The invention discloses a recoverable rocket power landing section guidance method based on an extended state observer, and relates to the field of aerospace and navigation guidance, and the method comprises the steps: constructing a motion equation of a recoverable rocket in a power landing section; according to the motion equation of the recoverable rocket in the dynamic landing section, under the condition that interference is not considered, the nominal control quantity and the nominal state quantity of the recoverable rocket moving according to a preset guidance track in the dynamic landing section are obtained, and the preset guidance track serves as a nominal guidance track; taking the external interference as an expansion state of the recoverable rocket in a power landing section, constructing an interference expansion state observer, and obtaining an observation value of the external interference; determining an interference compensation control quantity and a guidance control quantity according to the nominal guidance track and the observation value of the external interference; the guidance control quantity is the sum of the nominal control quantity and the interference compensation control quantity. According to the invention, the anti-interference capability, task adaptability and reliability of the recoverable rocket can be improved.
本发明公开一种基于扩张状态观测器的可回收火箭动力着陆段制导方法,涉及航空航天与导航制导领域,该方法包括:构建可回收火箭在动力着陆段的运动方程;根据可回收火箭在动力着陆段的运动方程,在不考虑干扰的情况下,得到可回收火箭在动力着陆段按照预设制导轨迹运动的标称控制量和标称状态量,并将预设制导轨迹作为标称制导轨迹;以外部干扰作为可回收火箭在动力着陆段的扩张状态,构建干扰扩张状态观测器,得到外部干扰的观测值;根据标称制导轨迹和外部干扰的观测值,确定干扰补偿控制量和制导控制量;制导控制量为标称控制量和干扰补偿控制量之和。本发明能够提高可回收火箭的抗干扰能力、任务适应性和可靠性。
Recoverable rocket power landing phase guidance method based on extended state observer
基于扩张状态观测器的可回收火箭动力着陆段制导方法
2023-12-22
Patent
Elektronische Ressource
Chinesisch
IPC: | B64G Raumfahrt , COSMONAUTICS |