A window adaptation linear estimation method of propellant mass is designed, to provide the correct propellant mass input for the utilization system in a variety of malfunction modes, and improve malfunction tolerance. In this way the utilization system can adjust the liquid oxygen control valve according to the predetermined adjustment scheme, amend the mixture ratio of the two propellants close to the theoretical value, and reduce the amount of remaining propellant that cannot be utilized due to the engine mixture ratio errors. And then the delivery capacity of the launch vehicle can be improved.
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