CN110977349B - Machining process for aero-engine moving bracket - Google Patents
Machining process for aero-engine moving bracket Download PDFInfo
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- CN110977349B CN110977349B CN201911268793.4A CN201911268793A CN110977349B CN 110977349 B CN110977349 B CN 110977349B CN 201911268793 A CN201911268793 A CN 201911268793A CN 110977349 B CN110977349 B CN 110977349B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
Abstract
The invention relates to a machining process of a movable bracket of an aero-engine, which relates to the technical field of metal machining and solves the problem that the machining precision is reduced by adopting a laser cutting mode; according to the processing reference point, cutting the aluminum material to be processed through a cutter according to a preset support plate model; thinning the cut support plate through a machining center to machine the base, and keeping a preset machining distance; placing the base and the contact plane for a preset time; performing finish machining through a cutter according to the preset size of the support plate model; defining one side of the base connected with the support plate as a reference surface, and processing one side of the base away from the support plate to obtain a mounting surface parallel to the reference surface, wherein the distance between the reference surface and the mounting surface is a preset processing distance. The present invention has the effect of improving the processing accuracy of the aluminum material.
Description
Technical Field
The invention relates to the technical field of metal processing, in particular to a processing technology of a mobile bracket of an aero-engine.
Background
The aircraft engine is a highly complex and precise thermal machine, and is used as the heart of an aircraft, not only as the power for flying the aircraft, but also as an important driving force for promoting the development of aviation industry.
When the aircraft engine is transported, the aircraft engine is mounted on the movable support so as to move.
In the prior art, for example, chinese patent No. CN105215357A, a method for laser rapid prototyping of aluminum, aluminum alloy and aluminum-based composite materials, includes steps of establishing a geometric model by using a computer to generate a prototyping path; step two, manufacturing a vacuum or protective gas processing environment; step three, supplying raw materials to a processing area, melting the supplied raw materials by using laser with the wavelength of 700-900nm, judging whether the processing is finished or not, if not, entering step three, scanning the next layer, if so, entering step five, and cleaning and recycling redundant supplied raw materials in step five; and step six, taking out the product. The high absorptivity of the aluminum, the aluminum alloy and the aluminum-based composite material to the laser with the wavelength of 700nm-900nm is fully utilized, the reflection of the aluminum, the aluminum alloy and the aluminum-based composite material to the laser is reduced to the maximum extent, the energy utilization efficiency in the forming process is high, the forming speed is high, the forming precision is high, and the rapidness of 3D printing is realized.
The above prior art solutions have the following drawbacks: when the aluminum material is cut by laser, the aluminum material can be deformed by being heated, and the laser cutting mode can cause the processing precision to be reduced and has room for improvement.
Disclosure of Invention
The invention aims to provide a machining process of a movable support of an aero-engine, which improves the machining precision of an aluminum material.
The above object of the present invention is achieved by the following technical solutions:
a machining process for a movable support of an aircraft engine comprises the following steps:
acquiring a processing reference point of an aluminum material to be processed;
according to the processing reference point, cutting the aluminum material to be processed through a cutter according to a preset support plate model;
thinning the cut support plate through a machining center to machine the base, and keeping a preset machining distance;
placing the base and the contact plane for a preset time;
performing finish machining through a cutter according to the preset size of the support plate model;
defining one side of the base, which is connected with the support plate, as a reference surface, and processing one side of the base, which is far away from the support plate, so as to obtain an installation surface which is parallel to the reference surface, wherein the distance between the reference surface and the installation surface is a preset processing distance;
punching the support plate according to the machining reference point and a preset support plate model to complete support plate machining;
the universal wheel is welded on the chassis, the gasket is welded on one side of the chassis far away from the universal wheel, and the support plate and the gasket are fixed through the bolt.
Through adopting above-mentioned technical scheme, the inquiry of setpoint is conveniently carried out to the processing reference point, in order to make things convenient for later processing, in processing, the mode that adopts the cutter cutting is processed, and the base adopts the mode of thinning to process, thereby improve the wholeness of product, and through placing radiating placing, and when placing, adopt vertical placing, not only improved the area of contact with the air, conveniently form the oxide film, also can improve radiating ability simultaneously, processing back because the temperature is too high, the material of aluminium can take place to warp, vertical placing can also improve the elimination of internal stress, after the cooling, carrying out finish machining, the precision of processing has been improved, the quality of product has also been improved, and process the installation face, thereby improve holistic installation stability.
