有控火箭靶弹的控制方式和弹道特性  

Control Mode and Trajectory Characteristics of Controllable Rocket Target

作　　者：王朋飞 周前进 WANG Pengfei;ZHOU Qianjin(Xi’an Aeronautical Polytechnic Institute, Xi’an 710089, China;State Factory No.990, Hefei 230601, China)

机构地区：[1]西安航空职业技术学院,西安710089 [2]国营990厂,合肥230601

出　　处：《兵器装备工程学报》2021年第3期79-82,共4页Journal of Ordnance Equipment Engineering

摘　　要：针对有控火箭靶弹模拟平飞类目标飞行弹道问题,提出了采用变舵偏角控制和直线滑翔飞行控制两种舵面控制方式调整方案,仿真分析了两种控制方式下的飞行弹道。结果表明:变舵偏角控制方式调整舵偏角可以得到滑翔飞行弹道,直线滑翔飞行控制方式可以得到平飞弹道,均满足供靶条件。Two kinds of adjustment schemes of rudder control modes were proposed,which are variable rudder angle control and linear glide flight control,aiming at the problem of simulating the flight trajectory of level flying target with controllable rocket target.The flight trajectory of the two control modes was simulated and analyzed.The results showed that glide trajectory can be obtained by adjusting the rudder deflection angle of the variable rudder deflection control mode,the level trajectory can be obtained by linear glide control mode,and the flight trajectory obtained by two control modes meet the target supply conditions.

关 键 词：有控火箭靶弹 飞行弹道 舵面控制方式 舵偏角 弹道仿真 

分 类 号：TJ013.2[兵器科学与技术—兵器发射理论与技术]