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机动检测是多模型目标跟踪中的一个关键问题.在卡尔曼滤波中,当目标机动被噪声淹没时,传统的机动检测算法将失效,多分辨方法虽然能够有效地抑制噪声,可靠检测机动,但由于计算复杂导致严重的检测延迟,从而限制了它的应用.本文提出一种基于三阶累积量的机动检测新算法,它有效地克服了上述二者的缺陷.由于高阶累积量能够抑制高斯噪声,因此在三阶累积量域易于检测机动.同时通过采用逐点更新法,可实时进行机动检测.仿真结果表明,该算法优于传统算法和多分辨方法,特别是在低信噪比的情况下. 相似文献
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地面机动目标的红外伪装技术探讨 总被引:1,自引:0,他引:1
利用红外热像仪对行驶中车辆的红外特征进行了实验测试和研究,在对传统红外伪装
技术分析的基础上,探讨了机动目标红外伪装的难点,提出了针对重要地面机动目标的新型红外伪装技术,并介绍了实验测试方法。 相似文献
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XuHai Yang ZhiGang Li ChuGang Feng Ji Guo HuLi Shi GuoXiang Ai FengLei Wu RongChuan Qiao 《中国科学G辑(英文版)》2009,52(3):333-338
A geostationary (GEO) satellite may serve as a navigation satellite, but there is a problem that maneuvers frequently occur
and the forces are difficult to model. Based on the technique of determining satellite orbits by transfer, a predicted orbit
with high accuracy may be achieved by the method of statistical orbit determination in case of no maneuver force. The predicted
orbit will soon be invalid after the maneuver starts, and it takes a long time to get a valid orbit after the maneuver ends.
In order to improve ephemeris usability, the method of rapid orbit forecasting after maneuvers is studied. First, GEO satellite
movement is analyzed in case of maneuvers based on the observation from the orbit measurement system by transfer. Then when
a GEO satellite is in the free status just after maneuvers, the short arc observation is used to forecast the orbit. It is
assumed that the common system bias and biases of each station are constant, which can be obtained from orbit determination
with long arc observations. In this way, only 6 orbit elements would be solved by the method of statistical orbit determination,
and the ephemeris with high accuracy may be soon obtained. Actual orbit forecasting with short arc observation for SINOSAT-1
satellite shows that, with the tracking network available, the precision of the predicted orbit (RMS of O-C) can reach about
5 m with 15 min arc observation, and about 3 m with 30 min arc observation.
Supported by the National High Technology Research and Development Program of China (Grant No. 2006AA12Z322), the National
Basic Research Program of China (Grant No. 2007CB815503), and the West Light Program of Chinese Academy of Sciences (Grant
No. 2007LH01) 相似文献
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Jingrui Zhang 《Acta Mechanica Sinica》2010,26(1):141-146
Studied in this paper are the attitude control law design and the output torque estimation problem of micro control moment gyros (MCMGs) for the agile satellites executing rapid attitude maneuver mission. An algorithm is proposed for estimating the output torques and the gimbal angular rates of MCMGs, which can help engineers to choose reasonable size for actuators so that the cost of satellite can be decreased. According to some special maneuver missions, a numerical example of attitude control system for a small satellite with MCMGs in pyramid configuration is studied, and the simulation results validate the proposed estimation algorithm. 相似文献
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本文提出了基于增量学习神经模糊网络机动目标跟踪模型.当被跟踪目标发生机动时,该模型立刻检测到机动并对卡尔曼滤波器的自适应系统协方差进行精确估计,系统得到及时、正确的补偿.增量学习神经模糊网络能够随着环境变化,自动调整、找到最优的网络结构及参数,当发生机动时,总是能产生接近真实机动值的估计输出,从而提高跟踪性能及避免错误跟踪.仿真结果表明,该模型比传统的机动目标跟踪模型有更好的跟踪性能,并且该模型能动态的适应环境的变化,使系统更加实时,精确的跟踪机动目标. 相似文献
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提出了一种基于控制力矩陀螺的挠性卫星姿态大角度快速机动控制方法。结合卫星姿态动力学,运动学和挠性附件的振动方程,建立了面向预测控制方法的非线性预测方程;在建立了包含卫星姿态跟踪误差,控制力矩能量以及挠性附件振动能量的优化目标函数基础上,采用非线性模型预测控制方法设计了兼顾机动性能与抑制附件振动的卫星姿态机动律。为进一步消除挠性附件振动,采用输入成形技术对规划的控制力矩进行处理,成形出合理的控制力矩指令。最后以成形后的控制力矩指令为输入条件,基于鲁棒伪逆方法设计了金字塔控制力矩陀螺群的操纵律,完成挠性卫星姿态机动的非线性滚动控制。针对算例的研究表明:卫星滚动轴姿态能够在约27 s内机动50°,且具有指向精度小于0.03°,姿态稳定度小于0.03(°)/s的性能。 相似文献