Structural and Aeroelastic Design of a Joined-Wing UAV

Belardo, Marika; Paletta, Nicola; Palma, Luigi Di; Pecora, M.

doi:10.1061/(asce)as.1943-5525.0000251

Cited by 10 publications

(11 citation statements)

References 22 publications

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“…Other studies [4,5] have demonstrated that the loads under impact and validation in non-linear conditions represent another challenge in landing gear design, in normal, and off nominal flight conditions, such as crash-landing ones. The design of the Racer trap doors requires stiffness considerations and the coupling effects of aerodynamic and inertial load with structure behavior [6]. In the literature, only few examples exist of landing gear trap doors optimization.…”

Section: Main Landing Gear Trap Doors Outlinesmentioning

confidence: 99%

Development of a Morphing Landing Gear Composite Door for High Speed Compound Rotorcraft

Chiariello

Orlando²,

Vitale³

et al. 2020

Aerospace

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In the framework of fast rotorcraft, smoothness and flushness of external aerodynamic surfaces present challenges for high-speed conditions, where aerodynamics is the driver of helicopter performance. For AIRBUS-RACER helicopter the main landing gear trap doors are parts of the lower wing skins (in retracted configuration) affecting helicopter performance by minimizing the drag. Flushness requirements must not be in contrast with the functionally of the Landing gear system that must open and close the doors during the landing gear retraction-extension phases at moderately low velocity. To manage these goals, a novel design logic has been identified to support the trap doors development phase. The identified way to proceed needs of relevant numerical method and tool as well. This method is aimed at identifying the main landing gear composite compartment doors in pre-shaped configuration to match the smoothness and door-stopper engagements over each aerodynamic conditions. The authors propose a detailed non-linear Finite Element method, based on MSC Nastran (MSC Software, Newport Beach, US) SOL-400 solver in which the structure is modelled with deformable contact bodies in a multiple load step sequence, open door condition and pre-shaped, deformed under actuator pre-load, under flight load conditions. The method includes the entire pre-stressed field due to the preload and the actual door stiffness, considering the achieved large displacement to verify the most representative strain field during loads application. The paper defines a robust methodology to predict the deformation and ensure the most appropriate door “pre-bow” and pre-load, in order to achieve the desiderated structural shape that matches aerodynamic requirements. The main result is the identification of a pre-shaped doors configuration for the Airbus RACER Fast Rotorcraft.

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Section: Main Landing Gear Trap Doors Outlinesmentioning

confidence: 99%

Development of a Morphing Landing Gear Composite Door for High Speed Compound Rotorcraft

Chiariello

Orlando²,

Vitale³

et al. 2020

Aerospace

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“…In reference [16] a large review of the project was given, starting from the feasibility study of the full-scale 80-meter HALE propelled with 8 electric motors. The investigators revisited also the calculations presented in their previous works regarding structural loads, strength and buckling analyses, adding interesting information.…”

Section: Studies Of a Hale Joined Wing At The Italian Aerospace Research Center (Cira)mentioning

confidence: 99%

“…Eigenvalue analysis to detect buckling was also used in reference [16] and it was found that the out-ofplane bending stiffness of the front wing was the driving parameter, thus the decision to increase spar-cap thickness of about a 60% was made. References [61,62,88], featuring nonlinear analyses, showed that indeed the bending stiffness has a relevant effect on the stability properties.…”

Section: Buckling Eigenvalue Analysis or Nonlinear Response?mentioning

confidence: 99%

“…Following the previous discussion regarding the buckling analysis, it is in the authors' opinion that a fully nonlinear response study is required to assess where the structure needs to be actually stiffened (see reference [16]), since the buckling eigenvalue analysis may not provide complete information of the true nonlinear structural behavior.…”

Section: Buckling Eigenvalue Analysis or Nonlinear Response?mentioning

confidence: 99%

See 1 more Smart Citation

Challenges, Ideas, and Innovations of Joined-Wing Configurations: A Concept from the Past, an Opportunity for the Future

Cavallaro

Demasi

2016

Progress in Aerospace Sciences

120

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“…Ertugrul Cetinsoy et al [2] worked on Aerodynamic Design and Characterization of a Quad Tilt-Wing UAV via Wind Tunnel Tests which is very useful for us when the design stage was initiated.Junlan Li et al [3] have done Shape Representation of the Nose Cone and also explained same by numerical example.Guowei Cai et al [4] have done work oncomprehensive design methodology for constructing small-scale UAV.Elisa Capello et al [5] have designed a quad rotor UAV.M. Belardo et al [6] have designed the UAV keeping structural and aeroelastic design of a joined wing UAV. Apart from these our project also focuses on aerodynamic modeling.…”

Section: Introductionmentioning

confidence: 99%

Proposed Design of Self Propelled Aerial Vehicle

2014

IJAERD

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Day by day the usage of Unmanned Aerial Vehicle (UAV) increases. But advancements in the design field for UAV were very less. Our project outlines the design of an UAV/model aircraft which is. Our first goal is to achieve a design of UAV which satisfies functions such as seamless joint, most appropriate aerodynamic shape, enough internal space to contain all equipment into it. They are generally fulfilled by aeromodelling.

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Structural and Aeroelastic Design of a Joined-Wing UAV

Cited by 10 publications

References 22 publications

Development of a Morphing Landing Gear Composite Door for High Speed Compound Rotorcraft

Development of a Morphing Landing Gear Composite Door for High Speed Compound Rotorcraft

Challenges, Ideas, and Innovations of Joined-Wing Configurations: A Concept from the Past, an Opportunity for the Future

Proposed Design of Self Propelled Aerial Vehicle

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