CN104690572B - Weakly rigid aviation structural member small stress filling and shock absorption clamping machining method - Google Patents

Weakly rigid aviation structural member small stress filling and shock absorption clamping machining method Download PDF

Info

Publication number
CN104690572B
CN104690572B CN201510116853.6A CN201510116853A CN104690572B CN 104690572 B CN104690572 B CN 104690572B CN 201510116853 A CN201510116853 A CN 201510116853A CN 104690572 B CN104690572 B CN 104690572B
Authority
CN
China
Prior art keywords
aerospace component
fluid
little stress
aerospace
weak rigid
Prior art date
Application number
CN201510116853.6A
Other languages
Chinese (zh)
Other versions
CN104690572A (en
Inventor
刘波
杨洲元
Original Assignee
四川明日宇航工业有限责任公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 四川明日宇航工业有限责任公司 filed Critical 四川明日宇航工业有限责任公司
Priority to CN201510116853.6A priority Critical patent/CN104690572B/en
Publication of CN104690572A publication Critical patent/CN104690572A/en
Application granted granted Critical
Publication of CN104690572B publication Critical patent/CN104690572B/en

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23QDETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
    • B23Q3/00Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine

Abstract

The invention relates to the field of machining of aviation structural members, in particular to a weakly rigid aviation structural member small stress filling and shock absorption clamping machining method. The method includes the steps of firstly, installing clamps which can support an aviation structural member at the two ends of the aviation structural member in the length direction; secondly, fixedly installing a supporting body penetrating through the aviation structural member between the clamps at the two ends of the aviation structural member; thirdly, filling the inner portion of the aviation structural member with fluid capable of being solidified, wrapping a supporting body in the fluid, and filling the internal space of the aviation structural member; fourthly, solidifying the fluid, completing clamping, and conducting machining. The invention aims at providing the weakly rigid aviation structural member small stress filling and shock absorption clamping machining method which can reduce the machining cost, improve the machining efficiency and reduce the study cost of workers.

Description

The little stress of weak rigid aerospace component fills shock-absorbing clamping processing method

Technical field

The present invention relates to the manufacture field of aerospace component, particularly to the little stress filling of the weak rigid aerospace component of one kind Shock-absorbing clamping processing method.

Background technology

In aerospace component, some is frame-type part, its poor rigidity, and machining can cause judder, or even Cannot process;

In prior art, to the solution technique of this problem it is: using a large amount of fixtures, for the part of different-stiffness, adopt Different clamping scheme, meanwhile, cutting parameter is also individually supporting, and will make a complete scheme, needs to produce system Make substantial amounts of fixture, the position that simultaneously clamps, contact area etc., need through long-term experience accumulation, or complexity is limited Meta-analysis, and after clamping, for the processing of structural member, because the rigidity at each position is different, so processing scheme is also to need Will be through long-term experience accumulation, or finite element analyses of complexity, all very conservative under normal circumstances, because this frame-type Not, if producing vibration in processing, meeting error is very big for aerospace component rigidity;

As previously discussed, these techniques all can the serious processing cost that must increase aerospace component, efficiency is very low simultaneously, work The learning cost of people is also of a relatively high.

Content of the invention

It is an object of the invention to the above-mentioned deficiency in the presence of overcoming prior art, provide a kind of reduce processing cost, Improve the weak rigid aerospace component little stress filling shock-absorbing clamping processing method of working (machining) efficiency, reduction workman's learning cost.

In order to realize foregoing invention purpose, the invention provides technical scheme below:

A kind of little stress of weak rigid aerospace component fills shock-absorbing clamping processing method, the steps include:

A, install at the two ends of described aerospace component length direction and can drag the fixture of aerospace component;

B, between the fixture at aerospace component two ends fixed installation run through the supporter of aerospace component;

C, the fluid that filling can solidify inside aerospace component, Fluid inclusions supporter, fills up in aerospace component Portion space;

D, curing liquid, complete clamping, are processed.

