Method for rapidly adding canard outer section

Abstract

The invention belongs to the field of aircrafts, and discloses a method for quickly adding canard outer sections, which comprises the following steps: S1, providing a canard outer section; s2, an unmanned aerial vehicle body is provided, and vehicle arms are arranged on fixed wings of the unmanned aerial vehicle body; and S3, the canard outer section is inserted into the vehicle arm, the canard outer section comprises a positioning piece and a locking piece, and after the canard outer section is installed at the fixed position of the vehicle arm through the positioning piece, the canard outer section and the vehicle arm are locked through the locking piece.

Description

How to quickly add the outer section of the canard Technical Field

[0001] The present invention relates to the field of aircraft, in particular to a method for quickly adding a canard outer section. Background Art

[0002] In actual use, it is found that aircraft takeoffs have different operating conditions. For example, the aircraft needs to have a larger cruising load, reduce noise pollution, or reduce energy loss during flight. Therefore, it is necessary to design a fast structure that can enable the aircraft to meet different cruising load requirements.

[0003] Summary of the Invention

[0004] The purpose of the present invention is to provide a method for quickly adding a canard outer section, which is simple to operate and time-saving, and can achieve the purpose of quickly adding a canard to an aircraft arm.

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

[0006] The present invention provides a method for quickly adding a canard outer section, comprising:

[0007] S1: Provide a canard outer section;

[0008] S2: Provide a drone fuselage, wherein an organic arm is provided on the fixed wing of the drone fuselage;

[0009] S3: Insert the canard outer section into the aircraft arm. The canard outer section includes a positioning piece and a locking piece. After the canard outer section is installed in a fixed position of the aircraft arm through the positioning piece, the canard outer section and the aircraft arm are locked by the locking piece.

[0010] Preferably, the outer section of the canard extends from one end away from the fixed wing to one end close to the fixed wing, and is divided into three regions by the positioning member in the cross section along its thickness direction: a first region, a second region and a third region. The locking member is located in the first region, and the locking member extends from one end of the outer section of the canard away from the fixed wing to one side of the upper wing surface and the lower wing surface of the outer section of the canard away from the fixed wing.

[0011] Preferably, the positioning member includes a first positioning member and a second positioning member, the first positioning member is located at the junction of the first area and the second area, the second positioning member is located at the junction of the second area and the third area, and the diameter range of the positioning member is 20mm-40mm.

[0012] Preferably, the diameter of the first positioning member is greater than that of the second positioning member so as to withstand greater stress on the machine arm, and the diameter ratio between the first positioning member and the second positioning member is 1.44:1.

[0013] Preferably, the canard outer section includes a fixing seat, and before the S3 inserts the canard outer section into the aircraft arm, it also includes S30: placing the fixing seat in the canard outer section in a fitting manner, and the canard outer section is an area enclosed by the upper and lower wing surfaces of the canard outer section away from the fixed wing and the intersection of the upper and lower wing surfaces of the canard outer section close to the fixed wing.

[0014] Preferably, the fixing seat placed in the outer section of the canard is provided with a mounting hole, one end of the positioning member is connected to the fixing seat placed in the outer section of the canard through the mounting hole of the fixing seat, and the other end of the positioning member is connected to the machine arm.

[0015] Preferably, the positioning piece is fixed in the outer section of the canard by gluing.

[0016] Preferably, the locking member includes a bolt and a locking member, the locking member has an internal thread that engages with the bolt and is used to limit the displacement of the bolt; locking the canard outer section and the aircraft arm by the locking member specifically includes: after installing the bolt in the first area, locking the canard outer section and the aircraft arm by the locking member.

[0017] Preferably, the longest line length connecting the two ends of the outer peripheral surface of the locking member is greater than the longest line length connecting two points on the cross section of the locking member in the thickness direction of the canard outer section in the first area, so that the locking member will not rotate with the bolt.

[0018] The present invention also provides a drone, comprising a canard outer segment locked by using the method for quickly adding a canard outer segment as described in the above solution.

