An aircraft with assembled fixed wings

Abstract

The present application relates to the field of aircraft structures, and specifically to an aircraft with assembled fixed wings, comprising a fixed wing provided with a first connecting portion and a second connecting portion arranged front and back in a first direction; a base provided with a first docking portion and a second docking portion for docking the first connecting portion and the second connecting portion, respectively, so that when the fixed wing moves in the first direction, the first connecting portion and the first docking portion, the second connecting portion and the first docking portion can be docked synchronously; a locking member for fixing the second connecting portion and the second docking portion in the docked state to fix the fixed wing and the base. Through the above scheme, it is finally possible to achieve effective connection of multiple points of the fixed wing on the base by locking the fixed wing in one position, greatly improving the assembly speed and having good connection stability.

Description

Technical Field

[0001] This application relates to the field of aircraft structures, and in particular to an aircraft with assembled fixed wings. Background Technology

[0002] Stable flight of aircraft typically involves large fixed wings or rudders, which are usually securely connected to the aircraft using connectors. However, in transport and high-density storage applications, these fixed wings and rudders occupy significant space, resulting in low space utilization. Some aircraft employ folding mechanisms to fold and unfold the fixed wings and rudders; while these mechanisms offer the advantage of rapid unfolding and folding, they also suffer from drawbacks such as complex structure, significant impact, inability to use large-sized, heavy rudders, and inconsistent connection stiffness due to movement gaps. Other aircraft use direct bolt connections, which offer good connection stiffness, but the numerous connection points lead to long overall operation times. Summary of the Invention

[0003] This application provides an aircraft with an assembled fixed wing to solve the problem of cumbersome connection between the fixed wing and the aircraft in related technologies.

[0004] An aircraft with an assembled fixed wing, comprising:

[0005] A fixed wing, which is provided with a first connecting part and a second connecting part arranged front and rear in a first direction;

[0006] The base is provided with a first docking part and a second docking part that respectively dock with the first connecting part and the second connecting part, so that when the fixed wing moves in the first direction, the first connecting part can dock with the first docking part, the second connecting part and the first docking part simultaneously;

[0007] A locking element is used to securely connect the second connecting part and the second docking part in the docking state, so as to securely connect the fixed wing and the base.

[0008] In some embodiments, the first direction is opposite to the flight direction of the base, and when the fixed wing and the base are docked, the first connecting portion and the second connecting portion are respectively located upstream of the first docking portion and the second docking portion, so as to resist the fixed wing in the first direction through the first docking portion and the second docking portion.

[0009] In some embodiments, the fixed wing is provided with a first mounting groove extending along the first direction, and the first connecting portion is fixedly disposed in the first mounting groove and extends along the first direction;

[0010] A snap-fit ​​groove extending in a first direction is provided on one side of the first docking part. After the first docking part extends into the first mounting groove, it cooperates with the first connecting part and limits its movement in the first direction through the first mounting groove.

[0011] In some embodiments, the first mating portion is inclined relative to one side of the first mounting groove and engages with the inner wall of the first mounting groove in an inclined manner.

[0012] In some embodiments, the first connecting portion is a waist-shaped front toe block, and the first mating portion is perpendicular to the waist-shaped front toe block so that the waist shape and the snap-fit ​​groove are in a cross-shaped snap-fit ​​engagement.

[0013] In some embodiments, the second connecting portion is a through post that is connected at one end to the fixed wing and extends along the first direction;

[0014] The second docking part is a docking block with a through hole. The through post is connected to and fixed with the second docking part by passing through the through hole and a locking member that abuts against the docking block on the other side.

[0015] In some embodiments, the fixed wing has a second mounting groove extending along the first direction, and the through post is fixedly disposed in the second mounting groove; the downstream end of the second mounting groove in the first direction has a first operating hole communicating with the outside.

[0016] In some embodiments, the locking element is a locking sleeve that engages with the threaded part of the through post.

[0017] In some embodiments, an installation cavity is formed within the mating block, the side of the installation cavity away from the base is open, the through hole connects to the installation cavity, and a second operating hole with a diameter smaller than that of the locking sleeve is provided on the side of the installation cavity away from the through hole. The first operating hole, the second operating hole, the through hole, and the through post are coaxially arranged. The end of the locking sleeve is coaxially provided with an operating section with a smaller diameter, and a locking pin with a diameter smaller than that of the second operating hole is threaded into the operating section.

