CN112723180A - Intelligent airplane engine position changing device and position changing method thereof - Google Patents
Intelligent airplane engine position changing device and position changing method thereof Download PDFInfo
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- CN112723180A CN112723180A CN202011591735.8A CN202011591735A CN112723180A CN 112723180 A CN112723180 A CN 112723180A CN 202011591735 A CN202011591735 A CN 202011591735A CN 112723180 A CN112723180 A CN 112723180A
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- 230000005540 biological transmission Effects 0.000 claims description 42
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- 230000003044 adaptive effect Effects 0.000 claims description 2
- 230000005484 gravity Effects 0.000 abstract description 6
- 238000013459 approach Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000011161 development Methods 0.000 description 1
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- 239000003345 natural gas Substances 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66C—CRANES; LOAD-ENGAGING ELEMENTS OR DEVICES FOR CRANES, CAPSTANS, WINCHES, OR TACKLES
- B66C19/00—Cranes comprising trolleys or crabs running on fixed or movable bridges or gantries
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66C—CRANES; LOAD-ENGAGING ELEMENTS OR DEVICES FOR CRANES, CAPSTANS, WINCHES, OR TACKLES
- B66C1/00—Load-engaging elements or devices attached to lifting or lowering gear of cranes or adapted for connection therewith for transmitting lifting forces to articles or groups of articles
- B66C1/10—Load-engaging elements or devices attached to lifting or lowering gear of cranes or adapted for connection therewith for transmitting lifting forces to articles or groups of articles by mechanical means
- B66C1/107—Load-engaging elements or devices attached to lifting or lowering gear of cranes or adapted for connection therewith for transmitting lifting forces to articles or groups of articles by mechanical means for lifting engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66C—CRANES; LOAD-ENGAGING ELEMENTS OR DEVICES FOR CRANES, CAPSTANS, WINCHES, OR TACKLES
- B66C1/00—Load-engaging elements or devices attached to lifting or lowering gear of cranes or adapted for connection therewith for transmitting lifting forces to articles or groups of articles
- B66C1/10—Load-engaging elements or devices attached to lifting or lowering gear of cranes or adapted for connection therewith for transmitting lifting forces to articles or groups of articles by mechanical means
- B66C1/42—Gripping members engaging only the external or internal surfaces of the articles
- B66C1/425—Gripping members engaging only the external or internal surfaces of the articles motor actuated
- B66C1/427—Gripping members engaging only the external or internal surfaces of the articles motor actuated by hydraulic or pneumatic motors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66C—CRANES; LOAD-ENGAGING ELEMENTS OR DEVICES FOR CRANES, CAPSTANS, WINCHES, OR TACKLES
- B66C11/00—Trolleys or crabs, e.g. operating above runways
- B66C11/08—Trolleys or crabs, e.g. operating above runways with turntables
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66C—CRANES; LOAD-ENGAGING ELEMENTS OR DEVICES FOR CRANES, CAPSTANS, WINCHES, OR TACKLES
- B66C13/00—Other constructional features or details
- B66C13/04—Auxiliary devices for controlling movements of suspended loads, or preventing cable slack
- B66C13/06—Auxiliary devices for controlling movements of suspended loads, or preventing cable slack for minimising or preventing longitudinal or transverse swinging of loads
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66C—CRANES; LOAD-ENGAGING ELEMENTS OR DEVICES FOR CRANES, CAPSTANS, WINCHES, OR TACKLES
- B66C13/00—Other constructional features or details
- B66C13/04—Auxiliary devices for controlling movements of suspended loads, or preventing cable slack
- B66C13/08—Auxiliary devices for controlling movements of suspended loads, or preventing cable slack for depositing loads in desired attitudes or positions
- B66C13/085—Auxiliary devices for controlling movements of suspended loads, or preventing cable slack for depositing loads in desired attitudes or positions electrical
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66C—CRANES; LOAD-ENGAGING ELEMENTS OR DEVICES FOR CRANES, CAPSTANS, WINCHES, OR TACKLES
- B66C13/00—Other constructional features or details
- B66C13/18—Control systems or devices
- B66C13/46—Position indicators for suspended loads or for crane elements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66C—CRANES; LOAD-ENGAGING ELEMENTS OR DEVICES FOR CRANES, CAPSTANS, WINCHES, OR TACKLES
- B66C13/00—Other constructional features or details
- B66C13/18—Control systems or devices
- B66C13/50—Applications of limit circuits or of limit-switch arrangements
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66C—CRANES; LOAD-ENGAGING ELEMENTS OR DEVICES FOR CRANES, CAPSTANS, WINCHES, OR TACKLES
- B66C5/00—Base supporting structures with legs
- B66C5/02—Fixed or travelling bridges or gantries, i.e. elongated structures of inverted L or of inverted U shape or tripods
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66C—CRANES; LOAD-ENGAGING ELEMENTS OR DEVICES FOR CRANES, CAPSTANS, WINCHES, OR TACKLES
- B66C9/00—Travelling gear incorporated in or fitted to trolleys or cranes
- B66C9/14—Trolley or crane travel drives
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66C—CRANES; LOAD-ENGAGING ELEMENTS OR DEVICES FOR CRANES, CAPSTANS, WINCHES, OR TACKLES
- B66C9/00—Travelling gear incorporated in or fitted to trolleys or cranes
- B66C9/18—Travelling gear incorporated in or fitted to trolleys or cranes with means for locking trolleys or cranes to runways or tracks to prevent inadvertent movements
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66D—CAPSTANS; WINCHES; TACKLES, e.g. PULLEY BLOCKS; HOISTS
- B66D5/00—Braking or detent devices characterised by application to lifting or hoisting gear, e.g. for controlling the lowering of loads
- B66D5/32—Detent devices
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Automation & Control Theory (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Transmission Devices (AREA)
Abstract
The invention discloses an intelligent aircraft engine position changing device, which comprises: the lifting device comprises a walking assembly fixedly arranged on the ground and a lifting frame fixedly connected with the walking assembly; the hanger comprises an upright post fixedly connected with the walking assembly, a cross frame fixedly connected with the upright post, a sliding assembly matched with the cross frame, a rotating assembly fixedly connected with the sliding assembly, a lifting assembly fixedly connected with the rotating assembly and a clamp assembly fixedly connected with the lifting assembly; and a brake matched with the rotating assembly is fixedly arranged below the sliding assembly. According to the invention, the brake disc and the brake stopper are designed to complete the limiting work of the rotating assembly and the inertia limiting generated in the rotating process of the rotating assembly driving the aircraft engine to rotate, so that the situation that the preset position of the aircraft engine is inconsistent with the actual position when the orientation of the aircraft engine is changed due to inertia influence when the aircraft engine rotates due to the overweight gravity of the aircraft engine is avoided.
