Aircraft and canard and arm connecting structure thereof

Abstract

The invention 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 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. The canards and the vehicle arms form a detachable structure, transportation is convenient, and the transportation cost is reduced.

Description

Technical Field

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

[0002] At present, the canards and arms of many aircraft are integrally formed structures, which means that the canards and arms need to be transported together as a whole when the aircraft is transported, which is bulky and inconvenient to transport. Summary of the invention

[0003] The purpose of the present application is to provide an aircraft and a canard-arm connection structure thereof. The canard and the arm of the present application form a detachable structure, which is convenient for transportation and reduces transportation costs.

[0004] 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 a plurality of fixing portions; the arm includes an arm plug-in cavity, and one end of the arm plug-in cavity is provided with a plug-in interface, and the coupling plug-in portion is configured to be inserted into the arm plug-in cavity through the plug-in interface and fixed in the arm through the fixing portion.

[0005] 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 connecting structure.

[0006] 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 canard fixing hole opened vertically.

[0007] 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.

[0008] 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 with the outer wall of the coupling plug-in portion.

[0009] 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.

[0010] 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.

[0011] 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.

[0012] 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.

[0013] 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 extension directions of the first fixing pin hole and the second fixing pin hole are perpendicular to each other.

[0014] 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

[0015] Figure 1 It is a schematic structural diagram of the canard-arm connection structure of the first embodiment of the present application;

[0016] Figure 2 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;

[0017] Figure 3 It is a schematic structural diagram of the canard-arm connection structure of the first embodiment of the present application;

[0018] Figure 4 It is a schematic structural diagram of the aileron and the machine arm connection structure of the first embodiment of the present application;

[0019] Figure 5 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;

[0020] Figure 6 Shown is a schematic structural diagram of an aircraft according to a second embodiment of the present application. DETAILED DESCRIPTION

[0021] 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.

[0022] 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.

[0023] 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.

[0024] 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 and arm connection structure of an 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 a plug-in interface 21 is provided at one end of the arm plug-in cavity 20, and the coupling plug-in portion 10 is configured to be inserted into the arm plug-in cavity 20 through the plug-in interface 21, and fixed in the arm 2 by the fixing portion 11.

[0025] 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. Figure 3As shown, the coupling plug-in part 10 includes a pair of supporting beams 12 and fixing holes 13 that are matched and connected to each other. The fixing holes 13 are bolted to the side walls of the supporting beams 12. A plurality of fixing parts (11) are arranged on each fixing hole 13, 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 supporting beam 12, and is only subjected to the shear force in the vertical direction, so it is not easy to loosen. In this embodiment, there are 3 canard fixing holes, and of course, it can also be other numbers. An arm fixing plate 22 is provided at the bottom of the arm plug-in cavity 20, which itself is fixed on the arm. A plurality of arm fixing holes 23 are provided on the arm fixing plate 22, and the number thereof is the same as that of 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 opposite to the arm fixing holes 23 one by one and connected by bolts. Specifically, an upper box portion 24 is provided at the upper part of the arm plug-in cavity 20. 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 form an upper and lower clamping for the coupling plug-in portion 10 to absorb the vibration of the coupling plug-in portion 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 portion 24, and a bolt can be connected in series through the through hole passing through the upper box portion 24 to the canard fixing hole 14 and the arm fixing hole 23, thereby fixing the coupling plug-in portion 10 in the arm plug-in cavity 20. A structural member 25 is also provided at the upper part of the upper box portion 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 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 mutually 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, which are coupled one-to-one with the pair of support beams 12 of the coupling plug-in part 10, so that they are not easily broken by force, 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.

[0026] 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.

[0027] Furthermore, if Figure 4 and Figure 5As 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, the arm 2 includes a second end face 26, the second end face 26 is provided with three pin holes 17, a positioning pin 31 and two fixing pins 32 can be plugged into the three pin holes 17 one by one, so that the first end face 30 and the second end face 26 fit 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, 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 can pass through the fixing plate on the arm and then enter the first fixing pin hole a, so as to realize the bolt connection between 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 insertion direction, and the bolt can be inserted from the upper part of the arm downward, pass through the fixing plate on the arm and enter the second fixing pin hole b, so as to realize the bolt connection between the second fixing pin 322 and the arm 2. Through the bolt connection in two mutually perpendicular directions, the connection between the aileron 3 and the arm 2 can be better guaranteed. 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. It should be noted that 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.

[0028] The second embodiment of the present application also provides an aircraft, such as Figure 6 As shown, it includes canard 1 and a pair of arms 2, which are coupled via the canard and arm connection structure. The canard and arm of the aircraft in the second embodiment of the present application form a detachable structure, which is convenient for transportation and reduces transportation costs.

[0029] 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 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) are in contact with 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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