Manufacturing Aspects of Creating Low-Curvature Panels for Prospective Civil Aircraft

Dubovikov, Evgeny; Fomin, Danil; Guseva, Natalia Vyacheslavovna; Kondakov, Ivan; Kruychkov, Evgeny; Mareskin, Ivan; Shanygin, A. N.

doi:10.3390/aerospace6020018

Cited by 5 publications

(4 citation statements)

References 5 publications

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“…Work by Rahman and Whidborne [6] has shown that a feedback loop is needed for enhanced lateral stability due to the oscillation and the damping factor of the Dutch roll mode. Apart from the potential flying and handling qualities issues, the BWB concept is also challenged with regards to its weight efficiency [7]. In theory, flying wings can be designed to be inherently stable [8] and there have been 'flying wings' that have flown successfully; an example of this being the Northrop YB-49.…”

Section: Introductionmentioning

confidence: 99%

Conceptual Design, Flying, and Handling Qualities Assessment of a Blended Wing Body (BWB) Aircraft by Using an Engineering Flight Simulator

2020

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The Blended Wing Body (BWB) configuration is considered to have the potential of providing significant advantages when compared to conventional aircraft designs. At the same time, numerous studies have reported that technical challenges exist in many areas of its design, including stability and control. This study aims to create a novel BWB design to test its flying and handling qualities using an engineering flight simulator and as such, to identify potential design solutions which will enhance its controllability and manoeuvrability characteristics. This aircraft is aimed toward the commercial sector with a range of 3000 nautical miles, carrying 200 passengers. The BWB design was flight tested at an engineering flight simulator to first determine its static stability through a standard commercial mission profile, and then to determine its dynamic stability characteristics through standard dynamic modes. Its flying qualities suggested its stability with a static margin of 8.652% of the mean aerodynamic chord (MAC) and consistent response from the pilot input. In addition, the aircraft achieved a maximum lift-to-drag ratio of 28.1; a maximum range of 4,581 nautical miles; zero-lift drag of 0.005; while meeting all the requirements of the dynamic modes.

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Section: Introductionmentioning

confidence: 99%

Conceptual Design, Flying, and Handling Qualities Assessment of a Blended Wing Body (BWB) Aircraft by Using an Engineering Flight Simulator

2020

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“…This design follows very similar characteristics to that of the 'flying wing', including th e downside that, without a horizontal stabiliser, the aircraft is liable to longitudinal instability, which is a phenomenon that has been reported for various prototypes and studies (Okonkwo and Smith, 2016). Apart from the potential flying and handling qualities issues, the BWB concept is also challenged with regards to its weight efficiency (Dubovikov et al, 2019). In theory, flying wings can be designed to be inherently stable (Karl and Wohlfahrt, 1994) and there have been 'flying wings' that have flown successfully; an example of this being the Northrop YB-49.…”

Section: Introductionmentioning

confidence: 94%

Conceptual Design optimization of a Blended Wing Body (BWB) Aircraft Using Flying and Handling Qualities Assessment

Humphreys-Jennings¹,

Lappas²,

Dm³

2019

Preprint

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The Blended Wing Body (BWB) configuration is considered to have the potential of providing significant advantages when compared to conventional aircraft designs. At the same time, numerous studies have reported that technical challenges exist in many areas of its design, including stability and control. This study aims to create a novel BWB design to test its flying and handling qualities using an engineering flight simulator and as such, to identify potential design solutions which will enhance its controllability and manoeuvrability characteristics. This aircraft is aimed toward the commercial sector with a range of 3,000 nautical miles, carrying a payload of 20,000kg. In the engineering flight simulator a flight test was undertaken; first, to determine the BWB design’s static stability through a standard commercial mission profile, and then to determine its dynamic stability characteristics through standard dynamic modes. Its flying qualities suggested its stability with a static margin of 8.652% of the Mean Aerodynamic Chord (MAC) and consistent response from the pilot input. In addition, the aircraft achieved a maximum lift-to-drag ratio of 28.1; a maximum range of 4,581 nautical miles; zero-lift drag of 0.005; and meeting all the requirements of the dynamic modes.

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“…Porous materials are a class of substances that contain numerous interconnected or enclosed pores or voids inside, with the key features of high porosity, low density, large specific surface area, and high specific strength. These characteristics contribute to their lightweight, good sound and heat insulation, high permeability, and energy adsorption capacity, making porous materials suitable for widespread applications in aerospace, automotive, construction, and other industries [1][2][3]. The development of porous materials has therefore become an active area of research, with scientists exploring new methods to prepare and modify porous materials with desired properties for specific applications.…”

Section: Introductionmentioning

confidence: 99%

Examination of Beam Theories for Buckling and Free Vibration of Functionally Graded Porous Beams

Wu,

Li,

Bao

et al. 2024

Materials

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This paper examines the accuracy and effectiveness of various beam theories in predicting the critical buckling loads and fundamental frequencies of functionally graded porous (FGP) beams whose material properties change continuously across the thickness. The beam theories considered are classical beam theory (CBT), first-order shear deformation beam theory (FSDBT), third-order shear deformation beam theory (TSDBT), and the broken-line hypothesis-based shear deformation beam theory (BSDBT). Governing equations for those beam theories are formulated by using the Hamilton’s principle and are then solved by means of the generalised differential quadrature method. Finite element simulation solutions are provided as reference results to assess the predictions of those beam theories. Comprehensive numerical results are presented to evaluate the influences of the porosity distribution and coefficient, slenderness ratio, and boundary condition on the difference between theoretical predictions and simulation results. It is found that the differences significantly increase as the porosity coefficient rises, and this effect becomes more noticeable for the rigid beam with a smaller slenderness ratio. Nonetheless, the results produced by the BSDBT are always the closest to simulation ones. The findings in this paper will contribute to the establishment of more refined theories for the mechanical analysis of FGP structures.

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Manufacturing Aspects of Creating Low-Curvature Panels for Prospective Civil Aircraft

Cited by 5 publications

References 5 publications

Conceptual Design, Flying, and Handling Qualities Assessment of a Blended Wing Body (BWB) Aircraft by Using an Engineering Flight Simulator

Conceptual Design, Flying, and Handling Qualities Assessment of a Blended Wing Body (BWB) Aircraft by Using an Engineering Flight Simulator

Conceptual Design optimization of a Blended Wing Body (BWB) Aircraft Using Flying and Handling Qualities Assessment

Examination of Beam Theories for Buckling and Free Vibration of Functionally Graded Porous Beams

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