The invention is further configured to: the method comprises the following steps:
obtaining the current distance between a gasket and a plane after the gasket is welded with a chassis;
and correcting the current distance to the distance reference value according to the comparison relationship between the current distance and the preset distance reference value.
Through adopting above-mentioned technical scheme, weld back earlier with gasket and chassis, inspect the distance between gasket to the plane again to process and correct, with stability and the accuracy nature that improves holistic, the practicality is strong.
The invention is further configured to: the method comprises the following steps:
obtaining the current levelness between a gasket and a plane after the gasket is welded with a chassis;
and correcting the current levelness to the levelness reference value according to the comparison relationship between the current distance and the preset levelness reference value.
Through adopting above-mentioned technical scheme, weld back earlier gasket and chassis, inspect the distance between gasket to the plane again to process and correct, with improvement holistic stationarity and accuracy nature, the practicality is strong.
The invention is further configured to: the method for cutting the aluminum material to be processed comprises the following steps:
processing an installation groove for placing an aircraft engine on the aluminum material to be processed according to the processing reference point;
and after the mounting groove is cut, verifying the machining reference point again, and machining a weight reduction groove on the aluminum material to be machined.
Through adopting above-mentioned technical scheme, the mounting groove is cut out earlier, and the material under the cutting can also supply other spare parts to process the use, processes to subtracting the heavy groove again to improve holistic intensity, in case when cutting earlier and subtract the heavy groove, will be because of the high problem that leads to whole deformation of temperature.
The invention is further configured to: the method comprises the following steps:
according to the machining reference point, the cutting directions of the mounting groove and the weight reduction groove are all cut from the direction close to the machining reference point to the direction far away from the machining reference point;
cutting the single weight reduction groove from the position close to the machining reference point, wherein the initial point of cutting is one side far away from the mounting groove and close to the machining reference point, and the cutting moving direction is one side close to the mounting groove;
defining the number of the weight reduction grooves as N, arranging the weight reduction grooves from a position close to a machining reference point to a position far away from the machining reference point, and sequentially setting the number of the weight reduction grooves as 1 and 2 … … N;
the first cutting sequence of the lightening slots is 2N-1 and the second cutting sequence is 2N.
By adopting the technical scheme, when the mounting groove and the weight reducing groove are machined, the cutting is carried out by taking the machining reference point as the starting point, and the temperature residue is considered after the machining is carried out, so that the mounting groove is machined firstly, the weight reducing groove is machined at the starting point position when the mounting groove is machined, and the machining is carried out in an interval machining mode, and the machining efficiency is improved.
The invention is further configured to: the method comprises the following steps:
and after the preset time, soaking the support plate in the water, keeping the base in contact with the contact plane of the water bottom, and keeping the preset holding time.
Through adopting above-mentioned technical scheme, through soaking the support in aqueous, cool off through the temperature, also through the buoyancy of water simultaneously to improve the internal stress of product, reduce the deformation that the product leads to because of weight, the practicality is strong.
The invention is further configured to: the device comprises a container for storing water for soaking a support plate, wherein a water inlet is formed in the bottom of the container, a water outlet is formed in the top of the container, the water inlet and the water outlet are arranged on the same side, and a circulating water pump and a cooling water tank for cooling the water are connected between the water inlet and the water outlet;
acquiring current water temperature information of water in a current container;
controlling the on-off of the circulating water pump according to the comparison relationship between the current water temperature information and preset water temperature reference values;
if the temperature corresponding to the water temperature information at that time is greater than or equal to the temperature corresponding to the water temperature reference value, starting the circulating water pump; otherwise, the circulating water pump is closed.
Through adopting above-mentioned technical scheme, the water in the container carries out the heat exchange through cooling trough and circulating water pump, controls the temperature simultaneously to improve the controllability of temperature, thereby make the extension board refrigerated more effective, the practicality is strong.
The invention is further configured to: the method comprises the following steps:
when the cutter head cuts the aluminum material, the processing surface is blown by the blowing device, and the blowing device blows out towards the processing reference point.
Through adopting above-mentioned technical scheme, blow to the machined surface through blast apparatus to reduce the temperature of machined surface, and blow off from the processing reference point, can avoid hiding of processing reference point, improve the discernment degree, can blow off the piece simultaneously, reduce the interference, the practicality is strong.
