Aircraft, and method for connecting canard and arm thereof

Abstract

The present application relates to the technical field of aircrafts, and discloses an aircraft, and a method for connecting a canard and an arm thereof. The method for connecting the canard and the arm in the present application is used for coupling the canard to the arm. The canard comprises a coupling insertion portion, and the coupling insertion portion comprises a plurality of fixing portions; the arm comprises an arm insertion cavity, an insertion port is formed on one end of the arm insertion cavity, and the coupling insertion portion is configured to be inserted into the arm insertion cavity by means of the insertion port and be fixed in the arm by means of the fixing portions. According to the method for connecting the canard and the arm in the embodiments of the present application, the canard and the arm form a detachable structure, and the position of the center of lift can be adjusted by replacing the canards of different styles so as to adapt to aircraft cabins having different centers of gravity.

Description

Aircraft and method for connecting its canard and aircraft arm Technical Field

[0001] The present application relates to the field of aircraft technology, and in particular to an aircraft and a method for connecting its canards to an aircraft arm. Background Art

[0002] Currently, the flight platform is equipped with a cabin to enable the aircraft to carry people and cargo. The flight platform generally includes components such as arms, fuselage, canards and control systems. At present, many aircraft have also begun to carry out platform management of components in design, that is, to make certain components universal. Platform management is conducive to reducing R&D investment and reducing R&D costs. For example, the same flight platform can be equipped with different styles of cabins, such as cockpits or cargo holds, to meet different project requirements. However, the replacement of the cabin may cause the center of gravity of the aircraft to change, while the center of lift cannot be adjusted accordingly. Therefore, the aircraft will not be able to obtain the best positional relationship between the center of lift and the center of gravity, and will not be able to obtain the best flight stability.

[0003] Summary of the Invention

[0004] The purpose of the present application is to provide an aircraft and a method for connecting its canards and arms. The method for connecting the canards and arms in the embodiment of the present application enables the canards and arms to form a detachable structure, and the position of the lift center can be adjusted by replacing canards of different styles to adapt to aircraft cabins with different centers of gravity.

[0005] To solve the above technical problems, the present application provides a method for connecting a canard to an arm, for coupling the canard and the arm, the method comprising:

[0006] S1: Provide a canard, wherein the canard includes a coupling plug-in portion, and the coupling plug-in portion includes a plurality of fixing portions;

[0007] S2: Provide an arm, the arm comprising an arm plug-in cavity, one end of the arm plug-in cavity being provided with a plug-in interface;

[0008] S3: inserting the coupling plug-in portion into the arm plug-in cavity through the plug interface, and fixing it in the arm through the fixing portion.

[0009] The present application provides an aircraft, comprising a canard and a pair of arms, wherein the canard and the pair of arms are respectively coupled by the above-mentioned canard-arm connection method.

[0010] Optionally, the coupling plug-in portion includes a pair of mutually matched support beams and fixed hole plates, the fixed hole plates are coupled to the side walls of the support beams, the fixed portion is arranged on the fixed hole plates, and the fixed portion includes a plurality of vertically opened canard fixing holes.

[0011] Optionally, an arm fixing plate is provided at the bottom of the arm plug-in cavity, and a plurality of arm fixing holes are provided on the arm fixing plate;

[0012] The fixing part is fixed to the machine arm, specifically comprising:

[0013] The canard fixing holes are aligned one by one with the machine arm fixing holes, and the canard fixing holes are connected with the machine arm fixing holes by bolts, so as to fix the coupling plug-in part in the machine arm.

[0014] Optionally, after the coupling plug-in portion is inserted into the arm plug-in cavity, the inner wall of the arm plug-in cavity and the outer wall of the coupling plug-in portion fit together.

[0015] Optionally, the canard includes a canard body and a pair of coupling plug-in parts, and the pair of coupling plug-in parts are symmetrically distributed on both sides of the canard body.

[0016] Optionally, the canard body includes a pair of canard beams, and the pair of canard beams are coupled to the pair of support beams of the coupling plug-in portion in a one-to-one correspondence.

[0017] Optionally, an upper box portion is provided on the upper part of the arm plug-in cavity, and the upper box portion is configured such that after the coupling plug-in portion is inserted into the arm plug-in cavity, the upper box portion and the arm fixing plate form an upper and lower clamping of the coupling plug-in portion to form a stable support.

[0018] Optionally, the canard further includes an aileron, the aileron includes a first end surface, the first end surface is provided with at least one locating pin and at least two fixing pins, the arm includes a second end surface, the second end surface is provided with at least three pin holes, wherein the locating pin and the fixing pin have different lengths;

[0019] After S3, the method further includes: step S4: aligning the at least one positioning pin and the at least two fixing pins with the at least three pin holes one by one in sequence, so that the first end surface and the second end surface are fitted with each other.