Description
Technical Field
The invention relates to an intelligent aircraft engine deflection device, in particular to an intelligent aircraft engine deflection device and a deflection method thereof.
Background
Generally, an aircraft engine is a highly complex and precise thermal machine, and as the heart of an aircraft, the aircraft engine is not only the power for flying the aircraft, but also an important driving force for promoting the development of aviation industry, and each important change in human aviation history is inseparable from the technical progress of the aircraft engine.
The aero-engine has been developed into a mature product with extremely high reliability, and the aero-engine in use includes various types such as a turbojet/turbofan engine, a turboshaft/turboprop engine, a ramjet engine and a piston engine, and not only is used as power for military and civil aircrafts, unmanned planes and cruise missiles for various purposes, but also a gas turbine developed by using the aero-engine is widely used in the fields of ground power generation, marine power, mobile power stations, natural gas and petroleum pipeline pump stations and the like.
When the aircraft engine needs to be shifted, the traditional mode is that the shifting work of the aircraft engine is completed through a gantry crane frame, and when the orientation of the aircraft engine needs to be changed, a rotating mechanism is generally installed on the gantry crane frame in the traditional mode to complete the change of the orientation of the aircraft engine, but when the change of the orientation of the aircraft engine is completed, because the gravity of the aircraft engine is too heavy, the aircraft engine rotates to generate inertia, and the preset position of the mechanism when the aircraft engine is driven to change the orientation is often not consistent with the actual position.
Disclosure of Invention
The purpose of the invention is as follows: the utility model provides an intelligent aircraft engine device that shifts to solve the above-mentioned problem that prior art exists.
The technical scheme is as follows: an intelligent aircraft engine indexing device comprising:
the lifting device comprises a walking assembly fixedly arranged on the ground and a lifting frame fixedly connected with the walking assembly;
the hanger comprises an upright post fixedly connected with the walking assembly, a cross frame fixedly connected with the upright post, a sliding assembly matched with the cross frame, a rotating assembly fixedly connected with the sliding assembly, a lifting assembly fixedly connected with the rotating assembly and a clamp assembly fixedly connected with the lifting assembly;
and a brake matched with the rotating assembly is fixedly arranged below the sliding assembly.
In a further embodiment, the walking assembly comprises a walking bottom plate fixedly installed on the ground, a walking motor fixedly connected with the walking bottom plate, a walking screw rod coaxially rotating with the walking motor, and a walking slider sleeved on the walking screw rod and fixedly connected with the upright post;
and a walking guide rod inserted in the walking sliding block is fixedly arranged on the walking bottom plate.
In a further embodiment, the cross-frame is an i-shaped cross-frame; the lifting device is fixedly provided with a meshing rack;
the sliding assembly comprises two groups of sliding units which are matched with the meshing rack and arranged in parallel, each group of sliding units comprises a sliding transmission left gear and a sliding transmission right gear which are matched with the meshing rack, a sliding drive gear which is meshed with the sliding transmission left gear and the sliding transmission right gear, a sliding drive shaft which is inserted in the sliding drive gear, a sliding motor which is in transmission connection with the sliding drive shaft, a sliding fixed plate which is sleeved on the sliding drive shaft, a sliding fixed rod which is fixedly connected with the sliding fixed plate, a sliding connecting plate which is fixedly connected with the sliding fixed rod, a sliding follow-up shaft which is inserted in the sliding connecting plate, a sliding follow-up wheel which is sleeved on the sliding follow-up shaft and is abutted against the cross frame, and a sliding bottom plate which is fixedly arranged below the sliding connecting plate;
and the sliding transmission left gear and the sliding transmission right gear are rotationally connected with the sliding fixing plate.
