ORGANIZATION METHODS OF OPERATING PROCEDURE IN A LASER-DRIVEN ROCKET ENGINE AND LASER-DRIVEN ROCKET ENGINE Russian patent published in 2012 - IPC F03H1/00 F02K99/00 

FIELD: space and aeronautics.

SUBSTANCE: device refers to the rocket engines based on the rodding reception by absorbing the laser emission, and is made to control small spacecrafts. Organization method for operating procedures in the laser-driven rocket engine include inlet of the 6th control agent into the absorption section from the 3th gas-dynamic window side, and forming a plasma kernel in it by means if laser emission, by heating the control agent's flowing plasma kernel and creating a plasma stream from the c-d nozzle 9 when the control agent exhausts. From the c-d nozzle 9's choke side a control agent is additionally supplied tangentally to the absorption section's surface, create a warped and axisymmetric control agent's stream directed to the laser ray's source. This stream reaches the absorption section 6 bottom from the gas-dynamic window, turns and together with the main stream engulfs the plasma kernel. The laser rocket engines includes the source of the laser emission 1, system of rotating on focusing mirrors 2, absorption section 6, gas-dynamic window 3, exhaust section 9 and the control agent input system 5 from the gas-dynamic window 3's side. In the absorption section 6, from the c-d nozzle 9's choke side, the additional channels 8 are made for the control agent input, the axes of which are placed tangentally to the absorption section's surface.

EFFECT: sustaining of the high performance index and enhanced the laser rocket engine operation.

6 cl, 2 dwg