CN114684384B - Installation device and installation method of aircraft engine - Google Patents
Installation device and installation method of aircraft engine Download PDFInfo
- Publication number
- CN114684384B CN114684384B CN202011559344.8A CN202011559344A CN114684384B CN 114684384 B CN114684384 B CN 114684384B CN 202011559344 A CN202011559344 A CN 202011559344A CN 114684384 B CN114684384 B CN 114684384B
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- engine
- sliding table
- flexible cable
- aircraft engine
- winding
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- 238000009434 installation Methods 0.000 title claims abstract description 23
- 238000000034 method Methods 0.000 title claims abstract description 8
- 238000004804 winding Methods 0.000 claims abstract description 37
- 238000011900 installation process Methods 0.000 description 3
- 239000003638 chemical reducing agent Substances 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 230000008092 positive effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Abstract
The invention relates to the field of aircraft engines, in particular to an installation device and an installation method of an aircraft engine, wherein the installation device comprises an engine installation frame, a two-dimensional slipway, a parallel flexible cable mechanism and a yaw adjustment mechanism, wherein the two-dimensional slipway is arranged at the top end of the engine installation frame, the two-dimensional slipway comprises an X-direction slipway, a Y-direction slipway and a base, the base is driven to horizontally rotate through the yaw adjustment mechanism, the Y-direction slipway is movably arranged on the base, the X-direction slipway is movably arranged on the Y-direction slipway, the parallel flexible cable mechanism comprises a plurality of flexible cables and a plurality of flexible cable winding and unwinding devices, the flexible cables are controlled to be wound and unwound through the corresponding flexible cable winding and unwinding devices respectively, each flexible cable winding and unwinding device is arranged on the X-direction slipway, and the lower end of each flexible cable stretches into the engine installation frame and is connected with the aircraft engine. The invention can realize the precise installation of the aircraft engine.
Description
Technical Field
The invention relates to the field of aircraft engines, in particular to an installation device and an installation method of an aircraft engine.
Background
The aircraft engine mounting system is mainly used for assisting in safely, accurately and quickly mounting an aircraft engine to an aircraft engine nacelle manually. The installation process mainly has the following characteristics:
1. the aircraft engine mounting system can adjust the spatial position and attitude of the engine;
2. the lifting weight of the system is more than or equal to 1.2t;
3. the course adjustment distance is more than or equal to 200mm, and the adjustment precision is less than or equal to 0.1mm;
4. the span adjustment distance is more than or equal to 200mm, and the adjustment precision is less than or equal to 0.1mm;
5. the vertical adjustment distance is more than or equal to 4000mm, and the adjustment precision is less than or equal to 1mm;
6. yaw adjustment range is +/-5 degrees, and adjustment accuracy is less than or equal to 0.1 degree;
the aircraft engine mounting system in the prior art mainly comprises the following forms: (1) The lifting type mounting system based on the lifter mainly realizes mounting by clamping the bottom of the engine, occupies the bottom space of the aircraft engine, and cannot meet the condition that the bottom of the engine needs to be subjected to repair processing; (2) The hoisting system based on the travelling crane and the balance carrier has low control precision on the position and the gesture of the engine, so that the condition of manual brute force assembly is unavoidable in the field installation process.
Disclosure of Invention
The invention aims to provide an installation device and an installation method of an aircraft engine, which can realize precise installation of the aircraft engine.
The aim of the invention is realized by the following technical scheme:
the utility model provides an aircraft engine's installation device, includes engine mounting frame and locates two-dimensional slip table, parallelly connected flexible cable mechanism and yaw adjustment mechanism on engine mounting frame top, two-dimensional slip table includes X to slip table, Y to slip table and base, wherein the base passes through yaw adjustment mechanism drive horizontal rotation, Y is to the slip table movably locates on the base, X is to the slip table movably locates on the Y to slip table, parallelly connected flexible cable mechanism includes a plurality of flexible cable and a plurality of flexible cable winding and unwinding devices, just the flexible cable is received through corresponding flexible cable winding and unwinding device control respectively, and each flexible cable winding and unwinding device is all located on the X to the slip table, each flexible cable lower extreme stretches into to engine mounting frame inside and connects the aircraft engine.
