LOW-THRUST SINGLE-COMPONENT LIQUID-PROPELLANT ROCKET ENGINE (VERSIONS) Russian patent published in 2019 - IPC F02K9/68 

FIELD: astronautics.

SUBSTANCE: invention relates to space engineering and can be used in making single-component liquid-propellant rocket engines. Low-thrust single-component liquid-propellant engine comprises fuel feed tube 1, injector 2 in decomposition chamber bottom 3 and nozzle 4. Catalytic pack 5 consisting of briquettes made of porous refractory metal material is arranged in fuel decomposition chamber 3. Alternating impermeable reflecting elements are arranged between catalytic pack 5 briquettes. According to the first version of the engine, after the first fuel briquetted fuel, a reflecting element in the form of disk 6 is installed in the center of the chamber, the area of which is (10–25) % of the cross-section area of the decomposition chamber, and downstream of the second fuel briquetted there is a reflecting element in the form of annular washer 7. According to the second version of the engine design, the reflecting element installed after the first fuel briquette is made in the form of triangular figure 8, the area of which is (25–35) % of the decomposition chamber cross-section area, at that every next reflecting element in the form of triangular figure 8 is turned through 60° relative to previous similar element.

EFFECT: invention provides higher limiting flow rate of decomposition chamber due to higher efficiency of engine at start-up and higher specific impulse of engine thrust overall.

3 cl, 5 dwg