CN106624632A - Titanium alloy polyhedron rudder frame and preparation method thereof - Google Patents
Titanium alloy polyhedron rudder frame and preparation method thereof Download PDFInfo
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- CN106624632A CN106624632A CN201611109393.5A CN201611109393A CN106624632A CN 106624632 A CN106624632 A CN 106624632A CN 201611109393 A CN201611109393 A CN 201611109393A CN 106624632 A CN106624632 A CN 106624632A
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Abstract
The invention discloses a titanium alloy polyhedron rudder frame and preparation method thereof. The section of the titanium alloy polyhedron rudder frame is a right trapezoid which comprises a leading hedge slope and an inclined surface. The leading hedge slope and the inclined surface comprise two slopes which are symmetrical about the right trapezoid. The section of the inclined surface is a right trapezoid which shares the same right-angle waist with the rudder frame. The upper base of the inclined surface is less than the upper base of the rudder frame. The inclined surface is provided with several weight loss windows, which makes integrated components form a framework structure.
Description
Technical field
The present invention relates to the slim polyhedron rudder skeleton of spacecraft rudder skeleton structure, more particularly to titanium alloy and its processing
Method.
Background technology
In order to adapt to modern space flight type product lightweight, high-strength requirement, the welding of rudder skeleton is employed in some new models
The design of covering, with skeleton covering rudder face flight attitude and control direction are kept.Rudder skeleton is strength member therein, part material
Expect for Ti6Al4V, be the Typical Representative of alpha+beta titanium alloys.The material is added in titanium with α phase stable element Al, based on O, N, C
Element, while and adding with β phase stable element Mo, the alloy that the element based on V, Cr, Fe, Si is formed, with preferable
Comprehensive mechanical property, structure stability is good, there is good toughness, plasticity and high temperature deformation ability, and machining temperature is high, cutter
Abrasion is violent, efficiency is not good.
Rudder skeleton part is frame with the sheet panel structure, and appearance profile size is about 400*65mm, thinnest part thickness 2mm, overall
Face type is angled ramp, and multiple mitigation mouth frames not of uniform size are distributed on type face, and material entirety removal amount, up to more than 70%, is allusion quotation
The weak rigid thin-walls of type, process yielding.Especially part material is titanium alloy, and in cutting, temperature is high, is also easy to produce thermal deformation,
So as to aggravate part deformation, product surface quality and dimensional accuracy are affected.Rudder skeleton bottom is distributed two groups of High-precision Deep Holes, major diameter
Than respectively, up to 19 and 31, inner bore surface roughness requires 1.6 μm, and aperture size required precision reaches IT8 levels, and holes is relative to face
Type central plane symmetry is not more than 0.05mm.In addition the mouth frame and breach in two groups of deep and long hole quilt cover types is divided into 3 sections, if adopting
With interrupted cut, tool tip easily shifts, and aperture and the accuracy of form and position are difficult to ensure that.Rudder skeleton part is either in product matter
Amount ensures all meet research and production mission requirements in still working (machining) efficiency.Therefore, in control part machining deformation and guarantee
On the premise of crudy, realize that the slim polyhedron parts high efficiency of titanium alloy framework, the manufacture method of stable processing are one
Core key technology.
The content of the invention
The problem that the present invention is solved is that the slim polyhedron parts working (machining) efficiency of existing titanium alloy framework is low, stability is poor；For
The problem is solved, the present invention provides the slim polyhedron rudder skeleton of titanium alloy and its processing method.
The section of the slim polyhedron rudder skeleton of titanium alloy that the present invention is provided is right-angled trapezium, including leading edge inclined-plane and oblique type
Face, the leading edge inclined-plane and oblique type face are included respectively with regard to two symmetrical inclined-planes of right-angled trapezium；The section in the oblique type face is
With the right-angled trapezium of the common right angle waist of rudder skeleton, the upper bottom in oblique type face is less than the upper bottom of rudder skeleton.
Further, the oblique type face go to the bottom on be provided with a bottom notch；Tiltedly matrix face is respectively provided with the Liang Ge inclined-planes of type face,
Mitigation window is provided with the matrix face.
