...
  • 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Aerospace science and technology >Spacecraft attitude tracking control under actuator magnitude deviation and misalienment
【24h】

Spacecraft attitude tracking control under actuator magnitude deviation and misalienment

机译：致动器幅度偏差和误配下的航天器姿态跟踪控制

获取原文
获取原文并翻译 | 示例
           
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

Adaptive backstepping control combined with a novel dynamic control allocation scheme is develops for attitude tracking control of a rigid spacecraft, in which multiple constraints are simultaneous considered, such as actuator uncertainties including torque magnitude deviation and misalignmer actuator constraints like saturation, external disturbances and even constrained energy consumptio More specifically, an adaptive backstepping control algorithm is firstly developed for the relative attituc tracking problem, in which the external disturbances and actuator uncertainties are explicitly considere and Lyapunov stability analysis shows that asymptotical stability of the overall system is guarantee Moreover, to overcome the singularity or parameter drift caused by the parameter updating lai a switching parameter modification strategy is involved. In view of the above, a dynamic contr allocation is further investigated to distribute the designed total control torques among the individu actuators. This method extends the conventional quadratic programming control allocation by penalizir the previous step before sampling intervals at a lower cost, and also the actuator magnitude ar rate limitation are considered simultaneously by an auxiliary saturation function. Finally, a numeric simulation example for a rigid spacecraft is included to illustrate the feasibility and effectiveness of usir the proposed scheme.
机译：针对刚性航天器的姿态跟踪控制，开发了一种自适应反推控制与一种新颖的动态控制分配方案相结合的方法，其中同时考虑了多个约束条件，例如致动器不确定性（包括扭矩大小偏差）和不对准器致动器约束（例如饱和度，外部干扰，甚至受约束）能量消耗更具体地说，首先针对相对姿态跟踪问题开发了一种自适应反步控制算法，其中明确考虑了外部干扰和执行器不确定性，Lyapunov稳定性分析表明，可以保证整个系统的渐近稳定性。由参数更新引起的奇异或参数漂移会涉及切换参数修改策略。有鉴于此，进一步研究了动态控制分配，以在各个执行器之间分配设计的总控制转矩。该方法通过以较低的成本在采样间隔之前惩罚前面的步骤扩展了常规的二次编程控制分配，并且还通过辅助饱和函数同时考虑了执行器幅度ar速率限制。最后，包括一个刚性航天器的数值仿真示例，以说明所提出方案的可行性和有效性。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号