CN108907618A - A kind of aircraft skin mirror image milling postpositive disposal method - Google Patents
A kind of aircraft skin mirror image milling postpositive disposal method Download PDFInfo
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- CN108907618A CN108907618A CN201810734132.5A CN201810734132A CN108907618A CN 108907618 A CN108907618 A CN 108907618A CN 201810734132 A CN201810734132 A CN 201810734132A CN 108907618 A CN108907618 A CN 108907618A
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- mirror image
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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
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Abstract
The present invention relates to a kind of mechanical manufacturing technology, especially a kind of aircraft skin mirror image milling postpositive disposal method.A kind of aircraft skin mirror image milling postpositive disposal method, includes the following steps：Step 1: in the knife rail compilation process of CAM software, according to skin thickness to be processed, identify the knife rail statement interlude of different processing thickness.Meanwhile according to the milling of skin thickness mirror image, trimming, drilling processing, the knife rail statement interlude of different Processing Strategies is identified；Step 2: reading the cutter location file of CAM software output, the ownership of discrete knife rail point is determined according to above- mentioned information；Step 3: the NC program and thickness mirror image milling NC program of trimming and drilling processing are calculated according to the ownership of discrete knife rail point and point position and vector, wherein discrete knife rail point bit format, that is, preposition cutter location is：,For preposition tool position,For preposition generating tool axis vector,Indicate covering editing objective wall thickness；Step 4: step 3 is constantly repeated, until the equal postposition of entire aircraft skin mirror image milling APT file is the output of NC program.The present invention has the following advantages that：1, situation existing for different calculation methods has been fully considered.2, algorithm foundation is provided for the application of mirror image milling device.
Description
Technical field
The present invention relates to a kind of mechanical manufacturing technology, especially a kind of aircraft skin mirror image milling postpositive disposal method.
Background technique
Since the milling of aircraft skin mirror image has compared with traditional milling, high-precision, small pollution, energy consumption be small, primary dress
Folder completes the advantages that covering processing, is the Typical Representative of aviation green manufacture technology.But how by the program of CAM software programming
Being converted to the identifiable NC program of lathe is to realize the premise of aircraft skin mirror image milling.
Five-axis machine tool postpositive disposal only needs preposition APT file translation, calculates, is converted to the identifiable NC program of lathe,
And aircraft skin mirror image milling device is double five axis equipment, the position of milling cutter and posture shore dress with cooperateing in milling process
The position and posture moment set are mirrored into relationship, synchronous synergetic movement.Therefore, need to calculate the position of main shaft in mirror image milling
And posture, while needing to calculate position and the posture of supporting device.For the milling of skin thickness mirror image, trimming, drilling processing three
Kind processing technology, is needed to distinguish it, be interpreted using different marks.
Summary of the invention
The purpose of the present invention is the APT point program for double five axis mirror image milling attachment machining prgramings outputs is only five axis
Milling head cutter location provides a kind of aircraft skin mirror image milling postpositive disposal method.
To achieve the goals above, the present invention adopts the following technical scheme that：A kind of aircraft skin mirror image milling postpositive disposal
Method includes the following steps：
Step 1: in the knife rail compilation process of CAM software, according to skin thickness to be processed, identify different processing thickness
Knife rail statement interlude.Meanwhile according to the milling of skin thickness mirror image, trimming, drilling processing, the knife rail sentence of different Processing Strategies is identified
Section；
Step 2: reading the cutter location file of CAM software output, the ownership of discrete knife rail point is determined according to above- mentioned information；
Step 3: according to the ownership of discrete knife rail point and point position and vector calculate trimming and drilling processing NC program and
Thickness mirror image milling NC program, wherein discrete knife rail point bit format, that is, preposition cutter location is：,For preposition tool position,For preposition generating tool axis vector,Indicate covering processing
Target wall thickness；
Step 4: step 3 is constantly repeated, until the equal postposition of entire aircraft skin mirror image milling APT file is that the output of NC program is
Only.
