The invention provides a dual-channel angle tracking guidance method for pneumatically assisted orbit descending, which comprises the following steps of: establishing a spacecraft pneumatically assisted orbit descending kinetic model under attack angle-sideslip angle modulation by considering J2 perturbation and celestial body rotation influence; respectively selecting a lift coefficient and a lateral force coefficient as control variables of a longitudinal channel and a lateral channel, and respectively taking a track angle and a course angle as tracking variables; the method comprises the following steps: comprehensively considering uncertainty of aerodynamic parameters and an atmospheric environment, and combining a spacecraft aerodynamic-assisted orbit descending kinetic model to obtain an aerodynamic-assisted orbit descending tracking guidance problem model under attack angle-sideslip angle modulation, and constructing a lumped uncertain item; approaching a tracking variable and a lumped uncertain item by adopting an extended state observer; and based on linear state error feedback, tracking guidance laws are designed in the longitudinal channel and the lateral channel respectively. Therefore, by the adoption of the method, the tracking guidance performance under the parameter disturbance and uncertain conditions can be guaranteed, and high-precision tracking of the nominal trajectory of pneumatic auxiliary orbit descending is achieved.
本发明提供了一种气动辅助降轨的双通道角度跟踪制导方法,包括考虑J2摄动和天体自转影响,建立攻角‑侧滑角调制下的航天器气动辅助降轨动力学模型;分别选取升力系数、侧向力系数作为纵向、侧向通道的控制量,并分别以航迹角和航向角作为跟踪变量;综合考虑气动参数和大气环境的不确定性,结合航天器气动辅助降轨动力学模型,获得攻角‑侧滑角调制下的气动辅助降轨跟踪制导问题模型,构建集总不确定项;采用扩张状态观测器对跟踪变量和集总不确定项进行逼近;基于线性状态误差反馈在纵、侧向双通道分别设计跟踪制导律。因此,采用上述方法,能够保障在参数扰动及不确定情况下的跟踪制导性能,实现对气动辅助降轨标称轨迹的高精度跟踪。
Dual-channel angle tracking guidance method for pneumatic auxiliary orbit descending
一种气动辅助降轨的双通道角度跟踪制导方法
2024-11-08
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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