Device and method for mounting aircraft engine

Abstract

This aircraft engine mounting device and method are provided with: a linear movement device that supports an engine support frame that supports an aircraft engine in a horizontal direction so as to be movable in a movement direction orthogonal to the axis of rotation of the aircraft engine; and a first swing device that swingably supports the support frame about a first axis parallel to the rotation axis.

Description

Technical Field

[0001] The present disclosure relates to an aircraft engine mounting device and method. Background Art

[0002] The aircraft is provided with left and right main wings relative to the fuselage, and engines are respectively mounted on the lower parts of the left and right main wings 102. For example, the aircraft removes the engine from the main wing when the engine is maintained. Then, when the engine maintenance is completed, the engine is mounted on the main wing. The engine maintenance work is carried out at a maintenance yard. At the maintenance yard, the engine is lifted by, for example, a bridge crane and moved to the bottom of the main wing. Then, the engine is fixed to the bottom surface of the main wing in a state where the engine is close to the bottom surface of the main wing. As such a conventional aircraft engine mounting device, there is, for example, a device described in the following patent document 1.

[0003] Prior art literature

[0004] Patent Literature

[0005] Patent Document 1: (Japan) Patent No. 6450076 Summary of the invention

[0006] Technical problem to be solved by the invention

[0007] In addition, the main wing extends from the side of the fuselage in the horizontal direction. However, the main wing extends obliquely from the fuselage to the upper side in the vertical direction at a predetermined inclination angle relative to the horizontal direction. Therefore, the lower surface of the main wing for fixing the engine becomes an inclined surface with a predetermined inclination angle relative to the horizontal direction. The aircraft is provided with a mounted portion in a downward U-shape on the lower surface of the main wing, so that the mounting portion provided on the upper part of the engine is engaged with the mounted portion and fixed. However, since the mounted portion is fixed to the inclined lower surface of the main wing, it is difficult to engage the mounting portion with the mounted portion by simply lifting the engine with a crane, and there is a problem that the engine installation operation becomes complicated and requires a long time.

[0008] The present disclosure solves the above-mentioned problems, and an object of the present disclosure is to provide an aircraft engine mounting device and method that can improve the workability of mounting and dismounting operations of the aircraft engine.

[0009] Technical solutions for solving technical problems

[0010] The mounting device of the aircraft engine disclosed in the present invention for achieving the above-mentioned purpose comprises: a linear moving device, which supports the support frame so that it can move freely along a moving direction orthogonal to the rotation axis of the aircraft engine, and the support frame supports the aircraft engine in a horizontal direction; and a first swinging device, which supports the support frame so that it can swing freely around a first axis parallel to the rotation axis.

[0011] In addition, the aircraft engine installation method disclosed in the present invention has the following steps: moving a support frame that supports the aircraft engine in a horizontal direction downwardly from an engine installation position; swinging the support frame around a first axis parallel to the rotation axis of the aircraft engine to move the aircraft engine to a specified inclination angle; and moving the support frame upward in a vertical direction along the inclination angle to position the support frame at the engine installation position.

[0012] Effects of the Invention

[0013] According to the aircraft engine mounting device and method of the present disclosure, it is possible to improve the workability of mounting and dismounting operations of the aircraft engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is a schematic diagram showing the installation status of the engine relative to the aircraft.

[0015] Figure 2 It is a partially cutaway side view showing the aircraft engine mounting device according to the first embodiment.

[0016] Figure 3 It refers to the installation device of the aircraft engine. Figure 1 III-III sectional view.

[0017] Figure 4 It refers to the installation device of the aircraft engine. Figure 1 IV-IV cross-sectional view.

[0018] Figure 5 This is an explanatory diagram showing the installation operation of the engine with respect to the aircraft.

[0019] Figure 6 This is an explanatory diagram showing the installation operation of the engine with respect to the aircraft.

[0020] Figure 7 It is a partially cutaway side view showing a mounting device for an aircraft engine according to a second embodiment.

[0021] Figure 8 It refers to the installation device of the aircraft engine. Figure 6 VII-VII sectional view.

[0022] Fig. 9 This is a schematic diagram showing the operating state of the mounting device of the aircraft engine.

