Aircraft auxiliary power system mounting rack

Abstract

The invention discloses an aircraft auxiliary power system mounting rack which comprises a rack body and a hoisting mechanism mounted on the rack body through a triaxial movement mechanism, the triaxial movement mechanism can move along three axial directions in an O-xyz space rectangular coordinate system, and the hoisting mechanism comprises a turntable, a locking mechanism and three groups of hoisting tools; wherein the turntable is rotatably mounted on the triaxial movement mechanism, and the rotating axis of the turntable is vertical; the locking mechanism has a locking state and an unlocking state and is arranged between the rotating disc and the first lead screw so that the rotating disc can be limited to rotate around the rotating axis of the rotating disc in the locking state. The three groups of lifting appliances are arranged on the turntable around the rotating axis, and the upper end of each group of lifting appliances is in threaded connection with the turntable, so that the heights of the three groups of lifting appliances are independently adjustable; according to the aircraft auxiliary power system mounting frame, adjustment of six degrees of freedom including heading movement, transverse movement, up-down movement, pitching, deflection and rotation of an aircraft auxiliary power system can be achieved, the structure is small and light, and operation is convenient and reliable.

Description

Technical Field

[0001] The invention relates to the field of aircraft maintenance equipment, 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] At present, there are two main ways to disassemble and assemble the APU: jacking and hoisting. In some common APU hoisting structures, the upper ends of three sets of hoisting ropes are connected to the hoisting rods 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, in order to facilitate 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. In the actual disassembly and assembly process, it is easy to affect the normal progress of the aircraft ground maintenance work. Summary of the invention

[0004] The purpose of the present invention is to overcome the disadvantages 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 implemented by the following technical solutions:

[0006] An aircraft auxiliary power system mounting frame comprises a frame body and a hoisting 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 space rectangular coordinate system, and the hoisting mechanism comprises:

[0007] A turntable, which is rotatably mounted on the three-axial motion mechanism, and the rotation axis is vertical;

[0008] A locking mechanism having a locked state and an unlocked state, wherein the locking mechanism is disposed between the rotating disk and the first screw rod so as to limit the rotating disk from rotating around 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] Further, the three-axis motion mechanism includes a vertical displacement assembly, and the vertical displacement assembly includes a group of vertically arranged first screw rods, and the lower ends of the first screw rods are connected to the rotating disk;

[0011] The outer wall of the first screw rod is provided with an axially extending limit groove, and the vertical displacement assembly is provided with a nut threadedly connected to the first screw rod and a limit piece matched with the limit 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 rotating disk, and the lower end of the first screw rod is connected to the rotating parts;

[0013] The locking mechanism comprises a group of push rods movably arranged on the rotating disk, and the moving direction of the push rods points to the rotating member, so as to lock the rotating disk through the contact between 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 arranged at intervals on the outer peripheral side 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 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.

[0017] Further, the heading translation assembly includes a first frame that can be horizontally slidably arranged on the frame body, a third screw rod axially parallel to the sliding direction of the first frame is screwed on 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 its axial direction is parallel to the sliding direction of the second frame, and 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 moving ranges of the heading translation assembly and the lateral translation assembly do 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 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.

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

[0022] The technical solution of the embodiment of the present invention has 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 hoisting mechanism are integrated in the frame body, and the hoisting mechanism can realize the heading and lateral free motion in the horizontal direction and the lifting and lowering motion in the vertical direction through the three-axial motion mechanism;

[0024] In addition, through the rotational connection between the turntable and the three-axis 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 hoists on the turntable can perform three-point lifting of the aircraft auxiliary power system. The three sets of hoists can be raised and lowered independently. By operating the lifting of different hoists, 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 in an embodiment of the present invention;

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

[0029] Figure 3 It is a partial enlarged view of the heading translation assembly and the lateral translation assembly in the 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 section 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] Fig. 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-leg, 12-foot cup, 13-brace, 130-quick release pin, 2-lifting mechanism, 20-turntable, 21-lifting device, 210-second screw rod, 2100-second rotating wheel, 2101-connector, 211-sling, 212-second locking nut, 22-rotating member, 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] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are 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 here can be arranged and designed in various different configurations.

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

[0039] Reference Figures 1 to 8 The aircraft auxiliary power system mounting frame includes a frame body 1, on which a three-axial motion mechanism 3 is arranged, and a hoisting 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, and the three-axial motion mechanism 3 can drive the hoisting mechanism 2 to move in space within a certain range, so as to facilitate the hoisting operation of the aircraft auxiliary power system by the hoisting mechanism 2.

[0040] It is easy to understand that the three-axial motion mechanism 3 is similar to a three-dimensional displacement slide commonly seen in mechanical structures, which has a guide structure for the aforementioned three axial motions and a power for driving the aforementioned three axial displacements, wherein the power can be hydraulically or pneumatically transmitted. When more precise control of the displacement is required, the power can be a manual 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 top frame 10 in a square shape, 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 an aircraft, it can play an anti-slip role and avoid scratches on the aircraft body.

