航跡控制系統 的英文怎麼說

中文拼音 [hángjīkòngzhìxìtǒng]
航跡控制系統 英文
flight path control system
  • 航 : Ⅰ名詞（船） boat; shipⅡ動詞（航行） navigate （by water or air）; sail
  • 跡 : 名詞1 （留下的印子; 痕跡） mark; trace 2 （前人遺留的建築或器物等） remains; ruins; vestige 3 （...
  • 控 : 動詞1 （告發;控告） accuse; charge 2 （控制） control; dominate 3 （使容器口兒朝下 讓裏面的液體慢...
  • 制 : Ⅰ動詞1 （製造） make; manufacture 2 （擬訂; 規定） draw up; establish 3 （用強力約束; 限定; 管束...
  • 系 : 系動詞（打結; 扣） tie; fasten; do up; button up
  • 統 : Ⅰ名詞1 （事物間連續的關系） interconnected system 2 （衣服等的筒狀部分） any tube shaped part of ...
  • 控制 : control; dominate; regulate; govern; manage; check; cybernate; manipulate; encraty; rule; rein; c...
  • 系統 : 1. （按一定關系組成的同類事物） system 2. （有條理的;有系統的） systematic
  1. A integrated flight / propulsion control ( ifpc ) theoretical schema was designed based on this concept and a engineering schema was developed after take consideration of currently engineering condition and the requirements of in - service aircraft upgrade. a auto - flight system was designed which can achieve accurate flight movement control and increase performance of flight task such as ascend, cruise, te

    基於該概念設計了飛推綜合原理方案，並在考慮工程實現條件及現役飛機改進、改型要求后建立了工程實現方案，設計了軌跡跟蹤方式的自動飛行系統，解決了軌跡生成、表示、管理、跟蹤等問題，能夠實現運動狀態的精確控制，提高爬升、巡航等任務的性能。
  2. The improvements in the iaga contained adding strengthen operator, improving evaluation index of premature, etc. multi - phase homing project, making use of the flight properties of parafoil system in gliding and turning, was simple in control and facile in practice. based on frenet frame, the linear time - variable error equations of parafoil system were built

    基於frenet坐標系推導和建立了翼傘系統線性時不變的誤差方程，並運用「投影點」的思想來獲得frenet坐標系下偏差量的解析近似表達式，從而設計了用於翼傘系統航跡跟蹤的傳統pd控制器和增益調節型模糊pd控制器。
  3. Thirdly, by neglecting the coupling influence, the control laws of pitching, yawing and sloping movements are designed separately with frequency domain analysis and root locus, and then the parameters of the controller are chosen

    第三，忽略耦合影響，將控制系統分為俯仰、偏航、傾斜三個相互獨立的通道，用頻域分析法和根軌跡法設計控制律、選取控制器參數。
  4. Use energy - based control method to achieve the entry flight control of reusable launch vehicle. the basic concept is to take the energy as primary control variables, reduce the order of the system and design a tracking law to follow a three - dimensional entry trajectory

    本文採用基於能量的控制方法實現對航天器再入軌跡的控制，將能量作為獨立參量，從而降低系統的階數，利用線性反饋的方法設計一個跟蹤三維再入軌跡的控制律。
  5. Sufficient condition of global asymptotic stability for ship ' s straight - line tracking control system

    船舶直線航跡控制系統全局漸近穩定的充分條件
  6. The algorithm of strapdown inertial navigation system is also discussed and then use the flight - track generator to give a simulation, since a closed loop feedback integrated navigation system is designed in this paper, and the output of the filter must feed back to the strapdown inertial navigation system, the analysis of the algorithm in strapdown inertial navigation system is important. the scheme to design the trajectory of gps and the simulation of gps constellation are then studied, the simulation of gps constellation is given from the calculation of vernal equinox base on the principle of celestial mechanics, this method of different from other methods given by other paper and is useful to the research of satellite navigation system. a new method to abstract noise modal in integrated navigation system is proved to be useful in practice, this method, which is given by use the principles of stochastic processes, statistics, time series analysis, and system identification, is suitable for the kalman filter in integrated navigation system

