| ID | 原文 | 译文 |
| 10534 | 首先针对离散二进制粒子群(binary particle swarm optimization,BPSO)容易陷入局部收敛的问题,提出一种改进的BPSO算法。 | First on discrete binary particle swarm (binary particle swarm optimization, BPSO) easy to fall into local convergence problem, an improved BPSO algorithm. |
| 10535 | 在分析高斯密度函数对尺度敏感性的基础上,利用粒子群与全局最优粒子的一致性动态调节尺度参数,并利用密度函数对称区间的定积分确定全局最优粒子的变异概率。 | On the basis of analyzing the gaussian density function sensitivity to scale, using particle swarm and the consistency of the global optimal particle dynamic adjust the scale parameter, and density function symmetry interval of the definite integral is used to determine the global optimal particle mutation probability. |
| 10536 | 而后将聚类的选择性集成抽象为组合优化问题,利用聚类成员有效性和差异性的加权组合定义适应度并以改进BPSO的进化过程实现聚类的选择性集成。 | And then to integrate the clustering of selective abstraction to combinatorial optimization problems, using clustering validity and difference of the weighted combination members define fitness and to improve the course of the evolution of BPSO realize the selective integration of clustering. |
| 10537 | 最后基于标准数据集和图像数据集验证算法的有效性。 | Based on the standard data and image data sets verify the effectiveness of the algorithm. |
| 10538 | 研究了刚性航天器的时延姿态稳定控制问题。 | Studied the time delay of rigid spacecraft attitude stability control problem. |
| 10539 | 首先建立了基于修正罗德里格斯参数(modified rodrigues parameters,MRPs)的航天器非线性状态模型,具有确定上界的时延项在状态反馈控制律中体现。 | First based on the modified rodrigues parameters (modified rodrigues parameters, MRPs) spacecraft state of nonlinear model, to determine the upper bound of time delay item is in the state feedback control law. |
| 10540 | 通过构造Lyapunov-Krasovskii泛函进行稳定性分析,由此得到保证系统渐近稳定的线性矩阵不等式,依此设计状态反馈控制系数矩阵。 | By constructing Lyapunov - Krasovskii functional stability analysis, thus guaranteed the system asymptotic stability of linear matrix inequality (lmi), in accordance with the design of state feedback control coefficient matrix. |
| 10541 | 考虑到航天器三轴间的耦合非线性项,利用扩张状态观测器(extended state observer,ESO)方法,设计了二阶非线性扩张状态观测器,以获得航天器系统内部状态向量并用于状态反馈控制律。 | Considering the coupling between the spacecraft triaxial nonlinear term, using the extended state observer (extended state observer, ESO) method, the design of the second order nonlinear extended state observer, in order to obtain the spacecraft within the system state vector and applies it to the state feedback control law. |
| 10542 | 为便于工程实际应用,仿真中将MRPs响应输出转换为欧拉角响应。 | For convenience of practical engineering application, the simulation will be MRPs response output into euler Angle response. |
| 10543 | 仿真结果表明,本文所设计的控制系统能保证航天器三轴姿态稳定。 | The simulation results show that in this paper, the designed control system can guarantee the stability of aircraft three-axis attitude. |