Multi-disciplinary analysis and optimisation methodology for conceptual design of a box-wing aircraft

2016 ◽  
Vol 120 (1230) ◽  
pp. 1315-1333 ◽  
Author(s):  
Ishan Roy Salam ◽  
Cees Bil

ABSTRACTThis paper presents a multi-disciplinary analysis methodology for a box-wing aircraft configuration optimised for a given mission scenario. This conceptual design methodology and associated toolchain combines well-established vortex lattice analysis and a newly developed structural analysis tool called WingMASS, allowing the design space to be explored from a combined aerodynamics and structural design perspective. For a given mission scenario, the method optimises a box-wing configuration and compares it with an equivalent conventional configuration. This study shows that, for a given mission, a box-wing configuration can lead to a fuel burn reduction of up to 5% by optimising aspect ratio, horizontal and vertical wing separation.

2021 ◽  
Author(s):  
Saptarshi Datta

A parametric, concurrent design methodology for manufacturing of metallic and composite structures is established. Often, during a new product development, designs prepared using the “Sequential” or “Waterfall” approach are rejected or require significant rework during manufacturing, as designers are not always versed with manufacturing principles. Similarly, manufacturers are not always versed in design principles resulting in designs that do not cater to the functional requirements. The goal of this study is to establish a methodology right from the scope to the detailed design for developing manufacturable structures using the “Concurrent Engineering” approach. Existing literature on “Design Optimization for Manufacturing” predominantly focus on single variable optimization problems geared towards conceptual designs. The designs developed through such optimization cater towards functional performance within a “Fixed Design Space” while not accounting for manufacturing or operational challenges. The methodology developed in this study enables “Design for Manufacturing” for “Detailed Designs” through selection of a conceptual design and subsequently optimizing the selected conceptual design for a set of functional parameters. An “Integrated Product Development” approach is used, whereby, the functional requirements are linked to both design and manufacturing variables and optimization is conducted in an “Augmented Design Space” which is not available when only considering design or manufacturing variables. Three case studies involving both “Conceptual” and “Detailed” designs have been used to illustrate the methodology presented. Case I documents the design of a Flight Control System Bracket. Case II illustrates the use of “2D” composite structures to fabricate a roll frame. Case III involves the development of a “3D” composite door for a light unpressurized aircraft. For each of the three case studies a separate development approach has been employed. Case I uses an analytical approach, Case II uses FEM while CASE III employs a hybrid approach comprising of both FEM and analytical techniques.


Author(s):  
Paul O Jemitola ◽  
Guido Monterzino ◽  
John Fielding ◽  
Craig Lawson

Computational studies were performed at conceptual design level to investigate the structural implications of changing only the tip fin inclinations on a medium-range box wing aircraft. Tip fin inclination refers to the angle the tip fin makes to the vertical body axis of the aircraft. This study is mainly addressed to conceptual designers. For different tip fin inclinations, flight loads were generated using a vortex lattice tool. These flight loads were then input into finite element simulations allowing the preliminary structural elements to be sized. For the category of aircraft considered, no significant variations in wing structural design drivers as a function of tip fin inclination were observed.


1999 ◽  
Author(s):  
Sridhar S. Condoor ◽  
Richard G. Weber

Abstract Conceptual design is the seminal phase in the design process. This phase determines the level of product innovation, the efficiency of the product, and the effectiveness of the down-stream stages of the design process. It has tremendous leverage on the final product performance, cost, and time-to-market. To improve the efficiency of the conceptual design process, the paper combines the parameter analysis methodology with a fundamental insight from robust design. Parameter analysis is a generic design methodology that aids in systematically developing an idea into a viable design. It is particularly useful in creating innovative conceptual designs. Robust design is, often, used after finalizing the conceptual design. Robust design improves the product quality by first reducing the variability in product performance and then, tuning the low variability performance onto the target. The paper presents guidelines for executing the parameter analysis methodology which in turn provides consistent or low variability performance by considering robustness in the very early phases of the design process. The paper illustrates this process with two case studies. The case studies also show how to qualitatively optimize a conceptual design by developing the overall concept before details.


