Quick mounting method for outer side machine arm

Abstract

The invention belongs to the field of aircrafts, and discloses a quick mounting method for an outer side arm, which comprises the following steps: S1, providing an outer side arm; s2, a fixed-wing wing is provided, an inner-side machine arm and an outer-side machine arm are arranged on the fixed-wing wing in parallel at an interval, the height horizontal planes of the inner-side machine arm and the outer-side machine arm are flush, and power sources with propellers are distributed on the inner-side machine arm and the outer-side machine arm; and S3, the outer side machine arms are fixed to the fixed wing wings, and the distance between the outer side machine arms and the inner side machine arms is at least larger than the sum of the rotation radius of the rotor wing propellers installed on the inner side machine arms, the rotation radius of the rotor wing propellers installed on the outer side machine arms and the convection gaps.

Description

A quick installation method for outer machine arm Technical Field

[0001] The present invention relates to the field of aircraft, and in particular to a method for quickly installing an outer aircraft arm. Background Art

[0002] With the increasing popularity of vertical take-off and landing (VTOL) aircraft, their advantages are becoming increasingly apparent. They essentially eliminate the need for dedicated airports and runways, freeing them from runway dependence and making them suitable for complex scenarios with limited take-off and landing areas, such as tourism, logistics, medical emergency response, firefighting and disaster relief, search and rescue, air law enforcement, air taxis, and air ambulances. However, facing the diverse demands of complex scenarios, VTOL aircraft have proven unable to quickly handle the increased takeoff weight required for emergency medical and firefighting operations. Furthermore, they are unable to rapidly reduce noise and energy consumption, such as when operating at low altitudes in urban areas, where rotor decibels need to be reduced, or when encountering air traffic congestion and battery shortages, where motor losses need to be minimized.

[0003] Summary of the Invention

[0004] The purpose of the present invention is to provide a method for quickly installing an outer aircraft arm, which is simple to operate and can achieve the purpose of quickly installing and disassembling the outer aircraft arm on a fixed wing within 30 minutes.

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

[0006] The present invention provides a method for quickly installing an outer machine arm, comprising:

[0007] S1: Provide an outer arm;

[0008] S2: Provide a fixed-wing wing, wherein an inner arm and an outer arm are arranged parallel to each other on the fixed-wing wing, the inner arm and the outer arm are aligned at the same height, and a power source with a propeller is distributed on the inner arm and the outer arm;

[0009] S3: Fixing the outer arm to the wing of the national fixed wing, wherein the distance between the outer arm and the inner arm is at least greater than the sum of the rotation radius of the rotor propeller installed on the inner arm, the rotation radius of the rotor propeller installed on the outer arm, and the convection clearance.

[0010] Preferably, the convection gap is 8% to 15% of the maximum propeller diameter between the outer arm and the inner arm.

[0011] Preferably, the installation method of fixing the outer arm to the fixed-wing wing specifically includes: fixing the outer arm to the leading edge of the fixed-wing wing, or fixing the outer arm to the trailing edge of the fixed-wing wing, or fixing the outer arm to the leading edge and trailing edge of the fixed-wing wing respectively.

[0012] Preferably, the outer arm includes an arm recess, and the cross section of the arm recess in the longitudinal direction thereof is an inverted isosceles trapezoid, which is used to adapt to the outer shape separation surface of the fixed-wing wing.

[0013] Preferably, the arm recess is provided with reinforcing ribs and a plurality of fixing seats in the longitudinal direction thereof; and before S3, the method further includes:

[0014] S300: Align a pair of fixing seats in the width direction of the outer machine arm with the reinforcing rib as the symmetry center, and then stick them to the concave portion of the machine arm at intervals in the length direction of the outer machine arm.

[0015] Preferably, the fixed-wing wing is provided with a wing protrusion at the connection position with the outer arm, and the cross section of the wing protrusion in its length direction is a right isosceles trapezoid; S300 also includes: the wing protrusion covers the arm recess.

[0016] Preferably, each fixing seat is fixed with a fastener bracket, each fastener bracket has a threaded hole, and the wing protrusion is provided with an opening corresponding to the threaded hole;

[0017] S3 includes:

[0018] After the main bolt is inserted through the opening on the wing convex part, the wing convex part and the arm concave part are fixedly connected through the threaded hole of the fastener bracket.

[0019] Preferably, the wing convex portion is provided with a reinforcement portion along its length, and the reinforcement portion is provided with threaded holes at equal intervals on the outer circumferential surface near the junction with the arm concave portion, and the arm concave portion is provided with corresponding threaded holes;

[0020] S3 includes: inserting auxiliary bolts through the threaded holes of the reinforcement portion to fix and connect the wing protrusion and the arm recess.

[0021] Preferably, the bearing capacity range of a single main bolt is 1.8 tons to 2.2 tons; and / or the bearing capacity range of a single auxiliary bolt is 680 kg to 720 kg.

[0022] The present invention also provides a drone, comprising a machine arm installed using the outer machine arm quick installation method described in the above solution.

