飛機測高法 的英文怎麼說

中文拼音 [fēijīcègāofǎ]
飛機測高法 英文
aircraft altimetry
  • 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...
  • 機 : machineengine
  • 測 : 動詞1. （測量） survey; fathom; measure 2. （測度; 推測） conjecture; infer
  • 高 : Ⅰ形容詞1 （從下向上距離大; 離地面遠） tall; high 2 （在一般標準或平均程度之上; 等級在上的） above...
  • 法 : Ⅰ名詞1 （由國家制定或認可的行為規則的總稱） law 2 （方法; 方式） way; method; mode; means 3 （標...
  • 飛機 : airplane; plane; aeroplane; kite; bird; aircraft
  1. To sum up, tested and validated by data sets of shenzhou iv unmanned spacecraft and precise orbit ephemeris, the algorithms presented in the thesis can improve orbit accuracy and reduce random noise considerablely. derived conclusions have important value for reference, and lay the firm technological foundation for future applications

    總之，經過神舟四號飛船實測數據計算和精密星歷檢驗，表明本文提出的各種定軌方法可以較好的提高定軌精度，減少隨機噪聲，所得出的結論對于實際應用具有重要的參考價值，並為將來的應用奠定了堅實的技術基礎。
  2. The intelligent mine will be the most important weapon system to defend arming helicopter hedgehopping in future war. passive acoustic detection technology is the key technology. with the researching of the national defence pre - researching project which is the research of acoustics compound fuse of anti - helicopter intelligent mine, this paper presents two type of acoustic localization algorithm, emphasizes the discussion of algorithm and presicion of space acoustic localization with sensors at different height in detail and compares them

    智能雷彈是防禦超低空飛行的武裝直升機的重要武器系統，而被動聲探測技術是其關鍵技術，本文結合「十?五」國防預研項目「反直升機智能雷彈聲復合引信技術」的研究，對兩種空間目標聲定位演算法進行了深入分析，重點討論了空間高低陣定位演算法，分析了定位精度。
  3. Based on the investigation and research, the paper gives a testing method, which measures the taking off and landing distance of airplanes with the laser locating system for airplanes trace. and by way of the field measuring on plateau airports, we have got the integrated modifying coefficients of three kinds of airplanestaking off and landing running distance such as h6. all of these provide scientific basis for the runway length design of the plateau airport

    在調研論證的基礎上，提出了利用《飛機起落航跡激光定位系統》測定飛機起飛著陸滑跑距離的測試方法，並通過高原機場實地測試，得出了三種飛機在高原機場上起飛著陸滑跑距離的綜合修正系數值，為高原機場跑道長度設計提供了可靠的理論依據。
  4. Three - dimensional high - density space / time soundings serve as the main body of data consisting of 3 - hr interval doppler probings, 10 - 30 min rainfall intensity, surface raindrop sizes sampling and gps - guided flight cloud physics detections with output taken at 2 - sec and 200 - m intervals. and specific systems associated therewith are developed for multiple - way communication and data collection and storage, a platform for analysis, retrieval softwares for dominant items and multi - scale cloud models - all constitute a system of techniques for meso to microscale observations and analysis. 2 ) atmospheric water resource and macroscopic rainfall properties in dry periods of spring and autumn of the target region

    以加密觀測的多普勒雷達、 3小時探空、 10 30分鐘雨強、地面雨滴譜等間隔取樣及在gps引導下的飛機雲物理探測等獲取的三維高時空密度的綜合探測為主體；配合專項設計開發的多路通訊採集存貯系統、多類信息的分析處理平臺、主要觀測項目的分析反演軟體，結合多尺度雲系模式，綜合構成層狀雲系中微尺度探測和分析處理技術方法。
  5. In order to determination the thrust, the thrust definition and many control parameters are analyzed discussed, which mass flow rate and flight altitude are involved. it is difficult to measure the flight thrust of solid rocket ramjet directly

    通過討論高空飛行推力與地面可測試參數的關系，得到了固體火箭沖壓發動機高空飛行狀態下推力折算方法，並開發相應的計算程序。
  6. Unlike aircraft flights, measurement of meteorological parameters using radiosonde could reach an altitude of 30, 000 metres before the balloon burst

