Mounting apparatus and method for aircraft engines

Abstract

To improve workability of attachment / detachment work of an aircraft engine in a device and a method for attaching an aircraft engine.SOLUTION: A device for attaching an aircraft engine comprises: a linear movement device which supports a support frame, by which an aircraft engine is supported along a horizontal direction, so that the support frame can move along a movement direction orthogonal to a rotation axis of the aircraft engine; and a first swing device that supports the support frame so that the support frame can swing about a first axis parallel to the rotation axis.SELECTED DRAWING: Figure 1

Description

Technical Field

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

Background Art

[0002] An aircraft has left and right main wings provided on the fuselage, and engines are respectively mounted below the left and right main wings 102. For example, when performing maintenance on an engine, the engine is removed from the main wing. Then, when the maintenance of the engine is completed, the engine is mounted on the main wing. The engine maintenance work is carried out at a maintenance site. At the maintenance site, for example, the engine is lifted by an overhead crane and moved below the main wing. Then, with the engine approaching the lower surface of the main wing, the engine is fixed to the lower surface of the main wing. As such a conventional aircraft engine mounting device, for example, there is one described in Patent Document 1 below.

Prior Art Documents

Patent Documents

[0003]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0004] Incidentally, the main wing extends horizontally from the side of the fuselage. However, the main wing extends vertically upward from the fuselage at a predetermined angle of inclination relative to the horizontal. Therefore, the underside of the main wing, where the engine is fixed, is an inclined surface at a predetermined angle of inclination relative to the horizontal. The aircraft has a downward-facing U-shaped mounting section on the underside of the main wing, and the mounting section on the top of the engine is fitted into this mounting section to fix it in place. However, because the mounting section is fixed to the inclined underside of the main wing, it is difficult to fit the mounting section into the mounting section simply by raising the engine with a crane, resulting in a complicated and time-consuming engine installation process.

[0005] This disclosure aims to solve the aforementioned problems and to provide an aircraft engine mounting device and method that improves work efficiency in the attachment and detachment of aircraft engines. [Means for solving the problem]

[0006] To achieve the above objective, the aircraft engine mounting device of the present disclosure comprises a linear movement device that supports a support frame, on which the aircraft engine is supported so as to be aligned horizontally, so as to be movable along a direction of movement perpendicular to the rotation axis of the aircraft engine, and a first swinging device that supports the support frame so as to be swingable about a first axis parallel to the rotation axis.

[0007] Furthermore, the method for mounting an aircraft engine according to this disclosure includes the steps of: moving a support frame, which supports the aircraft engine so as to be aligned horizontally, below the engine mounting position; oscillating the support frame about a first axis parallel to the rotation axis of the aircraft engine to move the aircraft engine to a predetermined inclination angle; and moving the support frame vertically upward along the inclination angle to position it at the engine mounting position. [Effects of the Invention]

[0008] The aircraft engine mounting device and method of this disclosure can improve work efficiency in the installation and removal of aircraft engines. [Brief explanation of the drawing]

[0009] [Figure 1] Figure 1 is a schematic diagram showing the engine's mounting configuration on an aircraft. [Figure 2] Figure 2 is a partially cutaway side view showing the mounting device for an aircraft engine according to the first embodiment. [Figure 3] Figure 3 is a cross-sectional view taken along line III-III in Figure 1, showing the mounting device for an aircraft engine. [Figure 4] Figure 4 is a cross-sectional view taken along line IV-IV of Figure 1, showing the mounting device for an aircraft engine. [Figure 5] Figure 5 is an explanatory diagram illustrating the engine installation process on an aircraft. [Figure 6] Figure 6 is an explanatory diagram illustrating the engine installation process on an aircraft. [Figure 7] Figure 7 is a partially cutaway side view showing the mounting device for an aircraft engine according to the second embodiment. [Figure 8] Figure 8 is a cross-sectional view taken along line VII-VII of Figure 6, showing the mounting device for an aircraft engine. [Figure 9] Figure 9 is a schematic diagram showing the operating state of the aircraft engine mounting device. [Figure 10] Figure 10 is a side view showing the mounting device for an aircraft engine according to the third embodiment. [Modes for carrying out the invention]

[0010] Preferred embodiments of the present disclosure will be described in detail below with reference to the drawings. However, these embodiments do not limit the present disclosure, and where there are multiple embodiments, they may be combinations of these embodiments. Furthermore, the components in the embodiments include those readily conceivable by those skilled in the art, those that are substantially identical, and those that are equivalent.