Preferably, the aircraft skin mirror image milling postpositive disposal method is：
（1）Supporting device position processing method：According to preposition generating tool axis vectorWith target wall thicknessSupporting device vector can be calculated, and then calculate supporting device position, specially：
（2）The implementation method of thickness mirror image milling NC program：
1. when milling head and supporting device are C-A double pendulum header structure, milling head rotating shaft angle、Pass through machine where milling head
Bed motion chain carries out translation and rotary motion coordinate transform obtains：
Coordinate transform：
Solving result is：
WhereinTranslational coordination for machine tool rotary coordinate system relative to Cutter coordinate system converts,For tool coordinate system phase
Translational coordination transformation for machine tool rotary coordinate system；
Supporting device angle of revolution、For,, by the preposition point of knife position
Be converted to mirror image milling NC journey：。
2. when milling head is C-A double pendulum header structure, when supporting device is B-A double pendulum header structure, milling head rotating shaft angle、
It is obtained according to method described in 1., supporting device angle of revolution、It is translated and is turned round by supporting device kinematic chain
The coordinates of motion convert to obtain：
Coordinate transform：
Solving result is：
WhereinCoordinate system is turned round for supporting device to convert relative to the translational coordination of Cutter coordinate system,For supporting device
Translational coordination transformation of the driving point coordinate system relative to supporting device revolution coordinate system；
By the preposition point of knife positionBe converted to mirror image milling NC program：。
（3）The implementation method of trimming NC program is：It presses（2）Described in method obtain milling head rotating shaft angle、, by knife
The preposition point of positionBe converted to trimming NC program：。
（4）Drilling NC program implementation method be：According to（2）Described in method obtain milling head rotating shaft angle、, by knife position
Preposition pointBe converted to drilling NC program：。
Principle：According to five axis milling head cutter locations obtain cutter point and rotation angle, mirror image supporting device operation point and
Rotate angle, export the NC program of double five axis mirror image millings, guarantee in mirror image milling process the position of milling cutter and posture with
The position and posture moment for cooperateing with supporting device are mirrored into relationship, synchronous synergetic movement.When milling head rotating shaft angle or shore dress
Gyration is put back into there are when multiple groups value, if the angle not excess of stroke, according to angle change minimum value；If the angle excess of stroke, setting safety
Distance, preposition cutter location, cutter and supporting device are along respective normal vector calculating point position in space before recording the excess of stroke, i.e., actually
Cutter and supporting device are carried away along respective normal direction in process.Then angle of revolution is transformed to minimum value, before obtaining the excess of stroke
The new NC program of preposition cutter location.
The present invention has the following advantages that：
1, the present invention has distinguished the milling of skin thickness mirror image, trimming, three kinds of processing technologys of drilling processing and different milling thick layers,
Situation existing for different calculation methods is fully considered.
2, the invention proposes aircraft skin mirror image milling device postpositive disposal method, can by different skin thickness, no
With processing technology preposition file it is translated, be calculated as double identifiable NC codes of five axis mirroring devices and code format, be mirror
As the application of milling device provides algorithm foundation.
Detailed description of the invention
Fig. 1 is aircraft skin mirror image milling coordinate system；
Fig. 2 is that aircraft skin mirror image milling milling head and supporting device are servo-actuated schematic diagram；
In figure, 1, workpiece；2, cutter；3, milling head；4, supporting device；Wherein,For workpieces processing coordinate system；For tool coordinate system；Coordinate system is turned round for milling head；For supporting device
Driving point coordinate system；Coordinate system is turned round for supporting device；Indicate covering editing objective workpiece；For
Preposition tool position；For preposition generating tool axis vector；For supporting device vector；Position is shored for supporting device.
Specific embodiment
1-2 is further described the present invention with reference to the accompanying drawing：Step 1: in the knife rail compilation process of CAM software,
According to skin thickness to be processed, identify the knife rail statement interlude of different processing thickness.Meanwhile according to the milling of skin thickness mirror image,
Trimming, drilling processing identify the knife rail statement interlude of different Processing Strategies.
THKTAR/Skin thickness to be processedMark
MILL/START thickness mirror image milling mark
DRILL/START drilling mark
TRIM/ START trimming mark
Step 2: reading the cutter location file of CAM software output, the ownership of discrete knife rail point is determined according to above-mentioned identification information.
The appearance until next mark is read after certain is identified, indicates that the program determines to belong to according to above-mentioned mark.
Step 3: calculating the NC journey of trimming and drilling processing according to the ownership of discrete knife rail point and point position and vector
Sequence and thickness mirror image milling NC program, wherein discrete knife rail point bit format, that is, preposition cutter location is：,For preposition tool position,For preposition generating tool axis vector,Indicate covering processing
1 wall thickness of target workpiece.
