Aircraft auxiliary power system mounting bracket

Abstract

The present invention discloses an aircraft auxiliary power system mounting frame, comprising a frame body and a lifting mechanism mounted on the frame body through a three-axial motion mechanism, wherein the three-axial motion mechanism can move along three axes in an O-xyz spatial rectangular coordinate system, and the lifting mechanism comprises a turntable, a locking mechanism and three sets of lifting devices; wherein the turntable is rotatably mounted on the three-axial motion mechanism, and the rotation axis is vertical; the locking mechanism has a locking and an unlocking state, and is arranged between the turntable and a first screw rod, so as to limit the turntable from rotating around its own rotation axis when in the locked state; the three sets of lifting devices are arranged on the turntable around the rotation axis, and the upper end of each set of lifting devices is screwed to the turntable, so that the heights of the three sets of lifting devices can be independently adjusted; the aircraft auxiliary power system mounting frame of the present invention can realize the adjustment of a total of six degrees of freedom of the aircraft auxiliary power system, namely, heading movement, lateral movement, up and down movement, pitch, yaw and rotation, with a small and lightweight structure, and convenient and reliable operation.

Description

Technical Field

[0001] The present invention relates to the field of aircraft maintenance equipment, and in particular to an aircraft auxiliary power system mounting bracket. Background Art

[0002] The aircraft auxiliary power system (APU) is an independent power source installed on various types of aircraft. It is used to provide starting power to the aircraft engine and power supply to the interior of the aircraft. The aircraft auxiliary power unit needs to be disassembled and maintained regularly.

[0003] Currently, there are two main methods for disassembling and assembling an APU: jacking and hoisting. In some common APU hoisting structures, the upper ends of three sets of hoisting ropes are connected to the boom and the lower ends are directly hooked on the APU. The hoisting structure is bulky and simple in function. During the APU disassembly and assembly process, for ease of operation, it is sometimes necessary to fine-tune the position, rotation, and pitch angle of the APU. Obviously, the above hoisting structure cannot meet such requirements, and the actual disassembly and assembly process is likely to affect the normal progress of the aircraft's ground maintenance work. Summary of the Invention

[0004] The purpose of the present invention is to overcome the shortcomings of the background technology and provide an aircraft auxiliary power system mounting bracket which has a light structure and is easy to operate.

[0005] The embodiments of the present invention are achieved through the following technical solutions:

[0006] An aircraft auxiliary power system mounting frame includes a frame body and a hoisting mechanism mounted on the frame body via a three-axial motion mechanism, wherein the three-axial motion mechanism is capable of moving along three axes in an O-xyz spatial rectangular coordinate system, and the hoisting mechanism includes:

[0007] a turntable rotatably mounted on the three-axial motion mechanism, with its rotation axis vertical;

[0008] a locking mechanism having locked and unlocked states, the locking mechanism being disposed between the turntable and the first screw rod so as to restrict the turntable from rotating about its own rotation axis in the locked state; and

[0009] Three groups of slings are arranged on the turntable around the rotation axis, and the upper end of each group of slings is screwed to the turntable, so that the heights of the three groups of slings are independently adjustable.

[0010] Furthermore, the three-axial motion mechanism includes a vertical displacement assembly, and the vertical displacement assembly includes a set of vertically arranged first screw rods, the lower ends of the first screw rods are connected to the turntable;

[0011] An axially extending limiting groove is provided on the outer wall of the first screw rod, and the vertical displacement assembly comprises a nut threadedly connected to the first screw rod and a limiting member cooperating with the limiting groove, so that the first screw rod can be raised and lowered without self-rotation by screwing the nut.

[0012] Furthermore, a group of rotating parts is provided in the middle of the turntable, and the lower end of the first screw rod is connected to the rotating parts;

[0013] The locking mechanism includes a set of push rods movably arranged on the turntable, and the moving direction of the push rods points to the rotating member, so that the turntable is locked by the rotating member and the push rods.

