飛機加速度 的英文怎麼說
中文拼音 [fēijījiāsùdù]
飛機加速度
英文
aircraft acceleration-
Based on the mathematical model developed by the paper, the trim calculations are carried out in the conditions that the example aircraft converts from helicopter to airplane mode in level flight with zero longitudinal acceleration and angular rate
本文依據所建立的樣例機縱向動力學模型，假定飛機在給定高度平飛，縱向加速度和角加速度均為零，完成過渡模式下的動力學配平。Although aircraft designers and engineers continued to employ wing - warping techniques for years afterward ( especially on early monoplanes such as the bleriot xi ), ever faster flight speeds eventually led them to beef up wing structures to resist the resulting stresses
雖然其後許多年間，飛機設計師和工程師仍繼續採用翹曲機翼設計（尤其是布雷修xi型等早期單翼機） ，但由於飛行速度不斷提升，終于迫使他們加強機翼結構，以承擔所增加的應力。In high - performance aircraft the pilots are vulnerable to ci because of some of the aircrafts " characteristics, which include high sustained + gz ( hsg ) acceleration, high rate of onset and high angular acceleration etc. so it has all the while been attached much importance to the studies on the mechanism of ci and the preventing and overcoming method of ci by the researchers in aviation medicine field
目前以f - 16 、蘇- 27為代表的高性能戰斗機，其所具有的持續高加速度（ + gz ） 、高加速度增長率、高角加速度的特點更易導致飛行中科里奧利錯覺的發生，嚴重危害飛行安全。因此，對科里奧利錯覺的機理及預防與克服研究在航空醫學中一直受到人們的重視。The shear experienced by the departing aircraft was due to vertical shear as the plane passed through the low level jet. based on the winds measured on - board a flight departing 8 minutes earlier, there was a rapid increase in head wind component, from 13 kt at 1, 420 ft to 39 kt at 3, 100 ft
起飛的飛機所遇到的風切變是由於該機經過低層急流的垂直切變所引致，根據一架在8分鐘前起飛的航機量度到的風速，顯示逆風由1 ， 420尺的每小時13海里急速增加到在3 ， 100尺的每小時39海里。High energy explosive was used to create a powerful and planar shock wave for accelerating flyer plate to high velocity, and high pressure was produced when flyer impacting with the sample. in the experiments, the impactor was brass and target was ofhc copper. by measuring the shock wave velocities of hr2 steel, high - density glass, aluminium alloy ( ly12 / lf6 ), magnesium - aluminium alloy ( mb2 ), polymethyl methacrylate and air, shock pressure and release isentrope of ofhc copper have been obtained
採用化爆加載、平面波發生器和空腔增壓技術，以黃銅為飛片，無氧銅為靶板，測量了抗氫鋼（ hr2 ） 、重玻璃（ sio _ 2 ） 、鋁合金（ ly12 lf6 ） 、鎂鋁合金（ mb2 ） 、有機玻璃（ pmma ） 、空氣（ air ）和無氧銅（ ofhccopper ）各阻抗匹配樣品中的沖擊波速度，上述材料的hugoniot狀態參數c _ 0 、均為已知，由此確定了無氧銅的沖擊加載壓力和等熵卸載后的狀態，得到了等熵卸載路徑。Fly straight and level from left to right at a moderate speed as the helicopter is just about in front of the pilot, add extra collective momentarily, then simultaneously push forward cyclic, and adjust the collective to maintain constant altitude and speed and hold the forward cyclic until the helicopter completes one ( 1 ) full traveling tumbling front flip to upright
由左至右保持適當速度的水平直線飛行，當直升機在操控者的正前方時，瞬間加大主旋翼的螺距，同時將升降舵打降舵，控制主旋翼的螺距使直升機保持固定的高度及前進速度，直到直升機向前翻滾一圈完畢。Electronystagmography ( eng ) is usually used as the objective index to study ci. but it is not clear about the influence of different coriolis acceleration levels on human ci and concomitant nystagmus as well as the correlation between ci and eng parameters. as high maneuverability aircraft is concerned, angular acceleration and linear acceleration coexist in flight
對高機動性的戰斗機而言，飛行中角加速度與線加速度作用往往同時存在，有研究表明，在z軸向的線加速度（ + 0 . 8gz ）作用下，科里奧利錯覺更為顯著。What is the acceleration of the plane and how long does it take to become airborne ?
求飛機的加速度和從開動到騰空所需要的時間是多少？The main research work of the thesis is summarized as follows : 1. the improved fuzzy logic control method the phenomenon of steady - state errors and flutter exists in the traditional fuzzy controller. an improved fuzzy controller without quantilizing is presented
地形跟隨飛行控制律設計針對某型飛機應用控制航跡角法和控製法向加速度法對不同的反饋信號分別設計了pi控制器和模糊控制器，並做了模擬比較與魯棒性驗證。As well as a missile launch, yesterday ' s flight involved mid - air refuelling and a low - level pass just 200 yards above the sea ' s surface at 560mph
除了導彈發射，昨天普京總統還參加了空中加油、超低空飛行等軍事演習，飛機曾經以560英里每小時的速度在高出海平面僅200米的地方飛過。Airborne gravimetry is a new kind of technique for surveying the gravity acceleration over the earth ' s surface and is advanced in gravimetry history, which basing on aircraft, including gravimeter, gps, altimeter and attitude sensor etc.
