solution procedure造句
例句與造句
- In this thesis , an incremental - iterative solution procedure using the modified newton - raphson iteration is used to solve geometrically nonlinear problems
在涉及幾何非線性問題的數(shù)值方法中，通常都采用增量和迭代分析的方法。 - The given method is simple and high efficiency , because most classification problems could be done through the first criterion , and complex solution procedure in getting the object ' s area could be saved
該方法簡單有效，在大多數(shù)情況下用準(zhǔn)則一即可判斷物體形狀，從而避免進行較復(fù)雜的目標(biāo)面積的計算。 - In this paper , the general theory and numerical solution procedure were described . by building a diesel modeling with vertical valves and a piston bowl , a whole cycle was calculated , which include intake stroke , compression stroke , expansion stroke and exhaust stroke
通過對帶有進、排氣門的柴油機進行計算，模擬了一個完整循環(huán)內(nèi)進氣道、氣門和缸內(nèi)氣體流動的全過程。 - To solve an electrically large problem with clusters , the parallel solution procedure is very complex and the demands of the users ’ ability of development and application are very critical , such as the complex system and software environment , parallel programming and debugging
利用集群系統(tǒng)求解大問題,并行求解過程非常復(fù)雜,對用戶的開發(fā)和應(yīng)用要求極高,比如復(fù)雜的系統(tǒng)和軟件環(huán)境,并行程序的設(shè)計和調(diào)試等。 - The coordinate transformation rules , the combination characteristic of the transfer function are discussed . the solution procedure of series mechanical system is deduced by applying dual - vector addition and matrix multiplication . and the mathematical models are obtained
根據(jù)建立的數(shù)學(xué)模型，本文提出了相應(yīng)的按位存儲數(shù)據(jù)結(jié)構(gòu)以及樹型遞歸分解算法，實現(xiàn)了狀態(tài)變換矩陣(包括類型、方向及變換特征)的自動分解。 - It's difficult to find solution procedure in a sentence. 用solution procedure造句挺難的
- A multi - block incompressible viscous flow solver has been developed that can be applied to simulation of a variety of ship maneuvering related flows and calculation of hydrodynamic forces . validation and verification of the solution procedure are carried out on several model problems with good agreement to experimental and numerical results . the present block - structured viscous flow solver is based on solving the reynolds - averaged navier - stokes ( rans ) equations with a second - order cell - centered finite volume method ( fvm ) on non - staggered grids
本文即在這種背景下，瞄準(zhǔn)船舶操縱水動力預(yù)報方面的國際前沿和熱點課題，通過對現(xiàn)代船舶粘性流計算方法的研究，自主開發(fā)了一個船舶操縱粘性流求解器，并將所開發(fā)的求解器成功地應(yīng)用于一系列和船舶操縱問題相關(guān)的粘性流動與水動力計算，得到了令人滿意的結(jié)果。 - The contents of the course include the elastic problems and associated solution procedure ; the basic concepts and assumptions of elasticity ; the solution of a planar elastic problem defined in a rectangular coordinate ; the matrix expression of basic equations of a planar elastic problem ; the solution of a planar problem defined in a polar coordinate ; the basic equations and solution procedure of a three - dimensional elastic problem ; bending of a plate ; and the variational principles of energy
本課程的主要內(nèi)容包括:彈性力學(xué)問題及其求解思想;彈性力學(xué)中的基本概念及基本假定;彈性力學(xué)平面問題的直角坐標(biāo)解答;平面問題基本方程的矩陣表示;平面問題的極坐標(biāo)解答;彈性力學(xué)空間問題的基本方程及其解法;薄板的彎曲;能量變分原理等等 - Abstract : a new method , collaborative allocation ( ca ) , is proposed to solve the large - scale optimum allocation problem in aircraft conceptual design . according to the characteristics of optimum allocation in aircraft conceptual design . the principle and mathematical model of ca are established . the optimum allocation problem is decomposed into one main optimization problem and several sub - optimization problems . a group of design requirements for subsystems are provided by the main system respectively , and the subsystems execute their own optimizations or further provide the detailed design requirements to the bottom components of aircraft , such as spars , ribs and skins , etc . the subsystems minimize the discrepancy between their own local variables and the corresponding allocated values , and then return the optimization results to main optimization . the main optimization is performed to reallocate the design requirements for improving the