Assembling platform of combined type aircraft landing gear

Abstract

The utility model discloses an assembly platform of a combined aircraft landing gear, which comprises a posture adjusting mechanism which comprises a universal support structure, a posture adjusting platform, a multidirectional adjusting propeller and a piston rod, the fixing mechanism comprises a supporting frame and an outer cylinder; the vision positioning mechanism is located between the posture adjusting mechanism and the fixing mechanism, the vision positioning mechanism comprises a portal frame, and a binocular vision camera is installed on the portal frame; the utility model relates to the technical field of aircraft landing gear assembly, more accurate positioning is realized by using a binocular vision camera and marking points on two positioning sleeves, six-degree-of-freedom high-accuracy automatic posture adjustment of a piston rod is realized by using a pogo column and two sets of mobile platforms with screw rod modules and matching with vision positioning, and the precision of the piston rod is improved. The problem of reliable assembly of medium and large aircraft landing gears is solved, and the situation that labor is wasted when pure manual assembly or simple equipment is used for assembly is avoided.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of aircraft landing gear assembly, specifically to a kind of assembly platform of combined aircraft landing gear. BACKGROUND

[0002] Landing gear is the lower part of aircraft used for take-off and landing or taxiing to support aircraft and used for ground (water) movement accessory device.Landing gear includes shock absorber, which includes outer cylinder and piston rod, and the piston rod needs to be accurately aligned and pushed into the outer cylinder during assembly.

[0003] The existing assembly still uses manual pressure or simple external device to align and press in, and as the size and weight of aircraft landing gear continue to increase, the precision requirement is higher, and it is difficult to complete assembly by manpower or simple device, secondly, inaccurate assembly will also affect the normal extension of landing gear shock absorber, increase wear and reduce strength when bearing load.

[0004] Most of the products on the market currently only use multi-degree-of-freedom posture adjusting equipment, which has the problem of low posture adjusting accuracy.

[0005] Therefore, we propose a kind of aircraft landing gear posture adjusting assembly platform to solve the problem. CONTENT OF UTILITY MODEL

[0006] To solve the problem proposed in the background art, the utility model is implemented by the following technical solutions: an assembly platform of combined aircraft landing gear, comprising:

[0007] A posture adjusting mechanism, the posture adjusting mechanism includes a universal support structure, a posture adjusting platform, a multi-directional adjusting propeller and a piston rod;

[0008] A fixing mechanism, the fixing mechanism includes a support frame and an outer cylinder;

[0009] A visual positioning mechanism between the posture adjusting mechanism and the fixing mechanism, the visual positioning mechanism includes a gantry, a binocular vision camera is installed on the gantry, and the binocular vision camera is aligned with the mutual docking parts of the outer cylinder and the piston rod.

[0010] Preferably, the universal support structure includes four pogo columns, a force sensor is installed on the lifting end of each pogo column, a universal hinge is fixed on the force sensor, the posture adjusting platform is fixedly installed at one end of the universal hinge, and the posture adjusting platform is lifted and rotated through the universal hinge.

[0011] Preferably, the multi-directional adjusting propeller comprises a first moving platform, a hollow rotating device is installed on the first moving platform, a second moving platform is installed on the hollow rotating device, and the moving direction of the second moving platform is perpendicular to the moving direction of the first moving platform in a horizontal plane.

[0012] Preferably, the first moving platform comprises a first base fixed to an upper wall of the posture adjusting platform, a first screw rod module is installed on the first base along a y direction, a first platform is installed on a moving end of the first screw rod module, the hollow rotating device is installed on an upper wall of the first platform, a first guide rail parallel to the first screw rod module is installed on the first base, and a moving end of the first guide rail is installed on a lower wall of the first platform.

[0013] Preferably, the second moving platform comprises a second base fixedly installed on an upper wall of the hollow rotating device, a second screw rod module is installed on the second base along an x direction, a second platform is installed on a moving end of the second screw rod module, a second guide rail parallel to the second screw rod module is installed on the second base, and a moving end of the second guide rail is installed on a lower wall of the second platform.