[0023] Fig.10 It is a side view showing an aircraft engine mounting device according to a third embodiment. DETAILED DESCRIPTION

[0024] Hereinafter, the preferred embodiments of the present disclosure will be described in detail with reference to the accompanying drawings. In addition, the present disclosure is not limited to the embodiments, and in the case where there are multiple embodiments, embodiments formed by combining the embodiments are also included. In addition, the constituent elements in the embodiments include elements that can be easily thought of by those skilled in the art, substantially the same elements, and so-called elements of equivalent scope.

[0025] [First embodiment]

[0026] <Aircraft>

[0027] Figure 1 This is a schematic diagram showing the installation status of the engine relative to the aircraft.

[0028] like Figure 1 As shown, the aircraft 100 is configured such that a pair of left and right main wings 102 are provided at the front portion relative to a fuselage 101, a pair of left and right horizontal tail wings 103 are provided at the rear portion, and a vertical tail 104 is provided. Furthermore, the aircraft 100 is provided with an aircraft engine 105, for example, at the lower portion of each main wing 102. However, the installation position of the aircraft engine 105 is not limited to the lower portion of the main wing 102, and may also be installed at a position of the fuselage 101. In addition, the aircraft 100 is provided with a front landing gear 106 at the front portion, and a pair of left and right main landing gears 107 at the rear portion.

[0029] The main wing 102 of the aircraft 100 extends in the horizontal direction from the side of the fuselage 101. However, the main wing 102 extends from the fuselage 101 at a predetermined inclination angle relative to the horizontal direction toward the upper side in the vertical direction. The aircraft engine 105 is mounted on the lower surface 102a of the main wing 102. Therefore, the lower surface 102a of the main wing 102 on which the aircraft engine 105 is mounted is in an inclined direction HD1 having an inclination angle α relative to the horizontal direction HD.

[0030] The aircraft engine 105 is carried to the lower side of the mounting position on the lower surface 102a of the main wing 102. Here, the aircraft engine 105 is lifted and positioned at the mounting position on the lower surface 102a of the main wing 102. However, since the lower surface 102a of the main wing 102 is inclined, it is difficult to position the aircraft engine 105 at the mounting position on the lower surface 102a of the main wing 102 with high accuracy by simply lifting the engine upward in the vertical direction VD. That is, since the lower surface 102a of the main wing 102 is along the inclined direction HD1 inclined at an inclined angle α relative to the horizontal direction HD, it is necessary to lift the aircraft engine 105 obliquely along the moving direction VD1 orthogonal to the inclined direction HD1, that is, the moving direction VD1 inclined at an inclined angle β equal to the inclined angle α relative to the vertical direction VD. Therefore, it is difficult to install the aircraft engine 105 by a device that only lifts in the vertical direction, such as a crane or a lifter that is commonly used.

[0031] <Aircraft engine mounting device>

[0032] Figure 2 is a partially cutaway side view showing the aircraft engine mounting device according to the first embodiment, Figure 3 It refers to the installation device of the aircraft engine. Figure 1 III-III sectional view, Figure 4 It refers to the installation device of the aircraft engine. Figure 1 IV-IV cross-sectional view.

[0033] like Figures 1 to 3 As shown, the aircraft engine mounting device 10 includes a linear moving device 11 and a first swinging device 12 .

[0034] The aircraft engine 105 is supported by a support frame 110. The support frame 110 is in a semi-cylindrical shape. That is, the support frame 110 has a bottom surface 111 in a curved shape and a pair of end surfaces 112 and 113 in a flat shape. Figure 2 An end surface portion 112 is provided on the left side of the bottom surface portion 111. Figure 2 The support frame 110 is arranged along the horizontal direction and is open upward. The aircraft engine 105 is arranged horizontally inside the support frame 110. The aircraft engine 105 is supported by the support frame 110 in such a way that the rotation axis O is along the horizontal direction.

[0035] The support frame 110 restrains the aircraft engine 105 by a plurality of (three in this embodiment) restraint members 121, 122, and 123. The aircraft engine 105 is arranged inside the support frame 110, and the mounting portion 105a is restrained to the support frame 110 by the restraint member 121. In addition, one end 105b of the aircraft engine 105 is restrained to the support frame 110 by the restraint member 122, and the other end 105c is restrained to the support frame 110 by the restraint member 123.