integration performance and progressing toward the compatibilities among subsystems . ca provides the general optimum allocation architecture and is easy to be carried out . furthermore , the concurrent computation can also be realized . two examples of optimum reliability allocation are used to describe the implementation procedure of ca for two - level allocation and three - level allocation respectively , and to validate preliminarily its correctness and effectiveness . it is shown that the developed method can be successfully used in optimum allocation of design requirements . then taking weight requirement allocation as example , the mathematical model and solution procedure for collaborative allocation of design requirements in aircraft conceptual design are briefly depicted
文摘:探討了一種新的設(shè)計指標(biāo)最優(yōu)分配方法- -協(xié)同分配法,用于處理飛機頂層設(shè)計中的大規(guī)模設(shè)計指標(biāo)最優(yōu)分配問題.分析了飛機頂層設(shè)計中的設(shè)計指標(biāo)最優(yōu)分配特征,據(jù)此給出了協(xié)同法的原理并建立了數(shù)學(xué)模型.協(xié)同法按設(shè)計指標(biāo)分配關(guān)系將最優(yōu)分配問題分解為主系統(tǒng)優(yōu)化和子系統(tǒng)優(yōu)化,主優(yōu)化對子系統(tǒng)設(shè)計指標(biāo)進行最優(yōu)分配,子優(yōu)化以最小化分配設(shè)計指標(biāo)值與期望設(shè)計指標(biāo)值之間的差異為目標(biāo),進行子系統(tǒng)最優(yōu)設(shè)計,或?qū)Φ讓釉?如飛機翼梁、翼肋和翼盒等)進行設(shè)計指標(biāo)最優(yōu)分配,并把最優(yōu)解信息反饋給主優(yōu)化.主優(yōu)化通過子優(yōu)化最優(yōu)解信息構(gòu)成的一致性約束協(xié)調(diào)分配量,提高系統(tǒng)整體性能,并重新給出分配方案.主系統(tǒng)與子系統(tǒng)反復(fù)協(xié)調(diào),直到得到設(shè)計指標(biāo)最優(yōu)分配方案.兩層可靠度指標(biāo)分配算例初步驗證了本文方法的正確性與可行性,三層可靠度指標(biāo)分配算例證明了本文方法的有效性.最后,以重量指標(biāo)分配為例,簡要敘述了針對飛機頂層設(shè)計中設(shè)計指標(biāo)協(xié)同分配的數(shù)學(xué)模型和求解思路 - A new method , collaborative allocation ( ca ) , is proposed to solve the large - scale optimum allocation problem in aircraft conceptual design . according to the characteristics of optimum allocation in aircraft conceptual design . the principle and mathematical model of ca are established . the optimum allocation problem is decomposed into one main optimization problem and several sub - optimization problems . a group of design requirements for subsystems are provided by the main system respectively , and the subsystems execute their own optimizations or further provide the detailed design requirements to the bottom components of aircraft , such as spars , ribs and skins , etc . the subsystems minimize the discrepancy between their own local variables and the corresponding allocated values , and then return the optimization results to main optimization . the main optimization is performed to reallocate the design requirements for improving the integration performance and progressing toward the compatibilities among subsystems . ca provides the general optimum allocation architecture and is easy to be carried out . furthermore , the concurrent computation can also be realized . two examples of optimum reliability allocation are used to describe the implementation procedure of ca for two - level allocation and three - level allocation respectively , and to validate preliminarily its correctness and effectiveness . it is shown that the developed method can be successfully used in optimum allocation of design requirements . then taking weight requirement allocation as example , the mathematical model and solution procedure for collaborative allocation of design requirements in aircraft conceptual design are briefly depicted
探討了一種新的設(shè)計指標(biāo)最優(yōu)分配方法- -協(xié)同分配法,用于處理飛機頂層設(shè)計中的大規(guī)模設(shè)計指標(biāo)最優(yōu)分配問題.分析了飛機頂層設(shè)計中的設(shè)計指標(biāo)最優(yōu)分配特征,據(jù)此給出了協(xié)同法的原理并建立了數(shù)學(xué)模型.協(xié)同法按設(shè)計指標(biāo)分配關(guān)系將最優(yōu)分配問題分解為主系統(tǒng)優(yōu)化和子系統(tǒng)優(yōu)化,主優(yōu)化對子系統(tǒng)設(shè)計指標(biāo)進行最優(yōu)分配,子優(yōu)化以最小化分配設(shè)計指標(biāo)值與期望設(shè)計指標(biāo)值之間的差異為目標(biāo),進行子系統(tǒng)最優(yōu)設(shè)計,或?qū)Φ讓釉?如飛機翼梁、翼肋和翼盒等)進行設(shè)計指標(biāo)最優(yōu)分配,并把最優(yōu)解信息反饋給主優(yōu)化.主優(yōu)化通過子優(yōu)化最優(yōu)解信息構(gòu)成的一致性約束協(xié)調(diào)分配量,提高系統(tǒng)整體性能,并重新給出分配方案.主系統(tǒng)與子系統(tǒng)反復(fù)協(xié)調(diào),直到得到設(shè)計指標(biāo)最優(yōu)分配方案.兩層可靠度指標(biāo)分配算例初步驗證了本文方法的正確性與可行性,三層可靠度指標(biāo)分配算例證明了本文方法的有效性.最后,以重量指標(biāo)分配為例,簡要敘述了針對飛機頂層設(shè)計中設(shè)計指標(biāo)協(xié)同分配的數(shù)學(xué)模型和求解思路