Wing detachable structure of light sports aircraft

Abstract

The utility model discloses a detachable wing structure of a light sports aircraft, which comprises an aircraft body, a mounting plate, wings and a fixing piece, and slots which are symmetrically arranged are formed in wing tables of the aircraft body; the mounting plate is fixed between the opposite side walls of the two wing tables; a plurality of first through holes are formed in the plate surface of the mounting plate; the middle part of the wing root rib extends outwards and is fixedly provided with a main beam; the main beam is provided with a plurality of second through holes corresponding to the first through holes; the two main beams located on the two sides of the machine body are oppositely inserted into the inserting grooves. And the main beam and the mounting plate are fastened by the fixing piece. The left wing and the right wing on the two sides of the fuselage are of independent structures, the wings and the fuselage are integrated in an opposite insertion mode, on the premise that the structural strength of the aircraft is not lost, the disassembly and assembly portability of the wings is improved, the connecting mode is simple in structure, high in stability and convenient and fast to operate, and the problems that the aircraft wings are not easy to disassemble or cannot be disassembled and assembled, and the aircraft is inconvenient to disassemble and assemble are solved. The transportation cost and the storage cost are too high.

Description

TECHNICAL FIELD

[0001] The utility model relates to light aviation aircraft manufacturing technical field, more specifically relates to a light sport aircraft wing detachable structure. BACKGROUND

[0002] With the rapid development of general aviation industry, the demand of general aviation aircraft, especially light sport aircraft, greatly increases.

[0003] People use light sport aircraft to meet the needs of entertainment sightseeing, flight experience, training of primary pilots, etc., which requires the aircraft to have the characteristics of agility, lightness, safety, etc.

[0004] With the development of science and technology, fixed-wing unmanned aerial vehicles are also developing towards long endurance and large size, thereby bringing the optimization design of large wingspan. With the increase of wingspan, the problem of poor convenience follows. The existing wing technology is generally fixed on the fuselage and cannot be detached. This leads to the problems of large wingspan of general light sport aircraft, inconvenient transportation and high transportation cost.

[0005] Therefore, how to provide a wing detachable aircraft with simple connection method, strong stability and convenient operation is a technical problem that technicians in the field need to solve. CONTENT OF THE UTILITY MODEL

[0006] Therefore, the utility model provides a light sport aircraft wing detachable structure, which solves the problem of high transportation cost and storage cost caused by the difficulty or impossibility of disassembling and assembling the aircraft wing.

[0007] In order to achieve the above purpose, the utility model adopts the following technical scheme:

[0008] A light sport aircraft wing detachable structure comprises:

[0009] A fuselage is provided with two wing platforms symmetrically fixed on the top surface, and the length direction of the wing platform is parallel to the length direction of the fuselage. Two wing platforms are provided with insertion slots.

[0010] An installation plate is fixed between the opposite side walls of the two wing platforms, and the end thereof is fixed perpendicularly to the side wall of the wing platform. The plate surface of the installation plate is arranged perpendicularly to the top surface of the fuselage and located on the same horizontal plane as the slot wall surface of the insertion slot, and a plurality of first through holes are formed in the plate surface of the installation plate.

[0011] A wing is provided with a main beam fixed outwardly in the middle of the wing rib, and a plurality of second through holes corresponding to the first through holes are formed in the main beam. Two main beams located on both sides of the fuselage are inserted into the insertion slot in opposite directions.

[0012] A fixing member is sequentially inserted through the first and second through holes to fasten the two main beams and the mounting plate.

[0013] The beneficial effects of the above technical solution are that the left and right wings on both sides of the fuselage are independent structures, the main beams of the wings are inserted in an opposite direction, and the main beams and the mounting plate are fixed by the fixing member, so that the wings and the fuselage become a whole, and the portability of the wings is improved without losing the structural strength of the aircraft.

[0014] Preferably, the fixing member comprises a beam pin, a nut and a split pin, one end of the beam pin is sequentially inserted through the second through hole and the first through hole of the two main beams and extends outward along the plate surface of the mounting plate to form an extension end, the extension end is provided with a beam pin safety hole, the nut is threadedly connected with the extension end to fasten the beam pin, the main beams and the mounting plate, and the split pin is inserted into the beam pin safety hole. The beam pin and the nut fasten the main beams of the two wings and the mounting plate, and the split pin is inserted into the beam pin safety hole for safety, and a special tool is used to split the split pin at the opening end to form a Y-shaped structure, thereby further improving the mounting effect of the wings. When the nut is loose, the split pin can prevent the nut from being displaced to cause a gap between the mounting plate and the main beams and small-range shaking, thereby affecting the flight safety of the aircraft.

