Combination method of modular components of aircraft and aircraft

Abstract

The invention belongs to the field of aircrafts, and discloses a method for combining modular components of an aircraft, which comprises the following steps: providing an aircraft flying platform which is provided with a left fixed wing and a right fixed wing; a left canard and a right canard; the avionics cabin is jointed with the left fixed wing and the right fixed wing; the left inner side arm is used for connecting the left fixed wing and the left canard wing; the right inner side arm is used for connecting the right fixed wing with the right canard; the left inner side arm is provided with first, second and third lift propellers and a left vertical fin; the right inner side arm is provided with a fourth lift propeller, a fifth lift propeller, a sixth lift propeller and a right vertical fin; according to the requirement for cruise load increase, the aircraft modular assembly is selected to be installed under the condition that the structure of an aircraft flying platform is not changed, so that different function and task requirements of the aircraft are met.

Description

Method for assembling modular components of aircraft and aircraft Technical Field

[0001] The present invention relates to the field of aircraft, and in particular to a method for assembling modular components of an aircraft and an aircraft. Background Art

[0002] With the development of electric technology, eVTOL (Electric Vertical Takeoff and Landing) aircraft have become a new form of aerial transportation, offering a powerful path to developing new dimensions of aerial space. Due to their vertical takeoff and landing capabilities, eVTOL aircraft do not require a runway, making them adaptable to a variety of temporary takeoff environments. This lack of a runway also eliminates the need for dedicated airports for eVTOL aircraft takeoffs, placing higher demands on their maintenance and overhaul.

[0003] During actual use, it was found that most of the existing aircraft are of integrated design and the installation and disassembly of the aircraft require specialized technicians. In order to cope with sudden and different working conditions, such as air taxis and air ambulances, a combination method of aircraft modular components and an aircraft are provided.

[0004] Summary of the Invention

[0005] The purpose of the present invention is to provide a method for assembling modular components of an aircraft and an aircraft in accordance with the requirement of increasing cruising load, so that the modular components of the aircraft can be selected and installed without changing the structure of the aircraft flight platform. The operation method is simple and meets the different functions and mission requirements of the aircraft.

[0006] To achieve this object, the present invention adopts the following technical solutions:

[0007] A method for assembling modular components of an aircraft, comprising:

[0008] Provided is an aircraft flight platform, comprising: a left fixed wing and a right fixed wing; a left canard and a right canard; an avionics compartment coupled to the left fixed wing and the right fixed wing; a left inner arm connecting the left fixed wing and the left canard; a right inner arm connecting the right fixed wing and the right canard; the left inner arm having first, second, and third lift propellers and a left vertical tail; the right inner arm having fourth, fifth, and sixth lift propellers and a right vertical tail;

[0009] According to the requirement of increasing cruising load, modular components of the aircraft are selected to be installed without changing the structure of the aircraft flight platform to meet the different functions and mission requirements of the aircraft.

[0010] Preferably, the modular components of the aircraft include a quickly detachable canard outer section. When it is required to increase the lift of the aircraft in the fixed-wing state by 10% to 20% based on the original lift value obtained by the applicable aircraft flight platform, the quickly detachable canard outer section is selected to be installed on the inner arm.

[0011] Preferably, the modular components of the aircraft include quickly detachable outer arms. When it is required to increase the lift of the aircraft in the rotor state by 20% to 70% based on the original lift value obtained by the applicable aircraft flight platform, the quickly detachable outer arms are selected for installation.

[0012] Preferably, the installation method of the quickly detachable outer arm includes: installing the outer arm on the leading edge of the left fixed wing and the right fixed wing, or installing the outer arm on the trailing edge of the left fixed wing and the right fixed wing, or installing the outer arm on the leading edge and trailing edge of the left fixed wing and the right fixed wing respectively.

[0013] Preferably, the left canard, the left inner arm, the avionics compartment, the right inner arm, and the right canard are combined into an A-type fuselage, which significantly improves the mounting structural rigidity of the first four motors of the fuselage.

[0014] Preferably, the cross-sectional shape of the arm is streamlined, which can reduce the formation of vortices when the propeller downwash is disturbed by the aircraft fuselage, thereby reducing the loss of the lift motor.

