最小正整數解 的英文怎麼說

中文拼音 [zuìxiǎozhēngzhěngshǔjiě]
最小正整數解 英文
minimal positive integral solution
  • : 副詞(表示某種屬性超過所有同類的人或事物) most; best; worst; first; very; least; above all; -est
  • : Ⅰ形容詞1 (體積、面積、數量、強度等不大) small; little; petty; minor 2 (年紀小的; 年幼的) youn...
  • : 正名詞(正月) the first month of the lunar year; the first moon
  • : Ⅰ形容詞1 (全部在內; 完整) whole; all; complete 2 (整齊) neat; tidy; orderly Ⅱ動詞1 (整理; 整...
  • : 數副詞(屢次) frequently; repeatedly
  • : 解動詞(解送) send under guard
  • 整數 : 1. (不含分數或小數的數) integer; whole number; integral number2. (沒有零頭的數目) round number; round figure
  1. Disigning coolant channel on the firebox of liquid rocket engine to loxodrome ( equal - angle helix ) groove can improve firebox coolant capability greatly. because the width dimension of loxodrome groove is narrow and the depth is deep, some machining methods are incapable, such as end - milling or electrochemistry. according to the peculiarities, a cnc disk - cutter - milling method which is composed of five motion axes with four simultaneously interpolated ones is researched. because most firebox generatrix is composed of complex curves, it is very difficult to get cnc cutting program with manual means. in order to deal with the problem, the loxodrome mathematics model is studied, and an auto - programming software system is developed. the software system can generate cnc cutting program of loxodrome on many kinds of turned surface. the constriction - distension segment of firebox is the most representative workpiece. the sharp changing of its generatrix slope makes loxodrome milling difficult. with the theory analyzing and practice cutting experiment, some applied techniques, which include milling mode and direction, choosing cutter diameter and cutting start point setting, are developed. adopting the technology above, tens regular workpiece have been manufacturing. the two - year manufacture practice has confirmed the validity and feasibility of developed loxodrome coolant channel milling method. the developed technology is also worth to be referenced to other similar workpiece

    將液體火箭發動機燃燒室的冷卻通道設計為斜航線(等傾角螺旋線)槽形,可以大幅度改善燃燒室的冷卻性能.斜航線冷卻槽的槽寬尺寸較而槽深尺寸較大,所以無法使用棒銑刀銑削、電化學等加工方式.針對這些特點,提出了五軸控制、四軸聯動的控片銑刀銑削加工方法.由於燃燒室外表面的母線輪廓復雜,手工編制控加工程序難度大.為了控加工程序的編制問題,研究了斜航線的學模型,開發了自動編程軟體系統.使用該系統,可以生成多種母線輪廓回轉體外表面上的斜航線控加工程序.燃燒室收斂-擴張段的母線斜率變化大,加工難度大,是斜航線冷卻通道加工的典型工件.經過理論分析和實際切削實驗,研究了針對該類型工件的片銑刀直徑選擇、銑削方式和方向、刀具調和起刀點的設置等多項實際的加工方案.採用上述的一系列技術,已經成功地加工了十個合格工件.經過兩年多的實際生產過程應用,驗證了所開發的斜航線冷卻通道加工方法的確性和可行性.這些加工技術的研製成功,對其他相似類型零件的加工亦具有參考意義
  2. A integrated algorithm of ambiguity resolution is proposed. by using triple carrier phase, integer gauss transformations, qr factorization, cholesky factorization, and geometry constraint, the correlation between ambiguity components is reduced, and more error ambiguity can be discarded, also process of ambiguity searching getting rapidly. the ratio test combining constraint of baseline is used to fix ambiguity rapidly

    利用三差二乘求模糊度浮點,然後採用高斯變換降低模糊度分量間的相關性,再根據qr分和基線幾何約束減少需搜索的模糊度組合,採用cholesky分在搜索過程中及早淘汰不確的模糊度組合,後利用ratio檢驗與基線幾何約束條件相結合檢驗模糊度組合,盡快固定確的模糊度。
  3. For parameter a, there is a close relationship exist between a ( 9, sr ) in two different radar incident angle that can be expressed as : with considering the effects of soil texture, we get the final expression of the inversion model : where mv ( t1 ), mv ( t2 ) is volumetric soil moisture content in two different temp, c, d is soil type related parameters, and v ( t1 ), s ( t2 ) is coresponding bare soil radar backscattering coefficients. inversion results show that for the c band hh polarized radarsat scansar data with a range of incidence angle from 20 to 40, the soil moisture change value can be derived with an acceptable accuracy using the above model. the temporal and spatial soil moisture change patterns are associated with rainfall and vegetation cover, as well as the soil hydraulic characteristics

    利用新發展的電磁波散射模型研究了不同植被覆蓋地表雷達波對地表土壤水分的敏感性,建立了半經驗植被雷達後向散射模型; 2 ) .研究發現在農作物等矮植被覆蓋地表,植被層直接後向散射與植被類型相關,且在植被生長期,雷達後向散射系對植被含水量的敏感性要高於對植被高度變化的敏感性; 3 ) .決了單參雷達地表土壤水分反演問題中,雷達入射角和地表粗糙度的影響這一難點問題; 4 ) .利用土壤介電模型校了不同土壤類型對反演地表土壤體積含水量的影響; 5 ) .在以上成果基礎上,建立了完的單參雷達地表土壤水分變化探測反演演算法,經地表驗證,模型反演地表土壤水分變化值的精度為rmse = 0
  4. 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:探討了一種新的設計指標優分配方法- -協同分配法,用於處理飛機頂層設計中的大規模設計指標優分配問題.分析了飛機頂層設計中的設計指標優分配特徵,據此給出了協同法的原理並建立了學模型.協同法按設計指標分配關系將優分配問題分為主系統優化和子系統優化,主優化對子系統設計指標進行優分配,子優化以化分配設計指標值與期望設計指標值之間的差異為目標,進行子系統優設計,或對底層元件(如飛機翼梁、翼肋和翼盒等)進行設計指標優分配,並把信息反饋給主優化.主優化通過子優化信息構成的一致性約束協調分配量,提高系統體性能,並重新給出分配方案.主系統與子系統反復協調,直到得到設計指標優分配方案.兩層可靠度指標分配算例初步驗證了本文方法的確性與可行性,三層可靠度指標分配算例證明了本文方法的有效性.後,以重量指標分配為例,簡要敘述了針對飛機頂層設計中設計指標協同分配的學模型和求思路
  5. 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

    探討了一種新的設計指標優分配方法- -協同分配法,用於處理飛機頂層設計中的大規模設計指標優分配問題.分析了飛機頂層設計中的設計指標優分配特徵,據此給出了協同法的原理並建立了學模型.協同法按設計指標分配關系將優分配問題分為主系統優化和子系統優化,主優化對子系統設計指標進行優分配,子優化以化分配設計指標值與期望設計指標值之間的差異為目標,進行子系統優設計,或對底層元件(如飛機翼梁、翼肋和翼盒等)進行設計指標優分配,並把信息反饋給主優化.主優化通過子優化信息構成的一致性約束協調分配量,提高系統體性能,並重新給出分配方案.主系統與子系統反復協調,直到得到設計指標優分配方案.兩層可靠度指標分配算例初步驗證了本文方法的確性與可行性,三層可靠度指標分配算例證明了本文方法的有效性.後,以重量指標分配為例,簡要敘述了針對飛機頂層設計中設計指標協同分配的學模型和求思路
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