[0023] The beneficial effects of the present invention are as follows: the present invention installs the outer arm on the drone, which can increase the take-off load of the drone from about 1.5 tons to about 2 tons; at the same time, the outer arm is equipped with a corresponding motor, which generates noise when running. After the outer arm is disassembled, reducing the corresponding motor will produce a noise reduction effect.

[0024] Secondly, the present invention uses a bolt-clamping system to secure the outer arm to the wing. Eight bolts serve as the main fixing bolts, carrying the majority of the load. Several smaller bolts at the leading and trailing edges of the outer arm provide additional load-bearing support. During installation, the eight main bolts are first inserted through the openings in the wing, aligned with the threaded holes in the outer arm, and tightened. The auxiliary fixing bolts are then tightened in sequence to complete the quick installation of the outer arm. Disassembly is similar: after removing the main and auxiliary bolts, the outer arm can be quickly installed or disassembled in under 30 minutes. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] FIG1 is a flow chart of a method for quickly installing an outer arm of the present invention;

[0026] FIG2 is a schematic diagram of the outer arm and wing of the present invention;

[0027] FIG3 is a schematic diagram of the fixing seat and the fastener bracket of the present invention. DETAILED DESCRIPTION

[0028] 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.

[0029] 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.

[0030] 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.

[0031] This application provides a method for quickly installing an outer machine arm, including:

[0032] S1: Provide an outer machine arm 100;

[0033] S2: Provide a fixed-wing wing 200, wherein an inner arm and an outer arm 100 are spaced apart and arranged in parallel on the fixed-wing wing 200, the inner arm and the outer arm 100 being at the same height level, and a power source with a propeller is distributed on the inner arm and the outer arm 100;

[0034] S3: Secure outboard arm 100 to national wing 200, with the distance between outboard arm 100 and inboard arm at least greater than the sum of the rotation radius of the rotor propeller mounted on the inboard arm, the rotation radius of the rotor propeller mounted on outboard arm 100, and the convection clearance between the two parallel propellers. Preferably, the convection clearance is 8% to 15% of the diameter of the largest propeller between outboard arm 100 and inboard arm.

[0035] Specifically, regarding the outboard arms, on the one hand, from the perspective of the overall aircraft structural design, the outboard arms are required to be close to the aircraft's central axis to reduce the aircraft's weight, freeing up more weight space to increase power and payload. On the other hand, according to aerodynamic requirements, when the propellers operate, corresponding airflow is generated. If the outboard and inboard arms are installed too close, flow interference will occur, forming vortices that increase the efficiency of the lift motor. Therefore, the outboard arms 100 and the inboard arms should not be installed too close. However, if they are too far apart, the aircraft's weight will inevitably increase. Therefore, when the convection gap is 8% to 15% of the largest propeller diameter between the outboard and inboard arms, the interference vortices generated between the outboard and inboard arms and the aircraft weight can be balanced, while meeting the aircraft's payload and aerodynamic efficiency requirements.

[0036] Furthermore, the outer arm 100 may be attached to the fixed-wing wing 200 by attaching it to the leading edge of the fixed-wing wing 200, the trailing edge of the fixed-wing wing 200, or both the leading and trailing edges of the fixed-wing wing 200. Attaching the outer arm 100 to either the leading or trailing edge, or both, allows for adjustment of the aircraft's center of gravity.

[0037] Specifically, the outer arm 100 includes an arm recess 101 , and the cross section of the arm recess 101 in the longitudinal direction thereof is an inverted isosceles trapezoid, which is used to adapt to the outer shape separation surface of the fixed-wing wing 200 .

[0038] The inverted isosceles trapezoid of the arm recess 101 meets the aerodynamic surface requirements.

[0039] As shown in FIG2 , the arm recess 101 is provided with reinforcing ribs and a plurality of fixing seats 300 along its length direction; and before S3 , the following steps are also included:

[0040] S300 : A pair of fixing seats 300 are aligned in the width direction of the outer arm 100 with the reinforcing rib as the symmetry center, and then glued to the arm recess 101 at intervals in the length direction of the outer arm 100 .

[0041] The reinforcing ribs can compensate for the stress loss caused by the recesses.

[0042] Furthermore, the fixed-wing wing 200 is provided with a wing protrusion 201 at the connection position with the outer arm, and the cross section of the wing protrusion 201 in its length direction is a right isosceles trapezoid; S300 also includes: the wing protrusion 201 covers the arm recess 101.

[0043] The right isosceles trapezoid of the wing bulge 201 meets the aerodynamic surface requirements.

[0044] Specifically, each fixing seat 300 is fixed with a fastener bracket 400, each fastener bracket 400 has a threaded hole, and the wing protrusion 201 is provided with an opening corresponding to the threaded hole;

[0045] S3 includes:

[0046] After the main bolt is inserted from the opening on the wing protrusion, the wing protrusion 201 and the arm recess 101 are fixedly connected through the threaded hole of the fastener bracket 400.

[0047] The main fixing bolts are preferably eight bolts, which bear most of the load, and the bearing capacity of a single main bolt ranges from 1.8 tons to 2.2 tons.