[0036] The linear moving device 11 and the first swinging device 12 are mounted on the traveling trolley 21. The traveling trolley 21 is in the shape of a plate along the horizontal direction. The traveling trolley 21 is equipped with a plurality of (four in this embodiment) traveling wheels 22 on the lower surface. However, the number of the traveling wheels 22 is not limited to four. Each traveling wheel 22 can rotate relative to the traveling trolley 21 with the axis in the vertical direction as the center, and can turn toward the moving direction of the traveling trolley 21. Although not shown in the figure, the traveling trolley 21 has a steering device that can turn each traveling wheel 22 and a driving device that can drive the rotating traveling wheel. The traveling trolley 21 can be driven by an operator riding in the vehicle and operating the steering wheel and the accelerator pedal or the brake pedal. However, the traveling trolley 21 can also be set to allow the operator to drive the trolley without riding in the vehicle through remote operation. In addition, the traveling trolley 21 can also be configured to be towed by a vehicle and travel.

[0037] The linear moving device 11 is provided on the traveling carriage 21, and supports the support frame 110 so as to be movably supported along a moving direction perpendicular to the rotation axis O. The first swinging device 12 supports the support frame 110 so as to be swung freely around a first axis O1 parallel to the rotation axis O. Specifically, the traveling carriage 21 is provided with the first swinging device 12, the first swinging device 12 supports the linear moving device 11, and the linear moving device 11 supports the support frame 110.

[0038] That is, the traveling carriage 21 is provided with a pair of support members 31 and 32 on one side and the other side in the direction of the first axis O1. The support members 31 and 32 are in the same plate shape. The support member 31 is fixed to one side of the axial direction of the first axis O1 on the upper surface of the traveling carriage 21 along a direction orthogonal to the axial direction of the first axis O1. The support member 32 is fixed to the other side of the axial direction of the first axis O1 on the upper surface of the traveling carriage 21 along a direction orthogonal to the axial direction of the first axis O1. The support member 31 and the support member 32 are parallel and opposite to each other with a gap longer than the axial length of the first axis O1 of the support frame 110.

[0039] The first swing device 12 includes a pair of first swing members 33 and 34 and a pair of first drive devices 35 and 36. The first swing member 33 is arranged on the support member 32 side of the support member 31. The first drive device 35 is arranged on the side of the support member 31 opposite to the support member 32. The first drive device 35 is fixed to the support member 31, and the output shaft 35a located at the first axis O1 passes through the support member 31 and is connected to the first swing member 33. Therefore, the first swing member 33 is supported by the support member 31 so as to be swingable (rotatable) around the first axis O1, and can be swung (rotatable) by the first drive device 35.

[0040] In addition, the first swing member 34 is arranged on the support member 31 side of the support member 32. The first drive device 36 is arranged on the side of the support member 32 opposite to the support member 31. The first drive device 36 is fixed to the support member 32, and the output shaft 36a located at the first axis O1 passes through the support member 32 and is connected to the first swing member 34. Therefore, the first swing member 34 is supported by the support member 32 so as to be swingable (rotatable) around the first axis O1, and can be swung (rotatable) by the first drive device 36.

[0041] It should be noted that the pair of first swinging members 33 and 34 are configured as separate members, but can also be formed into an integral member in a rectangular frame shape by connecting the first swinging members 33 and 34 using a connecting member. In addition, as the first swinging device 12, a pair of first swinging members 33 and 34 are provided, but only one of them can be provided.

[0042] The linear motion device 11 has guide rails 41, 42 and drive devices 43, 44. The guide rail 41 has a pair of parallel guide rail portions, which are fixed to the outer surface of the end surface portion 112 of the support frame 110. On the other hand, a guide recess (not shown) is provided on the side surface of the first swing member 33 on the support frame 110 side. And the guide rail 41 of the support frame 110 is fitted into the guide recess of the first swing member 33 so as to be linearly movable. The drive device 43 is, for example, a pair of air cylinders (or hydraulic cylinders, etc.), which are fixed to both sides of the first swing member 33. The front end portion of the drive rod 43a of the drive device 43 is connected to the connecting portion 112a fixed to the end surface portion 112 of the support frame 110.

[0043] In addition, the guide rail 42 has a pair of parallel guide rail portions, which are fixed to the outer surface of the end surface portion 113 of the support frame 110. On the other hand, a guide recess (not shown) is provided on the side surface of the first swing member 34 on the support frame 110 side. And the guide rail 42 of the support frame 110 is fitted into the guide recess of the first swing member 34 so as to be linearly movable. The driving device 44 is, for example, a pair of air cylinders (or hydraulic cylinders, etc.), which are fixed to both sides of the first swing member 34. The front end portion of the driving rod 44a of the driving device 44 is connected to the connecting portion 113a fixed to the end surface portion 113 of the support frame 110.