[0011] [First Embodiment] <Aircraft> Figure 1 is a schematic diagram showing the engine's mounting configuration on an aircraft.

[0012] As shown in Figure 1, the aircraft 100 is constructed with a fuselage 101, a pair of main wings 102 at the front, a pair of horizontal stabilizers 103 at the rear, and a vertical stabilizer 104. The aircraft 100 has, for example, an aircraft engine 105 mounted on the underside of each main wing 102. However, the mounting position of the aircraft engine 105 is not limited to the underside of the main wings 102; some are mounted on the fuselage 101. The aircraft 100 also has a nose gear 106 at the front and a pair of main landing gears 107 at the rear.

[0013] The aircraft 100 has wings 102 that extend horizontally from the sides of the fuselage 101. However, the wings 102 extend vertically upward from the fuselage 101 at a predetermined angle of inclination with respect to the horizontal direction. The aircraft engine 105 is mounted on the lower surface 102a of the wings 102. Therefore, the lower surface 102a of the wings 102 to which the aircraft engine 105 is mounted has an inclination direction HD1 with an inclination angle α with respect to the horizontal direction HD.

[0014] The aircraft engine 105 is conveyed to below 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 accurately position the engine at the mounting position on the lower surface 102a of the main wing 102 only by lifting the engine above the vertical direction VD. That is, since the main wing 102 has its lower surface 102a inclined along the inclination direction HD1 at an inclination angle α with respect to the horizontal direction HD, it is necessary to obliquely lift the aircraft engine 105 along the moving direction VD1 orthogonal to the inclination direction HD1, that is, along the moving direction VD1 inclined by the same inclination angle β as the inclination angle α with respect to the vertical direction VD. Therefore, it is difficult to mount the aircraft engine 105 using a device that can only be lifted in the vertical direction, such as a commonly used crane or lifter.

[0015] <Aircraft Engine Mounting Device> FIG. 2 is a side view with a part cut away showing the aircraft engine mounting device of the first embodiment, FIG. 3 is a cross-sectional view taken along line III-III of FIG. 1 showing the aircraft engine mounting device, and FIG. 4 is a cross-sectional view taken along line IV-IV of FIG. 1 showing the aircraft engine mounting device.

[0016] As shown in FIGS. 1 to 3, the aircraft engine mounting device 10 includes a linear movement device 11 and a first swing device 12.

[0017] The aircraft engine 105 is supported by a support frame 110. The support frame 110 has a semi-cylindrical shape. That is, the support frame 110 has a bottom surface portion 111 having a curved shape and a pair of end surface portions 112, 113 having a planar shape. The end surface portion 112 is provided on one side (the left side in FIG. 2) of the bottom surface portion 111, and the end surface portion 113 is provided on the other side (the right side in FIG. 2) of the bottom surface portion 111. The support frame 110 is arranged along the horizontal direction and opens upward. The aircraft engine 105 is arranged inside the support frame 110 along the horizontal direction. The aircraft engine 105 is supported by the support frame 110 such that the rotation axis O is along the horizontal direction.

[0018] The support frame 110 restrains the aircraft engine 105 with a plurality of restraining members 121, 122, and 123 (three in this embodiment). The aircraft engine 105 is positioned inside the support frame 110, and its mounting portion 105a is restrained to the support frame 110 by the restraining member 121. In addition, one end 105b of the aircraft engine 105 is restrained to the support frame 110 by the restraining member 122, and the other end 105c is restrained to the support frame 110 by the restraining member 123.

