飛行試驗研究 的英文怎麼說

中文拼音 [fēihángshìyànyánjiū]
飛行試驗研究 英文
flight investigation
  • 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...
  • 試 : 名詞（古代占卜用的器具） astrolabe
  • 驗 : 動詞1. （察看; 查考） examine; check; test 2. （產生預期的效果） prove effective; produce the expected result
  • 研 : 研同 「硯」
  • 究 : Ⅰ動詞（仔細推求; 追查） study carefully; go into; investigate Ⅱ副詞[書面語] （到底; 究竟） actually; really; after all
  • 飛行 : flight; flying; aviate; voyage; volitate; hop
  • 試驗 : trial; experiment; test
  • 研究 : 1. （探求） study; research 2. （考慮或商討） consider; discuss; deliberate
  1. The results are summarized as follows. solid culture. in preliminary experiments, broomcorn millets ( yielded by the crop panicum miliaceum l. ) and foxtail millets ( yielded by the crop setaria italica l. ) were determined as optimal substrate for solid culture of p. delphacis

    主要研究內容和結果分述如下：固體培養篩選確定了以黍米（ panicummiliaceuml . ，俗稱黃米）和粟米（ setariaitalical . ，俗稱小米）為最適固體培養基質，對飛虱蟲癘霉進行了成功的繁殖試驗。
  2. Flight test is one of the four measures of the aeronautics research, used in the whole proceeding of research, design, appraisement, production and usage. and it is the most direct, the most accurate, the ultimo test measures

    飛行試驗是航空研究的四大技術手段之一，它貫穿于研究、設計、鑒定、生產和使用的全過程，是最直接、最準確、最終的試驗手段。
  3. This paper analyses the applied characteristic of phase - locked loops ( pll ) for the forward motion compensation technology of lmk aerial survey camera. according to the analysis, a new style pcb is produced. the realization by software for the forward motion compensation is discussed in this paper, which is realized by the ti prduction tms320f240

    在對lmk航空攝影機像移補償控制系統的再設計工作中，本人設計出了新的補償電路線路板，並進行了幾項典型的實驗研究和前向運動補償效果評價，經過外場飛行試驗，進一步證明了該設計的可靠性、可行性、實用性。
  4. Through the exploding experiment of discrete rod warheads at shooting range, the flight performance of the rods about discrete rod warheads is researched

    摘要通過離散桿戰斗部靶場靜爆試驗，對離散桿式破片的飛行性能進行了試驗研究。
  5. 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。
  6. Research on ac500 aircraft spin flight test

    500飛機尾旋特性飛行試驗研究
  7. Flight test investigation of helicopter vortex - ring state boundary

    直升機渦環狀態邊界的飛行試驗研究
  8. 7 the investigation of the thermoeconomic performance of an existing facility used for thermal fatigue experiments of aircraft canopy reveals the possibility and practicability of taking measures to improve it significantly. a piping system with alternative variation of flow temperature exists in this facility

    對一現行的飛機座艙蓋熱疲勞試驗系統? ?即流體溫度升降交替變化的管路系統，進行了熱經濟行為的研究，揭示出它具有潛在與可行的重大改進方向和途徑。
  9. 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
  10. For researching the flight test techniques of thrust vector controlled aircraft, dynamic models of thrust vector controlled aircraft were established, four post stall maneuver control laws were designed with the dynamic inverse method, tested and investigated according to a standard evaluation maneuver set ( stems )

    摘要為研究推力矢量飛機的試飛技術，建立了推力矢量飛機的動力學模型，用動態逆方法設計了4種過失速機動控制律，並在地面飛行模擬器上參考標準評估機動動作集（ stems ）進行了飛行模擬試驗研究。
  11. In this paper, the vacuum thermo - cycling effects and vacuum ultraviolet effects on space inflatable structural materials were analyzed based on a thorough survey over the studies done through flight tests, ground simulation experiments and theoretical research. the main contents of this thesis are as follows : the performance damage effects of thermo - cycling on space inflatable structural fabric carbon fiber reinforced epoxy laminates ( cf / ep ), aluminized kapton ( al / kapton ) films which used as reflector of space inflatable antenna were investigated by a temperature range of - 120 120 with the vacuum degree 10 - 5 pa which conducted with space environment ground - based simulation facility