[0044] Furthermore, the guide rails 41 and 42 are provided on the support frame 110 and the guide recesses are provided on the first swing members 33 and 34 . Alternatively, the guide recesses may be provided on the support frame 110 and the guide rails 41 and 42 may be provided on the first swing members 33 and 34 .

[0045] When the first drive devices 35 and 36 are synchronously driven by the first swing device 12, the output shafts 35a and 36a rotate, and the first swing members 33 and 34 rotate around the first axis O1. Then, the support frame 110 connected to the first swing members 33 and 34 via the guide rails 41 and 42 rotates around the first axis O1. Therefore, the aircraft engine 105 supported by the support frame 110 can be swung, and the circumferential position (mounting angle) of the mounting portion 105a in the aircraft engine 105 can be adjusted.

[0046] In addition, when the driving devices 43 and 44 are synchronously driven by the linear motion device 11, the driving rods 43a and 44a are extended, for example, and the support frame 110 moves along the guide rails 41 and 42 via the connecting parts 112a and 113a. At this time, when the support frame 110 is rotated by the first swing device 12 and the guide rails 41 and 42 are in a state of being inclined relative to the vertical direction, the support frame 110 rises in a direction inclined relative to the vertical direction. Therefore, the aircraft engine 105 supported by the support frame 110 can be raised in a direction inclined relative to the vertical direction.

[0047] <Aircraft engine installation method>

[0048] Figure 5 and Figure 6 This is an explanatory diagram showing the installation operation of the engine with respect to the aircraft.

[0049] The engine installation method of the first embodiment has the following steps: moving the support frame 110 that supports the aircraft engine 105 in the horizontal direction downwardly toward the engine installation position; swinging the support frame 110 around a first axis O1 parallel to the rotation axis O of the aircraft engine 105 to move the aircraft engine 105 to a specified inclination angle; and moving the support frame 110 upwardly in the vertical direction along the inclination angle to position it at the engine installation position.

[0050] like Figure 1 As shown, the aircraft 100 has an aircraft engine 105 mounted on the lower surface 102a of the main wing 102. The aircraft engine 105 needs to be regularly maintained. When the aircraft engine 105 is maintained, the aircraft 100 is transported to a maintenance site. Furthermore, the aircraft engine 105 is removed from the main wing 102, maintained, and then mounted on the main wing 102 again.

[0051] like Figure 5 As shown, the main wing 102 has a mounting member 131 fixed to the lower surface 102a. The lower surface 102a of the main wing 102 is inclined, so the mounting member 131 fixed to the lower surface 102a is also inclined, and the aircraft engine 105 mounted on the mounting member 131 needs to be inclinedly raised along the moving direction VD1 inclined at an inclination angle β relative to the vertical direction VD. Therefore, when the aircraft engine 105 is mounted on the main wing 102 using the mounting member 131, the aircraft engine 105 needs to be inclined to match the inclination angle of the mounting member 131, and then raised upward in the vertical direction to be positioned at the mounting position.

[0052] like Figure 2 As shown, the aircraft engine 105 is supported on a support frame 110, and the support frame 110 is supported on the mounting device 10 of the aircraft engine. Figure 5 As shown, the traveling carriage 21 is moved, and the aircraft engine 105 supported by the support frame 110 is moved below the mounting position, that is, below the mounting member 131 fixed to the main wing 102, and then stopped.

[0053] And, if Figure 6 As shown, by making the first swing device 12 (refer to Figure 2 ) to swing the support frame 110 at an inclination angle β around the first axis O1. Then, the aircraft engine 105 supported by the support frame 110 moves upward on the mounting portion 105a at a position where the mounting portion 105a and the mounting component 131 are opposite, and the direction in which the aircraft engine 105 moves upward on the mounting portion 105a is consistent with the direction in which the aircraft engine 105 moves relative to the mounting component 131. In this state, by moving the linear motion device 11 (see Figure 2) action, the support frame 110 is raised upward in the moving direction VD1 inclined at the inclination angle β relative to the vertical direction VD while maintaining the inclination angle β of the support frame 110. Then, the mounting portion 105a of the aircraft engine 105 supported by the support frame 110 is properly engaged with the mounting member 131 of the main wing 102 and is positioned at an appropriate position.

