two-control aircraft 中文意思是什麼
two-control aircraft
解釋
雙操縱面飛機-
The aircraft used throughout the hydraulic system, two aircraft integration design pressure and pressure and pressure and can independently accomplish suing time control moves make big vehicles with tight solid, more eggective your savings artificial, time, electricity and lower costs, improve efficiency, it can help make up the hydraulic pessure at the end of the department to achieve shoes second fill pressure of functions to enhance the quality of diesel
本機採用油壓系統，兩機一體設計，壓邊及壓前後均能獨立完成，採用時間控制動作，出力大，貼合緊牢固，更為你有效的節省人工、時間、電力及降低成本，提高工作效率，可以彌補全油壓壓底機死角之處，達到鞋子二次補壓之功能，提升壓著品質。 -
The civil aviation department ( cad ) has conducted a detailed investigation into the air traffic control ( atc ) incident of january 22, 2000, which involved two civil aircraft operating within the hong kong flight information region ( fir ) at approximately 110 nautical miles east of hong kong
二年三月三日民航處已就二零零零年一月二十二日發生的航空交通管制事件進行詳細調查。事件涉及在香港以東約一百一十海里的香港飛行情報區內飛行的兩架民航機。 -
This dissertation presents how to use the ultrasonic motor as an actuator to suppress the flutter of a two - dimensional airfoil section with a control surface. the ultrasonic motor, which features simple structure, high torque at low speed, small size, low weight and no electromagnetic contamination, is a promising actuator for the flutter suppression of small aircraft
超聲電機以其結構簡單緊湊、轉矩/質量比大、低速大扭矩、直接驅動，動態響應快、斷電自鎖和不產生磁場且不受外界磁場干擾等優點，有望成為一種非常有前途的作動器，用於小型飛機的機翼顫振主動抑制。 -
Flight control system and propulsion control system are two of important control systems on an aircraft
飛行控制系統和推進控制系統是飛機上兩個重要的控制系統。 -
Firstly, there is a full discuss of space aircraft thermal control. the background of the research for this paper is also presented here, in chapter 2, there is a complete discussing of fem realization in numerical heat transfer, including delaunay grids generation and display, two - dimension temperature field function eduction and collectivity compound
首先全面論述了航天器熱控制和熱分析的基本內容，指出本課題產生的工程背景。在第二章中完整地論述了有限元數值計算方法在解決傳熱問題中的實現，包括delaunay網格的生成與顯示，二維溫度場泛函的推導和溫度場的總體合成等。 -
The angle of attack and the sideslip angle are the two important measured quantities for the aircraft navigation / control aerodynamics analysis and structure analysis. for the different kinds of disturbance influence, now the sensors ca n ' t measure it accurately, in the high angle of attack, the error will add with the angle of attack increase
迎角和側滑角是飛機飛行導航控制、航電等方面重要的兩個測量量，由於受到各種干擾因素的影響，現代傳感器很難對其精確測量，在超大迎角飛行過程中，其測量誤差隨迎角增加而增加。 -
According to the study above, we bring forward combined rbf - rbf neural network to target assignment and attack sequence decision, which is proved to be feasible by matlab simulation. thirdly, we build mathematics model of super - maneuver fighter and part the aircraft states to two loops based on principle of time delay. then nonlinear dynamic inverse theory is applied to design the flight control law
接下來本文建立了超機動飛機的數學模型，並根據時標分離的原則，將飛機狀態劃分為快迴路和慢迴路，然後應用非線性動態逆理論分別構造兩個迴路的控制律，同時利用設計的飛控系統對赫布斯特機動進行了模擬。 -
The two aircraft were descending on converging tracks under radar control. at their closest, they were about 1. 3 nautical miles laterally and 900 feet vertically apart with slk928 passing behind hda437
兩機最相近時的距離約為一點三海里，相隔高度則為九百尺， slk928號航機在hda437號航機後面經過。 -
Abstract : two computational techniques for inverse fight dynamics, namely derivation - iteration and integration - iteration techniques, are investigated. the application of inverse dynamics to determine control power requirements for post - stall maneuvering is researched, and a maneuvering flight trajectory based algorithm is provided, which lays a numerical foundation for simplifying design criteria for post - stall aircraft. with the model of inverse dynamics employed, a flight control mode for the outermost loop of the control system, named maneuver generator, is designed to follow desired complicated maneuvering flight trajectories. an example of rapid heading - reversal maneuver and other numerical simulations show the feasibility of the algorithm and the design idea
文摘:考察了求解輸入類飛行逆動力學問題的微分-迭代與積分-迭代演算法;探討了利用逆動力學確定過失速機動操縱效能要求問題，這構成了進一步提出過失速機動飛機設計簡化判據的數值基礎;利用逆動力學設計機動發生模塊進行飛控系統的最外環控制，以便跟蹤期望的復雜機動軌跡.飛機最速反向示例及其它數值模擬結果表明設計思想與演算法是可行的 -
A loa between two air traffic control units specifies the coordination procedures between them. these include handover position ( s ), cruising levels available, separation between aircraft, communication equipment and coordination requirements, etc
兩個航管單位之間的協議書說明雙方的航管協調程序，包括交接點位置、可供使用的飛行高度、飛機飛行間隔、通訊儀器和航管協調需要等。 -
The mechanism of two possible ways of thrust vectoring control : force and moment control are analyzed. the effects of thrust vectoring on aircraft supersonic performance, take - off and landing performance, low speed and high angle of attack performance are studied. the air combat effectiveness of thrust vectoring control and post - stall maneuvers are also analyzed
5 、分析了推力矢量的兩種應用方式：力控制和力矩控制的機理，研究了推力矢量對飛機超音速性能、起降性能、低速大迎角性能的影響，討論了推力矢量與過失速機動對空戰效能的影響。 -
This paper aims at model of vertical tail based on certain type aircraft. the method of distributed actively vibration control based on multi dsp has been carried on this model. a distributed actively vibration control system based on dsps is designed to real timely control the structural vibration of two modes
本文以某型飛機的尾翼模型為目標，採用基於多dsp處理器的分散式控制方法實現對垂直尾翼模型的振動主動控制，開發出了一套基於dsp的振動主動控制系統，針對結構的兩階模態振動實施了分散式振動主動控制，並進行了相關的理論和實驗研究。
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