Further, the quantity for mitigating window is 9, and respectively there is a mitigation window bottom notch both sides.
Further, the rudder skeleton bottom includes oblique angle, and bottom oblique angle is connected with oblique type face straight line by fillet.
Further, the bottom surface in the oblique type face is rectangle, and the bottom surface on the leading edge inclined-plane is triangle.
Further, the rudder skeleton bottom thickness is 18mm, and oblique type face top thinnest part is 5mm, and leading edge inclined-plane is most thin
Place thickness 2mm.
The processing method that the present invention also provides the described slim polyhedron rudder skeleton of titanium alloy, including：To titanium alloy blank
Roughing is carried out, blank is formed；Eight mitigation windows are cut off, mitigation window of the bottom notch near right-angle side side does not cut；
Finishing, cuts off mitigation window of the bottom notch near right-angle side side.
Further, forming blank includes：
Step 1, by rectangle titanium alloy blank flat numerical control contours profiles are rough milled out, and reserve clamping process block, outside profile
Shape is monolateral to leave 2mm allowances for finish；
Bottom surface and bottom middle process block two sides in step 2, numerical control finish-milling appearance profile；
1.6 μm of step 3, rear surface roughness, soffit plane degree 0.05mm, as following process positioning datum；
Step 4, clamping is kept flat on work top by part, and thickness direction both sides leading edge inclined-plane is rough milled in numerical control, monolateral to stay
There are 1mm allowances for finish；
Step 5, numerical control roughing bottom oblique angle is monolateral to leave 1mm allowance.
Further, the finishing, cutting off mitigation window of the bottom notch near right-angle side side includes：
Step 7, using plain-milling machine amendment part surrounding technique block, it is positive and negative symmetrically and evenly to remove surplus, it is ensured that technique block
Flatness is not more than 0.05mm, and compared to type face central plane symmetry 0.1mm is not more than；
Step 8, remove flash removed；
Step 9, Special slope frock clamping is used, the oblique type face of numerical control finish-milling thickness direction two；The inclined-plane of positive and negative symmetrical milling two
Clamping need to be stood up；
Step 10, Special slope frock clamping is used, numerical control finish-milling thickness direction both sides matrix face；Positive and negative symmetrical milling two is recessed
Type face need to stand up clamping；
Step 11, keeps flat clamping on work top, numerical control finish-milling thickness direction both sides leading edge inclined-plane by part；
Step 12, numerical control finishing bottom oblique angle and with oblique type face joint knuckle；
Step 13, using the high-precision deep hole of customization drill gun drilling processing feature bottom；
Step 14, cuts out part portion profile；Low-speed WEDM cuts out part back contoured surface and breach, base plane
And breach；
Step 15, high speed WEDM cuts off mitigation window of the bottom notch near right-angle side side；
Step 16, high speed WEDM cuts out leading edge and top profile；
Step 17, frustrates and repaiies leading edge and profile top edge fillet；
Step 18, inspection, oil sealing, warehouse-in.
Further, the step 13 includes：
Step A：With the horizontal clamping parts of technique block；
Step B：Technique block flatness is measured with dial gauge, and part is adjusted, it is ensured that technique block flatness is little
In 0.05mm；
Step C：With infrared line side head detection process block upper surface, and according to technique block thickness by thickness direction zero point
It is arranged on technique block thickness direction central plane；
Step D：Bored with centre drill point in deep hole machining plane and positioned, put drilling depth 1-1.5mm；
Step E：Bullport bottom outlet, hole depth L=2～3D are processed in fluted drill drilling, and D is the diameter in hole；
Step F：Reamer finish reams bullport to deep hole nominal dimension；
Step G：The continuous disposable drilling of drill gun is machined to deep hole desired depth.