[0054] After that, the mounting portion 105a of the aircraft engine 105 is fastened to the mounting member 131, and the support by the support frame 110 is released. In addition, the aircraft engine 105 is provided with a cabin surrounding the aircraft engine 105 at the lower part of the main wing 102, but it is omitted here.

[0055] In addition, here, the operation of mounting the aircraft engine 105 on the main wing 102 using the aircraft engine mounting device 10 of the present embodiment is described, but it can also be applied to the operation of removing the aircraft engine 105 from the main wing 102 using the aircraft engine mounting device 10.

[0056] [Second embodiment]

[0057] Figure 7 is a partially cutaway side view showing a mounting device for an aircraft engine according to a second embodiment, Figure 8 It refers to the installation device of the aircraft engine. Figure 6 VII-VII sectional view, Fig. 9 1 is a schematic diagram showing the operating state of the mounting device of the aircraft engine. In addition, the same reference numerals are attached to the components having the same functions as those of the first embodiment described above, and detailed descriptions thereof are omitted.

[0058] like Figure 7 and Figure 8 As shown, the aircraft engine mounting device 10A includes a linear motion device 11, a first swing device 12, and a second swing device 13. The linear motion device 11 and the first swing device 12 are substantially the same as those of the first embodiment.

[0059] The second swing device 13 is provided on the travel carriage 21, and supports the support frame 110 so as to swing freely around the second axis O2 which is perpendicular to the first axis O1 and along the horizontal direction. Specifically, the second swing device 13 is provided on the travel carriage 21, and the second swing device 13 supports the first swing device 12, and the first swing device 12 supports the linear motion device 11, and the linear motion device 11 supports the support frame 110. In addition, the vertical positions of the first axis O1 and the second axis O2 may be consistent or offset.

[0060] That is, the traveling vehicle 21 is provided with a pair of support members 31 and 32 on one side and the other side in the direction of the second axis O2. The support members 31 and 32 are in the same plate shape. The support member 31 is fixed to the upper surface on one side of the axial direction of the second axis O2 along a direction orthogonal to the axial direction of the second axis O2 of the traveling vehicle 21. The support member 32 is fixed to the upper surface on the other side of the axial direction of the second axis O2 along a direction orthogonal to the axial direction of the second axis O2 of the traveling vehicle 21. The support member 31 and the support member 32 are parallelly opposed to each other with a gap longer than the axial length of the second axis O2 of the support frame 110.

[0061] The second swing device 13 includes a second swing member 51 and a pair of second drive devices 52 and 53. The second swing member 51 is in a rectangular frame shape and is arranged between the support member 31 and the support member 32 along the vertical direction. The second swing member 51 includes first members 51a and 51b arranged opposite to the support member 31 and the support member 32, and second members 51c and 51d connecting the first members 51a and 51b. The second drive device 52 is arranged on the side of the support member 31 opposite to the support member 32. The second drive device 53 is arranged on the side of the support member 32 opposite to the support member 31. The second drive device 52 is fixed to the support member 31, and the output shaft 52a located at the second axis O2 penetrates the support member 31 and is connected to the first member 51a of the second swing member 51. The second drive device 53 is fixed to the support member 32, and the output shaft 53a located at the second axis O2 penetrates the support member 32 and is connected to the first member 51b of the second swing member 51.

[0062] Therefore, the second swing member 51 is supported by the support members 31 and 32 so as to be swingable (rotatable) about the second axis O2, and can be swingable (rotatable) by the second drive devices 52 and 53. In addition, as the second swing device 13, a pair of second drive devices 52 and 53 are provided, but only one of them may be provided.

[0063] The first swing device 12 has a pair of first swing members 33, 34 and a pair of first drive devices 35, 36. The first swing member 33 is arranged on the first member 51b side of the first member 51a of the second swing member 51. The first drive device 35 is arranged on the side of the first member 51a opposite to the first member 51b. The first drive device 35 is fixed to the first member 51a, and the output shaft 35a located at the first axis O1 passes through the first member 51a and is connected to the first swing member 33. Therefore, the first swing member 33 is supported by the first member 51a so as to be swingable (rotatable) around the first axis O1, and can be swung (rotated) by the first drive device 35.

