Quick installation method for outer arms

Abstract

The present invention belongs to the field of aircraft and discloses a method for quickly installing an outer arm, which includes: providing an outer arm (S1); providing a fixed-wing aircraft wing (S2) in which an inner arm and an outer arm are arranged parallel to each other with a gap between them, the inner arm and the outer arm having the same horizontal height plane, and a power source with a propeller distributed between the inner arm and the outer arm; and fixing the outer arm to the fixed-wing aircraft wing (S3) so that the distance between the outer arm and the inner arm is greater than at least the sum of the rotation radius of the propeller rotor attached to the inner arm, the rotation radius of the propeller rotor attached to the outer arm, and the convection gap.

Description

[Technical Field]

[0001] The present invention relates to the field of air vehicles, and more particularly to a method for quick attachment of outer arms. [Background technology]

[0002] As vertical take-off and landing (VTOL) aircraft become more widespread, their advantages are gradually becoming apparent, as they rarely require dedicated airports and runways, freeing us from dependency on runways and allowing us to apply them to complex operational scenarios with limited take-off and landing sites, such as tourism, logistics transportation, medical emergency services, firefighting rescue, search and rescue, aerial law enforcement, air taxis, air ambulances, etc. It has been noticed that VTOL aircraft cannot quickly load increased take-off weights to meet the different requirements of complex operational scenarios, for example, in the case of emergency medical emergency services and firefighting rescue, while, for example, when entering low altitudes over cities, it is necessary to reduce the decibels of the propeller rotor blades, or when encountering air traffic congestion and running out of power, it is necessary to reduce motor losses, but noise and energy consumption cannot be quickly reduced. Summary of the Invention [Problem to be solved by the invention]

[0003] SUMMARY OF THE INVENTION The object of the present invention is to provide a quick installation method for an outer arm, which is simple in operation and can achieve the objective of quickly installing and removing an outer arm from a fixed wing within 30 minutes. [Means for solving the problem]

[0004] To achieve this objective, the present invention provides the following technical solutions.

[0005] The present invention provides S1, which provides the outer arm; S2 provides a fixed-wing aircraft wing in which an inner arm and an outer arm are provided in parallel with a gap therebetween, the inner arm and the outer arm have the same horizontal plane height, and a power source with a propeller is distributed to the inner arm and the outer arm; and S3 fixing the outer arm to the wing of the fixed wing so that the distance between the outer arm and the inner arm is greater than at least the sum of the rotation radius of the propeller rotor attached to the inner arm, the rotation radius of the propeller rotor attached to the outer arm, and the convection gap. To provide a quick method of attachment of outer arms.

[0006] Preferably, the convection gap is 8% to 15% of the maximum propeller diameter in the outer arm and the inner arm.

[0007] Preferably, the mounting manner 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.

[0008] Preferably, the outer arm includes an arm recess, the cross section of which in its longitudinal direction is an inverted isosceles trapezoid to fit the contour separation surface of the fixed wing wing.

[0009] Preferably, the arm recess is provided with a reinforcing rib and several fixing bases in its longitudinal direction, and before S3, S300: The method further includes aligning the pair of fixing bases in the width direction of the outer arm with the reinforcing rib as the center of symmetry, and then adhering the fixing bases to the arm recesses at intervals in the longitudinal direction of the outer arm.

[0010] Preferably, the fixed-wing wing has a wing convex portion at a connection position with the outer arm, and a cross section of the wing convex portion in its longitudinal direction is an isosceles trapezoid, and S300 further includes the wing convex portion covering the arm concave portion.

[0011] Preferably, a fastener holder is fixed to each fixing base, each fastener holder has a screw hole, and an opening corresponding to the screw hole is formed in the wing convex portion; S3 is The method includes inserting the main bolt through the opening in the wing convex portion, and then fastening the wing convex portion and the arm concave portion together using the screw hole in the fastener holder.

