METHOD FOR CONTROLLING A PROPULSION SYSTEM

摘要

The invention relates to the field of propulsion assemblies, and in particular to rocket engines of the “expander” type, wherein at least one propulsion chamber (40) is fed with at least a first propellant by a first pump (33) coupled to a first turbine (34) that is driven by partial expansion of said first propellant upstream from said propulsion chamber (40) after passing, downstream from the first pump (33), through a heat exchanger (23) heated by said propulsion chamber (40). A method of the invention for controlling such a propulsion assembly (10) comprises the steps of determining whether there exists a risk of instability for the propulsion assembly (10), and in response to determining that said risk of instability exists, using a branch connection (28) situated between the first turbine (34) and the propulsion chamber (40) to shed a portion of said first propellant.

主权项

1. A control method for controlling a propulsion assembly in which at least one propulsion chamber is fed with at least a first propellant by a first pump coupled to a first turbine that is driven by partial expansion of said first propellant upstream from said propulsion chamber after passing, downstream from the first pump, through a heat exchanger heated by said propulsion chamber, the control method comprising the steps of:
determining whether there exists a risk of instability for the propulsion assembly; and in response to determining that said risk of instability exists, using a branch connection situated between the first turbine and the propulsion chamber to shed a portion of said first propellant.