[0018] In some embodiments, the bottom wall of the second mounting groove slides in contact with the locking screw sleeve, or...

[0019] A rotating pad is provided between the bottom wall of the second mounting groove and the locking screw sleeve. The two sides of the rotating pad respectively abut against the bottom wall of the second mounting groove and slide against the circumferential surface of the locking screw sleeve.

[0020] The beneficial effects of the technical solution provided in this application include:

[0021] This application provides an assembly-type fixed-wing aircraft. Since all the connecting structures on the fixed wing dock with the docking structure on the base in the same direction at the same time, and the first connecting part and the second connecting part have a limiting function in other directions besides the first direction, and the second connecting part and the second docking part are fixedly connected by locking members, and are also limited in the first direction, during the installation of the fixed wing, the fixed wing and the base can be quickly docked in the first direction by means of the first connecting part, the second connecting part, the first docking part and the second docking part, and after docking, the two are fixedly connected by locking members. Finally, by locking the fixed wing in one position, multiple points of the fixed wing can be effectively connected on the base, which greatly improves the assembly speed and has good connection stability. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 This is a structural diagram of the fixed wing and base before assembly, provided in an embodiment of this application.

[0024] Figure 2 This is a schematic diagram of the assembled structure of the fixed wing and base provided in an embodiment of this application;

[0025] Figure 3 A partial structural cross-sectional view of the first connecting portion provided for an embodiment of this application;

[0026] Figure 4 A partial structural cross-sectional view of the second connecting portion provided for an embodiment of this application;

[0027] Figure 5 A partial structural cross-sectional view of the second connecting portion provided for an embodiment of this application;

[0028] Figure 6 for Figure 5 Sectional view of the inner AA line.

[0029] In the picture:

[0030] 1. Fixed wing; 10. First connecting part; 100. Waist-shaped front preload block; 101. Waist-shaped body; 102. First pin hole; 11. Second connecting part; 110. Through-post; 1101. Column surface; 12. First mounting groove; 120. Waist-shaped groove; 13. Second mounting groove; 130. First operating hole; 14. Second pin hole; 15. Anti-detachment pin;

[0031] 2. Base; 20. First mating part; 200. Snap-fit ​​groove; 21. Second mating part; 210. Through hole; 22. Mating block; 220. Mounting cavity; 221. Second operating hole; 222. Rotating pad;

[0032] 3. Locking component; 30. Locking nut; 300. Operating section; 301. Locking pin. Detailed Implementation

[0033] To make the purpose, technical solutions, and advantages of the embodiments of this application more clear, the technical solutions in the embodiments of this application will be clearly and completely described below in conjunction with the drawings in the embodiments of this application. Obviously, the described embodiments are part of the embodiments of this application, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0034] This application provides an aircraft with an assembled fixed wing, which solves the problem of cumbersome connection between the fixed wing and the aircraft in related technologies.

[0035] Reference Figure 1 and Figure 2 An aircraft having an assembled fixed-wing 1, comprising:

[0036] Fixed wing 1, which is provided with a first connecting part 10 and a second connecting part 11 arranged front and back in a first direction;

[0037] The base 2 is provided with a first docking part 20 and a second docking part 21 that respectively dock with the first connecting part 10 and the second connecting part 11, so that when the fixed wing 1 moves in the first direction, the first connecting part 10 can dock with the first docking part 20, the second connecting part 11 and the first docking part 20 simultaneously.

[0038] Locking member 3 is used to fix the second connecting part 11 and the second docking part 21 in the docking state to fix the fixed wing 1 and the base 2.

[0039] In this embodiment, the fixed wing 1 and the base 2 are connected by the first connecting part 10 to the first docking part 20, the second connecting part 11 and the second docking part 21. In other embodiments, there may be multiple first connecting parts 10 and multiple first connecting parts 10. It should be noted that by simultaneously docking all the connecting structures on the fixed wing 1 with the docking structures on the base 2, the first connecting part 10 and the second connecting part 11 have a limiting function that allows movement in the first direction. The second connecting part 11 and the second docking part 21 are fixedly connected by the locking member 3, and are also limited in the first direction.

