最大飛行重量 的英文怎麼說

中文拼音 [zuìdàfēihángzhòngliáng]
最大飛行重量 英文
weight; allowable gross
  • 最 : 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
  • 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...
  • 行 : 行Ⅰ名詞1 （行列） line; row 2 （排行） seniority among brothers and sisters:你行幾? 我行三。where...
  • 重 : 重Ⅰ名詞（重量; 分量） weight Ⅱ動詞（重視） lay [place put] stress on; place value upon; attach im...
  • 量 : 量動1. （度量） measure 2. （估量） estimate; size up
  • 飛行 : flight; flying; aviate; voyage; volitate; hop
  • 重量 : weight; scale; heft
  1. On the basis of collecting and processing many datum and materials. firstly. this paper analyzes main activities and cost constitutions of each stage of the life cycle of a fcs, and lay a foundation for later analysis and evaluation of system lcc. secondly, a basis method and usage range for estimating the system lcc are introduced. a multivariate linear regression model of pcs development cost and cost driven factor is built by use of the parametric method and supplies the base of cost estimation of newly - developed systems. thirdly, combine actual examples and make statistical analysis of lcc of a certain pcs developed by our institute, predict unhappened usage and service cost with grey prediction method, obtain proportion of each constitute to the lcc. forthly, according to actual conditions, use the fuzzy theory to overall evaluate efficacy of the fcs, fifthly, combimng our actual conditions, investigate specific measures of how to implement the life cycle cost management in our institute and put forward a new conception of developing web - based flight control system lcc management information system with pdm as the platform. at last, investigate important factors such as reliability and maintainability that may affect the life cycle cost of the fcs in detail, and put forward specific methods of lowering the life cycle cost of the fcs

    論文在收集和整理大量資料的基礎上，首先深入分析了飛控系統壽命周期各階段的主要活動以及各階段的費用構成，為以後系統壽命周期費用的分析和評價奠定了基礎；其次，介紹了壽命周期費用估算的基本方法和使用范圍，並利用參數法建立了飛控系統研製費用與費用驅動因子的多元線性回歸模型，為新研系統的費用估算提供了依據；第三，結合實例對我所研製的某型飛控系統的壽命周期費用進行統計分析，運用灰色預測方法對未發生的使用及維修費用進行預測，得出了該系統的壽命周期費用以及各組成部分所佔比例；第四，根據實際情況，首次運用模糊理論對飛控系統的系統效能進行了綜合評價，構造了飛控系統系統效能模糊綜合評價模型；第五，結合我所實際，探討了如何在本單位實施加強壽命周期費用管理的具體措施，提出以pdm為平臺，開發基於web的飛控系統lcc管理信息系統的新構思；最後，對影響飛控系統壽命周期費用的重要因素如可靠性和維修性等進行了詳細地研究，提出了降低飛控系統壽命周期費用的具體方法。
  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. During flight of a solar powered aircraft, latitude and direction are changing at all times, therefore the optimal latitude and the optimal direction at different period is developed

    太陽能飛機在飛行時，飛行緯度和太陽方位角都在隨時發生變化，所以本文著重討論了每個時段使太陽能飛機獲得最大輻射量的緯度和方向（太陽方位角） 。
  5. He / she prepares flight plans containing information such as maximum allowable takeoff and landing weights, weather reports, field conditions, notams and many other informational components required for the safe completion of flight

    收集保證飛行安全的各種信息（最大允許的起飛、著陸重量、天氣報告、機場情況、航行通告和其他有必要的信息） ，制訂飛行計劃。
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