2) Guidance instrumentation systematic error
制导工具误差
1.
Guidance instrumentation systematic error and initial launched parameters error are two principal factors in the submarine launched missile precision analysis.
影响海基导弹落点偏差的因素主要是制导工具误差和初始发射参数误差。
2.
The least squares support vector machines(LS-SVM) are applied to separating and converting the guidance instrumentation systematic error(GISE),and the estimation of GISE is obtained based on the linear kernel function.
将最小二乘支持向量机方法应用于制导工具误差分离于折合。
3) guidance instrument error
制导工具误差
1.
Fast evaluating methods on guidance instrument error based on experiment design and trajectory simulation;
基于试验设计与弹道仿真的制导工具误差快速评价方法
2.
Application of improved latent regression to SINS guidance instrument error estimation;
特征根估计方法在SINS制导工具误差估计中的应用
3.
To the limitation of the evaluating method of guidance instrument error and the precision of impact point,the methods synthetically estimating guidance instrument error by environmental function and trajectory simulation are presented.
针对目前制导工具误差评价和落点精度评定的方法中存在的缺陷,提出了基于环境函数法和弹道仿真法的制导工具误差综合评价方法,推导了制导工具各单机单项性能指标与导弹落点精度的函数关系式和交叉耦合关系式。
4) Guidance instrumentation error
制导工具误差
1.
A new method for separating and converting of guidance instrumentation error was proposed which is the support vector machines.
制导工具误差分离与折合是导弹精度评定中的重要问题。
2.
Considering initial error and guidance instrumentation error synthetically a full model of error separation is constructed,and then a corresponding calculational method based on time intervals is presented.
首先分析了发射初始误差对导弹落点偏差的影响机理,然后利用初始误差在发射惯性系中的传递关系得到了初始误差环境函数矩阵,建立了综合考虑初始误差与制导工具误差的完整误差分离模型,并提出了一种分时间段的误差分离方法。
5) guidance instrument error modeling
制导工具误差建模
6) inertial guidance instrument error
惯性制导工具误差
1.
Based on the inertial guidance instrument error model,the model of reentry point’s parameters is established in this paper.
基于惯性制导工具误差模型,推导出存在工具误差时的再入点运动参数模型。
补充资料：波束制导(见遥控制导)
波束制导(见遥控制导)
beam-rider guidance
boshu zhidao波束制导(beam一rider guidanee)见遥控制导。
说明：补充资料仅用于学习参考，请勿用于其它任何用途。
参考词条