火箭最優化 的英文怎麼說
中文拼音 [huǒjiànzuìyōuhuà]
火箭最優化
英文
rocket optimization-
In this thesis, based on pershing ii surface to surface missile, a new kind of ballistic missile was designed with an additional rocket engine, which can be ignited twice. firstly, aerodynamic computational models of missile body and warhead which reentry with supersonic are built according to the task requirements ; secondly, the propulsion system model of missile is built whose first two stages are solid rocket engines and the third stage is liquid - solid combined rocket engine. the nozzle and the shape of the engine are designed to meet the needs of the populsion project ; thirdly, the trajectory model of the mass point is built and a wavy trajectory is designed & optimized ; finally, the ability of a missile ' s breaking through defence is analyzed
以美國潘興導彈為原型，增加可兩次點火的末級發動機，改裝成具有跳躍能力的地地彈道導彈；首先，根據任務需求，建立了導彈的氣動模型，並建立了彈頭再入時高超聲速氣動模型；其次，建立了導彈推進系統模型，前兩級採用了固體火箭發動機，第三級採用了固?液組合火箭發動機，並在總體方案要求下，對發動機噴管和外形進行了設計；第三部分，建立了導彈質點彈道模型，設計了一條跳躍式彈道，並對跳躍式彈道進行了優化設計；最後，對導彈進行了突防能力分析，從分析的結果可以看出，跳躍式彈道的突防能力比常規的拋物線彈道要強。It has been maked for immediate and statistical analysis that the calculation about the work order parameter of the base - bleed - rocket is calculated in the taguchi method, its influencing trend is bring out in the open, the theoretical base is settled for confirming the greatest combination about the work order parameter of the base - bleed - rocket. the multi - objectile optimal design model is established that the indexes have been taked into account first and synthetically, such as physical parameter range lethality power strength and flight stability and so on, the program is compiled and the example is calculated. the true worth of the theoretical work in this paper is validated by flight experimentation of 130mm hybrid base - bleed - rocket extended - range principium projectile
本文進行了底排?火箭復合增程彈工作時序參數正交試驗設計的直觀分析與方差分析，揭示了每個參數對射程計算的影響趨勢，為進一步確定底排?火箭工作時序參數值的最佳匹配組合奠定了理論基礎；建立了底排?火箭復合增程彈多目標優化設計模型，該模型首次綜合考慮了底排?火箭復合增程彈的結構特徵參量、結構強度性能、飛行穩定性、威力性能和射程指標，編制了相應的分析程序，進行了算例計算；完成了130mm底排?火箭復合增程原理樣彈的結構設計與飛行試驗，其試驗結果驗證了本文理論研究工作的實際應用價值。The conclusion that the optimal secondary nozzle exit area generating the maximum thrust agrees well with the numerical simulation, indicating that the exit area of secondary nozzle should be optimized according to structure and flow parameters during design
表明在引射火箭設計時，應結合引射火箭的結構和流動參數對二次噴管出口面積進行優化設計，以達到最佳推力性能。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。Third, on the basis hypothesis of mean gravitation, optimal control functional of the launch vehicle equations of state are set up by optimal control theory. the optimal control results of launch vehicle are worked out. this control method of automatic start is inferred, which can satisfy the terminal condition of satellite trajectories
3 、通過引入「平均引力」的簡化假設，利用最優控制理論，建立運載火箭的最優控制泛函，得出運載火箭的最優控制問題的解，推導出了可自動起步，滿足衛星軌道終端條件的迭代制導方程。In this thesis, based on the available research of this field, the method to resolve the constraint conditions of the optimization problems has been improved and the parametric sensitivity analysis of the trajectory optimization has been completed. guided by object - oriented method and considering the mission needs and user requirements adequately, the hierarchical structure of the system is analyzed. the uml ( unified modeling language ) is also applied to establish the simulation systems framework
本文在已有研究的基礎上，對優化問題的約束處理方法進行了改進，並完成了軌跡優化問題的靈敏度分析，在面向對象方法學的指導下，根據系統的優化模型和優化策略，分析了系統的層次結構，並基於uml建立了模擬系統框架，運用泛型技術進行程序設計，最終實現了運載火箭性能優化軟體。分享友人