[0012] Preferably, the wing protrusion is provided with a reinforcing portion along its longitudinal direction, and the reinforcing portion has screw holes formed at equal intervals on an outer circumferential surface near the boundary where the reinforcing portion is connected to the arm recess, and corresponding screw holes are formed in the arm recess; S3 includes inserting the auxiliary bolt through the screw hole of the reinforcing part, and then fixing and connecting the wing convex part and the arm concave part.

[0013] Preferably, the load-bearing capacity range of one main bolt is 1.8 tons to 2.2 tons, and / or the load-bearing capacity range of one auxiliary bolt is 680 kg to 720 kg.

[0014] The present invention provides The arm is attached by the quick attachment method for the outer arm described above. Providing more drones. [Effects of the Invention]

[0015] The beneficial effects of the present invention are as follows: By attaching an outer arm to a drone, the present invention can increase the drone's takeoff load from approximately 1.5 tons to approximately 2 tons, and although a corresponding motor is attached to the outer arm and generates noise when the motor is operating, removing the outer arm and removing the corresponding motor can achieve a noise reduction effect.

[0016] Next, the present invention further fastens the outer arm to the wing using a bolt clamping method, of which eight bolts are main fixing bolts that carry the majority of the load, and several small bolts are attached to the front and rear edges of the outer arm to support auxiliary forces in addition to the main fixing bolts. When installing, first insert the eight main bolts through the openings in the wing and align them with the screw holes in the outer arm before tightening them, and then tighten the auxiliary fixing bolts in sequence, thereby completing the quick installation of the outer arm. Similarly, when removing, simply remove the main bolts and auxiliary bolts, and the outer arm can be quickly installed and removed within 30 minutes. [Brief explanation of the drawings]

[0017] [Figure 1] 1 is a flow chart of the outer arm quick installation method of the present invention. [Figure 2] FIG. 2 is a schematic diagram of the outer arm and wing of the present invention. [Figure 3] 1 is a schematic diagram of a fixture and fastener holder of the present invention. DETAILED DESCRIPTION OF THE INVENTION

[0018] The technical solution of the present application will be further described below with reference to the following embodiments. It should be understood that the specific examples described here are merely for the purpose of interpreting the present application. For the sake of convenience, the drawings only show parts relevant to the present application, rather than all of the structures.

[0019] In this application, unless otherwise clearly specified or limited, the terms "attached," "connected," and "coupled" should be interpreted broadly, and may refer to, for example, a fixed connection, a detachable connection, a mechanical connection, an electrical connection, a direct connection, an indirect connection via an intermediate medium, or internal communication between two elements. Those skilled in the art will be able to understand the specific meanings of the above terms in this application according to specific circumstances.

[0020] In this application, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include direct contact between the first and second features, or may include contact between the first and second features via another feature between them rather than direct contact. Furthermore, a first feature being "above," "above," and "on the upper surface" of a second feature may include the first feature being directly above and diagonally above the second feature, or may simply mean that the first feature is higher in horizontal height than the second feature. A first feature being "below," "below," and "on the lower surface" of a second feature may include the first feature being directly below and diagonally below the second feature, or may simply mean that the first feature is lower in horizontal height than the second feature.

[0021] The present application provides a quick installation method for the outer arm, which includes the following steps:

[0022] At S1, an outer arm 100 is provided.

[0023] In S2, an inner arm and an outer arm 100 are arranged parallel to each other with a gap between them, the horizontal planes at the same height of the inner arm and the outer arm 100, and a fixed-wing aircraft wing 200 is provided in which a power source with a propeller is distributed to the inner arm and the outer arm 100.

[0024] In S3, the outer arm 100 is fixed to the fixed-wing aircraft wing 200 so that the distance between the outer arm 100 and the inner arm is greater than at least the sum of the rotation radius of the propeller rotor attached to the inner arm, the rotation radius of the propeller rotor attached to the outer arm 100, and the convection gap between two parallel propellers. Preferably, the convection gap is 8% to 15% of the maximum propeller diameter in the outer arm 100 and the inner arm.

