A fuselage support device adaptable to various types of aircraft

Abstract

The application provides a fuselage supporting device capable of adapting to various types of aircrafts, which comprises a front main supporting mechanism, a rear main supporting mechanism and a rear auxiliary supporting mechanism, the front main supporting mechanism, the rear main supporting mechanism and the rear auxiliary supporting mechanism each comprise two supporting frames, the two supporting frames of the front main supporting mechanism are connected through a first connecting rod, the front main supporting mechanism and the rear main supporting mechanism are connected through two second connecting rods, the rear main supporting mechanism is connected with the rear auxiliary supporting mechanism through two third connecting rods, and the two supporting frames of the rear auxiliary supporting mechanism are connected through a fourth connecting rod, and the lengths of the first connecting rod and the second connecting rod are adjustable.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of aircraft supporting device, and particularly relates to a fuselage supporting device capable of supporting multiple types of aircraft. BACKGROUND

[0002] At present, medium and large manned and unmanned aircrafts are sometimes transferred from one airport to another by land, and sometimes need to be transferred from the airport to a specific condition for task execution, at which time a vehicle is needed to transport the aircraft. The transport vehicle generally adopts the form of holding the front and rear wheels of the aircraft to fix the aircraft, but does not support the fuselage, and the vibration and impact caused by long time and poor road conditions are easy to cause fatigue damage to the fuselage. SUMMARY

[0003] To solve the above problems, the present application provides a fuselage supporting device capable of supporting and protecting the aircraft fuselage and capable of supporting different sizes of aircraft.

[0004] The above technical purpose of the present application is achieved by the following technical scheme: a fuselage supporting device capable of supporting multiple types of aircraft, comprising a front main supporting mechanism, a rear main supporting mechanism and a rear auxiliary supporting mechanism, the front main supporting mechanism, the rear main supporting mechanism and the rear auxiliary supporting mechanism each comprising two supporting frames, the two supporting frames of the front main supporting mechanism being connected by a first connecting rod, the front main supporting mechanism and the rear main supporting mechanism being connected by two second connecting rods, the rear main supporting mechanism being connected with the rear auxiliary supporting mechanism by two third connecting rods, the two supporting frames of the rear auxiliary supporting mechanism being connected by a fourth connecting rod, the lengths of the first connecting rod and the second connecting rod being adjustable.

[0005] The front main supporting mechanism of the fuselage is used to support the position of the keel load-bearing part of the front part of the aircraft fuselage, the rear main supporting mechanism of the fuselage is used to support the position of the keel load-bearing part of the rear part of the aircraft fuselage, and the rear auxiliary supporting mechanism is used to support the position of the keel of the rear part of the aircraft fuselage. The front main supporting mechanism, the rear main supporting mechanism and the rear auxiliary supporting mechanism support the different parts of the fuselage, the weight of the fuselage is dispersed to the multiple supporting frames of the supporting mechanism, and the damage to the fuselage caused by excessive force on the local position of the aircraft during transportation is avoided; the length of the first connecting rod can be adjusted to make the present supporting device applicable to aircrafts of different widths, the length of the third connecting rod can be adjusted to make the present supporting device applicable to aircrafts of different lengths, and the present supporting device can support and fix aircrafts of different sizes through the adjustment of the first connecting rod and the third connecting rod.

[0006] As a preferred scheme of the present application, the supporting frame of the front main supporting mechanism comprises a supporting seat and an adjusting block provided at the top end of the supporting seat, the adjusting block comprises a block seat, a block provided on the block seat and a lead screw, a groove is formed at the top of the block seat, the block is installed in the groove and can slide in the groove, and the block is connected with the lead screw.

[0007] By rotating the handwheel screw and cooperating with the slide rail and rail groove, the handwheel screw can drive the support block to slide on the support block seat so that the support block is close to the machine body.

[0008] As a preferred embodiment of the present invention, the support base includes a base and a first adjusting screw sleeve. The upper part of the base is a threaded screw rod. The first adjusting screw sleeve has an internal thread corresponding to the screw rod and is sleeved on the screw rod. A locking nut is provided at the bottom of the first adjusting screw sleeve. The adjusting block is provided at the top of the first adjusting screw sleeve.

