CN114684384A - Installation device and installation method of aircraft engine - Google Patents
Installation device and installation method of aircraft engine Download PDFInfo
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- CN114684384A CN114684384A CN202011559344.8A CN202011559344A CN114684384A CN 114684384 A CN114684384 A CN 114684384A CN 202011559344 A CN202011559344 A CN 202011559344A CN 114684384 A CN114684384 A CN 114684384A
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- 238000009434 installation Methods 0.000 title claims abstract description 24
- 238000000034 method Methods 0.000 title claims abstract description 8
- 238000004804 winding Methods 0.000 claims description 25
- 238000011900 installation process Methods 0.000 description 3
- 239000003638 chemical reducing agent Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 230000000295 complement effect Effects 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
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- 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
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention relates to the field of aircraft engines, in particular to an installation device and an installation method of an aircraft engine, which comprises an engine installation rack, a two-dimensional sliding table, a parallel flexible cable mechanism and a yaw adjusting mechanism, wherein the two-dimensional sliding table, the parallel flexible cable mechanism and the yaw adjusting mechanism are arranged at the top end of the engine installation rack, the two-dimensional sliding table comprises an X-direction sliding table, a Y-direction sliding table and a base, the base is driven by the yaw adjusting mechanism to rotate horizontally, the Y-direction sliding table is movably arranged on the base, the X-direction sliding table is movably arranged on the Y-direction sliding table, the parallel flexible cable mechanism comprises a plurality of flexible cables and a plurality of flexible cable retracting devices, the flexible cables are respectively controlled to be retracted through the corresponding flexible cable retracting devices, each flexible cable retracting device is arranged on the X-direction sliding table, and the lower end of each flexible cable extends into the engine installation rack 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 manually and safely, accurately and quickly mounting an aircraft engine to an aircraft engine nacelle. The installation process mainly has the following characteristics:
1. the aircraft engine mounting system can adjust the spatial position attitude of the engine;
2. the hoisting weight of the system is more than or equal to 1.2 t;
3. the course adjusting distance is more than or equal to 200mm, and the adjusting precision is less than or equal to 0.1 mm;
4. the wingspan adjusting distance is more than or equal to 200mm, and the adjusting precision is less than or equal to 0.1 mm;
5. the plumb adjusting distance is more than or equal to 4000mm, and the adjusting precision is less than or equal to 1 mm;
6. the yaw adjusting range is +/-5 degrees, and the adjusting precision is less than or equal to 0.1 degree;
the prior art aircraft engine mounting systems generally comprise the following form: (1) the lift type installation system based on the elevator is mainly installed by clamping the bottom of an engine, needs to occupy the bottom space of the aircraft engine, and cannot meet the condition that the bottom of the engine needs to be subjected to complementary processing; (2) the hoisting system based on the 'travelling crane + balance carrier' has low control precision on the position and the posture of an engine, so that manual brute force assembly is inevitable 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 the precise installation of the aircraft engine.
The purpose of the invention is realized by the following technical scheme:
the utility model provides an aircraft engine's installation device, includes engine mount frame and locates two-dimentional slip table, parallelly connected flexible cable mechanism and driftage guiding mechanism on engine mount frame top, two-dimentional slip table includes X to slip table, Y to slip table and base, and wherein the base passes through driftage guiding mechanism drive horizontal rotation, Y are movably located to the slip table on the base, X is movably located to the slip table Y is to on the slip table, parallelly connected flexible cable mechanism includes a plurality of flexible cables and a plurality of flexible cable winding and unwinding devices, just the flexible cable is respectively receive and releases through the flexible cable winding and unwinding devices control that corresponds, and each flexible cable winding and unwinding devices all locates X is to on the slip table, and each flexible cable lower extreme stretches into to engine mount frame inside and connect aircraft engine.
Y is to slip table and downside base sliding connection, be equipped with Y on the base to the lead screw, base one side is equipped with Y to drive arrangement, just Y passes through to the lead screw Y rotates to drive arrangement drive, Y is equipped with Y to the slip table downside and adorns to the screw suit in Y is to on the lead screw.
X is to slip table and downside Y to slip table sliding connection, Y is equipped with X to the lead screw to the slip table, Y is equipped with X to drive arrangement to slip table one side, just X passes through to the lead screw X rotates to the drive arrangement drive, X is equipped with X to the slip table downside and adorns in X is to screw suit on the lead screw.
The flexible cable winding and unwinding device 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 is wound on the winding and unwinding roller.
