发明名称 |
Whole-spacecraft hybrid isolation system for launch vehicles |
摘要 |
A whole-spacecraft passive isolation system consisting of a plurality of titanium flexures that act as soft springs to isolate a satellite from its launch vehicle is improved by the addition of piezoceramic wafers attached to the flexures. A low-pass filter feedforward controller is used to cancel out disturbances by applying out-of-phase signals to the piezoceramic wafers thereby creating a hybrid isolation system that significantly reduces the dynamic loads on the spacecraft.
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申请公布号 |
US6135390(A) |
申请公布日期 |
2000.10.24 |
申请号 |
US19990277595 |
申请日期 |
1999.03.26 |
申请人 |
THE UNITED STATES OF AMERICA AS REPRESENTED BY THE SECRETARY OF THE AIR FORCE |
发明人 |
SCIULLI, DINO;GRIFFIN, STEVEN F. |
分类号 |
B64G1/64;(IPC1-7):B64G1/22 |
主分类号 |
B64G1/64 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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