ID	原文	译文
8524	所以采用循环最小化算法和凸松弛的方法将这个非凸的优化模型转化为凸优化模型进行求解。	So the loop minimization algorithm and convex relaxation methods will the non-convex optimization model is transformed into solving the convex optimization model.
8525	最后,仿真结果表明,利用所提出的资源分配算法能明显提高机动目标的跟踪精度。	Finally, the simulation results show that using the proposed resource allocation algorithm can obviously improve the maneuvering target tracking accuracy.
8526	研究了一类基于Delta算子的通信受限条件下参数不确定网络系统H∞滤波问题。	For a class of communication based on the Delta operator limited parameter uncertain network system under the condition of h-infinity filtering problem.
8527	在通信受限条件下,采用通信序列对网络控制系统进行分析,构建Delta算子描述的不确定系统滤波误差模型。	Under the condition of limited communication, the communication sequence analysis of network control system, build the Delta operator uncertain systems described filtering error model.
8528	利用线性矩阵不等式和Lyapunov-Krasovskii泛函提出滤波误差系统渐近稳定的充分条件,证明了系统的H∞性能,并给出滤波器的设计方法。	Using linear matrix inequality (lmi) and Lyapunov - Krasovskii functional sufficient conditions for the asymptotic stability of filtering error system is proposed, the h-infinity performance is proved, and the design method of filter is given.
8529	数值仿真结果验证了所提方法的有效性。	The numerical simulation results verify the effectiveness of the proposed method.
8530	微纳卫星姿控的反作用飞轮输出力矩小,难以克服普通气浮转台的干扰力矩,为了解决上述问题,实现微纳卫星姿控地面半物理仿真验证,必须对干扰力矩进行有效补偿。	Micro-nano reaction of the satellite attitude control flywheel output torque is small, difficult to overcome disturbance torque of ordinary air flotation turntable, in order to solve the above problem, realize the micro-nano satellite attitude control ground half physical simulation, must be effective compensation of moment of interference.
8531	为此,对干扰力矩分类并分析了各自的特性,针对性提出了干扰力矩主动补偿方法,研制了主动补偿式超低干扰力矩气浮转台,并基于此开发了微纳卫星姿控半物理仿真平台。	Of disturbance torque for this purpose, the classification and analyses their features, targeted interference torque active compensation method is proposed, developed active compensating low torque air flotation turntable, and based on the development of the micro satellite attitude control semi physical simulation platform.
8532	研制的气浮转台的干扰力矩达到2×10-5 Nm,小于微纳卫星反作用飞轮的最小输出力矩,利用半物理仿真平台有效地验证了微纳卫星大角度姿态机动控制算法。	Disturbance torque of air bearing turntable at 2 x 10-5 Nm, less than the minimum of micro-nano satellite reaction flywheel output torque, using semi physical simulation platform effectively verify the micro-nano satellite large Angle manetwer control algorithm.
8533	提出一种自适应建模相关向量机(adaptive modeling relevance vector machine,AM-RVM)并将其用于电子系统的状态预测。	Puts forward an adaptive modeling relevance vector machine (the adaptive modeling relevance vector machine, AM - RVM) and use it to electronic system state prediction.