The thickness mirror image milling NC program refers to that reading thickness mirror image milling mark is carried out decision procedure section needs and passed through
Mirror image Post-processing Algorithm obtains NC program；Thickness value is read, coordinate transform is turned round by vector and space and is solved, is obtained
Milling head rotates angle, supporting device point and rotation angle, obtains NC program, guarantees milling cutter 2 in mirror image milling process
Position and posture are mirrored into relationship, synchronous synergetic movement with the position and posture moment for cooperateing with supporting device 4.Concrete methods of realizing
For：
（1）Supporting device position processing method：According to preposition generating tool axis vectorWith target wall thicknessSupporting device vector can be calculated, and then calculate supporting device position, specially：
（2）The implementation method of thickness mirror image milling NC program：
1. when milling head 3 and supporting device 4 are C-A double pendulum header structure, milling head rotating shaft angle、By where milling head
Machine tool motion chain carries out translation and rotary motion coordinate transform obtains.
Machine coordinates transformation where milling head：
WhereinTranslational coordination for machine tool rotary coordinate system relative to Cutter coordinate system converts,
Translational coordination for tool coordinate system relative to machine tool rotary coordinate system converts.Lathe translation and spin matrix are where milling head：
Solving result is：
To be mirrored into relationship, supporting device angle of revolution when guaranteeing milling、For,.It will
The preposition point of knife positionBe converted to mirror NC program：
.It is verified for following face thickness mark, mirror image milling mark and preposition cutter location.
THKTAR/ 1.2
MILL/START
GOTO/ 627.54356,-1022.85924,291.14575, 0.014675,0.564550,0.825268
Use obtain after mirror image processing algorithm result for：
THCKTARGET 1.200
X627.544 Y-1022.859 Z291.146 A-34.384 C-1.489 XA=627.526 YA=-1023.537 ZA=
290.155 AA=34.371 CA=-1.489
2. when milling head 3 is C-A double pendulum header structure, when supporting device 4 is B-A double pendulum header structure, milling head rotating shaft angle、
It is obtained according to method described in 1., supporting device angle of revolution、It is translated and is turned round by supporting device kinematic chain
The coordinates of motion convert to obtain.
Supporting device coordinate transform：
WhereinCoordinate system is turned round for supporting device to convert relative to the translational coordination of Cutter coordinate system,The translational coordination for driving point coordinate system to turn round coordinate system relative to supporting device for supporting device converts.Shore dress
Horizontalization moves and spin matrix is：
Solving result is：
By the preposition point of knife positionBe converted to mirror image NC program：,
Guarantee to be mirrored into relationship when milling.It is verified for following face thickness mark, mirror image milling mark and preposition cutter location.
THKTAR/ 1.2
MILL/START
GOTO/ 627.54356,-1022.85924,291.14575, 0.014675,0.564550,0.825268
Use obtain after mirror image processing algorithm result for：
THCKTARGET 1.200
X627.544 Y-1022.859 Z291.146 A-34.384 C-1.489 XA=627.526
YA=-1023.537 ZA=290.155 AA=-34.371 BA=1.019
The NC program of the trimming refer to read trimming mark come decision procedure section need according to（2）Described in method milled
Head rotating shaft angle、, by the preposition point of knife positionBe converted to trimming NC program：。
The NC program of the drilling refer to read trimming mark come decision procedure section need according to（2）Described in method obtain
Milling head rotating shaft angle、, by the preposition point of knife positionBe converted to drilling NC program：。
The milling head rotating shaft angle or supporting device angle of revolution is there are when multiple groups value, if the angle not excess of stroke, according to
Angle change minimum value；If the angle excess of stroke, safe distance is set, preposition cutter location before the excess of stroke is recorded, cutter and shores dress
It sets and calculates point position in space along respective normal vector, i.e., cutter and supporting device are carried away along respective normal direction during actual processing.So
Angle of revolution is transformed to minimum value afterwards, the new NC program of preposition cutter location before the acquisition excess of stroke.
Step 4: step 3 is constantly repeated, until the equal postposition of entire aircraft skin mirror image milling APT file is that NC program is defeated
Until out.
