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控制输入饱和的挠性航天器姿态机动智能鲁棒控制 总被引:2,自引:0,他引:2
针对挠性航天器带有执行机构饱和的姿态控制问题,提出了一种将自适应变结构和智能控制相结合的智能鲁棒控制方法。首先,在基于非线性和低阶模态的动力学模型基础上,针对挠性模态不可测的特点,给出了仅利用输出信息的智能自适应变结构输出反馈控制器的设计方法,其中利用神经网络控制来补偿执行机构饱和非线性和采用自适应控制技术克服确定不确定性的界的困难,并基于Lyapunov方法分析了滑动模态的存在性及系统的稳定性。最后,将该方法应用于挠性航天器的姿态机动控制,在反作用飞轮存在饱和特性约束的情况下,完成姿态机动的同时,可有效地抑制挠性附件的振动。
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红外型空空导弹智能制导律研究 总被引:1,自引:0,他引:1
本文论述了红外型空空导弹应用智能控制的理论基础及结构特点,以多级智能控制的框架和机理设计出以比例导引为主、智能控制为辅的变指令智能制导律,并编制计算机软件以数字仿真的形式验证变指令智能制导规律的有效性和可行性 相似文献
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航天器智能自主控制技术发展现状与展望 总被引:13,自引:1,他引:13
本文首先介绍国内外在航天器智能自主控制领域的发展模式与发展水平 :发展模式包括战略规划、研究开发、型号应用三个层次 ;发展水平包括功能齐备与指标精良两个方面。然后对该领域的阶段发展目标进行了展望 :( 1 )实时智能自主姿态控制 ;( 2 )智能自主GNC ;( 3)智能信息技术在航天器控制系统、平台和有效载荷上的应用。 相似文献
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Unified Propulsion Systems present perceptible advantages for geostationary spacecrafts design: mass savings, as the ergols tanks are the same for the apogee motor and for the Attitude and Orbit Control System, higher performance, as specific impulse of bi-ergols motors is higher than the one of solid propellant motors and higher operational flexibility as the fuel amount can be adapted to the real flight conditions and as biliquid motors are restartable. On the other hand, the use of these propulsion systems for geostationary spacecrafts sets quite new mission analysis problems: the “predictability” of each delivered Delta-V is rather coarse (the corresponding uncertainty is about 4% for the existing motors). Also, only midlevel thrusters (about 400N) are available and so the finite burn losses associated with long burns arcs have to be minimized. This paper surveys the problems resulting from these new operational constraints and deals successively with the following items: optimal splitting up of the apogee manoeuvre, taking into account the possible dispersions on each Delta-V and the on-station longitude acquisition; minimization of the finite burn losses; adaptation of the apogee manoeuvre to the initial orbit parameters corresponding to the first North-South station-keeping cycle. The operation procedures derived from this survey will be used for the future launch of the ARABSAT spacecraft and for the following spacecrafts of the SPACEBUS family. 相似文献
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This paper presents a general framework for synchronized multiple spacecraft rotations via consensus-based virtual structure. In this framework, attitude control systems for formation spacecrafts and virtual structure are designed separately. Both parametric uncertainty and external disturbance are taken into account. A time-varying sliding mode control (TVSMC) algorithm is designed to improve the robustness of the actual attitude control system. As for the virtual attitude control system, a behavioral consensus algorithm is presented to accomplish the attitude maneuver of the entire formation and guarantee a consistent attitude among the local virtual structure counterparts during the attitude maneuver. A multiple virtual sub-structures (MVSSs) system is introduced to enhance current virtual structure scheme when large amounts of spacecrafts are involved in the formation. The attitude of spacecraft is represented by modified Rodrigues parameter (MRP) for its non-redundancy. Finally, a numerical simulation with three synchronization situations is employed to illustrate the effectiveness of the proposed strategy. 相似文献
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未来复杂航天器低频模态密集,其敏感载荷要求很高的指向精度和稳定度,只对航天器本体姿态控制很难满足要求.本文采用Stewart超静平台对敏感载荷进行6自由度主动隔振,建立了非线性动力学模型,并根据线性模型设计了多变量鲁棒控制器,采用DK迭代算法求解.频域分析可得Stewart平台对3~800Hz的扰动主动隔振大于25dB,仿真证明Stewart平台对10Hz谐波扰动隔振性能优于40dB,对白噪声随机扰动隔振性能优于30dB,有效抑制了微小扰动,起到了6自由度超静隔振平台作用. 相似文献
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复杂航天器稳态控制性能估计 总被引:1,自引:0,他引:1
未来复杂航天器应该按照期望的指向精度和稳定度来设计恰当的姿态控制系统。本文在全面考虑测量噪声、对象不确定性、环境扰动、执行机构与控制器非线性的前提下 ,首先分析了控制参数对稳态控制品质的影响 ;然后在详细探讨了测量噪声传播效应的基础上 ,提出稳态控制精度和稳定度的估计方法 ;最后通过对不同的噪声、不确定性、摄动和非线性情形进行大量仿真验证 ,结果同估计分析完全吻合 相似文献
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用非相干多普勒跟踪系统取代相干多普勒跟踪系统是可能的,只需消除其振荡器频率漂移对测速的有害 影响即可。TADT技术能使之达到相干系统的准确度。文中介绍TADT方法的数学原理及其在TDKSS网中的应用。结 论认为,TADT方法是解决非相干多普勒跟踪系统高精度和高可靠性这一矛盾的有效方法,从而使航天器的多普勒跟踪 技术取得突破性进展。 相似文献