CN102430892A

CN102430892A - Method for machining aluminum base silicon carbide structure part of aerospace gyroscope

Info

Publication number: CN102430892A
Application number: CN2011102562832A
Authority: CN
Inventors: 杨�嘉
Original assignee: Individual
Current assignee: Individual
Priority date: 2011-09-01
Filing date: 2011-09-01
Publication date: 2012-05-02

Abstract

The invention relates to the field of machining, in particular to a method for machining an aluminum base silicon carbide structure part of an aerospace gyroscope. The method comprises the following steps of: performing forging, solution treatment and ageing treatment on a blank, wherein the temperature of solution treatment is 530-560 DEG C; roughly milling the base face, the upper surface and the side faces of the workpiece by using a vertical hard alloy milling cutter subjected to nitriding, and drilling the front wall and the side walls, wherein the wall thickness of the workpiece is 6 mm after rough milling; taking the roughly milled upper surface as a reference, finely milling the outer wall, the inner wall and the base surface to the cutting depth of 0.05 mm, finely boring four holes, scraping the four holes with a scraper, wherein the coaxiality phi of each hole is less than 0.005 mm. According the method disclosed by the invention, the cutting parameters are reasonably set, most of cutting allowance is removed by using the hard alloy cutter, the use of a diamond cutter is reduced, the machining cost is low, and the rate of finished products is high.

Description

Space flight is with the processing method of the aluminium base silicon carbide structure spare of gyroscope

Technical field

The present invention relates to field of machining, particularly a kind of space flight is with the processing method of the aluminium base silicon carbide structure spare of gyroscope.

Background technology

Aluminium base carbofrax material is doped silicon carbide particle and the composite processed in aluminum substrate; This material has advantages such as high strength, high rigidity, high-wearing feature, deflection is little; Be applied to fields such as Aero-Space, automobile making, instrument and meter now, especially obtained extensive use at the aerospace field that hear resistance and deflection are had higher requirements.But, therefore machining is brought very big difficulty owing to be doped with the carborundum hard particles in this material.Gyroscope arrangement spare claimed structure rigidity is big, light weight; Therefore the blank of making this type of part all is through need forging and pressing and heat treatment; The material of getting rid of from blank in the process is more than 80%, and is bigger to tool wear, and diamond cutter is all adopted in thick fine finishining in the therefore existing processing method; But diamond cutter costs an arm and a leg, and cost is high.

Summary of the invention

The present invention is directed to the weak point of prior art, propose a kind of tool wear that makes and prolong, cost reduces, and working (machining) efficiency improves, and the space flight that product qualified rate improves is with the processing method of the aluminium base silicon carbide structure spare of gyroscope.

Technical scheme of the present invention is: space flight may further comprise the steps with the processing method of the aluminium base silicon carbide structure spare of gyroscope:

Step 1: earlier with the blank forging behind the casting, the blank after will forging then carries out solution treatment, and the temperature of solution treatment is at 530～560 ℃, and the time was at 2～6 hours; Place the water below 30 ℃ to cool off fast rapidly blank after the solution treatment, Ageing Treatment is more than 36 hours then;

Step 2: the carbide end mill with diameter of phi 10mm is above is rough milled basal plane, and the blade of carbide end mill is handled through nitriding, is the outer surface that thick benchmark is rough milled antetheca and sidewall with basal plane then, made allowance 0.5mm; Rough mill respectively again and antetheca and sidewall facing surfaces, made allowance 0.5mm; Geometric center with antetheca and sidewall is the center, bores the through hole of Φ 10mm; At last, rough mill upper surface,, stay wall thickness to be not less than 6mm all around until milling out a rectangular through-hole, in the process speed of mainshaft at 1000～2000r/min, feed speed 100～200mm/min, cutting depth 0.05～0.15mm;

Step 3: the upper surface of rough milling with process is smart benchmark, inner surface, outer surface and the basal plane of this workpiece of utilization diamond milling cutter finish-milling, and inner surface and outer surface be chamfering all; Be benchmark finish-milling upper surface with the basal plane behind the finish-milling then; During finish-milling, speed of mainshaft 2000r/min, feed speed 50mm/min; Cutting depth 0.05mm, wall thickness is 5.5mm behind the finish-milling; Diamond boring cutter, speed of mainshaft 500r/min are used in the hole that gets out in the last right boring roughing operation during right boring;

Step 4: with four through holes of diamond scraper scraping, the axiality between relative hole

is less than 0.005mm.