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

[0043] In addition, refer to Figure 1 In a preferred embodiment, the four groups of legs 11 are each 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 to be quickly connected to 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 spatial 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 arranged on two opposite sets of frame frames on the top frame 10, and four sets of second sliders 3000 are arranged 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, and the first frame 300 can smoothly reciprocate along the heading through the cooperation and guidance of the first guide rails 101 and the second sliders 3000. 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, and 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 on 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 arranged 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 a fourth screw rod 312 axially parallel to the sliding direction of the second frame 310 is screwed to the threaded seat on the first frame 300, 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 rods 320 and the second frame 310 are provided with a first locking nut 322, the first locking nut 322 is rotatably supported and fixed on the second frame 310 through a bearing, and the first locking nut 322 is provided with a first rotating wheel 321, the upper end of the first screw rod 320 is penetrated and threadedly connected to the first locking nut 322; in addition, the outer wall of the first screw rod 320 has an axially extending limit groove 3200, and the second frame 310 has a limit member that cooperates with the limit groove 3200, and the first locking nut 322 is driven to rotate by screwing the first rotating wheel 321, so that 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 pluggable 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 plug, the first screw rod 320 can be removed from the three-axial motion mechanism 3.

[0051] In this embodiment, the moving ranges of the heading translation assembly 30 and the lateral translation assembly 31 do not exceed the rectangular area surrounded 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, and the rotating parts 22 include two parts that are rotatably connected. The first part of the rotating part 22 is locked with the turntable 20 by a fastener, and the second part is connected with 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 arranged at the three vertices of its outline, which can be used to 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 abutting against the second part of the rotating member 22, 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 arranged on the outer peripheral side 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 hanger 21 includes a vertically arranged second screw rod 210, and the turntable 20 is provided with a second locking nut 212 threadedly connected to the second screw rod 210. Consistent with the principle of the first locking nut 322, the second locking nut 212 is rotatably connected to the turntable 20, and the second locking nut 212 is provided with a second rotating wheel 2100, the second screw rod 210 is provided with an axially extending limiting groove, and the turntable 20 is provided with a limiting mechanism corresponding to the limiting groove, and the second screw rod 210 can be raised and lowered without rotation by rotating the second rotating wheel 2100.

[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 part of the aircraft auxiliary power system through a corresponding hook structure.

[0062] In one embodiment, referring to Fig. 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 rotation directions of the two ends of one group of bidirectional screw rods 26 are opposite, 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 with a group of first sliders 25. By screwing the bidirectional screw rods 26, the spacing of 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 only preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An aircraft auxiliary power system mounting bracket, characterized in that: It includes a frame and a hanging mechanism installed on the frame through a three-axial motion mechanism, wherein the three-axial motion mechanism can move along three axes in an O-xyz space rectangular coordinate system, and the hanging mechanism includes: A turntable, which is rotatably mounted on the three-axial motion mechanism, and the rotation axis is vertical; A locking mechanism having a locked state and an unlocked state, wherein the locking mechanism is disposed between the rotating disk and the first screw rod so as to limit the rotating disk from rotating around its own rotation axis in the locked state; and 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.

2. The aircraft auxiliary power system mounting bracket according to claim 1, characterized in that: The three-axis motion mechanism includes a vertical displacement assembly, and the vertical displacement assembly includes a group of vertically arranged first screw rods, and the lower ends of the first screw rods are connected to the rotating disk; The outer wall of the first screw rod is provided with an axially extending limit groove, and the vertical displacement assembly is provided with a nut threadedly connected to the first screw rod and a limit piece matched with the limit groove, so that the first screw rod can be raised and lowered without self-rotation by screwing the nut.

3. The aircraft auxiliary power system mounting bracket according to claim 2, characterized in that: A group of rotating parts is provided in the middle of the rotating disk, and the lower end of the first screw rod is connected to the rotating parts; The locking mechanism comprises a group of push rods movably arranged on the rotating disk, and the moving direction of the push rods points to the rotating member, so as to lock the rotating disk through the contact between the rotating member and the push rods.

4. The aircraft auxiliary power system mounting bracket according to claim 3, characterized in that: The push rod is screwed on the rotating disk, and a plurality of insertion holes for inserting the push rod are evenly arranged at intervals on the outer peripheral side of the rotating member.

5. The aircraft auxiliary power system mounting bracket according to claim 1, characterized in that: The sling includes a second vertically arranged 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.

6. The aircraft auxiliary power system mounting bracket according to claim 2, characterized in that: The three-axis motion mechanism comprises a heading translation assembly arranged on the frame, a lateral translation assembly is arranged on the heading translation assembly, and the vertical displacement assembly is arranged on the lateral translation assembly.

7. The aircraft auxiliary power system mounting bracket according to claim 6, characterized in that: The heading translation assembly comprises a first frame which is horizontally slidably arranged on the frame body, a third screw rod which is axially parallel to the sliding direction of the first frame is screwed on 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; 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 its axial direction is parallel to the sliding direction of the second frame, and one end of the fourth screw rod is rotatably connected to the second frame to control the sliding position of the second frame.

8. The aircraft auxiliary power system mounting bracket according to claim 6, characterized in that: A plurality of legs are arranged at the lower end of the frame 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.

9. The aircraft auxiliary power system mounting bracket according to claim 8, 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.

10. The aircraft auxiliary power system mounting bracket according to claim 1, characterized in that: Among the three groups of slings, two groups of slings are adjustable in distance from each other and are arranged on the turntable.

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