[0019] The linear movement device 11 and the first rocking device 12 are mounted on a traveling carriage 21. The traveling carriage 21 has a plate shape aligned horizontally. Multiple (four in this embodiment) traveling wheels 22 are mounted on the underside of the traveling carriage 21. However, the number of traveling wheels 22 is not limited to four. Each traveling wheel 22 is rotatable about an axis perpendicular to the traveling carriage 21 and is steerable in the direction of movement of the traveling carriage 21. The traveling carriage 21 has a steering device that can steer each traveling wheel 22 and a drive device that can drive and rotate the traveling wheels. The traveling carriage 21 can be operated by a worker who is riding on it and operating the steering wheel, accelerator pedal, and brake pedal. However, the traveling carriage 21 may be operated remotely without a worker riding on it. The traveling carriage 21 may also be configured to be towed by a vehicle.

[0020] The linear movement device 11 is provided on the traveling carriage 21 and supports the support frame 110 so that it can move along a direction of movement perpendicular to the rotation axis O. The first rocking device 12 supports the support frame 110 so that it can rock around a first axis O1 parallel to the rotation axis O. Specifically, the first rocking device 12 is provided on the traveling carriage 21, the first rocking device 12 supports the linear movement device 11, and the linear movement device 11 supports the support frame 110.

[0021] In other words, the trolley 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 have the same plate shape. Support member 31 is fixed on the upper surface of the trolley 21 on one side in the axial direction of the first axis O1, along a direction perpendicular to the axial direction of the first axis O1. Support member 32 is fixed on the upper surface of the trolley 21 on the other side in the axial direction of the first axis O1, along a direction perpendicular to the axial direction of the first axis O1. Support members 31 and 32 face each other in parallel with a distance between them that is longer than the axial length of the support frame 110 at the first axis O1.

[0022] The first rocking device 12 includes a pair of first rocking members 33 and 34 and a pair of first drive devices 35 and 36. The first rocking member 33 is positioned on the support member 32 side of the support member 31. The first drive device 35 is positioned on the opposite side of the support member 31 from the support member 32. The first drive device 35 is fixed to the support member 31, and its output shaft 35a, located at the first axis O1, passes through the support member 31 and is connected to the first rocking member 33. Therefore, the first rocking member 33 is supported by the support member 31 so as to be able to swing (rotate) around the first axis O1 and is able to swing (rotate) by the first drive device 35.

[0023] Furthermore, the first oscillating member 34 is positioned on the support member 31 side of the support member 32. The first drive unit 36 ​​is positioned on the support member 32 on the opposite side from the support member 31. The first drive unit 36 ​​is fixed to the support member 32, and its output shaft 36a, located at the first axis O1, passes through the support member 32 and is connected to the first oscillating member 34. Therefore, the first oscillating member 34 is supported by the support member 32 so as to be able to swing (rotate) around the first axis O1 and is able to swing (rotate) by the first drive unit 36.

[0024] Although the pair of first oscillating members 33 and 34 are configured as separate components, they may be connected by a connecting member to form a single rectangular frame-shaped component. Furthermore, while the first oscillating device 12 is provided with a pair of first oscillating members 33 and 34, only one of them may be used.

[0025] The linear movement device 11 includes guide rails 41 and 42 and drive devices 43 and 44. The guide rail 41 has a pair of parallel rail sections and is fixed to the outer surface of the end face 112 of the support frame 110. On the other hand, the first swinging member 33 is provided with a guide recess (not shown) on the side facing the support frame 110. The guide rail 41 of the support frame 110 is fitted into the guide recess of the first swinging member 33 so as to be able to move linearly. The drive device 43 is, for example, a pair of air cylinders (or hydraulic cylinders, etc.) and is fixed to both sides of the first swinging member 33. The tip of the drive rod 43a of the drive device 43 is connected to a connecting portion 112a fixed to the end face 112 of the support frame 110.

[0026] Furthermore, the guide rail 42 has a pair of parallel rail sections and is fixed to the outer surface of the end face 113 of the support frame 110. On the other hand, the first oscillating member 34 is provided with a guide recess (not shown) on the side facing the support frame 110. The guide rail 42 of the support frame 110 is fitted into the guide recess of the first oscillating member 34 so as to be able to move in a straight line. The drive device 44 is, for example, a pair of air cylinders (or hydraulic cylinders, etc.) and is fixed to both sides of the first oscillating member 34. The tip of the drive rod 44a of the drive device 44 is connected to a connecting portion 113a fixed to the end face 113 of the support frame 110.