[0015] Preferably, the canard outer section includes a positioning member and a locking member. After the canard outer section is installed at a fixed position of the inner arm through the positioning member, the canard outer section and the inner arm are locked by the locking member.

[0016] Preferably, the distance between the outer arm and the inner arm is at least greater than the sum of the rotation radius of the lift propeller installed on the inner arm, the rotation radius of the lift propeller installed on the outer arm, and the convection gap.

[0017] Preferably, the convection gap is 8% to 15% of the maximum propeller diameter between the outer arm and the inner arm.

[0018] Preferably, the outer arm includes an arm recess, the cross section of which in the longitudinal direction is an inverted isosceles trapezoid, for adapting to the outer separation surface of the fixed-wing wing, and the outer separation surface of the fixed-wing wing has local carbon fiber reinforcement at the flange.

[0019] The present invention also provides an aircraft, which is applicable to the assembly method of aircraft modular components recorded in the above solution.

[0020] The beneficial effect of the present invention is that the present invention increases the lift of the aircraft in the fixed-wing state or the rotor-wing state by quickly adding the outer section of the canard or the outer arm without changing the structure of the aircraft flight platform through a modular combination method. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] FIG1 is a flow chart of the combination method of the present invention;

[0022] FIG2 is a schematic diagram of a UAV applicable to the combination method of the present invention;

[0023] FIG3 is a schematic diagram of the outer section of the canard of the present invention;

[0024] FIG4 is a schematic diagram of an outer machine arm of the present invention. DETAILED DESCRIPTION

[0025] The following embodiments further illustrate the technical solutions of the present application. It is understood that the specific embodiments described herein are merely for the purpose of explaining the present application. It should also be noted that, for ease of description, only portions relevant to the present application are shown in the accompanying drawings, not all of them.

[0026] In the description of this application, it should be noted that, unless otherwise specified or limited, the terms "mounted," "connected," and "connected" should be understood broadly. For example, they can refer to fixed or detachable connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in this application in specific contexts.

[0027] In this application, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features being in contact not directly but through another feature between them. Moreover, a first feature being "above," "above," and "above" a second feature may include the first feature being directly above or obliquely above the second feature, or may simply mean that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature may include the first feature being directly below or obliquely below the second feature, or may simply mean that the first feature is lower in level than the second feature.

[0028] The present application provides a method for assembling modular components of an aircraft, comprising:

[0029] An aircraft flight platform is provided, comprising: a left fixed wing and a right fixed wing; a left canard and a right canard; an avionics compartment connected to the left fixed wing and the right fixed wing; a left inner arm connecting the left fixed wing and the left canard; a right inner arm connecting the right fixed wing and the right canard; the left inner arm having first, second, and third lift propellers and a left vertical tail; and the right inner arm having fourth, fifth, and sixth lift propellers and a right vertical tail.

[0030] In response to the requirement of increased cruising payload, modular components of the aircraft are installed without changing the structure of the aircraft's flight platform to meet the different functions and mission requirements of the aircraft.

[0031] Specifically, the modular components of the aircraft include a quickly detachable canard outer section 100. When it is required to increase the lift of the aircraft in the fixed-wing state by 10% to 20% based on the original lift value obtained by the applicable aircraft flight platform, the quickly detachable canard outer section 100 is selected to be installed on the inner arm.

[0032] By adding the canard outer sections, the lift of the aircraft in fixed-wing mode can be increased by 10%-20% based on the original lift value obtained by the original aircraft flight platform. The installation of the quickly removable canard outer sections can overcome the nose-down effect during flight, avoiding undesirable pitching moments, thereby preventing the need to compensate for these pitching moments and affecting the UAV's flight efficiency. Furthermore, after the canard outer sections are installed, the structural combination of the canard outer sections and the original aircraft flight platform can increase the static stability margin of the aircraft by approximately 2%, thereby reducing the control losses of the flight control system.

