in-flight failure 中文意思是什麼
in-flight failure
解釋
飛行中的故障-
It is a new way in the development of aircraft flight line maintenance expert system. expertise and fault isolation manual that help maintainers quickly find fault causes and failure components were adopted to a great extent
本研究充分利用維修專家的經驗並結合飛機排故手冊，幫助航線維護人員快速準確地根據飛機故障現象定位故障原因及故障部件。 -
This paper studies optimal helicopter flight operations in the event one - engine failure. a three - dimensional point mass with a yawing motion of uh - 60a has been used to study rto and cto from an elevated heliport or from a heliport, a first order dynamic of the oei contingency power is considered. flight after engine failure are formulated as nonlinear optimal control problems
雙發及多發直升機單發失效后，直升機飛行所需要的功率由剩餘發動機提供，而在某些需要大功率的飛行狀態時，如起飛狀態、著陸狀態等，剩餘發動機提供的功率可能滿足不了，這就需要對剩餘發動機的可用功率進行合理利用。 -
Abstract : the control reconfigurable aircraft with multi - surfaces needs robust basic flight control system to support enough time for failure detection and isolation. when partial surface loses, it can keep the damaged aircraft stable. in this paper, multivariable output feedback digital control laws are designed for the control reconfigurable aircraft ( cra ). the method uses fast - sampling digital pi controllers to design digital flight control tracking system. this paper gives the way to design the controller and analyze its robustness characteristics. the simulation results indicate that the controller is very robust and the output responses are fully satisfactory
文摘:控制可重構飛機要求其基本飛行控制系統對舵面部分缺損故障具有強的魯棒特性，在故障發生后保證飛機的穩定性，提供足夠的時間進行故障的檢測和隔離，為控制系統重構提供條件.本文採用高速采樣pi控制器設計輸出反饋跟隨系統，給出了控制器的設計方法，並分析了它對于控制舵面部分缺損故障的魯棒特性.模擬結果表明，這種控制器具有好的魯棒特性 -
The application of control law developed above to the problem of reconflgurable flight control is described. based on the simulation results, the effects of learning rate ( or adaptation gain ) and slide model terms on the control system are discussed. comparing with adaptive control, the control law is helpful to improve system ' s transition response and reduce undesirable oscillations, provides nearly perfect tracking in the case of undetected failure
4 、探討了所設計的控制律在重構飛行控制中的應用，討論了自適應調整率對自適應控制性能的影響、滑模魯棒控制補償項對控制性能的影響；對幾種舵面損傷的模擬結果表明，本文的控制律較自適應控制具有響應改善速度快、響應振蕩小的優點，具有較好的重構功能。
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