Advantages of the present invention includes：
The processing method of the slim polyhedron parts of titanium alloy framework that the present invention is provided, by titanium alloy rudder skeleton part
The application of batch production processing, has the positive effect that：1st, the present invention is adopted with numerical control milling, high speed WEDM, drill gun
The process meanses that drilling, low-speed WEDM combine, reasonable arrangement technological process, distribution chipping allowance, effective control part
Machining deformation, the final precision of part is ensure that, while at utmost accomplishing that operation is concentrated, effectively reduce process number, shorten manufacture
Cycle.2nd, the present invention adopts inclined-plane Special tooling clamp, and by alignment pin, the positive and negative processing in the oblique type face of part can quick and precisely be determined
Position, convenient mounting and clamping is quick and accuracy is high.Manufacturing process disclosed in this invention has good stability and reliability, reaches
The design accuracy of part requires, improves the working (machining) efficiency of part, reduces the manufacturing cost of part, with significant economy
Benefit.
Description of the drawings
Fig. 1 is that the slim polyhedron rudder skeleton processing method technique block of titanium alloy provided in an embodiment of the present invention is reserved to be illustrated
Figure；
Fig. 2 (a) is the slim polyhedron rudder skeleton front view of titanium alloy provided in an embodiment of the present invention；B () is right view；
Fig. 3 is that the slim polyhedron rudder skeleton of titanium alloy provided in an embodiment of the present invention mitigates window number schematic diagram；
Fig. 4 is the special tooling knot that the slim polyhedron rudder skeleton processing method of titanium alloy provided in an embodiment of the present invention is adopted
Structure schematic diagram；
Fig. 5 is that the slim polyhedron rudder skeleton processing method leading edge tool track of titanium alloy provided in an embodiment of the present invention is illustrated
Figure；
Fig. 6 is the slim polyhedron rudder skeleton processing method flow chart of titanium alloy provided in an embodiment of the present invention.
Specific embodiment
Hereinafter, spirit and substance of the present invention are further elaborated in conjunction with the accompanying drawings and embodiments.
As shown in figure 1, the reserved schematic diagram of rudder framework process block.Its material be Ti6Al4V titanium alloy sheets, Jing three-axis numerical control millings
Part outline full-size is cut for 412x240x δ 20mm, technique block 11 stretches out contours profiles width for 18mm, technique block with
Part thickness is consistent.Part bottom surface and bottom middle process block two sides are Jing after finish-milling as following process positioning reference plane 12.
The bottom surface in the oblique type face is rectangle, and the bottom surface on the leading edge inclined-plane is triangle.
Such as Fig. 2 (a), the section of the slim polyhedron rudder skeleton of titanium alloy provided in an embodiment of the present invention is right-angled trapezium, bag
Include leading edge inclined-plane 22 and oblique type face 21, the leading edge inclined-plane 22 and oblique type face 21 are included respectively with regard to symmetrical two of right-angled trapezium
Inclined-plane；The section in the oblique type face is the right-angled trapezium with the common right angle waist of rudder skeleton, and the upper bottom in oblique type face is upper less than rudder skeleton
Bottom.The oblique type face is provided with a bottom notch 29 on going to the bottom, and right flank has back breach 28；It is tiltedly each on the inclined-plane of 21 two, type face
Matrix face 23 is provided with, mitigation window 26 is provided with the matrix face 23.As shown in Fig. 2 (b), the oblique side of type face 21 is provided with height
Profound hole 27, the rudder skeleton bottom is oblique angle 24, is connected by knuckle 25 between bottom oblique angle 24 and oblique type face.
With continued reference to Fig. 2, rudder skeleton part is titanium-alloy thin-plate frame structure, and appearance profile size is about 400*65mm；
The rudder skeleton integral face type is angled ramp, is grouped into by multi-sections such as oblique type face, leading edge inclined-plane, bottom oblique angles, and bottom is most thick
Place 18mm, oblique type face top thinnest part 5mm, leading edge inclined-plane thinnest part thickness 2mm；Multiple mitigations not of uniform size are distributed on type face
Mouth frame, makes this part material removal amount up to more than 70%, is typical weak rigid thin-walls.Two groups of rudder skeleton bottom distribution is high-precision
Deep hole is spent, one of through-hole aperture size isLength is about 230mm, and draw ratio is up to 19；Another is blind
Hole aperture size isLength is about 220mm, and up to 31, aperture size required precision is IT8 levels to draw ratio, endoporus
Surface roughness requirements Ra≤1.6m.Holes is not more than 0.05mm relative to face type central plane symmetry.Additionally, two groups profound
Mouth frame and breach in the quilt cover type of hole is divided into 3 sections, wherein bottom notch width dimensions tolerance 0.054mm, breach surface
Roughness Ra≤1.6m.
