique vertical take-off and landing capability, low noise, high efficiency, environmental protection and flexible flight mode. The tandem wing vertical take-off and landing aircraft can realize vertical take-off and landing without runway, greatly reducing the infrastructure demand, so that it can be flexibly applied in complex environments such as cities.

[0003] The main difficulties in the research and development of electric vertical take-off and landing aircraft include technical difficulties, safety and noise control, airspace restrictions, pricing strategy, actual utilization rate, battery technology and policy regulations. SUMMARY

[0004] Based on this, the embodiments of the present application provide a tandem wing vertical take-off and landing aircraft, aiming to improve flight performance, enhance safety, reduce noise and promote environmental protection, and explore new heights for urban air travel.

[0005] The present application provides a tandem wing vertical take-off and landing aircraft, which comprises a fuselage, wings, elevators and landing gear, specifically:

[0006] The fuselage is the main structure of the aircraft, adopts a streamlined structure, and is internally provided with an aircraft cabin, an electric propulsion device cabin and a power system. The power system is controlled by a control system inside the aircraft cabin to drive vertical take-off and landing.

[0007] The wings include main wings, ailerons and elevators. The main wings and elevators are arranged on both sides of the front and rear ends of the fuselage in tandem wing layout, and the length of the elevators extending transversely exceeds that of the main wings. A plurality of propellers are symmetrically arranged on the top of the main wings and elevators with the fuselage as the central axis. The trailing edge of the main wings is provided with ailerons, and the trailing edge of the elevators is provided with elevators, which are used to increase lift by changing the camber of the ailerons and elevators.

[0008] A vertical tail is connected at the central axis of the rear end of the fuselage and the bottom of the elevator. The vertical tail includes a fixed vertical stabilizer and a movable rudder.

[0009] The landing gear is located at the bottom of the fuselage and includes front landing gear and rear landing gear, which are used to support the aircraft when it is parked and sliding on the ground.

[0010] The power system is arranged inside the main body of the fuselage and includes an electric motor, a tilting frame, a main controller, a power system comprehensive display instrument, a propeller group, a battery group and a power management system.

[0011] Optionally, the electric motor is a lightweight air-cooled permanent magnet synchronous motor for directly driving the propeller.

[0012] Optionally, the motor mounting frame in the power system is a welded structure, and the motor mounting frame, the fuselage frame, the motor, and the electronic speed controller are all connected by bolts; the motor and the propeller set can generate a forward pulling force or a downward thrust through the action of the tilting structure, realizing vertical take-off and landing.

[0013] Optionally, the instruments in the aircraft cockpit use mechanical flight instruments and power comprehensive display instruments; the control system uses a push-pull steel cable form.

[0014] Optionally, a single-lever linkage central control column is provided in the aircraft cockpit, the front is an instrument panel, and the central control console between the two seats has a throttle lever and a brake handle, a fire extinguisher bottle is provided on the left side of the windshield frame, and the seat backrest angle is 26°.

[0015] Optionally, the instrument panel specifically includes a multifunction display, a backup display instrument, a backup display instrument label, a radio, a switch control panel, a switch control panel label, an altitude speedometer, a flight manual label, a sideslip instrument, a pilot warning label, an airspeed indicator, an altimeter, and a magnetic compass.

[0016] Optionally, the front landing gear is linked with the rudder in a spring damping form, and the main landing gear uses a leaf spring damping.

[0017] Optionally, the fuselage skin, the wing skin, and the tail skin of the aircraft are foam sandwich structures, and are formed by vacuum bag pressing.

[0018] The spars, the rear wall, the root ribs, the bulkheads, the cockpit, and the fairing are laminated structures, and are partially carbon sandwich structures, and are formed by vacuum bag pressing.

[0019] Optionally, the aircraft uses a full composite material structure, and the structural materials at least include carbon fibers and glass fibers.

[0020] Optionally, the aircraft monitors and controls defects and deformations of composite parts by using a grating reflection spectrum differentiation method and a multi-stage thermodynamic cycle method.

[0021] The technical scheme provided by the embodiments of the present application has at least the following beneficial effects:

[0022] (1) Improved flight performance: by optimizing the lift distribution and aerodynamic coupling effect, the aerodynamic performance of the aircraft is enhanced, the lift efficiency and stability are improved, and the flight performance is improved.

[0023] (2) Enhanced safety: The use of a distributed electric propulsion system and an intelligent flight control system based on AI algorithms improves the safety and vertical take-off and landing capabilities of the aircraft. Through the implementation of safety and redundancy design, the safety performance of the aircraft is further enhanced.