[0033] Conversely, without changing the aircraft's flight platform structure, by quickly removing the canard outer sections, the aircraft's lift in fixed-wing mode can be quickly reduced, thus reducing energy consumption, if endurance is insufficient. Similarly, the aircraft's modular components include quickly detachable outboard arms 200. When the aircraft's lift in rotor mode is required to be increased by 20% to 70% over the original lift value achieved by the applicable aircraft flight platform, the quickly detachable outboard arms 200 are the preferred option.

[0034] The addition of outboard arms, on the one hand, requires the outer arms to be closer to the aircraft's centerline, reducing weight and freeing up space to increase power and payload. On the other hand, aerodynamic considerations dictate that when the propellers rotate, they generate corresponding airflow. If the outboard and inboard arms are mounted too close together, flow interference will occur, creating vortices that increase lift motor efficiency. Therefore, the outboard and inboard arms should be mounted close together. However, if they are too far apart, the aircraft's weight will inevitably increase. Therefore, a convection gap of 8% to 15% of the largest propeller diameter between the outboard and inboard arms balances the interference vortices generated between the outboard and inboard arms with the aircraft's weight, achieving both payload and aerodynamic efficiency.

[0035] Of course, without changing the structure of the aircraft's flight platform, by quickly disassembling the outer arms and the lift propellers on the outer arms, if there is insufficient endurance or noise reduction is required, the lift of the aircraft in the fixed-wing state can be quickly reduced, and energy consumption and noise decibels can be reduced.

[0036] Furthermore, the installation method of the quickly detachable outer arm 200 includes: installing the outer arm 200 on the leading edge of the left fixed wing and the right fixed wing, thereby increasing the lift of the aircraft in the rotor state by 20% to 40% based on the original lift value obtained by the aircraft flight platform; or installing the outer arm 200 on the trailing edge of the left fixed wing and the right fixed wing, thereby increasing the lift of the aircraft in the rotor state by 25% to 45% based on the original lift value obtained by the aircraft flight platform; or installing the outer arm 200 on the leading edge and trailing edge of the left fixed wing and the right fixed wing respectively, thereby increasing the lift of the aircraft in the rotor state by 50% to 70% based on the original lift value obtained by the aircraft flight platform.

[0037] Installed alone on the leading or trailing edge, it can adjust the aircraft's center of gravity to different positions.

[0038] Furthermore, the left canard, left inner arm, avionics compartment, right inner arm, and right canard are combined into an A-type fuselage. The closed structural design significantly improves the installation structural rigidity of the first four motors of the fuselage.

[0039] It is worth noting that the cross-section of the arm is streamlined, which can reduce the formation of vortices after the propeller downwash is disturbed by the aircraft fuselage, thereby reducing the loss of the lift motor.

[0040] Furthermore, the canard outer section 100 includes a positioning member 101 and a locking member 102 . After the canard outer section is mounted at a fixed position of the inner arm through the positioning member 101 , the canard outer section 100 and the inner arm are locked through the locking member 102 .

[0041] The positioning member 101 is used to quickly position the canard outer section 100 on the inner arm to save operation time, and then the locking member 102 is used to lock it to prevent the canard outer section 100 from being separated from the inner arm during the operation of the drone.

[0042] Illustratively, the distance between the outer arm 200 and the inner arm is at least greater than the sum of the rotation radius of the lift propeller installed on the inner arm, the rotation radius of the lift propeller installed on the outer arm 200 , and the convection gap.

[0043] Specifically, regarding the outboard arm 200, on the one hand, the overall structural design of the aircraft requires that the outboard arm be close to the aircraft's centerline to reduce the aircraft's weight and free up space to increase power and payload. On the other hand, due to aerodynamic requirements, when the propellers operate, they generate corresponding airflow. If the outboard arm 200 and the inboard arm are installed too close together, flow interference will occur, forming vortices that increase the efficiency of the lift motor. Therefore, the outboard arm 200 and the inboard arm should not be installed too close together. However, if they are too far apart, the aircraft's weight will inevitably increase. Therefore, a convection gap of 8% to 15% of the largest propeller diameter between the outboard and inboard arms can balance the interference vortices generated between the outboard and inboard arms and the aircraft's weight, while meeting both the aircraft's payload and aerodynamic efficiency requirements.