The Y-direction sliding table is in sliding connection with a lower side base, a Y-direction screw rod is arranged on the base, a Y-direction driving device is arranged on one side of the base, the Y-direction screw rod is driven to rotate by the Y-direction driving device, and a Y-direction screw nut is arranged on the lower side of the Y-direction sliding table and sleeved on the Y-direction screw rod.
The X-direction sliding table is in sliding connection with the lower side Y-direction sliding table, the Y-direction sliding table is provided with an X-direction screw rod, one side of the Y-direction sliding table is provided with an X-direction driving device, the X-direction screw rod is driven to rotate by the X-direction driving device, and the lower side of the X-direction sliding table is provided with an X-direction screw nut sleeved on the X-direction screw rod.
The flexible cable winding and unwinding device comprises a winding and unwinding motor and a winding and unwinding roller, wherein the winding and unwinding roller is driven to rotate by the winding and unwinding motor, and the flexible cable is wound on the winding and unwinding roller.
Yaw adjustment mechanism includes rotary drive device, worm and revolving stage, engine mounting frame upper end is equipped with the mounting panel, the revolving stage rotationally is located the mounting panel downside, the base of two-dimensional slip table is located the mounting panel upside and with the revolving stage coaxial link firmly, mounting panel one side is equipped with rotary drive device and worm, the revolving stage downside is equipped with the worm wheel, the worm with the worm wheel meshing, and the worm passes through rotary drive device drive rotation.
According to the installation method of the installation device of the aircraft engine, the engine hanging frame is positioned in the upper end of the engine installation frame, the aircraft engine is firstly lifted to a set height below the engine hanging frame through the parallel flexible rope mechanism, then the aircraft engine is adjusted to enable the axis to be horizontal through the parallel flexible rope mechanism, then the aircraft engine is adjusted to enable the axis to be parallel to the axis of the engine hanging frame through the yaw angle Rz through the yaw adjusting mechanism, then the aircraft engine is adjusted to enable the axial position Tx and the transverse position Ty through the two-dimensional sliding table, and the axis of the engine hanging frame are positioned on the same straight line through the parallel flexible rope mechanism, and then the aircraft engine is driven to move along the X direction through the two-dimensional sliding table to enter the engine hanging frame.
The invention has the advantages and positive effects that:
1. the invention comprises a two-dimensional slipway, a yaw adjusting mechanism and a parallel flexible cable mechanism, wherein the two-dimensional slipway is used for adjusting the heading and the spanwise position of the aircraft engine, the yaw adjusting mechanism is mainly used for adjusting the yaw angle of the aircraft engine, the parallel flexible cable mechanism is mainly used for adjusting the height position, the pitching angle and the rolling angle of the engine, and the precise installation of the aircraft engine can be realized.
2. The parallel flexible cable mechanism comprises a plurality of flexible cables and a plurality of flexible cable winding and unwinding devices, and each flexible cable is driven to be wound and unwound through the corresponding flexible cable winding and unwinding device, so that the height position, the pitching angle and the rolling angle of the engine are adjusted in a hoisting mode, and the parallel flexible cable mechanism has the capacity of spatial precise posture adjustment.
3. The invention avoids the risks of crane lifting and replacement lifting and can ensure the quick and efficient installation of the aircraft engine.
Drawings
Figure 1 is a schematic view of the structure of the device of the present invention,
figure 2 is an enlarged schematic view of the two-dimensional slipway, yaw adjustment mechanism and parallel flexible cable mechanism of figure 1,
figure 3 is another angular schematic view of the two-dimensional slipway and parallel flexible cable mechanism of figure 2,
figure 4 is a bottom view of the yaw adjustment mechanism of figure 2,
figure 5 is a schematic view of the structural principle of the device of the invention,
FIG. 6 is a schematic view of an aircraft engine and engine pylon
FIG. 7 is a schematic view of a position adjustment of the aircraft engine of FIG. 6 in accordance with the present invention.
