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Supervised by Ministry of Industry and Information Technology of The People's Republic of China Sponsored by Harbin Institute of Technology Editor-in-chief Yu Zhou ISSNISSN 1005-9113 CNCN 23-1378/T

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A Calculation Method of Rolling Characteristics of Canard Missile with Free-Spinning Tails
Author NameAffiliationPostcode
Liu Pingan* College of Aerospace and Civil Engineering, Harbin Engineering University, Harbin 150001, China 150001
Mingyuan Liu College of Aerospace and Civil Engineering, Harbin Engineering University, Harbin 150001, China 150001
Abstract:
The steady flow field of a canard missile on different angles of attack and Mach numbers were studied. Based on analysis, a method was proposed to reduce the calculation for the rolling characteristics of the canard missile with free-spinning tails, and was tested to obtain the relations between rolling moment coefficient, Mach number, and angle of attack. All the computed rolling moment coefficients obtained from the proposed method greatly agreed with the experimental results of FD-06 wind tunnel in CAAA, which proved that the method can not only reduce the calculation cost but also keep precision in calculating the rolling characteristics of canard missiles.
Key words:  numerical simulation  canard missile  free-spinning tail  wind tunnel test  rolling characteristics
DOI：10.11916/j.issn.1005-9113.18093
Clc Number:TJ76
Fund:
Descriptions in Chinese:
  对固定尾翼鸭式布局导弹在不同攻角、不同马赫数下进行定常的数值模拟，根据数值计算的结果，提出了一种能够大幅度减小计算量的计算自旋尾翼鸭式导弹的滚转特性的方法，并用此方法算得了该鸭式导弹在自旋尾翼下的滚转力矩系数随马赫数和攻角的变化规律。将得到的计算数据与自旋尾翼鸭式导弹的风洞实验数据进行对比，结果表明计算数据与实验结果吻合较好，说明用此方法计算自旋尾翼鸭式布局导弹的滚转特性，保证了准确性的同时，可以达到大幅度减小计算量的目的，具有实用价值。

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