It is that rudder skeleton part mitigates window number schematic diagram referring to Fig. 3, for adding of not affecting feature bottom deep hole follow-up
Inside parts the 9th are mitigated 9 points of window to cut off twice by work.The first mitigation window 1 is first removed before deep hole machining, second is subtracted
Light window the 2, the 3rd mitigates the mitigation mitigation mitigation window the 6, the 7th of window the 5, the 6th of window the 4, the 5th of window the 3, the 4th and mitigates window
7th, the 8th mitigates window 8；Mitigate window, leave the 9th mitigation window 9 be with the matrix material for ensureing deep hole machining it is complete,
The hole scattering for avoiding interrupted drilling from causing, it is ensured that deep hole machining quality.Treat to remove the 9th mitigation window after the completion of deep hole machining again
9 technique blocks of mouth.
Rudder skeleton part inclined-plane special tooling structural representation shown in Figure 4, the special fixture specifically includes base plate
31st, the first alignment pin 32, the second alignment pin 33, the 3rd alignment pin 34.According to the oblique type face angle of bevel (monolateral) of part on base plate
2.27 ° of clamping main inclined planes 35 are provided with, for placing part；MakePin-and-hole, for installing alignment pin, makes
M16 screwed holes, for installing follower bolt；Benchmark elongated slot 36 is made, for measurement adjustment frock placement location.Additionally,
In a fixed inclination after being placed on clamping main inclined plane due to part, it is impossible to direct detection setting Y, the zero point of Z-direction on part,
Therefore, benchmark square groove has been designed and produced in tool base plate, for digital control processing zero detection and setting.Before processing, by frock
Base plate is placed on platen face, with amesdial measuring basis elongated slot, it is ensured that frock glacing flatness is adjusted within 0.02mm
Corner is fixed with pressing plate behind position；Again part is positioned over into (angle) on clamping main inclined plane, by 1-3# positioning finger settings, then with
Pressing plate pressing process block realizes the fixation of part.With the infrared line side head measuring basis square groove Y-direction of Digit Control Machine Tool and Z-direction gained
Numerical computations go out part processing Y, Z-direction dead-center position, and complete to arrange.
It is rudder skeleton part leading edge tool track schematic diagram referring to Fig. 5, either the milling of roughing square shoulder is still on leading edge inclined-plane
Finishing ball milling is with parallel to the path locus feed on leading edge inclined-plane cutting, such tool path pattern continuous linear feed
Distance is most long, and number of turns is most short, and stock-removing efficiency is higher, and so each section of continuous linear track cutter of feed be only X
Y plane is moved, and in Z-direction non-displacement, allowance for finish is relatively uniform after roughing, while tool wear can be reduced, is improved
Piece surface fineness.
The processing of rudder skeleton part adopts high accuracy CNC machine center with three axes, maximum speed 8000rpm, spindle power 13
Kilowatt, max. output torque 83KW, positioning precision 0.008mm, resetting error 0.005mm.UsingIt is indexable hard
Matter alloy TiAlN coatings cutter blade carries out the machining in oblique type face, with good resistance to elevated temperatures, 15 ° of blade hook angle, relief angle
10 °, with more preferably resistance to impact, cutting abrasion can be reduced, it is ensured that the smooth discharge of iron filings, realize roughing 3mm cutting-ins,
80% tool diameter and width, finish 1mm cutting-ins, and 60% cuts wide efficient material removes.Process is poured into a mould using cutting oil,
The heat that chip and cutting position produce is taken away in time by fluid, processing temperature is effectively reduced, reduces Part Thermal Deformation.Simultaneously
Cutting oil also can play lubrication protection effect in working angles to part finished surface and stage property, to obtain more preferably surface light
Cleanliness, and tool wear, tool life can be reduced.