Claims (5)
1. a kind of aircraft skin mirror image milling postpositive disposal method, it is characterised in that：Include the following steps：
Step 1:, according to skin thickness δ to be processed, identifying the knife of different processing thickness in the knife rail compilation process of CAM software
Rail statement interlude.Meanwhile according to the milling of skin thickness mirror image, trimming, drilling processing, the knife rail sentence of different Processing Strategies is identified
Section；
Step 2: reading the cutter location file of CAM software output, the ownership of discrete knife rail point is determined according to above- mentioned information；
Step 3: according to the ownership of discrete knife rail point and point position and vector calculate trimming and drilling processing NC program and
Thickness mirror image milling NC program, wherein discrete knife rail point bit format, that is, preposition cutter location is：X, Y, Z, I, J, K,For preposition tool position,For preposition generating tool axis vector, δ indicates that covering adds
Work target wall thickness；
Step 4: step 3 is constantly repeated, until the equal postposition of entire aircraft skin mirror image milling APT file is that the output of NC program is
Only.
2. aircraft skin mirror image milling postpositive disposal method according to claim 1, it is characterised in that：The thickness mirror image
The implementation method of milling NC program is：
(1) supporting device position processing method：According to preposition generating tool axis vectorSupporting device vector can be calculated with target wall thickness δAnd then calculate supporting device positionSpecially：
(2) implementation method of thickness mirror image milling NC program：
1. milling head rotating shaft angle A, C are transported by lathe where milling head when milling head and supporting device are C-A double pendulum header structure
Dynamic chain carries out translation and rotary motion coordinate transform obtains：
Coordinate transform：
Solving result is：
Wherein T1MTranslational coordination for machine tool rotary coordinate system relative to Cutter coordinate system converts, T2MFor tool coordinate system relative to
The translational coordination of machine tool rotary coordinate system converts；
Supporting device angle of revolution AA, CA AA=-A, CA=C, by the preposition point X, Y, Z of knife position, I, J, K is converted to mirror image
Milling NC journey：X, Y, Z, A, C, XA, YA, ZA, AA, CA；
2. when supporting device is B-A double pendulum header structure, milling head rotating shaft angle A, C are according to 1. when milling head is C-A double pendulum header structure
The method obtains, and supporting device angle of revolution AA, BA carries out translation by supporting device kinematic chain and rotary motion coordinate becomes
It gets in return：
Coordinate transform：
Solving result is：
Wherein T1HIt turns round coordinate system for supporting device to convert relative to the translational coordination of Cutter coordinate system, T2HFor supporting device driving
Translational coordination transformation of the point coordinate system relative to supporting device revolution coordinate system；
By the preposition point X, Y, Z of knife position, I, J, K is converted to mirror image milling NC program：X, Y, Z, A, C, XA, YA, ZA, AA, BA.
3. aircraft skin mirror image milling postpositive disposal method according to claim 2, it is characterised in that：The trimming NC journey
The implementation method of sequence is：Milling head rotating shaft angle A, C are obtained according to method described in (2), by preposition point X, Y, the Z of knife position,
I, J, K are converted to trimming NC program：X, Y, Z, A, C.
4. aircraft skin mirror image milling postpositive disposal method according to claim 2, it is characterised in that：The drilling NC journey
The implementation method of sequence is：Milling head rotating shaft angle A, C are obtained according to method described in (2), by preposition point X, Y, the Z of knife position,
I, J, K are converted to drilling NC program：X, Y, Z, A, C.
5. aircraft skin mirror image milling postpositive disposal method described in any claim, feature in -4 according to claim 1
It is：The milling head rotating shaft angle or supporting device angle of revolution is there are when multiple groups value, if the angle not excess of stroke, according to angle
Change minimum value.
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| CN201810734132.5A CN108907618A (en) | 2018-07-06 | 2018-07-06 | A kind of aircraft skin mirror image milling postpositive disposal method |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110703685A (en) * | 2019-11-08 | 2020-01-17 | 中国航空制造技术研究院 | Skin mirror image milling cutter path self-adaptive adjusting method and device |
| CN110737245A (en) * | 2019-11-18 | 2020-01-31 | 上海拓璞数控科技股份有限公司 | Post-processing method and system for double five-axis mirror milling |
| CN110756868A (en) * | 2019-11-18 | 2020-02-07 | 中航成飞民用飞机有限责任公司 | Milling system and method |
| CN112965442A (en) * | 2021-02-01 | 2021-06-15 | 中国航空制造技术研究院 | Cooperative motion control method and system for mirror milling |
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