[0024] (3) Reduce noise and promote environmental protection: The use of low-noise rotor design and noise suppression technology, as well as the design and application of environmentally friendly electric drive systems, effectively reduces the noise generated by the aircraft during operation. At the same time, the use of electric drive reduces environmental pollution, embodying the concept of environmental protection.

[0025] (4) Flexible task adaptability: Due to flexible load distribution, equipment can be arranged at different positions on the front and rear wings or fuselage according to different task requirements, making the aircraft adaptable to various tasks such as business, tourism, medical rescue, and fire fighting, with high task adaptability and use flexibility. BRIEF DESCRIPTION OF DRAWINGS

[0026] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description are only exemplary, and for those skilled in the art, other drawings can be derived from the provided drawings without creative labor.

[0027] Figure 1 A tandem wing vertical take-off and landing aircraft provided by the embodiment of the present application is shown in the schematic diagram.

[0028] Figure 2 A front view of a tandem wing vertical take-off and landing aircraft provided by the embodiment of the present application is shown in the schematic diagram.

[0029] Figure 3 A top view of a tandem wing vertical take-off and landing aircraft provided by the embodiment of the present application is shown in the schematic diagram.

[0030] Figure 4 A left view of a tandem wing vertical take-off and landing aircraft provided by the embodiment of the present application is shown in the schematic diagram.

[0031] Reference signs: 1-fuselage, 2-main wing, 3-elevon, 4-propeller, 5-landing gear, 6-aileron. DETAILED DESCRIPTION

[0032] In order to make the purpose, technical solutions and advantages of the present application more clear and explicit, the following will further describe the present application in combination with the drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and do not limit the present application.

[0033] In the description of the present application, the terms "comprising", "having", and any variations thereof, are intended to cover a non-exclusive inclusion, for example, a process, method, system, product or apparatus that includes a list of steps or units not necessarily limited to those explicitly listed, but can also include other steps or units inherent to such processes, methods, products or apparatus, or steps or units added based on further optimization of the inventive concept.

[0034] It provides a possibility to solve urban traffic congestion, improve travel efficiency and reduce carbon emissions. This technical disclosure aims to describe an innovative tandem wing VTOL aircraft design in detail, which aims to improve flight performance, enhance safety, reduce noise and promote environmental protection, and explore new heights for urban air travel.

[0035] The overall design (aerodynamic and structural) of the tandem wing VTOL aircraft, flight control system, power and energy system, vertical take-off mechanism, conversion flight mode technology, safety and redundancy design, material and lightweight technology, noise and environmental protection measures, etc. Many aspects. Specifically, it includes but is not limited to the following technical points:

[0036] 1. The overall structure of the tandem wing VTOL aircraft design has the characteristics of significant aerodynamic performance advantages. First, the lift distribution optimization allows the front and rear wings to bear different stages of lift requirements, which helps to improve the overall lift efficiency. Second, the stability is enhanced by the aerodynamic coupling effect between the front and rear wings, which can reduce the influence of turbulence. In addition, the load distribution is flexible, and equipment can be arranged at different positions of the front and rear wings or the fuselage according to task requirements. Finally, by adjusting the distance, area and angle of the front and rear wings, etc. Parameters can effectively control the aerodynamic resistance of the UAV;

[0037] 2. Distributed electric propulsion technology, our aircraft uses a distributed electric propulsion system, which distributes the generation of thrust by installing propellers at multiple locations on the aircraft. This design not only simplifies the structure and reduces the weight, but also improves the safety and vertical take-off capability of the aircraft;

[0038] 3. Intelligent flight control system based on AI algorithm;

[0039] 4. Combination of high-performance electric motors and battery packs;

[0040] 5. Seamless conversion technology between vertical take-off and horizontal cruising;

[0041] 6. The tandem wing layout design has its advantages in specific applications. In vertical take-off fixed-wing aircraft, this layout can combine the advantages of fixed-wing and multi-rotor, realize long endurance, large payload and fast cruising speed, and at the same time, get rid of the dependence on take-off and landing sites;

[0042] 7. Specific embodiments of security and redundancy design;

[0043] 8. Application and structure optimization of lightweight composite materials;

[0044] 9. Low-noise rotor design and noise suppression technology;

[0045] 10. Design and application of environmentally friendly electric drive system.

