飛機高度計 的英文怎麼說

中文拼音 [fēijīgāodùjì]
飛機高度計 英文
airborne altimeter
  • 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
  • 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...
  • 度 : 度動詞[書面語] （推測; 估計） surmise; estimate
  • 計 : Ⅰ動詞1 （計算） count; compute; calculate; number 2 （設想; 打算） plan; plot Ⅱ名詞1 （測量或計算...
  • 飛機 : airplane; plane; aeroplane; kite; bird; aircraft
  • 高度 : altitudeheightelevation
  1. 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。
  2. The method of wing shape optimization of space shutlle has been developed with penalty function approach in which the objective function is the mass of the wing and the constraints are the hypersonic re - entry flight cross range, lift / drag ratio, and subsonic flight lift / drag ratio, the margin of the longitudial static stability and the magnitude of the horizontal landing speed etc

    摘要介紹了在滿足高超音速再入橫向機動航程，高超音速再入飛行時的升阻比，亞音速進場飛行時的升阻比，縱向靜穩定性裕度和水平著陸速度等飛行性能設計要求下，用罰函數法尋求使航天飛機機翼質量為最小的外形優化方法並給出了算例。
  3. Nowadays with the booming development of microelectronic technique, the functions of the components of machinery, electricity, magnetism, optics, acoustics and thermotics have been improved rapidly. and the micromation of components, the integration of electronic equipments, the worse working environment, the increasing requirement and emi, all of these make the structural design of electronic equipments more and more important

    在微電子學高度發展的今天，促使機、電、磁、光、聲和熱等元器件功能飛速提高，隨著元器件微型化，電子設備趨向集成化，再加上一些日趨惡劣的工作環境，各種使用要求的提高，空間電磁環境的干擾，以及由於裝填密度高，產生的內在干擾等，使得電子設備的結構設計變得越來越重要。
  4. . it can be used as a part of aerometric measurement system in aerocrafts, sending dates to central computer by com port. furthermore, with lcd added on, it can be applied as a ground altimete

    該高度表既可作為飛機大氣數據系統的一部分，通過串口向大氣數據計算機傳送數據;也可加上lcd顯示作為地面測高儀表。
  5. 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。
  6. Second, by computing the trajectory of the missile and the method of analyzing cep, influences that the fighter ' s height, speed, pitch angle, the deflection angle between fighter and target, and the target moving characters make on the times of fighter attack and missile launch are deeply developed. third, by relating the motion of the missile and the fighter, the influences that fighter ' s dive angle and the deflection angle between fighter and target make on the attack field of the fighter are discussed in this paper when the fighter perform vertical and horizontal attack. criterion of attack effect is proposed focusing on attack time of the fighter, trajectory of the missile and destruction probability to the target

    本文主要完成了以下幾個方面的工作：對導彈可發射區和飛機可攻擊區進行建模，通過對導彈彈道的模擬計算，並運用典型的圓概率偏差精度分析方法，詳細討論了飛機實施攻擊時，飛機的飛行高度h 、速度v 、俯仰角、與目標的偏離角_ x及目標運動特性等對飛機攻擊時機和導彈發射時機的影響；因此，將飛機和導彈結合起來，詳細研究了飛機在垂直平面和水平平面內實施攻擊時，飛機俯沖角和與目標的偏離角_ x對飛機的攻擊范圍的影響；以飛機實施攻擊的時間t 、彈道特性和對目標的殺傷概率p來評判對地攻擊的效果；最後給出典型算例，通過對空地攻擊過程的模擬實現，對飛機飛行過載提出要求。
  7. Focusing on the flight control computer system of some type of airplane, this paper first analyzes the advantage and disadvantage of the structures of many kinds of fault tolerant flight control computer systems and their ability in tolerating fault, followed by summarizing the key design technology. the dual similar redundancy fault tolerant computer system is brought forward as the design scheme for the required flight control computer. also brought forward is the particular system design

    本文以某型號飛機飛控計算機系統為研究對象，首先分析了各種類型容錯飛控計算機體系結構的優缺點及容錯能力，總結了容錯計算機系統設計的關鍵技術，然後提出了二模相似余度容錯飛控計算機系統設計方案，詳細設計了以motorola公司生產的先進powerpc740微處理器為核心處理器、以高性能的國際標準化通用vme總線為內總線的交叉通道通信容錯計算機系統。
  8. Most countries in the world attach importance to the use of long - time uav ( unmanned aerial vehicle ) in the military. the kernel question of long - time uav is how to improve the reliability of flight control computer. the research of how to improve the reliability of flight control computer has became more and more important today

    長航時無人機的重要性尤其在軍事上已經得到國內外的高度重視，其核心飛行控制計算機（以下簡稱「飛控計算機」 ）的可靠性問題變的日益突出，對其容錯研究成為當今的熱點。
  9. In addition, airway winds, which are essentially grid - point wind and temperature data over the south china sea for 15 flight levels between 10, 000 and 43, 000 ft, are disseminated to the radar data processing and display system ( rdpds ) of the cad for calculation of the expected arrival time of aircraft at check points

    除此之外，氣象數據處理系統將飛機航道風的數據傳送至民航處的雷達數據處理及顯示系統，這些數據是風和溫度的網格點值，其水平范圍覆蓋南海，垂直范圍是由10 ， 000至43 ， 000尺之間的15個飛行高度；以上資料可用來計算航機抵達各定位點的時間。
  10. At fixed time intervals, the gts data are decoded by the hko main computer and quality control checks are applied. objective analyses are then carried out for data at various standard pressure levels to produce grid point values. charts showing flight level winds, temperatures and other information are made available at the airport meteorological office ( amo ) for the provision of flight documentation and airway winds

