An adaptive neural networks controller is designed for tilt rotor aircraft platform.
采用自適應(yīng)神經(jīng)網(wǎng)絡(luò)控制方法,設(shè)計(jì)出傾轉(zhuǎn)旋翼機(jī)模擬平臺(tái)姿態(tài)角控制器.
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Responses of tilt rotor to initial conditions in airplane mode were computed at typical flying speed.
計(jì)算了典型前飛速度時(shí)的系統(tǒng)對(duì)初始條件的響應(yīng).
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The multi - body analysis of the aeroelastic stability of the tilt rotor aircraft is presented.
通過多體動(dòng)力學(xué)方法建立了傾轉(zhuǎn)旋翼機(jī)動(dòng)力學(xué)分析模型.
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A complete tilt rotor aircraft flight control model was developed to enable design of rotor aircraft.
建立傾轉(zhuǎn)旋翼機(jī)數(shù)學(xué)模型是設(shè)計(jì)其合理的飛行控制律的基礎(chǔ).
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