[0014] Furthermore, the push rod is screwed onto the turntable, and a plurality of insertion holes for inserting the push rod are evenly spaced on the outer circumference of the rotating member.

[0015] Furthermore, the sling includes a vertically arranged second screw rod, and the turntable is provided with a second locking nut threadedly connected to the second screw rod, so that the lifting and lowering of the second screw rod can be controlled by screwing the second locking nut; the lower end of the second screw rod is provided with a sling for connecting to the aircraft auxiliary power system.

[0016] Furthermore, the three-axis motion mechanism includes a heading translation component provided on the frame, a lateral translation component is provided on the heading translation component, and the vertical displacement component is provided on the lateral translation component.

[0017] Furthermore, the panning translation assembly includes a first frame that is horizontally slidably arranged on the frame body, a third screw rod axially parallel to the sliding direction of the first frame is screwed onto the frame body, and one end of the third screw rod is rotatably connected to the first frame to control the sliding position of the first frame;

[0018] The lateral translation assembly includes a second frame that can be horizontally slidably arranged in the first frame, and the sliding direction of the second frame is perpendicular to the sliding direction of the first frame; a fourth screw rod is screwed on the first frame, and the axial direction is parallel to the sliding direction of the second frame. One end of the fourth screw rod is rotatably connected to the second frame to control the sliding position of the second frame.

[0019] Furthermore, a plurality of legs are provided at the lower end of the frame so as to be supported on the frame beam of the aircraft, and the movement range of the heading translation assembly and the lateral translation assembly does not exceed the area surrounded by the plurality of legs.

[0020] Furthermore, four groups of legs are hinged at the lower end of the frame, and a diagonal brace is detachably connected between the upper side of each group of legs and the frame, so that the legs can be folded after the diagonal brace is removed.

[0021] Furthermore, among the three groups of spreaders, the spacing between two groups of spreaders is adjustably arranged on the turntable.

[0022] The technical solutions of the embodiments of the present invention have at least the following advantages and beneficial effects:

[0023] In the aircraft auxiliary power system mounting frame of the present invention, a three-axial motion mechanism and a lifting mechanism are integrated in the frame body, and the three-axial motion mechanism can realize the heading and lateral free movement of the lifting mechanism in the horizontal direction and the lifting movement in the vertical direction;

[0024] In addition, through the rotation connection between the turntable and the three-axial motion mechanism, the rotation adjustment of the lifting mechanism can be achieved and can be locked by the locking mechanism;

[0025] In addition, the three sets of lifting devices on the turntable can perform three-point lifting of the aircraft auxiliary power system. The three sets of lifting devices can be raised and lowered independently. By operating the lifting and lowering of different lifting devices, the pitch and roll adjustment of the aircraft auxiliary power system can be achieved;

[0026] In summary, the above-mentioned mounting frame can realize the adjustment of a total of 6 degrees of freedom of the aircraft auxiliary power system, including heading movement, lateral movement, up and down movement, pitch, yaw and rotation. The above-mentioned 6-degree-of-freedom adjustment structures are all integrated in a set of frames, which has a small and lightweight structure and is easy and reliable to operate. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 is a front view of an aircraft auxiliary power system mounting bracket according to an embodiment of the present invention;

[0028] Figure 2 is a top view of an aircraft auxiliary power system mounting bracket according to an embodiment of the present invention;

[0029] Figure 3 A partially enlarged view of the heading translation assembly and the lateral translation assembly in an embodiment of the present invention;

[0030] Figure 4 The structure of the lifting mechanism in the embodiment of the present invention is shown in FIG. Figure 1 ;

[0031] Figure 5 The structure of the lifting mechanism in the embodiment of the present invention is shown in FIG. Figure 2 ;

[0032] Figure 6 for Figure 4 EE cross-sectional view in;

[0033] Figure 7 for Figure 5 The CC section view in the figure;

[0034] Figure 8 is a top view of a hoisting mechanism in one embodiment of the present invention;

