Morphing Aircraft: An Improbable Dream?

2014 ◽  
Author(s):  
Michael I. Friswell
Keyword(s):  
Smart Materials ◽  
Aircraft Design ◽  
System Level ◽  
Accurate Analysis ◽  
Bird Flight ◽  
Limited Region ◽  
Morphing Aircraft ◽  
Wing Sweep ◽  
Aircraft Performance ◽  
Morphing Technology

Compliant aircraft, with a range of deformations comparable to birds, has been a dream for many years. Earlier aviation pioneers tried to replicate aspects of bird flight, but higher air speeds and larger payloads have required aircraft design to deviate from their biological inspiration. The design of conventional fixed wing aircraft can only be optimized for a limited region of the flight envelope; mechanisms such as deployable flaps and wing sweep are used extensively to enlarge this envelope. The development of more accurate analysis tools, advanced smart materials, and the increasingly demands for improved aircraft performance, are driving research into compliant morphing aircraft. These aircraft have the potential to adapt and optimize their shape to improve flight performance or achieve multi-objective mission roles. However this technology has rarely been adopted on production aircraft. This paper will critically review the progress made to date on compliant morphing aircraft research, and summarize the challenges that need to be addressed before such technology can be adopted widely. In particular the need to demonstrate system level performance benefits for morphing technology is emphasized.

scholarly journals Comparative Aerodynamic Performance Analysis of Camber Morphing and Conventional Airfoils

2021 ◽  
Vol 11 (22) ◽  
pp. 10663
Author(s):  
Tuba Majid ◽  
Bruce W. Jo
Keyword(s):  
Performance Analysis ◽  
Smart Materials ◽  
Technology Development ◽  
Aerodynamic Performance ◽  
Improvement Rate ◽  
Morphing Aircraft ◽  
Morphing Wings ◽  
Flap Deflection ◽  
Morphing Technology ◽  
Foundational Work

This paper aims to numerically validate the aerodynamic performance and benefits of variable camber rate morphing wings, by comparing them to conventional ones with plain flaps, when deflection angles vary, assessing their D reduction or L/D improvement. Many morphing-related research works mainly focus on the design of morphing mechanisms using smart materials, and innovative mechanism designs through materials and structure advancements. However, the foundational work that establishes the motivation of morphing technology development has been overlooked in most research works. All things considered, this paper starts with the verification of the numerical model used for the aerodynamic performance analysis and then conducts the aerodynamic performance analysis of (1) variable camber rate in morphing wings and (2) variable deflection angles in conventional wings. Finally, we find matching pairs for a direct comparison to validate the effectiveness of morphing wings. As a result, we validate that variable camber morphing wings, equivalent to conventional wings with varying flap deflection angles, are improved by at least 1.7% in their L/D ratio, and up to 18.7% in their angle of attack, with α = 8° at a 3% camber morphing rate. Overall, in the entire range of α, which conceptualizes aircrafts mission planning for operation, camber morphing wings are superior in D, L/D, and their improvement rate over conventional ones. By providing the improvement rates in L/D, this paper numerically evaluates and validates the efficiency of camber morphing aircraft, the most important aspect of aircraft operation, as well as the agility and manoeuvrability, compared to conventional wing aircraft.

Shape Shifting Target

2015 ◽  
Vol 137 (05) ◽  
pp. 46-51
Author(s):  
Michael I. Friswell
Keyword(s):  
Smart Materials ◽  
Large Scale ◽  
Control Surface ◽  
Commercial Aircraft ◽  
Accurate Analysis ◽  
Low Weight ◽  
Compliant Control ◽  
Aircraft Performance ◽  
Near Term ◽  
The Cost

This article is a study of morphing aircrafts, which has attracted many research groups around the globe. The unmanned aerial vehicles (UAV) have some attractive features for aeronautic research. An important factor in morphing systems is the scale of the air vehicle on which they will be incorporated. With the development of more accurate analysis tools and advanced smart materials, researchers are once again investigating compliant morphing aircraft to improve aircraft performance. Such an aircraft would have the potential to adapt and optimize their shape to improve flight performance or to achieve multi-objective mission roles. Low aspect ratio wings provide more manoeuvrability and allow for high flight speeds, but at the cost of efficiency. An aircraft can be fast or efficient, but not both. Compliant control surfaces also lack the discontinuities found in hinged mechanisms, and thus have the potential to reduce drag and noise significantly. Compliant structures are promising solutions because of their low weight and maintenance costs. Large-scale morphing on commercial aircraft may not be practical in the near term. But the application of morphing to secondary structures, such as a compliant control surface, is a realistic goal.

