Suspension outer arm and modular aircraft

Abstract

A suspension outer arm (100) is applied to an aircraft and comprises an outer arm body, and the outer arm body is of a linear structure in the vertical projection direction; a plurality of openings are formed in the outer arm body and used for containing the lift motors. The outer arm body is of a structure converging from each opening to the two ends. The outer arm body can be selectively hung on a fixed wing of the aircraft according to different take-off weights.

Description

Suspension outer arms and modular aircraft Technical Field

[0001] The present invention relates to the field of aircraft, and in particular to a suspension outer arm and a modular aircraft. Background Art

[0002] During actual use, it was found that most of the existing aircraft are of integrated design, the arms cannot be disassembled, and most of them are repeatedly stacked, which cannot improve the efficiency of the lift motor. Therefore, the installation and disassembly of the aircraft requires specialized technicians. In order to cope with sudden different working conditions, such as air taxis, air ambulances, etc., there is an urgent need to provide a modular aircraft.

[0003] Summary of the Invention

[0004] The purpose of the present invention is to provide a suspension arm and a modular aircraft, which are simple to operate and meet the different functions and mission requirements of the aircraft.

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

[0006] A suspension outer arm is applied to an aircraft, and the suspension outer arm comprises:

[0007] An outer arm body, wherein the outer arm body is a linear structure in a vertical projection direction;

[0008] The body is provided with a plurality of openings for accommodating the lift motor;

[0009] The body presents a structure that converges from each opening to both ends:

[0010] The outer arm body can be selectively mounted on the fixed wing of an aircraft according to different take-off weights.

[0011] Preferably, the outer arm body has a streamlined design in a cross-section along its length, wherein the arc curvature at one end is smaller than that at the other end, and the cross-section gradually converges from the middle to both ends. The streamlined design can reduce the vortex formed when the propeller is disturbed by the aircraft fuselage, thereby increasing the efficiency of the lift motor.

[0012] Preferably, the outer arm has an arm recess, and the cross section of the arm recess in the length direction thereof is an inverted isosceles trapezoid, so as to adapt to the outer separation surface of the fixed wing.

[0013] A modular aircraft comprising:

[0014] 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; the right inner arm having fourth, fifth, and sixth lift propellers and a right vertical tail; and the suspension outer arm described in the above scheme;

[0015] 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.

[0016] 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.

[0017] Preferably, the modular components of the aircraft include a quickly detachable suspension outer arm. 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 suspension outer arm is selected for installation.

[0018] Preferably, the suspension outer arm is installed on the leading edge of the left fixed wing and the right fixed wing, or the suspension outer arm is installed on the trailing edge of the left fixed wing and the right fixed wing, or the suspension outer arm is installed on the leading edge and trailing edge of the left fixed wing and the right fixed wing respectively.

[0019] 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.

[0020] Preferably, the distance between the suspension 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 suspension outer arm and the convection gap.

[0021] Preferably, the convection gap is 8% to 15% of the maximum propeller diameter between the outer suspension arm and the inner arm.

[0022] The beneficial effects of the present invention are: the present invention uses a streamlined arm to reduce the vortex formed when the propeller is disturbed by the aircraft fuselage, thereby increasing the efficiency of the lift motor; the present invention also uses a modular aircraft to increase the lift of the aircraft in a fixed-wing state or a rotor state by quickly adding a canard outer section or a suspension outer arm without changing the structure of the aircraft flight platform. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] FIG1 is a schematic diagram of the aircraft of the present application;

[0024] FIG2 is a schematic diagram of the streamlined machine arm of the present application;

[0025] FIG3 is a schematic diagram of the outer section of the canard of the present application;

[0026] FIG4 is a schematic diagram of the outer arm of the suspension of the present application. DETAILED DESCRIPTION

[0027] 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.

[0028] 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.

[0029] 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.

[0030] As shown in Figures 1-2, the present application provides a suspension outer arm for use in aircraft, characterized in that the suspension outer arm 100 includes: an outer arm body, which has a linear structure in the vertical projection direction; the body has several openings for accommodating lift motors; the body has a structure that converges from each opening to both ends; the outer arm body can be selected to be mounted on the fixed wing of the aircraft according to different take-off weights.

