CN102248379B - Method for processing back-spraying hole in shell of rocket chamber by using conventional boring machine - Google Patents
Method for processing back-spraying hole in shell of rocket chamber by using conventional boring machine Download PDFInfo
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- CN102248379B CN102248379B CN 201110183386 CN201110183386A CN102248379B CN 102248379 B CN102248379 B CN 102248379B CN 201110183386 CN201110183386 CN 201110183386 CN 201110183386 A CN201110183386 A CN 201110183386A CN 102248379 B CN102248379 B CN 102248379B
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Abstract
The invention discloses a method for processing a back-spraying hole in a shell of a rocket chamber by using a conventional boring machine. The method comprises the following steps of: (1) aligning and assembling a special tool; (2) aligning and assembling the shell; (3) aligning a space angle of the back-spraying hole; (4) aligning the space location of the back-spraying hole; (5) processing a No.1 back-spraying hole; (6) aligning and processing a No. 3 back-spraying hole; (7) aligning a No.2 back-spraying hole; and (8) aligning and processing No.2 and No.4 back-spraying holes. By adopting a series of special aligning and clamping tools, the back-spraying holes in the shell of the rocket chamber are processed by using the conventional boring machine, the processing precision is high, and the requirement for product designing precision is completely met; compared with processing by using an imported high-precision numerical controlled boring machine, the processing by using the method provided by the invention has the advantage that the equipment cost is remarkably reduced.
Description
Technical field
The present invention relates to the process technology of rocket chamber housing, refer to particularly a kind of method with regurgitating the hole on the common boring machine processing rocket chamber housing.
Background technology
Solid propellant rocket is the power set of aerospace craft, is comprised of major parts such as combustion chamber, propellant charge, jet pipe, igniters.Burning chamber shell is the key component in the all-solid system, and the burning by propellant provides power for aircraft.There are four uniform bands to regurgitate the joint of regurgitating in hole on the housing front head, regurgitate installed thrust termination mechanism in the hole, cylindrical thread connection mozzle.When aircraft arrives the precalculated position, missile-borne computer sends separates quick-fried instruction, thrust termination mechanism is separated quick-fried, pressure release is regurgitated in the combustion gas of engine propellant from regurgitate the hole, under the acting in conjunction of escape engine, guarantee that engine is negative thrust or zero thrust to the reentry body of aircraft, reaches the position of accurate control reentry body, thereby guarantees the positional precision of expection.Therefore, angle, the positional precision of regurgitating the hole there is higher designing requirement.
The technological process of burning chamber shell is: skirt benchmark before and after assembly welding → annealing → radiographic inspection → quenching+tempering → radiographic inspection → car → boring processing front end → boring processing rear end → water pressure test → form and position tolerance detection → oil sealing packing warehouse-in, finish when boring processing front end in four uniform holes of regurgitating of housing front end.Regurgitate the hole and all equate with the angle in rocket chamber housing axle center for four on the rocket chamber housing.
At present, four high-precision holes of regurgitating of processing rocket chamber housing front end need numerical control borer expensive, that have the control of high-precision rotary angle and high precision position size Control, have the hole of regurgitating that common boring machine is difficult to machining high-precision now and adopt.
Summary of the invention
Purpose of the present invention will overcome the existing deficiency of prior art exactly, and a kind of method with regurgitating the hole on the common boring machine processing rocket chamber housing is provided.
For achieving the above object, what the present invention was designed processes the method for regurgitating the hole on the rocket chamber housing with common boring machine, may further comprise the steps:
1) centering of special tooling is installed: the dedicated platform centering is installed on the horizontal table of the common boring machine that each axle stroke meets the demands, special stand and special-purpose cutter setting frame centering are installed on the dedicated platform;
2) centering of housing is installed: with the front skirt of rocket chamber housing, rear skirt excircle orientation, the rocket chamber housing is installed on former and later two special stands, makes the level of groove everywhere on front skirt, the rear skirt end face contour;
3) regurgitate hole space angle centering: feeler block level centered by rotating shaft of special-purpose cutter setting frame is turned clockwise locate with latch afterwards, horizontal table, dedicated platform, special stand, special-purpose cutter setting frame and rocket chamber housing level with common boring machine is rotated counterclockwise again, anglec of rotation α is the angle of regurgitating hole and rocket chamber housing axle center on the rocket chamber housing, and the anglec of rotation adopts special-purpose cutter setting frame to proofread and correct;
4) regurgitate locus, hole centering: with horizontal table, rocket chamber housing and the special-purpose cutter setting frame horizontal translation of common boring machine, distance with between the feeler block of the main shaft of sizing slip gauge control common boring machine and special-purpose cutter setting frame makes the center, hole of regurgitating to be processed overlap with the alignment of shafts of common boring machine;
5) 1# regurgitates hole processing: in the taper hole of the main shaft of common boring machine special tool-post is installed, processing, the 1# of centering regurgitates end face, endoporus, outer round thread and the end face dowel hole in hole;
6) 3# regurgitates hole centering, processing: according to 3), 4), 5) described method, the identical angle [alpha] that turns clockwise, the 3# of level of processing direction symmetry regurgitates the hole;
7) 2# regurgitates the hole centering: the pressure ring lid that unclamps special stand, the rocket chamber housing is turned clockwise 90 °, the 1# that the vertical direction centering has been processed, 3# regurgitate the end face dowel hole in hole, reinstall the rocket chamber housing, make unprocessed 2#, 4# regurgitate the hole and be horizontal;
8) 2# and 4# regurgitate hole centering, processing: according to 3), 4), 5), 6) described method, corresponding processing 2# and 4# regurgitate the hole, thereby finish four processing of regurgitating the hole on the rocket chamber housing.