[0046] Specifically, as Figure 1 , the application discloses a tandem wing vertical take-off and landing aircraft, which comprises:

[0047] The aircraft comprises a fuselage 1, wings and a landing gear 5, the wings specifically comprising a main wing 2, an elevator 3 and ailerons 6, and specifically: the fuselage 1 is the main structure of the aircraft, adopts a streamlined structure, and is internally provided with an aircraft cabin, an electric propulsion device cabin and a power system, wherein the power system is controlled by a control system inside the aircraft cabin to drive vertical take-off and landing.

[0048] The wings comprise the main wing 2, the elevator 3 and the ailerons 6, the main wing 2 and the elevator 3 are arranged on both sides of the front end and the rear end of the fuselage in a tandem wing layout, the length of the elevator extending transversely exceeds the length of the main wing extending transversely, and a plurality of groups of propellers are symmetrically arranged on the top of the main wing and the elevator with the fuselage as the central axis. The vertical take-off and landing and hovering of the aircraft are realized by adjusting the rotating speed of the propellers.

[0049] The trailing edge of the main wing is provided with ailerons, and the trailing edge of the elevator is provided with elevators, which are used to increase the lift by changing the camber of the ailerons and the elevators; a vertical tail is connected and arranged at the central axis of the rear end of the fuselage and the bottom of the elevator, and the vertical tail comprises a fixed vertical stabilizer and a movable rudder.

[0050] The landing gear 5 is located at the bottom of the fuselage 1 and comprises a front landing gear and a rear landing gear, which are used to support the aircraft when it is parked and slid on the ground;

[0051] The power system is arranged in the main body of the fuselage 1 and comprises an electric motor, a main controller, a power system comprehensive display instrument, a battery pack and a power management system.

[0052] The structure of the tandem wing vertical take-off and landing aircraft mainly adopts a full composite material structure, and the structural materials mainly comprise carbon fibers and glass fibers, and the design concept of green environmental protection, vertical take-off, low cost and low noise is paid attention to in the design. The body structure mainly comprises the fuselage 1, the wing and the landing gear 5. The overall arrangement of the aircraft is as shown in Figure 1 , in addition Figure 2 , Figure 3 , Figure 4 Three views of the tandem wing vertical take-off and landing aircraft are given, wherein Figure 2is a front view, Figure 3 is a top view, Figure 4 is a left view.

[0053] The vertical take-off and landing aircraft adopts a cantilever large aspect ratio upper tandem wing, full-tilt six-electric-motor, propeller combination layout, hidden circular tail, front three-point fixed landing gear, tilting propeller, and 5-seat side-opening door layout. The power device is six permanent magnet motors (tilt mechanism), the speed is adjusted by motor controller, the power source is solid-state battery; the aircraft structure is made of high-performance carbon fiber composite material; the instrument adopts mechanical flight instrument and power comprehensive display instrument; the control system adopts push-pull steel cable form. The above is the overall design of the electric vertical take-off and landing aircraft.

[0054] The aircraft cabin has a single lever linkage central control column; the instrument panel specifically includes a multifunction display, a backup display instrument, a backup display instrument label, a radio, a switch control panel, a switch control panel label, an altitude and airspeed indicator, a flight manual label, a sideslip indicator, a pilot warning label, an airspeed indicator, an altimeter, and a magnetic compass. The central control table between the two seats has a throttle lever and a brake handle; the windshield frame left side has a fire extinguisher bottle; the seat backrest angle is 26°.

[0055] The aircraft adopts a full composite material structure mainly composed of carbon fiber and glass fiber, including a fuselage 1, wings, propellers 4, and landing gears. The fuselage 1 mainly includes an electric propulsion device cabin, a firewall, a cabin, a battery cabin, a partition frame, a circular vertical stabilizer, etc.; the wings 2 adopt a large aspect ratio tandem wing shape, which is composed of a main wing, a winglet, and an elevator. The main wing structure includes a wing skin, a wing spar, a rear wall, a root rib, and a general rib; the elevator structure includes a horizontal stabilizer and an elevator; the landing gear is composed of a front landing gear and a main landing gear. The front landing gear adopts a spring damping form and is linked with the rudder, and the main landing gear adopts a leaf spring damping form.

[0056] Specifically, in the structure of the present application, the wings of the aircraft are composed of a main wing, a winglet, and an elevator. The main wing is located at the front end of the fuselage, and the elevator is arranged at the rear end of the fuselage, forming a tandem wing layout. This layout allows the aircraft to obtain greater lift during vertical take-off and landing, while maintaining stability during horizontal flight.

