CN106041432A - Method for molding six support parts at a time - Google Patents
Method for molding six support parts at a time Download PDFInfo
- Publication number
- CN106041432A CN106041432A CN201610530770.6A CN201610530770A CN106041432A CN 106041432 A CN106041432 A CN 106041432A CN 201610530770 A CN201610530770 A CN 201610530770A CN 106041432 A CN106041432 A CN 106041432A
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- support part
- rudder
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- aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/01—Aircraft parts
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Forging (AREA)
Abstract
The invention relates to a method for molding six support parts at a time, and belongs to the field of aircraft part design and manufacturing. According to the technical scheme, multiple important same-structure connecting pieces of large-scale series aircrafts are machined and molded at a time in a concentrated manner, and the requirement for digitization in-batch machining and production is met. The method has the beneficial effects that the size and the assembly accuracy of the support parts can be improved, meanwhile, consistency of tolerance accuracy of one aircraft is guaranteed, and the effects of uniformity, harmony and reliability of parts and assemblies during assembling can be fully played; a digitization multi-piece one-time concentrated machining and molding technology is adopted, the requirement of a suspension system can be met, and the phenomenon of sinking, caused by the size and the assembling accuracy of the parts, of an aircraft rudder after the aircraft rudder is hung on a vertical safety face can be avoided; and the process is simplified, the machining difficulty is reduced, the production and manufacturing cost is reduced, and the machining schedule is greatly increased. High-accuracy parts are provided for the aircrafts, and trouble-free delivery of the aircrafts is guaranteed.
Description
Technical field
A kind of 6 support part one-step moulding methods of the present invention belong to airplane parts design, manufacture field, relate to large-scale
The mutually isostructural heavy connection of series aircraft carries out concentrated processing molding of more than one piece, meets what digitized batch machining produced
Requirement.
Background technology
Rudder of aircraft has sinkage after being hanging to vertical safety face, and this phenomenon is reflected in rudder and hangs system
Unite, between bearing and rudder, gap is deviateed, tolerance differs or rigidity is poor caused.It is in gravitational load effect that rudder sinks
Under, due in rudder suspension arm, the rigidity of the part such as bearing poor, and the size of each parts of part and build-up tolerance are relatively
Big or differ and cause, the load that rudder bears is divided into two big classes by its action direction, and a class is perpendicular to rudder hinge axis
The power of line (i.e. rotation axis), the aerodynamic force that mainly control surface deflection causes in-flight；The another kind of power being parallel to hinge lines,
The inertia force mainly caused by rudder quality in flight, normal landing.It addition, in order to avoid the vibration of control surface in-flight is drawn
The destruction of supporting structure risen, and make rudder suspension can bear the load of both direction, has two kinds of mentalities of designing at present:
The first design is to be subjected only to aerodynamic loading by suspension, and the inertial load being parallel to hinge is then held by rudder control system
It is subject to.The second design is to be born whole first kind, Equations of The Second Kind load by suspension.Sink to solve rudder and make it hold
By inertial load, aircraft rudder suspension install additional between rudder end rib and fuselage bearing (former 4 install additional after be
6), in order to rudder vertical load is directly transmitted to fuselage, original suspension arm only undertakes aerodynamic loading, thus composition is new
Suspension.
Therefore this support part is just proposed the highest requirement, and improves supporting stand size and assembly precision, ensure same simultaneously
The concordance of airplane tolerance grade, can give full play to zero, the work of assembly uniformity, harmony and reliability when assembling
With, use concentrated processing forming technique of digitized more than one piece, it is possible to meeting suspension requirement, two is to simplify work
Skill, reduce difficulty of processing, reduce manufacturing cost, substantially increase processing progress.High, smart, accurate zero is provided for aircraft
Part product, it is ensured that aircraft fault-free is paid, allows user's is relieved, satisfied.