[0035] Figure 9 is a top view of a hoisting mechanism in yet another embodiment of the present invention;

[0036] Icons: 1-frame, 10-top frame, 100-connecting seat, 101-first guide rail, 102-lifting ring, 11-support leg, 12-foot cup, 13-bracing piece, 130-quick release pin, 2-lifting mechanism, 20-turntable, 21-sling, 210-second screw rod, 2100-second rotating wheel, 2101-connector, 211-sling, 212-second locking nut, 22-rotating part, 23-slide, 24-locking mechanism, 240-top rod , 25-first slider, 26-bidirectional screw, 3-three-axial motion mechanism, 30-heading translation assembly, 300-first frame, 3000-second slider, 301-third screw, 31-lateral translation assembly, 310-second frame, 311-second guide rail, 312-fourth screw, 32-vertical displacement assembly, 320-first screw, 3200-limiting groove, 3201-connecting pin, 321-first rotating wheel, 322-first locking nut. DETAILED DESCRIPTION

[0037] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings herein can be arranged and designed in various different configurations.

[0038] The invention provides an aircraft auxiliary power system mounting rack, which is used for disassembly, assembly and maintenance of an aircraft auxiliary power system (APU).

[0039] Reference Figures 1 to 8 The aircraft auxiliary power system mounting frame includes a frame body 1, a three-axial motion mechanism 3 is provided on the frame body 1, and a lifting mechanism 2 is installed on the three-axial motion mechanism 3, wherein the so-called three-axial motion mechanism 3 refers to a mechanism that can move along the three axes of x-axis, y-axis and z-axis in the O-xyz space rectangular coordinate system. The three-axial motion mechanism 3 can drive the lifting mechanism 2 to move in space within a certain range, which is convenient for the lifting operation of the aircraft auxiliary power system by the lifting mechanism 2.

[0040] It is easy to understand that the three-axial motion mechanism 3 is similar to the three-dimensional displacement slide commonly seen in mechanical structures. The three-dimensional displacement slide has a guide structure for the aforementioned three axial motions and a power to drive the aforementioned three axial displacements. The power can be hydraulically or pneumatically transmitted. When more precise control of the displacement is required, the power can be a manually or electrically driven screw transmission structure, etc.

[0041] Reference Figures 1 to 3 In order to reduce the overall weight of the aircraft auxiliary power system mounting frame, the frame 1 can be partially made of aluminum alloy. In this embodiment, the frame 1 includes a square-shaped top frame 10, and the lower ends of the four groups of top corners of the top frame 10 are respectively provided with a group of connecting seats 100 made of aluminum alloy. The lower ends of each group of connecting seats 100 are respectively provided with a group of supporting legs 11 made of aluminum alloy profiles. The lower ends of the supporting legs 11 are provided with foot cups 12, and the bottom of the foot cups 12 is a rubber layer. When the frame 10 is placed on the aircraft, it can play an anti-slip role and avoid scratches on the aircraft body.

[0042] Among them, reference Figure 2 The top frame 10 is provided with three sets of lifting rings 102 , which can be used as lifting points for external equipment such as a crane, so as to conveniently place the top frame 10 on the aircraft.

[0043] In addition, refer to Figure 1 In a preferred embodiment, each of the four groups of legs 11 is hinged to a group of connecting seats 100, so that each group of legs 11 can be folded, wherein a diagonal support member 13 is connected between the upper side of each group of legs 11 and the top frame 10, and quick-release pins 130 are provided at both ends of the diagonal support member 13 for quick-release connection with the legs 11 and the top frame 10 respectively; after at least one end of the diagonal support member 13 is removed, the four groups of legs 11 can be folded, reducing the overall volume and floor space of the frame 1, and facilitating transfer and transportation.

