摘要
针对舰载火箭炮在瞄准过程中,高低机不仅要克服火箭炮起落部分自身负载所产生的阻力矩,同时还需克服由于舰船摇摆导致火箭炮起落部分所产生的惯性力矩的特点,系统分析了高低机瞄准过程的负载力矩,分别采用概率法和仿真分析法对高低机静态和动态传动误差进行了研究,并推导了高低机的负载力矩及传动误差计算公式。结合实例计算结果,分析了高低机负载力矩各组成部分的权重及影响因素,对比分析了传动总误差与实测传动误差值,验证了公式正确性,研究结果可为舰载火箭炮总体设计、部件设计、高低机可靠性和安全性评估以及分析高低机对火箭炮稳瞄精度的影响提供参考。
In the course of sighting,the shipborne rocket launcher elevating mechanism has to overcome resistance distance of the elevating mechanism and the inertial torque caused by the ship’s sway in the the elevating mechanism.The load torque of elevating mechanism in the course of sighting was systematically analyzed.The probability method was applied to analyze the static error of elevating mechanism transmission,while simulation analysis was applied to study the dynamic error,with the calculation formulas of load torque and transmission error deduced.In combination with the calculation results of the example,which analyzed the weight and influencing factors of each component of the load torque of elevating mechanism,with the total transmission error and the measured transmission error compared and analyzed,and with the correctness of the formula verified.The research results can provide references for the overall and component designs,reliability and safety evaluations as well as the analysis of the impact of the elevating mechanism on the stabalized sighting accuracy of the shipborne rocket launcher.
作者
范虎成
方帆
牛天宏
崔二巍
朱汉顺
柯彪
FAN Hucheng;FANG Fan;NIU Tianhong;CUI Erwei;ZHU Hanshun;KE Biao(Northwest Institute of Mechanical & Electrical Engineering, Xianyang 712099, Shaanxi, China;Unit 32382 of PLA,Beijing 100072, China)
出处
《火炮发射与控制学报》
北大核心
2020年第2期53-58,68,共7页
Journal of Gun Launch & Control
关键词
舰载火箭炮
高低机
惯性力矩
传动误差
shipborne rocket launcher
elevating mechanism
inertial torque
transmission error