    探空氣球可升至30公里高才爆裂，相對于用飛機探測的方法，無線電探空儀可探測更高層的大氣資料。
  7. The oil loading system and the management of oil bin in the oil - bin area is intensive and the measurement method is under - developed at present time. in order to resolve this problem and realize the automatic management, this thesis analyzed the demands of the system, and then integrated the optical fiber sensing technology, the advanced computer technologies of hardware and software, the technologies of intelligent instrument, auto - control and communication ; finally a distributed and intelligent monitoring system of the automatic oil - loading system was developed. the thesis contains hardware design, software design and communication design

    為了解決罐區裝車手動付油與油罐手工檢尺測量勞動強度大，方法落後以及油庫安全性要求非常高的問題，提高油庫自動化和信息化管理水平，本文從監控系統用戶需求與功能分析入手，結合當前飛速發展的光纖傳感技術、計算機軟體、硬體技術、智能儀表技術、自動控制技術和通訊技術，開發了一套用於石化行業的基於光纖傳感技術的集自動付油管理及儲油液位、溫度等安全檢測功能於一體的油罐庫區自動付油管理系統。
  8. In this paper, by analyzing the measuring of instantaneous speed, it was found that the main error is come from the angular measuring error, and then the method to decrease the error is given and the measurement precision is improved greatly

    摘要通過分析柴油機飛輪瞬時轉速的測量誤差，指出角度誤差是飛輪瞬時轉速的主要誤差來源，從而提出了減少誤差的方法，提高了瞬時轉速的測量精度。
  9. Target state estimater ( tse ) is an important and indispensable part of integrated flight and fire control system ( iffcs ). this article takes the ground mobile object as the study model. it established the system state equation and observation equation from the perspective of promoting system accuracy, simplifying the calculation and facilitating the engineering realization, the tse was set up by using the kalman filtering calculation method in the wake of linearizing the observation equation to make it adapt the precondition

    目標狀態估計器是綜合飛行/火力控制系統中的一個重要組成環節，本文以地面機動目標為模型，從提高目標估計精度、簡化計算以及便於工程實現為出發點，建立目標的狀態方程及觀測方程，並對其進行線性化，利用自適應卡爾曼濾波演算法構造目標狀態估計器。
  10. In paper, reaching the aim, firstly, we have researched thorough about symbol recognition and theory understanding relative theory and technology, and basing on those theory and technology, we adopt the based global characteristic symbol recognition and engineering drawing understanding algorithm which can automatic convert the vectorgraph which doesn ’ t include the relative physical information into the vectorgraph which includes the relative physical information. secondly, researching about the 2d computer animation technology and combine the cbt system, we have presented the new path animation model which include the union path description, animation pattern and time - velocity and time ? distance parts

    為達到上述目標，本文首先對目前圖形符號識別技術進行系統的、較深入的分析，結合民航飛機原理圖特點採用基於全局特徵的符號識別演算法對原理圖進行符號處理，並以此為基礎改進了基於圖的方法和全局知識的語義分析方法相結合的原理圖理解演算法，可將無序的矢量圖轉化成高層的知識表示，為動畫製作提供素材，為后續的電路完整性檢測及動畫自動播放提供相應的知識支持。
  11. The main part and key technique of the cpa system is study : the generation of the femtosecond laser pulse is study, the modulation and maintenance of the ti : s laser is learned ; the types of the measurement for ultrashort laser pulse is generalized and the interferometric autocorrelation is expatiated ; the varieties of the stretchers is sum up and aberration - free stretcher is calculated and optimized to improve the stretching ratio ; the pulse selection is analyzed and a single pulse can be selected successful from the pulse train at a repetition rate of 82mhz ; the kinds of the amplifier in cpa system is gathered up, the eight - pass pre - amplifier and a good many effects in it is investigated. finally, the second, third and fourth - order dispersions in cpa system is analyzed systemicly, and the according means for dispersion compensation is worked out

    對cpa系統的主要環節及關鍵技術進行了研究：掌握了鈦寶石激光器的調節和維護技術，較深入地研究了飛秒激光脈沖產生的機理，其中對群速色散、自相位調制、自鎖模等問題進行了詳盡的分析；總結了超短激光脈沖的測量技術，重點研究了干涉自相關測量法；在總結展寬器類型的基礎上，對無象差展寬器進行了理論計算、優化設計，提高了展寬倍數；深入論述了脈沖列的選單問題，熟練掌握了脈沖選單技術。
  12. Simulations show that the average error of the proposed method is reduced 72 % of the traditional method

    對飛機目標角運動參數估計過程的模擬結果表明，與傳統高分辨測角方法相對比，所提方法的平均誤差降低了72 % 。
  13. 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。
  14. So, inventing a new measuring method, which is simple while installing, convenient when operating, and of higher precision and adaptability, is very important to the making and testing departments of airplanes