Further, each axle stroke of described common boring machine satisfies following requirement:
The X-axis of common boring machine is horizontal table horizontal direction (being the width of horizontal table), X-axis stroke X with regurgitate the hole end surface center to front skirt end face distance L
1, regurgitate the hole end surface center to front skirt cylindrical distance L
2, the horizontal table centre of gyration is to the distance L of front skirt end face
3, anglec of rotation α, front skirt outside diameter d relationship be X=2[L
3(d/2 L
2)/tg α+L
1] sin α;
The Y-axis of common boring machine is horizontal table longitudinal direction (being the length direction of horizontal table), and Y-axis stroke Y and the horizontal table centre of gyration are to the distance L of front skirt end face
3Relationship be Y=L
3+ 200 ~ 500mm;
The Z axis of common boring machine is the direction perpendicular to horizontal table, and the tangent line of the inner arc surface of the bracket base lower end of the thickness A of Z axis stroke Z and dedicated platform, special stand is Z=A+B+d+300 ~ 700mm to bottom surface, bracket base lower end apart from the front skirt of B, rocket chamber housing and the relationship of rear skirt outside diameter d;
Stroke W=300 ~ the 1000mm of the main shaft of common boring machine.
Further, be provided with the T-shaped groove that special stand and special-purpose cutter setting frame are installed on the end face of described dedicated platform, the horizontal table central alignment of the center of described dedicated platform and common boring machine, and the T-shaped groove of the horizontal table by bolt and nut fastener and common boring machine is fastenedly connected.
Further, the relationship of the front skirt of the length C of described dedicated platform and rocket chamber housing and rear skirt end distance C1 is C=C1+600 ~ 1000mm, the relationship of the width E of described dedicated platform and the front skirt of rocket chamber housing, rear skirt outside diameter d is E=d+200 ~ 400mm, the thickness A of described dedicated platform=200 ~ 400mm.
Further, described special stand comprises pressure ring lid and bracket base, and described pressure ring lid and bracket base location are clamped in the periphery of the front and back skirt of rocket chamber housing, and fastening by bolt and nut fastener; The bottom of described bracket base is provided with flat key, and described flat key is embedded in the T-shaped groove of described dedicated platform, and described special stand is fastenedly connected by bolt and nut fastener and dedicated platform; The arc diameter D that is comprised of pressure ring lid and bracket base equates with the front and back skirt outside diameter d of rocket chamber housing.
Further, described special-purpose cutter setting frame comprises tool rest bracket, and the feeler block that arranges on the described tool rest bracket, rotating shaft and three pin holes are provided with latch in the described pin hole, described feeler block is installed on the center line of tool rest bracket, and described rotating shaft is positioned on the same center line of feeler block one side; Described three pin holes evenly are arranged on the tool rest bracket and are on the same section circular arc, and a middle pin hole is positioned on the same center line of opposite side of feeler block, and two pin holes equate with described anglec of rotation α with middle formed arc chord angle of pin hole respectively in addition; The bottom of described tool rest bracket is embedded in the T-shaped groove of described dedicated platform, and is fastenedly connected by bolt and nut fastener and dedicated platform.
Further, on the described special-purpose cutter setting frame alignment of shafts of feeler block center and common boring machine apart from L
5With regurgitate the hole end surface center to the front skirt end face distance L of rocket chamber housing
1, regurgitate the hole end surface center to the front skirt cylindrical distance L of rocket chamber housing
2, the special-purpose cutter setting frame centre of gyration is to the distance L of the front skirt end face of rocket chamber housing
4, anglec of rotation α, rocket chamber housing the relationship of front skirt outside diameter d be L
5=[(d/2 L
2)/tg α L
1+ L
4] sin α.
Further, described special tool-post comprises handle of a knife, feed mechanism, tool rest and is installed in cutter on the tool rest, and described handle of a knife is connected with the main shaft of common boring machine by the locking wedge, and an end of described feed mechanism is connected with described handle of a knife, and the other end is connected with tool rest.
Further, the flatness error of described dedicated platform is not more than 0.1mm, and the straightness error of the side, location of the T-shaped groove in dedicated platform center is not more than 0.1mm, and the plane position error is not more than 0.1mm on the dedicated platform; The tangent line of the inner arc surface of the bracket base lower end of described two special stands is not more than 0.03mm to the high level error that waits apart from B of bottom surface, bracket base lower end; The angular error of the pin hole of described special-purpose cutter setting frame colonel positive rotation angle is not more than ± 1 ', feeler block side straightness error is not more than 0.005mm;
In the centering installation process of described housing, on the front skirt of rocket chamber housing, the rear skirt end face everywhere the high level error such as groove level be not more than 0.2, the front skirt end face of rocket chamber housing is not more than 0.03mm to special stand front end face range error, and the front skirt end face of rocket chamber housing, endoporus runout error are not more than 0.05mm;
Described regurgitating in the space angle centering process of hole, beat and be not more than 0.015/200mm in the feeler block side;
Described 2# regurgitates in the centering process of hole, and the error that the 1# that vertical direction has been processed up and down, 3# regurgitate the end face dowel hole in hole is not more than 0.02mm.