[0009] The height of the support frame can be adjusted by using screws and adjusting sleeves to support different types of aircraft and adapt to different installation environments; the locking nut is used to lock the adjusting sleeve in place to prevent loosening and make the support more stable.

[0010] As a preferred embodiment of the present invention, the adjusting screw sleeve is provided with a handle.

[0011] The handle makes it easy to rotate the adjusting nut.

[0012] In a preferred embodiment of the present invention, the bottom of the support block is provided with a groove to accommodate the top end of the first adjusting screw sleeve. The support block is fixed to the top end of the first adjusting screw sleeve by positioning pins. There are two positioning pins, respectively located on both sides of the top end of the first adjusting screw sleeve, and both ends of the positioning pins are fixed to the support block. With this structure, the adjusting block can rotate 360° at the top of the support base to adapt to different machine body shapes.

[0013] As a preferred embodiment of the present invention, the top end of the first adjusting screw sleeve is an "I" shaped structure, the positioning pin passes through the concave part of the "I" shaped structure, and the top surface of the "I" shaped structure is convex and spherical.

[0014] By making the top of the first adjusting screw sleeve into an "I" shape, and having the locating pin pass through the groove of the "I" shape, and the top surface of the "I" shape protruding into a spherical shape, the adjusting block can be appropriately tilted left and right at the top of the first adjusting screw sleeve. When tilting left and right, the wear on the "I" shape is small, extending its service life. When applied to support the fuselage of different aircraft models, the adjusting block can fit the fuselage and protect it. Moreover, in bumpy road conditions, the aircraft fuselage will inevitably shake. The 360° rotation and appropriate left and right tilt of the adjusting block can prevent damage to the fuselage when it shakes.

[0015] As a preferred embodiment of the present invention, the support frame of the rear main support mechanism has the same structure as the support frame of the front main support mechanism.

[0016] As a preferred scheme of the present application, the third connecting rod is rotatably connected with the support frame of the rear main support mechanism, and the included angle between the third connecting rod and the support frame of the rear main support mechanism is less than 90 degrees. When the front main support mechanism and the rear main support mechanism are fixed on the mounting surface, the rear auxiliary support mechanism is suspended. The rear auxiliary support mechanism adopts a triangular support structure and is fixed on the support frame of the rear main support mechanism. The suspension of the rear auxiliary support mechanism makes the rear auxiliary support mechanism fit the rear part of the fuselage, and the rotatable connection between the third connecting rod and the support frame of the rear main support mechanism enables the rear auxiliary support mechanism to swing left and right appropriately, thereby avoiding damage to the fuselage caused by vibration during long-time and poor road vehicle transportation.

[0017] The rear part of the fuselage is upwarping compared with the front part of the fuselage. The suspension of the rear auxiliary support mechanism makes the rear auxiliary support mechanism fit the rear part of the fuselage. The rotatable connection between the third connecting rod and the support frame of the rear main support mechanism enables the rear auxiliary support mechanism to swing left and right appropriately, thereby avoiding damage to the fuselage caused by vibration during long-time and poor road vehicle transportation.

[0018] As a preferred scheme of the present application, the second connecting rod comprises a connecting rod and a connecting rod adjusting mechanism, and the connecting rod adjusting mechanism is used for adjusting the length of the second connecting rod.

[0019] As a preferred scheme of the present application, the second connecting rod comprises two connecting rods with external threads at one end. The thread directions of the two connecting rods are opposite. The threaded ends of the two connecting rods are connected through a second adjusting sleeve. The two ends of the second adjusting sleeve are respectively provided with positive and reverse internal threads. The two ends of the second adjusting sleeve are fixed through locking nuts. The other ends of the two connecting rods are respectively fixed on the support frames of the front main support mechanism and the rear main support mechanism.

[0020] The distance between the front main support mechanism and the rear main support mechanism can be quickly adjusted by rotating the adjusting sleeve. After the distance is adjusted to an appropriate distance, the adjusting sleeve is locked through the locking nuts.

[0021] As a preferred scheme of the present application, the first connecting rod has the same structure as the second connecting rod.

[0022] Adjusting the length of the first connecting rod can adjust the distance between the two support frames of the front main support mechanism, so as to adapt to the support of different types of aircraft.

