Advanced numerical prediction correction guidance method based on adaptive control

Abstract

The invention discloses an advanced numerical prediction correction guidance method based on adaptive control. The method comprises the following steps: (1), establishing a spacecraft reentry guidancedynamics dimensionless equation considering earth rotation; (2), converting the thermal rate limit, the load limit and the dynamic pressure limit of the aircraft into height reference values; (3), performing differential homomorphic transformation on the longitudinal dynamics state of the aircraft to obtain a model taking voyage and height derivatives as states; (4), designing an active disturbance rejection guidance law for the voyage model; (5), designing an active disturbance rejection guidance law for the height derivative model; and (6), designing a guidance law. The method provided by the invention can be used for hypersonic aircrafts, (manned) airships, deep space exploration entering spacecrafts and pneumatic capture, and has high universality.

Description

technical field [0001] The invention relates to the aerospace field, in particular to an advanced numerical prediction and correction guidance method based on adaptive control. Background technique [0002] Guidance is one of the key technologies for spacecraft reentry (entry), and it is also a key research direction in the aerospace field at home and abroad. Due to the improvement of the performance of the on-orbit computer, the on-orbit application of the numerical prediction and correction guidance method has become possible, so it has become a current research hotspot. At present, the numerical prediction and correction guidance method is to use the gradient method to calculate the guidance variable from the position error in each guidance period. In order to make the guidance variables converge, it is necessary to integrate the dynamics multiple times in each guidance cycle, so the calculation required is large; and when there is uncertainty, it is difficult to ensure ...

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Problems solved by technology

In order to make the guidance variables converge, it is necessary to integrate the dynamics multiple times in each guidance cycle, so the calculation required is large; and when there is uncertainty, it is difficult to ensure the convergence of the gradient method; for the path limit problem, the tracking height reference is The current latest technology, but needs to design the feedback coefficient offline, lack of adaptability

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