Wherein 1 is an engine mounting frame, 101 mounting plate, 2 is a two-dimensional slipway, 201 is a Y-direction slipway, 202 is an X-direction slipway, 203 is a Y-direction driving device, 204 is an X-direction driving device, 205 is an X-direction slipway, 206 is a Y-direction slipway, 3 is a parallel flexible cable mechanism, 301 is a flexible cable, 302 is a flexible cable winding and unwinding device, 4 is an aircraft engine, 401 is an engine lifting point, 5 is an engine hanging frame, 6 is a yaw adjusting mechanism, 601 is a worm, 602 is a rotary driving device, and 603 is a turntable.
Detailed Description
The invention is described in further detail below with reference to the accompanying drawings.
As shown in fig. 1 to 7, the invention comprises an engine mounting frame 1, a two-dimensional sliding table 2, a parallel flexible cable mechanism 3 and a yaw adjustment mechanism 6, wherein the two-dimensional sliding table 2 is arranged at the top end of the engine mounting frame 1, the two-dimensional sliding table 2 comprises an X-direction sliding table 202, a Y-direction sliding table 201 and a base, the base is driven to horizontally rotate by the yaw adjustment mechanism 6, the Y-direction sliding table 201 is movably arranged on the base, the X-direction sliding table 202 is movably arranged on the Y-direction sliding table 201, the parallel flexible cable mechanism 3 comprises a plurality of flexible cables 301 and a plurality of flexible cable winding and unwinding devices 302, the flexible cables 301 are controlled to be wound and unwound by the corresponding flexible cable winding and unwinding devices 302 respectively, each flexible cable winding and unwinding device 302 is arranged on the X-direction sliding table 202, and the lower end of each flexible cable 301 stretches into the engine mounting frame 1 and is connected with an aircraft engine 4. In operation of the present invention, the yaw adjustment mechanism 6 is used to adjust the yaw angle (Rz) of the aircraft engine 4; the two-dimensional sliding table 2 is arranged on the yaw adjustment mechanism 6, wherein the X-direction sliding table 202 is used for adjusting the position (Tx) of the aircraft engine 4 along the axial direction of the engine, and the Y-direction sliding table 201 is used for adjusting the position (Ty) of the aircraft engine 4 along the transverse direction of the engine; the flexible cable winding and unwinding device 302 of the parallel flexible cable mechanism 3 is mounted on the two-dimensional sliding table 2, and is used for adjusting the height (Tz), the pitch angle (Ry) and the roll angle (Rx) of the aircraft engine 4 by controlling the flexible cable 301 to be wound and unwound in a combined manner.
As shown in fig. 3, in this embodiment, the Y-directional sliding table 201 is slidably connected with a lower base, a Y-directional sliding rail 206 is provided on the base, a Y-directional sliding block matched with the Y-directional sliding rail 206 is provided on the lower side of the Y-directional sliding table 201, a Y-directional screw is provided on the base, a Y-directional driving device 203 is provided on one side of the base, the Y-directional screw is driven to rotate by the Y-directional driving device 203, a Y-directional nut is provided on the lower side of the Y-directional sliding table 201 and is sleeved on the Y-directional screw, and the Y-directional screw rotates, i.e. drives the Y-directional sliding table 201 to move by the Y-directional nut. The Y-direction driving device 203 may be automatically controlled by a servo motor or the like.
As shown in fig. 3, in this embodiment, the X-direction sliding table 202 is slidably connected with the lower Y-direction sliding table 201, an X-direction sliding rail 205 is disposed on the Y-direction sliding table 201, an X-direction sliding block that is matched with the X-direction sliding rail 205 is disposed on the lower side of the X-direction sliding table 202, an X-direction screw is disposed on the Y-direction sliding table 201, an X-direction driving device 204 is disposed on one side of the Y-direction sliding table 201, the X-direction screw is driven to rotate by the X-direction driving device 204, an X-direction nut is disposed on the lower side of the X-direction sliding table 202 and is sleeved on the X-direction screw, and the X-direction screw is driven to move by the X-direction nut. The X-direction driving device 204 may be automatically controlled by a servo motor or the like.
As shown in fig. 3, in this embodiment, the flexible cable winding and unwinding device 302 includes a winding and unwinding motor, a worm gear reducer, and a winding and unwinding roller, the winding and unwinding roller is driven to rotate by the winding and unwinding motor, and the winding and unwinding motor transmits torque by the worm gear reducer, so that the flexible cable 301 is wound on the winding and unwinding roller.
