Viscous flow computations of aircraft with changing control surface deflection using unstructured dynamic meshes

2006 ◽  
Vol 52 (8) ◽  
pp. 925-940 ◽  
Author(s):  
Mitsuhiro Murayama ◽  
Yasushi Ito ◽  
Kazuhiro Nakahashi ◽  
Kisa Matsushima ◽  
Toshiyuki Iwamiya
Keyword(s):  
Viscous Flow ◽  
Control Surface ◽  
Surface Deflection

Viscous Flow Computations of Aircraft with Changing Control Surface Deflection Using Unstructured Grids

2003 ◽  
Author(s):  
Mitsuhiro Murayama ◽  
Yasushi Ito ◽  
Kazuhiro Nakahashi ◽  
Kisa Matsushima ◽  
Toshiyuki Iwamiya
Keyword(s):  
Viscous Flow ◽  
Unstructured Grids ◽  
Control Surface ◽  
Surface Deflection

Composite Wing Flutter Speed and Frequency due to Variable Control Surface Deflection in Low Speed Wind Tunnel

2013 ◽  
Vol 390 ◽  
pp. 3-7
Author(s):  
Muhammad Iyas Mahzan ◽  
Sallehuddin Muhamad ◽  
Sa’ardin Abdul Aziz ◽  
Mohamed Sukri Mat Ali
Keyword(s):  
Wind Tunnel ◽  
Dynamic Instability ◽  
Wind Tunnel Test ◽  
Control Surface ◽  
Wing Flutter ◽  
Flutter Speed ◽  
Surface Deflection ◽  
Relationship Of ◽  
Low Speed Wind Tunnel ◽  
The Relationship

Flutter is a dynamic instability problem represents the interaction among structural, aerodynamic, elastic and inertial forces and occurred when the energy is continuously transformed by the surrounding fluids to a flying structure in the form of kinetic energy. The study was conducted to investigate the relationship of the control surface deflection angle to the flutter speed and the flutter frequency. A wind tunnel test was performed using a flat plate wing made of composite material. It was found that by deflecting the control surface up to 45°, the flutter speed reduced almost linearly from 35.6 m/s to 22.7 m/s. The flutter frequency greatly reduced from 48 Hz without the control surface deflected to 34 Hz with the control surface deflected at 15°. After 15° deflection up to 45°, the flutter frequency reduced almost linearly.

Simulation of Aircraft Response to Control Surface Deflection Using Unstructured Dynamic Grids

2005 ◽  
Vol 42 (2) ◽  
pp. 340-346 ◽  
Author(s):  
Mitsuhiro Murayama ◽  
Fumiya Togashi ◽  
Kazuhiro Nakahashi ◽  
Kisa Matsushima ◽  
Takuma Kato
Keyword(s):  
Control Surface ◽  
Surface Deflection

scholarly journals Trim Optimizations of an Adaptive Tailless Aircraft with Composite Wing

2011 ◽  
Vol 213 ◽  
pp. 334-338
Author(s):  
Jiang Xie ◽  
Zhi Chun Yang ◽  
Shi Jun Guo
Keyword(s):  
Genetic Algorithm ◽  
Control Surface ◽  
Fe Model ◽  
Aeroelastic Tailoring ◽  
Induced Drag ◽  
Analysis Process ◽  
Surface Deflection ◽  
Slender Wing ◽  
Ply Orientation ◽  
Composite Wing

This paper investigates aeroelastic tailoring and optimal trailing edge control surface deflection to minimize induced drag for a HALE UAV flying wing configuration. The analysis process is conducted on the Finite Element(FE) model of a composite slender wing. Genetic Algorithm(GA) is employed to aeroelastically tailor the wing by setting the composite ply orientation. The study examined conformal and traditional flaps and explored two optimization formulations to minimize drag. The impacts of the conformal control surface are recognized as required deflection saving which can be translated to drag reduction. The results also show that the control demands for the optimal trim can be further reduced if the wing is properly tailored.

Simulation of Aircraft Response to Control Surface Deflection Using Unstructured Dynamic Grids

2002 ◽  
Author(s):  
Mitsuhiro Murayama ◽  
Fumiya Togashi ◽  
Kazuhiro Nakahashi ◽  
Kisa Matsushima ◽  
Takuma Kato
Keyword(s):  
Control Surface ◽  
Surface Deflection

scholarly journals Adaptive Command Filtered Integrated Guidance and Control for Hypersonic Vehicle with Magnitude, Rate and Bandwidth Constraints

2018 ◽  
Vol 151 ◽  
pp. 05004
Author(s):  
Liang Wang ◽  
Weihua Zhang ◽  
Ke Peng ◽  
Donghui Wang
Keyword(s):  
Sliding Mode ◽  
Integrated Design ◽  
Hypersonic Vehicle ◽  
Convergence Time ◽  
Control Surface ◽  
Control Input ◽  
Guidance And Control ◽  
Surface Deflection ◽  
Integrated Guidance And Control ◽  
And Control

This paper proposes a novel integrated guidance and control (IGC) method for hypersonic vehicle in terminal phase. Firstly, the system model is developed with a second order actuator dynamics. Then the back-stepping controller is designed hierarchically with command filters, where the first order command filters are implemented to construct the virtual control input with ideal states predicted by an adaptive estimator, and the nonlinear command filter is designed to produce magnitude, rate and bandwidth limited control surface deflection finally tracked by a terminal sliding mode controller with finite convergence time. Through a series of 6-DOF numerical simulations, it’s indicated that the proposed method successfully cancels out the large aerodynamics coefficient uncertainties and disturbances in hypersonic flight under limited control surface deflection. The contribution of this paper lies in the application and determination of nonlinear integrated design of guidance and control system for hypersonic vehicle.

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