[0023] 1. The front main support mechanism of the fuselage support device provided by the present application is used for supporting the position of the keel load-bearing part of the front part of the aircraft fuselage. The rear main support mechanism is used for supporting the position of the keel load-bearing part of the rear part of the aircraft fuselage. The rear auxiliary support mechanism is used for supporting the position of the keel of the rear part of the aircraft fuselage. Different parts of the fuselage are supported and loaded by the front main support mechanism, the rear main support mechanism and the movable rear auxiliary support mechanism. The weight of the fuselage is dispersed to the multiple support frames of the support mechanism, thereby avoiding damage to the fuselage caused by excessive force on the local position of the aircraft during transportation.

[0024] 2. The present application can be applied to support different models and sizes of aircraft fuselages by adjusting the height of the support frame and the length of the first and second connecting rods.

[0025] 3. The adjustment block of the support frame of the present application can not only rotate 360° at the top of the support base, but also appropriately tilt left and right, so that it can closely fit the fuselage when supporting different models of aircraft fuselages, thereby protecting the fuselage. In addition, when the aircraft fuselage shakes in a bumpy road condition, the 360° rotation and appropriate left and right tilt of the adjustment block can avoid the problem of fatigue damage to the aircraft fuselage caused by long-term and harsh road transportation vibrations and impacts. BRIEF DESCRIPTION OF DRAWINGS

[0026] Figure 1 is a front view schematic diagram of the support device of the specific embodiment of the present application supporting the aircraft state (i.e. the use state);

[0027] Figure 2 is a top view schematic diagram of the support device of the specific embodiment of the present application supporting the aircraft state (i.e. the use state);

[0028] Figure 3 is a front view schematic diagram of the fuselage support device of the specific embodiment of the present application;

[0029] Figure 4 is a top view schematic diagram of the fuselage support device of the specific embodiment of the present application;

[0030] Figure 5 is a schematic diagram of the front main support mechanism of the specific embodiment of the present application;

[0031] Figure 6 is a schematic diagram of the left rear main support frame of the specific embodiment of the present application;

[0032] Figure 7 is a sectional structure schematic diagram of the left rear main support frame of the specific embodiment of the present application;

[0033] Figure 8 is a structure schematic diagram of the rear main support mechanism and the third connecting rod of the specific embodiment of the present application;

[0034] Figure 9 is a sectional structure schematic diagram of the left rear auxiliary support frame of the specific embodiment of the present application;

[0035] Wherein: 1-Front main support mechanism, 11-Right front main support frame, 12-Left front main support frame, 13-First connecting rod, 2-Rear main support mechanism, 21-Right rear main support frame, 22-Left rear main support frame, 23-Second connecting rod, 231-Second adjusting sleeve, 232-Second locking nut, 234-Connecting rod, 3-Rear auxiliary support mechanism, 31-Right rear auxiliary support frame, 32-Left rear auxiliary support frame, 33-Fourth connecting rod, 331-Threaded rod, 332-Sleeve, 4-Third connecting rod, 41-A-shaped structure, 5-Support seat, 51-Base, 52-First adjusting sleeve, 53-First locking nut, 54-Handle, 55-Fixing plate, 6-Adjusting block, 61-Block, 62-Screw rod, 63-Block seat, 7-Positioning pin, 8-"I" shaped structure. Implementation

[0036] The present invention will be further described below with reference to specific embodiments. It should be noted that when an element is referred to as being "fixed to" another element, it can be directly on the other element or there may be an intervening element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementations. Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein in the specification of the invention is for the purpose of describing particular embodiments only and is not intended to limit the invention. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0037] like Figures 1-3 As shown, the fuselage support device provided in this specific embodiment includes a front main support mechanism 1, a rear main support mechanism 2, and a rear auxiliary support mechanism 3.