[0064] In addition, the first swing member 34 is arranged on the first member 51a side of the first member 51b of the second swing member 51. The first drive device 36 is arranged on the side of the first member 51b opposite to the first member 51a. The first drive device 36 is fixed to the first member 51b, and the output shaft 36a located at the first axis O1 passes through the first member 51b and is connected to the first swing member 34. Therefore, the first swing member 34 is supported by the first member 51b so as to be swingable (rotatable) around the first axis O1, and can be swung (rotated) by the first drive device 36.

[0065] The linear motion device 11 has guide rails 41 , 42 and drive devices 43 , 44 .

[0066] When the second drive devices 52 and 53 are synchronously driven by the second swing device 13, the output shafts 52a and 53a rotate, and the second swing member 51 rotates around the second axis O2. Then, the support frame 110 supported by the second swing member 51 via the first swing device 12 and the linear motion device 11 rotates around the second axis O2. Therefore, the aircraft engine 105 supported by the support frame 110 can be swung, and the angle of the mounting portion 105a in the aircraft engine 105 relative to the axial direction (the direction of the rotation axis) can be adjusted.

[0067] like Fig. 9 As shown, the lower surface 102a of the main wing 102 of the aircraft 100 is sometimes inclined upward in the vertical direction at a predetermined inclination angle relative to the horizontal direction in the front-rear direction. Therefore, when the aircraft engine 105 is mounted on the main wing 102, it is necessary to make the aircraft engine 105 inclined relative to the horizontal direction (vertical direction) in the front-rear direction of the rotation axis O (first axis O1).

[0068] That is, the aircraft engine 105 is supported by the support frame 110, and the support frame 110 is supported by the aircraft engine mounting device 10A. First, the travel carriage 21 is moved to move the aircraft engine 105 supported by the support frame 110 to the bottom of the mounting position, that is, to the bottom of the mounting member 131 fixed to the main wing 102, and then stops.

[0069] Then, by making the second swing device 13 (refer to Figure 8 ) to swing the support frame 110 at a predetermined tilt angle around the second axis O2. Then, the aircraft engine 105 supported by the support frame 110 moves upward on the mounting portion 105a at a position where the mounting portion 105a faces the mounting component 131, and the direction in which the aircraft engine 105 is inserted into the mounting portion 105a coincides with the direction in which the aircraft engine 105 is inserted into the mounting component 131. In this state, the linear motion device 11 (see Figure 7) action, the support frame 110 is raised while maintaining the tilt angle of the support frame 110. Then, the mounting portion 105a of the aircraft engine 105 supported by the support frame 110 is properly engaged with the mounting member 131 of the main wing 102 and positioned at an appropriate position.

[0070] After that, the mounting portion 105a of the aircraft engine 105 is fastened to the mounting member 131, and the support by the support frame 110 is released. In addition, here, the operation of mounting the aircraft engine 105 on the main wing 102 by the aircraft engine mounting device 10A of the present embodiment is described, but it can also be applied to the operation of removing the aircraft engine 105 from the main wing 102 by the aircraft engine mounting device 10A.

[0071] [Third Embodiment]

[0072] Fig.10 1 is a side view showing an aircraft engine mounting device according to a third embodiment. Components having the same functions as those of the first embodiment described above are denoted by the same reference numerals and detailed descriptions thereof are omitted.

[0073] like Fig.10 As shown, the aircraft engine mounting device 10B includes a linear motion device 11, a first swing device 12, and a second swing device 13A. The linear motion device 11 and the first swing device 12 are substantially the same as those of the first embodiment.

[0074] The second swing device 13A is provided on the travel carriage 21, and supports the support frame 110 so that it can swing freely around the second axis O2 which is perpendicular to the first axis O1 and along the horizontal direction. Specifically, the travel carriage 21 is equipped with four travel wheels 22 on the lower surface. One side of the first axis O1 ( Fig.10 The two travel wheels 22 (on the left side of the travel vehicle 21) are mounted on the lower surface of the travel vehicle 21 via the hydraulic cylinder 61 constituting the second swing device 13A. The second swing device 13A supports the support frame 110 so that it can swing freely by extending (or shortening) the hydraulic cylinder 61 and tilting the travel vehicle 21. In this case, the second axis O2 becomes the other side ( Fig.10 It should be noted that the other side of the first axis O1 ( Fig.10 The two traveling wheels 22 (on the right side) may also be mounted on the lower surface of the traveling vehicle 21 via a hydraulic cylinder constituting the second swing device 13A.

