飛機分配數量 的英文怎麼說

中文拼音 [fēijīfēnpèishǔliáng]
飛機分配數量 英文
aircraft allocation
  • 飛 : Ⅰ動詞1 （鳥、蟲等在空中活動） fly; flit 2 （利用動力機械在空中行動） fly 3 （在空中飄浮遊動） fly...
  • 機 : machineengine
  • 分 : 分Ⅰ名詞1. （成分） component 2. （職責和權利的限度） what is within one's duty or rights Ⅱ同 「份」Ⅲ動詞[書面語] （料想） judge
  • 配 : Ⅰ動詞1 （兩性結合） join in marriage 2 （使動物交配） mate （animals） 3 （按適當的標準或比例加以...
  • 數 : 數副詞（屢次） frequently; repeatedly
  • 量 : 量動1. （度量） measure 2. （估量） estimate; size up
  • 飛機 : airplane; plane; aeroplane; kite; bird; aircraft
  • 數量 : quantity; quantum; amount; magnitude; number
  1. The precision of the non - contact testing of flywheel gear ' s contour and location error of light electricity inspection machine based on virtual instrument has been carried on theory analysis in this paper. various contour and location tolerances of the part have been distributed depending on the result of the analysis, and the data handling method of measurement has been studied to find a data handling method of getting rid of the system error under one kind of condition of the big sample space

    本文對飛輪齒圈形位誤差光電檢驗機的精度進行了理論分析，依據分析的結果分配了零件的各種形位公差，並對測量結果的數據處理方法進行了研究，找到了一種在大樣本空間的條件下依概率排除系統誤差的數據處理方法，同時為了驗證其可靠度對其進行了計算機模擬實驗。
  2. 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最優分配方法- -協同分配法，用於處理飛機頂層設計中的大規模設計指標最優分配問題.分析了飛機頂層設計中的設計指標最優分配特徵，據此給出了協同法的原理並建立了數學模型.協同法按設計指標分配關系將最優分配問題分解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最優分配，子優化以最小化分配設計指標值與期望設計指標值之間的差異為目標，進行子系統最優設計，或對底層元件（如飛機翼梁、翼肋和翼盒等）進行設計指標最優分配，並把最優解信息反饋給主優化.主優化通過子優化最優解信息構成的一致性約束協調分配量，提高系統整體性能，並重新給出分配方案.主系統與子系統反復協調，直到得到設計指標最優分配方案.兩層可靠度指標分配算例初步驗證了本文方法的正確性與可行性，三層可靠度指標分配算例證明了本文方法的有效性.最後，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數學模型和求解思路
  3. 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最優分配方法- -協同分配法，用於處理飛機頂層設計中的大規模設計指標最優分配問題.分析了飛機頂層設計中的設計指標最優分配特徵，據此給出了協同法的原理並建立了數學模型.協同法按設計指標分配關系將最優分配問題分解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最優分配，子優化以最小化分配設計指標值與期望設計指標值之間的差異為目標，進行子系統最優設計，或對底層元件（如飛機翼梁、翼肋和翼盒等）進行設計指標最優分配，並把最優解信息反饋給主優化.主優化通過子優化最優解信息構成的一致性約束協調分配量，提高系統整體性能，並重新給出分配方案.主系統與子系統反復協調，直到得到設計指標最優分配方案.兩層可靠度指標分配算例初步驗證了本文方法的正確性與可行性，三層可靠度指標分配算例證明了本文方法的有效性.最後，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數學模型和求解思路
  4. Abstract : according to the probability model of aerointerceptor ' s interception effect under optimum target distribution form ( tdf ), the optimum tdf in which aerointerceptors intercept groups of attack - planes are deduced, the relation among dispatching fighter number, airport ' s tactical and technological parameters, aerointerceptor ' s tactical and technological parameters, and attack - situation of attack - planes is researched, the quantitacation relationship are then determined which should satisfy when airport ' s aerointerceptors conduct optimum target distribution on groups of attack - planes. starting from operational practice, the model can provide certain theoretical basis for the military decisions

    文摘:根據截擊機在優化的目標分配形式下攔截效果的概率模型，導出了截擊機在攔截多攻擊機機群時的最優目標分配形式;研究了機場飛機起飛架數與機場戰術、技術參數、機場飛機的戰術、技術參數以及與攻擊機的進攻態勢之間的關系;確定了多機場飛機對多攻擊機機群進行最優目標分配時所應滿足的量化關系，給出的模型可對作戰決策過程提供理論依據。
  5. The background of rapidly developed uhsm ( ultra high speed machining ) technology is introduced and the key function of the uhs ( ultra high speed ) motorized spindle to uhsm is discussed in the thesis. after analyzing international technology status and trend of the uhs motorized spindle study, we research the core technologies related to the uhs motorized spindle in detail, such as optimized design of the motorized spindle structure, high speed bearing technologies, oil - gas lubication technologies, precision machining and assembly technologies, design and manufacture technologies of the built - in frameless motor etc. then the digital simulation of the motorized spindle sensor - less vector control system is studied thoroughly

    本文從超高速加工技術飛速發展的背景出發，討論了超高速電主軸對超高速加工技術發展的重要作用和意義；分析了超高速電主軸研究的國內外現狀及發展趨勢；詳細論述了超高速電主軸的關鍵技術，包括電主軸結構優化設計、高速軸承技術、油氣潤滑技術、精密加工與精密裝配技術以及內裝式電機設計製造技術等，並深入研究了超高速電主軸無速度傳感器矢量控制系統的數字模擬技術。
  6. Generally speaking, the algorithm of terrain contour matching is adapted to be used in cruise missiles which made fight path prior for that this algorithm is not a real - time system for it makes use of historical terrain data. while kalman filter algorithm is a real - time, rapid calculation system. which is appropriate for pilot or pilotless aircraft

    得出，地形輪廓匹配演算法使用歷史地形數據，實時性差，比較適合事先規劃好航跡的導彈使用：卡爾曼濾波的方法有較好的實時性，計算速度快，很適合有人無人駕駛飛機的機動飛行要求；小波分層只是對地形信息做了高低頻分解，其本質還是相似性度量演算法，但它有效的降低了匹配演算法的計算量。
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