    天文臺的主電腦定時對接收到的資料進行譯碼及質量控制檢查，跟著對各個標準氣壓層面的資料進行客觀分析，計出各網格點的數值，從而製作各巡航高度的風、溫度及其他資料的天氣圖，讓機場氣象所用來編制飛行氣象文件和航道風。
  11. In addition, airway winds, which are essentially grid - point wind and temperature data over the south china sea for 15 flight levels between 10, 000 and 43, 000 ft, are disseminated to the radar data processing and display system rdpds of the cad for calculation of the expected arrival time of aircraft at check points

    除此之外，氣象數據處理系統將飛機航道風的數據傳送至民航處的雷達數據處理及顯示系統，這些數據是風和溫度的網格點值，其水平范圍覆蓋南海，垂直范圍是由10 ， 000至43 ， 000尺之間的15個飛行高度以上資料可用來計算航機抵達各定位點的時間。
  12. At fixed time intervals, the gts data are decoded by the hko main computer and quality control checks are applied. objective analyses are then carried out for data at various standard pressure levels to produce grid point values. charts showing flight level winds, temperatures and other information are made available at the airport meteorological office for the provision of flight documentation and airway winds

    天文臺的主電腦定時對接收到的資料進行譯碼及質量控制檢查，跟著對各個標準氣壓層面的資料進行客觀分析，計出各網格點的數值，從而製作各巡航高度的風溫度及其他資料的天氣圖，讓機場氣象所用來編制飛行氣象文件和航道風。
  13. The control laws of longitudinal and lateral - directional autopilot modes are designed based on root locus theory. the control laws of altitude holding mode, heading holding mode, auto - throttle control and air speed holding mode are designed as well

    研究了無人機的飛行控制技術，利用根軌跡法設計了無人機的縱向與側向姿態保持控制律，設計了高度保持、航向保持、自動油門及速度保持控制律。
  14. As the cumulate error, inertial navigation system ca n ' t provide perfect position and navigation for the autonomous underwater vehicles ( auv ) in unstructured, complex and instable ocean in a long time. the application of terrain - aided navigation techniques to the updating of an inertia navigation system has been investigated

    慣性導航系統是實現水下導航的一種重要方法，但慣性導航存在累計誤差，為了修正慣性導航的累積誤差，提高導航精度，本文將飛機、導彈等所使用的地形輔助導航系統，應用到水下航行器上，成功地滿足了自主水下航行器的導航需求。
  15. According to the requirements of propeller aerocraft model test in wind tunnel, specifications of the driven motor is presented by aerodynamic analysis, and a short - term operated high power density three - phase induction motor is developed with reasonably designing the motor, such as electromagnetism load, heat checkout and high - efficiency heat exchanger

    摘要針對螺旋槳飛機模型帶動力風洞實驗要求，通過氣動性能分析提出驅動電機的技術指標，在滿足結構約束的條件下，通過合理設計電機的電磁負荷、校核發熱、採用高效冷卻裝置等，研製出短時工作制高功率密度三相異步電機。
  16. The following are the main works : the maximum likelihood estimator ( mle ) was studied in detail, and the ocean return curve based on the sub - optimal maximum likelihood estimator ( smle ) was first obtained in china through the airborne flight experiment

    （ 2 ）深入研究了星載雷達高度計最大似然跟蹤演算法，並完成了基於準最大似然演算法的高度計跟蹤器的研製，通過機載校飛實驗，在國內第一次獲得了基於準最大似然演算法的海洋回波跟蹤曲線。
  17. The fdps processes the flight plan data from aeronautical messages and prints out flight progress strips automatically for use by air traffic controllers to updatemonitor the aircraft flight profile, such as flight route, estimated time of departurearrival, flight level, expected times at reporting points, cruising speed, etc

    飛行數據處理系統可作航機飛行計劃的數據處理，和即時印出飛行進度紙條，供航空交通管制員用以更新和監察航機的飛行狀況，例如航道、預計著陸起飛時間、飛行高度、位置報告的預計時間、飛行速度等。
  18. 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。
  19. The design of modem airplane is a kind of large and complex system engineering that includes various specialties, and the newly technical achievement of the various specialties should be utilized multipurposly only when the traditional engineering specialty and the special engineering specialty should be synthesized and managed effectively, the design quality will be improved insuring the airplane not only may meet the requirement of technical and tactical aims, but also has the well economy and tactical perfectness, so as to meet the requirement of anny with lower maintenance expenses

    現代飛機設計是一項十分龐大、眾多學科專業高度交互的系統工程，要綜合利用眾多學科的最新技術成果。只有把傳統的工程專業與特殊的工程專業予以綜合，實施行之有效的現代化管理，才能提高飛機的設計質量，保證設計出的飛機既滿足戰術技術指標的要求，又有良好的經濟性和戰備完好性，實現以較低的維修保障費用滿足部隊的使用要求。
  20. The altimeter used in most airplanes is a kind of barometer, which like barometers found in ordinary homes, is a measuring instrument for air pressure

    （許多飛機上使用高度計是氣壓計的一種。這種氣壓計就象普遍家庭使用的晴雨表一樣是測量空氣壓力的儀器。 ）
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