    本文在對國內外飛行試驗、地面模擬試驗以及理論研究等所取得的成果調研的基礎上，針對空間充氣結構材料進行地面模擬真空熱循環與真空紫外輻照的研究工作:利用真空熱循環地面模擬試驗機研究了真空環境（ 10 - 5pa ）中- 120 120的熱循環條件下空間充氣支撐結構織物碳纖維增強環氧樹脂（ cf / ep ）層合材料、空間充氣展開天線反射面鍍鋁聚酰亞胺（ al / kapton ）薄膜的空間環境效應。
  12. Abstract : this paper summarizes a series of tests and inve stigations on general layout, const ruction diversion, flood disposal, navigation, river closure, form of gate opening s ection, pattern of energy dissipation and scouring under sluice carried out for f eilaixia proj ect by the scientific research institute of prwrc during the period from 1983 to 1998 and presents their major results

    文摘:綜合闡述了珠江水利委員會科學研究所從1983 ? 1998年間對飛來峽水利樞紐的整體布置、施工導流、泄洪、通航、截流、閘孔斷面形式、閘下消能形式、閘下沖刷等所進行的一系列試驗和研究工作，並介紹主要試驗研究成果。
  13. Along with development of tiltrotor vehicle ’ s research some theoretical productions have been appeared in some project ( aerodynamic behavior of rotor, kinetic behavior of rotor, rotor / wing aerodynamic interactions, etc. ). in order to carry on further research and experimentation of these project, national - defence science and technology helicopter rotor kinetic lab of our school begin to building tiltrotor model bench. base on need of this bench, this paper study / design pitch control system on it

    隨著對傾轉旋翼飛行器的深入研究，傾轉旋翼的氣動特性、動力學特性、旋翼/機身間的氣動干擾等課題方面已有一定的理論成果出現。為了對這些課題進行深入研究和試驗驗證，我校直升機旋翼動力學國防科技重點實驗室著手建造了傾轉旋翼模型實驗臺。
  14. There are great differences between ground test of a flight vehicle ' s aerodynamics and that of a dual - mode scramjet when ground test facilities are used to do experiments on a dual - mode scramjet engine, the components of incoming flow and its parameters, including total pressure, total temperature ( or total enthalpy ) and velocity must be simulated. at the same time, since the fuel ' s resident time within a combustor is very short, on the order of one millisecond, it is difficult to measure the flow - fields

    進行雙模態沖壓發動機地面試驗研究時，必須要求試驗設備能模擬實際飛行條件下來流氣體的組分、總壓、總溫（或總焓）以及來流氣體的流動速度；同時由於燃料在燃燒室內駐留的時間很短，一般為毫秒量級，從而使流場物理量的測定顯得非常困難。
  15. Based on this, also described is the measurement method and request of the main antenna parameters, and carrying on the tests of antenna model, real antenna test and the flight - test, and studying and analyzing the data of all tests in the end

    在此基礎上，還闡述了天線主要參數測試方法和相關要求，並進行了隱蔽式天線縮比模型的地面測試試驗，全尺寸天線地面試驗及飛行試驗，最後對試驗數據進行了研究和分析。
  16. Study on wind tunnel testing of aerodynamic properties of highspeed landslide flying

    高速滑坡飛行氣動特性的風洞試驗研究
  17. The paper conducts flyer sensitivity testing of 3 explosives and gains some good conclusions

    本文進行了三種炸藥的飛片感度試驗研究，得到一些有益的結論。
  18. The subject of airplane power supply ground experiments test system come from china aviation experiment academe. this system is designed for the ground measurement of airplane power supply system to check whether these new powers have good characters, and offer basis for system examine and repair

    「飛機電源地面試驗測試系統」任務來源於中國飛行試驗研究院，該系統是為飛機電源系統的地面測試而設計的，其目的在於測試飛機電源系統的供電品質是否達到規定要求，從而為電源系統的檢修提供依據。
  19. This thesis targets to research the technique of engine vibration mortroing when performing flight test and lays the foundation for the engine condition mortroing and fault diagnosis in the future

    本文旨在根據發動機飛行試驗的要求，研究軍用航空發動機振動監測方法，為發動機狀態監控與故障診斷提供技術基礎。
  20. Research on fault diagnosis and assistant decision system for manned spaceship flying test

    飛船飛行試驗中故障診斷與輔助決策系統研究
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