Parametric Aircraft Design Optimisation Study Using Span and Mean Chord as Main Design Drivers

2014 ◽  
Vol 1016 ◽  
pp. 365-369 ◽  
Author(s):  
Pedro Albuquerque ◽  
Pedro Gamboa ◽  
Miguel Silvestre
Keyword(s):  
Design Methodology ◽  
Aircraft Design ◽  
Design Parameters ◽  
Flight Performance ◽  
Air Cargo ◽  
Main Design ◽  
Design Specifications ◽  
Performance Requirements ◽  
Aircraft Performance

The present work describes an aircraft design methodology that uses the wingspan and its mean aerodynamic chord as main design parameters. In the implemented tool, low fidelity models have been developed for the aerodynamics, stability, propulsion, weight, balance and flight performance. A Fortran® routine that calculates the aircraft performance for the user defined mission and vehicle’s performance requirements has been developed. In order to demonstrate this methodology, the results for a case study using the design specifications of the Air Cargo Challenge 2013 are shown.

System Design and Modeling of a Thermally Activated Reconfigurable Wing

2010 ◽  
Author(s):  
Richard Beblo ◽  
Darrel Robertson ◽  
James Joo ◽  
Brian Smyers ◽  
Gregory Reich
Keyword(s):  
Thermal Energy ◽  
High Speed ◽  
Frictional Heating ◽  
Mechanical Analysis ◽  
Design Tool ◽  
System Level ◽  
Morphing Aircraft ◽  
Thermal Actuation ◽  
Short Period ◽  
Reconfigurable Structures

Reconfigurable structures such as morphing aircraft generally require an on board energy source to function. Frictional heating during the high speed deployment of a blunt nosed low speed reconnaissance air vehicle can provide a large amount of thermal energy during a short period of time. This thermal energy can be collected, transferred, and utilized to reconfigure the deployable aircraft. Direct utilization of thermal energy has the ability to significantly decrease or eliminate the losses associated with converting thermal energy to other forms, such as electric. The following work attempts to describe possible system designs and components that can be utilized to transfer the thermal energy harvested at the nose of the aircraft during deployment to internal components for direct thermal actuation of a reconfigurable wing structure. A model of a loop heat pipe is presented and used to predict the time dependant transfer of energy. Previously reported thermal profiles of the nose of the aircraft calculated based on trajectory and mechanical analysis of the actuation mechanism are reviewed and combined with the model of the thermal transport system providing a system level feasibility investigation and design tool. The efficiency, implementation, benefits, and limitations of the direct use thermal system are discussed and compared with currently utilized systems.

Advanced aircraft performance analysis

2018 ◽  
Vol 90 (4) ◽  
pp. 627-638 ◽  
Author(s):  
Marc Immer ◽  
Philipp Georg Juretzko
Keyword(s):  
Performance Analysis ◽  
Design Process ◽  
Performance Optimization ◽  
Electric Propulsion ◽  
Vertical Plane ◽  
Aircraft Design ◽  
Efficient Design ◽  
Content Type ◽  
Aircraft Performance ◽  
Hybrid Electric

Purpose The preliminary aircraft design process comprises multiple disciplines. During performance analysis, parameters of the design mission have to be optimized. Mission performance optimization is often challenging, especially for complex mission profiles (e.g. for unmanned aerial vehicles [UAVs]) or hybrid-electric propulsion. Therefore, the purpose of this study is to find a methodology that supports aircraft performance analysis and that is applicable to complex profiles and to novel designs. Design/methodology/approach As its core element, the developed method uses a computationally efficient C++ software “Aircraft Performance Program” (APP), which performs a segment-based mission computation. APP performs a time integration of the equations of motion of a point mass in the vertical plane. APP is called via a command line interface from a flexible scripting language (Python). On top of APP’s internal radius of action optimization, state-of-the-art optimization packages (SciPy) are used. Findings The application of the method to a conventional climb schedule shows that the definition of the top of climb has a significant influence on the resulting optimum. Application of the method to a complex UAV mission optimization, which included maximizing the radius of action, was successful. Low computation time enables to perform large parametric studies. This greatly improves the interpretation of the results. Research limitations/implications The scope of the paper is limited to the methodology that allows for advanced performance analysis at the conceptual and preliminary design stages with an emphasis on novel propulsion concepts. The methodology is developed using existing, validated methods, and therefore, this paper does not contain comprehensive validation. Other disciplines, such as cost analysis, life-cycle assessment or market analysis, are not considered. Practical implications With the proposed method, it is possible to obtain not only the desired optimum mission performance but also off-design performance of the investigated design. A thorough analysis of the mission performance provides insight into the design’s capabilities and shortcomings, ultimately aiding in obtaining a more efficient design. Originality/value Recent developments in the area of hybrid or hybrid-electric propulsion systems have shown the need for performance computation tools aiding the related design process. The presented method is especially valuable when novel design concepts with complex mission profiles are investigated.

