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A Study on Roll Lock in Phenomena of a Canard-Controlled Missile with Freely Spinning Tailfins

机译:自由旋转Tai刀的鸭控导弹的滚动锁定研究

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This paper predicts the roll-rate and the roll lock-in phenomena of a canard-controlled missile with freely spinning tailfins by applying Falanga’s roll-rate equation. For calculation of the rollrate and the roll lock-in of freely spinning tailfins, the rolling moment coefficient on the fixed tailfins obtained from a wind tunnel test was used, while the tailfins’ roll-damping coefficient was calculated by missile DATCOM. The roll-rate and roll lock-in of the freely spinning tailfins were calculated by applying these values to the roll-rate equation for freely spinning tailfins. To confirm and validate the accuracy of the results of the roll-rate and roll lock-in calculation for freely spinning tailfins, the results were compared with those of the wind tunnel test data. The calculation results showed good agreement with the wind tunnel test data, and the roll lock-in of freely spinning tailfins could be predicted as well.
机译:本文通过应用Falanga的侧倾速率方程,预测了具有自由旋转的尾翼的鸭式控制导弹的侧倾速率和侧倾锁定现象。为了计算自由旋转的尾翼的侧倾率和侧倾锁定,使用了风洞试验获得的固定尾翼的侧倾力矩系数,而导弹DATCOM计算了尾翼的侧倾阻尼系数。通过将这些值应用于自由旋转的尾翼的侧倾速率方程,可以计算自由旋转的尾翼的侧倾速率和侧倾锁定。为了确认和验证自由旋转的尾翼的侧倾速率和侧倾锁定计算结果的准确性,将其与风洞测试数据的结果进行了比较。计算结果与风洞试验数据吻合良好,也可以预测自由旋转的尾翼的侧倾锁定。

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