Finally part back contoured surface and breach, base plane and breach are disposably cut out using low-speed WEDM, from
And the size tolerance requirements of guarantee feature bottom gap width 0.054mm, and bottom notch center and part back contoured surface
Between ± 0.05mm apart from size tolerance requirements, while ensureing the requirement of bottom notch face surface roughness Ra≤1.6m.
Rudder skeleton part manufacturing process flow diagram is as shown in Figure 6.Sequentially carry out as follows：
Step one, rough mills appearance profile.Contours profiles are rough milled into out in rectangle titanium alloy blank flat numerical control, and reserves clamping
Technique block, contours profiles are monolateral to leave 2mm allowances for finish, technique block reserved location such as Fig. 1.
Step 2, finish-milling positioning datum.Bottom surface and bottom middle process block two sides in numerical control finish-milling appearance profile, protects
1.6 μm of surface roughness after card finish-milling, soffit plane degree 0.05mm, as following process positioning datum.
Step 3, rough mills type face.Special slope frock clamping is used, the oblique type of thickness direction two is rough milled with square shoulder milling mode numerical control
Face, it is monolateral to leave 1mm allowances for finish.The inclined-plane of positive and negative symmetrical milling two need to stand up clamping.Tool specification and cutting parameter such as table 1
It is shown.
Step 4, rough mills leading edge inclined-plane.Part is kept flat into clamping on work top, thickness is rough milled with square shoulder milling mode numerical control
Degree direction both sides leading edge inclined-plane, it is monolateral to leave 1mm allowances for finish.The leading edge inclined-plane of positive and negative symmetrical milling two need to stand up clamping.Walk
Knife track is as shown in Figure 5.Shown in tool specification and cutting parameter table 1.
Step 5, rough mills bottom oblique angle.It is monolateral to leave 1mm plus spare time with square shoulder milling mode numerical control roughing bottom oblique angle
Amount.The oblique angle of positive and negative symmetrical milling two need to stand up clamping.Shown in tool specification and cutting parameter table 1.
Step 6, cuts off part mouth frame.High speed WEDM cuts off the 1-8# shown in Fig. 3 and mitigates mouth frame.
Step 7, corrects technique block.Using plain-milling machine amendment part surrounding technique block, positive and negative symmetrically and evenly removal is remaining
Amount, it is ensured that technique block thickness, flatness is not more than 0.05mm, and compared to type face central plane symmetry 0.1mm is not more than.
Step 8, removes flash removed.Pincers worker removes burr after milling.
Step 9, finish-milling type face.Special slope frock clamping is used, with the oblique type of square shoulder milling mode numerical control finish-milling thickness direction two
Face.The inclined-plane of positive and negative symmetrical milling two need to stand up clamping.Shown in tool specification and cutting parameter table 1.
Step 10, finish-milling matrix face.Special slope frock clamping is used, with square shoulder milling mode numerical control finish-milling thickness direction both sides
Matrix face.The matrix face of positive and negative symmetrical milling two need to stand up clamping.Shown in tool specification and cutting parameter table 1.
Step 11, finish-milling leading edge inclined-plane.Part is kept flat into clamping on work top, with bulb milling mode numerical control finish-milling
Thickness direction both sides leading edge inclined-plane.The leading edge inclined-plane of positive and negative symmetrical milling two need to stand up clamping.Tool track is as shown in Figure 5.Cutter
Shown in specification and cutting parameter table 1.
Step 12, finish-milling bottom oblique angle.With the numerical control of bulb milling mode finish bottom oblique angle and with oblique type face joint
Knuckle.The oblique angle of positive and negative symmetrical milling two need to stand up clamping.Shown in tool specification and cutting parameter table 1.
Step 13, deep hole drilling.Using the high-precision deep hole of customization drill gun drilling processing feature bottom, (aperture precision is required
IT8 levels).Cutting parameter is as shown in table 2.
The step 13 specifically includes following seven steps：
Step A：With the horizontal clamping parts of technique block.
Step B：Technique block flatness is measured with dial gauge, and part is adjusted, it is ensured that technique block flatness is little
In 0.05mm.
Step C：With infrared line side head detection process block upper surface, and according to technique block thickness by thickness direction zero point
It is arranged on technique block thickness direction central plane.