[0044] Preferably, the outer arm 200 includes an arm recess, the cross section of which in the longitudinal direction is an inverted isosceles trapezoid, for adapting to the outer separation surface of the fixed-wing wing, and the outer separation surface of the fixed-wing wing has local carbon fiber reinforcement at the flange.

[0045] The inverted isosceles trapezoid of the arm concave part meets the aerodynamic surface requirements.

[0046] The present application also provides an aircraft, which is applicable to the assembly method of aircraft modular components recorded in the above scheme.

[0047] The above embodiments are merely illustrative of the principles and effects of this application. Anyone skilled in the art may modify or alter the above embodiments without departing from the objectives of this application. Therefore, all equivalent modifications or alterations made by persons skilled in the art without departing from the objectives disclosed herein are intended to be covered by the claims of this application.

Claims

1. A method for assembling modular components of an aircraft, characterized in that: include: An aircraft flight platform is provided, which has: a left fixed wing and a right fixed wing; a left canard and a right canard; an avionics compartment coupled to the left and right fixed wings; a left inner arm connecting the left fixed wing and the left canard; a right inner arm connecting the right fixed wing and the right canard; the left inner arm having first, second, and third lift propellers and a left vertical tail; the right inner arm having fourth, fifth, and sixth lift propellers and a right vertical tail; According to the requirement of increasing cruising load, modular components of the aircraft are selected to be installed without changing the structure of the aircraft flight platform to meet the different functions and mission requirements of the aircraft.

2. The method for assembling modular components of an aircraft according to claim 1, characterized in that: The modular components of the aircraft include a quickly detachable canard outer section 100. When it is required to increase the lift of the aircraft in the fixed-wing state by 10% to 20% based on the original lift value obtained by the applicable aircraft flight platform, the quickly detachable canard outer section 100 is selected to be installed on the inner arm.

3. The method for assembling modular components of an aircraft according to claim 1, characterized in that: The modular assembly of the aircraft includes a quickly detachable outer arm 200. When it is required to increase the lift of the aircraft in the rotor state by 20% to 70% based on the original lift value obtained by the applicable aircraft flight platform, the quickly detachable outer arm 200 is selected for installation.

4. The method for assembling modular components of an aircraft according to claim 3, characterized in that: The installation method of the quickly detachable outer arm 200 includes: installing the outer arm 200 on the leading edge of the left fixed wing and the right fixed wing, or installing the outer arm 200 on the trailing edge of the left fixed wing and the right fixed wing, or installing the outer arm 200 on the leading edge and trailing edge of the left fixed wing and the right fixed wing respectively.

5. The method for assembling modular components of an aircraft according to claim 1, characterized in that: The left canard, the left inner arm, the avionics compartment, the right inner arm, and the right canard are combined into an A-type fuselage, which significantly improves the mounting structural rigidity of the first four motors of the fuselage.

6. The method for assembling aircraft modular components according to claim 1 or 3, characterized in that: The cross-sectional shape of the arm is streamlined, which can reduce the formation of vortices when the propeller downwash is disturbed by the aircraft fuselage, thereby reducing the loss of the lift motor.

7. The method for assembling modular components of an aircraft according to claim 2, characterized in that: The canard outer section 100 includes a positioning member 101 and a locking member 102 . After the canard outer section is installed at a fixed position of the inner arm through the positioning member 101 , the canard outer section 100 and the inner arm are locked through the locking member 102 .

8. The method for assembling modular components of an aircraft according to claim 3, characterized in that: The distance between the outer arm 200 and the inner arm is at least greater than the sum of the rotation radius of the lift propeller installed on the inner arm, the rotation radius of the lift propeller installed on the outer arm 200 and the convection gap.

9. The method for assembling modular components of an aircraft according to claim 3, characterized in that: The outer arm 200 includes an arm recess 300 , the cross section of which in the longitudinal direction is an inverted isosceles trapezoid, and is used to adapt to the outer separation surface of the fixed-wing wing. The outer separation surface of the fixed-wing wing has local carbon fiber reinforcement at the flange.

10. An aircraft, characterized in that: The aircraft is applicable to the assembly method of aircraft modular components described in claims 1-9.

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