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飞翼布局飞机舵面时延设计
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摘要
舵面时延大小是飞机飞行控制系统设计的重要约束之一。当舵面时延过大时,操纵输入不能及时作用飞机,在外界干扰或操纵下,飞机可能进入自激振荡状态,导致飞行品质下降,严重时危及飞行安全。本文建立了XX飞翼布局飞机舵面时延限制值的设计方法,从而计算出舵面时延限制值,在设计阶段作为舵机选择的依据,给出了XX飞翼布局飞机的三轴舵面时延设计的算例,分析了时延限制对飞机动态响应特性的影响。结果表明,对于XX飞翼布局飞机而言,其纵横向舵面时延限制值要求较高,航向较低。研究方法和结果可用于XX飞翼布局飞机的舵机选择与飞行控制系统设计时参考。
The actuator delay is one of the important constraints in designing flight control system. When the actuator delay is long. The input cannot affect the aircraft in time. The disturbed aircraft may go into pilot induced oscillation(PIO) resulting in lowering the flying quality and even be dangerous. The design method of actuator delay for flying wing is built and we can choose the actuator by calculating the actuator delay in design phase. The design results of a XX flying wing are introduced and the effects of actuator delay on flying quality is analyzed in the article. The result indicates that the requested actuator delay of roll control and pitch control surface is the higher, the directional control surface is the lower. The research method and result can be used to guide the preliminary design of actuator and flight control system for flying wing.
引文
[1]王广雄,何朕.控制系统设计.北京:清华大学出版社,2008.
    [2]何倩琳,王立新.飞翼布局飞机舵面偏转速率设计.航空学报.2013.
    [3]Hanke D.Flight test evaluation and data analysis of rate limiting induced PIO's.AIAA Atmospheric Flight Mechanics Conference and Exhibit.Texas:AIAA,2003,10:5317.
    [4]张跃,段镇.轴对称飞行器滚转稳定控制与舵机技术指标.光学精密工程.2010,18:100-107.
    [5]李淼,王立新.舵面特性对飞翼构型作战飞机短周期品质的影响.航空学报,2009,30:2059-2065.
    [6]张明廉.飞行控制系统.北京:航空工业出版社,1994.
    [7]方振平,陈万春,张曙光.航空飞行器飞行动力学.北京:北京航空航天大学出版社.2005.
    [8]飞机设计手册总编委会.飞机设计手册.北京:航空工业出版社,2002.
    [9]王磊,王立新.飞翼布局飞机开裂式方向舵的作用特性和使用特点.航空学报,2011,32:1392-1399.
    [10]MIL-STD-1797A,Military Standard:Flying qualities of piloted air plane.Washington D.C.Department of Defense,1990.
    [11]高金源,李陆豫,冯亚昌.飞机飞行品质.北京:国防工业出版社,2003.
    [12]李林,王立新.大展弦比飞翼构型作战飞机横航向飞行品质特性.北京航空航天大学学报,2009,35:661-664.
    [13]马超,李林,王立新.大展弦比飞翼布局飞机新型操纵面设计.北京航空航天大学学报,2007,33(2):149-153.
    [14]高洁,王立新,周堃.大展弦比飞翼构型飞机阵风载荷减缓控制,北京航空航天大学学报.2008,34:1076-1079.
    [15]杨凌宇,高金源,申功璋.飞行控制中的一种新型最优控制分配方法.北京航空航天大学学报.2007,33:572-576.
    [16]Klyde D H,McRuer D T,Myers T.Pilot-induced oscillation analysis and prediction with actuator rate limiting.Journal of Guidance Control and Dynamics,1997,20(1):81-89.

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