In a further embodiment, the rotating assembly comprises a rotating motor fixedly installed below the sliding bottom plate, a rotating input shaft inserted in the rotating motor, a brake disc and a rotating disc, wherein the brake disc and the rotating disc are fixedly connected with the rotating input shaft and are arranged in parallel;
and a brake stopper matched with the brake disc is fixedly arranged below the sliding bottom plate.
In a further embodiment, the brake comprises a brake connecting rod fixedly connected with the sliding bottom plate, a brake frame fixedly connected with the brake connecting rod, a brake upper shift rod and a brake lower shift rod fixedly connected with the brake frame, a brake upper shift block fixedly connected with the brake upper shift rod, and a brake lower shift block fixedly connected with the brake lower shift rod;
the brake disc is provided with a plurality of groups of grooves;
the brake disc is provided with a buffer block with a preset radian; meanwhile, a buffer block is designed to buffer inertia;
design brake disc and stopper accomplish spacing work and the rotating component of rotation component and drive the inertia that aircraft engine rotation process produced spacingly, shift the pole through stopping and shift the pole under the stopping and drive the stopping and shift the piece and shift under the stopping and be close to, and then make the stopping shift the piece and shift and carry out the butt brake disc under the stopping, and then accomplish spacing work and the rotating component of rotation component and drive the inertia that aircraft engine rotation process produced spacingly, avoid because aircraft engine's gravity is overweight, aircraft engine is when rotatory, because inertia influences, preset position when aircraft engine changes the orientation does not accord with actual position, brake simultaneously, avoid aircraft engine to appear the collision damage.
In a further embodiment, the lifting assembly comprises a lifting housing fixedly connected with a rotating disk, a lifting stabilizing plate fixedly mounted in the lifting housing, a lifting motor fixedly connected with the lifting stabilizing plate, a lifting driving shaft inserted in the lifting motor and penetrating through the lifting stabilizing plate, a lifting driving wheel sleeved on the lifting driving shaft, a lifting driving wheel in transmission connection with the lifting driving wheel, a lifting screw inserted in the lifting driving wheel, a lifting moving plate fixedly connected with the lifting screw, a plurality of groups of lifting guide rods fixedly mounted on the lifting moving plate, and a lifting sliding sleeve respectively matched with the plurality of groups of lifting guide rods and fixedly mounted in the lifting housing;
the lifting transmission wheel is rotationally and continuously impacted with the lifting shell, a bearing is sleeved outside the lifting transmission wheel, and the bearing is fixedly connected with the lifting shell;
the lifting driving shaft penetrates through the lifting driving wheel and coaxially rotates with the limiting assembly;
a transmission belt is arranged between the lifting driving wheel and the lifting transmission wheel;
the lifting work for driving the aircraft engine is completed by designing the lifting assembly, and then the clamping work for the aircraft engine is completed by the clamp assembly.
In a further embodiment, the limiting assembly comprises a limiting input shaft which coaxially rotates with the lifting drive shaft, a limiting ratchet wheel sleeved on the limiting input shaft, a limiting abutting block matched with the limiting ratchet wheel, a limiting hinge frame hinged with the limiting abutting block, a limiting telescopic rod hinged with the limiting hinge frame, and a limiting cylinder sleeved on the limiting telescopic rod;
the limiting cylinder is fixedly connected with the limiting lifting and stabilizing plate; the limiting abutting block is hinged with the lifting stable plate;
the limiting ratchet wheel is provided with a ratchet matched with the limiting abutting block;
after the aircraft engine is lifted, the limiting work of the lifting assembly is finished through the limiting assembly, so that the phenomenon that the lifting assembly is dislocated due to the fact that the aircraft engine is too heavy is avoided;
when the lifting driving shaft drives the lifting driving wheel to rotate, further drives the lifting lead screw to rotate, and further drives the lifting moving plate to descend, the lifting driving shaft simultaneously drives the limiting input shaft to rotate, and further drives the limiting ratchet wheel to rotate clockwise;
after lifting unit stopped the lift work, control spacing cylinder through handheld terminal this moment and drive spacing telescopic link and extend, and then drive spacing articulated frame and move, and then drive spacing piece and carry out the butt with spacing ratchet, accomplish the spacing work of lift to lifting unit.
In a further embodiment, the clamp assembly comprises a clamp fixing plate fixedly connected with the lifting moving plate, and two groups of clamp units which are fixedly arranged on the clamp fixing plate and symmetrically arranged;
each group of clamp units comprises a clamp cylinder fixedly mounted on the clamp fixing plate, a clamp telescopic rod inserted in the clamp cylinder, a clamp convex block hinged with the clamp telescopic rod, a clamp input shaft inserted in the clamp convex block, a clamp arm sleeved on the clamp input shaft, a supporting block cylinder fixedly connected with the clamp fixing plate, a supporting block telescopic shaft inserted in the supporting block cylinder, and a clamp supporting block fixedly connected with the supporting block telescopic shaft.
In a further embodiment, a camera is further mounted on the fixture fixing plate;
the gallows is external handheld terminal, still be equipped with the warning light on the gallows.