[0040] Therefore, during the installation of the fixed wing 1, the fixed wing 1 and the base 2 can be quickly connected in the first direction by means of the first connecting part 10, the second connecting part 11, the first docking part 20 and the second docking part 21, and after docking, the two are fixedly connected by the locking part 3. Finally, the fixed wing 1 can be effectively connected at multiple points on the base 2 by locking the fixed wing 1 at one position.

[0041] Reference Figure 1 and Figure 2 Optionally, the first direction is opposite to the flight direction of the base 2, and when the fixed wing 1 and the base 2 are docked, the first connecting part 10 and the second connecting part 11 are respectively located upstream of the first docking part 20 and the second docking part 21, so as to block the fixed wing 1 in the first direction through the first docking part 20 and the second docking part 21.

[0042] This configuration ensures that when the aircraft is subjected to the thrust of the airflow during flight, the fixed wing 1 is supported by the first docking part 20 and the second docking part 21 on the base 2 in the first direction, thus achieving a better force guiding effect. At the same time, the force direction of the fixed wing 1 is exactly opposite to its disassembly direction, making it difficult for the fixed wing 1 to move in the disassembly direction during flight, thereby effectively ensuring the connection stability between the fixed wing 1 and the base 2.

[0043] Optionally, the fixed wing 1 is provided with a first mounting groove 12 extending along the first direction, and the first connecting part 10 is fixedly disposed in the first mounting groove 12 and extends along the first direction;

[0044] A snap-fit ​​groove 200 extending in a first direction is provided on one side of the first docking part 20. After the first docking part 20 extends into the first mounting groove 12, it cooperates with the first connecting part 10 and limits its movement in the first direction through the first mounting groove 12.

[0045] The first mounting groove 12 extends longer than the first docking part 20 in the first direction, so that the first docking part 20 can be smoothly inserted and moved in the first direction.

[0046] This configuration allows the fixed wing 1 and the base 2 to have a small or no gap at the docking positions of the first connecting part 10 and the first docking part 20 through the insertion and engagement of the first mounting groove 12 and the first docking part 20. This effectively reduces the airflow resistance generated when the fixed wing 1 is connected to the base 2. At the same time, the first connecting part 10 is located in the first mounting groove 12, which also reduces the planar projected area of ​​the fixed wing 1 and facilitates transportation.

[0047] Optionally, the first mating part 20 is inclined relative to one side of the first mounting groove and engages with the inner wall of the first mounting groove 12 at an angle.

[0048] This design provides convenience for docking the fixed wing 1 and the base 2. When the first docking part 20 is inserted into the first mounting groove 12, staggered insertion can be achieved, which improves the installation and connection speed.

[0049] Reference Figure 3 Optionally, the first connecting part 10 is a waist-shaped front toe block 100, and the first mating part 20 is perpendicular to the waist-shaped front toe block 100 so that the waist-shaped front toe block 100 and the snap-fit ​​groove 200 are in a cross-shaped snap-fit ​​engagement.

[0050] The waist-shaped toe block 100 includes a block body and a waist-shaped body 101 disposed at the end. The snap-fit ​​groove 200 of the first docking part 20 is a correspondingly waist-shaped groove. The inner wall of the first mounting groove 12 is provided with a waist-shaped groove 120 for the waist-shaped toe block 100 to be inserted. At the same time, a first pin hole 102 is provided on the waist-shaped toe block 100. A second pin hole 14 communicating with the waist-shaped groove 120 is provided on the surface of the fixing wing 1 outside the first mounting groove 12. When the waist-shaped toe block 100 is inserted into the waist-shaped groove 120, the first pin hole 102 and the second pin hole 14 are aligned. The waist-shaped toe block 100 and the fixing wing 1 are fixedly connected by an anti-detachment pin 15 passing through the waist-shaped toe block 100 from the outside of the fixing wing 1 via the second pin hole 14 and the first pin hole 102.

[0051] With this configuration, the waist-shaped front toe block 100 engages and abuts against the snap-fit ​​groove 200 in the lateral direction, thereby enabling the first connecting part 10 and the first docking part 20 to dock in the first direction, and limiting the waist-shaped front toe block 100 to move only in the first direction.

[0052] Reference Figure 4 Optionally, the second connecting part 11 is a through post 110 that is connected at one end to the fixed wing 1 and extends along the first direction;

[0053] The second docking part 21 is a docking block 22 with a through hole 210. The through post 110 is docked and fixed with the second docking part 21 by passing through the through hole 210 and connecting to a locking member that abuts against the docking block 22 on the other side.

