飛機用高度計 的英文怎麼說

中文拼音 [fēijīyònggāodùjì]
飛機用高度計 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
  • 用 : Ⅰ動詞1 （使用） use; employ; apply 2 （多用於否定: 需要） need 3 （敬辭: 吃; 喝） eat; drink Ⅱ名...
  • 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. 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。
  5. The flight characteristics of high altitude long endurance uav are analyzed, several typical kinds of aeronautical weather are ingathered, and the vertical distributing model of large scale windfield is established, traditional numerical simulation methods of atmosphere environment are summarized. 2

    分析了高空長航時無人機的飛行特點，統計了幾種的典型航空氣象特徵，並提出大尺度風場的垂直分層型，最後總結了大氣風場的常用數值模擬方法； 2
  6. 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。
  7. 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。
  8. 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。
  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 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. 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。
  12. 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。
  13. 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。
  14. Motion control is a comprehensive subject. modern ac drive is a important embranchment in the field of motion control. however, it is difficult to rea1ize high - performance ac drive systems because induction motors are a kind of strongly - coupled nonlinear system with many variables and the torque is not easy to control. with vector control technology decoupling and torque control of ac motor are solved. the basic idea of vector control is that three - phase system is equiva1ent to two - phase system by coordinate transformation and it realizes the decoupling between field current and torque current of the stator in order to control the flux and current respectively, thus induction motor can be considered dc motor and high performance is achieved easily. with the progress of electric and electronic technology and the development of computer, high - integrated special modules and high - precision digital signal processor ( dsp ) are applied to ac drive so that vector control has been developed rapidly

    但是高性能的交流調速系統實現很困難，這是因為交流電機是多變量、強耦合的非線性系統，不易實現高性能轉矩控制。矢量控制技術則解決了交流電機解耦與轉矩控制問題，其基本思路? ?應用坐標變換將三相等效為二相，實現定子勵磁電流分量與轉矩電流分量之間的解耦，達到對交流電機磁鏈與電流分別控制的目的，交流電機等效為直流電機實現高性能調速。隨著電力電子技術的進步，計算機技術飛躍發展，高度集成的專用模塊和高精度的數字信號處理器應用於交流傳動系統中，促進矢量控制迅猛發展，日趨成熟。
  15. In this thesis, the calibration, laying and measuring error of the concentric capacitance fuel sensor are researched. and the major work is following : 1. taking the fuel entity of fully - filled airplane oil tank as studying object, the outhor calculates the central points of the section contours and the volume of the remnant fuel under the section height by means of numerical calculation

    本文研究了同心電容式油量傳感器的標定、敷設和誤差分析的方法，主要工作如下： （ 1 ）以飛機油箱滿載狀態下的油液實體為研究對象，用數值方法計算出實體模型各剖面的面積中心點和各剖面高度下的油液體積值。
  16. As the principal materials which are used as the high magnetic of hdd of computer mri and ct magnetic field hang float the railroad train motor of sound circle astro - airshop sound circle and engine etc. and the resposition hydrogen of the metal alloy manufacturing motive battery, these products are regarded as the new material industrial products in high scientific and technological circles

    等多種稀土金屬及合金產品，純度范圍99 - 99 . 9 % 。它們是當今世界認定的高科技領域新材料工業產品，是計算機磁盤驅動器的音圈電機vcm核磁共振成像儀mri磁懸浮列車航天飛船音圈馬達電機等所用高能磁體以及製造動力電池所用儲氫合金的主要材料。
  17. As the damage tolerance technique has being widely and deeply adopted in the design and life prediction of aircraft structures, the development of high performance and more suitable software used in damage tolerance design and assessment is more urgent. while at the same time the existing domestic software is not well suitable for requirements in engineering