[0025] Specifically, the outer arm must be close to the central axis of the aircraft, from the perspective of the overall structural design of the aircraft, to reduce the aircraft's weight, save more weight and space, and increase power and payload. On the other hand, to meet aerodynamic requirements, the outer arm 100 and the inner arm must not be installed too close together because, when the propeller operates, corresponding airflow occurs. If the outer arm and the inner arm are installed too close, airflow interference occurs, forming vortices after the interference, which increases the efficiency of the lift motor. However, if they are installed too far apart, the weight of the aircraft will inevitably increase. Therefore, if the convection gap is 8% to 15% of the maximum propeller diameter in the outer arm and the inner arm, the issues of the interference vortices generated between the outer arm and the inner arm and the aircraft's weight can be balanced, and the aircraft's payload and aerodynamic efficiency can be simultaneously satisfied.

[0026] Furthermore, the mounting manner of 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 both the leading edge and the trailing edge of the fixed-wing wing 200. By simply mounting the outer arm 100 to the leading edge or the trailing edge, or by simultaneously mounting the outer arm 100 to both the leading edge and the trailing edge, different center of gravity positions of the aircraft can be adjusted.

[0027] Specifically, the outer arm 100 includes an arm recess 101, and the cross section of the arm recess 101 in its longitudinal direction is an inverted isosceles trapezoid in order to fit the outer contour separation surface of the fixed wing wing 200.

[0028] The inverted isosceles trapezoid shape of the arm recess 101 meets the aerodynamic requirements.

[0029] Referring to FIG. 2, the arm recess 101 is provided with reinforcing ribs and some fixing bases 300 in its longitudinal direction, and before S3, the following steps are further included.

[0030] In S300, the pair of fixing bases 300 are aligned in the width direction of the outer arm 100 with the reinforcing rib as the center of symmetry, and then adhered to the arm recesses 101 of the outer arm 100 with a gap in the longitudinal direction.

[0031] The reinforcing rib can reinforce the stress loss caused by the provision of the recess.

[0032] Furthermore, the fixed wing wing 200 is provided with a wing convex portion 201 at the connection position with the outer arm, and the cross section of the wing convex portion 201 in its longitudinal direction is an isosceles trapezoid, and S300 further includes that the wing convex portion 201 covers the arm concave portion 101.

[0033] The isosceles trapezoid shape of the wing protrusion 201 meets the aerodynamic requirements.

[0034] Specifically, a fastener holder 400 is fixed to each fixing base 300, and each fastener holder 400 has a screw hole, and an opening corresponding to the screw hole is opened in the wing protrusion 201, Here, S3 is The method includes inserting the main bolt through the opening in the wing convex portion, and then fastening the wing convex portion 201 and the arm concave portion 101 together with the screw hole of the fastener holder 400 .

[0035] There are preferably eight main fixing bolts, which carry most of the load, and the load-bearing capacity of each main bolt is in the range of 1.8 tons to 2.2 tons.

[0036] Furthermore, the wing protrusion 201 is provided with a reinforcing portion along its longitudinal direction, and the reinforcing portion has screw holes provided at equal intervals on the outer circumferential surface near the boundary connected to the arm recess 101, and corresponding screw holes are opened in the arm recess 101, S3 specifically includes inserting the auxiliary bolt through the screw hole of the reinforcing part, and then fixing and connecting the wing convex part 201 and the arm concave part 101.

[0037] The auxiliary bolts carry some of the load, mainly the stress from the skin.

[0038] Preferably, the load-bearing capacity of one auxiliary bolt is in the range of 680 kg to 720 kg.

[0039] In this embodiment, the outer arm is fastened to the wing using a bolt clamping method, eight of which are main fixing bolts that carry the majority of the load, and several small bolts at the front and rear edges of the outer arm provide auxiliary force in addition to the main fixing bolts. When installing, first insert the eight main bolts through the openings in the wing and align them with the screw holes in the outer arm before tightening them, and then tighten the auxiliary fixing bolts in sequence, completing the quick installation of the outer arm. Similarly, when removing, simply remove the main bolts and auxiliary bolts, and the outer arm can be quickly installed or removed within 30 minutes.

