- 外插法，外推法
- 外推法
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extrapolated method中文什么意思
例句與用法
- Convergence of extrapolated method for solving non - hermitian linear systems
解非埃爾米特線性方程組的外推迭代法的收斂性 - Based on some rules of maneuvering targets on the sea , this paper analyses the movement character of maneuvering targets on the sea and builds the mathematics model of forecasting movement by the interpolation and extrapolate method
摘要分析了海上機(jī)動(dòng)目標(biāo)的運(yùn)動(dòng)特性，針對(duì)海上機(jī)動(dòng)目標(biāo)在某些時(shí)間段運(yùn)動(dòng)具有一定的規(guī)律性，用插值外推法建立了預(yù)測(cè)其運(yùn)動(dòng)的數(shù)學(xué)模型。 - Firstly , the existing extrapolating method of stress concentration factor from measured neighboring stress or strain is reviewed briefly , then , course of gm ( 1 , 1 ) model , error source and criterion of examining precision are introduced
文中首先對(duì)已有的應(yīng)力集中外推方法作了簡(jiǎn)要概述，然后，介紹了灰色系統(tǒng)理論gm ( 1 ， 1 )模型的建模過(guò)程、誤差來(lái)源及精度檢驗(yàn)標(biāo)準(zhǔn)。 - The software provides six methods to its user , including kissinger method . ozawa method , freeman - carroll method , zavkovik method , extrapolate method and satava - sestak method . users can choose appropriate methods from them and use them to deal with different curing systems
軟件目前提供給用戶六種各具特色的動(dòng)力學(xué)處理方法，包括kissinger方法， ozawa方法， freeman - carroll方法， zavkovik方法，最佳固化工藝外推的方法和satava - sestak方法。 - The basis of dynamics and simulation includes the iterative flyout angle algorithm to the solutions to lambert problem and battin ' s universal conic section state extrapolate method . then spacecraft ' s orbit roots , maneuver impulse and maneuver time are discussed as the following four part : first of all , the chaser ' s one orbit roots is selected as a variable to simulate its influence to the large scale orbital maneuver . the research reveals fact that the orbit roots both of chaser and target should be close to each other to achieve better maneuver and rendezvous " ability , moreover , the best orbit maneuver and rendezvous occurs when both chaser and target ' s initial phase angle are equal
為了研究了交會(huì)機(jī)動(dòng)中追蹤器和目標(biāo)器的軌道根數(shù)、機(jī)動(dòng)時(shí)限和機(jī)動(dòng)能耗等因素對(duì)交會(huì)機(jī)動(dòng)的影響,仿真和分析分為以下四個(gè)部分:首先,研究了追蹤器軌道單個(gè)參數(shù)為變量情況下兩航天器大范圍交會(huì)機(jī)動(dòng)問(wèn)題,研究表明,追蹤器的變化參量與目標(biāo)器相應(yīng)的參量在接近的情況下可以獲得良好的交會(huì)機(jī)動(dòng)特性,而對(duì)于兩航天器軌道共面的情況下,初始相位角相等時(shí)則獲得最佳的機(jī)動(dòng)效果。