[0014] Preferably, the second platform is provided with a first fixed tool, a piston rod positioning sleeve is connected to the first fixed tool through a pin shaft, a center frame is fixedly installed on the second screw rod module close to a fixed mechanism part, a piston rod is inserted into the piston rod positioning sleeve, and the piston rod is movably attached to the center frame.

[0015] Preferably, the fixed mechanism further comprises two second fixed tools, an outer cylinder positioning sleeve is connected to each of the two second fixed tools through a pin shaft, and an outer cylinder is inserted into the outer cylinder positioning sleeve.

[0016] Beneficial effects

[0017] The utility model provides a kind of assembly platform of combined aircraft landing gear, compared with prior art, with the following beneficial effects:

[0018] (1), the aircraft landing gear posture adjusting assembly platform in the utility model is based on binocular vision positioning scheme, more accurate positioning is realized using binocular vision camera and the mark point on two positioning sleeves.

[0019] (2), the aircraft landing gear posture adjusting assembly platform in the utility model utilizes pogo column and two sets of moving platforms with screw rod module, and realizes piston rod six-degree-of-freedom high-precision automatic posture adjustment in cooperation with visual positioning.

[0020] (3), the aircraft landing gear posture adjusting assembly platform realizes reliable assembly of medium and large aircraft landing gears, and avoids the laborious situation during pure manual assembly or assembly by using simple equipment. BRIEF DESCRIPTION OF DRAWINGS

[0021] Figure 1 It is a whole overhead angle three-dimensional structural schematic view of the assembly platform of the combined aircraft landing gear.

[0022] Figure 2 It is a local overhead angle three-dimensional structural schematic view of the assembly platform of the combined aircraft landing gear.

[0023] Figure 3 It is a top view structural schematic view of the assembly platform of the combined aircraft landing gear.

[0024] Figure 4 It is a side view structural schematic view of the assembly platform of the combined aircraft landing gear.

[0025] Figure 5 It is a Figure 1 local enlarged structural schematic view of the middle A.

[0026] In the figure: 1, pogo column, 2, force sensor, 3, universal hinge, 4, posture adjusting platform, 5, first base, 6, first guide rail, 7, first lead screw module, 8, first platform, 9, hollow rotating device, 10, second base, 11, second lead screw module, 12, second guide rail, 13, second platform, 14, first fixed tooling, 15, piston rod, 16, center frame, 17, support frame, 18, second fixed tooling, 19, outer cylinder, 20, piston rod positioning sleeve, 21, outer cylinder positioning sleeve, 22, gantry, 23, binocular vision camera. DETAILED DESCRIPTION

[0027] Based on the embodiments in the utility model, all other embodiments obtained by the ordinary skilled person in the art without making creative labor belong to the range protected by the utility model.

[0028] Embodiment: through the personnel in the art, all electrical components in the case and the power supply matched with them are connected through wires, and appropriate controllers should be selected according to actual conditions to meet the control requirements. The specific connection and control sequence should be completed according to the working order between the electrical components in the following working principle, and the detailed connection means is the known technology in the art. The following mainly introduces the working principle and process, and does not make an explanation on electrical control.

[0029] Please refer to Figures 1-5A kind of assembly platform of combined aircraft landing gear, comprising:

[0030] The pose adjusting mechanism includes a universal support structure, a pose adjusting platform 4, a multi-directional adjusting propeller and a piston rod 15, and is used for six-degree-of-freedom translation and rotation of the piston rod 15 and feeds it into the outer cylinder 19 at a correct angle.

[0031] The fixing mechanism includes a support frame 17 and an outer cylinder 19, and the bottom of the support frame 17 is supported by four ground anchors that can be finely adjusted in height to achieve stability on the ground without shaking.

[0032] The visual positioning mechanism is located between the pose adjusting mechanism and the fixing mechanism, and includes a gantry 22 on which a binocular vision camera 23 is installed, which is aligned with the mutual interfacing parts of the outer cylinder 19 and the piston rod 15, and is used to establish the relative pose of the piston rod 15 and the outer cylinder 19.

[0033] Specifically, the universal support structure includes four pogo columns 1, each of which is provided with a force sensor 2 at the lifting end, and a universal hinge 3 is fixed on the force sensor 2, and the pose adjusting platform 4 is fixedly installed at one end of the universal hinge 3 and is lifted and rotated through the universal hinge 3.

