Simplified 2D Skin Lattice Models for Multi-Axial Camber Morphing Wing Aircraft

Alsaidi, Bashir; Joe, Woong Yeol; Akbar, Muhammad

doi:10.3390/aerospace6080090

Cited by 5 publications

(3 citation statements)

References 38 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The homogenization method for a structural optimization procedure has been shown to dramatically increase stiffness [44], structural compliance [45], structural vibration [43], and energy absorption [46]. One of most common applications of using homogenization methods is design and analysis of morphing or adaptive structures for aircraft design [47][48][49][50]. In particular, lattice structure for flexible as well as stiff skin structure for morphing wing is one of major applications [51][52][53].…”

Section: Discussionmentioning

confidence: 99%

Homogenization Methods of Lattice Materials

Somnic

Joe

2022

Encyclopedia

View full text Add to dashboard Cite

The existing methods for analyzing the behaviors of lattice materials require high computational power. The homogenization method is the alternative way to overcome this issue. Homogenization is an analysis to understand the behavior of an area of lattice material from a small portion for rapid analysis and precise approximation. This paper provides a summary of some representative methodologies in homogenization.

show abstract

Section: Discussionmentioning

confidence: 99%

Homogenization Methods of Lattice Materials

Somnic

Joe

2022

Encyclopedia

View full text Add to dashboard Cite

show abstract

“…In the sense of the technology readiness level (TRL) of morphing aircraft, various levels of analysis and validation have been performed that range from analytical and numerical works to large-scale wind tunnel and flight tests [ 43 , 71 , 84 ]. Emphasizing manufacturability and feasibility according to implementation aspects, skin structure design and analysis of morphing wings is probably one of the most popular studied subjects [ 85 , 86 , 87 , 88 ].…”

Section: Introductionmentioning

confidence: 99%

Enhanced Range and Endurance Evaluation of a Camber Morphing Wing Aircraft

Joe

Majid

2023

Biomimetics

View full text Add to dashboard Cite

Flight range, endurance, maneuverability, and agility are the key elements that determine an aircraft’s performance. Both conventional and morphing wing aircraft have been well studied and estimated in all aspects of performance. When considering the performance of morphing aircraft, most works address aspects of the aerodynamical performance such as L and D as well as flight envelopes for flight dynamics and control perspectives. However, the actual benefits of adopting morphing technologies in practical aspects such as aircraft operation, mission planning, and sustainability have not been addressed so far. Thus, this paper addresses the practical aspect of the benefits when adopting a camber morphing wing aircraft. Identical geometrical and computational conditions were applied to an already-existing aircraft: the RQ-7a Shadow. The wing structure was switched between a fixed wing and a camber morphing wing to generate conventional and morphing wing geometries. The fixed-wing cases had varying flap deflection angles, and the camber morphing wing cases had varying camber rates from 4% to 8%. Once the CL values of the fixed and morphing wing cases were matched up to two significant figures, the CD and CL/CD were analyzed for these matching cases to calculate the flight endurance, range, and improvement. When NACA 6410 is adopted, a 17% improvement in flight range and endurance average was expected. In the case of NACA 8410, an average 60% improvement was expected.

show abstract

“…The skin was not attached to the ribs but was free to slide over them during morphing. Alsaidi et al [19,20] analyzed skins for multi-axial camber morphing wings made of lattice structures. Arena et al [21] developed a multi-segment adaptive trailing edge morphing wing with skin made of hard segments and elastomeric layers supported by foam pieces at the locations of the hinges of the trailing edge segments.…”

Section: Introductionmentioning

confidence: 99%

Parametric Study of a Composite Skin for a Twist-Morphing Wing

Bishay

Aguilar

2021

Aerospace

View full text Add to dashboard Cite

Although the benefits of morphing wings have been proven in many studies in the last few decades, the wing skin design remains one of the challenges to advancing and implementing the morphing technology. This is due to the conflicting design requirements of high out-of-plane stiffness to withstand aerodynamic loads and low in-plane stiffness to allow morphing with the available actuation forces. Advancements in the design of hybrid and flexible composites might allow for design solutions that feature this balance in stiffness required for this application. These composites offer new design parameters, such as the number of plies, the fiber-orientation angle of each ply in the skin laminate, and the spatial distribution of the plies on the skin surface. This paper presents a parametric study of a composite skin for a twist-morphing wing. The skin is made of periodic laminated composite sections, called “Twistkins”, integrated in an elastomeric outer skin. The twisting deformation is localized in the elastomeric sections between the Twistkins. The design parameters considered are the number of plies in the composite Twistkins, the fiber-orientation angle of the plies, the torsional rigidity of the elastomer, the width ratio, and the number of elastomeric sections. The computational analysis results showed that the torsional compliance can be increased by increasing the width ratio, decreasing the number of elastomeric sections, number of composite plies and the elastomer’s torsional rigidity. However, this would also lead to a decrease in the out-of-plane stiffness. The nonlinearity and rates at which these parameters affect the skin’s behavior are highlighted, including the effect of the fiber-orientation angle of the laminate plies. Hence, the study guides the design process of this twist-morphing skin.

show abstract

Simplified 2D Skin Lattice Models for Multi-Axial Camber Morphing Wing Aircraft

Cited by 5 publications

References 38 publications

Homogenization Methods of Lattice Materials

Homogenization Methods of Lattice Materials

Enhanced Range and Endurance Evaluation of a Camber Morphing Wing Aircraft

Parametric Study of a Composite Skin for a Twist-Morphing Wing

Contact Info

Product

Resources

About