Summary of the invention
The object of the invention: rudder of aircraft has sinkage after being hanging to vertical safety face, producing this phenomenon has
The factors such as the rigidity of rudder gravitational load, aerodynamic force, inertia force and suspension, tolerance grade produce.In order to solve to fly
Machine rudder problem, the present invention is by increasing rudder hitch point quantity, say, that increased to by 4 original suspended bearers
6, improve suspended bearer precision, it is ensured that slow down stress with the concordance of airplane tolerance and concentrate, it is to avoid because hanging simultaneously
Bearing accuracy tolerance and cause rudder of aircraft to sink；And meet part high-volume machine-shaping and digitized, mechanization
Requirement.
Technical scheme:
A kind of 6 support part one-step moulding methods, described 6 support part are divided into left member and two parts of right member, left
Part is by the identical support part 1 of structure, support part 22, support part 33, and right member is by the identical support part four of structure
4, support part 55, support part 66 composition, described left member and right member collectively constitute a machining cell；
It is as follows that the method implements step:
(1) materials behavior and the dimensions of blank needed for 6 support part are determined；
(2) Digit Control Machine Tool using more than three coordinates implements processing, and procedure of processing is as follows:
The first step: the processing boss in front, hole, curved surface and profile；
Second step: process the groove of upper and lower side with wire rod quality；
3rd step: the processing boss of reverse side, hole, curved surface and profile；
4th step: cutting separates each part；
5th step: pincers worker termination pilot hole also carries out Surface Finishing.
Advantages of the present invention: the compact siro spinning technology of the suspension of rudder, rudder and fuselage can be improved, not only determine
The size of the position aerodynamic balance of rudder rotating shaft, also controls structural strength between suspension, rudder well, fully keeps away
Exempt from rudder of aircraft and be hanging to the appearance of vertical safety face sinkage, shorten suspended bearer length and can substantially increase vertical
To bending support stiffness.Between rudder end rib and fuselage, it is further added by bearing 4 changes 6 into, weight balancing can be solved and ask
Topic, rudder hitch point increasing number, beneficially rudder face support stiffness,
Increase the rigidity of structure of rudder suspension, eliminate or slow down stress and concentrate, it is to avoid suspended bearer rigidity
Sudden change, avoids eccentric load path in structure, reduce local stress and stress is concentrated so that after each associated components and system connect
Uniform force, the system that substantially improves connects load distribution sinkage
In a word, use " 6 one-shot formings of support part " processing, it is possible to make rudder suspension should with rudder, hang down
Tail stabilization and operating system thereof can obtain best stabilized effect, improve rudder sinkage.
Accompanying drawing explanation
Fig. 1 is 6 support part schematic diagram front views of one-shot forming；
Fig. 2 is 6 support part schematic diagram left views of one-shot forming；
Fig. 3 is former single-piece work support part schematic diagram front view；
Fig. 4 is former single-piece work support part schematic diagram left view；
Wherein 1 is support part one, and 2 is support part two, and 3 is support part three, and 4 is support part four, and 5 is bearing zero
Part five, 6 is support part six, and 7 is support part front, and 8 is support part reverse side, and 9 is the signal of former single-piece work support part
Figure front view, 10 is former single-piece work support part schematic diagram front view, and dotted portion is boule portions.
Detailed description of the invention
A kind of 6 support part one-step moulding methods, described 6 support part are divided into left member and two parts of right member, left
Part by identical support part 1 support part 22 of structure, support part 33, right member by the identical support part 44 of structure,
Support part 55, support part 66 form, and described left member and right member collectively constitute a machining cell；
It is as follows that the method implements step:
First " 6 one-shot formings of support part " the simultaneously molding of same structure size parts can be realized, thus meet zero
Part every dimensional accuracy coherence request, it is simple to reduce part machinery difficulty of processing and realize the requirement of digitized, mechanization, it is possible to
Sufficiently improve processing, assembly precision, become the minimizing machining period of several times.Aircraft support part was by independently adding in the past
Work, the most directly impact is the cycle of aircraft manufacturing, according to the construction features of this part, can use open die forging or pretensioning plate
As blank, carry out typesetting, selected reference, allowance, cut size, false boss etc. as shown in Figure 1, work out 6 once
Molding digital process code.
