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高速飞行器气动控制耦合优化设计方法研究
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作者 董超 潘鑫 +1 位作者 姜璐璐 陈刚 《西安交通大学学报》 EI CAS CSCD 北大核心 2024年第8期196-204,共9页
针对传统串行设计过程由于空气动力学和控制系统数学模型复杂、无法综合考虑气动和控制的多目标优化的问题,提出了一种面向高速飞行器气动控制耦合优化设计方法。基于气动单学科代理优化(SBO)算法,将飞行器主动控制技术(ACT)的思想与多... 针对传统串行设计过程由于空气动力学和控制系统数学模型复杂、无法综合考虑气动和控制的多目标优化的问题,提出了一种面向高速飞行器气动控制耦合优化设计方法。基于气动单学科代理优化(SBO)算法,将飞行器主动控制技术(ACT)的思想与多学科优化方法(MDO)相结合,构建了高速飞行器气动控制耦合多目标优化流程架构。在2马赫来流条件下,对带有控制舵的双锥体外形开展了气动耦合优化设计研究,以提升飞行器的气动性能和控制能力为优化目标。结果表明:经过气动控制耦合优化后的最优模型在超声速环境下,升力系数和升阻比分别提升了0.401%、2.999%,同时超调量与控制增益分别降低了2.769%、0.655%,气动性能和控制能力得到提升,验证了耦合策略的可行性;气动控制耦合优化的最优模型不仅使飞行器在超声速工作环境下性能更卓越,还有助于降低后续控制系统的设计难度,提高飞行器设计效率。所提气动控制耦合优化设计方法为高速飞行器的先进设计提供了必要的技术支撑。 展开更多
关键词 高速飞行器 气动控制耦合 多学科优化 外形设计
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Cross-coupling integral adaptive robust posture control of a pneumatic parallel platform 被引量:1
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作者 左赫 陶国良 《Journal of Central South University》 SCIE EI CAS CSCD 2016年第8期2036-2047,共12页
A pneumatic parallel platform driven by an air cylinder and three circumambient pneumatic muscles was considered. Firstly, a mathematical model of the pneumatic servo system was developed for the MIMO nonlinear model-... A pneumatic parallel platform driven by an air cylinder and three circumambient pneumatic muscles was considered. Firstly, a mathematical model of the pneumatic servo system was developed for the MIMO nonlinear model-based controller designed. The pneumatic muscles were controlled by three proportional position valves, and the air cylinder was controlled by a proportional pressure valve. As the forward kinematics of this structure had no analytical solution, the control strategy should be designed in joint space. A cross-coupling integral adaptive robust controller(CCIARC) which combined cross-coupling control strategy and traditional adaptive robust control(ARC) theory was developed by back-stepping method to accomplish trajectory tracking control of the parallel platform. The cross-coupling part of the controller stabilized the length error in joint space as well as the synchronization error, and the adaptive robust control part attenuated the adverse effects of modelling error and disturbance. The force character of the pneumatic muscles was difficult to model precisely, so the on-line recursive least square estimation(RLSE) method was employed to modify the model compensation. The projector mapping method was used to condition the RLSE algorithm to bound the parameters estimated. An integral feedback part was added to the traditional robust function to reduce the negative influence of the slow time-varying characteristic of pneumatic muscles and enhance the ability of trajectory tracking. The stability of the controller designed was proved through Laypunov's theory. Various contrast controllers were designed to testify the newly designed components of the CCIARC. Extensive experiments were conducted to illustrate the performance of the controller. 展开更多
关键词 servo-pneumatic system pneumatic muscle parallel platform cross coupling adaptive robust control parameter estimation
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空空导弹过失速翻转后向发射方法
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作者 刘程鹏 宋文萍 +3 位作者 高昌昊 韩少强 王跃 韩忠华 《航空学报》 EI CAS CSCD 北大核心 2024年第20期229-241,共13页
为缩短近距格斗导弹越肩发射的响应时间,实现空空导弹在近距格斗时对于后方目标的快速打击,提出了一种利用导弹在大/超大攻角下的静不稳定性,并辅助喷流直接力控制、末段主动舵偏控制的空空导弹快速后向发射方法。为研究所提出的新发射... 为缩短近距格斗导弹越肩发射的响应时间,实现空空导弹在近距格斗时对于后方目标的快速打击,提出了一种利用导弹在大/超大攻角下的静不稳定性,并辅助喷流直接力控制、末段主动舵偏控制的空空导弹快速后向发射方法。为研究所提出的新发射方法中预置舵偏、喷流直接力、末段主动舵偏控制策略的影响,发展了基于动态嵌套网格的耦合主动舵偏控制策略的高精度计算流体力学/飞行动力学数值模拟方法。数值模拟结果表明,所提出的方法可以在1.53 s内完成导弹的快速重新定向并在翻转末段保持姿态稳定可控。新方法可以将越肩发射的重新定向时间缩短至传统方法的约1/10。 展开更多
关键词 空空导弹 越肩发射 过失速重新定向 气动/运动/控制耦合 动态嵌套网格
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