rocket optimization 中文意思是什麼

rocket optimization 解釋
火箭最優化
  • rocket : n 火箭；火箭彈，火箭發動機；火箭式投射器；〈英俚〉斥責。 a carrier [freight] rocket 載運火箭。 an...
  • optimization : n. 最佳化，最優化。
  1. Firing orders optimization of aero - defence rocket launcher by volley firing

    群射防空火箭炮射序優化
  2. Design optimization for solid rocket motor based on graph morphing

    基於圖形變形法的固體火箭發動機優化設計
  3. Uncertainty optimization design of solid rocket motor grain

    固體火箭發動機裝藥不確定性優化設計
  4. Design optimization of chamber pressure and nozzle area expansion ratio of solid rocket motors

    固體火箭發動機燃燒室壓強及噴管擴張比優化設計
  5. Analysis of failure and optimization for composite case of solid rocket engine

    固體火箭發動機復合材料殼體破壞分析及優化
  6. It is determined now by calculation with mathematical relationship of the flight thrust to the physical quantities which can be measured directly. the optimization of the software development platform is also analyzed inspect of the solid rocket - ramjet developmental program

    其次，為滿足固體火箭沖壓發動機試驗技術進一步研究需要，在深入分析labview圖形化編程軟體優化方法的基礎上，改進了現有的固體火箭沖壓發動機試驗測控程序，並應用於發動機試驗中。
  7. Using method of sumt and powell, the thesis carries out optimization design for air rocket with double - push accelerated velocity and spin - rate regularity, which dramatically decreases air rocket dispersion. in the end, some valuable conclusions are achieved for application

    綜合利用雙推力加速度，轉速規律，同時採用內點罰函數法和powell共軛方向法，對航空火箭彈的主要參數進行優化設計，實現了大幅度減小航空火箭彈散布的目的，得到了一些有應用價值的結論。
  8. Using the ipga and setting the terminal speed increment of the upper stage and the manufacture cost of cpkm as objective functions, the rocket motor are processed dual - objective optimization design that has six design parameters

    採用ipga演算法，以該運載火箭上面級末速度增量最大及cpkm發動機的製造成本最低作為目標函數，對該發動機進行了雙目標優化設計。
  9. The child system of calculation analysis includes the optimization design of total parameters of solid rocket motor, the calculation of internal trajectory, the calculation of thermodynamic parameters, the limited element analysis for stress of motor shell, the calculation of structure characteristic parameters, the calculation of particle external trajectory, the design and calculation of the ignition device

    計算分析子系統包括火箭發動機總體優化設計、內彈道計算、熱力參數計算、發動機殼體應力有限元分析、結構特徵值計算、質點外彈道計算、點火裝置的設計計算。
  10. Application of ansys program optimization techniques to solid rocket motor design

    程序優化技術在固體火箭發動機設計中的應用
  11. Genetic algorithm applied to integral design optimization of missile propelled by solid rocket ramjet

    固體火箭沖壓發動機導彈一體化遺傳演算法優化設計
  12. Comparison of design optimization methods for flight vehicle solid rocket booster

    飛行器固體火箭助推器設計優化方法比較
  13. Design of two propulsion systems is studied - solid rocket ramjet and liquid ramjet. the performance analysis models and design methods are set up for these two kinds of engines. the different characteristics are analyzed and compared, which provide basis for farther trajectory computation and conceptual optimization design

    （ 4 ）研究了兩種動力裝置? ?固體火箭沖壓發動機和液體燃料沖壓發動機的設計問題，建立了兩種發動機的性能分析模型和計算方法，對固體火箭沖壓發動機和液體燃料沖壓發動機的特性進行計算分析及比較，為彈道計算及總體優化設計提供依據。
  14. A ga to resolve process route optimization of solid rocket motor shell is studied

    研究了基於遺傳演算法的固體發動機殼體工藝流程面向成本優化問題。
  15. The emulation computation shows its availability. and taking the manufacturing process of the solid rocket motor shell for example, value of process route as objective and cost of process route as constraint, an optimization process is obtained using aga

    最後，針對固體發動機殼體製造工藝方案優化問題，以工藝路線的總價值系數為目標函數並以總成本小於某固定值作為約束條件，採用aga得到了一條最佳工藝路線。
  16. The optimization design of dfc is expounded and the concept and method of multiobjective optimization are used to the upper stage solid rocket motor ( cpkm ) of a kind of launching vehicle

    闡述了面向成本的優化設計問題，並將多目標優化概念和方法應用於某運載火箭上面級固體發動機（ cpkm ）方案設計。
  17. Collaborative optimization method is studied in depth, the causes leading to computational difficulty of this method are discussed by optimization theory and computation examples, and improve method which may solve this problem is presented. based on the comparison of several optimization methods and the characteristics of modern rocket - ramjet, step optimization pattern - a new integrated design mode is presented and is used to realize integrated design of rocket - ramjet. inner and outer fiowfield of a certain integral rocket - ramjet missile is simulated numerically using n - s equation

    （ 2 ）系統地研究了導彈總體優化設計方法，探討了多學科設計優化的原理、框架結構、具體表述形式，深入研究了協作優化方法的原理，從優化原理和算例兩方面討論了造成協作優化方法計算困難的原因，提出了可能克服這種計算困難的改進途徑；在比較幾種優化方法的基礎上，針對新一代沖壓式導彈的特點，提出了一體化設計的模式? ?分步優化模式，進行了整體式火箭沖壓發動機反艦導彈總體參數的一體化設計。
分享友人
分享到 Line

分享到臉書