A deflection method of an intelligent aircraft engine deflection device comprises the following steps:
step 4, after the aircraft engine is clamped, the orientation of the aircraft engine is changed through the rotating assembly, the rotating motor is controlled to rotate through the handheld terminal, the rotating input shaft is driven to rotate, the rotating disc is driven to rotate, the lifting assembly and the clamp assembly are driven to rotate, and the orientation of the aircraft engine is driven to change;
step 5, when the aircraft engine needs to be shifted, the aircraft engine is driven to be shifted through the sliding assembly, the sliding motor is controlled to work through the handheld terminal, the sliding driving shaft is driven to rotate, the sliding driving gear is driven to rotate, the sliding driving left gear and the sliding driving right gear are driven to rotate along the meshing rack, and the sliding assembly drives the clamp assembly to complete the shifting work;
and 7, after the aircraft engine is lifted, the limiting work of the lifting assembly is completed through the limiting assembly, and the phenomenon that the lifting assembly is dislocated due to the fact that the aircraft engine is too heavy is avoided.
Has the advantages that: the invention discloses an intelligent aircraft engine deflection device, which is characterized in that a brake disc and a brake are designed to complete the limiting work of a rotating assembly and the inertia limiting generated in the process of driving the rotating assembly to rotate an aircraft engine, an upper deflection rod of the brake and a lower deflection rod of the brake are used for driving an upper deflection block of the brake and a lower deflection block of the brake to approach, so that the upper deflection block of the brake and the lower deflection block of the brake abut against the brake disc, the limiting work of the rotating assembly and the inertia limiting generated in the process of driving the rotating assembly to rotate the aircraft engine are completed, the overweight of the aircraft engine is avoided, the phenomenon that the preset position and the actual position of the aircraft engine are not consistent when the orientation of the aircraft engine is changed due to inertia influence when the aircraft engine rotates is avoided, and meanwhile, the aircraft engine is braked, so that the collision and damage are.
Drawings
Fig. 1 is a schematic structural view of the present invention.
Figure 2 is a schematic view of the glide assembly of the present invention.
Figure 3 is a schematic view of the rotating assembly of the present invention.
Fig. 4 is a schematic view of the lift assembly of the present invention.
Figure 5 is a schematic view of a stop assembly of the present invention.
FIG. 6 is a schematic view of a clamp assembly of the present invention.
Figure 7 is a schematic view of a brake disc of the present invention.
Fig. 8 is a schematic diagram of the brake of the present invention.
FIG. 9 is a schematic view of the walking assembly of the present invention.
Reference numerals: the device comprises a walking assembly 1, a walking motor 11, a walking guide rod 12, a walking screw rod 13, a walking bottom plate 14, an upright post 2, a clamp assembly 3, a clamp cylinder 31, a clamp telescopic rod 32, a clamp fixing plate 33, a clamp lug 34, a clamp input shaft 35, a clamp arm 36, a block abutting cylinder 37, a clamp abutting block 38, a block abutting telescopic shaft 39, a sliding assembly 4, a sliding motor 41, a sliding transmission left gear 42, a sliding driving shaft 43, a sliding driving gear 44, a sliding transmission right gear 45, a sliding fixing plate 46, a sliding fixing rod 47, a sliding connecting plate 48, a sliding following wheel 49, a sliding bottom plate 50, a lifting assembly 5, a rotating motor 51, a brake disc 52, a brake stop frame 521, a brake stop upper shift rod 522, a brake stop upper shift block 523, a brake stop lower shift block 524, a brake stop lower shift rod 525, a brake 55, a rotating input shaft 53, a rotating disc 54, a cross frame 6, a lifting motor, A limiting ratchet wheel 611, a limiting input shaft 612, a limiting abutting block 613, a limiting hinge frame 614, a limiting telescopic rod 615, a limiting cylinder 616, a lifting driving wheel 62, a lifting screw 63, a lifting transmission wheel 64, a lifting shell 65, a lifting moving plate 66, a lifting sliding sleeve 67, a lifting guide rod 68 and a lifting stabilizing plate 69.
Detailed Description
Through research and analysis of the applicant, the reason for the problem (the preset position of the conventional aircraft engine is not consistent with the actual position when the orientation of the conventional aircraft engine is changed) is that when the aircraft engine needs to be shifted, the conventional mode is to complete the shifting operation of the aircraft engine through a gantry crane, and when the orientation of the aircraft engine needs to be changed, the conventional mode is to generally mount a rotating mechanism on the gantry crane to complete the changing of the orientation of the aircraft engine, but when the orientation of the aircraft engine is changed, because the gravity of the aircraft engine is too heavy, the aircraft engine generates inertia when rotating, and the preset position of the mechanism driving the aircraft engine to change the orientation is often not consistent with the actual position The nature is spacing, shift the pole through stopping to go up shifting the pole and stopping to shift the pole and drive the braking to go up shifting the piece and the braking shifts down and be close to, and then make the braking to go up shifting the piece and shift down with the braking and carry out the butt brake disc, and then accomplish spacing work and the rotating assembly of rotation subassembly and drive the inertia spacing of aircraft engine rotation process production, avoid because aircraft engine's gravity is overweight, aircraft engine is when rotatory, because inertia influences, preset position when the aircraft engine changes the orientation is not accorded with actual position, brake simultaneously, avoid aircraft engine to appear the collision damage.