Yaw guiding mechanism includes rotary drive device, worm and revolving stage, engine installation frame upper end is equipped with the mounting panel, the revolving stage is rotationally located the mounting panel downside, the base of two-dimentional slip table is located the mounting panel upside and with the revolving stage is coaxial to be linked 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 the rotary drive device drive is rotatory.
According to the installation method of the installation device of the aircraft engine, the engine hanger is located in the upper end of the engine installation rack, the aircraft engine is firstly hoisted to the position below the engine hanger by the parallel flexible cable mechanism to set the height, then the attitude of the aircraft engine is adjusted by the parallel flexible cable mechanism to enable the axis to be horizontal, then the aircraft engine adjusts the yaw angle Rz by the yaw adjusting mechanism to enable the axis to be parallel to the axis of the engine hanger, then the aircraft engine adjusts the axial position Tx and the transverse position Ty by the two-dimensional sliding table and adjusts the height Tz by the parallel flexible cable mechanism to enable the axis and the axis of the engine hanger to be located on the same straight line, and then the aircraft engine is driven by the two-dimensional sliding table to move along the X direction to enter the engine hanger.
The invention has the advantages and positive effects that:
1. the two-dimensional sliding table is used for adjusting the course direction and the wingspan direction position of an aircraft engine, the yaw adjusting mechanism is mainly used for adjusting the yaw angle of the aircraft engine, and the parallel flexible cable mechanism is mainly used for adjusting the height position, the pitching angle and the rolling angle of the engine, so that 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, each flexible cable is driven to be wound and unwound by the corresponding flexible cable winding and unwinding device, and the height position, the pitching angle and the rolling angle of an engine are adjusted in a hoisting mode, so that the parallel flexible cable mechanism has the space precision posture adjusting capability.
3. The invention avoids the risks of crane hoisting and replacement hoisting, and can ensure that the aircraft engine is installed quickly and efficiently.
Drawings
FIG. 1 is a schematic structural view of the apparatus of the present invention,
FIG. 2 is an enlarged view of the two-dimensional stage, yaw adjustment mechanism and parallel cable mechanism of FIG. 1,
figure 3 is another perspective view of the two-dimensional slide and parallel cable mechanism of figure 2,
figure 4 is a bottom view of the yaw adjustment mechanism of figure 2,
figure 5 is a schematic diagram of the structure of the device of the invention,
FIG. 6 is a schematic view of an aircraft engine and engine pylon
Fig. 7 is a schematic diagram of the pose adjustment of the aircraft engine of fig. 6 according to the present invention.
The system comprises an engine mounting frame 1, a mounting plate 101, a two-dimensional sliding table 2, a Y-direction sliding table 201, an X-direction sliding table 202, a Y-direction driving device 203, an X-direction driving device 204, an X-direction sliding rail 205, a Y-direction sliding rail 206, a parallel flexible cable mechanism 3, a flexible cable 301, a flexible cable winding and unwinding device 302, an aircraft engine 4, an engine suspension point 401, an engine hanger 5, a yaw adjusting mechanism 6, a worm 601, a rotary driving device 602 and a rotary table 603.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
As shown in fig. 1 to 7, the invention includes an engine mounting frame 1, and a two-dimensional sliding table 2, a parallel flexible cable mechanism 3 and a yaw adjusting mechanism 6 which are arranged on the top end of the engine mounting frame 1, wherein as shown in fig. 3, the two-dimensional sliding table 2 includes an X-direction sliding table 202, a Y-direction sliding table 201 and a base, wherein the base is driven by the yaw adjusting mechanism 6 to rotate horizontally, 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 includes a plurality of flexible cables 301 and a plurality of flexible cable retracting devices 302, and the flexible cables 301 are respectively controlled to retract and retract by the corresponding flexible cable retracting devices 302, each flexible cable retracting device 302 is arranged on the X-direction sliding table 202, and the lower end of each flexible cable 301 extends into the engine mounting frame 1 and is connected with an aircraft engine 4. When the invention is in operation, the yaw adjusting mechanism 6 is used for adjusting the yaw angle (Rz) of the aircraft engine 4; the two-dimensional sliding table 2 is mounted on a yaw adjusting 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 retracting device 302 of the parallel flexible cable mechanism 3 is mounted on the two-dimensional sliding table 2, and controls the flexible cable 301 to retract and retract the flexible cable for adjusting the height (Tz), the pitch angle (Ry) and the roll angle (Rx) of the aircraft engine 4.
