CN105690301A - Thermal deformation compensation clamp for aircraft assembly and assembly method - Google Patents
Thermal deformation compensation clamp for aircraft assembly and assembly method Download PDFInfo
- Publication number
- CN105690301A CN105690301A CN201610177471.9A CN201610177471A CN105690301A CN 105690301 A CN105690301 A CN 105690301A CN 201610177471 A CN201610177471 A CN 201610177471A CN 105690301 A CN105690301 A CN 105690301A
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- CN
- China
- Prior art keywords
- expansion
- assembly
- assembling jig
- wing
- expansion oplate
- Prior art date
- Legal status (The legal status 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 status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
- B25B11/02—Assembly jigs
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Connection Of Plates (AREA)
Abstract
The invention belongs to the technical field of aircraft assembly, and particularly relates to a thermal deformation compensation clamp for aircraft assembly and an assembly method. When existing aircraft assembly clamps are designed, the difference between the coefficient of thermal expansion of the clamps and the coefficient of thermal expansion of product materials is not considered, the dimensional deviation exists between the assembly clamps and products when the temperature difference is large, and assembly coordination is difficult. Especially in the northeast region, the temperature difference is large, the dimensional deviation exists between the assembly clamps and the products when the temperature difference is large, and assembly coordination is difficult. According to the thermal deformation compensation clamp for aircraft assembly and the assembly method, a structure basically identical with the products in thermal deformation is provided, thermal deformation of the assembly clamps and thermal deformation of the products are basically uniform when the environment temperature changes, and the assembly coordination problem of the clamps and the products caused by the temperature difference is solved.
Description
Technical field
The invention belongs to aircraft mounting technology field, be specifically related to a kind of aircraft assembling thermal distortion compensation fixture and assembly method。
Background technology
Existing aircraft assembling jig does not consider and the difference of product material thermal coefficient of expansion when design, and assembling jig and product exist dimensional discrepancy when the temperature difference is bigger, the problem of assembly coordination difficulty。Particularly the Northeast's temperature difference is big, and assembling jig and product exist dimensional discrepancy when the temperature difference is bigger, assembly coordination difficulty。
Summary of the invention
The technical problem to be solved is to provide a kind of structure basically identical with product thermal deformation, it is ensured that the thermal deformation when variation of ambient temperature of assembling jig and product is basically identical, eliminates the assembly coordination problem that fixture produces because of the temperature difference with product。
The aircraft assembling thermal distortion compensation fixture of the present invention, for compensating the dimensional discrepancy that assembling jig and wing produce when the temperature difference is bigger, this fixture is provided with some assembling jig expansion oplates along assembly direction on assembling jig skeleton, this expansion oplate selects the material same or like with wing thermal coefficient of expansion, and wing suspension joint localizer location and installation successively is on described assembling jig expansion oplate；Between each assembling jig expansion oplate, connected by expansion oplate connector, wherein inside assembling jig expansion oplate, have, along assembly direction, the flexible guide finger of expansion oplate that can move along expansion oplate oblong slots。
Aircraft thermal distortion compensation assembly method, have employed above-mentioned thermal distortion compensation fixture, comprises the following steps:
Step 1: choose the material of expansion oplate according to the thermal coefficient of expansion of wing；
Step 2: by the thermal coefficient of expansion of wing and assembling jig framework material, calculate thermal deformation direction and the numerical value of wing during variations in temperature；
Step 3: according to the thermal deformation direction that obtains and numerical value to determine expansion oplate layout on assembling jig skeleton；
Step 4: the expansion oplate of processing requirement and shape。
The assembling jig of the present invention and product are without the coordination problem produced because of the temperature difference。Ensure that the accuracy of product。
Accompanying drawing explanation
Fig. 1 is the assembling jig of aircraft wing；
Fig. 2 is the connection diagram of expansion oplate。
Wherein, 1-assembling jig expansion oplate；2-wing suspension joint localizer；3-assembling jig skeleton；4-expansion oplate connector；5-expansion oplate stretches guide finger；6-expansion oplate oblong slots
Detailed description of the invention
