optimum aircraft 中文意思是什麼
optimum aircraft
解釋
最佳方案的飛機-
Cnsatm systems will minimise airspace constraints and reduce traffic congestion, and this will enable aircraft to operate within their most optimum flight envelope, commensurate with achieving a marked increase in flight safety
衛星通訊、導航及監察航空交通管理系統可把空域限制減至最少，紓緩交通擠逼，從而讓航機充分發揮其性能，並且大大提升飛行安全。 -
By using the method of aircraft and turbofan engine integrated analysis, a model of maneuverable missile and turbofan engine integrated optimum design was developed and the computational examples and the analysis were presented
摘要利用飛機渦扇發動機一體化設計的思路，建立了飛航導彈渦扇發動機一體化設計的優化設計模型並給出了算例和分析。 -
From the point of view of attack - defense of tactical ballistic missile and aircraft carriers and through analyzing the mobile area and scouting early warnings and mobile evading capability of aircraft carrier the tactical ballistic missile ' s optimum attack tactics and aircraft carrier ' s defense tactics were made
摘要從常規彈道導彈與航空母艦攻防對抗的角度出發，通過對航母機動區城及偵察預警、機動規避能力的分析，確定了雙方的最優攻防策略。 -
" the cnsatm has immense benefits in enabling aircraft to operate more frequently within their most optimum flight envelop, while minimising airspace constraints, and reducing traffic congestion. it also commensurates with achieving a marked increase in flight safety
該系統不但能容讓航機在最佳的飛行狀態范圍增加飛行次數，把空域限制減至最少，紓緩航空交通擠塞，而且更可顯著提高飛行安全。 -
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 -
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 -
Firstly, a study of target sorting in air combat of single aircraft against multiple targets is presented using the fuzzy optimization method. according to given velocities, distance, relative angle, the target capability and the relative energy index between the target and the attack, the factors are changed into threaten index, which is between the attack and the target, using the mathematic optimum method
應用模糊多目標決策基本理論與方法，在單機攻擊多目標機過程中，根據與排序有關的載機與目標機相對速度、能量、距離等因素，用模糊優屬度演算法把它們換算成目標機對載機的威脅指數，然後確定載機對目標機攻擊的先後次序。 -
The integrated aerodynamic / structural design optimization of a simple general aviation aircraft wing demonstrates that the basic two - level optimization is simple in terms of implementation and stable in terms of computation, while the surrogate - based one has the better ability to find the global optimum
輕型飛機機翼設計的演算法表明，基本二級優化方法流程簡單，穩定可靠;而基於代理模型的二級優化方法全局尋優能力更強。
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