As shown in fig. 3, in this embodiment, the Y-direction sliding table 201 is slidably connected to the lower base, the base is provided with a Y-direction sliding rail 206, the Y-direction sliding table 201 is provided with a Y-direction sliding block engaged with the Y-direction sliding rail 206, the base is provided with a Y-direction lead screw, one side of the base is provided with a Y-direction driving device 203, the Y-direction lead screw is driven to rotate by the Y-direction driving device 203, the Y-direction sliding table 201 is provided with a Y-direction nut sleeved on the Y-direction lead screw, and the Y-direction lead screw rotates, i.e., the Y-direction lead screw is driven by the Y-direction nut to move to the sliding table 201. The Y-direction driving device 203 can 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 to the Y-direction sliding table 201 on the lower side, the Y-direction sliding table 201 is provided with an X-direction sliding rail 205, an X-direction sliding block matched with the X-direction sliding rail 205 is provided on the lower side of the X-direction sliding table 202, an X-direction lead screw is provided on the Y-direction sliding table 201, an X-direction driving device 204 is provided on one side of the Y-direction sliding table 201, the X-direction lead screw is driven to rotate by the X-direction driving device 204, an X-direction nut is provided on the lower side of the X-direction sliding table 202 and sleeved on the X-direction lead screw, and the X-direction lead screw rotates, that is, the X-direction lead screw is driven by the X-direction nut, and the X-direction sliding table 202 moves. The X-direction driving device 204 can 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 drum, the winding and unwinding drum is driven to rotate by the winding and unwinding motor, the winding and unwinding motor transmits torque through the worm gear reducer, and the flexible cable 301 is wound on the winding and unwinding drum.
As shown in fig. 4, in this embodiment, yaw adjustment mechanism 6 includes rotary drive device 602, worm 601 and revolving stage 603, engine installation frame 1 upper end is equipped with mounting panel 101, revolving stage 603 rotationally locates mounting panel 101 downside, the base of two-dimensional slip table 2 is located mounting panel 101 upside and with revolving stage 603 is coaxial to be linked firmly, mounting panel 101 one side is equipped with rotary drive device 602 and worm 601, revolving stage 603 downside is equipped with the worm wheel, worm 601 with the worm wheel meshing, and worm 601 passes through rotary drive device 602 drive is rotatory, and then drives the worm wheel is rotatory, the worm wheel is rotatory drive revolving stage 603 and with the two-dimensional slip table 2 base that revolving stage 603 is coaxial to be linked firmly is rotatory.
As shown in fig. 4, the flexible cable 301 is penetrated through a gap between the mounting plate 101 and the upper end beam of the engine mounting frame 1, and the gap is ensured to be large enough, so that when the two-dimensional sliding table 2 rotates, the flexible cable 301 does not collide with the mounting plate 101 or the upper end beam of the engine mounting frame 1 to interfere with the mounting plate to influence the pose adjustment of the aircraft engine 4. As shown in fig. 6, an engine hanging point 401 connected to the flexible cable 301 is provided on the aircraft engine 4, and the flexible cable 301 passes through a gap between front rails of the engine pylon 5 and then is connected to the aircraft engine 4 to drive the aircraft engine 4 to move.
The working principle of the invention is as follows:
when the invention is in operation, the yaw adjusting mechanism 6 is used for adjusting the yaw angle (Rz) of the aircraft engine 4; the two-dimensional sliding table 2 is mounted on a yaw adjusting 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 retracting 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 retract, which is further described below by using an application example.
As shown in fig. 1, an aircraft engine 4 is placed in an engine mount frame 1 and lifted by a parallel wire mechanism 3 to the vicinity of an engine pylon 5. 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 gap between the engine pylon 5 and the engine body in the span direction is small, the following adjustment method is adopted in the engine installation process: (1) adjusting the pose of the aircraft engine 4 by the parallel flexible cable mechanism 3 to ensure that the axis of the aircraft engine 4 is in a horizontal state, and (2) adjusting the yaw angle Rz of the aircraft engine 4 by the yaw adjusting mechanism 6 to ensure that ab moves to a1b1Position parallel to AB; (3) tx, Ty are adjusted through the two-dimensional sliding table 2, and the height T is adjusted through the parallel flexible cable mechanism 3z, moving the engine axis ab to a2b2The position of the engine pylon is in a straight line with the axis AB of the engine pylon 5, so that the gap allowance at two sides in the wingspan direction is close to symmetry when the engine enters the engine pylon, and the assembly interference risk is reduced; (4) the two-dimensional sliding table 2 drives the aircraft engine 4 to move along the X direction, so that the aircraft engine 4 is installed in the engine hanger 5.