An intelligent aircraft engine indexing device comprising: the device comprises a walking assembly 1, a walking motor 11, a walking guide rod 12, a walking screw rod 13, a walking bottom plate 14, an upright post 2, a clamp assembly 3, a clamp cylinder 31, a clamp telescopic rod 32, a clamp fixing plate 33, a clamp lug 34, a clamp input shaft 35, a clamp arm 36, a block abutting cylinder 37, a clamp abutting block 38, a block abutting telescopic shaft 39, a sliding assembly 4, a sliding motor 41, a sliding transmission left gear 42, a sliding driving shaft 43, a sliding driving gear 44, a sliding transmission right gear 45, a sliding fixing plate 46, a sliding fixing rod 47, a sliding connecting plate 48, a sliding following wheel 49, a sliding bottom plate 50, a lifting assembly 5, a rotating motor 51, a brake disc 52, a brake stop frame 521, a brake stop upper shift rod 522, a brake stop upper shift block 523, a brake stop lower shift block 524, a brake stop lower shift rod 525, a brake 55, a rotating input shaft 53, a rotating disc 54, a cross frame 6, a lifting motor, A limiting ratchet wheel 611, a limiting input shaft 612, a limiting abutting block 613, a limiting hinge frame 614, a limiting telescopic rod 615, a limiting cylinder 616, a lifting driving wheel 62, a lifting screw 63, a lifting transmission wheel 64, a lifting shell 65, a lifting moving plate 66, a lifting sliding sleeve 67, a lifting guide rod 68 and a lifting stabilizing plate 69.
An intelligent aircraft engine shifts device includes: the walking assembly comprises a walking assembly 1 fixedly installed on the ground and a hanging bracket fixedly connected with the walking assembly 1; the hanger comprises an upright post 2 fixedly connected with the walking assembly 1, a cross frame 6 fixedly connected with the upright post 2, a sliding assembly 4 matched with the cross frame 6, a rotating assembly fixedly connected with the sliding assembly 4, a lifting assembly 5 fixedly connected with the rotating assembly, and a clamp assembly 3 fixedly connected with the lifting assembly 5;
a brake 55 matched with the rotating assembly is fixedly arranged below the sliding assembly 4.
The walking assembly 1 comprises a walking bottom plate 14 fixedly mounted on the ground, a walking motor 11 fixedly connected with the walking bottom plate 14, a walking screw rod 13 coaxially rotating with the walking motor 11, and a walking slider sleeved on the walking screw rod 13 and fixedly connected with the upright post 2;
and a walking guide rod 12 inserted in the walking slider is fixedly arranged on the walking bottom plate 14.
The transverse frame 6 is an I-shaped transverse frame 6; the lifting device is fixedly provided with a meshing rack;
the sliding component 4 comprises two groups of sliding units which are matched with the meshing rack and are arranged in parallel, each group of sliding units comprises a sliding transmission left gear 42 and a sliding transmission right gear 45 which are matched with the meshing rack, a sliding drive gear 44 engaged with the sliding drive left gear 42 and the sliding drive right gear 45, a sliding drive shaft 43 inserted into the sliding drive gear 44, a sliding motor 41 in transmission connection with the sliding driving shaft 43, a sliding fixing plate 46 sleeved on the sliding driving shaft 43, a sliding fixing rod 47 fixedly connected with the sliding fixing plate 46, a sliding connecting plate 48 fixedly connected with the sliding fixing rod 47, a sliding follow-up shaft inserted in the sliding connecting plate 48, a sliding follow-up wheel 49 sleeved on the sliding follow-up shaft and abutted against the cross frame 6, and a sliding bottom plate 50 fixedly installed below the sliding connecting plate 48;
the sliding transmission left gear 42 and the sliding transmission right gear 45 are rotatably connected with the sliding fixing plate 46.
The rotating assembly comprises a rotating motor 51 fixedly installed below a sliding bottom plate 50, a rotating input shaft 53 inserted in the rotating motor 51, a brake disc 52 and a rotating disc 54 which are fixedly connected with the rotating input shaft 53 and are arranged in parallel;
a brake 55 adapted to the brake disc 52 is further fixedly mounted below the slide base plate 50.
The brake 55 comprises a brake connecting rod fixedly connected with the sliding bottom plate 50, a brake frame 521 fixedly connected with the brake connecting rod, a brake upper shift rod 522 and a brake lower shift rod 525 fixedly connected with the brake frame 521, a brake upper shift block 523 fixedly connected with the brake upper shift rod 522, and a brake lower shift block 524 fixedly connected with the brake lower shift rod 525;
a plurality of groups of grooves are formed on the brake disc 52;
the brake disc 52 is provided with a buffer block with a preset radian; meanwhile, a buffer block is designed to buffer inertia;
The lifting assembly 5 comprises a lifting shell 65 fixedly connected with the rotating disc 54, a lifting stabilizing plate 69 fixedly installed in the lifting shell 65, a lifting motor 61 fixedly connected with the lifting stabilizing plate 69, a lifting driving shaft inserted in the lifting motor 61 and penetrating through the lifting stabilizing plate 69, a lifting driving wheel 62 sleeved on the lifting driving shaft, a lifting driving wheel 64 in transmission connection with the lifting driving wheel 62, a lifting screw 63 inserted in the lifting driving wheel 64, a lifting moving plate 66 fixedly connected with the lifting screw 63, a plurality of groups of lifting guide rods 68 fixedly installed on the lifting moving plate 66, and lifting sliding sleeves 67 respectively matched with the plurality of groups of lifting guide rods 68 and fixedly installed in the lifting shell 65;
the lifting transmission wheel 64 is in rotary continuous impact with the lifting shell 65, a bearing is sleeved outside the lifting transmission wheel 64, and the bearing is fixedly connected with the lifting shell 65;
the lifting driving shaft penetrates through the lifting driving wheel 62 and coaxially rotates with the limiting assembly;
a transmission belt is arranged between the lifting driving wheel 62 and the lifting transmission wheel 64;
the lifting work for driving the aircraft engine is completed by designing the lifting assembly 5, and then the clamping work for the aircraft engine is completed by the clamp assembly 3.
