CONTROL METHOD OF SOLID-PROPELLANT PROPULSION SYSTEM OF SPACECRAFT AND DEVICE FOR ITS IMPLEMENTATION Russian patent published in 2020 - IPC F42B15/01 

FIELD: aerospace engineering.

SUBSTANCE: invention can be used in development of propulsion systems for controlled spacecraft. Method for control of solid-propellant propulsion system consists in change of solid-propellant propulsion unit pulse and vector of thrust using a combination of nozzle electromagnetic control units opening and closing by commands from the control system. Gas flow under pressure created by working medium sources passing through collector is provided through said units. Manifold pressure monitoring is performed in manifold with the help of sensors. Note here that gas pressure accumulation and stabilization in storage receiver is carried out at outlet of working medium sources. After that, gas pressure is reduced by means of step-down mechanical reduction gear separating the header into high and low pressure circuits. Control system controls pressure in both circuits. In accordance with the control algorithm, commands are sent to actuate the second and subsequent working body sources. Commands are supplied at reduction of pressure in high pressure circuit below allowable for correct operation of reduction gear, as well as to open all nozzle electromagnetic control units with accidental exceeding of maximum allowable pressure in low pressure circuit for discharge of excess gas into environment, without affecting the control of the spacecraft.

EFFECT: technical result is higher efficiency of control of spacecraft propulsion due to smoothing dynamics and efficient use of working medium, as well as increase in the device operation reliability.

10 cl, 3 dwg