[0044] For the three-axial motion mechanism 3, refer to Figures 1 to 3 In this embodiment, the three-axis motion mechanism 3 includes a heading translation component 30 arranged on the top frame 10, a lateral translation component 31 is provided on the heading translation component 30, and a vertical displacement component 32 is provided on the lateral translation component 31. In the O-xyz space rectangular coordinate system, the heading translation component 30 can move back and forth in the x-direction in the horizontal plane, the lateral translation component 31 can move back and forth in the y-axis direction in the horizontal plane, and the vertical displacement component 32 can move up and down in the z-axis direction in the vertical plane.

[0045] Specifically, refer to Figures 1 to 3The heading translation assembly 30 includes a first frame 300 that can be horizontally slidably arranged on the top frame 10, that is, first guide rails 101 are provided on two opposite sets of frames on the top frame 10, and four sets of second sliders 3000 are provided at the lower end of the first frame 300, that is, two sets of second sliders 3000 are slidably connected to each set of first guide rails 101. Through the cooperation and guidance of the first guide rails 101 and the second sliders 3000, the first frame 300 can slide back and forth smoothly along the heading. In addition, a third screw rod 301 is screwed on the top frame 10, and the axial direction of the third screw rod 301 is parallel to the sliding direction of the first frame 300, that is, the axial direction of the third screw rod 301 is the heading direction; one end of the first screw rod 301 is rotatably connected to the threaded seat on the top frame 10, and the other end of the third screw rod 301 is rotatably connected to the first frame 300, the sliding position of the first frame 300 can be controlled by extending / retracting the third screw rod 301, and the first frame 300 can be locked at any position in the heading.

[0046] Reference Figure 2 A rotating wheel is provided at the end of the third screw rod 301 to facilitate the control of the rotation of the third screw rod 301.

[0047] Reference Figure 3 The lateral translation assembly 31 includes a second frame 310 that can be horizontally slidably arranged in the first frame 300, that is, a second guide rail 311 extending laterally is provided in the first frame 300, and the second frame 310 is slidably arranged on the second guide rail 311, so that the sliding direction of the second frame 310 is perpendicular to the sliding direction of the first frame 300, wherein the threaded seat on the first frame 300 is screwed with a fourth screw rod 312 axially parallel to the sliding direction of the second frame 310, and one end of the fourth screw rod 312 is rotatably connected to the second frame 310 to control the sliding position of the second frame 310, and the second frame 310 can be locked at any position in the lateral direction.

[0048] Reference Figure 3 A rotating wheel is provided at the end of the fourth screw rod 312 to facilitate the control of the rotation of the fourth screw rod 312.

[0049] Reference Figures 1 to 4The vertical displacement assembly 32 includes a group of vertically arranged first screw rods 320, the first screw rod 320, and a first locking nut 322 are provided on the second frame 310. The first locking nut 322 is rotatably supported and fixed on the second frame 310 through a bearing, and a first rotating wheel 321 is provided on the first locking nut 322. The upper end of the first screw rod 320 is passed through and threadedly connected to the first locking nut 322; in addition, an axially extending limiting groove 3200 is provided on the outer wall of the first screw rod 320, and a limiting member cooperating with the limiting groove 3200 is provided in the second frame 310. By screwing the first rotating wheel 321 to drive the first locking nut 322 to rotate, the first screw rod 320 can be raised and lowered without self-rotation.

[0050] In addition, the upper end of the first screw rod 320 extends beyond the first locking nut 322, and a plug-in pin is provided at the top of the first screw rod 320 to limit the downward movement of the first screw rod 320. After removing the pin, the first screw rod 320 can be removed from the three-axial motion mechanism 3.

[0051] In this embodiment, the movement range of the heading translation assembly 30 and the lateral translation assembly 31 does not exceed the rectangular area formed by the four groups of legs 11, thereby ensuring the safety of the lifting operation.

[0052] Reference Figure 1 The lower end of the first screw rod 320 is connected to the lifting mechanism 2.

[0053] Reference Figures 4 to 8 The hoisting mechanism 2 in this embodiment includes a turntable 20, three sets of hoists 21 and a retracting mechanism 24.

