文献类型：期刊文献

中文题名：一种无静差倾斜稳定回路及其参数优化设计方法

英文题名：Method for Designing Zero Steady-State Error Tilt Stabilization Loop and Its Parameter Optimization

作者：高宏建 陈霖周廷 胡建兴 王文举 杨登红

第一作者：高宏建

机构：[1]贵州理工学院航空航天工程学院,贵阳550025;[2]贵州省无人机应急减灾信息化工程研究中心,贵阳550025;[3]中航贵州飞机有限责任公司,贵州安顺561000

第一机构：贵州理工学院航空航天工程学院

年份：2025

卷号：33

期号：2

起止页码：262-268

中文期刊名：计算机测量与控制

外文期刊名：Computer Measurement &Control

基金：贵州省基金基础研究计划(自然科学)项目(黔科合基础-ZK[2022]一般172);贵州省教育厅普通本科高校青年科技人才成长项目(黔教合KY字[2022]350号);贵州省普通高等学校工程研究中心项目(黔教合KY字[2018]007);贵州理工学院高层次人才引进科研启动项目(XJGC20190610);贵州省科技计划项目(黔科合重大专项[2022]007号)。

语种：中文

中文关键词：无静差;倾斜稳定回路;复杂滚动扰动;非线性自适应惯性因子;参数优化

外文关键词：zero steady-state error;tilt stabilization loop;complex rolling disturbance;nonlinear adaptive inertia factor;parameter optimization

摘要：针对常规倾斜角速度比例积分回路不能有效消除战术导弹滚动通道存在复杂扰动的问题,给出一种无静差倾斜稳定回路结构;采用极点配置方法,推导了期望特征多项式系数与无静差倾斜稳定回路控制参数之间的解析关系;通过带有非线性自适应惯性因子的粒子群优化算法,对期望特征多项式系数进行优化设计,优化结果能够同时满足时域和频域指标要求;将设计结果应用于某战术导弹,六自由度数字仿真和飞行试验结果均表明,该回路结构能够快速消除由初始扰动产生的倾斜角误差,克服各项滚动干扰,保证导弹在飞行过程中倾斜角误差始终为零或尽可能小,满足对倾斜角误差的工程应用要求,验证了方法的正确性和有效性;该方法具有一定的工程应用价值。
Conventional proportional-integration loops with tilt angular velocity can not effectively eliminate complex disturbance in the rolling channel of tactical missiles.To address this issue,,a tilt stabilization loop with zero steady-state error is proposed.Pole configuration method is used to derive analytical relationship between the desired characteristic polynomial coefficients and the control parameters of tilt stabilization loop with zero steady-state error.Through particle swarm optimization algorithm with nonlinear adaptive inertia factor,the desired characteristic polynomial coefficients are optimized and designed,and the optimization results can meet the requirements of both time-domain and frequency-domain indicators simultaneously.The design results are applied to a certain tactical missile,and six-degree-of-freedom digital simulation and flight test results show that,the loop structure can quickly eliminate the tilt angle error caused by the initial disturbance,overcome various rolling interference,and ensure that the tilt angle error of the missile is always zero or as small as possible during flight,which meets the engineering application requirements of tilt angle error,and verifies the correctness and effectiveness of the method.This method has certain engineering application value.