[0075] Note that the function of the aircraft engine mounting device 10B is the same as that of the aircraft engine mounting device 10A according to the second embodiment, and thus the description thereof will be omitted.

[0076] [Effects of this embodiment]

[0077] The first type of aircraft engine installation device comprises: a linear moving device 11, which supports the support frame 110 so that it can move freely along a moving direction orthogonal to the rotation axis O of the aircraft engine 105, and the support frame 110 supports the aircraft engine 105 in a horizontal direction; and a first swinging device 12, which supports the support frame 110 so that it can swing freely around a first axis O1 parallel to the rotation axis O.

[0078] According to the first embodiment of the aircraft engine mounting device, even if the mounting angle of the aircraft engine 105 relative to the aircraft 100 is inclined to the left or right relative to the vertical direction, the mounting angle of the aircraft engine 105 can be adjusted by swinging the support frame 110 supporting the aircraft engine 105 using the first swing device 12, thereby improving the operability in the disassembly and assembly operations of the aircraft engine.

[0079] The aircraft engine mounting device of the second embodiment is based on the aircraft engine mounting device of the first embodiment, and further includes a travel carriage 21, and the travel carriage 21 is provided with a first swing device 12, the first swing device 12 supports the linear motion device 11, and the linear motion device 11 supports the support frame 110. Therefore, by driving the travel carriage 21, the linear motion device 11, the first swing device 12, and the support frame 110 can be moved to a desired position.

[0080] The aircraft engine mounting device of the third embodiment is based on the aircraft engine mounting device of the second embodiment, wherein the traveling carriage 21 is provided with a pair of support members 31, 32 on one side and the other side in the direction of the first axis O1, a pair of first swing members 33, 34 constituting the first swing device 12 are swingably supported by the pair of support members 31, 32, and the linear motion device 11 is movably supported by the support frame 110 relative to the pair of first swing members 33, 34. Thus, the linear motion device 11 and the first swing device 12 can be efficiently mounted on the traveling carriage 21.

[0081] The fourth embodiment of the aircraft engine mounting device is based on the second or third embodiment of the aircraft engine mounting device, and the travel vehicle 21 further has at least three steerable travel wheels 22. This makes it easy to adjust the position of the aircraft engine 105 relative to the engine mounting position.

[0082] The aircraft engine mounting device of the fifth embodiment is based on the aircraft engine mounting device of any one of the first to fourth embodiments, and further includes a second swing device 13, 13A that swingably supports the support frame 110 around a second axis O2 that is orthogonal to the first axis O1 and along the horizontal direction. Thus, even if the mounting angle of the aircraft engine 105 relative to the aircraft 100 is tilted in the front-rear direction and the left-right direction relative to the vertical direction, the mounting angle of the aircraft engine 105 can be adjusted by swinging the support frame 110 that supports the aircraft engine 105 using the first swing device 12 and the second swing device 13, 13A.

[0083] The aircraft engine mounting device of the sixth embodiment is based on the aircraft engine mounting device of the fifth embodiment, and further includes a travel carriage 21, and the travel carriage 21 is provided with a second swing device 13, the second swing device 13 supports the first swing device 12, the first swing device 12 supports the linear motion device 11, and the linear motion device 11 supports the support frame 110. Thus, by driving the travel carriage 21, the linear motion device 11, the first swing device 12, the second swing device 13, and the support frame 110 can be moved to a desired position.

[0084] The seventh embodiment of the aircraft engine mounting device is based on the fifth embodiment or the sixth embodiment of the aircraft engine mounting device, wherein the traveling carriage 21 is provided with a pair of support members 31, 32 on one side and the other side in the direction of the second axis O2, the second swing member 51 constituting the second swing device 13 is swingably supported by the pair of support members 31, 32, the pair of first swing members 33, 34 constituting the first swing device 12 is swingably supported by the second swing member 51, and the linear motion device 11 is movably supported by the support frame 110 relative to the pair of first swing members 33, 34. Thus, the linear motion device 11, the first swing device 12, and the second swing device 13 can be efficiently mounted on the traveling carriage 21.

[0085] The aircraft engine mounting device of the eighth embodiment is based on the aircraft engine mounting device of the seventh embodiment, and the second swing device 13A swingably supports the support frame 110 by tilting the travel carriage 21. Therefore, there is no need to change the linear motion device 11 or the first swing device 12, and the structure can be simplified.