The present invention has directly cast out various other fixtures of the removing main clamp around aerospace component, in aerospace component Two fixtures with aerospace component cooperation are installed at two ends, arrange described supporter between fixture, constitute main holding capacity Structure, and the fluid after described solidification, fill full aerospace component inner space, at this moment the power on aerospace component framework is passed through Fluid after solidification, passed on described supporter, and the fixture cast out of the fluid, instead after solidification, originally from aeronautic structure Clamped outside part, the mode of lifting aerospace component rigidity, become to support inside aerospace component;

Remove substantial amounts of unnecessary fixture, after having clamped, during processing, as long as the fluid rigidity after solidification reaches wanting simultaneously Ask it is no longer necessary to consider whether the problem vibrated, greatly reduce requirement during machining it is not required that the clamping of complexity, Machining scheme, reduces great amount of cost, and technique is more simply too much than in the past, improves working (machining) efficiency, and scheme is convenient simultaneously Easy to learn, reduce workman's learning cost.

As the preferred version of the present invention, in step c, d, described fluid parameter meets: after described fluid solidification, its weight Ensure in the scope that aerospace component will not be caused with deformation, and make the integral rigidity of now aerospace component meet minimum processing Require, according to different aerospace components, using different curable fluids or different meterings, if for some rigidity Very low aerospace component is using the very big fluid of quality after solidification, then it may deform when undressed, thus " described After fluid solidification, its weight ensures aerospace component will not be caused with the scope that deforms, and makes the whole of now aerospace component Body rigidity meets minimum processing request " it is that critically important to the inventive method limits.

As the preferred version of the present invention, in step b, described supporter is strip extrusion, and structure links up symmetrical, just Degree is big, more stable.

As the preferred version of the present invention, described step b particularly as follows:

The strip extrusion running through aerospace component is installed between the fixture at aerospace component two ends, in strip stretching Between body and aerospace component shell space mounting pair supporting construction, described pair supporting construction be hollow structure, its two ends with Aerospace component two ends coordinate, and are fixed on described supporter, and described fixture gives its folder at the outside two ends of aerospace component Hold, described pair supporting construction internally supports aerospace component, and secondary supporting construction is fixedly mounted on supporter simultaneously, supporter It is fixedly connected with fixture again, form integrative-structure, after the fluid solidification of filling, make aerospace component rigidity more more stable greatly.

As the preferred version of the present invention, in step b, described pair supporting construction interlude is extrusion, and two ends are airtight, knot Structure links up symmetrically, and rigidity is big, more stable.

As the preferred version of the present invention, described step c particularly as follows:

Fill the fluid that can solidify, Fluid inclusions pair supporting construction inside aerospace component, fill up aerospace component Inner space.

As the preferred version of the present invention, in step a, described aerospace component two ends drag the fixture shape of aerospace component Shape is matched with aerospace component two ends profile, is respectively provided with some clamping holes above, needs unique two ends to aerospace component Clip position carries out the most comprehensive clamping it is ensured that the precision of overall processing.

Compared with prior art, beneficial effects of the present invention:

Reduce processing cost, improve working (machining) efficiency, reduce workman's learning cost.

Brief description:

Fig. 1 is the flow chart of the inventive method;

Fig. 2 is processed aerospace component schematic diagram by the embodiment of the present invention 1;

Fig. 3 is the two ends fixture and supporter schematic diagram when processing aerospace component in the embodiment of the present invention 1;

Fig. 4 is the scheme of installation of two ends fixture when processing aerospace component in the embodiment of the present invention 1;

Fig. 5 is the schematic diagram only installing two ends fixture when processing aerospace component in the embodiment of the present invention 1;

Fig. 6 is the design sketch that when processing aerospace component in the embodiment of the present invention 1, whole clamping scheme enforcements finish.

Fig. 7 is secondary supporting construction schematic diagram when processing aerospace component in the embodiment of the present invention 1.