Claims (6)
1. An aircraft engine mounting arrangement, characterized by: comprises an engine mounting frame (1), a two-dimensional sliding table (2) arranged at the top end of the engine mounting frame (1), a parallel flexible cable mechanism (3) and a yaw adjusting mechanism (6), the two-dimensional sliding table (2) comprises an X-direction sliding table (202), a Y-direction sliding table (201) and a base, wherein the base is driven by the yaw adjusting mechanism (6) to rotate horizontally, 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 coiling and uncoiling devices (302), and the flexible cables (301) are controlled to be retracted through corresponding flexible cable retracting devices (302), each flexible cable retracting device (302) is arranged on the X-direction sliding table (202), and the lower ends of the flexible cables (301) extend into the engine mounting frame (1) and are connected with the aircraft engine (4).
2. An aircraft engine mounting arrangement according to claim 1, wherein: y is to slip table (201) and downside base sliding connection, be equipped with Y on the base to the lead screw, base one side is equipped with Y to drive arrangement (203), just Y passes through to the lead screw Y rotates to drive arrangement (203) drive, Y is equipped with Y to slip table (201) downside and is in Y to the screw suit on to the lead screw.
3. An aircraft engine mounting arrangement according to claim 1, wherein: x is to slip table (202) and downside Y to slip table (201) sliding connection, Y is equipped with X to the lead screw on to slip table (201), Y is equipped with X to drive arrangement (204) to slip table (201) one side, just X passes through to the lead screw X rotates to drive arrangement (204) drive, X is equipped with X to slip table (202) downside and adorns to the screw suit X is to on to the lead screw.
4. An aircraft engine mounting arrangement 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.
5. An aircraft engine mounting arrangement according to claim 1, wherein: yaw guiding mechanism (6) are including rotary drive device (602), worm (601) and revolving stage (603), engine installation 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) are coaxial to be linked firmly, mounting panel (101) one side is equipped with rotary drive device (602) and worm (601), revolving stage (603) downside is equipped with the worm wheel, worm (601) with the worm wheel meshing, and worm (601) pass through rotary drive device (602) drive is rotatory.
6. A method of installing an aircraft engine mounting device according to claim 1, characterised in that: the engine hanger (5) is located in the upper end of the engine mounting rack (1), the aircraft engine (4) is firstly hoisted to the position below the engine hanger (5) through the parallel flexible cable mechanism (3) to set the height, then the aircraft engine (4) adjusts the pose through the parallel flexible cable mechanism (3) to enable the axis to be horizontal, then the aircraft engine (4) adjusts the yaw angle Rz through the yaw adjusting mechanism (6) to enable the axis to be parallel to the axis of the engine hanger (5), then the aircraft engine (4) adjusts the axial position Tx and the transverse position Ty through the two-dimensional sliding table (2) and adjusts the height Tz through the parallel flexible cable mechanism (3) to enable the axis and the axis of the engine hanger (5) to be located on the same straight line, and then the aircraft engine (4) is driven to move into the engine hanger (5) along the X direction through 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 true CN114684384A (en) | 2022-07-01 |
| CN114684384B CN114684384B (en) | 2023-11-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011559344.8A Active CN114684384B (en) | 2020-12-25 | 2020-12-25 | Installation device and installation method of aircraft engine |
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| CN (1) | CN114684384B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116443260A (en) * | 2023-06-20 | 2023-07-18 | 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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| CN105856205A (en) * | 2016-06-17 | 2016-08-17 | 中国矿业大学 | Parallel flexible cable suspension simulation system and parallel flexible cable suspension simulation method employing same |
| CN108216682A (en) * | 2017-12-28 | 2018-06-29 | 彩虹无人机科技有限公司 | Six degree of freedom Portable unmanned machine wing and the general posture adjustment docking motorcycle of vee tail |
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| FR859265A (en) * | 1938-11-19 | 1940-12-14 | Precision Moderne | Anti-aircraft fire conjugator |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116443260A (en) * | 2023-06-20 | 2023-07-18 | 中航西飞民用飞机有限责任公司 | Lifting type aeroengine in-place installation method |
| 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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| Publication number | Publication date |
|---|---|
| CN114684384B (en) | 2023-11-17 |
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