[0034] By lifting two adjacent pogo columns 1, the pose adjusting platform 4 drives the piston rod 15 to rotate in the α, β and γ directions under the connection of the universal hinge 3.

[0035] By simultaneously lifting the four pogo columns 1, the pose adjusting platform 4 drives the piston rod 15 to translate along the z-axis direction.

[0036] Specifically, the multi-directional adjusting propeller includes a first moving platform, a hollow rotating device 9 is installed on the first moving platform, a second moving platform is installed on the hollow rotating device 9, and the moving direction of the second moving platform is perpendicular to the moving direction of the first moving platform in the horizontal plane.

[0037] The second moving platform can be rotated by the hollow rotating device 9, and the piston rod 15 is thus rotated.

[0038] Specifically, the first moving platform includes a first base 5 fixed to the upper wall of the pose adjusting platform 4, a first lead screw module 7 is installed on the first base 5 along the y direction, a first platform 8 is installed on the moving end of the first lead screw module 7, the hollow rotating device 9 is installed on the upper wall of the first platform 8, a first guide rail 6 parallel to the first lead screw module 7 is installed on the first base 5, and the moving end of the first guide rail 6 is installed on the lower wall of the first platform 8.

[0039] Through the work of the first screw module 7, the first platform 8 can drive the piston rod 15 to translate along the y-axis direction, and the first guide rail 6 is used for supporting at both ends of the first platform 8 to ensure the stable movement of the first platform 8;

[0040] Specifically, the second moving platform comprises a second base 10 fixedly installed on the upper wall surface of the hollow rotating device 9, a second screw module 11 installed on the second base 10 along the x direction, a second platform 13 installed on the moving end of the second screw module 11, and a second guide rail 12 installed on the second base 10 and arranged in parallel with the second screw module 11, and the moving end of the second guide rail 12 is installed on the lower wall surface of the second platform 13;

[0041] Specifically, through the work of the second screw module 11, the second platform 13 can drive the piston rod 15 to translate along the x-axis direction, and the second guide rail 12 is used for supporting at both ends of the second platform 13 to ensure the stable movement of the second platform 13;

[0042] Specifically, the second platform 13 is installed with a first fixed tool 14, the first fixed tool 14 is connected with a piston rod positioning sleeve 20 through a pin shaft, a center frame 16 is fixedly installed on the second screw module 11 near the fixed mechanism part, the piston rod 15 is inserted into the piston rod positioning sleeve 20, and the piston rod 15 is movably attached to the center frame 16;

[0043] The piston rod 15 is inserted into the piston rod positioning sleeve 20 to position the piston rod 15, and under the connection of the pin shaft, the piston rod positioning sleeve 20 is rotated on the first fixed tool 14 to place the front end of the piston rod 15 on the center frame 16;

[0044] The center frame 16 has a v-shaped structure, and balls are movably embedded on the v-shaped wall surface, the balls are tangent to the surface of the piston rod 15, and the balls and the piston rod 15 can slide relative to each other, thereby achieving the functions of one-way positioning and supporting the front end of the piston rod 15;

[0045] During assembly, the pose adjusting mechanism can be used to achieve the precise adjustment of the x, y, z, α, β and γ six degrees of freedom of the piston rod 15;

[0046] Specifically, the fixed mechanism further comprises two second fixed tools 18, and the two second fixed tools 18 are connected with outer cylinder positioning sleeves 21 through pin shafts, and the outer cylinder 19 is inserted into the outer cylinder positioning sleeves 21;

[0047] The outer cylinder positioning sleeves 21 on the two second fixed tools 18 are aligned along the axis of the pin shafts, the outer cylinder 19 is inserted into the outer cylinder positioning sleeves 21, and the fixation of the outer cylinder 19 is achieved;

[0048] The piston rod positioning sleeve 20 and the outer cylinder positioning sleeve 21 are in the state of being sleeved with the piston rod 15 and the outer cylinder 19 during binocular vision positioning and attitude adjustment, and the piston rod positioning sleeve 20 and the outer cylinder positioning sleeve 21 are provided with positioning points, which assist in accurately judging the relative direction and position between the two sleeves by binocular vision.

