针对低慢小飞行器在综合处置中威胁环境复杂、多学科关键技术交互密切等现状,引入美国国防部体系架构框架(Department of Defense Architecture Framework,DoDAF)对低慢小飞行器综合处置体系进行顶层设计。对其视角视图进行“补充、裁...针对低慢小飞行器在综合处置中威胁环境复杂、多学科关键技术交互密切等现状,引入美国国防部体系架构框架(Department of Defense Architecture Framework,DoDAF)对低慢小飞行器综合处置体系进行顶层设计。对其视角视图进行“补充、裁剪、融合”,定义了各视角的建模顺序及各视角下视图的建模方法,形成一套面向各类复杂体系分析与设计问题完备的构建方法及一套体系架构快速设计方法。并以一种新型多元载荷协同作战的低慢小飞行器综合处置体系进行建模与仿真,验证了该方法能为低慢小飞行器的综合处置作战提供系统全面的描述和可靠的概念模型支撑、该模型可为作战体系架构设计与装备技术发展提供牵引。展开更多
Aimed at designing the unpower aerocraft attitude control system in a simple and practical way, the guaranteed cost control is adopted. To eliminate the steady-error, a novel tracking control approach--augmented state...Aimed at designing the unpower aerocraft attitude control system in a simple and practical way, the guaranteed cost control is adopted. To eliminate the steady-error, a novel tracking control approach--augmented state feedback tracking guaranteed cost control is proposed. Firstly, the unpower aerocraft is modeled as a linear system with norm bounded parameter uncertain, then the linear matrix inequality based state feedback guaranteed cost control law is combined with the augmented state feedback tracking control from a new point of view. The sufficient condition of the existence of the augmented state feedback tracking guaranteed cost control is derived and converted to the feasible problem of the linear matrix inequality. Finally, the proposed approach is applied to a specified unpower aerocraft. The six dimensions of freedom simulation results show that the proposed approach is effective and feasible.展开更多
Owing to the effect of crosswind, initial disturbance and the deviation of engine parameters.etc in the initial aviation, vari- able rolling velocity aerocraft will produce attitude angle deviation in the ideal orient...Owing to the effect of crosswind, initial disturbance and the deviation of engine parameters.etc in the initial aviation, vari- able rolling velocity aerocraft will produce attitude angle deviation in the ideal orientations. This paper adopts AVR microcontroller atmega16 and relevant signal process circuit to design the attitude controller and take the method of frequency discrimination and am- plitude discrimination to process attitude angle deviation of aerocraft. Accordingly, it amends attitude angle deviation of aerocraft ef- fect and implements the self- adapting attitude control of aerocraft’s rolling velocity.展开更多
文摘针对低慢小飞行器在综合处置中威胁环境复杂、多学科关键技术交互密切等现状,引入美国国防部体系架构框架(Department of Defense Architecture Framework,DoDAF)对低慢小飞行器综合处置体系进行顶层设计。对其视角视图进行“补充、裁剪、融合”,定义了各视角的建模顺序及各视角下视图的建模方法,形成一套面向各类复杂体系分析与设计问题完备的构建方法及一套体系架构快速设计方法。并以一种新型多元载荷协同作战的低慢小飞行器综合处置体系进行建模与仿真,验证了该方法能为低慢小飞行器的综合处置作战提供系统全面的描述和可靠的概念模型支撑、该模型可为作战体系架构设计与装备技术发展提供牵引。
基金the Spaceflight Innovation Foundation (20060115)the National Natural Science Foundation(60674105)
文摘Aimed at designing the unpower aerocraft attitude control system in a simple and practical way, the guaranteed cost control is adopted. To eliminate the steady-error, a novel tracking control approach--augmented state feedback tracking guaranteed cost control is proposed. Firstly, the unpower aerocraft is modeled as a linear system with norm bounded parameter uncertain, then the linear matrix inequality based state feedback guaranteed cost control law is combined with the augmented state feedback tracking control from a new point of view. The sufficient condition of the existence of the augmented state feedback tracking guaranteed cost control is derived and converted to the feasible problem of the linear matrix inequality. Finally, the proposed approach is applied to a specified unpower aerocraft. The six dimensions of freedom simulation results show that the proposed approach is effective and feasible.
基金This item is sponsored by science and technologydevelopment project of Beijing education commit-teeNO: KM200510772012
文摘Owing to the effect of crosswind, initial disturbance and the deviation of engine parameters.etc in the initial aviation, vari- able rolling velocity aerocraft will produce attitude angle deviation in the ideal orientations. This paper adopts AVR microcontroller atmega16 and relevant signal process circuit to design the attitude controller and take the method of frequency discrimination and am- plitude discrimination to process attitude angle deviation of aerocraft. Accordingly, it amends attitude angle deviation of aerocraft ef- fect and implements the self- adapting attitude control of aerocraft’s rolling velocity.