2021 ◽  
Author(s):  
Saptarshi Datta

A parametric, concurrent design methodology for manufacturing of metallic and composite structures is established. Often, during a new product development, designs prepared using the “Sequential” or “Waterfall” approach are rejected or require significant rework during manufacturing, as designers are not always versed with manufacturing principles. Similarly, manufacturers are not always versed in design principles resulting in designs that do not cater to the functional requirements. The goal of this study is to establish a methodology right from the scope to the detailed design for developing manufacturable structures using the “Concurrent Engineering” approach. Existing literature on “Design Optimization for Manufacturing” predominantly focus on single variable optimization problems geared towards conceptual designs. The designs developed through such optimization cater towards functional performance within a “Fixed Design Space” while not accounting for manufacturing or operational challenges. The methodology developed in this study enables “Design for Manufacturing” for “Detailed Designs” through selection of a conceptual design and subsequently optimizing the selected conceptual design for a set of functional parameters. An “Integrated Product Development” approach is used, whereby, the functional requirements are linked to both design and manufacturing variables and optimization is conducted in an “Augmented Design Space” which is not available when only considering design or manufacturing variables. Three case studies involving both “Conceptual” and “Detailed” designs have been used to illustrate the methodology presented. Case I documents the design of a Flight Control System Bracket. Case II illustrates the use of “2D” composite structures to fabricate a roll frame. Case III involves the development of a “3D” composite door for a light unpressurized aircraft. For each of the three case studies a separate development approach has been employed. Case I uses an analytical approach, Case II uses FEM while CASE III employs a hybrid approach comprising of both FEM and analytical techniques.


2020 ◽  
Vol 15 (1) ◽  
pp. 37-44
Author(s):  
El Mehdi Echebba ◽  
Hasnae Boubel ◽  
Oumnia Elmrabet ◽  
Mohamed Rougui

Abstract In this paper, an evaluation was tried for the impact of structural design on structural response. Several situations are foreseen as the possibilities of changing the distribution of the structural elements (sails, columns, etc.), the width of the structure and the number of floors indicates the adapted type of bracing for a given structure by referring only to its Geometric dimensions. This was done by studying the effect of the technical design of the building on the natural frequency of the structure with the study of the influence of the distribution of the structural elements on the seismic response of the building, taking into account of the requirements of the Moroccan earthquake regulations 2000/2011 and using the ANSYS APDL and Robot Structural Analysis software.


Aerospace ◽  
2021 ◽  
Vol 8 (2) ◽  
pp. 54
Author(s):  
Julia A. Cole ◽  
Lauren Rajauski ◽  
Andrew Loughran ◽  
Alexander Karpowicz ◽  
Stefanie Salinger

There is currently interest in the design of small electric vertical take-off and landing aircraft to alleviate ground traffic and congestion in major urban areas. To support progress in this area, a conceptual design method for single-main-rotor and lift-augmented compound electric helicopters has been developed. The design method was used to investigate the feasible design space for electric helicopters based on varying mission profiles and technology assumptions. Within the feasible design space, it was found that a crossover boundary exists as a function of cruise distance and hover time where the most efficient configuration changes from a single-main-rotor helicopter to a lift-augmented compound helicopter. In general, for longer cruise distances and shorter hover times, the lift-augmented compound helicopter is the more efficient configuration. An additional study was conducted to investigate the potential benefits of decoupling the main rotor from the tail rotor. This study showed that decoupling the main rotor and tail rotor has the potential to reduce the total mission energy required in all cases, allowing for increases in mission distances and hover times on the order of 5% for a given battery size.


2012 ◽  
Vol 116 (1178) ◽  
pp. 363-372
Author(s):  
P. O. Jemitola ◽  
J. Fielding ◽  
P. Stocking

Abstract A computational study was performed to compare the stress distributions in finite element torsion box models of a box wing structure that result from employing four different wing/end fin joint fixities. All considered wings were trimmed in pitch. The joint fixities refer to the type of attachment that connects the tip of the fore and aft wings to the end fin. Using loads from a vortex lattice tool, the analysis determined the best wing-joint fixity of a statically loaded idealised box wing configuration by comparing the stress distributions resulting from the different wing joints in addition to other essential aerodynamic requirements. Analysis of the wing joint fixity indicates that the rigid joint is the most suitable.


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