[0015] Preferably, a gasket is arranged between the nut and the plate surface of the mounting plate. The gasket can prevent the mounting plate from being pressed to affect the service life of the mounting plate due to excessive fastening of the nut.

[0016] Preferably, two wing pins are detachably connected to the root ribs of the wings, the two wing pins are located at two ends of the root ribs, side walls of the wing platforms are fixed with insertion members corresponding to the wing pins, and the insertion members and the wing pins are inserted and fastened with each other. The wing pins are inserted into the insertion members on the wing platforms to increase the stability of the connection between the wings and the fuselage and prevent the wings from being disconnected from the fuselage.

[0017] Preferably, an insertion pin safety hole is arranged at an end of the wing pin away from the wing, the insertion member comprises a bearing seat, a bearing, a hole clamping spring and a safety pin, the bearing seat is adhesively fixed on the side wall of the wing platform, the bearing is fixed on the wing platform through the bearing seat, the wing pin is inserted into the bearing, and an end of the wing pin is exposed on a side of the wing platform away from the wing, the hole clamping spring is embedded between the outer ring of the bearing and the inner wall of the bearing seat, and the safety pin is inserted into the insertion pin safety hole. An installation hole is arranged on the wing platform, the bearing is embedded in the installation hole and fixed through the bearing seat, the wing pin is inserted into the bearing, the hole clamping spring limits the axial rotation of the bearing, and the safety pin fixes the wing pin and the wing platform; the insertion mode of the wing pin and the bearing is more convenient and fast.

[0018] Preferably, a flange plate is fixed on the wing bolt, the flange plate is closely attached to the root rib of the wing, and the end face of the flange plate is closely attached to the end face of the bearing seat.

[0019] Preferably, the wing bolt is bolted on the root rib of the wing.

[0020] Preferably, the length of the main beam is the same as the length of the mounting plate.

[0021] Preferably, the wing is made of carbon fiber material, and the outer periphery is covered with a skin.

[0022] Compared with the prior art, the detachable structure of the wing of the light sport aircraft has the advantages of simple connection mode, strong stability, convenient operation, and solves the problem that the aircraft wing is not easy or cannot be disassembled, resulting in high transportation and storage costs. BRIEF DESCRIPTION OF DRAWINGS

[0023] In order to more clearly illustrate the technical scheme in the embodiments of the present application or the prior art, the drawings needed in the following embodiment or prior art description will be briefly introduced. Obviously, the drawings in the following description are only embodiments of the present application, and for those skilled in the art, other drawings can be obtained without creative labor on the basis of the provided drawings.

[0024] Figure 1 The wing assembly structure schematic diagram provided by the present application;

[0025] Figure 2 The wing assembly schematic diagram provided by the present application;

[0026] Figure 3 The Figure 2 The A part of the enlarged schematic diagram;

[0027] Figure 4 The Figure 2 The B part of the enlarged schematic diagram.

[0028] Among them,

[0029] 1 - fuselage; 11 - wing stand; 2 - slot; 3 - mounting plate; 31 - first through hole;

[0030] 4 - wing; 41 - wing bolt; 42 - main beam; 43 - second through hole; 44 - flange plate;

[0031] 5 - plug-in part; 51 - bearing seat; 52 - bearing; 53 - safety pin; 54 - hole with clasp spring;

[0032] 6 - fixing; 61 - beam pin; 62 - washer; 63 - nut; 64 - cotter pin. DETAILED DESCRIPTION

[0033] The technical solutions in the embodiments of the utility model will be apparently and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all the other embodiments obtained by the ordinary skilled in the art without creative labor belong to the scope of protection of the utility model.

[0034] In the description of the embodiments of the utility model, it should be explained that the orientation or position relation indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like is the orientation or position relation shown in the drawings or the orientation or position relation usually placed when the product is used, which is only for the convenience of describing the utility model and simplifying the description, and cannot be understood as indicating or implying that the indicated device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the utility model. In addition, the terms "first", "second" and the like are only used for differentiation in description, and cannot be understood as indicating or implying relative importance.

[0035] Referring to the drawings, Figures 1-4 The utility model embodiment discloses a kind of detachable structure of light sport aircraft wing, wing and fuselage are connected by the way of insertion and bolted, wing can be dragged using ordinary car, convenient transportation, suitable for M2 amphibious aircraft, comprising:

[0036] Fuselage 1, two wing platforms 11 are fixed symmetrically on the top surface of fuselage 1, and the length direction of wing platform 11 is parallel to the length direction of fuselage 1;Two wing platforms 11 are provided with insertion slot 2;Two insertion slots 2 located on both sides of fuselage 1 are symmetrically arranged;

