Flight Control Optimization and Wind Tunnel Validation of a Morphing Flying Wing

2019 ◽  
Author(s):  
Dominic Keidel ◽  
Urban Fasel ◽  
Giulio Molinari ◽  
Paolo Ermanni
Keyword(s):  
Wind Tunnel ◽  
Flight Control ◽  
Control Optimization

Joint Mechanical Design and Flight Control Optimization of a Nature-Inspired Unmanned Aerial Vehicle via Collaborative Co-Evolution

2021 ◽  
Vol 6 (2) ◽  
pp. 2044-2051
Author(s):  
Danial Sufiyan ◽  
Luke Soe Thura Win ◽  
Shane Kyi Hla Win ◽  
Gim Song Soh ◽  
Shaohui Foong
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Flight Control ◽  
Mechanical Design ◽  
Control Optimization ◽  
Aerial Vehicle

Divergence Speed Prediction for Practical Slung Load Shapes

2015 ◽  
Author(s):  
Brandon Liberi ◽  
Chau Ton ◽  
Narayanan Komerath
Keyword(s):  
Control System ◽  
Robust Control ◽  
Wind Tunnel ◽  
Flight Control ◽  
Flight Control System ◽  
Wind Tunnel Experiments ◽  
Flight Testing ◽  
Flight Vehicles ◽  
Analytical Functions ◽  
Speed Prediction

Given the innumerable combinations of flight vehicles, loads and flight conditions, alternatives are sought to flight testing, to certify the safe flight speed with slung loads. With well-resolved airload maps now feasible for arbitrary shapes as analytical functions, dynamic simulation predicts divergence speeds, regardless of the symmetry of the object. Likely modes of amplification are found using wind tunnel experiments with free-swinging objects. A robust control formulation enables safe flight close to divergence speed where the flight control system can prevent disturbance amplification.

Design of the wind tunnel based virtual flight testing evaluation method for flight control systems

2016 ◽  
Vol 232 (1) ◽  
pp. 17-29
Author(s):  
Min Huang ◽  
Zhong-wei Wang ◽  
Zhen-yun Guo ◽  
Yao-bin Niu
Keyword(s):  
Control System ◽  
Wind Tunnel ◽  
Control Systems ◽  
Flight Control ◽  
Evaluation Method ◽  
Simulation Models ◽  
Hardware In The Loop ◽  
Flight Control System ◽  
Flight Testing ◽  
Simulation Evaluation

In order to provide a method for evaluating flight control systems with the wind tunnel based virtual flight testing and provide a guide for building virtual flight testing systems, the virtual flight testing evaluation method was researched. The virtual flight testing evaluation method consisted of three parts: virtual flight testing method, virtual flight testing data processing method, and flight control system performance determination method, which were respectively designed for a pitching control system. Then, the hardware-in-the-loop simulation evaluation method was presented, and comparisons between the virtual flight testing and hardware-in-the-loop simulation evaluation method were conducted to highlight the characteristics of virtual flight testing evaluation method. Finally, virtual flight testing simulation models of a sample air vehicle were built and virtual flight testing were simulated to demonstrate the virtual flight testing evaluation method, which is helpful for the understanding of the virtual flight testing evaluation method with more sensibility. The evaluation results show that the virtual flight testing evaluation method designed can be used for flight control system evaluation.

scholarly journals Dynamics Analysis and Control Optimization of Devices for Power Generation From Fluid Flow

2020 ◽  
Author(s):  
◽  
Mārtiņš Irbe
Keyword(s):  
Wind Tunnel ◽  
Energy Savings ◽  
Optimization Criterion ◽  
Production Equipment ◽  
Robotic Fish ◽  
Negative Effects ◽  
Control Optimization ◽  
Ice Surface ◽  
Race Track ◽  
And Control

ss. In addition, the positive or negative effects of vibrations on the skeleton as it slides over the ice surface are considered. In these studies, the optimization criterion is energy savings on the race track. In turn, in solving energy extraction problems (in the second part of the work) a new method (theory) is developed, which helps to easily perform analysis, optimization and synthesis tasks for object interaction with liquids, if there is translational, rotational or complete motion of objects. shaped bodies in a fluid (liquid, gas), if it is possible to mathematically describe the interaction surfaces. The method was tested with computer programs and experimentally in the wind tunnel “Armfield”. The third part of the work deals with several other studies of fluid dynamics, including: – studied the actuator of robotic fish movement; – energy production equipment from robotic fish tail fin oscillations was analyzed and synthesized; – parametric shape optimization for SUP board drive fin motor cover was performed; – practical experiments were performed for a double valve in a wind tunnel and they were compared (validated) with a mathematical model.

