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The continuous improvement in diversification, new-type orientation and low cost of navigation control system, the accurate measurement of the spinning aircraft flight attitude parameters has becomes a more and more urgent task. In view of the above problems, a novel attitude estimator for the spinning aircraft is proposed by using earth infrared radiation field. The attitude estimation system possesses several key advantages over the current designs in low cost, no need of moving parts, and being free from reliance on GPS or other state feedback. Firstly, the mechanism of earth infrared radiation field is described in detail, and an 8-14 m atmospheric window is selected as the study object. The land surface infrared radiation is calculated by the land surface temperature and emissivity. The sky infrared radiation is calculated through layered atmosphere by combing with the sky emissivity and infrared atmospheric transmittance. According to the calculations of land surface infrared radiation and sky infrared radiation, the mathematical model of earth infrared radiation field is established by combining with propagation law of infrared radiation in the atmosphere. Then the measurement model of thermopile sensors is derived, after analyzing the motion feature of spinning aircraft during the flight. The thermopile sensors convert the observed infrared radiation into an electrical signal well suited for onboard data acquisition. To explore the inner link between the thermopile sensor output and the spinning aircraft attitude information, the characteristics of the sensor output under different attitude angles and fields of view are studied. When the thermopile sensor characteristics are included, the fully developed model can be used to generate accurate sensor output as a function of attitude angle. Finally, the installation of the thermopile sensors on the spinning aircraft is designed, and the measurement model of onboard thermopile sensor is established. In order to improve the accuracy of attitude measurement, an extended Kalman filter is developed, which enables the estimating of real-time attitude angles and roll rate by using solely three-axis thermopile sensors as feedback. The result indicates that by using this high accurate algorithm, the pitch angle estimation error is within 0.02, the roll angle estimation error is within 0.1 and the roll rate estimation error is within 1 rad/s. The detection system is simple and practical, works stably, and can meet the requirements for spinning projectile attitude measurement. The attitude estimation system will provide a new method and theory for further developing the spinning aircraft state detection.
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Keywords:
- earth infrared radiation field /
- thermopiles sensors /
- spinning aircraft /
- extended Kalman filter
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[2] Zheng W, Hsu H T, Zhong M, Yun M J 2014 Chin. Phys. B 23 109101
[3] Zhao G R, Huang J L, Su Y Q, Sun C 2015 Acta Phys. Sin. 64 210502 (in Chinese) [赵国荣, 黄婧丽, 苏艳琴, 孙聪 2015 64 210502]
[4] Nguyen T 2014 28th AIAA/USU Conference on Small Satellites Logan, USA, August 8-13, 2014 p1
[5] Sun C M, Yuan Y, Zhang X B 2010 Acta Phys. Sin. 59 7523 (in Chinese) [孙成明, 袁艳, 张修宝 2010 59 7523]
[6] Li M, Jing W, Huang X 2012 J. Guidance, Control, and Dynamics 35 344
[7] Su W, Hong T, Xu C, Hao P J 2014 J. Xi'an Jiaotong Univ. 48 116 (in Chinese) [苏威, 洪涛, 徐川, 郝培杰 2014 西安交通大学学报 48 116]
[8] Egan G K, Taylor B 2007 Monash Univ. TR MECSE-2007 Melbourne, Australia, August 2-7, 2007 p847
[9] Rogers J, Costello M 2012 Navigation 59 9
[10] Rogers J, Costello M, Hepner D 2011 J. Guidance, Control, and Dynamics 34 688
[11] Tokutake H, Kuribara M, Yuasa Y 2012 International Workshop on Instruction for Planetary Missions Greenbelt Maryland, USA, Octber 10-12, 2012 p1022
[12] Xu L J, Liu T, Chen H X 2014 J. Chin. Inertial Technol. 22 475 (in Chinese) [续立军, 刘涛, 陈海昕 2014 中国惯性技术学报 22 475]
[13] Li X Y, Ma C L, Zhi W 2014 Transducer and Microsystem Technologies 33 101 (in Chinese) [李晓雨, 马春林, 支炜 2014 传感器与微系统 33 101]
[14] Gillespie A 2014 Encyclopedia of Remote Sensing(Vol. 1) (New York: Springer New York) pp303-312
[15] Fang Y Q, Fan X, Cheng Z D, Zhu B, Deng P, Zhang F Q 2013 Laser Infrared 43 896 (in Chinese) [方义强, 樊祥, 程正东, 朱斌, 邓潘, 张发强 2013 激光与红外 43 896]
[16] Ma G, Zhang P, Qi C L, Xu N, Dong C H 2014 Acta Phys. Sin. 63 179503 (in Chinese) [马刚, 张鹏, 漆成莉, 徐娜, 董超华 2014 63 179503]
[17] Berger X, Bathiebo J 2003 Renewable Energy 28 1925
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[1] Guo C, Cai H, van der Heijden G H M 2013 J. Navigat. 66 799
[2] Zheng W, Hsu H T, Zhong M, Yun M J 2014 Chin. Phys. B 23 109101
[3] Zhao G R, Huang J L, Su Y Q, Sun C 2015 Acta Phys. Sin. 64 210502 (in Chinese) [赵国荣, 黄婧丽, 苏艳琴, 孙聪 2015 64 210502]
[4] Nguyen T 2014 28th AIAA/USU Conference on Small Satellites Logan, USA, August 8-13, 2014 p1
[5] Sun C M, Yuan Y, Zhang X B 2010 Acta Phys. Sin. 59 7523 (in Chinese) [孙成明, 袁艳, 张修宝 2010 59 7523]
[6] Li M, Jing W, Huang X 2012 J. Guidance, Control, and Dynamics 35 344
[7] Su W, Hong T, Xu C, Hao P J 2014 J. Xi'an Jiaotong Univ. 48 116 (in Chinese) [苏威, 洪涛, 徐川, 郝培杰 2014 西安交通大学学报 48 116]
[8] Egan G K, Taylor B 2007 Monash Univ. TR MECSE-2007 Melbourne, Australia, August 2-7, 2007 p847
[9] Rogers J, Costello M 2012 Navigation 59 9
[10] Rogers J, Costello M, Hepner D 2011 J. Guidance, Control, and Dynamics 34 688
[11] Tokutake H, Kuribara M, Yuasa Y 2012 International Workshop on Instruction for Planetary Missions Greenbelt Maryland, USA, Octber 10-12, 2012 p1022
[12] Xu L J, Liu T, Chen H X 2014 J. Chin. Inertial Technol. 22 475 (in Chinese) [续立军, 刘涛, 陈海昕 2014 中国惯性技术学报 22 475]
[13] Li X Y, Ma C L, Zhi W 2014 Transducer and Microsystem Technologies 33 101 (in Chinese) [李晓雨, 马春林, 支炜 2014 传感器与微系统 33 101]
[14] Gillespie A 2014 Encyclopedia of Remote Sensing(Vol. 1) (New York: Springer New York) pp303-312
[15] Fang Y Q, Fan X, Cheng Z D, Zhu B, Deng P, Zhang F Q 2013 Laser Infrared 43 896 (in Chinese) [方义强, 樊祥, 程正东, 朱斌, 邓潘, 张发强 2013 激光与红外 43 896]
[16] Ma G, Zhang P, Qi C L, Xu N, Dong C H 2014 Acta Phys. Sin. 63 179503 (in Chinese) [马刚, 张鹏, 漆成莉, 徐娜, 董超华 2014 63 179503]
[17] Berger X, Bathiebo J 2003 Renewable Energy 28 1925
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