飛行試驗導彈 的英文怎麼說

中文拼音 [fēihángshìyàndǎodàn]
飛行試驗導彈 英文
flight missile
  • 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
  • 導 : 動詞1. （引導） lead; guide 2. （傳導） transmit; conduct 3. （開導） instruct; teach; give guidance to
  • 彈 : 彈名詞1. （彈子; 小球形的東西） ball; pellet 2. （內裝爆炸物, 具有破壞和殺傷能力的東西） bullet; bomb
  • 飛行 : flight; flying; aviate; voyage; volitate; hop
  • 試驗 : trial; experiment; test
  • 導彈 : guided missile
  1. 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
  2. Firstly, this paper summarizes modern weaponry stealth technology at home and abroad, and lays special emphasis on analyzing stealth problem of cruise missile ’ s guidance head cover, aerocraft radar canopy and other privileged sites. secondly it makes a research on related theories of transparent metallic mesh that applied to missile ’ s guidance head cover and aerocraft radar canopy, and deduces relational expression between transparent metallic mesh structural parameters and radar wave - shielding efficiency, infrared transmitting. we use laser direct writing technique to fabricate a metallic mesh ( dimension : 70mm 70mm ; line width : 5 m ; period : 350 m ) on glass surface, then do experiment to test radar wave - shielding of metallic mesh via radar transmitting and receiving device

    本文首先綜述了國內外現代武器系統隱身技術方法;重點對巡航導彈導引頭罩和飛機雷達艙罩等特殊部位的隱身問題進行了研究，研究了金屬網柵用於導彈頭罩和飛機雷達艙罩隱身的相關理論，推導了金屬網柵結構參數對雷達波屏蔽效率和透紅外關系式;用激光直寫工藝，在玻璃表面上製作了一塊面積為70mm 70mm ，線寬為5 m ，線周期為350 m的金屬網柵;在實驗室里用雷達發射和接收裝置測試了網柵對雷達波的屏蔽實驗;認為利用金屬網柵技術對雷達波具有一定的屏蔽作用，而且不影響精確制導的紅外線高效透過。
  3. By simulation of this autopilot on standard state point and special state points, this robust control system ' s high - speed response ability and good robust stability is validated. under this autopilot ' s control, the btt missile can fly stably along many trajectories in a large airspace. 3

    通過對所設計的自動駕駛儀在標稱點和給定特徵點進行模擬試驗，驗證了所設計的魯棒控制系統能快速跟蹤指令信號，並具有較好的魯棒穩定性，能控制btt導彈在大空域內沿多條彈道穩定飛行。
  4. The thaad program began flight testing in november 2005 at white sands missile range ( wsmr ), nm

    薩德系統開始飛行試驗是在2005年的11月，當時是在白沙導彈靶場。
  5. Three axis optical tracking test table is a kind of powerful instrument used to reproduce the flying posture of flying weapons in laboratory. the test table, together with equipment producing target, simulates the attacked target and flying missile, which can really simulate the various flying postures in space and dynamic characteristics. thus, the performance of sensors, control system and actuator and so on can be tested and evaluated, which provides various reference bases for developing, improving and redesigning flying weapons

    三軸光學跟蹤試驗轉臺是一種在實驗室條件下復現飛行器或導彈在空中飛行姿態半實物模擬的有力工具，它和目標發生裝置組合在一起模擬導彈跟蹤目標的過程，可以真實地模擬出導彈等飛行器在空間的各種姿態和動力學特性，從而對其傳感器件、控制系統和執行機構等硬體設備的性能加以測試和評價，為飛行器的研製、改進和再設計提供各種參考依據。
  6. This thesis ’ research goal is carrying on the simulation using the view simulation technology to the missile launch process, so we can both simulate the missile ’ s flight trajectory and blast effect real time, and reappear the entire testing process after experiment

    本文的研究目的就是利用視景模擬技術對導彈的發射過程進行模擬，做到既可以實時地監控導彈的飛行狀態，又可以在試后直觀地重現整個試驗過程。
  7. 4. designing and realizing a missile testing and training view simulation system, that can simulate the flight trajectory real time and reappear the entire testing process after experiment. at last, this thesis provides the summarization of the work and the content of the future research

    4 、設計並實現了一個導彈試驗訓練視景模擬系統，既可以實時的模擬導彈的飛行狀態，又可以在試驗后直觀地重現整個試驗過程，便於分析試驗結果和數據。
  8. Flight reliability test method study of cannon launched guided projectile

    炮射導彈飛行可靠性試驗法研究
  9. As an important part of hardware - in - the - loop simulation equipments, advanced ehsls can provide data needed for new types of missiles and aircrafts " design. as a typical force servo system, ehsls can apply various load on the rudder during the experiments

    作為地面半實物模擬的主要設備，高性能的電液伺服加載設備為新型導彈等飛行器的設計、應用提供性能實驗數據，為新技術的推廣提供可靠的試驗資料。
  10. In this paper which was in the background of some model antitank missle, adopting maximum likelihood identification method estimated the aerodynamic parameters of the missle, with using flight datas

    本文以某型反坦克導彈為背景，利用導彈飛行試驗數據，應用最大似然遞推演算法估算了該導彈的氣動力參數。
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