The invention is further configured to: the method comprises the following steps:
acquiring current surface temperature information before processing of an aluminum material to be processed;
controlling the machining of the cutter according to the comparison relationship between the current surface temperature information and a preset temperature reference value;
and if the temperature corresponding to the surface temperature information is greater than or equal to the temperature corresponding to the temperature reference value, the cutter is not machined, and the blowing device is controlled to blow air.
Through adopting above-mentioned technical scheme, through detecting the surface temperature before processing to improved the detection to the machined surface, made the cutter when cutting, judged the temperature, thereby control wind device and cool down, with the deformation of reducing man-hour.
The invention is further configured to: the method comprises the following steps:
acquiring current processing temperature information during processing of an aluminum material to be processed;
and searching out the machining parameters of the cutter from a preset machining temperature database according to the current machining temperature information, and controlling the rotating speed and the moving speed of the cutter according to the machining parameters.
Through adopting above-mentioned technical scheme, through detecting the processing temperature to the rotational speed and the translation rate of cutter are controlled, thereby reduce the internal stress, have played the effect that improves product quality, and the practicality is strong.
In conclusion, the beneficial technical effects of the invention are as follows:
1. the processing precision of the aluminum material is improved;
2. reduce the residual of internal stress and improve the product quality.
Drawings
Fig. 1 is a schematic structural view of a mobile bracket.
FIG. 2 is a schematic view of a process flow for a support plate.
Fig. 3 is a schematic structural view of the plate.
Fig. 4 is a schematic view of the structure of the cooling soak.
In the figure, 1, a machining reference point; 2. a base; 3. a reference plane; 4. a mounting surface; 5. a support plate; 6. a universal wheel; 7. a chassis; 8. a gasket; 9. a weight reduction groove; 10. and (4) mounting the groove.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
Referring to fig. 1 and 4, the machining process of the mobile bracket of the aero-engine disclosed by the invention comprises the following steps of:
and S100, acquiring a machining reference point 1 of the aluminum material to be machined.
The machining reference point 1 is a virtual point defined by a user, and the point is convenient for a machine tool system to identify so as to conveniently judge the aluminum material during machining of the cutter, so that accurate machining can be performed.
And S101, according to the machining reference point 1, cutting the aluminum material to be machined through a cutter according to a preset support plate 5 model.
Through the discernment to processing reference point 1 to process the aluminum product, the aluminum product has extension board 5 models before processing, and extension board 5 models are predetermined model, for the model after the user needs to process the completion, thereby process the aluminum product through extension board 5 models to process out extension board 5 of corresponding size.
And S102, thinning the cut support plate 5 through a machining center to machine the base 2, and keeping the preset machining distance.
When the support plate 5 is thinned, the area which is not thinned is reserved, the thinned area is thinned on two sides, so that the support plate is processed into a T-shaped plate, the upper end part is the base 2, the lower end part is the support plate 5, meanwhile, a preset processing distance is reserved when the support plate is processed, and the processing distance is 3mm in the embodiment.
Step S103, placing the base 2 and the contact plane for a preset time.
After the preliminary machining is completed, the plate is placed so as to be cooled and eliminate a large amount of internal stress generated during the machining of the cutter. When placing, adopt vertical mode of placing, and base 2 places with contact plane, contact plane can be ground also can be horizontal planes such as desktop. The time of placing is set by the staff, and under normal state, the air is placed normally for 7 days.
And S104, performing finish machining through a cutter according to the preset size of the support plate 5 model.
The support plate 5 model has accurate dimensions, and a machining distance of 3mm is reserved during primary machining. At the moment, finish machining is carried out through a cutter, redundant distance is removed, the reserved distance of 3mm is eliminated in a normal state, the consistency of the sizes of the machined support plate 5 and the support plate 5 model is guaranteed, when more machining or less machining is needed, machining larger than or smaller than 3mm can be carried out, and the sizes of the support plate 5 and the support plate 5 model are kept as the standard.
Step S105, defining one side of the base 2 connected with the support plate 5 as a reference surface 3, and processing one side of the base 2 away from the support plate 5 to obtain a mounting surface 4 parallel to the reference surface 3, wherein the distance between the reference surface 3 and the mounting surface 4 is a preset processing distance.
