COMBINED METHOD OF CONTROLLING ROCKET ENGINE FUEL CONSUMPTION WITH MULTIPLE INITIATION AND COMBINED SYSTEM OF FUEL CONSUMPTION CONTROL Russian patent published in 2013 - IPC B64G1/24 F02K9/56 

FIELD: transport.

SUBSTANCE: set of invention relates to rocketry and serves to generate control commands to fuel components second consumption adjustment means in acceleration unit flight. Proposed method consists in maintaining preset ratio of fuel components second fuel components flow rates on the basis of continuous data of fuel components second fuel flow rate transducers. Note here that discrete fuel store time derivative is defined by measurements of two adjacent measurement points of fuel tank fuel level transducers. Proposed system comprises fuel second consumption transducers arranged in feed lines to transmit signals to computation device and, therefrom, to actuators. Additionally, this system incorporates fuel level discrete transducers mounted in fuel tanks. It includes also amplifying converter of signals from discrete transducers to generate logical 1 signal at their outputs at fuel passage through sensor of appropriate transducer and amplifying converter of oxidiser and fuel second flow rate transducer signals into digital code corresponding to measured volume second flows of fuel components. Fuel component temperature transducers are connected to signal amplifying converter to generate temperature correction to second flow rate transducer readings. Computer processes data from amplifying converters and used the control unit to generate instruction for throttle that controls ratios of fuel component second flow rates.

EFFECT: optimised parameters of mid flight rocket engine, decreased weight and increased payload.

2 cl, 3 dwg