Active control of supersonic transport aeroelastic oscillations using high-fidelity equations

被引:0
|
作者
Guruswamy, Guru [1 ]
机构
[1] NASA, Ames Res Ctr, Computat Phys Branch, Moffett Field, CA 94035 USA
关键词
Computational fluids dynamics; Navier-Stokes equations; Aeroelasticity; Active controls;
D O I
10.1016/j.ifacsc.2019.100057
中图分类号
TP [自动化技术、计算机技术];
学科分类号
0812 ;
摘要
A higher order computational procedure to alleviate aeroelastic oscillations by using active control surfaces is addressed. Flow is modeled using the high-fidelity Navier-Stokes (NS) equations, compared to the current use of the low-fidelity linear theory to design active controls. An active control module is embedded into a general-purpose NS flow solver developed for full aircraft configurations. The structure is modeled using the modal equations of motion, and existing active control equations based on the energy approach are utilized. Previously established transonic small perturbation theory and wind tunnel experiments are considered for validating. The use of active controls for next generation supersonic transport aircraft is demonstrated. (C) 2019 Elsevier Ltd. All rights reserved.
引用
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页数:7
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