| 喷流姿控战术导弹三维气动力数学模型 |
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| 引用本文： | 傅建明.喷流姿控战术导弹三维气动力数学模型[J].上海航天,2005,22(4):13-18. |
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| 作者姓名： | 傅建明 |
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| 作者单位： | 上海机电工程研究所,上海,200233 |
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| 摘 要： | 采用当量喷流控制力概念，推导了战术导弹三维气动力和铰链力矩数学模型。分析了喷流姿控（俯仰、偏航和滚转），以及副翼舵、方向舵和升降舵偏对导弹气动力的作用，并给出了气动力各分量的泰勒和傅里叶级数形式的表达式。模型还考虑了大攻角情况下对称外形零侧滑流动时的非对称涡型现象。
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| 关 键 词： | 战术导弹 气动力 数学模型 喷流姿控 |
| 文章编号： | 1006-1630（2005）04-0013-06 |
| 收稿时间： | 2004-10-21 |
| 修稿时间： | 2004-12-23 |
Three Dimensional Aerodynamic Mathematical Model for Tactical Missiles with Jet Steering |
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| Fu Jian-ming.Three Dimensional Aerodynamic Mathematical Model for Tactical Missiles with Jet Steering[J].Aerospace Shanghai,2005,22(4):13-18. |
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| Authors: | Fu Jian-ming |
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| Abstract: | The mathematical models of three dimension aerodynamic and hinge moment were derived by using the concept of equivalent jet steering in this paper. The function of the jet steering (pitch, yaw and rolling), and deflection of aileron vane, rudder and elevator to the aerodynamic force of tactical missile was analyzed, and the expressions in the form of Taylor and Fourier series for different component of the force were given. The unsymmetrical vortex phenomena of symmetrical configuration without sideslip at high attack angle were included in the formula. |
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| Keywords: | Tactical missile Aerodynamic force Mathematical model Jet steering |
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