| 融合惯导与飞控系统信息的飞行大气全参数估计算法 |
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| 引用本文： | 陆辰,李荣冰,刘建业,雷廷万,郭毅.融合惯导与飞控系统信息的飞行大气全参数估计算法[J].控制与决策,2017,32(2):363-367. |
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| 作者姓名： | 陆辰 李荣冰 刘建业 雷廷万 郭毅 |
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| 作者单位： | 南京航空航天大学江苏省物联网与控制技术重点实验室;南京航空航天大学自动化学院,南京航空航天大学江苏省物联网与控制技术重点实验室;南京航空航天大学自动化学院,南京航空航天大学江苏省物联网与控制技术重点实验室;南京航空航天大学自动化学院,成都飞机设计研究所,成都610041,成都飞机设计研究所,成都610041 |
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| 基金项目： | 国家自然科学基金重点项目(61533008)；国家自然科学基金项目(61374115). |
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| 摘 要： | 针对嵌入式大气数据系统高空飞行精度低、跨大气层易失效等问题,提出一种融合惯导与飞控系统信息的 飞行大气全参数估计算法.基于飞行器气动模型及动力学方程,建立惯导信息与大气参数之间的函数 关系,进而利用扩展卡尔曼滤波实现大气参数的实时精确估计.仿真结果表明,该方法具有较高的 精度、良好的稳定性和鲁棒性,而且可以提高大气数据系统的测量范围和可靠性,能够适用于全 飞行包线下攻角、侧滑角、真空速的测量.
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| 关 键 词： | 惯性导航系统 气动模型 飞行控制 大气参数 扩展卡尔曼滤波 |
| 收稿时间： | 2015/11/16 0:00:00 |
| 修稿时间： | 2015/11/16 0:00:00 |
Calculation method for air data based on information from inertial navigation system and flight control system |
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| LU Chen,LI Rong-bing,LIU Jian-ye,LEI Ting-wan and GUO Yi.Calculation method for air data based on information from inertial navigation system and flight control system[J].Control and Decision,2017,32(2):363-367. |
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| Authors: | LU Chen LI Rong-bing LIU Jian-ye LEI Ting-wan and GUO Yi |
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| Affiliation: | Jiangsu Key Laboratory of Internet of Things and Control Technologies,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China;College of Automatic Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China,Jiangsu Key Laboratory of Internet of Things and Control Technologies,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China;College of Automatic Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China,Jiangsu Key Laboratory of Internet of Things and Control Technologies,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China;College of Automatic Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China,Chengdu Aircraft Design and Research Institute,Chengdu 610041,China and Chengdu Aircraft Design and Research Institute,Chengdu 610041,China |
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| Abstract: | The flush air data system(FADS) gets low accuracy during high altitude flight, which can easily fail if the vehicle travel through the atmosphere. Therefore, a calculation method for air data based on inertial navigation system(INS) and flight control system(FCS) is proposed. On the base of the aerodynamic model, force equations, and moment equations, the mathematic relationship between INS and air data is established. Real-time estimation of air data is achieved by using EKF. The simulation results show that, this method not only has high precision, favorable stability and robustness, but also improves the measurement range and reliability of the air data system, which can effectively be used to measure the angle of attack, the angle of sideslip and true airspeed within full flight envelope. |
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