When the finish machining is performed, a folding angle between the base 2 and the support plate 5 is machined by a cutter, so that an L-shaped folding angle is generated, wherein the angle is 90 degrees, and therefore, the side where the base 2 is connected with the support plate 5 is defined as a reference surface 3.
And the other side of the base 2 is processed, i.e. the side placed against the contact plane. And after obtaining the reference surface 3, processing the mounting surface 4 to obtain the mounting surfaces 4 which are parallel to each other, wherein the distance between the reference surface 3 and the mounting surface 4 refers to the dimension in the support plate 5 model, and is a preset processing distance which can be adjusted by a user according to the actual situation. For example based on the weight of the aircraft engine on which it is placed.
And S106, punching the support plate 5 according to the machining reference point 1 and the preset support plate 5 model to finish machining the support plate 5.
And punching the support plate 5 after the finish machining according to the support plate 5 model, thereby finishing the machining of the support plate 5.
And S107, welding the universal wheel 6 to the chassis 7, welding the gasket 8 to one side of the chassis 7 far away from the universal wheel 6, and fixing the support plate 5 and the gasket 8 through bolts.
The universal wheels 6 are welded on the chassis 7, the chassis 7 is a standard size member purchased in advance, and the universal wheels 6 are provided with four universal wheels and are arranged at four corners of the chassis 7. Gasket 8 is located between chassis 7 and the extension board 5, and gasket 8 and base 2 welded fastening, and gasket 8 is fixed through the bolt with the support, and the fixed position is base 2 on the support.
Referring to fig. 1, when the gasket 8 is mounted, the overall height of the welded gasket 8 is detected to improve the overall accuracy. The detection steps are as follows:
and step S200, acquiring the current distance between the gasket 8 and the plane after the gasket 8 is welded with the chassis 7.
After the pad 8 has been welded to the chassis 7, the distance between the pad 8 and the contact plane is measured, i.e. the height of the pad 8 plus the height of the chassis 7 plus the height of the castor 6. During measurement, the measurement can be carried out in a manual detection mode, and the detection can also be carried out in an ultrasonic ranging mode, so that the current distance is obtained.
And step S201, correcting the current distance to a distance reference value according to the comparison relationship between the current distance and a preset distance reference value.
The distance reference value is a preset distance, and the detected distance is compared with the distance reference value. Under conventional state, the distance that detects can be greater than the distance benchmark value, need polish gasket 8 this moment through the instrument to reduce gasket 8's height, thereby carry out holistic regulation.
Referring to fig. 1, while the height of the spacer 8 is adjusted, the flatness of the spacer 8, i.e., the levelness of the upper surface of the spacer 8, is also adjusted, and the adjusting steps are as follows:
and step S300, acquiring the current levelness between the gasket 8 and the plane after the gasket 8 is welded with the chassis 7.
The levelness after 8 welding of gasket detects, and 8 when detecting to planar levelness of gasket, can adopt and carry out the mode of finding range to the difference and detect, also can directly detect through the spirit level.
In order to improve the stability of the support plate 5 after installation, the levelness of the upper end of the gasket 8 needs to be strictly controlled, and the gasket 8 is usually too thick, so that the levelness is detected in real time in the process of thinning the gasket 8, and the accuracy is improved.
And S301, correcting the current levelness to a levelness reference value according to the comparison relationship between the current distance and a preset levelness reference value.
The levelness reference value is a horizontal angle, and the horizontal angle is known, so that the inclined state is judged, and the overall stability is improved.
Referring to fig. 2 and 3, the method for cutting the aluminum material to be processed comprises the following steps:
and S400, machining a mounting groove 10 for placing the aircraft engine on the aluminum material to be machined according to the machining reference point 1.
The mounting groove 10 is machined firstly, so that the machining speed is high, and cut materials can be collected to facilitate machining of other materials.
And S401, after the installation groove 10 is cut, verifying the machining reference point 1 again, and machining a weight reduction groove 9 in the aluminum material to be machined.
And then the weight reduction groove 9 is processed, so that the overall processing difficulty is reduced. Since the position of each machining is different, the machining reference point 1 needs to be determined again.
Referring to fig. 2 and 3, in the cutting process, the cutting direction is defined in consideration of the temperature and the positioning, and the cutting process includes the following steps:
and S500, according to the machining reference point 1, cutting the mounting groove 10 and the weight reduction groove 9 from the direction close to the machining reference point 1 to the direction far away from the machining reference point 1.