Specific embodiment

With reference to embodiment and specific embodiment, the present invention is described in further detail.But this should not be understood Scope for the above-mentioned theme of the present invention is only limitted to below example, all belongs to this based on the technology that present invention is realized The scope of invention.

Embodiment 1

As Fig. 1, a kind of little stress of weak rigid aerospace component fills shock-absorbing clamping processing method, is to the method in Fig. 1 Rough flow illustrates, in the present embodiment, its specific step is:

A, in described aerospace component, (structural member of the present embodiment is as shown in Fig. 2 be the weak rigid structural member of aviation field In most commonly seen frame-like structures part) two ends of length direction install fixture, its shape and the boat that can drag aerospace component Hollow structure part two ends profile matches (fixture described in the present embodiment is rhombus), is respectively provided with some clamping holes above;

B, between the fixture at aerospace component two ends fixed installation run through the supporter of aerospace component, described supporter is Strip extrusion (such as Fig. 3, in the present embodiment, it is cylinder, and its two ends is connected to the middle part of rhombus), in strip stretching (such as Fig. 7, its two ends is hexagon to space mounting pair supporting construction between body and aerospace component shell, coordinates aeronautic structure Hexagonal outline within part framework two ends, this in figure perspective structure is intended merely to represent the position of supporter, secondary in practice The material of supporting construction does not limit perspective or non-perspective), described pair supporting construction is hollow structure, its two ends and aerospace component Two ends coordinate, and are fixed on described supporter, and described pair supporting construction interlude is extrusion, and two ends are airtight, described aviation Outside the fixture at structural member two ends, mounting bar is installed, it is fixedly connected with fixture, fixture is arranged on work by this mounting bar It is processed on platform, in the present embodiment, mounting bar is integrally fixed on the diagonal of the fixture of described rhombus, Stability Analysis of Structures, rigidity Big it is ensured that precision (such as Fig. 4, and the Fig. 5 in the present embodiment is only installing during processing aerospace component of aerospace component processing The schematic diagram of two ends fixture, in order to show state when aerospace component is clamped, in practice, its internal also supporter and pair Supporting construction),;

C, fill inside aerospace component can solidify fluid (for Gypsum Fibrosum or polyurethane foam it is easy to shape, A lot of industries all arrive and can use, and cheap, can use Gypsum Fibrosum for the enough aerospace components of rigidity, low for rigidity , if using Gypsum Fibrosum, proportion is excessive, part is caused to deform in rough, uses polyurethane foam in this case, After polyurethane foam solidification, density is about 0.04-0.06g/cm3, very gently, almost all-pervasive when using, hardening time is about 6-8 hour, has stronger hardness after solidification, but arbitrarily can be cut with cutter, and uses simple to operate, and i.e. can;Poly- Urethane foaming agent is extensively applied in furniture, repairs profession, but borrows in little in machining, in this application, curable Fluid optimization polyurethane foam), Fluid inclusions pair supporting construction, fill up aerospace component inner space (as Fig. 6);

D, curing liquid, complete clamping, are processed that (Fig. 6 can also represent the state after fixed line fluid, in this state Under, you can carry out the processing to aerospace component);

In the present embodiment, specific machined parameters are as follows:

Unit: mm

Cutter title Tool diameter Processing type Maximum cuts width Maximum cutting-in Rotating speed Per tooth feeds Tool blade number Milling cutter 16 Roughing 8 2 800 0.1 4 Milling cutter 16 Polish 5 1.5 800 0.1 4 Milling cutter 12 Roughing 4 0.5 1200 0.1 4 Milling cutter 12 Polish 4 0.5 1200 0.1 4 T shape knife 250 Polish 50 1 50 0.1 9 T shape knife 100 Polish 24 1 100 0.1 10 T shape knife 25 Polish 6 1 800 0.03 4 Milling cutter 20 Polish 1 10 800 0.06 4

Can see, due to employing the present processes, machined parameters, with respect to existing technology, simplify a lot, It is not directed to the special requirement of certain part yet;

So the clamping scheme of the application is coordinated with subsequently simple and direct processing scheme, convenient and swift reduces cost, make simultaneously Not only retained part workman learning cost is low for whole technique, and processing department division of labor people's learning cost is also low.