[0038] like Figure 4As shown in the figure, the front main supporting mechanism 1 comprises a right front main supporting frame 11 and a left front main supporting frame 12, which are oppositely arranged and connected by a first connecting rod 13. The rear main supporting mechanism 2 comprises a right rear main supporting frame 21 and a left rear main supporting frame 22, which are also oppositely arranged. The rear auxiliary supporting mechanism 3 comprises a right rear auxiliary supporting frame 31 and a left rear auxiliary supporting frame 32, which are also oppositely arranged and connected by a fourth connecting rod 33. The right rear main supporting frame 21 is connected with the right front main supporting frame 11 by a second connecting rod 23 and connected with the right rear auxiliary supporting frame 31 by a third connecting rod 4. The left rear main supporting frame 22 is connected with the left front main supporting frame 12 by another second connecting rod and connected with the left rear auxiliary supporting frame 32 by another third connecting rod 4. The six supporting frames form an enclosed area through the six connecting rods.

[0039] In order to facilitate the passage of the aircraft, the present application does not provide a connecting rod between the right rear main supporting frame 21 and the left rear main supporting frame 22. In use, the fourth connecting rod 33 is opened, the aircraft enters the enclosed area formed by the supporting mechanism, and then the fourth connecting rod 33 is fixed. The two supporting frames of the front main supporting mechanism 1 are supported at the position of the keel load-bearing of the front part of the aircraft fuselage, the two supporting frames of the rear main supporting mechanism 2 are supported at the position of the keel load-bearing of the rear part of the aircraft fuselage, and the two supporting frames of the rear auxiliary supporting mechanism 3 are supported at the position of the keel of the rear part of the aircraft fuselage. The front main supporting mechanism 1, the rear main supporting mechanism 2 and the rear auxiliary supporting mechanism 3 support the different parts of the fuselage, and the weight of the fuselage is dispersed to the multiple supporting frames of the three supporting mechanisms, so as to avoid that the local position of the aircraft is subjected to excessive force during transportation and causes damage to the fuselage.

[0040] In the embodiment, the structures of the supporting frames of the front main supporting mechanism 1 and the rear main supporting mechanism 2 are the same, and the specific structure of the left rear main supporting frame 22 is described as an example.

[0041] As shown in the figure, Figure 5 As shown in the figure, the left rear main supporting frame 22 comprises a supporting seat 5 and an adjusting block 6, and the adjusting block 6 is arranged at the top end of the supporting seat 5.

[0042] The support base 5 includes a base 51 and a first adjusting sleeve 52, with an adjusting block 6 located at the top of the first adjusting sleeve 52. The upper part of the base 51 is a threaded rod, and the first adjusting sleeve 52 has an internal thread corresponding to the threaded rod. The first adjusting sleeve 52 is fitted onto the upper threaded rod of the base 51. A locking nut 53 is provided at the bottom of the first adjusting sleeve 52, and a handle 54 is also provided on the first adjusting sleeve 52 for easy rotation. In this embodiment, the threads of both the screw and the first adjusting sleeve 52 are trapezoidal threads with a self-locking function to improve the connection's firmness. In this embodiment, a fixing plate 55 is welded to the bottom of the base 51. During use, the fixing plate is fixed to the mounting platform, thereby securing the support device. Screw holes can be drilled in the fixing plate 55, and corresponding screw holes can be pre-drilled on the mounting platform. Screws can be used to fix the fixing plate to the mounting platform for easy installation and disassembly.

[0043] The adjusting block 6 includes a block 61, a lead screw 62, and a block seat 63. The adjusting block 6 is mounted on the first adjusting screw sleeve 52 via the block seat 63. The top of the block seat 63 has a groove, and the block 61 is installed in the groove and can move within the groove. The block 61 is connected to the lead screw 62. By turning the handwheel, the lead screw drives the block 61 to move left and right on the block seat 63 for fine adjustment.

[0044] In use, the first adjusting sleeve 52 is adjusted to an appropriate height by rotating the handle 54, and then the locking nut 53 is tightened to adjust the height of the left front main support frame 12. After the aircraft is placed on the support device of the present invention, if the support block 61 is not in contact with the fuselage, the support block 61 is finely adjusted by rotating the handwheel on the lead screw 62 to make the support block 61 in contact with the fuselage.