[0054] Specifically, refer to Figure 6 A group of rotating parts 22 are rotatably provided on the turntable 20. The rotating parts 22 include two parts that are rotatably connected. The first part of the rotating part 22 is locked to the turntable 20 by a fastener, and the second part is connected to the first screw rod 320. Specifically, a connecting pin 3201 is provided at the lower end of the first screw rod 320 and is passed through the second part of the rotating part 22, that is, the turntable 20 can rotate around the axis of the first screw rod 320.

[0055] Reference Figure 8 The turntable 20 is in a triangular star shape, and a set of hoists 21 are respectively provided at the three vertices of its outline, which can lift the aircraft auxiliary power system at three points.

[0056] In addition, refer to Figure 6 and Figure 8 A locking mechanism 24 is provided on the turntable 20. The locking mechanism 24 has a locked state and an unlocked state. The locking mechanism 24 acts between the turntable 20 and the first screw rod 320 to limit the turntable 20 from rotating around its own rotation axis in the locked state.

[0057] Specifically, the locking mechanism 24 includes a group of top rods 240 movably arranged on the turntable 20. In this embodiment, the top rods 240 are screwed into a group of threaded seats on the turntable 20. The moving direction of the top rods 240 points to the second part of the rotating member 22. By the top rods 240 and the second part of the rotating member 22 being offset, the turntable 20 can be locked so that the turntable 20 cannot rotate.

[0058] In addition, in a preferred embodiment, a plurality of insertion holes for inserting the push rods 240 are evenly spaced apart on the outer circumference of the second portion of the rotating member 22 , so as to form a more secure locking for the turntable 20 .

[0059] Reference Figures 4 to 7 , three groups of slings 21 are arranged on the turntable 20 around the rotation axis of the turntable 20; in addition, the upper end of each group of slings 21 is screwed to the turntable 20, so that the heights of the three groups of slings 21 can be adjusted independently, thereby realizing the pitch and roll adjustment of the aircraft auxiliary power system.

[0060] Furthermore, the sling 21 includes a vertically arranged second screw rod 210, and a second locking nut 212 threadedly connected to the second screw rod 210 is provided on the turntable 20. Consistent with the principle of the first locking nut 322, the second locking nut 212 is rotationally connected to the turntable 20, and a second rotating wheel 2100 is provided on the second locking nut 212, and an axially extending limiting groove is provided on the second screw rod 210, and a limiting mechanism corresponding to the limiting groove is provided on the turntable 20. By rotating the second rotating wheel 2100, the second screw rod 210 can be raised and lowered without rotation.

[0061] In addition, the lower end of the second screw rod 210 is connected to a sling 211 through a connector 2101 , and the lower end of the sling 211 can be fixed to a connection portion of the aircraft auxiliary power system through a corresponding hook structure.

[0062] In one embodiment, referring to Figure 9 In order to better adapt to the hoisting of aircraft auxiliary power systems of different sizes, among the three groups of hoists 21, the spacing of two groups of hoists 21 is adjustably set on the turntable 20, that is, a slide groove 23 is set on the turntable 20, and two groups of first sliders 25 are set in the slide groove 23. The second locking nuts 212 in each group of hoists 21 are rotatably set on a group of first sliders 25; the thread threads at both ends of one group of bidirectional screw rods 26 have opposite rotation directions, the bidirectional screw rods 26 are rotatably set on the turntable 20, and the two ends of the bidirectional screw rods 26 are respectively threadedly connected to a group of first sliders 25. By screwing the bidirectional screw rods 26, the spacing between the two groups of first sliders 25 can be controlled, thereby realizing the adjustment of the spacing between the two groups of hoists 21.

[0063] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention.