Beneficial effect of the present invention is: the present invention adopts a series of Special alignings and clamping tooling, with regurgitating the hole on the common boring machine processing rocket chamber housing, has following technique effect:
One, machining accuracy is higher, satisfy the product design required precision fully: the product design documentation requirements is regurgitated axially bored line and shell theory axis angle allowable error and is ± 8', and regurgitating axially bored line is 0.8 ~ 1.3mm with the theoretical position deviation on the plane of crossing the housing axis; Actual machining angle deviation is ± 3' that position deviation is ± 0.2mm.
Its two, compare with the high precision numerical control Boring machine processing that adopts import, significantly reduce equipment cost, the common boring machine price of same size and stroke only has 30 ~ 40% of import numerical control borer price.
Description of drawings
Fig. 1 is for processing the tool structure schematic diagram of regurgitating the hole on the rocket chamber housing with common boring machine.
Fig. 2 is the plan structure schematic diagram of Fig. 1.
Fig. 3 is the infeed stroke of common boring machine among Fig. 1 and regurgitates hole processing translation distance schematic diagram.
Fig. 4 is the plan structure schematic diagram of special-purpose platform among Fig. 1.
Fig. 5 is the left TV structure schematic diagram of Fig. 4.
Fig. 6 is the structure for amplifying schematic diagram of special-purpose support among Fig. 1.
Fig. 7 is the structure for amplifying schematic diagram of special-purpose knife rest among Fig. 1.
Fig. 8 is the structure for amplifying schematic diagram of special-purpose cutter setting frame among Fig. 1.
Fig. 9 is the plan structure schematic diagram of Fig. 8.
Figure 10 is the structure for amplifying schematic diagram of regurgitating the hole among Fig. 1 on the rocket burning chamber shell.
The specific embodiment
The present invention is described in further detail below in conjunction with the drawings and specific embodiments.
Shown in Fig. 1 ~ 10, on the main shaft 2 of the common boring machine 1 of enforcement the inventive method special tool-post 3 is installed, special stand 4 is installed on the dedicated platform 5, dedicated platform 5 is installed on the horizontal table 9 of common boring machine 1, rocket chamber housing 6 is installed on the special stand 4, special-purpose cutter setting frame 7 is installed on the dedicated platform 5, use the location behind special-purpose cutter setting frame 7 anglec of rotation α, after on request centering being installed, utilize rotatablely moving of main shaft 2, the end face 8.1 in hole 8 is regurgitated in the radially hand feed campaign of axial feed motion and special tool-post 7, endoporus 8.2, the processing of outer round thread 8.3 and end face dowel hole 8.4.
Shown in Fig. 1,3,6, described common boring machine 1 each axle stroke satisfies following requirement:
The X-axis of common boring machine 1 is horizontal table 9 horizontal directions (being the width of horizontal table 9), X-axis stroke X with regurgitate 8 end face centers, hole to front skirt 6.1 end face distance L
1, regurgitate 8 end face centers, hole to front skirt 6.1 cylindrical distance L
2, horizontal table 9 centres of gyration are to the distance L of front skirt 6.1 end faces
3, anglec of rotation α, front skirt 6.1 outside diameter d relationship be X=2[L
3(d/2 L
2)/tg α+L
1] sin α;
The Y-axis of common boring machine 1 is horizontal table 9 longitudinal directions (being the length direction of horizontal table 9), and Y-axis stroke Y and horizontal table 9 centres of gyration are to the distance L of front skirt 6.1 end faces
3Relationship be Y=L
3+ 200 ~ 500mm;
The Z axis of common boring machine 1 is the direction perpendicular to horizontal table 9, and the tangent line of the inner arc surface of bracket base 4.3 lower ends of the thickness A of Z axis stroke Z and dedicated platform 5, special stand 4 is Z=A+B+d+300 ~ 700mm to bottom surface, bracket base 4.3 lower end apart from the front skirt 6.1 of B, rocket chamber housing 6 and the relationship of rear skirt 6.2 outside diameter d;
Stroke W=300 ~ the 1000mm of the main shaft 2 of common boring machine 1.
Such as Fig. 4, shown in Figure 5, be provided with the T-shaped groove 5.1 that special stand 4 and special-purpose cutter setting frame 7 are installed on the end face of dedicated platform 5.Horizontal table 9 central alignments of the center of dedicated platform 5 and common boring machine 1, and the T-shaped groove of the horizontal table 9 by bolt and nut fastener and common boring machine 1 is fastenedly connected.In conjunction with Fig. 1 and Fig. 2, the front skirt 6.1 of the length C of dedicated platform 5 and rocket chamber housing 6 is C=C1+600 ~ 1000mm with the relationship of rear skirt 6.2 end distance C1.The relationship of the width E of dedicated platform 5 and the front skirt 6.1 of rocket chamber housing 6, rear skirt 6.2 outside diameter d is E=d+200 ~ 400mm, the thickness A of dedicated platform 5=200 ~ 400mm.