[0020] Optionally, the at least two fixing pins include a first fixing pin and a second fixing pin, the first fixing pin is provided with a first fixing pin hole, and the second fixing pin is provided with a second fixing pin hole. After step S4, S5 is also included: passing a bolt through the machine arm and connecting it to the first fixing pin hole to connect the machine arm and the first fixing pin; passing a bolt through the machine arm and connecting it to the second fixing pin hole to connect the machine arm and the second fixing pin, wherein the extension directions of the first fixing pin hole and the second fixing pin hole are perpendicular to each other.

[0021] The purpose of the present application is to provide an aircraft and a method for connecting its canards and arms. The method for connecting the canards and arms in the embodiment of the present application enables the canards and arms to form a detachable structure, and the position of the lift center can be adjusted by replacing canards of different styles to adapt to aircraft cabins with different centers of gravity. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] FIG1 is a schematic diagram showing a flow chart of a method for connecting a canard to an aircraft arm according to a first embodiment of the present application.

[0023] FIG2 is a schematic structural diagram of the canard-to-arm connection structure according to the first embodiment of the present application;

[0024] FIG3 is a schematic diagram showing the separation structure of the canard and the aircraft arm connection structure according to the first embodiment of the present application;

[0025] FIG4 is a schematic structural diagram of the canard-to-arm connection structure according to the first embodiment of the present application;

[0026] FIG5 is a schematic structural diagram of the aileron-arm connection structure according to the first embodiment of the present application;

[0027] FIG6 is a schematic diagram showing the separation structure of the aileron and the arm connection structure according to the first embodiment of the present application;

[0028] FIG7 is a schematic structural diagram of an aircraft according to a second embodiment of the present application. DETAILED DESCRIPTION

[0029] 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.

[0030] 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.

[0031] 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.

[0032] The following describes a first embodiment of the present application with reference to the accompanying drawings. As shown in FIG1 and FIG2 , a method for connecting a canard to an arm according to an embodiment of the present application is used to couple a canard 1 to an arm 2. The method for connecting a canard to an arm according to an embodiment of the present application includes the following steps:

[0033] S1: Provide a canard, the canard including a coupling plug-in portion, and the coupling plug-in portion includes a plurality of fixing portions.

[0034] Specifically, as shown in Figures 2 to 4, the method for connecting a canard to an aircraft arm according to an embodiment of the present application includes: providing a canard 1, wherein the canard 1 includes a canard body 15 and a coupling plug-in portion 10, and a pair of coupling plug-in portions 10 are symmetrically distributed on both sides of the canard body 15. The coupling plug-in portion 10 includes a pair of supporting beams 12 and fixing holes 13 that are connected to each other. The fixing holes 13 are bolted to the side walls of the supporting beams 12. The fixing holes 13 include a plurality of fixing portions 11, and the fixing portions 11 include a plurality of vertically opened canard fixing holes 14. The fixing holes 13 are installed on the side walls of the supporting beams 12. The fixing holes 13 are only subjected to shear forces in the vertical direction, and therefore are not easy to loosen. In this embodiment, there are three canard fixing holes 14, but other numbers are also possible.

[0035] S2: Provide an arm, the arm including an arm plug-in cavity, and an insertion interface is provided at one end of the arm plug-in cavity.

[0036] Specifically, an arm 2 is provided. The arm 2 includes an arm insertion cavity 20, one end of which is provided with an insertion port 21. An arm fixing plate 22 is provided at the bottom of the arm insertion cavity 20 and is fixed to the arm 2. The arm fixing plate 22 is provided with a plurality of arm fixing holes 23, the same number as the canard fixing holes 14.

[0037] S3: Insert the coupling plug-in part into the machine arm plug-in cavity through the plug interface, and fix it in the machine arm through the fixing part.

[0038] After the coupling plug-in part 10 is inserted into the arm plug-in cavity 20, the canard fixing holes 14 can be aligned one by one with the arm fixing holes 23. The method for connecting the canard to the arm includes: aligning the canard fixing holes (14) with the arm fixing holes (23) one by one, and connecting the canard fixing holes (14) with the arm fixing holes by bolts, thereby fixing the coupling plug-in part (10) in the arm (2). An upper box part 24 is also provided on the upper part of the arm plug-in cavity 20. After the coupling plug-in part 10 is inserted into the arm plug-in cavity 20, the upper box part 24 and the arm fixing plate 22 form an upper and lower clamping for the coupling plug-in part 10 to absorb the vibration of the coupling plug-in part 10 in the arm plug-in cavity 20, thereby forming a stable support. A through hole corresponding to the canard fixing hole 14 can be provided inside the upper box part 24 , and a bolt is passed through the through hole of the upper box part 24 to connect the canard fixing hole 14 and the arm fixing hole 23 in series, thereby fixing the coupling plug part 10 in the arm plug cavity 20 .