[0037] Mounting plate 3, mounting plate 3 is fixed between the opposite side walls of two wing platforms 11, and the end portion is vertically fixed with the side wall of wing platform 11;The plate surface of mounting plate 3 is arranged perpendicular to the top surface of fuselage 1 and located on the same horizontal plane with the slot wall surface of insertion slot 2, and a plurality of first through holes 31 are formed on the plate surface of mounting plate 3;

[0038] Wing 4, the main beam 42 is fixed with the outer extension in the middle of the rib of wing 4, and the second through hole 43 corresponding to the plurality of first through holes 31 is formed on the main beam 42;Two main beams 42 located on both sides of fuselage 1 are inserted into insertion slot 2 in opposition;

[0039] Fixing piece 6, fixing piece 6 is sequentially penetrated through first through hole 31 and second through hole 43 to fasten two main beams 42 with mounting plate 3.

[0040] In the embodiment, the fixing member 6 comprises a beam pin 61, a nut 63 and a split pin 64. One end of the beam pin 61 is sequentially inserted through the second through hole 43 and the first through hole 31 on the two main beams 42 and extends outward along the plate surface of the mounting plate 3 to form an extended end, and the extended end is provided with a beam pin safety hole.

[0041] The nut 63 is provided between the plate surface of the mounting plate 3 and the plate surface.

[0042] Referring to the accompanying drawings Figure 2 And 4 The wing platform is an installation auxiliary device of the wing, and the wing platform is provided with a slot. The mounting plate is arranged vertically between the two wing platforms. An open space formed between the top surface of the fuselage, the mounting plate and the slot on the wing platform can be used as a beam box. The two main beams of the wings on the left and right sides are inserted into the beam box in opposite directions. The main beams of the wings on the left and right sides are arranged in a staggered manner and the opposite surfaces of the two main beams are attached to each other. The beam pin is inserted through the second through hole and the first through hole, and the beam pin is fastened by the nut to complete the fixing of the main beam and the mounting plate of the fuselage.

[0043] For safety, the split pin is inserted into the beam box safety hole at the end of the beam box. The split pin can block the nut. When the nut is loosened accidentally, the split pin can block the nut to prevent it from falling and affecting the installation effect of the wing. The split pin is split into a Y shape by the pliers to the two sides, which can prevent the split pin from falling off.

[0044] In this way, the assembly of the wing is completed. The installation is simple, fast, and can be completed by one person in about 15 minutes without affecting the overall structural strength of the aircraft.

[0045] In order to further optimize the above technical solution, two wing pins 41 are detachably connected to the root rib of the wing 4, and the two wing pins 41 are located at the two ends of the root rib. The side wall of the wing platform 11 is fixed with a plug-in member 5 corresponding to the wing pin 41, and the plug-in member 5 and the wing pin 41 are inserted and fastened with each other.

[0046] In the embodiment, the end of the wing pin 41 away from the wing 4 is provided with a pin safety hole, and the plug-in member 5 comprises a bearing seat 51, a bearing 52, a hole clamping spring 54 and a safety pin 53. The bearing seat 51 is adhesively fixed on the side wall of the wing platform 11, the bearing 52 is fixed on the wing platform 11 through the bearing seat 51, the wing pin 41 is inserted into the bearing 52, and the end of the wing pin 41 is exposed on the side of the wing platform 11 away from the wing 4. The hole clamping spring 54 is embedded between the outer ring of the bearing 52 and the inner wall of the bearing seat 51, and the safety pin 53 is inserted into the pin safety hole.

[0047] Referring to the accompanying drawingsFigure 2 And 3 In order to increase the stability of the connection between the fuselage and the wing, the utility model discloses a anti-disengagement design, the wing bolt is arranged at the wing root rib, the bearing is fixed on the wing platform, and the bolt is inserted into the bearing and is fixed by the safety pin, so that the connection is simple and reliable.

[0048] Compared with the wing inserted into the fuselage on the left and right sides, four connecting points are increased, the locking or unlocking is carried out by inserting or pulling out the safety pin, the insertion between the wing bolt and the bearing is convenient and fast, the axial rotation of the bearing is limited by the clamping spring, the method is simple and reliable, and the connecting performance between the wing and the fuselage is further improved.

[0049] In order to further optimize the above technical scheme, the flange plate 44 is fixed on the wing bolt 41, the flange plate 44 is closely attached to the root rib of the wing 4, and the end face of the flange plate 44 is closely attached to the end face of the bearing seat 51.

[0050] The wing bolt 41 is bolted on the root rib of the wing 4.

[0051] The wing bolt and the wing are connected by the bolted mode, the disassembly is convenient, and whether the wing bolt is arranged can be considered according to the actual use condition; the end face of the flange plate and the bearing seat is closely attached, and the effectiveness of the insertion of the wing bolt is guaranteed.