As shown in Figure 6, special stand 4 comprises pressure ring lid 4.1 and bracket base 4.3, and pressure ring lid 4.1 and bracket base 4.3 location are clamped in the periphery of the front and back skirt of rocket chamber housing 6, and fastening by bolt and nut fastener.Be provided with flat key 4.2 on bracket base 4.3 bottoms of special stand 4, flat key 4.2 is embedded in the T-shaped groove 5.1 of dedicated platform 5.Special stand 4 is fastenedly connected by bolt and nut fastener and dedicated platform 5; The arc diameter D that is comprised of pressure ring lid 4.1 and bracket base 4.3 equates with the front and back skirt outside diameter d of rocket chamber housing 6.
As shown in Figure 7, special tool-post 3 comprises handle of a knife 3.1, feed mechanism 3.3, tool rest 3.5 and is installed in cutter 3.4 on the tool rest 3.5.Handle of a knife 3.1 is connected with the main shaft 2 of common boring machine 1 by locking wedge 3.2.One end of feed mechanism 3.3 is connected with handle of a knife 3.1, and the other end is connected with tool rest 3.5.
Shown in Fig. 8,9, special-purpose cutter setting frame 7 comprises tool rest bracket 7.4, and feeler block 7.1, rotating shaft 7.3 and three pin holes 7.5 of arranging on the tool rest bracket 7.4 are provided with latch 7.2 in the pin hole 7.5.Feeler block 7.1 is installed on the center line of tool rest bracket 7.4, and rotating shaft 7.3 is positioned on the same center line of feeler block 7.1 1 sides.Three pin holes 7.5 evenly are arranged on the tool rest bracket 7.4 and are on the same section circular arc, and a middle pin hole 7.5 is positioned on the same center line of opposite side of feeler block 7.1, and two pin holes 7.5 equate with described anglec of rotation α with middle pin hole 7.5 formed arc chord angles respectively in addition.The bottom of tool rest bracket 7.4 is embedded in the T-shaped groove 5.1 of dedicated platform 5, and is fastenedly connected by bolt and nut fastener and dedicated platform 5.In conjunction with Fig. 3, the main shaft 2 centre distance L of feeler block 7.1 centers and common boring machine 1 on the special-purpose cutter setting frame 7
5With regurgitate 8 end face centers, hole to the front skirt 6.1 end face distance L of rocket chamber housing 6
1, regurgitate 8 end face centers, hole to the front skirt cylindrical distance L of rocket chamber housing 6
2, special-purpose cutter setting frame 7 centres of gyration are to the distance L of front skirt 6.1 end faces of rocket chamber housing 6
4, anglec of rotation α, rocket chamber housing 6 the relationship of front skirt 6.1 outside diameter d be L
5=[(d/2 L
2)/tg α L
1+ L
4] sin α.
Embodiment 1:
For certain aircraft Φ 880mm * 5000mm rocket chamber housing 6, front skirt 6.1 outside diameter d=880mm.Regurgitate the angle α in hole 8 and rocket chamber housing 6 axle center=38 °, regurgitate 8 end face centers, hole to front skirt 6.1 end face distance L
1=82.8mm regurgitates 8 end face centers, hole to front skirt 6.1 cylindrical distance L
2=125.25mm.Horizontal table 9 centres of gyration are to the distance L of front skirt 6.1 end faces
3=2500mm.The width E=1250mm of the length C=5600mm of dedicated platform 5, dedicated platform 5, the thickness A=250mm of dedicated platform 5.The tangent line of the inner arc surface of bracket base 4.3 lower ends of special stand 4 to bottom surface, bracket base 4.3 lower end apart from B=100mm.Special-purpose cutter setting frame 7 centres of gyration are to the distance L of front skirt 6.1 end faces
4=175mm.The main shaft 2 centre distance L of feeler block 7.1 centers and common boring machine 1 on the special-purpose cutter setting frame 7
5=[(d/2 L
2)/tg α L
1+ L
4] sin α=304.79mm.
The X-axis of common boring machine 1 is the horizontal direction of horizontal table 9, minimum stroke X=2 (L
3(d/2 L
2)/tg α+L
1) sin α=1342mm; The Y-axis of common boring machine 1 is horizontal table 9 longitudinal directions, minimum stroke Y=L
3+ 200 ~ 500mm=2700mm; The Z axis of common boring machine 1 is the direction perpendicular to horizontal table 9, minimum stroke Z=A+B+d+300 ~ 700mm=1530mm; Boring spindle minimum stroke W=300 ~ 1000mm=600mm.