[0027] In this design, guide rails 41 and 42 are provided on the support frame 110, and guide recesses are provided on the first oscillating members 33 and 34. However, it is also possible to provide guide recesses on the support frame 110 and guide rails 41 and 42 on the first oscillating members 33 and 34.

[0028] When the first drive units 35 and 36 are driven synchronously by the first oscillating device 12, the output shafts 35a and 36a rotate, causing the first oscillating members 33 and 34 to rotate around the first axis O1. As a result, the support frame 110, which is connected to the first oscillating members 33 and 34 via guide rails 41 and 42, rotates around the first axis O1. Therefore, the aircraft engine 105 supported by the support frame 110 can be oscillated, and the circumferential position (mounting angle) of the mounting portion 105a on the aircraft engine 105 can be adjusted.

[0029] Furthermore, when the linear movement device 11 drives the drive devices 43 and 44 synchronously, the drive rods 43a and 44a extend, 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, the support frame 110 rotates due to the first rocking device 12, and if the guide rails 41 and 42 are inclined with respect to the vertical, the support frame 110 rises along the direction inclined with respect to the vertical. As a result, the aircraft engine 105 supported by the support frame 110 can be raised along the direction inclined with respect to the vertical.

[0030] <Aircraft engine mounting method> Figures 5 and 6 are explanatory diagrams illustrating the engine installation process on an aircraft.

[0031] The engine mounting method of the first embodiment includes the steps of: moving a support frame 110, which supports the aircraft engine 105 so as to be aligned horizontally, to below the engine mounting position; swinging the support frame 110 about a first axis O1 parallel to the rotation axis O of the aircraft engine 105 to move the aircraft engine 105 to a predetermined inclination angle; and moving the support frame 110 vertically upward along the inclination angle to position it at the engine mounting position.

[0032] As shown in Figure 1, the aircraft 100 has an aircraft engine 105 mounted on the underside 102a of the main wing 102. The aircraft engine 105 requires periodic maintenance. When the aircraft engine 105 is to be maintained, the aircraft 100 is transported to a maintenance facility. The aircraft engine 105 is then removed from the main wing 102, and after maintenance is performed, it is reattached to the main wing 102.

[0033] As shown in Figure 5, the main wing 102 is fixed to the lower surface 102a with a mounting member 131. Since the lower surface 102a of the main wing 102 is inclined, the mounting member 131 fixed to the lower surface 102a is also inclined, and the aircraft engine 105 to be attached to the mounting member 131 needs to be raised diagonally along the direction of movement VD1, which is inclined by an angle β with respect to the vertical direction VD. Therefore, when attaching the aircraft engine 105 to the main wing 102 with 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 vertically upward to be positioned at the mounting location.

[0034] As shown in Figure 2, the aircraft engine 105 is supported by a support frame 110, and the support frame 110 is supported by an aircraft engine mounting device 10. First, as shown in Figure 5, the trolley 21 is moved to move the aircraft engine 105, which is supported by the support frame 110, below its mounting position, that is, below the mounting member 131 fixed to the main wing 102, and then it is stopped.

[0035] Then, as shown in Figure 6, the first rocking device 12 (see Figure 2) is activated to rock the support frame 110 by an inclination angle β about the first axis O1. As a result, the aircraft engine 105 supported by the support frame 110 is positioned so that the mounting portion 105a faces the mounting member 131, and the upward direction of the mounting portion 105a coincides with the insertion direction into the mounting member 131. In this state, the linear movement device 11 (see Figure 2) is activated to raise the support frame 110 upward in the movement direction VD1, which is inclined by an inclination angle β with respect to the vertical direction VD, while maintaining the inclination angle β of the support frame 110. As a result, the aircraft engine 105 supported by the support frame 110 is positioned correctly, with the mounting portion 105a properly fitted into the mounting member 131 of the main wing 102.

[0036] Subsequently, the aircraft engine 105 is fastened to the mounting member 131 at the mounting portion 105a, and the support from the support frame 110 is released. Although the aircraft engine 105 is surrounded by a nacelle and other components located below the main wing 102, these are omitted here.

