基于双旋运动弹道修正弹系统建模
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摘要
针对配装弹道修正组件的炮弹,其外弹道飞行过程中受力特性和运动状态相较于传统炮弹发生了较大改变,为准确描述修正弹的运动规律,提出了基于双旋运动的弹道修正弹系统建模方法。该方法通过分析修正组件与弹体之间的运动特点,建立运动约束关系,选择适宜的坐标系,利用多刚体理论建立起完整的适用于多种型号的修正弹弹道模型。仿真和飞行试验结果表明,所建立的数学模型可对弹丸的运动状态进行准确的描述,仿真结果与实际弹丸落点偏差小于弹丸射程的5‰,符合精度要求。
For the projectile which equiped with the trajectory correction fuze, the mechanical characteristics and motion state of the projectiles of which during the outer ballistic flight have been changed greatly compared with the traditional projectiles. In order to accurately describe the motion law of the modified missiles, a ballistic correction system modeling method based on double-rotation motion was proposed. The method analyzed the motion characteristics between the modified component and the projectile, established the motion constraint relationship, selected the appropriate coordinate system, and used the multi-rigid body theory to establish a complete modified ballistic model suitable for various models. Simulation and flight test results showed that the established mathematical model could accurately describe the motion state of the projectile. The deviation between the simulation result and the actual projectile point was less than 5‰ of the projectile's range, which met the accuracy requirements.
For the projectile which equiped with the trajectory correction fuze, the mechanical characteristics and motion state of the projectiles of which during the outer ballistic flight have been changed greatly compared with the traditional projectiles. In order to accurately describe the motion law of the modified missiles, a ballistic correction system modeling method based on double-rotation motion was proposed. The method analyzed the motion characteristics between the modified component and the projectile, established the motion constraint relationship, selected the appropriate coordinate system, and used the multi-rigid body theory to establish a complete modified ballistic model suitable for various models. Simulation and flight test results showed that the established mathematical model could accurately describe the motion state of the projectile. The deviation between the simulation result and the actual projectile point was less than 5‰ of the projectile's range, which met the accuracy requirements.
引文
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[3]徐明友.弹箭飞行力学[M].北京:高等教育出版社,2003.
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[8]Wernert P, Leopold F, Bodino D, et al.Wind tunnel tests and open-loop trajectory simulations for a 155mm canards guided spin stabilized projectile[C]//AIAA Atmospheric Flight Mechanics Conference and Exhibit. US: AIAA, 2008:1-17.
[9]Costello M.Modeling and simulation of a differential roll projectile [C].// Proceedings of the 1998 AIAA Modeling and Simulation Technologies Conference. US: AIAA, 1998: 490-499.
[10]Wernert P, Theodoulis S.Modeling and stability analysis for a class of 155 mm spin-stabilized projectiles with course correction fuse (CCF) [C].// Proceedings of the 2011 AIAA Atmospheric Flight Mechanics Conference and Exhibit. US:AIAA, 2011: 1-13.
[11]陈世年.控制系统设计[M].北京:宇航出版社,1996:313-316.
[2]A.A.德米特里耶夫斯基,H.JI.雷申科,C.C.波哥吉斯托夫.外弹道学[M].北京:国防工业出版社,2000.
[3]徐明友.弹箭飞行力学[M].北京:高等教育出版社,2003.
[4]徐明友.高等外弹道学[M].北京:高等教育出版社,2003.
[5]McCoy R L.Modern Exterior Ballistics [M].Atglen: Schiffer Publishing,,2004.
[6]Murphy C H.对称发射体的自由飞行运动[M].韩子鹏,译.北京:国防工业出版社,1984.
[7]Gagnon E,Lauzon M.Course correction fuse concept analysis for in-service 155mm spin-stabilized gunnery projectiles[C].// Proceedings of the 2008 AIAA Guidance, Navigation and Control Conference and Exhibit. US: AIAA, 2008: 1-20.
[8]Wernert P, Leopold F, Bodino D, et al.Wind tunnel tests and open-loop trajectory simulations for a 155mm canards guided spin stabilized projectile[C]//AIAA Atmospheric Flight Mechanics Conference and Exhibit. US: AIAA, 2008:1-17.
[9]Costello M.Modeling and simulation of a differential roll projectile [C].// Proceedings of the 1998 AIAA Modeling and Simulation Technologies Conference. US: AIAA, 1998: 490-499.
[10]Wernert P, Theodoulis S.Modeling and stability analysis for a class of 155 mm spin-stabilized projectiles with course correction fuse (CCF) [C].// Proceedings of the 2011 AIAA Atmospheric Flight Mechanics Conference and Exhibit. US:AIAA, 2011: 1-13.
[11]陈世年.控制系统设计[M].北京:宇航出版社,1996:313-316.