[0040] The present application further provides a drone having an arm attached by the quick attachment method for an outer arm described in the above aspect.

[0041] By attaching an outer arm to a drone, the present invention can increase the drone's takeoff load from approximately 1.5 tons to approximately 2 tons. A corresponding motor is attached to the outer arm, which generates noise when in operation. However, by removing the outer arm and reducing the corresponding motor, the noise reduction effect can be achieved.

[0042] The above embodiments are merely illustrative of the principles and effects of the present application. Those skilled in the art can modify or change the above embodiments without violating the application objectives of the present application. Therefore, all equivalent modifications or changes made by those skilled in the art without departing from the objectives disclosed in the present application still fall within the scope of the claims of the present application.

Claims

1. S1 providing the outer arm (100); S2 provides a fixed-wing aircraft wing (200) in which an inner arm and the outer arm (100) are arranged in parallel with a gap between them, the inner arm and the outer arm (100) have the same horizontal plane at the same height, and a power source with a propeller is distributed between the inner arm and the outer arm (100); and S3 fixing the outer arm (100) to the fixed-wing aircraft wing (200) so that the distance between the outer arm (100) and the inner arm is greater than at least the sum of the rotation radius of the propeller rotor attached to the inner arm, the rotation radius of the propeller rotor attached to the outer arm, and a convection gap. A method for quick installation of outer arms.

2. the convection gap is 8% to 15% of the maximum propeller diameter in the outer arm (100) and the inner arm; The quick installation method for outer arms of claim 1 .

3. The mounting manner of 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. The quick installation method for outer arms of claim 1 .

4. The outer arm (100) includes an arm recess (101), and the cross section of the arm recess (101) in its longitudinal direction is an inverted isosceles trapezoid to fit the outer separation surface of the fixed wing wing (200). The quick installation method for outer arms of claim 1 .

5. The arm recess (101) is provided with a reinforcing rib and several fixing bases (300) in its longitudinal direction, and before S3, The method further includes aligning the pair of fixing bases (300) in the width direction of the outer arm (100) with the reinforcing rib as the center of symmetry, and then adhering the fixing bases (300) to the arm recesses (101) at intervals in the longitudinal direction of the outer arm (100).

5. The quick installation method for outer arms of claim 4.

6. The fixed wing wing (200) is provided with a wing protrusion (201) at a connection position with the outer arm, and a cross section of the wing protrusion (201) in its longitudinal direction is an isosceles trapezoid, and the S300 further includes that the wing protrusion (201) covers the arm recess (101).

6. The quick installation method for outer arms of claim 5.

7. A fastener holder (400) is fixed to each of the fixing bases (300), and each of the fastener holders (400) has a screw hole, and an opening corresponding to the screw hole is opened in the wing protrusion (201); The S3 is and inserting a main bolt through an opening in the wing convex portion, and then fastening the wing convex portion (201) and the arm concave portion (101) together with a screw hole of the fastener holder (400). The quick installation method for outer arms according to claim 6.

8. The wing protrusion (201) is provided with a reinforcing portion along its longitudinal direction, and the reinforcing portion has screw holes provided at equal intervals on its outer circumferential surface near the boundary connected to the arm recess (101), and corresponding screw holes are opened in the arm recess (101). The step S3 includes inserting an auxiliary bolt through a screw hole of the reinforcing part, and then fixedly connecting the wing convex part (201) and the arm concave part (101). The quick installation method for outer arms according to claim 6.

9. The load-bearing capacity range of one of the main bolts is 1.8 tons to 2.2 tons, and / or the load-bearing capacity range of one of the auxiliary bolts is 680 kg to 720 kg.

9. The outer arm quick installation method of claim 8.

10. 10. The quick attachment method for outer arms according to claims 1 to 9, A drone characterized by

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