[0037] Furthermore, although this description has focused on the process of attaching the aircraft engine 105 to the main wing 102 using the aircraft engine mounting device 10 of this embodiment, the aircraft engine mounting device 10 can also be applied to the process of removing the aircraft engine 105 from the main wing 102.

[0038] [Second Embodiment] Figure 7 is a partially cutaway side view showing the aircraft engine mounting device of the second embodiment, Figure 8 is a cross-sectional view taken along line VII-VII in Figure 6 showing the aircraft engine mounting device, and Figure 9 is a schematic diagram showing the operating state of the aircraft engine mounting device. Note that components having the same function as those in the first embodiment described above are denoted by the same reference numerals, and detailed descriptions are omitted.

[0039] As shown in Figures 7 and 8, the aircraft engine mounting device 10A comprises a linear movement device 11, a first rocking device 12, and a second rocking device 13. The linear movement device 11 and the first rocking device 12 are substantially the same as those in the first embodiment.

[0040] The second rocking device 13 is provided on the traveling carriage 21 and supports the support frame 110 so that it can swing around a second axis O2 which is perpendicular to the first axis O1 and lies horizontally. Specifically, the second rocking device 13 is provided on the traveling carriage 21, the second rocking device 13 supports the first rocking device 12, the first rocking device 12 supports the linear movement device 11, and the linear movement device 11 supports the support frame 110. Note that the first axis O1 and the second axis O2 may be in the same vertical position or misaligned.

[0041] In other words, the trolley 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 have the same plate shape. Support member 31 is fixed to the upper surface of one side of the trolley 21 in the axial direction of the second axis O2, along a direction perpendicular to the axial direction of the second axis O2. Support member 32 is fixed to the upper surface of the other side of the trolley 21 in the axial direction of the second axis O2, along a direction perpendicular to the axial direction of the second axis O2. Support members 31 and 32 face each other in parallel, with a distance between them that is longer than the axial length of the support frame 110 in the second axis O2.

[0042] The second rocking device 13 includes a second rocking member 51 and a pair of second drive devices 52 and 53. The second rocking member 51 has a rectangular frame shape and is positioned vertically between the support member 31 and the support member 32. The second rocking member 51 has first members 51a and 51b positioned opposite 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 positioned on the support member 31 on the side opposite to the support member 32. The second drive device 53 is positioned on the support member 32 on the side opposite to the support member 31. The second drive device 52 is fixed to the support member 31, and its output shaft 52a, located at the second axis O2, passes through the support member 31 and is connected to the first member 51a of the second rocking member 51. The second drive unit 53 is fixed to the support member 32, and the output shaft 53a located at the second axis O2 passes through the support member 32 and is connected to the first member 51b of the second oscillating member 51.

[0043] Therefore, the second swinging member 51 is supported by the support members 31 and 32 so as to be able to swing (rotate) around the second axis O2, and is swingable (rotatable) by the second drive devices 52 and 53. Although a pair of second drive devices 52 and 53 are provided as the second swinging device 13, either one or the other may be used.

[0044] The first rocking device 12 includes a pair of first rocking members 33 and 34 and a pair of first drive devices 35 and 36. The first rocking member 33 is positioned on the side of the first member 51b of the first member 51a of the second rocking member 51. The first drive device 35 is positioned 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 its output shaft 35a, located at the first axis O1, passes through the first member 51a and is connected to the first rocking member 33. Therefore, the first rocking member 33 is supported on the first member 51a so as to be able to swing (rotate) around the first axis O1 and is able to swing (rotate) by the first drive device 35.

[0045] Furthermore, the first oscillating member 34 is positioned on the side of the first member 51a of the first member 51b of the second oscillating member 51. The first drive unit 36 ​​is positioned on the side of the first member 51b opposite to the first member 51a. The first drive unit 36 ​​is fixed to the first member 51b, and its output shaft 36a, located at the first axis O1, passes through the first member 51b and is connected to the first oscillating member 34. Therefore, the first oscillating member 34 is supported by the first member 51b so as to be able to swing (rotate) around the first axis O1 and is able to swing (rotate) by the first drive unit 36.