In step c, d, described fluid parameter meets: after described fluid solidification, its weight ensures will not be to aeronautic structure Part causes the scope deforming, and makes the integral rigidity of now aerospace component meet minimum processing request.

Claims (7)

1. a kind of little stress of weak rigid aerospace component fills shock-absorbing clamping processing method, the steps include:
A, install at the two ends of described aerospace component length direction and can drag the fixture of aerospace component;
B, between the fixture at aerospace component two ends fixed installation run through the supporter of aerospace component;
C, the fluid that filling can solidify inside aerospace component, Fluid inclusions supporter, fills up aerospace component internal empty Between;
D, curing liquid, complete clamping, are processed.
2. the little stress filling shock-absorbing clamping processing method of weak rigid aerospace component according to claim 1 it is characterised in that In step c, d, described fluid parameter meets: after described fluid solidification, its weight ensures aerospace component will not caused become The scope of shape, and make the integral rigidity of now aerospace component meet minimum processing request.
3. the little stress filling shock-absorbing clamping processing method of weak rigid aerospace component according to claim 1 it is characterised in that In step b, described supporter is strip extrusion.
4. the little stress filling shock-absorbing clamping processing method of weak rigid aerospace component according to claim 3 it is characterised in that Described step b particularly as follows:
Between the fixture at aerospace component two ends, fixed installation runs through the strip extrusion of aerospace component, in strip stretching Between body and aerospace component shell space mounting pair supporting construction, described pair supporting construction be hollow structure, its two ends with Aerospace component two ends coordinate, and are fixed on described supporter.
5. the little stress filling shock-absorbing clamping processing method of weak rigid aerospace component according to claim 4 it is characterised in that In step b, described pair supporting construction interlude is extrusion, and two ends are airtight.
6. the little stress filling shock-absorbing clamping processing method of weak rigid aerospace component according to claim 4 it is characterised in that Described step c particularly as follows:
Fill the fluid that can solidify, Fluid inclusions pair supporting construction inside aerospace component, fill up inside aerospace component Space.
7. the little stress filling shock-absorbing clamping processing method of weak rigid aerospace component according to claim 1 it is characterised in that In step a, described aerospace component two ends drag the clamp-shaped of aerospace component and aerospace component two ends profile matches, It is respectively provided with some clamping holes above.
CN201510116853.6A 2015-03-17 2015-03-17 Weakly rigid aviation structural member small stress filling and shock absorption clamping machining method CN104690572B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201510116853.6A CN104690572B (en) 2015-03-17 2015-03-17 Weakly rigid aviation structural member small stress filling and shock absorption clamping machining method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201510116853.6A CN104690572B (en) 2015-03-17 2015-03-17 Weakly rigid aviation structural member small stress filling and shock absorption clamping machining method

Publications (2)

Publication Number Publication Date
CN104690572A CN104690572A (en) 2015-06-10
CN104690572B true CN104690572B (en) 2017-02-01

Family

ID=53338325

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201510116853.6A CN104690572B (en) 2015-03-17 2015-03-17 Weakly rigid aviation structural member small stress filling and shock absorption clamping machining method

Country Status (1)

Country Link
CN (1) CN104690572B (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104889706B (en) * 2015-05-28 2017-06-20 北京航空航天大学 A kind of reverse segmental machining method and device of weak rigid workpiece
CN107234862A (en) * 2016-03-29 2017-10-10 成都飞机工业(集团)有限责任公司 A kind of holding method of honeycomb core
CN106378655B (en) * 2016-11-29 2018-06-08 武汉理工大学 A kind of weak rigid workpiece series-parallel connection intelligence grip device
CN107838704A (en) * 2017-09-29 2018-03-27 江西昌河航空工业有限公司 A kind of method being processed to U-shape structure carbon fiber blank
CN108655669A (en) * 2018-05-18 2018-10-16 陕西测易机电设备有限公司 A kind of processing method of space flight and aviation thin-walled parts