[0039] A structural member 25 is also provided above the upper box portion 24. This structural member 25 is used to connect the upper and lower skins of the arm to enhance the arm's rigidity. The structural member 25 does not interfere with the bolts connecting the canard fixing holes 14 and the arm fixing holes 23. Preferably, after the coupling plug-in portion 10 is inserted into the arm insertion cavity 20, the inner wall of the arm insertion cavity 20 can be aligned with the outer wall of the coupling plug-in portion 10, thereby forming a stable support. The canard body 15 also includes a pair of canard spars 16. These canard spars 16 are coupled to the pair of support beams 12 of the coupling plug-in portion 10 in a one-to-one manner, making them less likely to break under stress, thereby ensuring the connection strength of the coupling plug-in portion 10.

[0040] The method for connecting the canard and the arm in the embodiment of the present application enables the canard and the arm to form a detachable structure. The position of the lift center can be adjusted by replacing canards of different styles to adapt to aircraft cabins with different centers of gravity.

[0041] Furthermore, as shown in Figure 2, a canard cover 4 is provided on the side of the coupling plug-in part 10 close to the canard 1. After the coupling plug-in part 10 is inserted into the arm plug-in cavity 20, the canard cover 4 can be close to the side wall of the arm 2, which can effectively prevent rainwater and the like from entering the interior of the arm 2 through the plug-in interface 21.

[0042] In some embodiments, after step S3, the following steps are further included:

[0043] S4: Align at least one positioning pin and at least two fixing pins sequentially with the at least three pin holes, so that the first end surface and the second end surface fit together.

[0044] Specifically, as shown in Figures 5 and 6, the canard 1 also includes an aileron 3, which includes a first end surface 30, on which is provided a positioning pin 31 and two fixing pins 32. The arm 2 includes a second end surface 26, which is provided with three pin holes 17. After step S3, the process further includes inserting one positioning pin 31 and two fixing pins 32 into the three pin holes 17 in a one-to-one correspondence, so that the first end surface 30 and the second end surface 26 are aligned with each other. The positioning pin 31 can locate the installation position of the aileron 3. The two fixing pins 32 include a first fixing pin 321 and a second fixing pin 322. The positioning pins 31 and fixing pins 32 have different lengths. In this embodiment, the positioning pin 31 is longer than the fixing pin 32. The second fixing pin 322 is longer than the first fixing pin 321. Thus, the positioning pin 31, the second fixing pin 322, and the first fixing pin 321 are sequentially inserted into the corresponding pin holes 17.

[0045] After step S4, the method further includes step S5:

[0046] Pass the bolt through the machine arm and insert it into the first fixing pin hole to connect the machine arm and the first fixing pin; pass the bolt through the machine arm and insert it into the second fixing pin hole to connect the machine arm and the second fixing pin, wherein the extension directions of the first fixing pin hole and the second fixing pin hole are perpendicular to each other.

[0047] Specifically, the first fixing pin 321 includes a first fixing pin hole a, and the second fixing pin 322 includes a second fixing pin hole b. The first fixing pin hole a and the second fixing pin hole b extend perpendicularly to each other. For example, the first fixing pin hole a can extend within the first fixing pin 321 in the direction of fixing pin insertion. A bolt can be inserted through the fixing plate on the arm 2 and then inserted into the first fixing pin hole a to connect the first fixing pin 321 and the arm 2. The second fixing pin hole b can extend perpendicularly to the direction of fixing pin insertion. A bolt can be inserted downward from the top of the arm 2, through the fixing plate inside the arm 2, and then inserted into the second fixing pin hole b to connect the second fixing pin 322 and the arm 2. This connection, achieved by two bolts extending in perpendicular directions, can better secure the connection between the aileron 3 and the arm 2. It should be noted that the number of positioning pins 31 can be more than one, and the number of fixing pins 32 can be more than two. The extending directions of the first fixing pin hole a and the second fixing pin hole b can also be interchanged, and this is not a limitation here.