[0046] The linear movement device 11 includes guide rails 41 and 42, and drive devices 43 and 44.

[0047] When the second drive units 52 and 53 are driven synchronously by the second rocking device 13, the output shafts 52a and 53a rotate, causing the second rocking member 51 to rotate around the second axis O2. As a result, the support frame 110, which is supported by the second rocking member 51 via the first rocking device 12 and the linear movement device 11, rotates around the second axis O2. Therefore, the aircraft engine 105 supported by the support frame 110 is rocked, and the angle of the mounting portion 105a on the aircraft engine 105 with respect to the axial direction (direction of the rotation axis) can be adjusted.

[0048] As shown in Figure 9, the lower surface 102a of the main wing 102 of the aircraft 100 may be tilted vertically upward with a predetermined angle of inclination relative to the horizontal in the longitudinal direction. Therefore, when attaching the aircraft engine 105 to the main wing 102, it is necessary to tilt the aircraft engine 105 with respect to the horizontal (vertical) direction in the longitudinal direction of the rotation axis O (first axis O1).

[0049] In other words, the aircraft engine 105 is supported by a support frame 110, and the support frame 110 is supported by an aircraft engine mounting device 10A. First, the traveling carriage 21 is moved to move the aircraft engine 105, which is supported by the support frame 110, below its mounting position, that is, below the mounting member 131 fixed to the main wing 102, and then it is stopped.

[0050] Then, by activating the second rocking device 13 (see Figure 8), the support frame 110 is rocked by a predetermined inclination angle around the second axis O2. As a result, the aircraft engine 105 supported by the support frame 110 is positioned so that the mounting portion 105a faces the mounting member 131, and the upward direction of the mounting portion 105a coincides with the insertion direction into the mounting member 131. In this state, by activating the linear movement device 11 (see Figure 7), the support frame 110 is raised while maintaining the inclination angle of the support frame 110. As a result, the aircraft engine 105 supported by the support frame 110 is positioned correctly, with the mounting portion 105a properly fitted into the mounting member 131 of the main wing 102.

[0051] Subsequently, the aircraft engine 105 is fastened to the mounting member 131 at the mounting portion 105a, and the support from the support frame 110 is released. While this description focuses on the process of attaching the aircraft engine 105 to the main wing 102 using the aircraft engine mounting device 10A of this embodiment, the aircraft engine mounting device 10A can also be used to remove the aircraft engine 105 from the main wing 102.

[0052] [Third Embodiment] Figure 10 is a side view showing the mounting device for an aircraft engine according to the third embodiment. Components having the same function as those in the first embodiment described above are denoted by the same reference numerals, and detailed descriptions are omitted.

[0053] As shown in Figure 10, the aircraft engine mounting device 10B comprises a linear movement device 11, a first rocking device 12, and a second rocking device 13A. The linear movement device 11 and the first rocking device 12 are substantially the same as those in the first embodiment.

[0054] The second rocking device 13A is provided on the trolley 21 and supports the support frame 110 so that it can swing around a second axis O2 which is perpendicular to the first axis O1 and aligns horizontally. Specifically, the trolley 21 has four running wheels 22 mounted on its underside. Two running wheels 22 on one side of the first axis O1 (the left side in Figure 10) are mounted on the underside of the trolley 21 via a hydraulic cylinder 61 that constitutes the second rocking device 13A. The second rocking device 13A extends (or shortens) the hydraulic cylinder 61, tilting the trolley 21 and thereby supporting the support frame 110 so that it can swing around. In this case, the second axis O2 is the ground contact position of the running wheel 22 on the other side of the first axis O1 (the right side in Figure 10). Furthermore, the two running wheels 22 on the other side of the first axis O1 (the right side in Figure 10) may also be mounted on the underside of the running bogie 21 via the hydraulic cylinders that constitute the second rocking device 13A.

[0055] The operation of the aircraft engine mounting device 10B is the same as that of the aircraft engine mounting device 10A in the second embodiment, and therefore, a detailed explanation is omitted.