[0086] The ninth embodiment of the aircraft engine installation method has the following steps: moving the support frame 110 supporting the aircraft engine 105 in the horizontal direction to the lower side of the engine installation position; swinging the support frame 110 around the first axis O1 parallel to the rotation axis O of the aircraft engine 105 to move the aircraft engine 105 to a predetermined tilt angle; and moving the support frame 110 upward in the vertical direction along the tilt angle to position the support frame 110 at the engine installation position. Thus, even if the installation angle of the aircraft engine 105 relative to the aircraft 100 is tilted relative to the vertical direction, the installation angle of the aircraft engine 105 can be adjusted, and the workability in the disassembly and assembly of the aircraft engine can be improved.

[0087] Furthermore, in the above-described embodiment, the support frame 110 is formed into a semi-cylindrical shape, but the shape is not limited to this shape, and any shape may be used as long as it supports the aircraft engine 105 .

[0088] In the above embodiment, the second swing device is the hydraulic cylinder 61, but the first swing device may be a fluid pressure cylinder such as the hydraulic cylinder 61. The first and second swing devices are not limited to fluid pressure cylinders, but may be screw devices or the like.

[0089] Description of Reference Numerals

[0090] 10, 10A, 10B: Aircraft engine mounting devices

[0091] 11: Linear moving device

[0092] 12: First swing device

[0093] 13, 13A: Second swing device

[0094] 21: Driving trolley

[0095] 22: Driving wheels

[0096] 31, 32: Supporting parts

[0097] 33, 34: First swinging member

[0098] 35, 36: First drive device

[0099] 41, 42: Guide rail

[0100] 43, 44: Driving device

[0101] 51: Second swing member

[0102] 52, 53: Second drive device

[0103] 61: Hydraulic cylinder

[0104] 100: Aircraft

[0105] 101: Body

[0106] 102: Main wing

[0107] 103: Horizontal tail

[0108] 104: Vertical tail

[0109] 105: Aircraft engines

[0110] 110: Support frame

Claims

1. An aircraft engine mounting device, characterized in that: have: A linear moving device that supports the support frame movably along a moving direction orthogonal to the rotation axis of the aircraft engine, wherein the support frame supports the aircraft engine in a horizontal direction; The first swing device supports the support frame so as to be swingable around a first axis parallel to the rotation axis.

2. The aircraft engine mounting device according to claim 1, characterized in that: A traveling carriage is provided, and the first swing device is provided on the traveling carriage. The first swing device supports the linear motion device, and the linear motion device supports the support frame.

3. The aircraft engine mounting device according to claim 2, characterized in that: The traveling carriage is provided with a pair of supporting parts on one side and the other side in the direction of the first axis, a pair of first swinging parts constituting the first swinging device are swingably supported on the pair of supporting parts, and the linear moving device supports the supporting frame movably relative to the pair of first swinging parts.

4. The aircraft engine mounting device according to claim 2 or 3, characterized in that: The traveling vehicle has at least three steerable wheels.

5. The aircraft engine mounting device according to claim 1, characterized in that: A second swing device is provided for swingably supporting the support frame around a second axis that is perpendicular to the first axis and along a horizontal direction.

6. The aircraft engine mounting device according to claim 5, characterized in that: A traveling carriage is provided, and the second swing device is provided on the traveling carriage. The second swing device supports the first swing device. The first swing device supports the linear motion device. The linear motion device supports the support frame.

7. The aircraft engine mounting device according to claim 6, characterized in that: The traveling trolley is provided with a pair of supporting parts on one side and the other side in the direction of the second axis, the second swinging part constituting the second swinging device is swingably supported on the pair of supporting parts, the pair of first swinging parts constituting the first swinging device is swingably supported on the second swinging part, and the linear moving device supports the supporting frame movably relative to the pair of first swinging parts.

8. The aircraft engine mounting device according to claim 6 or 7, characterized in that: The second swing device supports the support frame in a swingable manner by tilting the traveling carriage.

9. A method for installing an aircraft engine, characterized in that: The process includes: Moving a support frame that supports the aircraft engine in a horizontal direction downwardly from the engine installation position; The support frame is swung about a first axis parallel to the rotation axis of the aircraft engine to move the aircraft engine to a predetermined tilt angle; The support frame is moved upward in the vertical direction along the inclination angle to be positioned at the engine mounting position.

Images