A kind of aircraft assembling thermal distortion compensation fixture, for compensating the dimensional discrepancy that assembling jig and wing produce when the temperature difference is bigger, this fixture is provided with some assembling jig expansion oplates 1 along assembly direction on assembling jig skeleton 3, this expansion oplate 1 selects the material same or like with wing thermal coefficient of expansion, and wing suspension joint localizer 2 location and installation successively is on described assembling jig expansion oplate 1；Between each assembling jig expansion oplate 1, connected by expansion oplate connector 4, wherein have, along assembly direction, the flexible guide finger 5 of expansion oplate that can move along expansion oplate oblong slots 6 in assembling jig expansion oplate 1 inside。
A kind of aircraft thermal distortion compensation assembly method, have employed above-mentioned thermal distortion compensation fixture, and the method comprises the following steps:
Step 1: choose the material of expansion oplate 1 according to the thermal coefficient of expansion of wing；
Step 2: by the thermal coefficient of expansion of wing and assembling jig skeleton 3 material, calculate thermal deformation direction and the numerical value of wing during variations in temperature；
Step 3: according to the thermal deformation direction that obtains and numerical value to determine the expansion oplate 1 layout on assembling jig skeleton 3；
Step 4: the expansion oplate of processing requirement and shape。
Claims (2)
1. an aircraft assembling thermal distortion compensation fixture, for compensating the dimensional discrepancy that assembling jig and wing produce when the temperature difference is bigger, it is characterized in that: this fixture is provided with some assembling jig expansion oplates (1) along assembly direction on assembling jig skeleton (3), this expansion oplate (1) selects the material same or like with wing thermal coefficient of expansion, and wing suspension joint localizer (2) location and installation successively is on described assembling jig expansion oplate (1)；Between each assembling jig expansion oplate (1), being connected by expansion oplate connector (4), wherein having along assembly direction in assembling jig expansion oplate (1) inside can along the flexible guide finger (5) of the expansion oplate of expansion oplate oblong slots (6) movement。
2. an aircraft thermal distortion compensation assembly method, have employed the thermal distortion compensation fixture described in claim 1, it is characterised in that the method comprises the following steps:
Step 1: choose the material of expansion oplate (1) according to the thermal coefficient of expansion of wing；
Step 2: by the thermal coefficient of expansion of wing and assembling jig skeleton (3) material, calculate thermal deformation direction and the numerical value of wing during variations in temperature；
Step 3: according to the thermal deformation direction that obtains and numerical value to determine the expansion oplate (1) layout on assembling jig skeleton (3)；
Step 4: the expansion oplate of processing requirement and shape。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610177471.9A CN105690301A (en) | 2016-03-25 | 2016-03-25 | Thermal deformation compensation clamp for aircraft assembly and assembly method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610177471.9A CN105690301A (en) | 2016-03-25 | 2016-03-25 | Thermal deformation compensation clamp for aircraft assembly and assembly method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105690301A true CN105690301A (en) | 2016-06-22 |
Family
ID=56232818
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610177471.9A Pending CN105690301A (en) | 2016-03-25 | 2016-03-25 | Thermal deformation compensation clamp for aircraft assembly and assembly method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105690301A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107263044A (en) * | 2017-04-27 | 2017-10-20 | 浙江大学 | A kind of design method for the large aircraft outer wing wing box assembly system for considering cause of deformation |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3973766A (en) * | 1975-03-27 | 1976-08-10 | Vernon Ernest Heath | Model aircraft wing construction jig |
| JP2001121362A (en) * | 1999-10-21 | 2001-05-08 | Kawasaki Heavy Ind Ltd | Three dimensional building method for special structure and building system device thereof |
| CN102632383A (en) * | 2012-04-19 | 2012-08-15 | 西安飞机工业（集团）有限责任公司 | Airplane assembly jig |
| CN102699843A (en) * | 2012-04-19 | 2012-10-03 | 西安飞机工业（集团）有限责任公司 | Aircraft assembly fixture made of materials with different expansion coefficients |
| CN104626606A (en) * | 2015-01-04 | 2015-05-20 | 哈尔滨飞机工业集团有限责任公司 | Carbon fiber composite material forming tool |
-
2016
- 2016-03-25 CN CN201610177471.9A patent/CN105690301A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3973766A (en) * | 1975-03-27 | 1976-08-10 | Vernon Ernest Heath | Model aircraft wing construction jig |
| JP2001121362A (en) * | 1999-10-21 | 2001-05-08 | Kawasaki Heavy Ind Ltd | Three dimensional building method for special structure and building system device thereof |
| CN102632383A (en) * | 2012-04-19 | 2012-08-15 | 西安飞机工业（集团）有限责任公司 | Airplane assembly jig |
| CN102699843A (en) * | 2012-04-19 | 2012-10-03 | 西安飞机工业（集团）有限责任公司 | Aircraft assembly fixture made of materials with different expansion coefficients |
| CN104626606A (en) * | 2015-01-04 | 2015-05-20 | 哈尔滨飞机工业集团有限责任公司 | Carbon fiber composite material forming tool |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107263044A (en) * | 2017-04-27 | 2017-10-20 | 浙江大学 | A kind of design method for the large aircraft outer wing wing box assembly system for considering cause of deformation |
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| C06 | Publication | ||
| PB01 | Publication | ||
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| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160622 |