[0056] [Effects of this embodiment] The aircraft engine mounting device according to the first embodiment includes a linear movement device 11 that supports a support frame 110, on which the aircraft engine 105 is supported so as to be aligned horizontally, so as to be movable along a direction of movement perpendicular to the rotation axis O of the aircraft engine 105, and a first swing device 12 that supports the support frame 110 so as to be swingable about a first axis O1 parallel to the rotation axis O.

[0057] According to the first embodiment of the aircraft engine mounting device, even if the mounting angle of the aircraft engine 105 to the aircraft 100 is tilted in the left-right direction with respect to the vertical direction, the mounting angle of the aircraft engine 105 can be adjusted by swinging the support frame 110 on which the aircraft engine 105 is supported by the first swinging device 12, thereby improving workability in the attachment and detachment of the aircraft engine.

[0058] The aircraft engine mounting device according to the second embodiment is the aircraft engine mounting device according to the first embodiment, further comprising a traveling carriage 21, the traveling carriage 21 being provided with a first rocking device 12, the first rocking device 12 supporting a linear movement device 11, and the linear movement device 11 supporting a support frame 110. As a result, by moving the traveling carriage 21, the linear movement device 11, the first rocking device 12, and the support frame 110 can be moved to a desired position.

[0059] The aircraft engine mounting device according to the third embodiment is an aircraft engine mounting device according to the second embodiment, further comprising: a traveling carriage 21 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 oscillating members 33, 34 constituting the first oscillating device 12 being oscillatingly supported by the pair of support members 31, 32; and a linear movement device 11 movably supporting a support frame 110 with respect to the pair of first oscillating members 33, 34. This allows the linear movement device 11 and the first oscillating device 12 to be efficiently mounted on the traveling carriage 21.

[0060] The aircraft engine mounting device according to the fourth embodiment is an aircraft engine mounting device according to the second or third embodiment, further comprising a traveling carriage 21 having at least three steerable traveling wheels 22. This allows for easy adjustment of the position of the aircraft engine 105 relative to the engine mounting position.

[0061] The fifth embodiment of the aircraft engine mounting device is an aircraft engine mounting device according to any one of the first to fourth embodiments, and further includes second swinging devices 13, 13A that swing the support frame 110 about a second axis O2 which is perpendicular to the first axis O1 and lies along the horizontal direction. As a result, even if the mounting angle of the aircraft engine 105 relative to the aircraft 100 is tilted in the front-rear and left-right directions with respect to the vertical direction, the mounting angle of the aircraft engine 105 can be adjusted by swinging the support frame 110 on which the aircraft engine 105 is supported by the first swinging device 12 and the second swinging devices 13, 13A.

[0062] The sixth embodiment of the aircraft engine mounting device is the fifth embodiment of the aircraft engine mounting device, further comprising a traveling carriage 21, the traveling carriage 21 being provided with a second rocking device 13, the second rocking device 13 supporting a first rocking device 12, the first rocking device 12 supporting a linear movement device 11, and the linear movement device 11 supporting a support frame 110. As a result, by moving the traveling carriage 21, the linear movement device 11, the first rocking device 12, the second rocking device 13, and the support frame 110 can be moved to desired positions.

[0063] The aircraft engine mounting device according to the seventh embodiment is an aircraft engine mounting device according to the fifth or sixth embodiment, further comprising: a traveling carriage 21 provided with a pair of support members 31, 32 on one side and the other side in the direction of the second axis O2; a second rocking member 51 constituting the second rocking device 13 being pivotably supported by the pair of support members 31, 32; a pair of first rocking members 33, 34 constituting the first rocking device 12 being pivotably supported by the second rocking member 51; and a linear movement device 11 providing a support frame 110 that is movably supported by the pair of first rocking members 33, 34. This allows the linear movement device 11, the first rocking device 12, and the second rocking device 13 to be efficiently mounted on the traveling carriage 21.

[0064] The aircraft engine mounting device according to the eighth embodiment is the same as the aircraft engine mounting device according to the seventh embodiment, wherein the second rocking device 13A supports the support frame 110 so that it can swing freely by tilting the traveling carriage 21. This eliminates the need to modify the linear movement device 11 or the first rocking device 12, thereby simplifying the structure.

