Aircraft and canard and arm connecting structure thereof

Abstract

The present application relates to the technical field of aircrafts, and discloses an aircraft and a canard and arm connecting structure thereof. The canard and arm connecting structure of the present application is used for coupling a canard and arms; the canard comprises coupling inserting parts, and each coupling inserting part comprises a plurality of fixing parts; each arm comprises an arm insertion cavity, an insertion port is formed on one end of the arm insertion cavity; and the coupling inserting part is configured to be inserted into the arm insertion cavity by means of the insertion port and fixed in the arm by means of the fixing parts. According to the present application, the canard and the arms form a detachable structure, thereby facilitating transportation and reducing the transportation costs.

Description

Aircraft and its canard and arm connection structure Technical Field

[0001] The present application relates to the field of aircraft technology, and in particular to an aircraft and a connection structure between its canard and an arm. Background Art

[0002] Currently, the canards and arms of many aircraft are integrally formed structures, which means that the canards and arms need to be transported together during transportation, which is bulky and inconvenient to transport.

[0003] Summary of the Invention

[0004] The purpose of the present application is to provide an aircraft and a connection structure between its canard and arm. The canard and arm of the present application form a detachable structure, which is convenient for transportation and reduces transportation costs.

[0005] In order to solve the above technical problems, the present application provides a canard and arm connection structure for coupling the canard and the arm, the canard includes a coupling plug-in portion, and the coupling plug-in portion includes several fixing portions; the arm includes an arm plug-in cavity, and one end of the arm plug-in cavity is provided with a plug interface, and the coupling plug-in portion is configured to be inserted into the arm plug-in cavity through the plug interface and fixed in the arm through the fixing portion.

[0006] 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 through the above-mentioned canard-arm connection structure.

[0007] 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 fixing portion is arranged on the fixed hole plates, and the fixing portion includes a vertically opened canard fixing hole.

[0008] 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. After the coupling plug-in part is inserted into the arm plug-in cavity, the canard fixing holes are configured to be opposite to the arm fixing holes one by one and connected by bolts.

[0009] Optionally, after the coupling plug-in portion is inserted into the arm plug-in cavity, the inner wall of the arm plug-in cavity is configured to fit together with the outer wall of the coupling plug-in portion.

[0010] 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.

[0011] 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.

[0012] 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.

[0013] Optionally, the canard also 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, and the at least one locating pin and the at least two fixing pins are configured to be able to be inserted into the at least three pin holes one by one, so that the first end surface and the second end surface fit each other.

[0014] 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 is bolted to the machine arm, the second fixing pin is provided with a second fixing pin hole and is bolted to the machine arm, wherein the extension directions of the first fixing pin hole and the second fixing pin hole are perpendicular to each other.

[0015] The canard and the aircraft arm of the present application form a detachable structure, which is convenient for transportation and reduces transportation costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] FIG1 is a schematic structural diagram of a canard-to-arm connection structure according to a first embodiment of the present application;

[0017] FIG2 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;

[0018] FIG3 is a schematic structural diagram of the canard-to-arm connection structure according to the first embodiment of the present application;

[0019] FIG4 is a schematic structural diagram of the aileron-to-arm connection structure according to the first embodiment of the present application;

[0020] FIG5 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;

[0021] FIG6 is a schematic structural diagram of an aircraft according to a second embodiment of the present application. DETAILED DESCRIPTION

[0022] 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 the parts relevant to the present application are shown in the accompanying drawings, not all of them.

[0023] 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.

[0024] 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.

[0025] The following describes the first embodiment of the present application with reference to the accompanying drawings. As shown in Figures 1 and 2, the canard and arm connection structure of the embodiment of the present application is used to couple the canard 1 and the arm 2, wherein the canard 1 includes a coupling plug-in portion 10, and the coupling plug-in portion 10 includes a plurality of fixing portions 11; 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. The coupling plug-in portion 10 is configured to be inserted into the arm plug-in cavity 20 through the plug-in port 21 and fixed to the arm 2 through the fixing portion 11.

[0026] Specifically, the canard 1 includes a canard body 15 and a pair of coupling plug-in parts 10, and the pair of coupling plug-in parts 10 are symmetrically distributed on both sides of the canard body 15. As shown in Figure 3, the coupling plug-in part 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. Each fixing hole 13 is provided with a plurality of fixing parts (11), and each fixing part (11) is provided with a canard fixing hole 14 opened vertically. The fixing hole 13 is installed on the side wall of the support beam 12 and is only subjected to shear force in the vertical direction, so it is not easy to loosen. In this embodiment, there are 3 canard fixing holes, of course, it can also be other numbers. The bottom of the arm plug-in cavity 20 is provided with an arm fixing plate 22, which itself is fixed to the arm. The arm fixing plate 22 is provided with a plurality of arm fixing holes 23, the number of which is the same as the canard fixing holes 14. After the coupling plug-in part 10 is inserted into the arm plug-in cavity 20, the canard fixing holes 14 can be aligned with the arm fixing holes 23 one by one and connected by bolts. Specifically, an upper box part 24 is 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. Through holes corresponding to the canard fixing holes 14 can be provided inside the upper box part 24. Bolts can be inserted through the through holes of the upper box part 24 to connect the canard fixing holes 14 and the arm fixing holes 23 in series, thereby fixing the coupling plug-in part 10 in the arm plug-in cavity 20. A structural member 25 is also provided on the upper part of the upper box part 24. 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 plug-in direction of the bolt. 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, thereby forming a stable support. The canard body 15 also includes a pair of canard beams 16. The pair of canard beams 16 are coupled one-to-one with the pair of support beams 12 of the coupling plug-in part 10, making it less likely to break under stress, thereby ensuring the firmness of the coupling plug-in part 10. The canard of the present application forms a detachable structure with the arm, which is convenient for transportation and reduces transportation costs.