The mounting groove 10 and the weight-reducing groove 9 are cut in a mode of being close to the machining reference point 1 and being far away from the machining reference point 1.
Step S501, cutting the single weight-reducing slot 9 from the side close to the machining reference point 1, where the initial point of cutting is the side far from the mounting slot 10 and close to the machining reference point 1, and the moving direction of cutting is the side close to the mounting slot 10.
When the weight-reducing grooves 9 are machined, the cutting is carried out in a circular machining mode.
Step S502, defining the number of the weight-reducing grooves 9 as N, arranging the weight-reducing grooves from being close to the machining reference point 1 to being far from the machining reference point 1, and sequentially setting the number of the weight-reducing grooves as 1 and 2 … … N;
the first cutting sequence of the lightening slots 9 is 2N-1 and the second cutting sequence is 2N.
Referring to FIG. 2, if there are 6 weight-reducing slots 9, the number is P1-1, P1-2, P1-3, P2-1, P2-2 and P2-3 in the order shown in the figure. And the processing sequence of the weight-reducing grooves 9 is analogized.
When cutting the aluminum product through the tool bit, in order to reduce the temperature on surface and reduce the piece on surface, when the tool bit cuts the aluminum product, blow to the machined surface through blast apparatus, blast apparatus can select according to actual demand, in this embodiment, the preference direct current fan.
During blowing, the blowing device blows towards the processing reference point 1, so that the wind direction of blowing is unified, and the installation and arrangement of the dividing device are automatically set by workers, which is common knowledge of technicians in the field and is not described herein.
When the tool bit is used for machining, the temperature of the machined aluminum product is detected in an infrared temperature measurement mode, and the detection mode is as follows:
and S600, acquiring current surface temperature information before the aluminum material to be processed is processed.
The surface temperature information is the current pre-processing temperature of the aluminum material to be processed, and the temperature is detected by adopting an infrared thermometer.
And step S601, controlling the machining of the cutter according to the comparison relationship between the current surface temperature information and a preset temperature reference value.
The temperature reference value is a temperature preset by a worker, and can be adjusted according to the current environment, and is preferably 24 ℃ in the embodiment. And comparing the temperature before machining with a preset temperature reference value so as to control the machining of the cutter.
And step S602, if the temperature corresponding to the surface temperature information is greater than or equal to the temperature corresponding to the temperature reference value, the cutter is not machined, and the blowing device is controlled to blow air.
And when the temperature corresponding to the surface temperature information is greater than or equal to the temperature corresponding to the temperature reference value, the cutter is not machined temporarily, and meanwhile, the air blowing device is controlled to blow air continuously so as to cool.
When the temperature drops below 24 ℃, the cutter can process, and the temperature of the processing state is detected, wherein the detection control mode is as follows:
and S700, acquiring current processing temperature information during processing of the aluminum material to be processed.
The processing temperature information adopts an infrared thermometer to detect the temperature, the detection position is adjusted according to the actual condition and is adjusted by workers, and the temperature of the position of the unprocessed position is preferentially detected, wherein the position is the edge being processed.
And step S701, searching out the machining parameters of the tool from a preset machining temperature database according to the current machining temperature information, and controlling the rotating speed and the moving speed of the tool according to the machining parameters.
As the cutter has the highest rotating speed and the lowest rotating speed, the moving speed is increased when the rotating speed is increased; when the rotating speed is reduced, the moving speed is also reduced.
The processing temperature database is provided with information of rotating speed and moving speed corresponding to different temperatures, and is configured by a worker, and the rotating speed and the moving speed of the tool are controlled through processing parameters.
When cooling, the cooling speed is slow by adopting a mode of placing in air, so that the cooling can be carried out in the air and then adding water for cooling, and the cooling method comprises the following steps:
after the preset time, the support plate 5 is soaked in the water, and the base 2 is kept in contact with the contact plane of the water bottom for the preset holding time.
At this moment, after the support plate 5 is placed in the water for cooling after the preset time, the support plate 5 is placed in the water for cooling, when the support plate 5 is placed in the water, the base 2 is in contact with a contact plane at the bottom of the water, the preset holding time for soaking and cooling in the water is controlled, and the holding time is set by a worker, so that the quality of the support plate 5 is ensured. The support plate 5 soaked in water is cooled more uniformly and is cooled more quickly.