[0031] Furthermore, the outer arm body presents a streamlined design in the cross-section along its length. The streamlined design is that the arc curvature at one end is smaller than the arc curvature at the other end, and the cross-section gradually converges from the middle to both ends. The streamlined design can reduce the vortex formed when the propeller is disturbed by the aircraft fuselage, thereby increasing the efficiency of the lift motor.

[0032] As shown in FIG4 , preferably, the suspension outer arm 100 has an arm recess 101 , and the cross-section of the arm recess 101 in its length direction is an inverted isosceles trapezoid, which is used to adapt to the outer separation surface of the aircraft fixed wing, and the outer separation surface of the fixed wing wing has local carbon fiber reinforcement at the flange.

[0033] The inverted isosceles trapezoid of the arm recess 101 meets the aerodynamic surface requirements.

[0034] As shown in Figure 1, the present application also provides a modular aircraft, including: a left fixed wing and a right fixed wing; a left canard and a right canard; an avionics compartment, which is connected to the left fixed wing and the right fixed wing; a left inner arm, which connects the left fixed wing with the left canard; a right inner arm, which connects the right fixed wing with the right canard; the left inner arm has a first, second, and third lift propeller and a left vertical tail; the right inner arm has a fourth, fifth, and sixth lift propeller and a right vertical tail; and the suspension outer arm 100 recorded in the above scheme; 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.

[0035] Specifically, the modular components of the aircraft include a quickly detachable canard outer section 200. 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 200 is selected to be installed on the inner arm.

[0036] By adding the canard outer section 200, the lift of the aircraft in fixed-wing mode can be increased by 10%-20% compared to the original lift value obtained by the original aircraft flight platform. Furthermore, the installation of the quickly removable canard outer section 200 can overcome the nose-down effect during flight, avoiding undesirable pitching moments, thereby preventing the need to compensate for such pitching moments and thus affecting the flight efficiency of the UAV. Furthermore, after the installation of the canard outer section 200, the structural combination of the canard outer section 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.

[0037] Similarly, the aircraft modular assembly includes a quickly detachable suspension outer arm 100. When it is required to increase the aircraft lift in the rotor state by 20% to 70% based on the original lift value obtained by the applicable aircraft flight platform, the quickly detachable suspension outer arm 100 is selected for installation.

[0038] The addition of the outer arm 100, on the one hand, requires the outer arm 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 demand that the propellers operate, generating corresponding airflow. If the outer arm 100 and the inner arm are mounted too close together, flow interference will occur, creating vortices that increase the efficiency of the lift motor. Therefore, the outer arm 100 and the inner arm should not be mounted too close together. However, if they are too far apart, the aircraft's weight will inevitably increase. Therefore, a convection clearance of 8% to 15% of the largest propeller diameter between the outer arm 100 and the inner arm can balance the interference vortices generated between the outer arm 100 and the inner arm with the aircraft's weight, achieving both payload and aerodynamic efficiency.

[0039] Of course, without changing the structure of the aircraft's flight platform, by quickly disassembling the suspension outer arm 100 and the lift propeller on the outer arm, 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.

[0040] For example, the suspension outer arms 100 can be installed on the leading edges of the left and right fixed wings to increase the lift of the aircraft in the rotor position by 20% to 40% based on the original lift value of the aircraft flight platform. Alternatively, the suspension outer arms 100 can be installed on the trailing edges of the left and right fixed wings to increase the lift of the aircraft in the rotor position by 25% to 45% based on the original lift value of the aircraft flight platform. Alternatively, the suspension outer arms 100 can be installed on the leading and trailing edges of the left and right fixed wings respectively to increase the lift of the aircraft in the rotor position by 50% to 70% based on the original lift value of the aircraft flight platform. Installing the suspension outer arms 100 on either the leading or trailing edge allows adjustment of different center of gravity positions of the aircraft.