[0054] One end of the through-post 110 is threaded into a slot on the inner wall of the second mounting groove 13 to achieve fixed installation within the second mounting groove 13. To ensure the accuracy of the through-post 110's length in the first direction during installation, a large-diameter cylindrical surface 1101 is provided in the middle section of the through-post 110. The cylindrical surface 1101 allows for positioning and engagement of the through-post 110 when it is installed in the slot.

[0055] With this configuration, the locking member is fixedly connected to the end of the through-post 110 after passing through the docking block 22 and then abuts against the docking block 22, thereby achieving the connection and position fixation of the second connecting part 11 with the second docking part 21 in the first direction.

[0056] Reference Figure 4 Optionally, the fixed wing 1 is provided with a second mounting groove 13 extending along the first direction, and the through post 110 is fixedly disposed in the second mounting groove 13; the second mounting groove 13 is provided with a first operating hole 130 communicating with the outside at one end downstream of the first direction.

[0057] This configuration allows the second connecting part 11 and the second docking part 21 to be docked inside the fixed wing 1, avoiding additional airflow resistance and reducing the planar projected area of ​​the fixed wing 1.

[0058] Reference Figure 5 Optionally, the locking element is a locking sleeve 30 that is threadedly engaged with the through post 110.

[0059] This configuration allows the locking sleeve 30 to be threaded onto the through post 110, achieving a connection that secures it to the through post 110 and abuts against the mating block 22.

[0060] Reference Figure 5Optionally, an installation cavity 220 is formed in the mating block 22. The side of the installation cavity 220 away from the base 2 is open. The through hole 210 connects to the installation cavity 220. The side of the installation cavity 220 away from the through hole 210 is provided with a second operating hole 221 with a diameter smaller than that of the locking screw sleeve 30. The first operating hole 130, the second operating hole 221, the through hole 210 and the through post 110 are coaxially arranged. The end of the locking screw sleeve 30 is coaxially provided with an operating section 300 with a diameter smaller than that of the second operating hole 221. The operating section 300 is internally threaded with a locking pin 301 with a diameter smaller than that of the second operating hole 221. The locking pin 301 is coaxial with the locking screw sleeve 30 and abuts against the through post 110.

[0061] With this configuration, the locking sleeve 30 rotates within the mounting cavity 220 via the operating section 300 and the second operating hole 221, thereby threadedly connecting to the through post 110. Since the mounting cavity 220 provides a limit for the locking sleeve 30, it cannot disengage from the mounting cavity 220, nor from the threaded through post 110. Therefore, the locking sleeve 30 will not fall off due to fuselage vibration during flight. Simultaneously, to prevent relative vibration between the locking sleeve 30 and the through post 110 due to gaps, a locking pin 301 is screwed into the operating section 300 through the second operating hole 221, pressing the locking pin 301 against the through post 110. This effectively prevents internal vibration gaps between the through post 110 and the locking sleeve 30, resulting in greater stability between them.

[0062] Reference Figure 6 Optionally, the bottom wall of the second mounting groove 13 slides in contact with the locking screw sleeve 30, or...

[0063] A rotating pad 222 is provided between the bottom wall of the second mounting groove 13 and the locking screw sleeve 30. The two sides of the rotating pad 222 abut against the bottom wall of the second mounting groove 13 and slide against the circumferential surface of the locking screw sleeve 30, respectively.

[0064] Among them, the rotating pad 222 is a cover plate with an arc bottom, so that the side away from the base 2 can make flat contact with the bottom wall of the second mounting groove 13, and the arc surface on the other side can slide and contact the circumferential surface of the locking screw sleeve 30.

[0065] With this configuration, a rotating pad 222 is placed on the side of the locking sleeve 30 in the mating block 22 away from the base 2. Using the rotating pad 222, the fixed wing 1, after installation, directly presses the rotating pad 222 onto the mating block 22 without affecting the rotational fit between the rotating pad 222 and the locking sleeve 30. This ultimately further improves the positional stability of the locking sleeve 30.

[0066] In the description of this application, it should be noted that the terms "upper" and "lower" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application. 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, a detachable connection, or an integral 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, or it can be internal communication between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to the specific circumstances.