    如航跡產生器的設計，該航跡產生器是研究組合導航問題的前提，從國外一些研究組合導航系統的文獻中可以看出，設計這樣一個航跡產生器是非常必要的，所以本文自行設計了這樣一個系統；還討論了捷聯慣性導航系統中捷聯解算的方法，並進行了模擬研究，由於在本文設計的閉環反饋式組合導航系統中，對捷聯慣導系統的平臺誤差進行閉環控制，需要將濾波器輸出的校正量反饋到捷聯解算內部，所以必須對捷聯解算進行深入的研究和分析，更何況捷聯解算問題本身也是導航界的一個熱門研究課題；另外，本文還介紹了gps軌道及其星座模擬的設計思想和方案，與以往gps軌道和星座模擬不同的是本文從天體力學中計算春分點開始，逐步進行gps軌道及其星座模擬，這樣的設計方法對從事衛星導航的研究工作是有價值的；還對組合導航中誤差建模方法進行了研究，綜合運用隨機過程、概率統計、時序分析及系統辯識等方面的理論提出了一套適合組合導航卡爾曼濾波的誤差建模方法，並運用實際研究工作中的測量數據對該方法進行了驗證。
  7. In the application of tf / ta2 flight control system, significant issues arise due to position errors, which is destructive for low altitude penetration aircraft. the concept of utilizing terrain contour matching technique to fixing the errors is introduced, and this concept is essential for military tf / ta2 flight applications without gps and forward looking radar in our nation

    論文首先簡要介紹了綜合tf ta ~ 2飛行控制系統的相關背景知識和技術，包括航跡規劃、飛行控制和航跡跟蹤等相關技術，給出了地形匹配系統設計和應用的技術背景和相關理論。
  8. In order to provide a basic and effective practical engineering tool for handling quality planning, analysing and evaluating, which is needed hi helicopter prototype development, this research work is launched on the fundation of comprehending the new aeronautical standard of united states army - ads - 33, and has obtained the achievements as following : ( 1 ) performance definition of pcs according to the criteria requirements for an explicit helicopter, beginning at analysis of its missions. ( 2 ) establishment of a helicopter attitude controller, which can meet the criteria requirements, by using the technology of adaptive neural network model - inverse control ; implementation of two response types ( rts ) and two control modes ; evaluation of quantitative parameters according to the ads - 33. ( 3 ) establishment of a helicopter trajectory contoller based on the attitude controller ; simulations of mission task elements ( mtes ) and evaluation of handling quality

    為了給型號研製中飛行品質的規劃、分析和評價提供基本的、有效的工程實用工具，本課題在充分消化理解美軍新航標ads - 33的基礎上，作了以下工作： （ 1 ）針對具體直升機，從任務分析入手，根據規范要求確定對飛控系統的要求； （ 2 ）應用自適應神經網路模型逆控制技術，構造了能夠滿足飛行品質要求的直升機姿態控制器，實現了兩種響應型式、兩種控制模式，並根據ads - 33進行了定量指標評估； （ 3 ）在姿態控制器的基礎上，構造了軌跡跟蹤器，進行了任務科目基元模擬和飛行品質評估。
  9. Route planning and trajectory control system of the attack helicopter is studied in this dissertation. divide the system into several sub - systems and study on the main techniques

    本文研究了武裝直升機航跡規劃與軌跡控制系統，給出了該系統的系統結構，並研究了各分系統的主要問題。
  10. In the end, the divisional resampling is applied to the demo system of trajectory planning and trajectory control, which indicates that it can increase the efficiency of the particle filter and be applied in practice

    最後，將其應用於飛行器航跡規劃與控制的模擬演示系統，結果表明，分區重采樣演算法提高了粒子濾波演算法的效率，可以在實際中推廣應用。
  11. In this thesis, the problems, related with research of automatic and precise homing of parafoil system, were analyzed thoroughly and systematically in method of theoretical analysis and numerical simulation, including dynamics, trajectory design and trajectory following

    本文以「實現翼傘系統自主、準確歸航」為中心，採用理論分析與數值模擬相結合的方法，對翼傘系統動力學、航跡規劃和跟蹤控制問題進行了比較系統深入的研究，得到了若干有意義的結論。
  12. Then the traditional pd controller and gain - scheduling fuzzy pd controller were designed to realize path following of parafoil system. simultaneously, several control strategies were brought forward in view of the basic flight properties of parafoil system. the important one was described as following : the

    同時，基於翼傘系統基本運動特性，提出了一系列有針對性的控制策略，其中重要的一條是，將平均風的影響在軌跡歸航中修正，而大氣紊流的影響作為干擾由控制器來補償。
  13. The system performed as obtaining the real - time navigation information, adjusting the on - line control parameters, programming flight path, storing and analyzing data, which insured the realization of long distance flight

    系統實現了導航參數實時獲取、飛行控制參數在線調整、航跡規劃與回顯、數據存儲及分析等功能，並為超視距飛行提供了有利保障。
  14. To solve the optimal control problem, some methods about pre - solver analysis and treatment were put forward, such as moving equations translated into frame of wind and normalized. those methods not only simplified the computation, but also favored the selection of weighting coefficient, and unified the solving methods for the optimal control problem in reachable or unreachable target point

    在最優控制的求解中，提出了向風坐標系轉化、無量綱化等解前分析的思想，簡化了計算，方便了加權因子的選擇，使目標點可達與不可達的翼傘系統歸航軌跡最優控制問題得到了統一的求解。
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