Smart materials applied in a micro remotely piloted aircraft system with morphing wing

2018 ◽  
Vol 29 (16) ◽  
pp. 3317-3332 ◽  
Author(s):  
Miguel A Barcala-Montejano ◽  
Ángel A Rodríguez-Sevillano ◽  
Rafael Bardera-Mora ◽  
Jaime García-Ramírez ◽  
Joaquín de Nova-Trigueros ◽  
...  
Keyword(s):  
Smart Materials ◽  
Fiber Composite ◽  
Experimental Results ◽  
Morphing Wing ◽  
Computational Calculations ◽  
Remotely Piloted Aircraft ◽  
Adaptive Wing ◽  
Wing Geometry ◽  
Macro Fiber Composite ◽  
Aircraft System

The article presents a research in the field of morphing wings (adaptive wing geometry) developed over a prototype of micro-unmanned air vehicle based on smart materials technology. This morphing wing will optimize the aircraft performance features. Modifying the curvature of the wing, the micro-unmanned air vehicles will adjust its performance in an optimum mode to cruise flight condition as well as in the phases of takeoff and landing. The installation of mechanical elements for control surfaces in small size aircraft means, on some occasions, an extra complexity. In addition, it takes into account an increase in aircraft weight. In this research, the adaptive wing geometry is based on macro-fiber composites, so that its position on the inner surfaces of the wing allows the appropriate modification of the curvature, adapting them to the flight profile. This research will present the conceptual design of the vehicle, computational calculations, experimental results of the wind tunnel testing, validations using non-intrusive techniques (particle image velocimetry) and a theoretical–experimental analysis of the macro-fiber composite effects over the wing. An Arduino board will perform the control parameters of the macro-fiber composite deformation. With these analytical, computational, and experimental results, the most relevant conclusions are presented.

Electricity-structure-fluid coupled modelling and experiment of underwater flexible structure with partially distributed macro fiber composites

2020 ◽  
pp. 107754632097691
Author(s):  
Junqiang Lou ◽  
Tehuan Chen ◽  
Yiling Yang ◽  
Chao Xu ◽  
Hairong Chen ◽  
...  
Keyword(s):  
Mode Shape ◽  
Fiber Composite ◽  
Coupled Model ◽  
Experimental Results ◽  
Dynamic Responses ◽  
Flexible Structure ◽  
Flexible Beam ◽  
Coupled Modelling ◽  
Hydrodynamic Damping ◽  
Macro Fiber Composite

Dynamic oscillating behavior of the flexible structure immerged in viscous fluids has attracted growing attention and been widely used in various practical applications. A general electricity-structure-fluid coupled model for the forced dynamic responses of a cantilever immersed in fluids, with partially distributed macro fiber composite, is proposed in this paper. Based on the classical Euler–Bernoulli beam theory, the first mass-normalized mode shape of the cantilever with partially bonded macro fiber composite is determined using assumed mode method. The attachment of the macro fiber composite actuators stiffens the macro fiber composite-bonded portion of the cantilever. The established mode shape matches perfectly with experimental results. Considering the macro fiber composite actuator as a set of representative elements connected in parallel, the internally actuation moment provided by the macro fiber composite actuators is obtained. The hydrodynamic load caused by the surrounding fluids, decomposed into the added mass and hydrodynamic damping parts, is also added to the theoretical model in the frequency-domain form. The predicted in-air and underwater dynamic behaviors of the flexible beam are consistent with the experimental results at different auction levels. Thus, the obtained general electricity-structure-fluid coupled model can be used to predict the forced dynamic responses of flexible structure with partially bonded actuators immersed in fluids.

A novel unmanned aircraft with solid-state control surfaces: Analysis and flight demonstration

2012 ◽  
Vol 24 (2) ◽  
pp. 147-167 ◽  
Author(s):  
Onur Bilgen ◽  
Lauren M Butt ◽  
Steven R Day ◽  
Craig A Sossi ◽  
Joseph P Weaver ◽  
...  
Keyword(s):  
Solid State ◽  
Wind Tunnel ◽  
Fiber Composite ◽  
Aerodynamic Characteristics ◽  
Unmanned Aircraft ◽  
Ocean Engineering ◽  
Remotely Piloted Aircraft ◽  
Macro Fiber Composite ◽  
Wing Morphing ◽  
Control Surfaces

This article presents a completely servo-less, piezoelectric controlled, wind tunnel and flight tested, remotely piloted aircraft that has been developed by the 2010 Virginia Tech Wing Morphing Design Team (a senior design project between the Departments of Mechanical Engineering and Aerospace and Ocean Engineering). A type of piezocomposite actuator, the Macro-Fiber Composite, is used for changing the camber of all control surfaces on the aircraft. The aircraft is analyzed theoretically for its aerodynamic characteristics to aid the design of the piezoelectric control surfaces. A vortex lattice analysis complemented the database of aerodynamic derivatives used to analyze control response. Steady-state roll rates were measured in a wind tunnel and were compared to a similar aircraft with servomotor actuated control surfaces. The theoretical analysis and wind tunnel testing demonstrated the stability and control authority of the concept, culminating in the first flight of the completely Macro-Fiber Composite controlled aircraft on 29 April 2010. An electric motor-driven propulsion system is used to generate thrust, and all systems are powered with a single lithium polymer battery. This vehicle became the first completely Macro-Fiber Composite controlled, flight tested aircraft. It is also known to be the first fully solid-state piezoelectric material controlled, nontethered, flight tested fixed-wing aircraft.