[0052] In order to further optimize the above technical scheme, the length of the main beam 42 is the same as the length of the mounting plate 3.

[0053] In order to further optimize the above technical scheme, the wing 4 is made of carbon fiber material, and the outer periphery is covered with a skin. The wing made of carbon fiber material is light and thin, and the weight is relatively light, the whole machine support is randomly provided, the wing can be placed on the support, the overall width is consistent with a cross-country vehicle, and the wing can be directly towed by a common automobile, so that the transportation is convenient.

[0054] The embodiments in the specification are described in a progressive manner, and each embodiment mainly explains the difference from other embodiments, and the same or similar parts of each embodiment can be referred to each other. For the device disclosed by the embodiments, since it corresponds to the method disclosed by the embodiments, the description is relatively simple, and the related parts can be referred to the method part.

[0055] The above description of the disclosed embodiments enables a person skilled in the art to implement or use the utility model. Various modifications of the embodiments will be apparent to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the utility model. Therefore, the utility model will not be limited to the embodiments shown herein, but will conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A detachable structure of a wing of a light sport aircraft, characterized by, The utility model provides a kind of wing mounting structure of aircraft, including: Machine body (1), two wing platforms (11) are fixed symmetrically on the top surface of machine body (1), the length direction of wing platform (11) is parallel with the length direction of machine body (1);Slot (2) is opened in two wing platforms (11); Mounting plate (3) is fixed between the opposite side walls of two wing platforms (11), and the end thereof is fixed perpendicularly to the side wall of wing platform (11);The plate surface of mounting plate (3) is arranged perpendicularly to the top surface of machine body (1) and is located on the same horizontal plane with the slot wall surface of slot (2), and a plurality of first through holes (31) are opened on the plate surface of mounting plate (3); Wing (4), the main girder (42) is fixed by the outward extension of the middle part of root rib, the second through hole (43) corresponding to a plurality of first through holes (31) is opened on the main girder (42);Two main girders (42) located on both sides of machine body (1) are inserted into slot (2) in opposition; Fixing member (6) is sequentially penetrated through first through hole (31) and second through hole (43) to fasten two main girders (42) with mounting plate (3).

2. A detachable wing structure for a light sports aircraft as claimed in claim 1, wherein, The fixing member (6) includes beam pin (61), nut (63) and split pin (64), one end of beam pin (61) is sequentially penetrated through second through hole (43) and first through hole (31) on two main girders (42) and extends outward along the plate surface of mounting plate (3) to form extension end, and beam pin safety hole is opened in the extension end;Nut (63) is threadedly connected with the extension end to fasten beam pin (61) with main girder (42) and mounting plate (3);Split pin (64) is inserted into beam pin safety hole.

3. A detachable wing structure for a light sport aircraft as defined in claim 2, wherein A gasket (62) is arranged between nut (63) and the plate surface of mounting plate (3).

4. The detachable wing structure of a light sports aircraft according to claim 1, wherein Two wing insertion pins (41) are also detachably connected on the root rib of wing (4), and two wing insertion pins (41) are located at both ends of root rib;Inserting member (5) is fixed on the side wall of wing platform (11) corresponding to wing insertion pin (41), and inserting member (5) and wing insertion pin (41) are inserted and fastened with each other.

5. A detachable wing structure for a light sport aircraft as defined in claim 4, wherein Wing insertion pin (41) is provided with insertion pin safety hole at one end away from wing (4), and inserting member (5) includes bearing seat (51), bearing (52), hole clasp (54) and safety pin (53), bearing seat (51) is adhesively fixed on the side wall of wing platform (11), bearing (52) is fixed on wing platform (11) through bearing seat (51), wing insertion pin (41) is inserted into bearing (52), and the end of wing insertion pin (41) is exposed on the side of wing platform (11) away from wing (4), hole clasp (54) is embedded between the outer ring of bearing (52) and the inner wall of bearing seat (51), and safety pin (53) is inserted into insertion pin safety hole.

6. A detachable wing structure for a light sport aircraft as defined in claim 5, wherein A flange (44) is fixed on the wing bolt (41), and the flange (44) is tightly fitted with the root rib of the wing (4), and the end face of the flange (44) is tightly fitted with the end face of the bearing seat (51).

7. A detachable wing structure for a light sport aircraft as defined in claim 4, wherein The wing bolt (41) is bolted on the root rib of the wing (4).

8. A detachable wing structure for a light sport aircraft as defined in claim 1, wherein The length of the main beam (42) is the same as the length of the mounting plate (3).

9. The detachable wing structure of a light sport aircraft according to claim 1, wherein, The wing (4) is made of carbon fiber material, and the outer periphery is covered with a skin.

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