Adopt domestic TPX6113 horizontal boring machine, the technical process of regurgitating hole 8 processing on the rocket chamber housing 6 is as follows:
1) the special tooling centering is installed: dedicated platform 5 centerings are installed on the horizontal table 9 of boring machine, horizontal table 9 centres of gyration of dedicated platform 5 centers and boring machine are basically identical, the flatness error of dedicated platform 5 is 0.08mm, adjust dedicated platform 5 levels, play table with dial gauge and detect that the plane position error is not more than 0.1mm on the dedicated platform 5; Location flat key 4.2 sides on special stand 4 bracket bases 4.3 are installed 4, two supports of fastening special stand 4 are the most left to equal the distance of the front and back skirt end face of rocket chamber housing 6 with the distance low order end face after near side, the T-shaped groove in dedicated platform 5 centers 5.1 location; Fastening special-purpose cutter setting frame is installed after near side, the T-shaped groove in dedicated platform 5 centers 5.1 location in flat key side, location on the tool rest bracket 7.4 of special-purpose cutter setting frame 7, and the straightness error of the side, location of the T-shaped groove 5.1 in dedicated platform 5 centers is not more than 0.06mm;
2) housing centering, installation: with the front skirt 6.1 of rocket chamber housing 6, rear skirt 6.2 excircle orientations, rocket chamber housing 6 is installed on former and later two special stands 4, with on the front skirt 6.1 of vernier height gauge centering, rear skirt 6.2 end faces everywhere the high level error such as groove level be not more than 0.2; Front skirt 6.1 end faces are not more than 0.03mm to special stand 4 front end face range errors; Dial gauge is adsorbed on the main shaft 2 of boring machine, skirt 6.1 end faces, endoporus runout error are not more than 0.05mm before the centering;
3) regurgitate hole space angle centering: feeler block 7.1 level centered by rotating shaft 7.3 of special-purpose cutter setting frame 7 is turned clockwise after 38 ° with latch 7.2 location, horizontal table 9, dedicated platform 5, special stand 4, special-purpose cutter setting frame 7 and rocket chamber housing 6 levels of boring machine are rotated counterclockwise 38 °, the anglec of rotation adopts special-purpose cutter setting frame 7 to proofread and correct, method is for to be adsorbed on dial gauge on the main shaft 2 of boring machine, and on the special-purpose cutter setting frame 7 of front and back centering beat and be not more than 0.015/200mm in feeler block 7.1 sides;
4) regurgitate locus, hole centering: with horizontal table 9, rocket chamber housing 6, special-purpose cutter setting frame 7 horizontal translations of boring machine, with the distance between the feeler block 7.1 on sizing slip gauge control main shaft 2 and the special-purpose cutter setting frame 7, the distance L at main shaft 2 centers of feeler block 7.1 centers and boring machine on the special-purpose cutter setting frame 7 after the translation
5=304.79mm makes main shaft 2 center superpositions of regurgitating 8 centers, hole and boring machine to be processed;
5) 1# regurgitates hole processing: in the taper hole of the main shaft 2 of boring machine special tool-post 3 is installed, processing, the 1# of centering regurgitates end face 8.1, endoporus 8.2, outer round thread 8.3 and the end face dowel hole 8.4 in hole 8;
6) 3# regurgitates hole centering, processing: according to 3), 4), 5) described method, the identical angle [alpha] that turns clockwise, the 3# of level of processing direction symmetry regurgitates the hole;
7) 2# regurgitates the hole centering: the pressure ring lid 4.1 that unclamps special stand 4, rocket chamber housing 6 is turned clockwise 90 °, dial gauge is adsorbed on the main shaft 2 of boring machine, vertical direction is reinstalled rocket chamber housing 6 after up and down the 1#, the 3# that have processed of centering end face dowel hole 8.4 errors of regurgitating hole 8 are not more than 0.02mm, makes unprocessed 2#, 4# regurgitate hole 8 and is horizontal;
8) 2# regurgitates hole processing and 4# regurgitates hole centering, processing: according to 3), 4), 5), 6) described method, corresponding processing 2#, 4# regurgitate hole 8, thereby finish four processing of regurgitating hole 8 on the rocket chamber housing 6.
The actual machining angle deviation of regurgitating hole 8 is ± 2' that position deviation is ± 0.15mm that machining accuracy is higher, satisfies the product design required precision.
Embodiment 2:
For certain aircraft Φ 1200mm * 6000mm rocket chamber housing 6, front skirt 6.1 outside diameter d=1200mm.Regurgitate the angle α in hole 8 and rocket chamber housing 6 axle center=40 °, regurgitate 8 end face centers, hole to front skirt 6.1 end face distance L
1=136.3mm regurgitates 8 end face centers, hole to front skirt 6.1 cylindrical distance L
2=171.7mm.Horizontal table 9 centres of gyration are to the distance L of front skirt 6.1 end faces
3=3000mm.The tangent line of the inner arc surface of bracket base 4.3 lower ends of the width E=1400mm of the length C=6600mm of dedicated platform 5, dedicated platform 5, the thickness A=300mm of dedicated platform 5, special stand 4 to bottom surface, bracket base 4.3 lower end apart from B=120mm.Special-purpose cutter setting frame 7 centres of gyration are to the distance L of front skirt 6.1 end faces
4=200mm.The main shaft 2 centre distance L of feeler block 7.1 centers and common boring machine 1 on the special-purpose cutter setting frame 7
5=[(d/2 L
2)/tg α L
1+ L
4] sin α=369.04mm.
The X-axis of common boring machine 1 is horizontal table 9 horizontal directions, minimum stroke X=2[L
3(d/2 L
2)/tg α+L
1] sin α=1688mm; The Y-axis of common boring machine 1 is horizontal table 9 longitudinal directions, minimum stroke Y=L
3+ 200 ~ 500mm=3200mm; The Z axis of common boring machine 1 is the direction perpendicular to horizontal table 9, minimum stroke Z=A+B+d+300 ~ 700mm=1920mm; Boring spindle minimum stroke W=300 ~ 1000mm=650mm.