[0045] The installation method of the adjusting block 6 on the first adjusting screw sleeve 52 is shown in Figure 6. The top of the first adjusting screw sleeve 52 is an "I"-shaped structure 8, and the top surface of the "I"-shaped structure 8 is convex and spherical. The bottom of the block seat 63 has a groove to accommodate the top of the first adjusting screw sleeve 52. In this embodiment, the bottom of the block seat 63 is a hollow structure, and two positioning pins 7 pass through the two sides of the groove of the "I"-shaped structure, with both ends of the positioning pins 7 fixed on the block seat 63. The two positioning pins 7 are not tightly attached to the "I"-shaped structure, leaving a small gap between them, so that the adjusting block can be flexibly and appropriately tilted left and right on the top of the support seat, and the wear on the "I"-shaped structure and positioning pins is small.

[0046] In this specific embodiment, the lengths of both the first connecting rod 13 and the second connecting rod 23 are adjusted by adjusting the screw sleeves. The second connecting rod 23 will be used as an example for further explanation. Figure 4As shown, the second connecting rod 23 comprises two connecting rods 234 with external threads at one end, the threads of the two connecting rods 234 are opposite, the threaded ends of the two connecting rods 234 are connected through a second adjusting sleeve 231, the two ends of the second adjusting sleeve 231 are respectively provided with positive and reverse internal threads matched with the two connecting rods 234, and the two ends of the second adjusting sleeve 231 are locked and fixed through two second locking nuts 232. The other ends of the two connecting rods 234 are respectively fixed on the right front main supporting frame 11 and the right rear main supporting frame 21. Of course, other length adjusting mechanisms in the prior art can also be used to adjust the length of the connecting rod.

[0047] In the embodiment, the third connecting rod and the fourth connecting rod are not adjustable in length. Of course, the third connecting rod and the fourth connecting rod can also be provided in a structure adjustable in length according to needs.

[0048] As shown in the figure, Figure 8 The third connecting rod 4 comprises an A-shaped structure composed of a circular tube, and the top end of the A-shaped structure is fixed on the rear auxiliary supporting mechanism 3. The other two ends of the A-shaped structure are rotatably sleeved on the non-threaded area of the base 51 and the first adjusting sleeve 52 through a circular sleeve. Adjusting the height of the first adjusting sleeve 52 can simultaneously adjust the height of the third connecting rod 4. The included angle b between the third connecting rod 4 and the base 51 is less than 90 degrees, so that the rear auxiliary supporting mechanism 3 is suspended, and more space positions are left for the installation of the aircraft task load.

[0049] In the embodiment, the two supporting frames of the rear auxiliary supporting mechanism 3 are similar in structure to the supporting frames of the front main supporting mechanism. Take the left rear auxiliary supporting frame 32 as an example for specific description, as shown in the figure, Figure 9 The left rear auxiliary supporting frame 32 comprises an adjusting block and a trapezoidal threaded rod 331 with a self-locking function, the adjusting block is arranged at the top end of the threaded rod 331, the adjusting block is the same in structure as the adjusting block 6 of the left rear main supporting frame 22, the third connecting rod is fixed on the threaded rod 331 through a sleeve 332, and the bottom of the sleeve 332 is provided with a locking nut. Rotating the sleeve can adjust the height of the left rear auxiliary supporting frame 32 relative to the third connecting rod, and after being adjusted to a suitable height, the locking nut is tightened for fixation. The right rear auxiliary supporting frame 31 and the left rear auxiliary supporting frame 32 are the same in mechanism and are oppositely arranged, and will not be described herein.

[0050] The fuselage supporting device provided in the embodiment can support and protect the fuselage of the aircraft, and can also adapt to the fuselage supporting device fixed on different sizes of aircrafts.

[0051] It should be further pointed out that the fuselage supporting device provided in the embodiment is used in cooperation with a pull belt to fix the aircraft, and the supporting device mainly plays a supporting role on the fuselage and does not play a main fixing role.

