Aircraft and method for connecting canards and arms of aircraft

Abstract

The invention relates to the technical field of aircrafts, and discloses an aircraft and a canard and arm connecting method thereof. The canard and arm connecting method is used for coupling a canard and an arm, the canard comprises a coupling insertion part, and the coupling insertion part comprises a plurality of fixing parts; the vehicle arm comprises a vehicle arm insertion cavity, an insertion opening is formed in one end of the vehicle arm insertion cavity, and the coupling insertion part can be inserted into the vehicle arm insertion cavity through the insertion opening and is fixed in the vehicle arm through the fixing part. According to the method for connecting the canards and the arms, the canards and the arms form a detachable structure, and the position of the lift center can be adjusted by replacing the canards of different styles so as to adapt to aircraft cabins of different gravity centers.

Description

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 canard and an 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. Many aircraft are also beginning to conduct 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 a cockpit or a cargo hold, 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. As a result, 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. Summary of the invention

[0003] 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 an 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.

[0004] In order to solve the above technical problems, the present application provides a method for connecting a canard wing and a machine arm, which is used to couple the canard wing and the machine arm. The method includes:

[0005] S1: Provide a canard wing, the canard wing comprising a coupling plug-in portion, the coupling plug-in portion comprising a plurality of fixing portions;

[0006] 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;

[0007] S3: inserting the coupling plug-in part into the arm plug-in cavity through the plug-in interface, and fixing it in the arm through the fixing part.

[0008] 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.

[0009] Optionally, the coupling plug-in portion includes a pair of supporting beams and fixing hole plates that match each other, the fixing hole plates are coupled to the side walls of the supporting beams, the fixing portion is arranged on the fixing hole plates, and the fixing portion includes a plurality of vertically opened canard fixing holes.

[0010] 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;

[0011] The fixing in the machine arm by the fixing part specifically includes:

[0012] 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.

[0013] 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 each other.

[0014] 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.

[0015] Optionally, the canard body includes a pair of canard beams, and the pair of canard beams are coupled to a pair of support beams of the coupling plug-in portion in a one-to-one correspondence.

[0016] Optionally, an upper box portion is provided on the upper portion 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 on the coupling plug-in portion to form a stable support.

[0017] Optionally, the canard further comprises an aileron, the aileron comprises a first end surface, at least one positioning pin and at least two fixing pins are provided on the first end surface, the arm comprises a second end surface, at least three pin holes are provided on the second end surface, wherein the positioning pin and the fixing pin have different lengths;

[0018] The step S3 also 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 fit each other.

[0019] 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, and after step S4, it also includes S5: 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 extension directions of the first fixing pin hole and the second fixing pin hole are perpendicular to each other.

[0020] 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 an 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

[0021] Figure 1 The figure shows a flow chart of the method for connecting the canard wing and the aircraft arm according to the first embodiment of the present application.

[0022] Figure 2 It is a schematic structural diagram of the canard-arm connection structure of the first embodiment of the present application;

[0023] Figure 3 It is a schematic diagram showing the separation structure of the canard and the machine arm connection structure of the first embodiment of the present application;

[0024] Figure 4 It is a schematic structural diagram of the canard-arm connection structure of the first embodiment of the present application;

[0025] Figure 5 It is a schematic structural diagram of the aileron and the arm connection structure of the first embodiment of the present application;

[0026] Figure 6 It 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;

[0027] Figure 7 Shown is a schematic structural diagram of an aircraft according to a second embodiment of the present application. DETAILED DESCRIPTION

[0028] The following embodiments further illustrate the technical solution of the present application. It is to be understood that the specific embodiments described herein are only used to explain the present application. It should also be noted that, for ease of description, only the parts related to the present application are shown in the drawings, not all.

[0029] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0030] In the present application, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0031] The following describes the first embodiment of the present application with reference to the accompanying drawings. Figure 1 and Figure 2 As shown, the canard-arm connection method of the embodiment of the present application is used to couple the canard 1 and the arm 2. The canard-arm connection method of the embodiment of the present application includes the following steps:

[0032] S1: Provide a canard wing, the canard wing includes a coupling plug-in part, and the coupling plug-in part includes a plurality of fixing parts.

[0033] Specifically, Figures 2 to 4 As shown, the method for connecting a canard wing to an arm of an embodiment of the present application includes: providing a canard wing 1, wherein the canard wing 1 includes a canard wing 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 wing body 15. The coupling plug-in portion 10 includes a pair of supporting beams 12 and fixing holes 13 that are matched and connected to each other, and the fixing holes 13 are bolted to the side wall of the supporting beam 12, and the fixing holes 13 include a plurality of fixing portions 11, and the fixing portions 11 include a plurality of canard fixing holes 14 opened vertically. The fixing holes 13 are installed on the side wall of the supporting beam 12, and the fixing holes 13 are only subjected to shear force in the vertical direction, so they are not easy to loosen. In this embodiment, there are 3 canard fixing holes 14, but of course, it can also be other numbers.

[0034] S2: Provide an arm, the arm comprising an arm plug-in cavity, and an insertion interface is provided at one end of the arm plug-in cavity.