[0019] The present invention uses two sets of positioning parts to nest with each other and cooperate with locking parts to position and fasten the outer section of the canard. The canard can be quickly positioned and fixed to the original aircraft fuselage within 20 minutes to meet the different load requirements of the UAV during cruising.

[0020] The beneficial effect of the present invention is that by quickly adding the outer section of the canard, the lift of the aircraft in the fixed-wing state can be increased by 8%-20% based on the original lift value obtained by the original aircraft flight platform, thereby increasing the cruising load of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] FIG1 is a flow chart of a method for quickly adding a canard outer segment according to the present invention;

[0022] FIG2 is a schematic diagram of the outer section of the canard of the present invention;

[0023] FIG3 is a schematic diagram of a positioning member of the present invention;

[0024] FIG4 is a schematic diagram of a locking member 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] This application provides a method for quickly adding a canard outer section, comprising:

[0029] S1: Provide a canard outer section 100;

[0030] S2: Provide a drone fuselage, wherein an organic arm 200 is provided on the fixed wing of the drone fuselage;

[0031] S3: Insert the canard outer section 100 into the arm 200. The canard outer section 100 includes a positioning piece 110 and a locking piece 120. After the canard outer section 100 is installed in a fixed position of the arm 200 through the positioning piece 110, the canard outer section 100 and the arm 200 are locked by the locking piece 120.

[0032] By quickly adding canard segments, the lift of the fixed-wing aircraft can be increased by 8%-20% compared to the original lift value of the original aircraft flight platform. The installation of the quickly removable canard segments can overcome the nose-down effect during flight, avoiding undesirable pitching moments that would otherwise affect the UAV's flight efficiency due to the need to compensate for such moments. Furthermore, the combination of the canard segments with the original aircraft flight platform improves the aircraft's static stability margin by approximately 2%, thereby reducing control losses in the flight control system.

[0033] Furthermore, the canard outer section 100 extends from the end away from the fixed wing to the end closer to the fixed wing. Its cross-section along the thickness direction is divided into three regions by a positioning member 110: a first region, a second region, and a third region. The locking member 120 is located in the first region. The locking member 120 extends from the end of the canard outer section 100 away from the fixed wing to one of the upper and lower wing surfaces of the canard outer section 100 away from the fixed wing. The positioning member 110 can quickly position the canard outer section 100 on the aircraft arm.

[0034] Specifically, in the present application, the positioning member 110 includes a first positioning member and a second positioning member. The first positioning member is located at the junction of the first area and the second area, and the second positioning member is located at the junction of the second area and the third area. Preferably, the diameter range of the positioning member 110 is 20mm-40mm.

[0035] In this embodiment, the diameter of the first positioning member is larger than that of the second positioning member to withstand greater stress on the machine arm. The diameter ratio between the first positioning member and the second positioning member is 1.44:1. Of course, in other embodiments, the diameter of the first positioning member may also be equal to the diameter of the second positioning member.

[0036] The present invention uses two sets of positioning parts to nest with each other and cooperate with locking parts to position and fasten the outer section of the canard. The canard can be quickly positioned and fixed to the original aircraft fuselage within 20 minutes to meet the different load requirements of the UAV during cruising.

[0037] Furthermore, the canard outer section 100 includes a fixing seat 130. Before inserting the canard outer section 100 into the aircraft arm 200 in step S3, the step also includes S30: placing the fixing seat 130 in the canard outer section 100. The canard outer section 100 is the area enclosed by the upper and lower wing surfaces of the canard outer section 100 away from the fixed wing and the intersection of the upper and lower wing surfaces of the canard outer section 100 close to the fixed wing.

[0038] For example, a mounting hole is provided on a fixing seat 130 placed in the canard outer section 100. One end of the positioning member 110 is connected to the fixing seat placed in the canard outer section 100 through the mounting hole of the fixing seat 130, and the other end of the positioning member 110 is connected to the aircraft arm 200. Preferably, the positioning member 110 is fixed to the canard outer section 100 by gluing.