The S that adopts domestic middle prompt machine tool plant to produce
2-225 horizontal boring machines, the technical process of regurgitating hole 8 processing on the rocket chamber housing 6 is as follows:
1) the special tooling centering is installed: dedicated platform 5 centerings are installed on the horizontal table 9 of boring machine, horizontal table 9 centres of gyration of dedicated platform 5 centers and boring machine are basically identical, the flatness error of dedicated platform is 0.10mm, adjust dedicated platform 5 levels, play table with dial gauge and detect that the plane position error is not more than 0.1mm on the dedicated platform 5; Location flat key 4.2 sides on special stand 4 bracket bases 4.3 are installed 4, two supports of fastening special stand 4 are the most left to equal the distance of the front and back skirt end face of rocket chamber housing 6 with the distance low order end face after near side, the T-shaped groove in dedicated platform 5 centers 5.1 location; Fastening special-purpose cutter setting frame is installed after near side, the T-shaped groove in dedicated platform 5 centers 5.1 location in flat key side, location on the tool rest bracket 7.4 of special-purpose cutter setting frame 7, and the straightness error of the side, location of the T-shaped groove 5.1 in dedicated platform 5 centers is not more than 0.08mm;
2) housing centering, installation: with the front skirt 6.1 of rocket chamber housing 6, rear skirt 6.2 excircle orientations, rocket chamber housing 6 is installed on former and later two special stands 4, with on the front skirt 6.1 of vernier height gauge centering, rear skirt 6.2 end faces everywhere the high level error such as groove level be not more than 0.2; Front skirt 6.1 end faces are not more than 0.03mm to special stand 4 front end face range errors; Dial gauge is adsorbed on the main shaft 2 of boring machine, skirt 6.1 end faces, endoporus runout error are not more than 0.05mm before the centering;
3) regurgitate hole space angle centering: feeler block 7.1 level centered by rotating shaft 7.3 of special-purpose cutter setting frame 7 is turned clockwise after 40 ° with latch 7.2 location, horizontal table 9, dedicated platform 5, special stand 4, special-purpose cutter setting frame 7 and rocket chamber housing 6 levels of boring machine are rotated counterclockwise 40 °, the anglec of rotation adopts special-purpose cutter setting frame 7 to proofread and correct, method is for to be adsorbed on dial gauge on the main shaft 2 of boring machine, and on the special-purpose cutter setting frame 7 of front and back centering beat and be not more than 0.015/200mm in feeler block 7.1 sides;
4) regurgitate hole space angle centering: with horizontal table 9, rocket chamber housing 6, special-purpose cutter setting frame 7 horizontal translations of boring machine, with the distance between the feeler block 7.1 on sizing slip gauge control main shaft 2 and the special-purpose cutter setting frame 7, the distance L at main shaft 2 centers of feeler block 7.1 centers and boring machine on the special-purpose cutter setting frame 7 after the translation
5=369.04mm makes main shaft 2 center superpositions of regurgitating 8 centers, hole and boring machine to be processed;
5) 1# regurgitates hole processing: in the taper hole of the main shaft 2 of boring machine special tool-post 3 is installed, processing, the 1# of centering regurgitates end face 8.1, endoporus 8.2, outer round thread 8.3 and the end face dowel hole 8.4 in hole 8;
6) 3# regurgitates hole centering, processing: according to 3), 4), 5) described method, the identical angle [alpha] that turns clockwise, the 3# of level of processing direction symmetry regurgitates the hole;
7) 2# regurgitates the hole centering: the pressure ring lid 4.1 that unclamps special stand 4, rocket chamber housing 6 is turned clockwise 90 °, dial gauge is adsorbed on the main shaft 2 of boring machine, vertical direction is reinstalled rocket chamber housing 6 after up and down the 1#, the 3# that have processed of centering end face dowel hole 8.4 errors of regurgitating hole 8 are not more than 0.02mm, makes unprocessed 2#, 4# regurgitate hole 8 and is horizontal;
8) 2# regurgitates hole processing and 4# regurgitates hole centering, processing: according to 3), 4), 5), 6) described method, corresponding processing 2#, 4# regurgitate hole 8, thereby finish four processing of regurgitating hole 8 on the rocket chamber housing 6.
The actual machining angle deviation of regurgitating hole 8 is ± 3' that position deviation is ± 0.2mm that machining accuracy is higher, satisfies the product design required precision.