Multi-Functional Soft Smart Materials and their Applications

2011 ◽  
Vol 410 ◽  
pp. 25-25
Author(s):  
Jin Song Leng
Keyword(s):  
Smart Materials ◽  
Ph Value ◽  
Shape Memory Polymer ◽  
Soft Materials ◽  
Aerospace Engineering ◽  
Artificial Muscles ◽  
Automobile Engineering ◽  
Micro Electro Mechanical Systems ◽  
Morphing Aircraft ◽  
Space Deployable Structures

Stimulus-active polymers can change their shapes with respect to configuration or dimension upon exposure to a particular stimulus such as heat, electricity, light, magnetic, solvent and pH value. These unique characteristics enable stimulus-active polymers to be used in a myriad of fields, including clothing manufacturing, automobile engineering, medical treatment, and aerospace engineering. Stimulus-active polymers can be applied in smart textiles and apparels, intelligent medical instruments and auxiliaries, artificial muscles, biomimetic devices, heat shrinkable materials for electronics packaging, micro-electro-mechanical systems, self-deployable sun sails in spacecrafts, miniature manipulator, actuators and sensors, and many more. This paper presents some recent progress of soft smart materials and their applications. Special emphasis is focused upon shape memory polymer (SMP), electro-active polymer (EAP) for aerospace engineering such as space deployable structures and morphing aircraft, which has highlighted the need for development of these materials. A detailed overview of development in these smart soft materials, of which the undergoing and future applications are used in adaptive structures and active control, is presented. The paper concludes with a short discussion for multi-functional soft smart materials and their composites that are expected to extend the range of development and applications available to the related researches and engineers.

System Level Performance and Emissions Evaluation of Renewable Fuels for Jet Engines

2014 ◽  
Author(s):  
Kadambari Lokesh ◽  
Vishal Sethi ◽  
Theoklis Nikolaidis ◽  
Devaiah Karumbaiah
Keyword(s):  
Engine Performance ◽  
Operating Conditions ◽  
System Level ◽  
Civil Aviation ◽  
Jet Engines ◽  
Stirred Reactor ◽  
Fuel Burn ◽  
Performance And Emissions ◽  
Aircraft Performance ◽  
Level Performance

Incessant demand for fossil derived energy and the resulting environmental impact has urged the renewable energy sector to conceive one of the most anticipated sustainable, alternative “drop-in” fuels for jet engines, called as, Bio-Synthetic Paraffinic Kerosene (Bio-SPKs). Second (Camelina SPK & Jatropha SPK and third generation (Microalgae SPK) advanced biofuels have been chosen to analyse their influence on the behaviour of a jet engine through numerical modelling and simulation procedures. The thermodynamic influence of each of the biofuels on the gas turbine performance extended to aircraft performance over a user-defined trajectory (with chosen engine/airframe configuration) have been reported in this paper. Initially, the behaviour of twin-shaft turbofan engine operated with 100% Bio-SPKs at varying operating conditions. This evaluation is conducted from the underpinning phase of adopting the chemical composition of Bio-SPKs towards an elaborate and careful prediction of fluid thermodynamics properties (FTPs). The engine performance was primarily estimated in terms of fuel consumption which steers the fiscal and environmental scenarios in civil aviation. Alternative fuel combustion was virtually simulated through stirred-reactor approach using a validated combustor model. The system-level emissions (CO2 and NOx) have been numerically quantified and reported as follows: the modelled aircraft operating with Bio-SPKs exhibited fuel economy (mission fuel burn) by an avg. of 2.4% relative to that of baseline (Jet Kerosene). LTO-NOx for the user-defined trajectory decreased by 7–7.8% and by 15–18% considering the entire mission. Additionally, this study reasonably qualitatively explores the benefits and issues associated with Bio-SPKs.

Automatic Thermal Modeling for System Level Design of Electronic Equipment

2003 ◽  
Author(s):  
Kenichiro Aoki ◽  
Koichi Shimizu ◽  
Akira Ueda ◽  
Akira Tamura ◽  
Masanori Motegi
Keyword(s):  
Model Building ◽  
Software Tool ◽  
System Level ◽  
Analysis Model ◽  
Accurate Analysis ◽  
Fluid Analysis ◽  
Analytical Accuracy ◽  
Thermal Fluid Analysis ◽  
Short Time ◽  
Large Investment

The development of hardware needs cost reduction by shortening a development period and reducing experimental man-hour. In order to satisfy these demands, thermal fluid analysis with higher accuracy in short time is indispensable for product development. At present, thermal fluid analyses are conducted using different software tools. Each software tool requires model building and meshing for simulations using its own format. That leads to a large investment in time, and therefore cost. VPS/Simulation-Hub software Fujitsu developed is able to convert data from various CADs. It has the features to create a data fitting to numerical analysis software, create an accurate analysis model, and delete unnecessary components. With these main features, VPS/Simulation-Hub greatly contributes to the man-hour reduction for model building and the improvement of analytical accuracy. In this paper, VPS/Simulation-Hub is introduced with the detail explanation of the above 3 main features.

scholarly journals Flight Dynamics of a Morphing Aircraft Utilizing Independent Multiple-Joint Wing Sweep

2010 ◽  
Vol 2 (2) ◽  
pp. 91-106 ◽  
Author(s):  
Daniel T. Grant ◽  
Mujahid Abdulrahim ◽  
Rick Lind
Keyword(s):  
Flight Dynamics ◽  
Morphing Aircraft ◽  
Wing Sweep
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