[0039] It is worth noting that in the present application, the locking member 120 includes a bolt and a locking member 121, and the locking member 121 has an internal thread that engages with the bolt to limit the displacement of the bolt; locking the canard outer section 100 and the arm 200 by the locking member 120 specifically includes: after installing the bolt in the first area, locking the canard outer section 100 and the arm 200 by the locking member 121.

[0040] Preferably, the length of the longest line connecting the two ends of the outer peripheral surface of the locking member 121 is greater than the length of the longest line connecting the two points on the cross section of the locking member 121 in the thickness direction of the canard outer section in the first area, so that the locking member 121 will not rotate with the bolt, that is, the locking member 121 can play an anti-loosening effect.

[0041] The present application also provides a drone, which includes a canard outer segment 100 locked using the method for quickly adding a canard outer segment described in the above solution.

[0042] 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 adding a canard outer section, characterized in that: include: S1: Provide a canard outer section 100; S2: Provide a drone fuselage, wherein an organic arm 200 is provided on the fixed wing of the drone fuselage; S3: Insert the canard outer section 100 into the arm 200. The canard outer section 100 includes a positioning member 110 and a locking member 120. After the canard outer section 100 is installed in a fixed position of the arm 200 through the positioning member 110, the canard outer section 100 and the arm 200 are locked by the locking member 120.

2. The method for quickly adding a canard outer section according to claim 1, characterized in that: The canard outer section 100 extends from one end away from the fixed wing to one end close to the fixed wing, and is divided into three areas by the positioning member 110 in the cross section along its thickness direction: a first area, a second area and a third area. The locking member 120 is located in the first area. The locking member 120 extends from one end of the canard outer section 100 away from the fixed wing to one side of the upper wing surface and the lower wing surface of the canard outer section 100 away from the fixed wing.

3. The method for quickly adding a canard outer section according to claim 1, characterized in that: The positioning member 110 includes a first positioning member and a second positioning member. The first positioning member is located at the intersection of the first area and the second area, and the second positioning member is located at the intersection of the second area and the third area. The diameter range of the positioning member 110 is 20 mm-40 mm.

4. The method for quickly adding a canard outer section according to claim 3, characterized in that: The diameter of the first positioning member is greater than that of the second positioning member so as to withstand greater stress on the machine arm. The diameter ratio between the first positioning member and the second positioning member is 1.44:

1.

5. The method for quickly adding a canard outer section according to claim 1, characterized in that: The canard outer section 100 includes a fixing seat 130. Before inserting the canard outer section 100 into the aircraft arm 200 in S3, the step further includes S30: placing the fixing seat 130 in a fit within the canard outer section 100. The canard outer section 100 is an area enclosed by the upper and lower wing surfaces of the canard outer section 100 away from the fixed wing and the intersection of the upper and lower wing surfaces of the canard outer section 100 close to the fixed wing.

6. The method for quickly adding a canard outer section according to claim 5, characterized in that: The fixing seat 130 placed in the canard outer section 100 is provided with a mounting hole, one end of the positioning member 110 is connected to the fixing seat placed in the canard outer section 100 through the mounting hole of the fixing seat 130, and the other end of the positioning member 110 is connected to the machine arm 200.

7. The method for quickly adding a canard outer section according to claim 6, characterized in that: The positioning member 110 is fixed in the canard outer section 100 by gluing.

8. The method for quickly adding a canard outer section according to claim 2, characterized in that: The locking member 120 includes a bolt and a locking member 121, and the locking member 121 has an internal thread that engages with the bolt to limit the displacement of the bolt; locking the canard outer section 100 and the arm 200 by the locking member 120 specifically includes: after installing the bolt in the first area, locking the canard outer section 100 and the arm 200 by the locking member 121.

9. The method for quickly adding a canard outer section according to claim 8, characterized in that: The longest connecting length of the two ends of the outer peripheral surface of the locking member 121 is greater than the longest connecting length of the two points on the cross section of the locking member 121 in the thickness direction of the canard outer section in the first area, so that the locking member 121 will not rotate with the bolt.

10. A drone, characterized in that: The drone includes a canard outer segment 100 locked using the method for quickly adding a canard outer segment according to claims 1-9.

Images