[0041] As shown in FIG3 , the canard outer section 200 further includes a positioning member 201 and a locking member 202 . After the canard outer section 200 is installed at a fixed position of the inner arm through the positioning member 201 , the canard outer section 200 and the inner arm are locked through the locking member 202 .

[0042] The positioning member 201 is used to quickly position the canard outer section 200 on the inner arm to save operation time, and then the locking member 202 is used to lock it to prevent the canard outer section 200 from being separated from the inner arm during the operation of the drone.

[0043] Furthermore, the distance between the suspension outer arm 100 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 suspension outer arm 100, and the convection gap. The convection gap is 8% to 15% of the maximum propeller diameter between the suspension outer arm and the inner arm.

[0044] Furthermore, regarding the connection method between the suspension outer arm 100 and the aircraft wing, this solution uses a bolt clamping method to fix the suspension outer arm 100 and the wing, of which eight bolts are the main fixing bolts, which bear most of the load, and the bearing capacity of a single main bolt is in the range of 1.8 tons to 2.2 tons. In addition to the main fixing bolts, there are several auxiliary bolts at the front and rear edges of the suspension outer arm 100 to assist in bearing the load, and the bearing capacity of a single auxiliary bolt is in the range of 680 kg to 720 kg. During installation, first insert the eight main bolts from the opening on the wing, align them with the threaded holes on the outer arm and tighten the bolts, and then tighten the auxiliary fixing bolts in sequence to complete the rapid installation of the suspension outer arm 100. The same applies to disassembly. After removing the main bolts and auxiliary bolts, the suspension outer arm 100 can be quickly installed and disassembled within 30 minutes.

[0045] 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 suspension outer arm, used in aircraft, characterized in that: The suspension outer arm 100 comprises: An outer arm body, wherein the outer arm body is a linear structure in a vertical projection direction; The body is provided with a plurality of openings for accommodating the lift motor; The body presents a structure that converges from each opening to both ends: The outer arm body can be selectively mounted on the fixed wing of an aircraft according to different take-off weights.

2. The suspension outer arm according to claim 1, characterized in that The outer arm body has a streamlined design in a cross-section along its length. The streamlined design is that the arc curvature at one end is smaller than the arc curvature at the other end, and the cross-section gradually converges from the middle to both ends. The streamlined design can reduce the vortex formed when the propeller is disturbed by the aircraft fuselage, thereby increasing the efficiency of the lift motor.

3. The suspension outer arm according to claim 2, characterized in that: The suspension outer arm 100 has an arm recess 101 . The cross section of the arm recess 101 in the longitudinal direction is an inverted isosceles trapezoid, which is used to adapt to the outer separation surface of the fixed wing.

4. A modular aircraft, characterized in that: include: Left fixed wing and right fixed wing; left canard and 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; and the suspension outer arm 100 according to claims 1-3; 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.

5. The modular aircraft according to claim 4, characterized in that: The modular components of the aircraft include a quickly detachable canard outer section 200. 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 200 is selected to be installed on the inner arm.

6. The modular aircraft according to claim 4, characterized in that: The modular assembly of the aircraft includes a quickly detachable suspension outer arm 100. 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 suspension outer arm 100 is selected for installation.

7. The modular aircraft according to claim 6, characterized in that: The suspension outer arm 100 is installed on the leading edge of the left fixed wing and the right fixed wing, or the suspension outer arm 100 is installed on the trailing edge of the left fixed wing and the right fixed wing, or the suspension outer arm 100 is installed on the leading edge and trailing edge of the left fixed wing and the right fixed wing respectively.

8. The modular aircraft according to claim 5, characterized in that: The canard outer section 200 includes a positioning member 201 and a locking member 202 . After the canard outer section 200 is installed at a fixed position of the inner arm through the positioning member 201 , the canard outer section 200 and the inner arm are locked through the locking member 202 .

9. The modular aircraft according to claim 6, characterized in that: The distance between the suspension outer arm 100 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 suspension outer arm 100 and the convection gap.

10. The modular aircraft according to claim 9, characterized in that The convection gap is 8% to 15% of the maximum propeller diameter between the suspension outer arm and the inner arm.

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