Step D：Bored with centre drill point in deep hole machining plane and positioned, put drilling depth 1-1.5mm.
Step E：Bullport bottom outlet, hole depth L=2～3D are processed in fluted drill drilling.
Step F：Reamer finish reams bullport to deep hole nominal dimension.From reamer diameter at edge part required precision IT4.
Step G：The continuous disposable drilling of drill gun is machined to deep hole desired depth.
Step 14, cuts out part portion profile.Low-speed WEDM cuts out the contoured surface of part back shown in Fig. 1 and lacks
Mouth, base plane and breach.
Step 15, cuts off remaining mouth frame.High speed WEDM cuts off 9# shown in Fig. 3 and mitigates mouth frame.
Step 10 six, cuts out part residue profile.High speed WEDM removes technique block, cuts out leading edge shown in Fig. 1 and top
Contouring.
Step 10 seven, removes flash removed, frustrates rounded corner.Pincers worker removal institute is jagged, frustrates and repaiies leading edge and profile top edge circle
Angle.
Step 10 eight, inspection, oil sealing, warehouse-in.
The NC milling cutting parameter of table 1
By mechanical processing technique and Special tooling clamp using the present invention, carrying out in the reality processing of rudder skeleton should
With part machining deformation is effectively controlled, and preferably, either type face or deep hole are special for the rudder skeleton surface quality for processing
Levy, high-precision requirement size is effectively ensured.The processing technology of the part has good stability and reliability, processing
Efficiency is largely increased, and part crudy complies fully with design requirement
Although the present invention is disclosed as above with preferred embodiment, it is not for limiting the present invention, any this area
Technical staff without departing from the spirit and scope of the present invention, may be by the methods and techniques content of the disclosure above to this
Bright technical scheme makes possible variation and modification, therefore, every content without departing from technical solution of the present invention, according to the present invention
Technical spirit any simple modification, equivalent variations and modification that above example is made, belong to technical solution of the present invention
Protection domain.
Claims (10)
1. the slim polyhedron rudder skeleton of titanium alloy, it is characterised in that section is right-angled trapezium, including leading edge inclined-plane and oblique type face,
The leading edge inclined-plane and oblique type face are included respectively with regard to two symmetrical inclined-planes of right-angled trapezium；The section in the oblique type face is and rudder
The right-angled trapezium of the common right angle waist of skeleton, the upper bottom in oblique type face is less than the upper bottom of rudder skeleton.
2. according to the slim polyhedron rudder skeleton of titanium alloy described in claim 1, it is characterised in that the oblique type face go to the bottom on open
There is a bottom notch；Tiltedly matrix face is respectively provided with the Liang Ge inclined-planes of type face, in the matrix face mitigation window is provided with.
3. according to the slim polyhedron rudder skeleton of titanium alloy described in claim 1, it is characterised in that the quantity of the mitigation window
For 9, respectively there is a mitigation window bottom notch both sides.
4. according to the slim polyhedron rudder skeleton of titanium alloy described in claim 1, it is characterised in that the rudder skeleton bottom includes
Oblique angle, bottom oblique angle is connected with oblique type face straight line by fillet.
5. according to the slim polyhedron rudder skeleton of titanium alloy described in claim 1, it is characterised in that the bottom surface in the oblique type face is
Rectangle, the bottom surface on the leading edge inclined-plane is triangle.
6. according to the slim polyhedron rudder skeleton of titanium alloy described in claim 1, it is characterised in that the rudder skeleton bottom is most thick
Locate as 18mm, oblique type face top thinnest part is 5mm, leading edge inclined-plane thinnest part thickness 2mm.
7. the processing method of the slim polyhedron rudder skeleton of titanium alloy that any one is provided in claim 1 to 6, its feature
It is, including：Roughing is carried out to titanium alloy blank, blank is formed；Eight mitigation windows are cut off, bottom notch is near right-angle side
The mitigation window of side does not cut；Finishing, cuts off mitigation window of the bottom notch near right-angle side side.
