STATIC SHAPE CONTROL FOR ADAPTIVE WINGS

被引:70
作者
AUSTIN, F [1 ]
ROSSI, MJ [1 ]
VANNOSTRAND, W [1 ]
KNOWLES, G [1 ]
JAMESON, A [1 ]
机构
[1] PRINCETON UNIV,PRINCETON,NJ 08544
关键词
D O I
10.2514/3.12189
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
A theoretical method was developed, and experimentally validated, to control the static shape of flexible structures by employing internal translational actuators. A finite element model of the structure, without the actuators present, is employed to obtain the multiple-input, multiple-output control-system gain matrices for actuator-load control as well as actuator-displacement control. The method is applied to the quasistatic problem of maintaining an optimum-wing cross section during various transonic-cruise flight conditions to obtain significant reductions in the shock-induced drag. Only small, potentially achievable, adaptive modifications to the profile are required. The adaptive-wing concept employs actuators as truss elements of active ribs to reshape the wing cross section by deforming the structure. Finite element analyses of an adaptive-rib model verify the controlled-structure theory. Experiments on the model were conducted, and arbitrarily selected deformed shapes were accurately achieved.
引用
收藏
页码:1895 / 1901
页数:7
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