The limiting assembly comprises a limiting input shaft 612 which coaxially rotates with the lifting drive shaft, a limiting ratchet 611 which is sleeved on the limiting input shaft 612, a limiting abutting block 613 which is matched with the limiting ratchet 611, a limiting hinge frame 614 which is hinged with the limiting abutting block 613, a limiting telescopic rod 615 which is hinged with the limiting hinge frame 614, and a limiting cylinder 616 which is sleeved on the limiting telescopic rod 615;
the limit cylinder 616 is fixedly connected with the limit lifting and stabilizing plate 69; the limiting abutting block 613 is hinged to the lifting stabilizing plate 69;
the limiting ratchet wheel 611 is provided with a ratchet matched with the limiting abutting block 613;
after the aircraft engine is lifted, the limiting work of the lifting assembly 5 is finished through the limiting assembly, so that the phenomenon that the lifting assembly 5 is dislocated due to the fact that the aircraft engine is too heavy is avoided;
when the lifting driving shaft drives the lifting driving wheel 62 to rotate, and further drives the lifting driving wheel 64 to rotate, and further drives the lifting screw 63 to rotate, and further drives the lifting moving plate 66 to descend, the lifting driving shaft simultaneously drives the limiting input shaft 612 to rotate, and further drives the limiting ratchet 611 to rotate clockwise;
after the lifting assembly 5 stops lifting, the handheld terminal controls the limiting cylinder 616 to drive the limiting telescopic rod 615 to extend, so as to drive the limiting hinge frame 614 to move, and further drive the limiting support block 613 to abut against the limiting ratchet wheel 611, so that the lifting limiting work of the lifting assembly 5 is completed.
The clamp assembly 3 comprises a clamp fixing plate 33 fixedly connected with the lifting moving plate 66 and two groups of clamp units which are fixedly arranged on the clamp fixing plate 33 and symmetrically arranged;
each group of clamp units comprises a clamp cylinder 31 fixedly mounted on the clamp fixing plate 33, a clamp expansion rod 32 inserted in the clamp cylinder 31, a clamp projection 34 hinged to the clamp expansion rod 32, a clamp input shaft 35 inserted in the clamp projection 34, a clamp arm 36 sleeved on the clamp input shaft 35, a resisting block cylinder 37 fixedly connected with the clamp fixing plate 33, a resisting block telescopic shaft 39 inserted in the resisting block cylinder 37, and a clamp resisting block 38 fixedly connected with the resisting block telescopic shaft 39; the clamp fixing plate 33 is also provided with a camera; the hanger is externally connected with a handheld terminal and is also provided with a warning lamp; the design camera is mainly in order to carry out and input engine size, both ends diameter and fixed pivot position through handheld terminal, carries out and controls anchor clamps subassembly 3 through the camera cooperation and accomplish the work of lifting by crane to aircraft engine.
Description of the working principle: when the aircraft engine needs to be steered and shifted, the traveling assembly 1 works at the moment, so that the hanger is driven to move to the position above the aircraft engine, and the warning lamp is turned on when the shifting device works;
at the moment, the handheld terminal controls the traveling motor 11 to work, so that the traveling screw rod 13 is driven to rotate, the traveling slide block is driven to move, and the hanger is driven to move until the hanger moves above the aircraft engine;
after the hanger frame is moved above the aircraft engine, the lifting assembly 5 is controlled by the handheld terminal to move the clamp assembly 3 to a proper clamping position;
firstly, the handheld terminal controls a lifting motor 61 to work, so as to drive a lifting driving shaft to rotate, further drive a lifting driving wheel 62 to rotate, further drive a lifting driving wheel 64 to rotate, further drive a lifting screw 63 to rotate, further drive a lifting moving plate 66 to lift, further drive a clamp assembly 3 to lift, and further complete the movement of the clamp assembly 3;
after the clamp assembly 3 moves to the proper position, the size of the engine, the diameters of two ends and the position of a fixed fulcrum are input through a handheld terminal, and the clamp assembly 3 is controlled through the cooperation of a camera to complete the hoisting work of the aircraft engine;
at the moment, the handheld terminal controls the two groups of clamp units to approach to each other, so that the clamping work of the aircraft engine is finished;
firstly, the clamp cylinder 31 drives the clamp telescopic rod 32 to move, so as to drive the clamp lug 34 to swing, further drive the clamp input shaft 35 to rotate, further drive the clamp arm 36 to swing, and further enable the clamp arm 36 to clamp the aircraft engine;
after the aircraft engine is clamped, the abutting block air cylinder 37 works to drive the abutting block telescopic shaft 39 to work, and the clamp abutting block 38 is driven to abut against the aircraft engine to avoid the phenomenon that the aircraft engine shakes;
after the aircraft engine is clamped, the orientation of the aircraft engine is changed through the rotating assembly, firstly, the rotating motor 51 is controlled to rotate through the handheld terminal, so that the rotating input shaft 53 is driven to rotate, the rotating disc 54 is driven to rotate, the lifting assembly 5 and the clamp assembly 3 are driven to rotate, and the orientation change of the aircraft engine is further completed;
when the aircraft engine needs to be shifted, the aircraft engine is driven to be shifted through the sliding assembly 4, the sliding motor 41 is controlled to work through the handheld terminal, the sliding driving shaft 43 is driven to rotate, the sliding driving gear 44 is driven to rotate, the sliding transmission left gear 42 and the sliding transmission right gear 45 are driven to rotate along the meshing rack, and the sliding assembly 4 drives the clamp assembly 3 to complete the shifting work;