8., according to the processing method described in claim 7, it is characterised in that carry out roughing to titanium alloy blank, blank is formed
Including
Step 1, by rectangle titanium alloy blank flat numerical control contours profiles are rough milled out, and reserve clamping process block, contours profiles list
While leaving 2mm allowances for finish；
Bottom surface and bottom middle process block two sides in step 2, numerical control finish-milling appearance profile；
1.6 μm of step 3, rear surface roughness, soffit plane degree 0.05mm, as following process positioning datum；
Step 4, clamping is kept flat on work top by part, and thickness direction both sides leading edge inclined-plane is rough milled in numerical control, monolateral to leave 1mm
Allowance for finish；
Step 5, numerical control roughing bottom oblique angle is monolateral to leave 1mm allowance.
9., according to the processing method described in claim 8, it is characterised in that the finishing, bottom notch is cut off near right angle
The mitigation window of side side includes：
Step 7, using plain-milling machine amendment part surrounding technique block, it is positive and negative symmetrically and evenly to remove surplus, it is ensured that technique block plane
Degree is not more than 0.05mm, and compared to type face central plane symmetry 0.1mm is not more than；
Step 8, remove flash removed；
Step 9, Special slope frock clamping is used, the oblique type face of numerical control finish-milling thickness direction two；The inclined-plane of positive and negative symmetrical milling two need to be turned over
Body clamping；
Step 10, Special slope frock clamping is used, numerical control finish-milling thickness direction both sides matrix face；The matrix face of positive and negative symmetrical milling two
Clamping need to be stood up；
Step 11, keeps flat clamping on work top, numerical control finish-milling thickness direction both sides leading edge inclined-plane by part；
Step 12, numerical control finishing bottom oblique angle and with oblique type face joint knuckle；
Step 13, using the high-precision deep hole of customization drill gun drilling processing feature bottom；
Step 14, cuts out part portion profile；Low-speed WEDM cuts out part back contoured surface and breach, base plane and lacks
Mouthful；
Step 15, high speed WEDM cuts off mitigation window of the bottom notch near right-angle side side；
Step 16, high speed WEDM cuts out leading edge and top profile；
Step 17, frustrates and repaiies leading edge and profile top edge fillet；
Step 18, inspection, oil sealing, warehouse-in.
10. according to the processing method described in claim 8, it is characterised in that the step 13 includes：
Step A：With the horizontal clamping parts of technique block；
Step B：Technique block flatness is measured with dial gauge, and part is adjusted, it is ensured that technique block flatness is not more than
0.05mm；
Step C：With infrared line side head detection process block upper surface, and according to technique block thickness by thickness direction reset
In technique block thickness direction central plane；
Step D：Bored with centre drill point in deep hole machining plane and positioned, put drilling depth 1-1.5mm；
Step E：Bullport bottom outlet, hole depth L=2 ~ 3D are processed in fluted drill drilling, and D is the diameter in hole；
Step F：Reamer finish reams bullport to deep hole nominal dimension；
Step G：The continuous disposable drilling of drill gun is machined to deep hole desired depth.
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| CN109733088A (en) * | 2018-12-28 | 2019-05-10 | 国营第六一六厂 | A kind of numerical control processing technology card design method of process control |
| CN111347090A (en) * | 2020-04-07 | 2020-06-30 | 四川源维机械科技有限公司 | Method for machining deep holes in a control surface assembly |
| CN111347090B (en) * | 2020-04-07 | 2021-08-06 | 四川源维机械科技有限公司 | Method for machining deep holes in a control surface assembly |
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| CN112658720A (en) * | 2020-12-11 | 2021-04-16 | 北京星航机电装备有限公司 | Positioning tool and positioning method for quickly clamping inner cavities of left and right side beams |
| CN113686206A (en) * | 2021-08-18 | 2021-11-23 | 上海机电工程研究所 | 3D printing air vane and processing method |
| CN114160851A (en) * | 2021-12-30 | 2022-03-11 | 湖北三江航天红阳机电有限公司 | Method for processing empennage framework of aircraft |
| CN117548998A (en) * | 2023-11-21 | 2024-02-13 | 华钛空天(北京)技术有限责任公司 | Preparation method, device, equipment and medium for thin-wall cavity rudder |
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