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1130285A (en) * 1967-05-05 1968-10-16 Rolls Royce Method of making an aerofoil shaped blade for a fluid flow machine
US20100122459A1 (en) * 2008-11-17 2010-05-20 General Electric Company Method of making wind turbine blade
CN101912990B (en) * 2010-07-27 2011-11-23 沈阳黎明航空发动机(集团)有限责任公司 Method for milling and vibration-damping blisk
US20120027609A1 (en) * 2011-05-17 2012-02-02 Prasad Ogde Wind turbine rotor blade with precured fiber rods and method for producing the same
CN103786003B (en) * 2014-01-15 2016-04-06 西安航空动力股份有限公司 A kind of processing method of aero-engine guide vane listrium
CN106216479A (en) * 2014-04-22 2016-12-14 李明 A kind of manufacturing process of hollow unit
CN104259883B (en) * 2014-09-15 2016-06-01 北京卫星制造厂 A kind of filling method for supporting strengthening thin-walled part processing rigidity
CN104400452A (en) * 2014-10-31 2015-03-11 沈阳黎明航空发动机(集团)有限责任公司 High-temperature alloy honeycomb part milling processing clamping method

Also Published As

Publication number Publication date
CN104690572A (en) 2015-06-10

Similar Documents

Publication Publication Date Title
CN103934713A (en) Needle type locating adjustable hydraulic type clamp for machining of tenon of precisely forged blade
CN204819086U (en) Nonrust steel pipe polisher
CN202684618U (en) Feeding system of cutter
CN103817957B (en) The tool locating method of adhesive bonding of composites co-curing
WO2005061182A3 (en) Reconfigurable workpiece support
CN204209473U (en) Two sides location type planer frock
CN103470861B (en) Vertical pipe vibration vibration damping pipe carrier
CN103201064A (en) Method for machining a casing of an aircraft turboshaft engine and scraper tool for implementing said method
CN204621124U (en) A kind of clipping chuck of split being suitable for annular workpieces
CN202336765U (en) Mechanical hand structure of clamping workpiece
CN205184290U (en) Thin wall sheet metal component numerical control milling anchor clamps
RU2012154199A (en) System for fastening turbo machines with axial movement of the working body, and also the method for producing such a system
CN103962807B (en) A kind of method of ram Flexible Manufacture
FI904433A0 (en) Method for reducing the pressure drop in the fluid flow, as well as in tanks for fluid flow in hydraulic systems
CN203509263U (en) Clamp of blade machining groove
CN203343830U (en) Bridge type numerical control planogrinder
DE602006002316D1 (en) Adjustable fittings for attaching support members to fluid lines, including aircraft fuel lines, and related systems and methods
CN104625803A (en) Universal clamp for large milling machine milling plane
CN207757255U (en) A kind of speed reducer precision component that clamping effect is good processing perforating device
CN202591649U (en) Vibration damping boring bar
CN202684137U (en) Hydraulic clamp for numerically controlled lathe
CN204585043U (en) A kind of tool for clamp cylinders shape object
CN102756397A (en) Punching tool for automobile sealing strip
CN102528667B (en) Metal cutting machine with grinding wheel protecting device
CN103846698A (en) Composite material long purlin milling flexible tool and clamping method of same

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
COR Change of bibliographic data
CB02 Change of applicant information

Address after: 618400 Deyang City, Shifang Province Economic Development Zone (North), blue sky Avenue, No. 3

Applicant after: SICHUAN MINGRI AEROSPACE INDUSTRY CO., LTD.

Address before: 618400 Deyang City, Shifang Province Economic Development Zone (North), blue sky Avenue, No. 3

Applicant before: Shifang Mingri Aerospace Industry Co.,Ltd.

C14 Grant of patent or utility model
GR01 Patent grant