[0065] The method for mounting an aircraft engine according to the ninth embodiment includes the steps of: moving a support frame 110, which supports the aircraft engine 105 so as to be aligned horizontally, to below the engine mounting position; swinging the support frame 110 about a first axis O1 parallel to the rotation axis O of the aircraft engine 105 to move the aircraft engine 105 to a predetermined inclination angle; and moving the support frame 110 vertically upward along the inclination angle to position it at the engine mounting position. This makes it possible to adjust the mounting angle of the aircraft engine 105 even if the mounting angle of the aircraft engine 105 relative to the aircraft 100 is inclined with respect to the vertical, thereby improving workability in the installation and removal of the aircraft engine.

[0066] In the embodiment described above, the support frame 110 is semi-cylindrical in shape, but it is not limited to this shape; any shape is acceptable as long as it supports the aircraft engine 105.

[0067] Furthermore, although the second oscillating device is a hydraulic cylinder 61 in the embodiment described above, the first oscillating device may be a fluid pressure cylinder such as a hydraulic cylinder 61. Also, the first and second oscillating devices are not limited to fluid pressure cylinders, but may be screw devices or the like. [Explanation of symbols]

[0068] 10, 10A, 10B Aircraft engine mounting device 11 Linear movement device 12 First rocking device 13,13A Second rocking device 21. Running bogie 22 running wheels 31,32 Support members 33,34 First rocking member 35,36 First drive unit 41,42 Guide rails 43,44 Drive unit 51 Second rocking member 52, 53 Second drive unit 61 Hydraulic Cylinder 100 aircraft 101 Torso 102 Main wing 103 Horizontal stabilizer 104 Vertical stabilizer 105 aircraft engine 110 Support Frame

Claims

1. A linear movement device that supports a support frame, which supports an aircraft engine so as to be aligned horizontally, so as to be movable along a direction of movement perpendicular to the rotation axis of the aircraft engine, A first rocking device that supports the support frame so as to be able to swing about a first axis parallel to the rotation axis, Equipped with, The linear movement device has a pair of moving drive devices connected to both ends of the rotation axis in the support frame, The first rocking device has a pair of rocking drive devices connected to both ends of the rotation axis in the support frame. A mounting device for aircraft engines.

2. The device has a trolley, the trolley is provided with the first rocking device, the first rocking device supports the linear movement device, and the linear movement device supports the support frame. The mounting device for an aircraft engine according to claim 1.

3. The traveling carriage is provided with a pair of support members on one side and the other side in the direction of the first axis, and a pair of first oscillating members constituting the first oscillating device are movably supported by the pair of support members, and the linear movement device movably supports the support frame with respect to the pair of first oscillating members. The mounting device for an aircraft engine according to claim 2.

4. The aforementioned trolley has at least three steerable wheels. The mounting device for an aircraft engine according to claim 2 or claim 3.

5. The support frame has a second rocking device that supports it so as to be able to swing about a second axis that is perpendicular to the first axis and lies horizontally. The mounting device for an aircraft engine according to claim 1.

6. The device has a traveling carriage, the traveling carriage is provided with the second rocking device, the second rocking device supports the first rocking device, the first rocking device supports the linear movement device, and the linear movement device supports the support frame. The mounting device for an aircraft engine according to claim 5.

7. The traveling carriage is provided with a pair of support members on one side and the other side in the direction of the second axis, the second rocking member constituting the second rocking device is pivotably supported by the pair of support members, the pair of first rocking members constituting the first rocking device is pivotably supported by the second rocking member, and the linear movement device supports the support frame so as to be movable relative to the pair of first rocking members. The mounting device for an aircraft engine according to claim 6.

8. The second rocking device supports the support frame so that it can swing freely by tilting the traveling carriage. The mounting device for an aircraft engine according to claim 6 or claim 7.

9. A step of moving a support frame that supports the aircraft engine so that it is aligned horizontally to below the engine mounting position, A step of supporting both ends of the rotation axis of the aircraft engine in the support frame and swinging it about a first axis parallel to the rotation axis to move the aircraft engine to a predetermined inclination angle, A step of supporting both ends of the rotation axis in the support frame and moving it vertically upward along the inclination angle to position it at the engine mounting position, A method for mounting an aircraft engine having [a specific feature / feature].

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