[0035] Specifically, an arm 2 is provided, the arm 2 includes an arm plug-in cavity 20, and an insertion port 21 is provided at one end of the arm plug-in cavity 20. An arm fixing plate 22 is provided at the bottom of the arm plug-in cavity 20, and the arm fixing plate 22 is fixed to the arm 2. A plurality of arm fixing holes 23 are provided on the arm fixing plate 22, and the number of the arm fixing holes 23 is the same as that of the canard fixing holes 14.

[0036] S3: Insert the coupling plug-in part into the machine arm plug-in cavity through the plug-in interface, and fix it in the machine arm through the fixing part.

[0037] After the coupling plug-in part 10 is inserted into the arm plug-in cavity 20, the canard fixing hole 14 can be aligned one by one with the arm fixing hole 23. The method for connecting the canard to the arm includes: aligning the canard fixing hole (14) with the arm fixing hole (23) one by one, and connecting the canard fixing hole (14) with the arm fixing hole 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 wing fixing hole 14 can be provided inside the upper box portion 24 , and a bolt is passed through the through hole of the upper box portion 24 to connect the canard wing fixing hole 14 and the arm fixing hole 23 in series, thereby fixing the coupling plug-in portion 10 in the arm plug-in cavity 20 .

[0038] A structural member 25 is also provided at the upper part of the upper box part 24, and the structural member 25 is used to connect the upper and lower skins of the arm to enhance the rigidity of the arm. The structural member 25 does not interfere with the bolts connecting the canard fixing hole 14 and the arm fixing hole 23. Preferably, after the coupling plug-in part 10 is inserted into the arm plug-in cavity 20, the inner wall of the arm plug-in cavity 20 can be fitted with the outer wall of the coupling plug-in part 10 to form a stable support. The canard body 15 also includes a pair of canard beams 16, and the pair of canard beams 16 are coupled to the pair of support beams 12 of the coupling plug-in part 10 in a one-to-one manner, so that they are not easily broken by force, thereby ensuring the connection strength of the coupling plug-in part 10.

[0039] The canard-arm connection method of the embodiment of the present application enables the canard and the arm 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.

[0040] Furthermore, if Figure 2 As shown, a canard cover 4 is also 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.

[0041] In some embodiments, after step S3, the following steps are further included:

[0042] S4: Align at least one positioning pin and at least two fixing pins sequentially with at least three pin holes, so that the first end surface and the second end surface fit each other.

[0043] Specifically, Figure 5 and Figure 6As shown, the canard 1 also includes an aileron 3, the aileron 3 includes a first end face 30, a positioning pin 31 and two fixing pins 32 are provided on the first end face 30, and the arm 2 includes a second end face 26, and the second end face 26 is provided with three pin holes 17. After step S3, it also includes: inserting a positioning pin 31 and two fixing pins 32 into the three pin holes 17 in sequence one by one, so that the first end face 30 and the second end face 26 fit each other, wherein 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, and the lengths of the positioning pin 31 and the fixing pin 32 are different. In this embodiment, the length of the positioning pin 31 is greater than the length of the fixing pin 32. The length of the second fixing pin 322 is greater than the length of 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.

[0044] After step S4, the method further includes step S5:

[0045] 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.

[0046] 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, wherein the extension directions of the first fixing pin hole a and the second fixing pin hole b are perpendicular to each other. For example, the extension direction of the first fixing pin hole a inside the first fixing pin 321 can be along the fixing pin insertion direction, and the bolt is passed through the fixing plate on the arm 2 and then connected to the first fixing pin hole a, thereby connecting the first fixing pin 321 and the arm 2. The extension direction of the second fixing pin hole b inside the second fixing pin 322 is perpendicular to the fixing pin insertion direction. The bolt is inserted downward from the upper part of the arm 2, passed through the fixing plate inside the arm 2 and then connected to the second fixing pin hole b, so as to connect the second fixing pin 322 and the arm 2. Thus, the connection between the aileron 3 and the arm 2 can be better ensured by connecting two bolts in perpendicular directions. It should be noted that the number of the positioning pins 31 can also be more than one, and the number of the fixing pins 32 can also be more than two. The extension directions of the first fixing pin hole a and the second fixing pin hole b can also be interchanged, which is not limited here.

[0047] The second embodiment of the present application also provides an aircraft, such as Figure 7 As shown, it includes a canard 1 and a pair of arms 2, and the canard 1 and the pair of arms 2 are coupled respectively by the canard-arm connection method described above. The canard-arm connection method of the embodiment of the present application enables the canard and the arm to form a detachable structure, and the position of the lift center can be adjusted by replacing different styles of canards to adapt to aircraft cabins with different centers of gravity.

[0048] The above embodiments are merely illustrative of the principles and effects of the present application. Anyone familiar with the technology may modify or change the above embodiments without violating the purpose of the present application. Therefore, all equivalent modifications or changes made by a person with ordinary knowledge in the relevant technical field without departing from the purpose disclosed in the present application shall still be covered by the claims of the present 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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