Macro-fiber composite actuators for a swept wing unmanned aircraft

2009 ◽  
Vol 113 (1144) ◽  
pp. 385-395 ◽  
Author(s):  
O. Bilgen ◽  
K. B. Kochersberger ◽  
D. J. Inman
Keyword(s):  
Wind Tunnel ◽  
Smart Materials ◽  
Shape Control ◽  
Fiber Composite ◽  
Unmanned Aircraft ◽  
Control Surface ◽  
Swept Wing ◽  
Roll Control ◽  
Macro Fiber Composite ◽  
Lift And Drag

Abstract The purpose of the research presented here is to exploit actuation via smart materials to perform shape control of an aerofoil on a small aircraft and to determine the feasibility and advantages of smooth control surface deformations. A type of piezoceramic composite actuator known as Macro-Fiber Composite (MFC) is used for changing the camber of the wings. The MFC actuators were implemented on a 30° swept wing, 0·76m wingspan aircraft. The experimental vehicle was flown using two MFC patches in an elevator/aileron (elevon) configuration. Preliminary flight and wind-tunnel testing has demonstrated the stability and control of the concept. Flight tests were performed to quantify roll control using the MFC actuators. Lift and drag coefficients along with pitch and roll moment coefficients were measured in a low-speed, open-section wind tunnel. A vortex-lattice analysis complemented the database of aerodynamic derivatives used to analyse control response. The research, for the first time, successfully demonstrated that piezoceramic devices requiring high voltages can be effectively employed in small air vehicles without compromising the weight of the overall system.

Technical and economic analysis of certain types of service robots

2020 ◽  
Vol 19 (10) ◽  
pp. 1965-1986
Author(s):  
T.A. Komkina ◽  
M.A. Nikonova ◽  
M.G. Dubinina
Keyword(s):  
Dynamic Models ◽  
Unit Price ◽  
Service Robots ◽  
Technical Level ◽  
Positive Correlation ◽  
Technical Indicators ◽  
Technical Parameters ◽  
Prosthetic Hands ◽  
Remotely Piloted Aircraft ◽  
Aircraft System

Subject. The article analyzes development trends in certain types of service robots, namely, hybrid UAVs, bionic prosthetic hands, robotic vacuum cleaners. Objectives. We focus on identifying the main trends in the development of certain types of service robots, building dynamic models of their technical indicators and models of dependence of their price and weight on absolute characteristics and technical parameters. Methods. The study employs methods of correlation and multiple regression analysis. The data of the IFR, the Remotely Piloted Aircraft System, and websites of robot manufacturers serve as the informational basis of the paper. Results. The modeling unveils positive correlation between the integrated indicator of the technical level of hybrid UAVs of convertiplane type and the wingspan. The analysis of modern bionic prosthetic hands shows that the developers focus on optimizing the structure of the prosthetic, however, as the functions of the hand improve, the weight of bionic hand increases. The main factors influencing the price of robot vacuum cleaners are their power, weight, and operating hours. Conclusions. The unit price of a complex indicator of the technical level of hybrid UAVs is lower than the corresponding indicator of fixed-wing UAVs, reflecting a greater efficiency of hybrid UAVs. The analysis of technical indicators of robotic prosthetics (using the case of bionic hands) shows that any improvement of functional characteristics leads to deterioration of weight. The analysis of technical and economic indicators of robotic vacuum cleaners reveals a positive correlation between the price and weight, operating hours and power.

Numerical study of geometric morphing wings of the 1303 UCAV

2021 ◽  
pp. 1-17
Author(s):  
B. Nugroho ◽  
J. Brett ◽  
B.T. Bleckly ◽  
R.C. Chin
Keyword(s):  
Flight Control ◽  
Numerical Study ◽  
Aerodynamic Characteristics ◽  
Morphing Wing ◽  
Rolling Moment ◽  
Wide Range ◽  
Morphing Wings ◽  
Wing Geometry ◽  
Lift And Drag ◽  
Wing Morphing

ABSTRACT Unmanned Combat Aerial Vehicles (UCAVs) are believed by many to be the future of aerial strike/reconnaissance capability. This belief led to the design of the UCAV 1303 by Boeing Phantom Works and the US Airforce Lab in the late 1990s. Because UCAV 1303 is expected to take on a wide range of mission roles that are risky for human pilots, it needs to be highly adaptable. Geometric morphing can provide such adaptability and allow the UCAV 1303 to optimise its physical feature mid-flight to increase the lift-to-drag ratio, manoeuvrability, cruise distance, flight control, etc. This capability is extremely beneficial since it will enable the UCAV to reconcile conflicting mission requirements (e.g. loiter and dash within the same mission). In this study, we conduct several modifications to the wing geometry of UCAV 1303 via Computational Fluid Dynamics (CFD) to analyse its aerodynamic characteristics produced by a range of different wing geometric morphs. Here we look into two specific geometric morphing wings: linear twists on one of the wings and linear twists at both wings (wash-in and washout). A baseline CFD of the UCAV 1303 without any wing morphing is validated against published wind tunnel data, before proceeding to simulate morphing wing configurations. The results show that geometric morphing wing influences the UCAV-1303 aerodynamic characteristics significantly, improving the coefficient of lift and drag, pitching moment and rolling moment.

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