[0057] Propeller configuration: multiple sets of propellers are symmetrically arranged on the top of the main wing and the elevator with the fuselage as the central axis. These propellers provide the necessary thrust during vertical take-off and landing, and assist in propulsion and control during horizontal flight.

[0058] Winglet and elevator: the trailing edge of the main wing is equipped with a winglet (winglet rudder), and the trailing edge of the elevator is equipped with an elevator. By changing the camber of the winglet and the elevator, the lift of the aircraft during take-off and landing can be increased, and the take-off and landing performance can be improved.

[0059] Vertical tail: The vertical tail is connected to the bottom of the lifting wing and the rear end of the fuselage, including a fixed vertical stabilizer and a movable rudder. The vertical stabilizer provides directional stability, while the rudder is used to control the direction of the aircraft, ensuring directional control during flight.

[0060] The vertical take-off and landing aircraft power system includes: electric motor, tilt frame, main controller, power system integrated display instrument; propeller, battery pack, battery management system (BMS). A practical and safe aircraft electric propulsion system based on new rare earth permanent magnet motor and high efficiency solid state battery is developed, forming a high efficiency integration technology of motor drive system, power battery and propeller.

[0061] The light-weight air-cooled permanent magnet synchronous motor has very high continuous torque density and high efficiency, and can be used to directly drive the propeller. At a speed of about 1000 r / min, its continuous power can reach 130 kW, and its efficiency is 97%, and its weight is 30.6 kg.

[0062] The motor mounting frame is a welded structure, and the motor mounting frame, the fuselage frame, the motor, and the electronic speed controller are connected by bolts. The motor and the propeller can generate a forward pulling force of the aircraft (aircraft cruising flight mode) through the action of the tilting structure. At the same time, under the action of the tilting structure, the motor and the propeller axis are converted to an angle of 90 degrees with the horizontal line, so that the motor drives the propeller to generate a downward thrust, completing the vertical take-off of the aircraft (take-off and landing mode). After completing the cruising flight mode of the aircraft, the tilting structure is converted to the take-off and landing mode again, and the power output of the motor is reduced, and the aircraft slowly lands and lands on the ground.

[0063] The aircraft adopts a relatively mature process system, taking manual laying, vacuum bag pressing, hot press forming, and connection assembly as the basis of composite material process manufacturing technology. The leaf spring is a laminated plate structure, which is formed by hot press. The fuselage skin, wing skin, and tail skin are foam plate sandwich structures, which are formed by vacuum bag pressing. The beams, walls, ribs, partitions, cockpits, and fairings are laminated structures, and some are carbon plate sandwich structures, which are formed by vacuum bag pressing. Metal parts are self-developed and outsourced.

[0064] The whole machine uses a jig assembly to position and support key components such as wings, fuselage, and lifting wings. Combined with horizontal measurement and laser tracking three-coordinate measurement equipment, the assembly is calibrated to meet the design accuracy requirements. The machine body is fixed to the jig, and the connection parts are fixed or glued. For the first time, a new principle and method of monitoring and controlling composite defects and deformation by using grating reflection spectrum differentiation and multi-stage thermal cycle method are proposed, which greatly reduces the curing defects and deformation of composite components, ensuring lightweight, low cost, and process stability.

[0065] The vertical take-off and landing aircraft has been manufactured according to the design drawings since July 2022, with a scale of 1:4. Two complete machines and several test pieces have been manufactured. The production drawings, process files, and manufacturing records during the manufacturing process are complete. We have also conducted manufacturing compliance checks on the test pieces used for verification tests and the vertical take-off and landing aircraft according to the type qualification approval procedures required by the review team, and are preparing to obtain approval for manufacturing compliance review from the bureau. It has excellent low-speed characteristics and vertical take-off and landing performance, and is suitable for aircraft rental, cargo transportation, aerial photography, aerial surveying and mapping, power line inspection, rescue, tourism, and other tasks, and also meets the flight needs of private flight enthusiasts and business. The tandem wing vertical take-off and landing aircraft has a wingspan of 15.18 meters, a take-off weight of 2210 kilograms, a maximum endurance of 600 kilometers, a maximum cruise speed of 280 kilometers / hour, and an altitude of over 1000 meters, making it a perfect aircraft for the country's low-altitude economy initiative. It does not require a runway for take-off and landing, and is a unique aircraft that can take off and land in place, demonstrating its excellent low-speed characteristics and safe and stable landing performance.