    因此，研究一種安裝調試簡單、操作方便、精度較高、適應能力強的測量方法和測量系統對飛機生產、研製和試驗部門顯得十分重要。
  15. Abstract : the control reconfigurable aircraft with multi - surfaces needs robust basic flight control system to support enough time for failure detection and isolation. when partial surface loses, it can keep the damaged aircraft stable. in this paper, multivariable output feedback digital control laws are designed for the control reconfigurable aircraft ( cra ). the method uses fast - sampling digital pi controllers to design digital flight control tracking system. this paper gives the way to design the controller and analyze its robustness characteristics. the simulation results indicate that the controller is very robust and the output responses are fully satisfactory

    文摘:控制可重構飛機要求其基本飛行控制系統對舵面部分缺損故障具有強的魯棒特性，在故障發生后保證飛機的穩定性，提供足夠的時間進行故障的檢測和隔離，為控制系統重構提供條件.本文採用高速采樣pi控制器設計輸出反饋跟隨系統，給出了控制器的設計方法，並分析了它對于控制舵面部分缺損故障的魯棒特性.模擬結果表明，這種控制器具有好的魯棒特性
  16. Since the western countries began the srfcs research in the eighties, theory of signal detection is used in fdi, and it was successful in some fdi functions in several types of testing aircraft. china did the srfcs research recently, but lack of the engineering fdi algorithm. because the " model based signal detection algorithm " is sensitive to the matching accuracy of the mathematics model and aircraft has prominent nonlinear aerodynamic factors, it is difficulty to upgrade the ability of fdi based on the classical signal detection theory and data fusion only

    國外自八十年代開展自修復研究，一般採用基於常規數據處理的故障檢測理論來實現飛控系統故障檢測與隔離功能，現已在幾種驗證機上取得初步成果，而國內的研究尚缺乏實用的工程演算法；同時，基於常規數據處理的故障檢測精度對被檢測對象的數學模型匹配度敏感，且飛機的氣動特性在故障情況下又具有較強的非線性特性，因此，單純依靠常規的信號處理演算法難以進一步提高故障檢測的精度。
  17. Finally, it briefly discusses the feasibility, the applying foreground and the approach with regard to the calculating method about the amount of catalyst provided in this paper by integrating the ascending - velocity field and cloud water field in the possible working section abstracted from the mm5 mesoscale model with the thickness of the ice crystal particles in nucleation layer and supercooled water quantity which is surveyed by the plane

    得出適合的催化劑引入高度等。最後，簡要討論了用mm5中尺度區域模式提取可能作業區的升速場和雲水量場，並結合飛機實測核化層冰晶粒子濃度、過冷水量等，探討了本文提出的催化劑用量計算方法的可行性，應用前景和途徑。
  18. This thesis introduces the key technique of the us military distributed information system, with focuses on algorithms about related navigation of military tactics. kalman filtering combined with least square method is proposed for the current military development stage. the method of observation result including velocity component minimizes the convergence time, improves the positioning precision and acquired satisfied experiment results, which makes the pla independence of the us high - tech equipments

    本文簡要介紹了現階段美軍在戰術信息分佈系統實現中所採用的關鍵技術，重點對戰術飛機相對導航的各種實現演算法進行了深入探討，針對我軍當前在該系統領域中的技術現狀，提出了以最小二乘法輔助卡爾曼濾波，濾波過程中觀測量加入速度分量的方法，縮短了導航濾波起始階段的收斂時間，提高了定位精度，在工程上取得了較理想的實驗數據，在一定程度上擺脫了我軍在相對導航領域對美軍先進技術裝備的依賴。
  19. This algorithm successfully estimated sonobuoy position for simulated aircraft data. the effect of aircraft - to - sonobuoy range, the frequency of measurement, and changes in altitude are also analyzed

    模擬表明，對于給定的飛行模式和飛機參數，該演算法可以成功地估計浮標的位置，並且分析了飛機與浮標的距離、測量頻率和飛行高度對定位的影響。
  20. The scramjet engine is highly integrated with the airframe of airbreathing hypersonic vehicle, which makes the performance evaluation very difficult. it ’ s urgent to develop a kind of scramjet performance evaluation method which can take full advantages of data acquired in experiments

    該發動機與高超聲速飛行器機體的高度一體化構型，導致其性能評估相對困難，迫切需要發展一套能夠充分利用試驗測量數據評估超燃沖壓發動機性能的方法。
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