THRUST PULSE OUTPUT SYSTEM Russian patent published in 2015 - IPC F02K9/00 F02K9/56 

FIELD: aircraft engineering.

SUBSTANCE: proposed system comprises control system, spherical tanks with deforming metal webs separating fuel and gas chambers, balloons, filling necks, low-thrust liquid-propellant control engine units, correction-braking engine, chokes, air-operated electrical valves, fluid-operated electrical valves and check valves, pressure indicators, fuel feed lines and supercharge lines. Additionally, this system is equipped with sealed resilient medium separators connecting the oxidizer and propellant and oxidizer tanks fuel chambers outlet pipes with those of gas chambers. Stiffness of these separators is smaller than that of deforming metal webs. Correction-braking engine is integrated with the three extra engines to make the unit fitted at spacecraft lengthwise axis. Note here that low-thrust liquid-propellant control engines are integrated into four units of three engines each. Two engines of each said unit are arranged so that their thrust vectors are diametrically opposite in the pane perpendicular to spacecraft lengthwise axis. Third engine thrust vector in the spacecraft lengthwise axis is directed opposite the flight direction. Said low-thrust liquid-propellant control engines are secured in pairs in diametrically opposite points. Lines of propellant feed to the main manifolds of said low-thrust liquid-propellant control engines and to manifolds of correction-braking are provided with four pairs of fluid-controlled electrical valves interconnected in parallel.

EFFECT: higher reliability at long-term operation, decreased weight, better controllability.

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