Aero-structural optimization and analysis of a camber-morphing flying wing: Structural and wind tunnel testing

2019 ◽  
Vol 30 (6) ◽  
pp. 908-923 ◽  
Author(s):  
Dominic Keidel ◽  
Giulio Molinari ◽  
Paolo Ermanni
Keyword(s):  
Wind Tunnel ◽  
Internal Structure ◽  
Flight Control ◽  
Three Dimensional ◽  
Structural Behaviour ◽  
Electromechanical Actuators ◽  
Aerodynamic Efficiency ◽  
Numerical Predictions ◽  
Novel Structure ◽  
And Performance

This article presents the design, optimization and performance assessment of a novel structure-actuation morphing concept for a flying wing, enabling the flight control for straight flight and around the pitch and roll axes. The applied camber-morphing concept utilizes an optimized selectively compliant internal structure, combined with electromechanical actuators to achieve a trailing edge deflection. These deflections lead to variations of the local and global lift, permitting to control the flight of the aircraft. The aero-structural behaviour of the wing is analysed using a coupled three-dimensional aerodynamic and structural simulation tool. An optimization of the planform, aerodynamic shape, internal structure and actuation parameters is performed to attain a longitudinally stable and aerodynamically efficient flying wing. The drag increment caused by morphing is minimized through the numerical optimization, resulting in high aerodynamic efficiency across a range of flight speeds. The stiffness and morphing capabilities of the manufactured wing are characterized experimentally and are compared with the numerical predictions, and the aerodynamic and aeroelastic behaviour of the wing is investigated through wind tunnel tests. The test results indicate the ability of the flying wing to achieve sufficient variations in lift, roll and pitch to control the flight completely through camber morphing.

Stalling transport aircraft

2013 ◽  
Vol 117 (1198) ◽  
pp. 1183-1206 ◽  
Author(s):  
P. J. Bolds-Moorehead ◽  
V. G. Chaney ◽  
T. Lutz ◽  
S. Vaux
Keyword(s):  
Wind Tunnel ◽  
Flight Control ◽  
Flight Test ◽  
High Angle ◽  
Flight Testing ◽  
Control Laws ◽  
Transport Aircraft ◽  
Wind Tunnel Data ◽  
Predictive Validation ◽  
Flight Deck

Abstract Airbus and Boeing are cooperatively presenting this topic dealing with transport aircraft stalls. The paper will begin by defining a stall, followed by a review of requirements, predictive validation and flight testing. There are various ways of designing modern jet transports for the stall regime such as aerodynamic approaches, flight deck indications, and augmentation control laws to deal with the high angle-of-attack (α) arena. The goal of augmented control laws for high α is common – no full aerodynamic stall or loss of climb performance should occur in the operational flight envelope, in Normal flight control modes. The validation techniques employed in preparation for a flight test campaign will follow. These include flight characteristic predictions based on wind-tunnel data as well as pilot-in-the-loop simulation rehearsals. The preparation for flight testing will be reviewed from both the engineer and pilot viewpoints. This will be followed by a review of various flight testing that has been conducted. The paper will close with a brief foray into what the future of transport stalls could be – perhaps protection features in degraded flight control modes? What are the benefits as well as drawbacks to increased augmentation for high α?

scholarly journals Polynomial Chaos-Based Flight Control Optimization with Guaranteed Probabilistic Performance

2020 ◽  
Vol 53 (2) ◽  
pp. 7274-7279
Author(s):  
Dalong Shi ◽  
Xiang Fang ◽  
Florian Holzapfel
Keyword(s):  
Flight Control ◽  
Polynomial Chaos ◽  
Control Optimization
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