[0066] By analyzing the application scenarios of this product and promoting its product features, we can attract more potential customers. At the same time, we need to develop different service customization plans based on user needs, such as business, tourism, medical rescue, and fire fighting. In summary, the development of tandem wing vertical take-off and landing aircraft technology requires coordination and development from all aspects. In the future, with the continuous progress of technology and the continuous expansion of the market, it is not impossible for tandem wing vertical take-off and landing aircraft to become a new mode of air travel or to achieve development in the fields of medical care, fire fighting, and logistics.

[0067] The technical features of the above-described embodiments can be combined in any manner. To make the description concise, not all possible combinations of the technical features in the above-described embodiments are described, but as long as the combinations of the technical features do not conflict, they should be considered within the scope of the present disclosure.

[0068] The above-described embodiments only express several implementation manners of the present application, and the description is more specific and detailed, but it should not be construed as a limitation on the scope of the patent application. It should be noted that for ordinary skilled persons in the art, without departing from the concept of the present application, a number of modifications and improvements can be made, which are within the scope of the present application. Therefore, the scope of the patent of the present application should be subject to the appended claims.

Claims

1. A tandem-wing vertical takeoff and landing aircraft, characterized in that, Specifically: The fuselage is the main structure of the aircraft and adopts a streamlined structure. The fuselage contains the aircraft cockpit, electric propulsion unit compartment and power system. The power system is controlled by the control system inside the aircraft cockpit to drive vertical take-off and landing. The wings include main wings, ailerons, and elevators. The main wings and elevators are located on the front and rear sides of the fuselage, respectively. The main wings and elevators adopt a tandem wing layout, and the lateral extension of the elevators exceeds the lateral extension of the main wings. Multiple propellers are symmetrically arranged on the top of the main wings and elevators with the fuselage as the central axis. Ailerons are located on the trailing edge of the main wings, and elevators are located on the trailing edge of the elevators, which are used to increase lift by changing the camber of the ailerons and elevators. A vertical tail is installed at the rear of the fuselage and at the bottom center axis of the elevator. The vertical tail includes a fixed vertical stabilizer and a movable rudder. The landing gear is located at the bottom of the fuselage and includes the nose landing gear and the rear landing gear, which are used to support the aircraft when it is parked and taxiing on the ground; The power system is located inside the main body of the fuselage and includes an electric motor, a main controller, a power system integrated display instrument, a battery pack, and a power management system. The aircraft uses an all-composite material structure, with structural materials including at least carbon fiber and glass fiber.

2. The tandem-wing vertical takeoff and landing aircraft according to claim 1, characterized in that, The electric motor is a lightweight, air-cooled permanent magnet synchronous motor used to directly drive the propeller.

3. The tandem-wing vertical takeoff and landing aircraft according to claim 2, characterized in that, The motor mounting bracket in the power system is a welded structure, and the motor mounting bracket is bolted to the fuselage frame, the motor, and the ESC compartment. The motor and propeller assembly can generate forward thrust or downward thrust through the tilting structure, enabling vertical takeoff and landing.

4. The tandem-wing vertical takeoff and landing aircraft according to claim 1, characterized in that, The aircraft cockpit instruments are a combination of mechanical flight instruments and power display instruments; the control system is a push-pull cable system.

5. The tandem-wing vertical takeoff and landing aircraft according to claim 4, characterized in that, The aircraft cockpit features a single-lever central control stick, with the instrument panel in front. The throttle lever and brake lever are located on the central control panel between the two seats. A fire extinguisher is located on the left side of the windshield frame, and the seat back angle is 26°.

6. The tandem-wing vertical takeoff and landing aircraft according to claim 4, characterized in that, The instrument panel specifically includes a multifunction display, backup display instrument, backup display instrument sign, radio, switch control panel, switch control panel sign, vertical speedometer, flight manual sign, sideslip indicator, pilot warning sign, airspeed indicator, altimeter, and magnetic compass.

7. The tandem-wing vertical takeoff and landing aircraft according to claim 1, characterized in that, The nose landing gear uses spring damping in conjunction with the rudder, while the main landing gear uses leaf spring damping.

8. The tandem-wing vertical takeoff and landing aircraft according to claim 1, characterized in that, The fuselage skin, wing skin, and tail skin of the aircraft are foam board sandwich structures, which are vacuum bag compression molded. The wing spars, rear wall, root ribs, bulkhead, cockpit, and fairing are laminated structures, with some areas being carbon plate sandwich structures, all formed using vacuum bag molding.

9. The tandem-wing vertical takeoff and landing aircraft according to claim 1, characterized in that, The aircraft uses grating reflection spectral heterogeneity and multi-stage thermodynamic cycling to monitor and control defects and deformations in composite material parts.

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