康林 , 王新龙 , 陈万春 , 雷文贵 . 基于混合式惯导系统构型优化的弹道导弹落点精度研究[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2025.32815

[1] 秦永元. 惯性导航[M]. 第三版. 北京: 科学出版社, 2020: 1-7. QIN Y Y. Inertial Navigation[M]. 3rd ed. Beijing: Science Press, 2020: 1-7 (in Chinese). [2] 张士峰, 李俊, 杨华波. 惯性制导工具误差分离技术综述[J]. 航空学报, 2023, 44(15): 175-194. ZHANG S F, LI J, YANG H B. Review of inertial guidance instrumental error separation techniques[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(15): 175-194 (in Chinese). [3] 贺杰, 黄显林, 李学峰. Sins制导工具误差补偿研究[J]. 航空学报, 2007(1): 182-186. HE J, HUANG X L, LI X F. Study on SINS guidance instrument error compensation[J]. Acta Aeronautica et Astronautica Sinica, 2007(1): 182-186 (in Chinese). [4] ZHANG Z, ZHANG H, HAO Y, et al. A review on MEMS silicon resonant accelerometers[J]. Journal of Microelectromechanical Systems, 2024, 33(2): 174-208. [5] JIANG L, QUAN W, LI R, et al. A parametrically modulated dual-axis atomic spin gyroscope[J]. Applied Physics Letters, 2018, 112(5). [6] 徐明. 美国“和平卫士”式导弹[J]. 航天, 1994(6): 14-16. XU M. The US “Peacekeeper” missile[J]. Aerospace, 1994(6): 14-16 (in Chinese). [7] IEEE standard specification format guide and test procedure for single-degree-of-freedom rate-integrating gyros[J]. IEEE Std 517-1974, 1974: 1-60. [8] 吴梦旋. 惯性仪表高阶误差模型系数在精密离心机上的测试方法[D]. 哈尔滨工业大学, 2018. WU M X. Test method for high order error model coefficients of inertial instruments on precision centrifuge[D]. Harbin Institute of Technology, 2018 (in Chinese). [9] 孙闯, 任顺清. 陀螺加速度计交叉二次项的线振动台测试方法[J]. 导航定位与授时, 2017, 4(5): 105-110. SUN C, REN S Q. Measurement method for cross-quadratic coefficient of PIGA on linear vibration table[J]. Navigation, Positioning & Timing, 2017, 4(5): 105-110 (in Chinese). [10] 陈东生, 魏宗康, 房建成. 验证石英加速度计误差模型的火箭橇试验[J]. 中国惯性技术学报, 2009, 17(2): 236-239+245. CHEN D S, WEI Z K, FANG J C. Verifying QFPA’s error model based on rocket sled testing[J]. Journal of Chinese Inertial Technology, 2009, 17(2): 236-239+245 (in Chinese). [11] SECER G, BARSHAN B. Improvements in deterministic error modeling and calibration of inertial sensors and magnetometers[J]. Sensors and Actuators A: Physical, 2016, 247: 522-538. [12] KHANKALANTARY S, RANJBARAN S, EBADOLLAHI S. Simplification of calibration of low-cost MEMS accelerometer and its temperature compensation without accurate laboratory equipment[J]. Measurement Science and Technology, 2021, 32(4): 045102. [13] 朱建丰, 徐世杰. 基于误差椭球理论的惯性部件构型分析[J]. 导弹与航天运载技术, 2008(2): 40-45. ZHU J F, XU S J. Configuration analysis of inertial units based on error ellipsoid theory[J]. Missiles and Space Launch Vehicles, 2008(2): 40-45 (in Chinese). [14] JAFARI M. Optimal redundant sensor configuration for accuracy increasing in space inertial navigation system[J]. Aerospace Science and Technology, 2015, 47: 467-472. [15] HE Q, YU H, LIANG D, et al. Enhancing pure inertial navigation accuracy through a redundant high-precision accelerometer-based method utilizing neural networks[J]. Sensors, 2024, 24(8): 2566. [16] GAO C, WEI G, WANG L, et al. A systematic calibration modeling method for redundant INS with multi-sensors non-orthogonal configuration[J]. Micromachines, 2022, 13(10): 1684. [17] 程建华, 董金鲁, 陈岱岱. 