Referring to fig. 4, when the support plates 5 are cooled in water, the water is stored in a container, and a plurality of support plates 5 can be put into the container at the same time, so that the temperature of the water is increased, and the temperature is reduced through a cooling water tank.
The container is used for depositing the water of soaking extension board 5, and places in order to supply extension board 5, and the bottom of container is the plane, and the bottom of container is provided with the water inlet, and the top of container is provided with the delivery port, and the water inlet sets up in same one side with the delivery port to conveniently carry out the interaction of rivers, be connected with circulating water pump and be used for carrying out the refrigerated cooling trough with water between water inlet and the delivery port.
The circulating water pump is used for pumping water in the cooling water tank to the bottom of the container, the water is pumped out from the water outlet after passing through the support plate 5, and the height of the water level in the container is higher than that of the water outlet. Preferentially adopt the air to cool off water among the cooling trough, adopt the mode of waterfall, pour water into the cooling trough from last to down, for improving the cooling effect, in the cooling trough, also be provided with the stirring fan blade that carries out the stirring through the motor to improve refrigerated effect.
And the water cooling steps are as follows:
and step S800, acquiring current water temperature information of water in the current container.
The temperature in the tank is detected by a temperature sensor, and water temperature information is output.
And step S801, controlling the on-off of the circulating water pump according to the comparison relationship between the current water temperature information and preset water temperature reference values.
The water temperature reference value is the water temperature during cooling, in the embodiment, the water temperature is set to be 24 ℃, and the opening and the closing of the circulating water pump are controlled through temperature comparison.
Step S802, if the temperature corresponding to the water temperature information at that time is greater than or equal to the temperature corresponding to the water temperature reference value, starting a circulating water pump; otherwise, the circulating water pump is closed.
Once the water temperature is higher than or equal to the water temperature reference value, the circulating water pump is started, and the motor and the stirring fan blades can synchronously stir.
And once the water temperature is lower than the water temperature reference value, the circulating water pump is closed, the motor and the stirring fan blades are synchronously stirred at the moment, the stirring is delayed, and the stirring is stopped after 2 min.
The embodiments of the present invention are preferred embodiments of the present invention, and the scope of the present invention is not limited by these embodiments, so: all equivalent changes made according to the structure, shape and principle of the invention are covered by the protection scope of the invention.
Claims (10)
1. The machining process of the aero-engine moving bracket is characterized by comprising the following steps of:
acquiring a processing reference point (1) of an aluminum material to be processed;
according to the processing reference point (1), cutting the aluminum material to be processed through a cutter according to a preset support plate (5) model;
thinning the cut support plate (5) through a machining center to machine the base (2), and keeping a preset machining distance;
placing the base (2) and the contact plane for a preset time;
performing finish machining through a cutter according to the preset size of the model of the support plate (5);
defining one side of the base (2) connected with the support plate (5) as a reference surface (3), and processing one side of the base (2) far away from the support plate (5) to obtain an installation surface (4) parallel to the reference surface (3), wherein the distance between the reference surface (3) and the installation surface (4) is a preset processing distance;
punching the support plate (5) according to the machining reference point (1) and a preset support plate (5) model to finish machining the support plate (5);
the universal wheel (6) is welded on the chassis (7), the gasket (8) is welded on one side, far away from the universal wheel (6), of the chassis (7), and the support plate (5) and the gasket (8) are fixed through bolts.
2. The machining process of the aircraft engine moving bracket according to claim 1, characterized in that: the method comprises the following steps:
obtaining the current distance between the gasket (8) and a contact plane after the gasket (8) is welded with the chassis (7);
and correcting the current distance to the distance reference value according to the comparison relationship between the current distance and the preset distance reference value.
3. The machining process of the aircraft engine moving bracket according to claim 1, characterized in that: the method comprises the following steps:
obtaining the current levelness between the gasket (8) and a contact plane after the gasket (8) is welded with the chassis (7);
and correcting the current levelness to the levelness reference value according to the comparison relationship between the current distance and the preset levelness reference value.
4. The machining process of the aircraft engine moving bracket according to claim 1, characterized in that: the method for cutting the aluminum material to be processed comprises the following steps:
according to the processing reference point (1), processing an installation groove (10) for placing an aircraft engine on an aluminum material to be processed;
and after the mounting groove (10) is cut, verifying the machining reference point (1) again, and machining a weight reduction groove (9) on the aluminum material to be machined.