[0048] Furthermore, the wing protrusion 201 is provided with a reinforcement portion along its length direction, and the reinforcement portion is provided with threaded holes at equal intervals on the outer circumference near the junction with the arm recess 101, and the arm recess 101 is provided with corresponding threaded holes;

[0049] S3 specifically includes: inserting auxiliary bolts through the threaded holes of the reinforcement portion to fix the wing protrusion 201 and the arm recess 101 together.

[0050] The auxiliary bolts carry part of the load, mainly carrying the stress from the skin.

[0051] Preferably, the bearing capacity of a single auxiliary bolt ranges from 680 kg to 720 kg.

[0052] This solution uses bolt clamping to secure the outer arm to the wing. Eight bolts serve as the primary fixing bolts, carrying the majority of the load. Several smaller bolts at the leading and trailing edges of the outer arm provide additional load-bearing support. During installation, the eight main bolts are first inserted through the openings in the wing, aligned with the threaded holes in the outer arm, and tightened. The auxiliary fixing bolts are then tightened in sequence to quickly install the outer arm. Disassembly is similar: after removing the main and auxiliary bolts, the outer arm can be quickly installed or removed in under 30 minutes.

[0053] The present application also provides a drone, which includes an arm installed using the outer arm quick installation method described in the above solution.

[0054] The present invention installs an outer arm on the drone, which can increase the takeoff load of the drone from about 1.5 tons to about 2 tons; at the same time, the outer arm is equipped with a corresponding motor, which generates noise when running. After the outer arm is disassembled, reducing the corresponding motor will produce a noise reduction effect.

[0055] 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 quickly installing an outer machine arm, characterized in that: include: S1: Provide an outer machine arm 100; S2: Provide a fixed-wing wing 200, wherein an inner arm and an outer arm 100 are arranged parallel to each other on the fixed-wing wing 200, the inner arm and the outer arm 100 being at the same height level, and a power source with a propeller is distributed on the inner arm and the outer arm 100; S3: Fix the outer arm 100 to the national fixed wing 200, and the distance between the outer arm 100 and the inner arm is at least greater than the sum of the rotation radius of the rotor propeller installed on the inner arm, the rotation radius of the rotor propeller installed on the outer arm, and the convection gap.

2. The method for quickly installing an outer machine arm according to claim 1, characterized in that: The convection gap is 8% to 15% of the maximum propeller diameter between the outer arm 100 and the inner arm.

3. The method for quickly installing an outer machine arm according to claim 1, characterized in that: The installation method of fixing the outer arm 100 to the fixed-wing wing 200 specifically includes: fixing the outer arm 100 to the leading edge of the fixed-wing wing 200, or fixing the outer arm 100 to the trailing edge of the fixed-wing wing 200, or fixing the outer arm 100 to the leading edge and trailing edge of the fixed-wing wing 200 respectively.

4. The method for quickly installing an outer machine arm according to claim 1, characterized in that: The outer arm 100 includes 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 wing 200 .

5. The method for quickly installing an outer machine arm according to claim 4, characterized in that: The arm recess 101 is provided with reinforcing ribs and a plurality of fixing seats 300 in its length direction; and before S3, the following steps are also included: A pair of the fixing seats 300 are aligned in the width direction of the outer arm 100 with the reinforcing rib as the symmetry center, and then adhered to the arm recess 101 at intervals in the length direction of the outer arm 100 .

6. The method for quickly installing an outer machine arm according to claim 5, characterized in that: The fixed-wing wing 200 is provided with a wing protrusion 201 at the connection position with the outer arm, and the cross section of the wing protrusion 201 in its length direction is a right isosceles trapezoid; the S300 also includes: the wing protrusion 201 covers the arm recess 101.

7. The method for quickly installing an outer machine arm according to claim 6, characterized in that: A fastener bracket 400 is fixed on each of the fixing seats 300 , and each of the fastener brackets 400 has a threaded hole, and an opening corresponding to the threaded hole is opened on the wing protrusion 201 ; The S3 includes: After the main bolt is inserted from the opening on the wing protrusion, the wing protrusion 201 and the arm recess 101 are fixedly connected through the threaded hole of the fastener bracket 400 .

8. The method for quickly installing an outer machine arm according to claim 6, characterized in that: The wing protrusion 201 is provided with a reinforcement portion along its length, and the reinforcement portion is provided with threaded holes at equal intervals on the outer circumference near the junction with the arm recess 101, and the arm recess 101 is provided with corresponding threaded holes; The step S3 includes inserting auxiliary bolts through the threaded holes of the reinforcement portion to securely connect the wing protrusion 201 and the arm recess 101 .

9. The method for quickly installing an outer machine arm according to claim 8, characterized in that: The bearing capacity range of a single main bolt is 1.8 tons to 2.2 tons; and / or the bearing capacity range of a single auxiliary bolt is 680 kilograms to 720 kilograms.

10. A drone, characterized in that: The drone includes an arm that is installed using the outer arm quick installation method described in claims 1-9.

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