一种对称斜置式四陀螺惯导冗余配置方案[J]. 传感器与微系统, 2015, 34(2): 16-19+27. CHENG J H, DONG J L, CHEN D D. Symmetrical and sideling redundancy configuration scheme of SINS using four gyroscopes[J]. Sensor and Microsystems, 2015, 34(2): 16-19+27. (in Chinese) [18] 陈世年. 控制系统设计[M]. 北京: 宇航出版社, 1996. CHEN S N. Control System Design[M]. Beijing: Astronautic Publishing House, 1996 (in Chinese). [19] 冯培德. 论混合式惯性导航系统[J]. 中国惯性技术学报, 2016, 24(3): 281-284, 290. FENG P D. On hybrid inertial navigation system[J]. Journal of Chinese Inertial Technology, 2016, 24(3): 281-284, 290 (in Chinese). [20] 王蕾, 王玮, 刘增军, 等. 混合式惯性导航系统全数字平台技术研究[J]. 兵工学报, 2018, 39(7): 1316-1322. WANG L, WANG W, LIU Z J, et al. Research on the digital platform for hybrid inertial navigation system[J]. Acta Armamentarii, 2018, 39(7): 1316-1322 (in Chinese). [21] 尤太华, 禹春梅, 杜建邦. 混合式惯导原理及其在弹载环境下应用[J]. 航天控制, 2020, 38(1): 23-29. YOU T H, YU C M, DU J B. Principle and application of Hybrid-INS in the missile borne environment[J]. Aerospace Control, 2020, 38(1): 23-29 (in Chinese). [22] SHKEL A M, WANG Y. Navigation error analysis in strapdown inertial navigation[M]//Pedestrian Inertial Navigation with Self-Contained Aiding. IEEE, 2021: 47-64. [23] ZHOU X, WANG Z, LI D, et al. Guidance systematic error separation method based on nonlinear combinatorial model[C]//2018 37th Chinese Control Conference (CCC). 2018: 4685-4690. [24] HE J, HUANG X lin. Modeling, identification and compensation of sins guidance instrument error[C]//2006 International Conference on Machine Learning and Cybernetics. 2006: 2479-2484. [25] 杨洪森. 弹载SINS/双星组合导航系统建模与仿真精度分析[D]. 国防科学技术大学, 2006. YANG H S. Modeling and accuracy assessment on missile-borne SINS/Double-Satellite integrated navigation system[D]. National University of Defense Technology, 2006 (in Chinese). [26] 郑伟, 汤国建. 扰动引力场中弹道导弹飞行力学[M]. 北京: 国防工业出版社, 2009. ZHENG W, TANG G J. Flight Mechanics of Ballistic Missiles in Perturbed Gravity Field[M]. Beijing: National Defense Industry Press, 2009 (in Chinese). [27] 温永智, 谢愈, 吴杰, 等. 基于环境函数矩阵法的惯导精度快速评估[J]. 弹箭与制导学报, 2011, 31(3): 56-58. WEN Y Z, XIE Y, WU J, et al. Rapid accuracy assessment of INS based on environment function matrix method[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2011, 31(3): 56-58 (in Chinese). [28] 张金槐. 远程火箭精度分析与评估[M]. 长沙: 国防科技大学出版社, 1995. ZHANG J H. Analysis and Assessment of Long-Range Rocket Accuracy[M]. Changsha: National University of Defense Technology Press, 1995 (in Chinese). [29] YANG Y. Spacecraft attitude determination and control: Quaternion based method[J]. Annual Reviews in Control, 2012, 36(2): 198-219. [30] EL-HAKEM HEGAZY S A, KAMEL A M, ARAFA, I I, et al. INS Stochastic Noise Impact on Circular Error Probability of Ballistic Missiles[J]. NAVIGATION: Journal of the Institute of Navigation, 2022, 69(2): navi.523. [31] 魏宗康, 高荣荣, 周姣, 等. 基于椭圆概率误差的落点精度评定方法[J]. 导弹与航天运载技术, 2020(2): 58-63. WEI Z K, GAO R R, ZHOU J, et al. An accuracy evaluation method of fall points based on elliptic error probable[J]. Missiles and Space Launch Vehicles, 2020(2): 58-63 (in Chinese). [32] 徐明. “民兵Ⅲ”号洲际弹道导弹[J]. 航天, 1994(5): 12-14. XU M. “Minuteman III" intercontinental ballistic missile[J]. Aerospace, 1994(5): 12-14 (in Chinese).