[0049] After the attitude adjustment is completed, the push-in process is carried out, and the piston rod positioning sleeve 20 and the outer cylinder positioning sleeve 21 need to be detached from the first fixing tool 14 and the second fixing tool 18.

[0050] The above merely illustrates the specific implementation of the present application, and is not intended to limit the scope of the present application. Any equivalent changes and modifications made by those skilled in the art without departing from the concept and principles of the present application shall fall within the scope of the present application. It should be noted that the components of the present application are not limited to the above overall application, and the technical features described in the specification of the present application can be selected for single use or combined use according to actual needs, therefore, the present application naturally covers other combinations and specific applications related to the present application.

[0051] Although the embodiments of the present application have been shown and described, it will be understood by those skilled in the art that various changes, modifications, replacements and modifications can be made to these embodiments without departing from the principles and spirits of the present application, and the scope of the present application is defined by the appended claims and their equivalents.

Claims

1. An assembly platform for a combined aircraft landing gear, characterized in that The utility model relates to a kind of multi-axis positioning device, including: Positioning mechanism, the positioning mechanism includes universal support structure, positioning platform (4), multi-directional adjustment propeller and piston rod (15); Fixing mechanism, the fixing mechanism includes support frame (17) and outer cylinder (19); Visual positioning mechanism is positioned between positioning mechanism and fixing mechanism, the visual positioning mechanism includes portal frame (22), binocular vision camera (23) is installed on the portal frame (22), and binocular vision camera (23) is aimed at outer cylinder (19) and piston rod (15) mutual interface part.

2. The assembly platform for a combined aircraft landing gear according to claim 1, characterized in that The universal support structure includes four pogo columns (1), force sensor (2) is installed on the lifting end of each pogo column (1), universal hinge (3) is fixed on force sensor (2), and positioning platform (4) is fixedly installed on one end of universal hinge (3), and positioning platform (4) is lifted and rotated by universal hinge (3).

3. The assembly platform for a combined aircraft landing gear according to claim 1, characterized in that The multi-directional adjustment propeller includes first mobile platform, hollow rotating device (9) is installed on the first mobile platform, second mobile platform is installed on hollow rotating device (9), and the moving direction of second mobile platform is perpendicular to the moving direction of first mobile platform in horizontal plane.

4. The assembly platform for a combined aircraft landing gear according to claim 3, characterized in that The first mobile platform includes first base (5), and the first base (5) is fixed on the upper wall of positioning platform (4), first screw module (7) is installed on the first base (5), first platform (8) is installed on the moving end of first screw module (7), hollow rotating device (9) is installed on the upper wall of first platform (8), first guide rail (6) is installed on the first base (5) and is arranged in parallel with first screw module (7), and the moving end of first guide rail (6) is installed on the lower wall of first platform (8).

5. An assembly platform for a combined aircraft landing gear as claimed in claim 4, characterised in that, The second mobile platform includes second base (10), and the second base (10) is fixedly installed on the upper wall of hollow rotating device (9), second screw module (11) is installed on the second base (10), second platform (13) is installed on the moving end of second screw module (11), second guide rail (12) is installed on the second base (10) and is arranged in parallel with second screw module (11), and the moving end of second guide rail (12) is installed on the lower wall of second platform (13).

6. An assembly platform for a combined aircraft landing gear as claimed in claim 5, characterised in that, First fixed tooling (14) is installed on the second platform (13), piston rod (15) positioning sleeve is connected by pin shaft on the first fixed tooling (14), center frame (16) is fixedly installed on second screw module (11) and is close to fixed mechanism part, piston rod (15) is inserted on piston rod positioning sleeve (20), and piston rod (15) is movably attached to center frame (16).

7. The assembly platform for a combined aircraft landing gear according to claim 1, wherein The fixing mechanism further includes two second fixed toolings (18), and outer cylinder positioning sleeve (21) is connected by pin shaft on the two second fixed toolings (18), and outer cylinder (19) is inserted on outer cylinder positioning sleeve (21).

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