[0048] A second embodiment of the present application further provides an aircraft, as shown in FIG7 , comprising a canard 1 and a pair of arms 2, the canard 1 and the pair of arms 2 being coupled using the canard-to-arm connection method described above. The canard-to-arm connection method of the present embodiment allows the canard and the arms to form a detachable structure, and the position of the center of lift can be adjusted by replacing different canard styles to accommodate aircraft cabins with different centers of gravity.

[0049] 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 connecting a canard wing to an arm, applied to a drone, characterized in that: The method comprises: S1: A canard wing (1) is provided, wherein the canard wing (1) comprises a coupling plug-in portion (10), and the coupling plug-in portion (10) comprises a plurality of fixing portions (11); S2: providing an arm (2), the arm (2) comprising an arm plug-in cavity (20), one end of the arm plug-in cavity (20) being provided with a plug-in interface (21); S3: inserting the coupling plug-in portion (10) into the machine arm plug-in cavity (20) via the plug-in port (21), and fixing it in the machine arm (2) via the fixing portion (11).

2. The method for connecting a canard to an arm according to claim 1, characterized in that: The coupling plug-in portion (10) comprises a pair of supporting beams (12) and fixing holes (13) that match each other, the fixing holes (13) being coupled to the side wall of the supporting beam (12), the fixing portion (11) being arranged on the fixing holes (13), and the fixing portion (11) comprising a plurality of canard fixing holes (14) that are vertically opened.

3. The method for connecting a canard to an arm according to claim 2, characterized in that: An arm fixing plate (22) is provided at the bottom of the arm plug-in cavity (20), and a plurality of arm fixing holes (23) are provided on the arm fixing plate (22); The fixing part (11) is fixed to the machine arm (2), and specifically comprises: The canard wing fixing holes (14) are aligned one by one with the machine arm fixing holes (23), and the canard wing fixing holes (14) are connected with the machine arm fixing holes by bolts, thereby fixing the coupling plug-in portion (10) in the machine arm (2).

4. The method for connecting a canard to an arm according to claim 1, characterized in that: After the coupling plug-in portion (10) is inserted into the machine arm plug-in cavity (20), the inner wall of the machine arm plug-in cavity (20) and the outer wall of the coupling plug-in portion (10) fit each other.

5. The method for connecting a canard to an arm according to claim 1, characterized in that: The canard (1) comprises a canard body (15) and a pair of coupling plug-in parts (10), wherein the pair of coupling plug-in parts (10) are symmetrically distributed on both sides of the canard body (15).

6. The method for connecting a canard to an arm according to claim 5, characterized in that: The canard body (15) comprises a pair of canard beams (16) inside, and the pair of canard beams (16) are coupled with a pair of support beams (12) of the coupling plug-in portion (10) in a one-to-one correspondence.

7. The method for connecting a canard to an aircraft arm according to claim 3, characterized in that: An upper box portion (24) is provided on the upper portion of the machine arm plug-in cavity (20); After the coupling plug-in portion (10) is inserted into the machine arm plug-in cavity (20), the upper box portion (24) and the machine arm fixing plate (22) clamp the coupling plug-in portion (10) up and down to form a stable support.

8. The method for connecting a canard to an aircraft arm according to claim 5, characterized in that: The canard (1) further comprises an aileron (3), the aileron (3) comprising a first end surface (30), the first end surface (30) being provided with at least one positioning pin (31) and at least two fixing pins (32), the arm (2) comprising a second end surface (25), the second end surface (25) being provided with at least three pin holes (17), wherein the positioning pin (31) and the fixing pin (32) have different lengths; After S3, the method further includes: step S4: aligning the at least one positioning pin (31) and the at least two fixing pins (32) with the at least three pin holes (17) one by one in sequence, so that the first end surface (30) and the second end surface (25) are in contact with each other.

9. The method for connecting a canard to an aircraft arm according to claim 8, characterized in that: The at least two fixing pins (32) include a first fixing pin (321) and a second fixing pin (322), wherein the first fixing pin (321) is provided with a first fixing pin hole (a), and the second fixing pin (322) is provided with a second fixing pin hole (b), and after the step S4, the step S5 further includes: passing a bolt through the machine arm (2) and connecting it to the first fixing pin hole (a) to connect the machine arm (2) and the first fixing pin (321); passing a bolt through the machine arm (2) and connecting it to the second fixing pin hole (b) to connect the machine arm (2) and the second fixing pin (322), wherein the extension directions of the first fixing pin hole (a) and the second fixing pin hole (b) are perpendicular to each other.

10. An aircraft, characterized in that: The invention comprises a canard (1) and a pair of machine arms (2), wherein the canard (1) and the pair of machine arms (2) are respectively coupled by the canard and machine arm connection method according to any one of claims 1 to 9.

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