Claims (8)
1. one kind with the method for regurgitating the hole on the common boring machine processing rocket chamber housing, may further comprise the steps:
1) centering of special tooling is installed: dedicated platform (5) centering is installed on the horizontal table (9) of the common boring machine (1) that each axle stroke meets the demands, special stand (4) and special-purpose cutter setting frame (7) centering are installed on the dedicated platform (5);
2) centering of housing is installed: with the front skirt (6.1) of rocket chamber housing (6), rear skirt (6.2) excircle orientation, rocket chamber housing (6) is installed on former and later two special stands (4), makes the level of groove everywhere on front skirt (6.1), rear skirt (6.2) end face contour;
3) regurgitate hole space angle centering: turn clockwise feeler block (7.1) level centered by rotating shaft (7.3) of special-purpose cutter setting frame (7) rear with latch (7.2) location, horizontal table (9), dedicated platform (5), special stand (4), special-purpose cutter setting frame (7) and rocket chamber housing (6) level with common boring machine (1) is rotated counterclockwise again, anglec of rotation α is the angle of regurgitating axle center and rocket chamber housing (6) axle center in hole (8) on the rocket chamber housing (6), and the anglec of rotation adopts special-purpose cutter setting frame (7) to proofread and correct;
4) regurgitate locus, hole centering: with horizontal table (9), rocket chamber housing (6) and special-purpose cutter setting frame (7) horizontal translation of common boring machine (1), distance with between the feeler block (7.1) of the main shaft (2) of sizing slip gauge control common boring machine (1) and special-purpose cutter setting frame (7) makes (8) center, hole of regurgitating to be processed and main shaft (2) center superposition of common boring machine (1);
5) 1# regurgitates hole processing: in the taper hole of the main shaft (2) of common boring machine (1) special tool-post (3) is installed, processing, the 1# of centering regurgitates end face (8.1), endoporus (8.2), outer round thread (8.3) and the end face dowel hole (8.4) of hole (8);
6) 3# regurgitates hole centering, processing: according to 3), 4), 5) described method, the identical angle [alpha] that turns clockwise, the 3# of level of processing direction symmetry regurgitates hole (8);
7) 2# regurgitates the hole centering: the pressure ring lid (4.1) that unclamps special stand (4), rocket chamber housing (6) is turned clockwise 90 °, the 1# that the vertical direction centering has been processed, 3# regurgitate the end face dowel hole (8.4) in hole (8), reinstall rocket chamber housing (6), make unprocessed 2#, 4# regurgitate hole (8) and be horizontal;
8) 2# and 4# regurgitate hole centering, processing: according to 3), 4), 5), 6) described method, corresponding processing 2# and 4# regurgitate hole (8), thereby finish upper four processing of regurgitating hole (8) of rocket chamber housing (6).
2. the method with regurgitating the hole on the common boring machine processing rocket chamber housing according to claim 1, it is characterized in that: each axle stroke of described common boring machine (1) satisfies following requirement:
The X-axis of common boring machine (1) is horizontal table (9) horizontal direction, X-axis stroke X with regurgitate end face center, hole (8) to front skirt (6.1) end face distance L
1, regurgitate end face center, hole (8) to front skirt (6.1) cylindrical distance L
2, horizontal table (9) centre of gyration is to the distance L of front skirt (6.1) end face
3, anglec of rotation α, front skirt (6.1) outside diameter d relationship be X=2[L
3(d/2 L
2)/tg α+L
1] sin α;
The Y-axis of common boring machine (1) is horizontal table (9) longitudinal direction, and Y-axis stroke Y and horizontal table (9) centre of gyration is to the distance L of front skirt (6.1) end face
3Relationship be Y=L
3+ 200 ~ 500mm;
The Z axis of common boring machine (1) is the direction perpendicular to horizontal table (9), and the tangent line of the inner arc surface of bracket base (4.3) lower end of the thickness A of Z axis stroke Z and dedicated platform (5), special stand (4) is Z=A+B+d+300 ~ 700mm to bracket base (4.3) bottom surface, lower end apart from the front skirt (6.1) of B, rocket chamber housing (6) and the relationship of rear skirt (6.2) outside diameter d;
Stroke W=300 ~ the 1000mm of the main shaft (2) of common boring machine (1).
3. the method with regurgitating the hole on the common boring machine processing rocket chamber housing according to claim 1 and 2, it is characterized in that: be provided with the T-shaped groove (5.1) that special stand (4) and special-purpose cutter setting frame (7) are installed on the end face of described dedicated platform (5), horizontal table (9) central alignment of the center of described dedicated platform (5) and common boring machine (1), and the T-shaped groove of the horizontal table (9) by bolt and nut fastener and common boring machine (1) is fastenedly connected.
4. the method with regurgitating the hole on the common boring machine processing rocket chamber housing according to claim 3, it is characterized in that: the front skirt (6.1) of the length C of described dedicated platform (5) and rocket chamber housing (6) is C=C1+600 ~ 1000mm with the relationship of rear skirt (6.2) end distance C1, the relationship of the front skirt (6.1) of the width E of described dedicated platform (5) and rocket chamber housing (6), rear skirt (6.2) outside diameter d is E=d+200 ~ 400mm, the thickness A of described dedicated platform (5)=200 ~ 400mm.
5. the method with regurgitating the hole on the common boring machine processing rocket chamber housing according to claim 3, it is characterized in that: described special stand (4) comprises pressure ring lid (4.1) and bracket base (4.3), described pressure ring lid (4.1) and bracket base (4.3) location are clamped in the periphery of the front and back skirt of rocket chamber housing (6), and fastening by bolt and nut fastener; The bottom of described bracket base (4.3) is provided with flat key (4.2), described flat key (4.2) is embedded in the T-shaped groove (5.1) of described dedicated platform (5), and described special stand (4) is fastenedly connected by bolt and nut fastener and dedicated platform (5); The arc diameter D that is comprised of pressure ring lid (4.1) and bracket base (4.3) equates with the front and back skirt outside diameter d of rocket chamber housing (6).
