| 惯性测量装置火箭橇试验模拟导弹飞行过载方法 |
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| 引用本文： | 陈东生,魏宗康.惯性测量装置火箭橇试验模拟导弹飞行过载方法[J].导弹与航天运载技术,2009(2). |
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| 作者姓名： | 陈东生 魏宗康 |
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| 作者单位： | 北京航天控制仪器研究所,北京,100039 |
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| 摘 要： | 由于火箭橇试验具有产生大过载、高速度、强振动和冲击等综合条件的能力,可以最逼真地模拟导弹真实飞行环境.主要针对捷联系统和平台系统,提出火箭橇试验的总体方案,包括三维模拟法、分段等效法、变推力模拟法等.并根据典型过载曲线,给出仿真结果,验证了此方法的正确性.
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| 关 键 词： | 惯性测量装置 火箭橇试验 过载 |
Acceleration Simulation of Missile flight for IMU in Sled Testing |
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| Chen Dongsheng,Wei Zongkang.Acceleration Simulation of Missile flight for IMU in Sled Testing[J].Missiles and Space Vehicles,2009(2). |
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| Authors: | Chen Dongsheng Wei Zongkang |
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| Affiliation: | Beijing Institute of Space Control Devices;Beijing;100039 |
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| Abstract: | For sled testing can produce large acceleration,high velocity and strong vibration,it is the best method to simulate the flight condition of missiles.A system scheme of acceleration simulation of missile flight is presented for the strapdown IMU system and platform system,such as the three dimensional method,the time division method,the adjustable thrust method and so on.According to a typical acceleration figure,a demonstration is given to validate this method. |
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| Keywords: | Inertial measurement device Sled testing Acceleration |
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