Online Ballistic Planning and Guidance Method for Hopping Reentry Vehicle Based on Linear Pseudospectrum

Abstract

The invention provides a skip reentry aerial vehicle online trajectory planning guidance method based on a linear pseudo spectrum. The method comprises the following steps of initializing, performingstandard control on a flight segment, performing skip segment tilting counter-rotating determining, performing skip segment predictive trajectory integrating, performing precision determining, correcting skip segment rolling counter-rotating time correction, re-establishing parameter control, performing skip segment predictive trajectory integrating, performing precision determining, performing skip segment control parameter correction, and performing Kepler trajectory flight. According to the skip reentry aerial vehicle online trajectory planning guidance method, a roll angle modulus is updated through iteration and furthermore a terminal range deviation is corrected. When a segmentation condition is not decided by time, control compensation is introduced, thereby supplying a good initialcondition for terminal guidance. Furthermore a roll angle modulus value control rule and roll angle counter-rotating time are synchronously updated in one guidance period. Furthermore terminal transverse range and longitudinal range precision are simultaneously ensured. Through an analysis relation between a control amount correction value and a terminal offset, no iterative integration is required in updating the control amount at each time. Only 2ms are required in calculation at each time. The skip reentry aerial vehicle online trajectory planning guidance method is particularly suitable for online application.

Description

technical field [0001] The invention relates to the field of guidance for a jumping reentry vehicle, and more specifically relates to an online trajectory planning and guidance method for a jumping reentry vehicle based on a linear pseudospectrum. Background technique [0002] With the continuous progress of the Chang'e project, the design of the lunar exploration and return orbit has become a research hotspot. Different from general hypersonic re-entry vehicles, take the American Apollo lunar exploration return module as an example. This type of vehicle has a high re-entry speed and high initial energy. By designing a jumping re-entry trajectory, it can ensure heat flow constraints and overload. Under the premise of constraints, the energy of the aircraft can be effectively reduced, so that it can directly enter the terminal guidance section during the second reentry. In addition, this type of aircraft generally adopts aerodynamic design with low lift-to-drag ratio, and th...

AI Technical Summary

Problems solved by technology

This predictive correction method uses a cyclic integral similar to trial and error, and does not touch the essence of the problem. It cannot describe the correspondence between the terminal deviation and the control correction amount in a mathematical form.

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