[0067] It should be noted that, in this application, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, an element defined by the sentence "comprising a ..." does not exclude the presence of other identical elements in the process, method, article or device comprising the element.

[0068] The foregoing is merely a list of specific embodiments of the present application, intended to enable those skilled in the art to understand or implement the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application is not limited to the embodiments shown herein, but is intended to conform to the broadest scope consistent with the principles and novel features of the present application.

Claims

1. An aircraft with detachable fixed wings, characterized in that, It includes: A fixed wing (1) is provided with a first connecting part (10) and a second connecting part (11) arranged front and back in a first direction; The base (2) is provided with a first docking part (20) and a second docking part (21) respectively docking with the first connecting part (10) and the second connecting part (11), so that when the fixed wing (1) moves in the first direction, the first connecting part (10) can dock with the first docking part (20), the second connecting part (11) and the first docking part (20) synchronously; Locking member (3) is used to fix the second connecting part (11) and the second docking part (21) in the docking state to fix the fixed wing (1) and the base (2); The first direction is opposite to the flight direction of the base (2), and when the fixed wing (1) and the base (2) are docked, the first connecting part (10) and the second connecting part (11) are respectively upstream of the first docking part (20) and the second docking part (21), so as to resist the fixed wing (1) in the first direction through the first docking part (20) and the second docking part (21); The fixed wing (1) is provided with a first mounting groove (12) extending along the first direction. The first connecting part (10) is fixedly disposed in the first mounting groove (12) and extends along the first direction. A snap-fit ​​groove (200) extending along the first direction is provided on one side of the first docking part (20). After the first docking part (20) extends into the first mounting groove (12), it cooperates with the first connecting part (10) and limits its movement along the first direction through the first mounting groove (12).

2. The aircraft with a detachable fixed wing (1) according to claim 1, characterized in that, The first mating part (20) is inclined relative to one side of the first mounting groove and is inclined to fit the inner wall of the first mounting groove (12).

3. The aircraft with a detachable fixed wing (1) according to claim 1, characterized in that, The first connecting part (10) is a waist-shaped front toe block (100), and the first mating part (20) is perpendicular to the waist-shaped front toe block (100) so that the waist-shaped front toe block (100) and the snap-fit ​​groove (200) are in a cross-shaped snap-fit ​​engagement.

4. The aircraft with a detachable fixed wing (1) according to claim 1, characterized in that, The second connecting part (11) is a through post (110) that is connected at one end to the fixed wing (1) and extends along the first direction; The second docking part (21) is a docking block (22) with a through hole (210) on it. The through post (110) is connected to the second docking part (21) by passing through the through hole (210) and a locking member that abuts against the docking block (22) on the other side of the docking block (22).

5. The aircraft with a detachable fixed wing (1) according to claim 4, characterized in that, The fixed wing (1) is provided with a second mounting groove (13) extending along the first direction, and the through post (110) is fixedly installed in the second mounting groove (13); the second mounting groove (13) is provided with a first operating hole (130) communicating with the outside at the downstream end of the first direction.

6. The aircraft with a detachable fixed wing (1) according to claim 5, characterized in that, The locking element is a locking sleeve (30) that is threadedly engaged with the through post (110).

7. The aircraft with a detachable fixed wing (1) according to claim 6, characterized in that, An installation cavity (220) is provided in the docking block (22). The side of the installation cavity (220) away from the base (2) is open. The through hole (210) connects to the installation cavity (220). The side of the installation cavity (220) away from the through hole (210) is provided with a second operating hole (221) with a diameter smaller than that of the locking nut (30). The first operating hole (130), the second operating hole (221), the through hole (210) and the through post (110) are coaxially arranged. The end of the locking nut (30) is coaxially provided with an operating section (300) with a diameter smaller than that of the second operating hole (221). The operating section (300) is threaded with a locking pin (301) with a diameter smaller than that of the second operating hole (221). The locking pin (301) is coaxial with the locking nut (30) and abuts against the through post (110).

8. The aircraft with a detachable fixed wing (1) according to claim 7, characterized in that, The bottom wall of the second mounting groove (13) slides in contact with the locking nut (30), or, A rotating pad (222) is provided between the bottom wall of the second mounting groove (13) and the locking screw sleeve (30). The two sides of the rotating pad (222) abut against the bottom wall of the second mounting groove (13) and slide against the circumference of the locking screw sleeve (30).

Images