5. The machining process of the aircraft engine moving bracket according to claim 4, characterized in that: the method comprises the following steps:
according to the machining reference point (1), cutting directions of the mounting groove (10) and the weight reduction groove (9) are all cut from the direction close to the machining reference point (1) to the direction far away from the machining reference point (1);
cutting the single weight-reducing groove (9) from a position close to the machining reference point (1), wherein the initial point of cutting is one side far away from the mounting groove (10) and close to the machining reference point (1), and the cutting moving direction is one side close to the mounting groove (10);
defining the number of the weight reducing grooves (9) as N, arranging the weight reducing grooves from a position close to the machining reference point (1) to a position far away from the machining reference point (1), and sequentially setting the number of the weight reducing grooves as 1 and 2 … … N, wherein N is a positive integer;
the first cutting sequence of the weight-reducing grooves (9) is 2N-1 and the second cutting sequence is 2N.
6. The machining process of the aircraft engine moving bracket according to claim 1, characterized in that: the method comprises the following steps:
after the preset time, the support plate (5) is soaked in the water, the base (2) is kept in contact with the contact plane of the water bottom, and the preset holding time is kept.
7. The machining process of the aircraft engine moving bracket according to claim 6, characterized in that: the device comprises a container for storing water for soaking a support plate (5), wherein a water inlet is formed in the bottom of the container, a water outlet is formed in the top of the container, the water inlet and the water outlet are arranged on the same side, and a circulating water pump and a cooling water tank for cooling the water are connected between the water inlet and the water outlet;
acquiring current water temperature information of water in a current container;
controlling the on-off of the circulating water pump according to the comparison relationship between the current water temperature information and preset water temperature reference values;
if the temperature corresponding to the water temperature information at that time is greater than or equal to the temperature corresponding to the water temperature reference value, starting the circulating water pump; otherwise, the circulating water pump is closed.
8. The machining process of the aircraft engine moving bracket according to claim 1, characterized in that: the method comprises the following steps:
when the cutter head cuts the aluminum material, the blowing device blows air to the processing surface, and the blowing device blows air to the processing reference point (1).
9. The machining process of the aircraft engine moving bracket according to claim 1, characterized in that: the method comprises the following steps:
acquiring current surface temperature information before processing of an aluminum material to be processed;
controlling the machining of the cutter according to the comparison relationship between the current surface temperature information and a preset temperature reference value;
and if the temperature corresponding to the surface temperature information is greater than or equal to the temperature corresponding to the temperature reference value, the cutter is not machined, and the blowing device is controlled to blow air.
10. The machining process of the aircraft engine moving bracket according to claim 1, characterized in that: the method comprises the following steps:
acquiring current processing temperature information during processing of an aluminum material to be processed;
and searching out the machining parameters of the cutter from a preset machining temperature database according to the current machining temperature information, and controlling the rotating speed and the moving speed of the cutter according to the machining parameters.
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| CN103770046A (en) * | 2012-10-18 | 2014-05-07 | 长沙市天映机械制造有限公司 | High accuracy frame for aircraft assembling tool and machining method thereof |
| CN104439975A (en) * | 2014-11-28 | 2015-03-25 | 吴中区光福华宇钣金厂 | Processing technology of supports |
| CN104626075A (en) * | 2014-12-15 | 2015-05-20 | 天津迎新船舶机械有限公司 | Deformation-preventing support and machining method thereof |
| CN105215357A (en) * | 2015-09-22 | 2016-01-06 | 重庆塞拉雷利科技有限公司 | Aluminium, aluminium alloy and aluminum matrix composite laser fast forming method |
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| KR101693642B1 (en) * | 2010-12-21 | 2017-01-17 | 삼성전자 주식회사 | Manufacturing method of Light emitting device package |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103770046A (en) * | 2012-10-18 | 2014-05-07 | 长沙市天映机械制造有限公司 | High accuracy frame for aircraft assembling tool and machining method thereof |
| CN104439975A (en) * | 2014-11-28 | 2015-03-25 | 吴中区光福华宇钣金厂 | Processing technology of supports |
| CN104626075A (en) * | 2014-12-15 | 2015-05-20 | 天津迎新船舶机械有限公司 | Deformation-preventing support and machining method thereof |
| CN105215357A (en) * | 2015-09-22 | 2016-01-06 | 重庆塞拉雷利科技有限公司 | Aluminium, aluminium alloy and aluminum matrix composite laser fast forming method |
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