FIELD: rocket propulsion systems.
SUBSTANCE: invention relates to rocket propulsion systems for small spacecraft (SSC) and is intended for use as a shunting control matrix of microengines of small spacecraft. A method is proposed for the operation of a matrix of solid propellant jet microengines with renewable fuel filling, the main elements of which are a flat round substrate with at least four microengines installed on each of its horizontal and vertical surfaces. The thrust of the micromotors installed on the lower and upper horizontal surfaces of the substrate is used to accelerate or decelerate the spacecraft, respectively, and the thrust of the micromotors on its vertical surface is used to turn it. The method uses multiple pneumatic or other supply of fuel capsules into the combustion chambers of spent microengines. The matrix is provided with additional pneumatic or other fuel filling devices, two horizontal and one vertical rotating annular belts. The first and second belts are respectively installed in front of the combustion chambers of the micromotors used to accelerate or decelerate the spacecraft, and the third vertical belt is installed in front of the combustion chambers of the micromotors used to turn the spacecraft. On the surfaces of each tape there are holes and refractory flint plates. The holes are used to supply fuel capsules to the combustion chambers, and the flint plates are used to close the combustion chambers with fuel capsules.
EFFECT: invention provides periodic supply of fuel capsules into the combustion chamber of the microengine and regulation of the vector and magnitude of the microengine thrust.
1 cl, 1 dwg