[0052] The use method of the fuselage supporting device suitable for various types of aircrafts is as follows: the device is placed on the mounting platform of the transfer trolley and assembled. Then the fixing plates 55 of the four supporting frames of the front main supporting device and the rear main supporting device are fixed on the mounting platform, then the fourth connecting rod 33 is opened, the aircraft enters the enclosed area formed by the supporting mechanism, and then the fourth connecting rod 33 is fixed. The two supporting frames of the front main supporting mechanism 1 are supported at the position of the keel load-bearing part of the front part of the aircraft fuselage, the two supporting frames of the rear main supporting mechanism 2 are supported at the position of the keel load-bearing part of the rear part of the aircraft fuselage, and the two supporting frames of the rear auxiliary supporting mechanism 3 are supported at the position of the keel of the rear part of the aircraft fuselage. According to the size and shape of the aircraft fuselage, the length of the first connecting rod 13 and the second connecting rod 23, the height of the two supporting frames of the front main supporting mechanism and the two supporting frames of the rear main supporting mechanism, the position and direction of the block seat are adjusted or finely adjusted, so that the block of the front main supporting mechanism, the rear main supporting mechanism and the rear auxiliary supporting mechanism is in close contact with the aircraft fuselage, and the supporting adjustment of the aircraft fuselage is completed. Then the aircraft is fixed by cooperating with the mounting platform and the pull belt, and the transfer can be started.

[0053] Obviously, the above only describes some embodiments of the present application and is not used to limit the present application. For those skilled in the art, the present application can have combinations and variations of the above-mentioned technical features, and those skilled in the art can make improvements, variations, equivalent replacements or use the structure or method of the present application in other fields to achieve the same effect without departing from the spirit and scope of the present application.

Claims

1. A fuselage support device adaptable to a plurality of aircraft types, comprising a front primary support mechanism, a rear primary support mechanism, and a rear secondary support mechanism, characterized in that: The front main support mechanism, the rear main support mechanism, and the rear auxiliary support mechanism each include two support frames. The two support frames of the front main support mechanism are connected by a first link. The front main support mechanism and the rear main support mechanism are connected by two second links. The rear main support mechanism is connected to the rear auxiliary support mechanism by two third links. The two support frames of the rear auxiliary support mechanism are connected by a fourth link. The lengths of the first link and the second link are adjustable. The third link is rotatably connected to the support frame of the rear main support mechanism. The angle between the third link and the support frame of the rear main support mechanism is less than 90 degrees. The front main support mechanism and the rear main support mechanism are fixed on the mounting surface, while the rear auxiliary support mechanism is suspended. The second connecting rod includes a connecting rod and a connecting rod adjustment mechanism. The connecting rod adjustment mechanism is used to adjust the length of the second connecting rod. The second connecting rod includes two connecting rods with external threads at one end. The threads of the two connecting rods are opposite in direction. The threaded ends of the two connecting rods are connected by a second adjusting screw sleeve. The two ends of the second adjusting screw sleeve are respectively provided with positive and negative internal threads. The two ends of the second adjusting screw sleeve are respectively provided with a second locking nut. The other ends of the two connecting rods are respectively fixed on the support frames of the front main support mechanism and the rear main support mechanism. The support frame of the front main support mechanism includes a support base and an adjusting block disposed at the top of the support base. The adjusting block includes a block seat, a block disposed on the block seat, and a lead screw. The top of the block seat has a groove, the block is installed in the groove and can slide in the groove, and the block is connected to the lead screw. The support base includes a base and a first adjusting screw sleeve. The upper part of the base is a threaded screw rod. The first adjusting screw sleeve has an internal thread corresponding to the screw rod and is sleeved on the screw rod. The bottom of the first adjusting screw sleeve is provided with a first locking nut. The adjusting block is provided at the top of the first adjusting screw sleeve. The bottom of the support block is provided with a groove to accommodate the top end of the first adjusting screw sleeve. The support block is fixed to the top end of the first adjusting screw sleeve by positioning pins. There are two positioning pins, which are respectively located on both sides of the top end of the first adjusting screw sleeve. The two ends of the positioning pins are fixed on the support block. The top of the first adjusting screw sleeve is an "I" shaped structure, the top surface of the "I" shaped structure is convex and spherical, and the positioning pin passes through the concave part of the "I" shaped structure.

2. A fuselage support assembly adaptable to a plurality of aircraft types as set forth in claim 1, further characterized by: The support frame of the rear main support mechanism has the same structure as the support frame of the front main support mechanism.

3. A fuselage support assembly for accommodating a plurality of aircraft types as set forth in claim 1, further characterized by: The first link has the same structure as the second link.

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