As shown in fig. 4, in this embodiment, the yaw adjustment mechanism 6 includes a rotation driving device 602, a worm 601 and a turntable 603, a mounting board 101 is disposed at an upper end of the engine mounting frame 1, the turntable 603 is rotatably disposed at a lower side of the mounting board 101, a base of the two-dimensional sliding table 2 is disposed at an upper side of the mounting board 101 and is fixedly connected with the turntable 603 coaxially, the rotation driving device 602 and the worm 601 are disposed at one side of the mounting board 101, a worm wheel is disposed at a lower side of the turntable 603, the worm 601 is meshed with the worm wheel, and the worm 601 is driven to rotate by the rotation driving device 602, so as to drive the worm wheel to rotate, and the worm wheel rotates to drive the turntable 603 and the base of the two-dimensional sliding table 2 fixedly connected with the turntable 603 coaxially.
As shown in fig. 4, the flexible cable 301 is penetrated by a gap between the mounting plate 101 and the upper end beam of the engine mounting frame 1, and the gap should be ensured to be large enough, so that when the two-dimensional sliding table 2 rotates, the flexible cable 301 does not collide with and interfere with the mounting plate 101 or the upper end beam of the engine mounting frame 1 to affect the pose adjustment of the aircraft engine 4. As shown in fig. 6, the aircraft engine 4 is provided with an engine hanging point 401 connected with the flexible cable 301, and the flexible cable 301 passes through a gap between the rails at the front part of the engine hanger 5 and then is connected with the aircraft engine 4 to drive the aircraft engine 4 to move.
The working principle of the invention is as follows:
in operation of the present invention, the yaw adjustment mechanism 6 is used to adjust the yaw angle (Rz) of the aircraft engine 4; the two-dimensional sliding table 2 is arranged on the yaw adjustment mechanism 6, wherein the X-direction sliding table 202 is used for adjusting the position (Tx) of the aircraft engine 4 along the axial direction of the engine, and the Y-direction sliding table 201 is used for adjusting the position (Ty) of the aircraft engine 4 along the transverse direction of the engine; the flexible cable winding and unwinding device 302 of the parallel flexible cable mechanism 3 is mounted on the two-dimensional sliding table 2, and is used for adjusting the height (Tz), the pitch angle (Ry) and the roll angle (Rx) of the aircraft engine 4 by controlling the winding and unwinding of the flexible cable 301, and is further described below with reference to an application example.
As shown in fig. 1, an aircraft engine 4 is placed in an engine mounting frame 1 and lifted to the vicinity of an engine pylon 5 by a parallel flexible wire mechanism 3. As shown in fig. 6 to 7, assuming that the axis AB of the aircraft engine 4 and the axis AB of the engine pylon 5 do not coincide in the initial state, since the clearance between the engine pylon 5 and the engine body in the spanwise direction is small, the following adjustment method is adopted in the engine installation process: (1) The pose of the aircraft engine 4 is adjusted through the parallel flexible rope mechanism 3, so that the axis of the aircraft engine 4 is in a horizontal state, (2) the yaw angle Rz of the aircraft engine 4 is adjusted through the yaw adjusting mechanism 6, so that ab moves to a 1 b 1 The position is parallel to AB; (3) Tx and Ty are adjusted through the two-dimensional sliding table 2, and the height Tz is adjusted through the parallel flexible cable mechanism 3, so that the axis ab of the engine is moved to a 2 b 2 The position is in a straight line with the axis AB of the engine pylon 5, so that the clearance allowance on two sides in the wingspan direction is nearly symmetrical when the engine enters the engine pylon, and the assembly interference risk is reduced; (4) The two-dimensional slipway 2 drives the aircraft engine 4 to move along the X direction, so that the aircraft engine 4 is installed in the engine pylon 5.