航空重力測量是一種新型的重力測量技術，它以飛機為載體，綜合應用重力傳感器、 gps 、高度傳感器、姿態傳感器等設備測定近地空間重力加速度。航空重力測量是重力測量的一次歷史性變革。On the other hand, the status quo of air transportation keeps increasing, altogether with the quick pace of the economy ' s going up. the density of airplanes in the sky is increasing, meanwhile, the distance between them are much smaller. therefore, it is pivotal to guarantee security of these airplanes
加上我國幅員遼闊，改革開放以來，隨著經濟的持續快速增長，航空運輸業的發展導致了空中交通流量的日益增大，使得空域中飛機密度增加，間距縮小，因而空中交通安全問題十分突出。3. the project using ins / gps system data to estimate the angle of attack and sideslip is brought forward first. this project using the ins / gps system data, such as acceleration and velocity signal, and others signals of the aircraft, such as gyros and the mathematic models, to estimate virtual signal
首次採用ins gps系統數據來估計迎角和側滑角傳感器參數原理和方法，利用ins gps系統測量的地速和總加速度信號結合飛機其他傳感器和數學模型估計得到了迎角和側滑角傳感器的虛擬信號，該種方法具有很好的實時性。An on - line minimum - variance estimator was developed for thrust acceleration applied to orbit transfer using discrete - time radar measurements. the mass - flow - rate of propellant was selected as a state variant, which was estimated by employing an integral state model and ekf filter. the variation equations for measurement vector to mass - flow - rate have been established to linearize the discrete - time measurement equations. the algorithm has applied successfully to maneuver process in commanding satellite into geo - stationary orbit. the results show that the algorithm developed here can monitor and determine whether engine works well or failure precisely and quickly during orbit transfer process
飛行器軌道機動過程中，為跟蹤、定位機動目標和干預機動控制過程，需要統計處理離散的雷達觀測量實時估計推進發動機的推力，進而確定飛行器的瞬時軌道參數.本文所述演算法是該工程問題的探討和解決方案.文章建立了軌道機動過程中連續變質量運動模型和離散雷達量測模型，推進發動機的質量秒耗量作為表徵推力加速度的一個近似常量，應用擴展卡爾曼濾波對離散的雷達測量數據進行順序統計處理給出秒耗量的最小方差估計;文章詳細地推導了線性化量測模型的變分方程和觀測矩陣;模擬結果表明該演算法能快速、準確地估計推進發動機的質量秒耗量和向機動目標施加的實際推力With the development of material technology, information technology, automation control technology, aeronautics and astronautics technology, the modern flight vehicles are required of high velocity, light structure, great flexibility and super maneuverability, which lead to the serious aeroelastic effects such as aeroservoelasticity, the coupling among the aerodynamics, structure, and control system
隨著材料技術、信息技術、控制技術以及航空航天技術本身的飛速發展，飛行器開始向高速度、輕結構、大柔性、超機動的方向發展，氣動彈性效應更加嚴重，從而引發了氣動、結構、控制系統相互耦合的氣動伺服彈性力學問題。Modern high - performance fighter planes can develop very high acceleration ( + gz ). under such a situation, pilots have to undertake a high - sustained g acceleration stress, which may produce loss of consciousness ( g - loc ), even result in fatal flight accidents
現代高性能戰斗機在機動飛行中可產生很高的正加速度（ + gz ） ，飛行員中+ gz致意識喪失（ g - loc ）的發生率增多，對飛行安全構成嚴重威脅。During the procedure, the airspeed continues accelerating ( or decreasing ) and the aircraft configuration is rapidly changing. the aerodynamic interactions are complex and lead to dynamic instabilities. the shift between helicopter and airplane flight modes necessitates a change in control strategy
過渡模式下，飛機速度不斷增加（或減小） ，氣動布局不斷改變，飛機動力穩定性差且氣動干擾嚴重，直升機控制和固定翼控制切換，因此過渡模式動力學特性和控制系統研究是整個傾轉旋翼飛機研製的主要難點。By using airport runway pavement assessment software, the author simulates the vertical acceleration and dynamic load while an aircraft is taxing on two different - roughness runway pavements, and analyzes the impact of runway pavement roughness on aircraft operation on the basis of the result of simulation
藉助機場道面平整度評估軟體，對飛機在兩種平整度不同的跑道上滑行時的豎向加速度和動載進行了模擬，並根據模擬結果分析了跑道道面平整度對飛機運行的影響。Based on gyro - free inertial navigation theory while revolve about mems accelerometer and dsp, this dissertation mainly focuses on the research of gyro - free inertial measurement unit for shell flight path measurement - the first step for guidance
本文以無陀螺慣性導航理論為基礎，以微機械加速度傳感器、高性能dsp處理器為核心，研製應用於某型炮彈的無陀螺慣性測量系統，該系統將用於炮彈飛行軌跡的測量，是實現炮彈制導的第一步。The table is a important device in the hardware - in - the - loop simulation system, and it simulates the flight of unmanned aerial vehicle so as to achieve flying parameters from those sensors. the signals of sensors in the table are transmitted by many cables previously, thus it confines the movement range of the three - axis frameworks. as the perfomance of uav become complicated, the signals cables are replaced by wire rings in some tables, but it brings many difficulties and unreliable factors for the simulation table ’ s design also. bluetooth, as a new short - range wireless communication technology, is a reasonable and feasible scheme in this condition
三軸模擬轉臺是無人機地面半實物模擬系統中的重要設備，用來模擬飛機在空中的姿態和角運動，以驅動傳感器產生飛行姿態、角速度及角加速度信號。早期轉臺上傳感器信號通過穿在框架中的電纜進行傳輸，這就限制了框架的運動范圍。隨著無人機任務的復雜程度不斷提高，出現了採用導電滑環傳遞信號的模擬轉臺，但這也給轉臺設計帶來了困難，且存在不可靠因素。分享友人