    隨著損傷容限技術在飛機結構設計和壽命評估中的廣泛採用，研製高性能且實用的損傷容限分析與評定軟體系統越來越迫切，而國內現有的損傷容限分析軟體經實踐證明其性能和適用性不能很好滿足工程需要，特別是結構剩餘強度和裂紋擴展分析程序。
  18. Abstract : a new method, collaborative allocation ( ca ), is proposed to solve the large - scale optimum allocation problem in aircraft conceptual design. according to the characteristics of optimum allocation in aircraft conceptual design. the principle and mathematical model of ca are established. the optimum allocation problem is decomposed into one main optimization problem and several sub - optimization problems. a group of design requirements for subsystems are provided by the main system respectively, and the subsystems execute their own optimizations or further provide the detailed design requirements to the bottom components of aircraft, such as spars, ribs and skins, etc. the subsystems minimize the discrepancy between their own local variables and the corresponding allocated values, and then return the optimization results to main optimization. the main optimization is performed to reallocate the design requirements for improving the integration performance and progressing toward the compatibilities among subsystems. ca provides the general optimum allocation architecture and is easy to be carried out. furthermore, the concurrent computation can also be realized. two examples of optimum reliability allocation are used to describe the implementation procedure of ca for two - level allocation and three - level allocation respectively, and to validate preliminarily its correctness and effectiveness. it is shown that the developed method can be successfully used in optimum allocation of design requirements. then taking weight requirement allocation as example, the mathematical model and solution procedure for collaborative allocation of design requirements in aircraft conceptual design are briefly depicted

    文摘:探討了一種新的設計指標最優分配方法- -協同分配法，用於處理飛機頂層設計中的大規模設計指標最優分配問題.分析了飛機頂層設計中的設計指標最優分配特徵，據此給出了協同法的原理並建立了數學模型.協同法按設計指標分配關系將最優分配問題分解為主系統優化和子系統優化，主優化對子系統設計指標進行最優分配，子優化以最小化分配設計指標值與期望設計指標值之間的差異為目標，進行子系統最優設計，或對底層元件（如飛機翼梁、翼肋和翼盒等）進行設計指標最優分配，並把最優解信息反饋給主優化.主優化通過子優化最優解信息構成的一致性約束協調分配量，提高系統整體性能，並重新給出分配方案.主系統與子系統反復協調，直到得到設計指標最優分配方案.兩層可靠度指標分配算例初步驗證了本文方法的正確性與可行性，三層可靠度指標分配算例證明了本文方法的有效性.最後，以重量指標分配為例，簡要敘述了針對飛機頂層設計中設計指標協同分配的數學模型和求解思路
  19. A new method, collaborative allocation ( ca ), is proposed to solve the large - scale optimum allocation problem in aircraft conceptual design. according to the characteristics of optimum allocation in aircraft conceptual design. the principle and mathematical model of ca are established. the optimum allocation problem is decomposed into one main optimization problem and several sub - optimization problems. a group of design requirements for subsystems are provided by the main system respectively, and the subsystems execute their own optimizations or further provide the detailed design requirements to the bottom components of aircraft, such as spars, ribs and skins, etc. the subsystems minimize the discrepancy between their own local variables and the corresponding allocated values, and then return the optimization results to main optimization. the main optimization is performed to reallocate the design requirements for improving the integration performance and progressing toward the compatibilities among subsystems. ca provides the general optimum allocation architecture and is easy to be carried out. furthermore, the concurrent computation can also be realized. two examples of optimum reliability allocation are used to describe the implementation procedure of ca for two - level allocation and three - level allocation respectively, and to validate preliminarily its correctness and effectiveness. it is shown that the developed method can be successfully used in optimum allocation of design requirements. then taking weight requirement allocation as example, the mathematical model and solution procedure for collaborative allocation of design requirements in aircraft conceptual design are briefly depicted

    探討了一種新的設計指標最優分配方法- -協同分配法，用於處理飛機頂層設計中的大規模設計指標最優分配問題.分析了飛機頂層設計中的設計指標最優分配特徵，據此給出了協同法的原理並建立了數學模型.協同法按設計指標分配關系將最優分配問題分解為主系統優化和子系統優化，主優化對子系統設計指標進行最優分配，子優化以最小化分配設計指標值與期望設計指標值之間的差異為目標，進行子系統最優設計，或對底層元件（如飛機翼梁、翼肋和翼盒等）進行設計指標最優分配，並把最優解信息反饋給主優化.主優化通過子優化最優解信息構成的一致性約束協調分配量，提高系統整體性能，並重新給出分配方案.主系統與子系統反復協調，直到得到設計指標最優分配方案.兩層可靠度指標分配算例初步驗證了本文方法的正確性與可行性，三層可靠度指標分配算例證明了本文方法的有效性.最後，以重量指標分配為例，簡要敘述了針對飛機頂層設計中設計指標協同分配的數學模型和求解思路
  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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