(1) materials behavior and the dimensions of blank needed for this part are determined,
(2) Digit Control Machine Tool using more than three coordinates can implement processing, and procedure of processing is as follows:
The first step: the processing boss in front, hole, curved surface and profile；
Second step: process the groove of upper and lower side with wire rod quality；
3rd step: the processing boss of reverse side, hole, curved surface and profile；
4th step: cutting separates each part,
5th step: pincers worker termination pilot hole also carries out Surface Finishing.
Claims (1)
1. 6 support part one-step moulding methods, described 6 support part are divided into left member and two parts of right member, left member
By the identical support part one (1) of structure, support part two (2), support part three (3), right member is by the identical bearing zero of structure
Part four (4), support part five (5), support part six (6) form, and described left member and right member collectively constitute a machining cell；
It is as follows that the method implements step:
(1) materials behavior and the dimensions of blank needed for 6 support part are determined；
(2) Digit Control Machine Tool using more than three coordinates implements processing, and procedure of processing is as follows:
The first step: the processing boss in front, hole, curved surface and profile；
Second step: process the groove of upper and lower side with wire rod quality；
3rd step: the processing boss of reverse side, hole, curved surface and profile；
4th step: cutting separates each part；
5th step: pincers worker termination pilot hole also carries out Surface Finishing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610530770.6A CN106041432B (en) | 2016-07-06 | 2016-07-06 | A kind of 6 support part one-step moulding methods |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610530770.6A CN106041432B (en) | 2016-07-06 | 2016-07-06 | A kind of 6 support part one-step moulding methods |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106041432A true CN106041432A (en) | 2016-10-26 |
| CN106041432B CN106041432B (en) | 2018-07-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610530770.6A Active CN106041432B (en) | 2016-07-06 | 2016-07-06 | A kind of 6 support part one-step moulding methods |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109325257A (en) * | 2018-08-17 | 2019-02-12 | 四川腾盾科技有限公司 | A kind of modeling method quickly generating flight load analysis model |
| CN109514204A (en) * | 2018-12-26 | 2019-03-26 | 泉州佰源机械科技股份有限公司 | Disk processing technology on two-sided large circle machine |
| CN112719804A (en) * | 2020-12-18 | 2021-04-30 | 湖北三江航天江北机械工程有限公司 | Processing method of air-to-air missile hanging combination for training |
| CN112935707A (en) * | 2019-12-10 | 2021-06-11 | 中航贵州飞机有限责任公司 | Machining method for airplane support type parts |
| CN114102068A (en) * | 2021-12-17 | 2022-03-01 | 江西洪都航空工业集团有限责任公司 | Method and die for machining support arm part with special-shaped structure |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109325257A (en) * | 2018-08-17 | 2019-02-12 | 四川腾盾科技有限公司 | A kind of modeling method quickly generating flight load analysis model |
| CN109514204A (en) * | 2018-12-26 | 2019-03-26 | 泉州佰源机械科技股份有限公司 | Disk processing technology on two-sided large circle machine |
| CN109514204B (en) * | 2018-12-26 | 2021-09-24 | 泉州佰源机械科技股份有限公司 | Processing technology for upper disc of double-sided large circular machine |
| CN112935707A (en) * | 2019-12-10 | 2021-06-11 | 中航贵州飞机有限责任公司 | Machining method for airplane support type parts |
| CN112719804A (en) * | 2020-12-18 | 2021-04-30 | 湖北三江航天江北机械工程有限公司 | Processing method of air-to-air missile hanging combination for training |
| CN114102068A (en) * | 2021-12-17 | 2022-03-01 | 江西洪都航空工业集团有限责任公司 | Method and die for machining support arm part with special-shaped structure |
| CN114102068B (en) * | 2021-12-17 | 2023-10-03 | 江西洪都航空工业集团有限责任公司 | Processing method and die for support arm part with special-shaped structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106041432B (en) | 2018-07-24 |
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Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: Box 34, Hanzhong City, Shaanxi Province, 723213 Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |
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