when the direction of the aircraft engine is adjusted, the brake 55 is used for finishing the limiting work of the rotating assembly and the inertia limiting generated in the rotating process of the aircraft engine driven by the rotating assembly;
the upper brake shifting block 523 and the lower brake shifting block 525 are driven to approach through the upper brake shifting rod 522 and the lower brake shifting rod 525, so that the upper brake shifting block 523 and the lower brake shifting block abut against the brake disc 52, and the limiting work of the rotating assembly and the inertia limiting generated in the rotating process of the rotating assembly driving the aircraft engine are completed;
after the aircraft engine is lifted, the limiting work of the lifting assembly 5 is finished through the limiting assembly, so that the phenomenon that the lifting assembly 5 is dislocated due to the fact that the aircraft engine is too heavy is avoided;
when the lifting driving shaft drives the lifting driving wheel 62 to rotate, and further drives the lifting driving wheel 64 to rotate, and further drives the lifting screw 63 to rotate, and further drives the lifting moving plate 66 to descend, the lifting driving shaft simultaneously drives the limiting input shaft 612 to rotate, and further drives the limiting ratchet 611 to rotate clockwise;
after the lifting assembly 5 stops lifting, the handheld terminal controls the limiting cylinder 616 to drive the limiting telescopic rod 615 to extend, so as to drive the limiting hinge frame 614 to move, and further drive the limiting support block 613 to abut against the limiting ratchet wheel 611, so that the lifting limiting work of the lifting assembly 5 is completed.
The preferred embodiments of the present invention have been described in detail with reference to the accompanying drawings, however, the present invention is not limited to the specific details of the embodiments, and various equivalent changes can be made to the technical solution of the present invention within the technical idea of the present invention, and these equivalent changes are within the protection scope of the present invention.
Claims (10)
1. The utility model provides an intelligent aircraft engine device that shifts, characterized by includes:
the lifting device comprises a walking assembly fixedly arranged on the ground and a lifting frame fixedly connected with the walking assembly;
the hanger comprises an upright post fixedly connected with the walking assembly, a cross frame fixedly connected with the upright post, a sliding assembly matched with the cross frame, a rotating assembly fixedly connected with the sliding assembly, a lifting assembly fixedly connected with the rotating assembly and a clamp assembly fixedly connected with the lifting assembly;
and a brake matched with the rotating assembly is fixedly arranged below the sliding assembly.
2. An intelligent aircraft engine indexing device according to claim 1, wherein: the walking assembly comprises a walking bottom plate fixedly mounted on the ground, a walking motor fixedly connected with the walking bottom plate, a walking screw rod coaxially rotating with the walking motor, and a walking slider sleeved on the walking screw rod and fixedly connected with the stand column;
and a walking guide rod inserted in the walking sliding block is fixedly arranged on the walking bottom plate.
3. An intelligent aircraft engine indexing device according to claim 1, wherein: the transverse frame is an I-shaped transverse frame; the lifting device is fixedly provided with a meshing rack;
the sliding assembly comprises two groups of sliding units which are matched with the meshing rack and arranged in parallel, each group of sliding units comprises a sliding transmission left gear and a sliding transmission right gear which are matched with the meshing rack, a sliding drive gear which is meshed with the sliding transmission left gear and the sliding transmission right gear, a sliding drive shaft which is inserted in the sliding drive gear, a sliding motor which is in transmission connection with the sliding drive shaft, a sliding fixed plate which is sleeved on the sliding drive shaft, a sliding fixed rod which is fixedly connected with the sliding fixed plate, a sliding connecting plate which is fixedly connected with the sliding fixed rod, a sliding follow-up shaft which is inserted in the sliding connecting plate, a sliding follow-up wheel which is sleeved on the sliding follow-up shaft and is abutted against the cross frame, and a sliding bottom plate which is fixedly arranged below the sliding connecting plate;
and the sliding transmission left gear and the sliding transmission right gear are rotationally connected with the sliding fixing plate.
4. An intelligent aircraft engine indexing device according to claim 1, wherein: the rotating assembly comprises a rotating motor fixedly arranged below the sliding bottom plate, a rotating input shaft inserted in the rotating motor, a brake disc and a rotating disc, wherein the brake disc and the rotating disc are fixedly connected with the rotating input shaft and are arranged in parallel;
and a brake stopper matched with the brake disc is fixedly arranged below the sliding bottom plate.
5. An intelligent aircraft engine indexing device according to claim 4, wherein: the brake device comprises a sliding bottom plate, a brake upper shifting rod, a brake lower shifting rod, a brake upper shifting block and a brake lower shifting block, wherein the brake upper shifting rod is fixedly connected with the sliding bottom plate;
the brake disc is provided with a plurality of groups of grooves;
and the brake disc is provided with a buffer block with a preset radian.
