Positioning method and assembly precision for aircraft wing skin

Guo, Fanghong; Wang, Zhongqi; Kang, Young Jin; Li, Xining; Chang, Zhengping; Wang, Binbin

doi:10.1177/0954405416640168

Cited by 15 publications

(11 citation statements)

References 14 publications

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“…V ij (i = 1, 2, ., 2n) is the displacement calculated by FEA at the ith point due to the unit deviation at the jth source of variation. V is the sensitivity matrix and U is the total spring-back (assembly variation) as in equation (19)…”

Section: Deformation Prediction Of Rigid-flexible Hybrid Assemblymentioning

confidence: 99%

“…Equations of statics of elastic beam are used to calculate the elastic deformation of panel component while considering the nonlinear behavior of physical expressions. Guo et al 19 developed a low-cost flexible assembly tooling system for different wing components. Two kinds of positioning method and the corresponding assembly precision were studied to improve the assembly accuracy of aircraft wing components.…”

Section: Introductionmentioning

confidence: 99%

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Assembly variation analysis of complicated products based on rigid–flexible hybrid vector loop

Liu

Zhou

Qiu

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part B:

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The performance of mechanical products is closely related to their key feature errors. It is essential to predict the final assembly variation by assembly variation analysis to ensure product performance. Rigid–flexible hybrid construction is a common type of mechanical product. Existing methods of variation analysis in which rigid and flexible parts are calculated separately are difficult to meet the requirements of these complicated mechanical products. Another methodology is a result of linear superposition with rigid and flexible errors, which cannot reveal the quantitative relationship between product assembly variation and part manufacturing error. Therefore, a kind of complicated products’ assembly variation analysis method based on rigid–flexible vector loop is proposed in this article. First, shapes of part surfaces and sidelines are estimated according to different tolerance types. Probability density distributions of discrete feature points on the surface are calculated based on the tolerance field size with statistical methods. Second, flexible parts surface is discretized into a set of multi-segment vectors to build vector-loop model. Each vector can be orthogonally decomposed into the components representing position information and error size. Combining the multi-segment vector set of flexible part with traditional rigid part vector, a uniform vector-loop model is constructed to represent rigid and flexible complicated products. Probability density distributions of discrete feature points on part surface are regarded as inputs to calculate assembly variation values of products’ key features. Compared with the existing methods, this method applies to the assembly variation prediction of complicated products that consist of both rigid and flexible parts. Impact of each rigid and flexible part’s manufacturing error on product assembly variation can be determined, and it provides the foundation of parts tolerance optimization design. Finally, an assembly example of phased array antenna verifies effectiveness of the proposed method in this article.

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Section: Deformation Prediction Of Rigid-flexible Hybrid Assemblymentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Assembly variation analysis of complicated products based on rigid–flexible hybrid vector loop

Liu

Zhou

Qiu

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part B:

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show abstract

“…In Zhong et al, 43 the assembly accuracy range of aircraft wing skin is (20.273, + 0.350) mm based on contour board. And it becomes (20.36, + 0.25) mm based on coordinate holes.…”

Section: Experimental Verificationmentioning

confidence: 99%

Geometric accuracy design and error compensation of a one-translational and three-rotational parallel mechanism with articulated traveling plate

Sun

Wang

Lian

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part B:

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The demands for advanced and flexible docking equipment are increasing in the fields of aerospace, shipbuilding and construction machinery. Position and orientation accuracy is one of the most important criteria, which would directly affect the docking quality. Taking a novel one-translational and three-rotational docking equipment, referred to as PaQuad parallel mechanism as example, this article proposed an accuracy improvement strategy by geometric accuracy design and error compensation. Drawing mainly on screw theory, geometric error modeling of PaQuad parallel mechanism was first carried out via four independent routes. Joint perturbations and geometric errors were included in each route error twist. Wrenches due to articulated traveling plate were applied to eliminate joint perturbations. Then, geometric accuracy design was implemented at component and substructure levels. The basic principle was to transfer geometric errors into dimensional or geometric tolerance. High-precision machining/assembling techniques were applied to satisfy the tolerance. Finally, error compensation resorting to kinematic calibration was implemented at mechanism level. It can be summarized as identification modeling, measurement planning, and parameter identification and modification. Maximum deviations of PaQuad parallel mechanism before calibration experiment were 0.01 mm, À0:197 8 , À0:522 8 , and 2:908 8. And they become 0.01 mm, 0:027 8 , 0:046 8 , and 0:521 8 after kinematic calibration. Orientation accuracy of PaQuad parallel mechanism has improved one order of magnitude. It proves the effectiveness of accuracy improvement in terms of geometric accuracy design and error compensation.

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“…The increased pressure on current aircraft manufacturers to achieve high rate production has led to investigations into improvements in assembly methods, changes to build philosophy and re-design of systems and structure to improve assembly performance [6] [7][8] [10]. Automating structural assembly tasks has received significant research attention, with accurate metrology and component positioning solution being a key enable for any automated processes [11] [12]. In comparison, automation of systems assembly tasks is more difficult due to their complexity, varying access conditions and part handling.…”

Section: Introductionmentioning

confidence: 99%

“…[7][8][9][10] Automating structural assembly tasks has received significant research attention, with accurate metrology and component positioning solution being a key enable for any automated processes. 11,12 In comparison, automation of systems assembly tasks is more difficult due to their complexity, varying access conditions and part handling. A proposal to increase production rate in the near term and enable automation in the far term preequips the major structural components with systems components before the wing-box is completed, 13 mimicking common practice in the automotive and other industries.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation into aircraft system manual assembly performance under varying structural component orientations

Judt

Lawson

Lockett

2019

Proceedings of the Institution of Mechanical Engineers, Part B:

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Installation of aircraft wing systems is a bottleneck in the assembly process. This phase is typically composed of many work packages, taking hundreds of man-hours per wing. In addition to this volume of work, tasks are specialized and completed in a difficult environment in terms of access and visibility. In current industrial practice, the wing is mounted horizontally on a transport trolley, which exposes the workforce to prolonged periods of overhead working. Future wing designs may consider a pre-equipping build philosophy, where systems are installed to major structure assemblies before the wing box is assembled. This allows for a change in the orientation and position of the major structure and provides new freedoms in assembly station design and layout. This research presents results of experiments to investigate manual assembly performance of aircraft wing systems, under varying wing structure orientation. A mock-up of a section of an A320 aircraft wing front spar, mounted on a rotation device, functions as the testbed. Manual installation activities are then conducted to emulate real aircraft system equipping for electric harnesses, raceways and hot air ducts. The results show a best-case assembly performance change of 36% for electric system installation activities of cable harnesses and raceway housing components. Tilted and horizontal orientations of the structure show the highest time reductions, with the vertical orientation either non-conclusive or increasing the assembly time. The outcomes of this study are intended to aid in effective trade-off decision making for future wing systems and assembly station layouts from the perspective of structural orientation and assembly task interaction.

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Positioning method and assembly precision for aircraft wing skin

Cited by 15 publications

References 14 publications

Assembly variation analysis of complicated products based on rigid–flexible hybrid vector loop

Assembly variation analysis of complicated products based on rigid–flexible hybrid vector loop

Geometric accuracy design and error compensation of a one-translational and three-rotational parallel mechanism with articulated traveling plate

Experimental investigation into aircraft system manual assembly performance under varying structural component orientations

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