Guidance method for endoatmospheric powered phase of RLV (reusable launch vehicle)

Abstract

The invention provides a guidance method for the endoatmospheric powered phase of a RLV (reusable launch vehicle), which includes the following steps: (S1) according to flight altitude, the ascent phase of the flight track of the RLV is divided into a previous flight phase and a later flight phase; (S2) open-loop guidance is adopted at the previous flight phase, and closed-loop guidance is adopted at the later flight phase; (S3) in the process of closed-loop guidance at the later flight phase, a compensation scheme for altitude and / or trajectory inclination angle is adopted. Compared with the prior art, the guidance method has the following advantages: (1) according to flight altitude, the guidance method divides the ascent phase into the two phases, which respectively adopt open-loop guidance and closed-loop guidance, consequently, not only is the problem that the robustness of closed-loop guidance is decreased by strong interference factors within the dense atmosphere effectively prevented, but also the high precision requirement of the guidance is ensured, and thereby both the robustness of a guidance algorithm and the high precision are taken into consideration; (2) the requirement of the scheme on the memory space and on-line computation load of an onboard computer of launch vehicle is low, guidance commands can be obtained only by interpolation and simple calculation, the reliability is high, and engineering implementability is ensured.

Description

technical field [0001] The invention belongs to the field of aerospace vehicle guidance, in particular to a guidance method for an active segment in the atmosphere of an RLV. Background technique [0002] The ascent of the RLV (Reusable Vehicle) is all in the atmosphere. If we learn from the open-loop guidance method of using launch vehicles or foreign X-33 and other RLVs to track the program angle in the atmosphere, the uncertainty of thrust and aerodynamic force will cause the parameters of the terminal state of the RLV's ascent phase to deviate greatly from the predetermined one. The end state of the ascent segment determines the energy state and initial position of the aircraft for reentry and return. Since the RLV returns without power, it has the characteristics of limited ability to adapt to the deviation of the initial state and no go-around. Therefore, higher terminal guidance accuracy of the ascent phase is very important for the safe landing of the RLV aircraft ...

AI Technical Summary

Problems solved by technology

[0003] For the flight in the atmosphere of the RLV ascent section, the existing open-loop guidance scheme cannot meet the high-precision requirements, and it is necessary to adopt a closed-loop guidance method to improve the guidance accuracy to ensure that the end state of the ascent section is within the allowable deviation range

Professional scholars at home and abroad have proposed many methods for closed-loop guidance in the atmosphere, such as feedback linearization methods and optimal guidance algorithms. few

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