6. An intelligent aircraft engine indexing device according to claim 1, wherein: the lifting assembly comprises a lifting shell fixedly connected with the rotating disc, a lifting stabilizing plate fixedly arranged in the lifting shell, a lifting motor fixedly connected with the lifting stabilizing plate, a lifting driving shaft inserted in the lifting motor and penetrating through the lifting stabilizing plate, a lifting driving wheel sleeved on the lifting driving shaft, a lifting driving wheel in transmission connection with the lifting driving wheel, a lifting lead screw inserted in the lifting driving wheel, a lifting moving plate fixedly connected with the lifting lead screw, a plurality of groups of lifting guide rods fixedly arranged on the lifting moving plate, and a lifting sliding sleeve respectively matched with the plurality of groups of lifting guide rods and fixedly arranged in the lifting shell;
the lifting transmission wheel is rotationally and continuously impacted with the lifting shell, a bearing is sleeved outside the lifting transmission wheel, and the bearing is fixedly connected with the lifting shell;
the lifting driving shaft penetrates through the lifting driving wheel and coaxially rotates with the limiting assembly;
and a transmission belt is arranged between the lifting driving wheel and the lifting transmission wheel.
7. An intelligent aircraft engine indexing device according to claim 6, wherein: the limiting assembly comprises a limiting input shaft which coaxially rotates with the lifting driving shaft, a limiting ratchet wheel sleeved on the limiting input shaft, a limiting abutting block matched with the limiting ratchet wheel, a limiting hinge frame hinged with the limiting abutting block, a limiting telescopic rod hinged with the limiting hinge frame and a limiting cylinder sleeved on the limiting telescopic rod;
the limiting cylinder is fixedly connected with the limiting lifting and stabilizing plate; the limiting abutting block is hinged with the lifting stable plate;
and the limiting ratchet wheel is provided with ratchets matched with the limiting abutting block.
8. An intelligent aircraft engine indexing device according to claim 1, wherein: the clamp assembly comprises a clamp fixing plate fixedly connected with the lifting moving plate and two groups of clamp units which are fixedly arranged on the clamp fixing plate and symmetrically arranged;
each group of clamp units comprises a clamp cylinder fixedly mounted on the clamp fixing plate, a clamp telescopic rod inserted in the clamp cylinder, a clamp convex block hinged with the clamp telescopic rod, a clamp input shaft inserted in the clamp convex block, a clamp arm sleeved on the clamp input shaft, a supporting block cylinder fixedly connected with the clamp fixing plate, a supporting block telescopic shaft inserted in the supporting block cylinder, and a clamp supporting block fixedly connected with the supporting block telescopic shaft.
9. An intelligent aircraft engine indexing device according to claim 8, wherein: the clamp fixing plate is also provided with a camera;
the gallows is external handheld terminal, still be equipped with the warning light on the gallows.
10. A deflection method of an intelligent aircraft engine deflection device is characterized by comprising the following steps:
step 1, when an aircraft engine needs to be steered and shifted, a walking assembly works at the moment, so that a hanger is driven to move to the position above the aircraft engine, a warning lamp is turned on when a shifting device works, and the warning lamp is turned off after the shifting device finishes working;
step 2, after the hanger is moved above the aircraft engine, the lifting assembly is controlled by the handheld terminal to move the clamp assembly to a proper clamping position;
step 3, after the clamp assembly moves to the adaptive position, inputting the size of the engine, the diameters of two ends and the position of a fixed fulcrum through a handheld terminal, and controlling the clamp assembly to complete the lifting work of the aircraft engine through the cooperation of a camera;
step 4, after the aircraft engine is clamped, the orientation of the aircraft engine is changed through the rotating assembly, the rotating motor is controlled to rotate through the handheld terminal, the rotating input shaft is driven to rotate, the rotating disc is driven to rotate, the lifting assembly and the clamp assembly are driven to rotate, and the orientation of the aircraft engine is driven to change;
step 5, when the aircraft engine needs to be shifted, the aircraft engine is driven to be shifted through the sliding assembly, the sliding motor is controlled to work through the handheld terminal, the sliding driving shaft is driven to rotate, the sliding driving gear is driven to rotate, the sliding driving left gear and the sliding driving right gear are driven to rotate along the meshing rack, and the sliding assembly drives the clamp assembly to complete the shifting work;
step 6, when the direction of the aircraft engine is adjusted, the brake is used for finishing the limiting work of the rotating assembly and the inertia limiting generated in the process that the rotating assembly drives the aircraft engine to rotate;
and 7, after the aircraft engine is lifted, the limiting work of the lifting assembly is completed through the limiting assembly, and the phenomenon that the lifting assembly is dislocated due to the fact that the aircraft engine is too heavy is avoided.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011591735.8A CN112723180A (en) | 2020-12-29 | 2020-12-29 | Intelligent airplane engine position changing device and position changing method thereof |
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| CN202011591735.8A CN112723180A (en) | 2020-12-29 | 2020-12-29 | Intelligent airplane engine position changing device and position changing method thereof |
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| CN202011591735.8A Pending CN112723180A (en) | 2020-12-29 | 2020-12-29 | Intelligent airplane engine position changing device and position changing method thereof |
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