| 飞行器在再入段中升阻比计算方法 |
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| 引用本文： | 张殿祜,施志佳.飞行器在再入段中升阻比计算方法[J].战术导弹技术,1992(4). |
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| 作者姓名： | 张殿祜 施志佳 |
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| 作者单位： | 西北工业大学
(张殿祜)，西北工业大学(施志佳) |
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| 摘 要： | 利用恒定动态系统综合分析方法的数学基础。求出了飞行器在再入段中的升阻比,以便在有干扰作用下,保证飞行器的着陆精度。
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| 关 键 词： | 飞行器 升阻比 非线性系统 控制向量 干扰 着陆精度 |
CALCULATION METHOD OF LIFT-DRAG RATIO OF FLYING VEHICLE AT RE-ENTFRY PHASE |
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| Zhang Dianhu Shi Zhijia Northwestern Polytechnical University.CALCULATION METHOD OF LIFT-DRAG RATIO OF FLYING VEHICLE AT RE-ENTFRY PHASE[J].Tactical Missile Technology,1992(4). |
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| Authors: | Zhang Dianhu Shi Zhijia Northwestern Polytechnical University |
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| Affiliation: | Zhang Dianhu Shi Zhijia Northwestern Polytechnical University |
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| Abstract: | Using Synthesis analysis of invariable dynamic system, a lift-drag ratio of flying vehicle at re-entry phase has been obtained to ersure landing accuracy under circumstance of disturbing force. |
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| Keywords: | Vehicle Lift-drag ratio Nonlinear system ~*Control vector Disturbance ~*Landing accuracy |
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