Claims

1. An aircraft auxiliary power system mounting bracket, characterized in that: The invention comprises a frame and a lifting mechanism mounted on the frame via a three-axial motion mechanism, wherein the three-axial motion mechanism is capable of moving along three axes in an O-xyz space rectangular coordinate system, and the lifting mechanism comprises: a turntable rotatably mounted on the three-axial motion mechanism, with its rotation axis vertical; The triaxial motion mechanism includes a vertical displacement assembly, which includes a set of vertically arranged first screw rods, the lower ends of which are connected to the turntable; the outer walls of the first screw rods have axially extending limit grooves, and the vertical displacement assembly includes a nut threadedly connected to the first screw rods and a limit member cooperating with the limit grooves, so that the first screw rods can be raised and lowered without self-rotation by screwing the nut; a locking mechanism having locked and unlocked states, the locking mechanism being disposed between the turntable and the first screw rod so as to restrict the turntable from rotating about its own rotation axis in the locked state; and Three groups of spreaders are arranged on the turntable around the rotation axis, and the upper end of each group of spreaders is screwed to the turntable so that the heights of the three groups of spreaders are independently adjustable; The sling includes a second vertically arranged screw rod, a second locking nut threadedly connected to the second screw rod is provided on the turntable; the second locking nut is rotatably connected to the turntable, and a second rotating wheel is provided on the second locking nut, an axially extending limiting groove is provided on the second screw rod, and a limiting mechanism corresponding to the limiting groove is provided on the turntable, and the second screw rod can be raised and lowered without rotating by rotating the second rotating wheel; A set of rotating parts is provided in the middle of the turntable, and the lower end of the first screw rod is connected to the rotating parts; the locking mechanism includes a set of push rods movably provided on the turntable, and the moving direction of the push rods points to the rotating parts, so that the turntable is locked by the rotation parts and the push rods. The sling includes a vertically arranged second screw rod, and the turntable is provided with a second locking nut threadedly connected to the second screw rod, so that the lifting and lowering of the second screw rod can be controlled by screwing the second locking nut; the lower end of the second screw rod is provided with a sling for connecting to the aircraft auxiliary power system.

2. The aircraft auxiliary power system mounting bracket according to claim 1, characterized in that: The push rod is screwed onto the turntable, and a plurality of insertion holes for inserting the push rod are evenly arranged at intervals on the outer circumference of the rotating member.

3. The aircraft auxiliary power system mounting bracket according to claim 1, characterized in that: The three-axis motion mechanism includes a heading translation component arranged on the frame, a lateral translation component is arranged on the heading translation component, and the vertical displacement component is arranged on the lateral translation component.

4. The aircraft auxiliary power system mounting bracket according to claim 3, characterized in that: The panning translation assembly includes a first frame that is horizontally slidably disposed on the frame body, a third screw rod having an axial direction parallel to the sliding direction of the first frame being screwed onto the frame body, and one end of the third screw rod being rotatably connected to the first frame to control the sliding position of the first frame; The lateral translation assembly includes a second frame that can be horizontally slidably arranged in the first frame, and the sliding direction of the second frame is perpendicular to the sliding direction of the first frame; a fourth screw rod is screwed on the first frame, and the axial direction is parallel to the sliding direction of the second frame. One end of the fourth screw rod is rotatably connected to the second frame to control the sliding position of the second frame.

5. The aircraft auxiliary power system mounting bracket according to claim 3, characterized in that: The lower end of the frame is provided with a plurality of legs so as to be supported on the frame beam of the aircraft, and the moving ranges of the heading translation assembly and the lateral translation assembly do not exceed the area surrounded by the plurality of legs.

6. The aircraft auxiliary power system mounting bracket according to claim 5, characterized in that: Four groups of legs are hinged at the lower end of the frame, and an oblique support piece is detachably connected between the upper side of each group of legs and the frame, so that the legs can be folded after the oblique support piece is removed.

7. The aircraft auxiliary power system mounting bracket according to claim 1, characterized in that: Among the three groups of spreaders, the spacing between the spreaders of two groups is adjustable and arranged on the turntable.

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