6. the method with regurgitating the hole on the common boring machine processing rocket chamber housing according to claim 3, it is characterized in that: described special-purpose cutter setting frame (7) comprises tool rest bracket (7.4), upper feeler block (7.1), rotating shaft (7.3) and three pin holes (7.5) that arrange of described tool rest bracket (7.4), be provided with latch (7.2) in the described pin hole (7.5), described feeler block (7.1) is installed on the center line of tool rest bracket (7.4), and described rotating shaft (7.3) is positioned on the same center line of feeler block (7.1) one sides; Described three pin holes (7.5) evenly are arranged on tool rest bracket (7.4) upward and are on the same section circular arc, and a middle pin hole (7.5) is positioned on the same center line of opposite side of feeler block (7.1), and two pin holes (7.5) equate with described anglec of rotation α with the formed arc chord angle of a middle pin hole (7.5) respectively in addition; The bottom of described tool rest bracket (7.4) is embedded in the T-shaped groove (5.1) of described dedicated platform (5), and is fastenedly connected by bolt and nut fastener and dedicated platform (5).
7. the method with regurgitating the hole on the common boring machine processing rocket chamber housing according to claim 6 is characterized in that: main shaft (2) the centre distance L of upper feeler block (7.1) center of described special-purpose cutter setting frame (7) and common boring machine (1)
5With regurgitate end face center, hole (8) to front skirt (6.1) the end face distance L of rocket chamber housing (6)
1, regurgitate end face center, hole (8) to the front skirt cylindrical distance L of rocket chamber housing (6)
2, special-purpose cutter setting frame (7) centre of gyration is to the distance L of front skirt (6.1) end face of rocket chamber housing (6)
4, anglec of rotation α, rocket chamber housing (6) the relationship of front skirt (6.1) outside diameter d be L
5=[(d/2 L
2)/tg α L
1+ L
4] sin α.
8. the method with regurgitating the hole on the common boring machine processing rocket chamber housing according to claim 6, it is characterized in that: described special tool-post (3) comprises handle of a knife (3.1), feed mechanism (3.3), tool rest (3.5) and is installed in cutter (3.4) on the tool rest (3.5), described handle of a knife (3.1) is connected with the main shaft (2) of common boring machine (1) by locking wedge (3.2), one end of described feed mechanism (3.3) is connected with described handle of a knife (3.1), and the other end is connected with tool rest (3.5).
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|---|---|---|---|
| CN 201110183386 CN102248379B (en) | 2011-07-01 | 2011-07-01 | Method for processing back-spraying hole in shell of rocket chamber by using conventional boring machine |
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|---|---|---|---|
| CN 201110183386 CN102248379B (en) | 2011-07-01 | 2011-07-01 | Method for processing back-spraying hole in shell of rocket chamber by using conventional boring machine |
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| CN102248379B true CN102248379B (en) | 2013-01-30 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103157824B (en) * | 2011-12-16 | 2015-08-19 | 上海重型机器厂有限公司 | The processing method of elongated blind hole on 100 kilowatts of high pressure nuclear steam turbine cylinder bodies |
| CN103009127B (en) * | 2012-12-07 | 2015-05-20 | 哈尔滨汽轮机厂有限责任公司 | Milling tool of flame tube installation edge of combustion chamber of gas turbine engine for direct drive |
| CN103557761B (en) * | 2013-10-28 | 2016-03-02 | 湖北三江航天江北机械工程有限公司 | Rocket chamber shell regurgitates measuring method and the special purpose device in hole |
| CN104439366B (en) * | 2014-11-18 | 2016-12-07 | 哈尔滨汽轮机厂有限责任公司 | A kind of turbine high-pressure outer shell back oblique flange hole Boring machine processing method |
| CN113414553B (en) * | 2021-06-30 | 2022-05-13 | 哈尔滨电气动力装备有限公司 | Machining process of main pump impeller cover of shaft seal of nuclear power station |
| CN114505688B (en) * | 2022-03-04 | 2023-07-28 | 西安零壹空间科技有限公司 | Thin-wall special-shaped combustion chamber shell and processing method thereof |
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|---|---|---|---|---|
| US3597821A (en) * | 1968-08-09 | 1971-08-10 | Rohr Corp | Method of making an integrated match machining rocket nozzle |
| US4766657A (en) * | 1985-08-05 | 1988-08-30 | Morton Thiokol, Inc. | Rocket motor extendible nozzle exit cone |
| US5613299A (en) * | 1994-11-09 | 1997-03-25 | Ring; Peter J. | Method of fabricating a rocket thrust chamber |
| CN1095720C (en) * | 1997-10-30 | 2002-12-11 | 沃尔沃航空有限公司 | Method for producing rotational-symmetrical articles of sheet metal with double curved surface and varying thickness of material |
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2011
- 2011-07-01 CN CN 201110183386 patent/CN102248379B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3597821A (en) * | 1968-08-09 | 1971-08-10 | Rohr Corp | Method of making an integrated match machining rocket nozzle |
| US4766657A (en) * | 1985-08-05 | 1988-08-30 | Morton Thiokol, Inc. | Rocket motor extendible nozzle exit cone |
| US5613299A (en) * | 1994-11-09 | 1997-03-25 | Ring; Peter J. | Method of fabricating a rocket thrust chamber |
| CN1095720C (en) * | 1997-10-30 | 2002-12-11 | 沃尔沃航空有限公司 | Method for producing rotational-symmetrical articles of sheet metal with double curved surface and varying thickness of material |
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