[0027] 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.

[0028] Furthermore, as shown in Figures 4 and 5, the canard 1 also includes an aileron 3. The aileron 3 includes a first end surface 30, on which a positioning pin 31 and two fixing pins 32 are provided. The arm 2 includes a second end surface 26, on which three pin holes 17 are provided. One positioning pin 31 and two fixing pins 32 can be inserted 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 first fixing pin 321 includes a first fixing pin hole a and is bolted to the arm 2. The second fixing pin 322 includes a second fixing pin hole b and is bolted to the arm 2. 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 within the first fixing pin 321 can extend in the direction of the fixing pin insertion. A bolt can pass through the fixing plate on the arm and then enter the first fixing pin hole a, thereby bolting the first fixing pin 321 to the arm 2. The second fixing pin hole b within the second fixing pin 322 can extend perpendicular to the insertion direction. A bolt can be inserted downward from the upper portion of the arm, pass through the fixing plate on the arm, and enter the second fixing pin hole b, thereby bolting the second fixing pin 322 to the arm 2. This two bolted connections in mutually 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 one or more, and the number of fixing pins 32 can be two or more. It should be noted that the positioning pins 31 and fixing pins 32 have different lengths. In this embodiment, the length of the positioning pin 31 is greater than that of the fixing pin 32. The length of the second fixing pin 322 is greater than that 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.

[0029] A second embodiment of the present application further provides an aircraft, as shown in FIG6 , comprising a canard 1 and a pair of arms 2, the canard 1 and the pair of arms 2 being coupled to each other via the aforementioned canard-to-arm connection structure. The canard and arms of the aircraft of the second embodiment of the present application form a detachable structure, facilitating transportation and reducing transportation costs.

[0030] 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 canard-arm connection structure, used for coupling a canard (1) and an arm (2), characterized in that: The canard (1) comprises a coupling plug-in portion (10), wherein the coupling plug-in portion (10) comprises a plurality of fixing portions (11); the machine arm (2) comprises an machine arm plug-in cavity (20), wherein one end of the machine arm plug-in cavity (20) is provided with a plug-in interface (21), and the coupling plug-in portion (10) is configured to be inserted into the machine arm plug-in cavity (20) through the plug-in interface (21), and to be fixed in the machine arm (2) through the fixing portion (11).

2. The canard-to-arm connection structure 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 canard fixing hole (14) that is vertically opened.

3. The canard-to-arm connection structure 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). After the coupling plug-in portion (10) is inserted into the arm plug-in cavity (20), the canard fixing holes (14) are configured to be opposite to the arm fixing holes (23) one by one and connected by bolts.

4. The canard-to-arm connection structure according to claim 1, characterized in that: After the coupling plug-in portion (10) is inserted into the arm plug-in cavity (20), the inner wall of the arm plug-in cavity (20) is configured to fit with the outer wall of the coupling plug-in portion (10).

5. The canard-to-arm connection structure 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 canard-to-arm connection structure 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 canard-to-arm connection structure according to claim 3, characterized in that: An upper box portion (24) is provided on the upper portion of the arm plug-in cavity (20), and the upper box portion (24) is configured such that after the coupling plug-in portion (10) is inserted into the arm plug-in cavity (20), the upper box portion (24) and the arm fixing plate (22) clamp the coupling plug-in portion (10) from top to bottom to form a stable support.

8. The canard-to-arm connection structure according to claim 5, characterized in that: The canard (1) also includes an aileron (3), the aileron (3) includes a first end surface (30), the first end surface (30) is provided with at least one positioning pin (31) and at least two fixing pins (32), the arm (2) includes a second end surface (26), the second end surface (26) is provided with at least three pin holes (17), wherein the positioning pin (31) and the fixing pin (32) have different lengths, and the at least one positioning pin (31) and the at least two fixing pins (32) are configured to be plugged into the at least three pin holes (17) in a one-to-one correspondence, so that the first end surface (30) and the second end surface (26) fit each other.

9. The canard-to-arm connection structure 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 is bolted to the machine arm (2), and the second fixing pin (322) is provided with a second fixing pin hole (b) and is bolted to the machine arm (2), 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 via a canard-arm connection structure according to any one of claims 1 to 9.

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