空對面火箭 的英文怎麼說

中文拼音 [kōngduìmiànhuǒjiàn]
空對面火箭 英文
air-to-surface rocket
  • 空 : 空Ⅰ形容詞（不包含什麼; 裏面沒有東西或沒有內容; 不切實際的） empty; hollow; void Ⅱ名詞1 （天空） s...
  • 對 : Ⅰ動詞1 （回答） answer; reply 2 （對待; 對付） treat; cope with; counter 3 （朝; 向; 面對） be tr...
  • 面 : Ⅰ名詞1 （頭的前部; 臉） face 2 （物體的表面） surface; top 3 （外露的一層或正面） outside; the ri...
  • 火 : fire
  • 箭 : 名詞（古代兵器） arrow
  • 火箭 : [航空] rocket; fire arrow; bird
  1. The remote sensing refers to air to ground one, namely from different working platform far away the ground ( for example gao ta, balloon, airplane, rocket, the artificial earth satellite, spaceship, aerospace craft and so on ), through the sensor, exploring the information ( radiation ) to the earth ' s surface electromagnetic wave, and after the information transmission, processes, estimation and analysis, it can be regarded as a kind of comprehensive technology of surveying and monitoring earth ' s resources and its environment

    摘要遙感是指空對地的遙感，即從遠離地面的不同工作平臺上（如高塔、氣球、飛機、火箭、人造地球衛星、宇宙飛船、航天飛機等）通過傳感器，對地球表面的電磁波（輻射）信息進行探測，並經信息的傳輸、處理和判讀分析，對地球的資源與環境進行探測和監測的綜合性技術。
  2. The influence of double - push accelerated velocity, spin - rate regularity and unfolding fins on air rocket dispersion and the mechanism of decreasing of air rocket dispersion are also studied respectively

    分別研究了雙推力加速度，轉速規律和尾翼延時張開，對地面火箭彈和航空火箭彈散布的影響，以及減小航空火箭彈散布的機理。
  3. As far as the system observation for accuracy evaluation of carrier rocket is concerned, there may exist different types of observed data and priors. heterogeneous information means that the different information describing the different characteristics of the same object. since all of the information is relevant to the same object, the fusion is possible. it is a key problem that how to fuse the heterogeneous information to obtain the better evaluation result. therefore, the different heterogeneous information and data is thoroughly studied, moreover, the mathematical description for information fusion of different parameter priors and data is constructed in this paper. based on their relationship between different parameters, indirect prior and observation data is transformed into prior in impact point observation space, which is fused with original prior by weight determined by maximum entropy rule to obtain the mixed posterior distribution. therefore, the test results can be given by combining posterior distribution and impact error observed data. then its application on evaluating guidance systematic error is elaborated as it applies trajectory tracking data, test value of coefficients of guidance instrumentation systematic error, impact point observation data and prior. especially, the advantage of this method lies in its application in case that guidance instrumentation systematic error may not be computed precisely. finally a detailed example on evaluation of carrier rocket is given to verify the theory

    為充分利用運載火箭觀測中的不同觀測空間和過程的信息來進行精度評估，針對該背景建立了異質先驗融合的數學描述.研究了飛行試驗中不同觀測空間和過程的異質先驗信息和數據，基於不同觀測過程的解析關系，將間接過程的先驗和觀測數據算出的后驗分佈轉換成落點觀測空間上的先驗，與原落點的先驗進行了最大熵加權融合，得到混合后驗分佈，從而結合落點觀測數據給出評定結果.在無法解算出精確的制導工具誤差系數的情況下，這種方法充分利用了彈道跟蹤數據、工具誤差系數的地面測試先驗值、落點先驗及落點數據，穩健性更好，準確性更高
  4. For the research requirement of the high g - load mobile missile srm, the work process of solid rocket motor under lateral overload is investigated by the use of theoretical analysis and numerical simulation methods involving the calculation of internal ballistics, the simulation of flow field and the analysis of structural integrity

    本文以高速機動防空導彈固體發動機研製需求為背景，採用理論分析和數值模擬方法，從內彈道計算、內流場模擬、結構完整性分析等幾個方面對橫向過載作用下固體火箭發動機工作過程進行了研究。
  5. According to the definition and expression of the thrust, as well as the condition derived from them, a method of solid rocket ramjet thrust determination and its program are provided on the basis of engine ground simulation test

    本文以西北工業大學固體火箭沖壓發動機直連式試車臺為研究對象，探討固體火箭沖壓發動機地面試驗技術。首先，從推力的定義出發，建立了試驗中來流空氣流量、燃料流量與固體火箭沖壓發動機推力之關系。
  6. It is shown that when the exit area of secondary nozzle and the fuel / oxidizer ratio is fixed, the increase of mass flow rate of secondary flow lead to the decrease of velocity of mixed flow, and increase of total mass flow rate. the synthetical result of these two phenomenon cause the increase of thrust of rocket ejector, but the increasing magnitude is relatively small, indicating that these is no necessary to claim large bypass ratio in rocket ejector design. in the comparison between two configurations, the typical one has better performance, indicating the importance of pressure ratio

    結果表明：在固定二次噴管出口面積和氧燃比的條件下，二次流（引射空氣流）流量的增加引起混合氣體出口速度的下降和總流量的增加，二者綜合作用使發動機推力增加，但增幅不大，表明在設計發動機結構和工作參數時，不必過分追求大的引射系數；兩種結構的性能對比分析表明了增壓比對引射火箭性能的提高具有重要意義；對引射火箭的熱力循環分析同樣表明，增壓比對于提高發動機性能非常關鍵。
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