Residual carrying capacity evaluation method applicable to condition of thrust drop failure

Abstract

The invention discloses a residual carrying capacity evaluation method applicable to the condition of thrust drop failure. The method includes: judging whether a carrier rocket can be sent into the intended target orbit by using available thrust and residual fuel after the thrust drop failure of the carrier rocket occurs; if so, sending the carrier rocket into the intended target orbit by using the available thrust and residual fuel, if not, determining whether the carrier rocket can enter a safe orbit with the available thrust and residual fuel, and if the available thrust and residual fuel meet the condition for entering the safe orbit, sending the carrier rocket into a rescue orbit between the intended target orbit and the safe orbit or into the safe orbit with the available thrust andresidual fuel; otherwise, determining that the remaining carrying capacity is insufficient to enter the safe orbit; quantifying the residual carrying capacity as solving the minimum normal working time required for an engine to enter the intended target orbit and the safe orbit, which reduces the solving space of the rescue orbit and improves the solving efficiency.

Description

Technical field [0001] The invention relates to a method for evaluating the remaining carrying capacity under the condition of a thrust drop failure, and belongs to the field of launch vehicle control. Background technique [0002] In the history of aerospace at home and abroad, there are many cases of launch vehicle failures due to power system failures. One type of non-fatal failure is the phenomenon of a rocket's thrust drop at a certain moment after launch. After this type of failure, the rocket was unable to keep up with the nominal flight trajectory designed on the ground due to insufficient acceleration, resulting in a final crash. In order to enhance the performance of the launch vehicle and avoid or reduce the economic losses caused by such failures, it is a feasible method to re-plan the flight trajectory and rescue trajectory based on the failure situation. The current launch vehicle trajectory planning method is not real-time and fast enough to meet the online calcul...

AI Technical Summary

Problems solved by technology

[0003] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, and provide a method for evaluating the remaining carrying capacity applicable to the failure condition of thrust decline, by estimating the remaining carrying capacity of the rocket after t

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