The present invention compared with prior art has following beneficial effect: adopt the carbide-tipped milling cutter of handling through nitriding to carry out roughing; Removed most of chipping allowance; Reduce the service time of diamond cutter, adopted rational cutting parameter, prolonged cutter life; Promote product percent of pass, reduce cost; The carbide-tipped milling cutter that uses nitriding to handle during roughing has increased cutting data, and efficient is improved.

Description of drawings

Fig. 1 is the structural representation of aluminium base carborundum blank;

Fig. 2 is the structural representation of finished product structural member.

The specific embodiment

The specific embodiment one: combine Fig. 1-2 that this embodiment is described, the space flight of this embodiment is following with the processing method of the aluminium base silicon carbide structure spare of gyroscope:

Step 1: earlier with the blank forging behind the casting; Blank after will forging then carries out solution treatment, and the temperature of solution treatment is at 530～560 ℃, and the time was at 2～6 hours; Place the water below 30 ℃ to cool off fast rapidly blank after the solution treatment, Ageing Treatment is more than 36 hours then;

Step 2: the carbide end mill with diameter of phi 10mm is above is rough milled basal plane 1, and carbide end mill is handled through nitriding, is the outer surface that thick benchmark is rough milled antetheca 2 and sidewall 4 with basal plane 1 then, made allowance 0.5mm; Rough mill respectively and antetheca 2 and sidewall 4 facing surfaces, made allowance 0.5mm is the center with the geometric center of antetheca 2 and sidewall 4, bores the through hole of Φ 10mm again; At last, rough mill upper surface 3,, stay wall thickness to be not less than 6mm all around until milling out a rectangular through-hole, in the process speed of mainshaft at 1000～2000r/min, feed speed 100～200mm/min, cutting depth 0.05～0.15mm;

Step 3: the upper surface of rough milling with process 3 is smart benchmark, inner surface, outer surface and the basal plane 1 of this workpiece of utilization diamond milling cutter finish-milling, and inner surface and outer surface be chamfering all; Be benchmark finish-milling upper surface 3 with the basal plane behind the finish-milling 1 then, during finish-milling, speed of mainshaft 2000r/min; Feed speed 50mm/min, cutting depth 0.05mm, wall thickness is 5.5mm behind the finish-milling; Diamond boring cutter, speed of mainshaft 500r/min are used in the hole that gets out in the last right boring roughing operation during right boring;

Step 4: with four through holes of diamond scraper scraping, the axiality φ between relative hole is less than 0.005mm.

The specific embodiment two: combine Fig. 1-2 that this embodiment is described, the carbide end mill surface is coated with the TiN coating in this embodiment step 2, coating layer thickness 0.05mm; Diamond boring cutter speed of mainshaft 400r/min in the step 3.All the other method steps are identical with step 1.

Claims

1. a space flight is characterized in that may further comprise the steps with the processing method of the aluminium base silicon carbide structure spare of gyroscope:

Step 2: the carbide end mill with diameter of phi 10mm is above is rough milled basal plane (1), is the outer surface that thick benchmark is rough milled antetheca (2) and sidewall (4) with basal plane (1) then, made allowance 0.5mm; Rough mill respectively and antetheca (2) and sidewall (4) facing surfaces, made allowance 0.5mm is the center with the geometric center of antetheca (2) and sidewall (4) again, the through hole of brill Φ 10mm; At last, rough mill upper surface (3),, stay wall thickness to be not less than 6mm all around until milling out a rectangular through-hole, in the process speed of mainshaft at 1000～2000r/min, feed speed 100～200mm/min, cutting depth 0.05～0.15mm;

Step 3: the upper surface of rough milling with process (3) is smart benchmark, inner surface, outer surface and the basal plane (1) of this workpiece of utilization diamond milling cutter finish-milling, and inner surface and outer surface be chamfering all; Be benchmark finish-milling upper surface (3) with the basal plane behind the finish-milling (1) then, during finish-milling, speed of mainshaft 2000r/min; Feed speed 50mm/min, cutting depth 0.05mm, wall thickness is 5.5mm behind the finish-milling; Diamond boring cutter, speed of mainshaft 500r/min are used in the hole that gets out in the last right boring roughing operation during right boring;

is less than 0.005mm.

2. space flight according to claim 1 is characterized in that with the processing method of aluminium base carborundum gyroscope arrangement spare: the blade of the carbide end mill in the said step 2 is handled through nitriding.