Claims (3)
1. An aircraft engine mounting device, characterized in that: the device comprises an engine mounting rack (1) and a two-dimensional sliding table (2), a parallel flexible cable mechanism (3) and a yaw adjusting mechanism (6) which are arranged at the top end of the engine mounting rack (1), wherein the two-dimensional sliding table (2) comprises an X-direction sliding table (202), a Y-direction sliding table (201) and a base, the base is driven to horizontally rotate through the yaw adjusting mechanism (6), the Y-direction sliding table (201) is movably arranged on the base, the X-direction sliding table (202) is movably arranged on the Y-direction sliding table (201), the parallel flexible cable mechanism (3) comprises a plurality of flexible cables (301) and a plurality of flexible cable winding and unwinding devices (302), the flexible cables (301) are controlled to be wound and unwound through the corresponding flexible cable winding and unwinding devices (302), the flexible cable winding and unwinding devices (302) are respectively arranged on the X-direction sliding table (202), and the lower ends of the flexible cables (301) are stretched into the engine mounting rack (1) and are connected with an aircraft engine (4);
the Y-direction sliding table (201) is in sliding connection with a lower base, a Y-direction screw rod is arranged on the base, a Y-direction driving device (203) is arranged on one side of the base, the Y-direction screw rod is driven to rotate by the Y-direction driving device (203), and a Y-direction screw nut is arranged on the lower side of the Y-direction sliding table (201) and sleeved on the Y-direction screw rod;
the X-direction sliding table (202) is in sliding connection with the Y-direction sliding table (201) at the lower side, an X-direction screw rod is arranged on the Y-direction sliding table (201), an X-direction driving device (204) is arranged at one side of the Y-direction sliding table (201), the X-direction screw rod is driven to rotate by the X-direction driving device (204), and an X-direction screw nut is arranged at the lower side of the X-direction sliding table (202) and sleeved on the X-direction screw rod;
yaw guiding mechanism (6) are including rotary drive (602), worm (601) and revolving stage (603), engine mount frame (1) upper end is equipped with mounting panel (101), revolving stage (603) rotationally locate mounting panel (101) downside, the base of two-dimensional slip table (2) is located mounting panel (101) upside and with revolving stage (603) coaxial fixedly link, mounting panel (101) one side is equipped with rotary drive (602) and worm (601), revolving stage (603) downside is equipped with the worm wheel, worm (601) with the worm wheel meshing, and worm (601) are through rotary drive (602) drive rotation, flexible cable (301) are passed by the space between mounting panel (101) and engine mount frame (1) upper end roof beam.
2. The aircraft engine mounting device according to claim 1, wherein: the flexible cable winding and unwinding device (302) comprises a winding and unwinding motor and a winding and unwinding roller, the winding and unwinding roller is driven to rotate by the winding and unwinding motor, and the flexible cable (301) is wound on the winding and unwinding roller.
3. A method of installing an aircraft engine installation device according to claim 1, characterized in that: the engine hanging frame (5) is positioned in the upper end of the engine mounting frame (1), the aircraft engine (4) is firstly lifted to a set height below the engine hanging frame (5) through the parallel flexible rope mechanism (3), then the aircraft engine (4) is adjusted to enable an axis to be horizontal through the parallel flexible rope mechanism (3), then the aircraft engine (4) is enabled to enable the axis to be parallel to the axis of the engine hanging frame (5) through the yaw angle Rz adjusted through the yaw adjusting mechanism (6), then the aircraft engine (4) is enabled to enable the axis to be located on the same straight line with the axis of the engine hanging frame (5) through the parallel flexible rope mechanism (3) by adjusting the axial position Tx and the transverse position Ty through the two-dimensional sliding table (2) and then the aircraft engine (4) is enabled to move into the engine hanging frame (5) along the X direction through the driving of the two-dimensional sliding table (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011559344.8A CN114684384B (en) | 2020-12-25 | 2020-12-25 | Installation device and installation method of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011559344.8A CN114684384B (en) | 2020-12-25 | 2020-12-25 | Installation device and installation method of aircraft engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114684384A CN114684384A (en) | 2022-07-01 |
| CN114684384B true CN114684384B (en) | 2023-11-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011559344.8A Active CN114684384B (en) | 2020-12-25 | 2020-12-25 | Installation device and installation method of aircraft engine |
Country Status (1)
| Country | Link |
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| CN (1) | CN114684384B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116443260B (en) * | 2023-06-20 | 2023-09-19 | 中航西飞民用飞机有限责任公司 | Lifting type aeroengine in-place installation method |
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| FR859265A (en) * | 1938-11-19 | 1940-12-14 | Precision Moderne | Anti-aircraft fire conjugator |
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