Grid-based LPV Modeling of Aeroelastic Aircraft with Parametrized Control Surface Design

2019 ◽  
Author(s):  
Reka Dora Mocsanyi ◽  
Bela Takarics ◽  
Balint Vanek
Keyword(s):  
Control Surface ◽  
Surface Design ◽  
Grid Based

Control Surface Design in Theory and Practice

1945 ◽  
Vol 49 (416) ◽  
pp. 431-510 ◽  
Author(s):  
M.B. Morgan ◽  
H.H.B.M. Thomas
Keyword(s):  
Theory And Practice ◽  
Control Surface ◽  
Lecture Hall ◽  
Surface Design

A meeting of the Royal Aeronautical Society was held in the lecture hall of the Institution of Mechanical Engineers, Storey's Gate, St. James's Park, Westminster, London, S.W.1, on Thursday, March 1st, 1945, at which a paper on “Control Surface Design in Theory and Practice ” was read by Mr. M. B. Morgan, M.A., F.R.Ae.S., and Mr. H. H. B. M. Thomas, A.F.R.Ae.S.

scholarly journals Grid-Based and Polytopic Linear Parameter-Varying Modeling of Aeroelastic Aircraft with Parametric Control Surface Design

Fluids ◽  
2020 ◽  
Vol 5 (2) ◽  
pp. 47
Author(s):  
Réka Dóra Mocsányi ◽  
Béla Takarics ◽  
Aditya Kotikalpudi ◽  
Bálint Vanek
Keyword(s):  
Iterative Process ◽  
Control Design ◽  
Aircraft Design ◽  
Control Surface ◽  
Linear Parameter ◽  
Control Laws ◽  
Surface Design ◽  
Linear Parameter Varying ◽  
Parametric Control ◽  
Surface Sizing

The main direction of aircraft design today and in the future is to achieve more lightweight and higher aspect ratio airframes with the aim to improve performance and to reduce operating costs and harmful emissions. This promotes the development of flexible aircraft structures with enhanced aeroelastic behaviour. Increased aeroservoelastic (ASE) effects such as flutter can be addressed by active control technologies. Control design for flutter suppression heavily depends on the control surface sizing. Control surface sizing is traditionally done in an iterative process, in which the sizing is determined considering solely engineering rules and the control laws are designed afterwards. However, in the case of flexible vehicles, flexible dynamics and rigid body control surface sizing may become coupled. This coupling can make the iterative process lengthy and challenging. As a solution, a parametric control surface design approach can be applied, which includes limitations of control laws in the design process. For this a set of parametric models is derived in the early stage of the aircraft design. Therefore, the control surfaces can be optimized in a single step with the control design. The purpose of this paper is to describe as well as assess the developed control surface parameterized ASE models of the mini Multi Utility Technology Testbed (MUTT) flexible aircraft, designed at the University of Minnesota. The ASE model is constructed by integrating aerodynamics, structural dynamics and rigid body dynamics. In order to be utilized for control design, control oriented, low order linear parameter-varying (LPV) models are developed using the bottom-up modeling approach. Both grid- and polytopic parametric LPV models are obtained and assessed.

scholarly journals Control surface design for radio-controlled aircraft. Case: SAE Aero Design Micro-class prototype

2021 ◽  
Author(s):  
Rafael A. Márquez ◽  
Miguel A. Martínez ◽  
Manuel J. Martínez
Keyword(s):  
Weight Ratio ◽  
Aircraft Design ◽  
Control Surface ◽  
Primary Control ◽  
Surface Design ◽  
C Language ◽  
Design Variables ◽  
Surface Sizing ◽  
Design Competition ◽  
Control Surfaces

This research article presents a design methodology for primary control surfaces (Ailerons, Rudder and Elevator) for experimental unmanned radio-controlled aircraft. The methodology is based on the proposal and standardization of the required mechanical and aerodynamic analysis for each control surface sizing, considering the SAE Aero Design competition objectives within Micro Class. It is used on empirical results previously described in references about aeronautical design, computerized fluids dynamics (CFD) software, and aircraft controllability regulations in order to obtain the design variables. Based on this information, the iteration sequences required for design were automated by a C++ language code to obtain the optimal characteristics for each surface, thereby reducing the possibility of calculation errors, overall time, and workload invested in the design process. The application of the methodology to the latest aircraft design reduced the total control systems weight to the aircraft’s empty weight ratio to a minimum of 3.4%.

Control allocation performance for blended wing body aircraft and its impact on control surface design

2013 ◽  
Vol 29 (1) ◽  
pp. 18-27 ◽  
Author(s):  
Stephen M. Waters ◽  
Mark Voskuijl ◽  
Leo L.M. Veldhuis ◽  
François J.J.M.M. Geuskens
Keyword(s):  
Control Surface ◽  
Control Allocation ◽  
Surface Design ◽  
Blended Wing Body

Control Surface Design Analysis and Actuation Requirements Development for Munitions

2020 ◽  
Author(s):  
Joshua Bryson ◽  
Joseph D. Vasile ◽  
Benjamin C. Gruenwald ◽  
Frank Fresconi
Keyword(s):  
Design Analysis ◽  
Control Surface ◽  
Surface Design ◽  
Requirements Development

Application of Pulsed Blowing Technique in High-Lift Control Surface Design

2012 ◽  
Vol 482-484 ◽  
pp. 121-125
Author(s):  
Peng Wu ◽  
Xue Ying Deng ◽  
Yan Kui Wang
Keyword(s):  
Flow Separation ◽  
Deflection Angle ◽  
Leading Edge ◽  
Control Surface ◽  
Control Technique ◽  
High Lift ◽  
Surface Design ◽  
Aerodynamic Efficiency ◽  
Lift Control ◽  
Control Surfaces

Because the flight performance of aircraft is so dependent on aerodynamic efficiency of control surfaces, it is very important to eliminate the flow separation over the control surfaces at high deflection angle in order to keep the aircraft having good flight capability, especially for the modern aircraft with tailless aerodynamic configuration. A novel flow control technique to eliminate flow separation of control surface at high deflection angle and creat high lift increment by pulsed blowing at leading edge of control surface is discussed in this paper. The performance of lift enhancment of control surface which used this technique is investigated, and based on the zonal analysis of pulsed frequency, the control characteristic of this technique is also discussed.

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