FIELD: engines and pumps.
SUBSTANCE: invention relates to motor missile systems for small space vehicles and is intended for use as a shunting engine in the performance of linear and angular displacements. According to the invention, the planar monolithic heat-resistant dielectric substrate comprises conically shaped micropores arranged on the surface from opposite sides, ranked by volume in proportions of successive degrees of number two (1-2-4-8-16) and filled with solid fuel. On the centers of the bases of conical micropores, spherical ignitors are placed fixed in through cylindrical micropores and clamped by center holes of bus bars of rows and columns of first and third heat-resistant dielectric membranes, on which the second and fourth heat-resistant dielectric membranes with through cone-shaped micropores are superposed, forming nozzles over cone-shaped micropores filled with solid fuel. Address bus bars of rows and columns are connected respectively to the first and second row decoders and, through the address switch of the reversing engine cells, with the column decoder and the data decoder, which control the coordinates, magnitudes and direction of thrust vectors of reversible engine cells. Inputs of the decoders are connected to the outputs of the alternative code combinations memory unit whose inputs are connected to the outputs of the spent code combinations memory unit and information outputs of the controller.
EFFECT: invention makes it possible to provide the possibility of individual digital control of the thrust magnitude of each reversible engine cell of the reversible matrix motor system of a small spacecraft.
1 cl, 3 dwg
