| 摘要 |
The invention relates to a pressure-fed hybrid fuel rocket engine with a synchronous starting system, which may be used for laboratory tests or for equipping rockets for various purposes, whose propelling system needs to operate for a long period of time and, possibly, whose propelling system needs to be stopped or restarted successively. Inside the claimed motor there take place some functional processes which constitute the starting sequence, said processes being triggered and carried out simultaneously by the synchronous starting system, upon the engine operation, and the injection of the liquid or gaseous component from a tank (3) into a transfer chamber (g) is carried out by means of an injector unit (E) represented by a system (e) of radial holes cut in a body (5) of the injector unit (E) and the final sequence from the transfer chamber (g) into the combustion chamber (B) by means of a cylindrical-type axial single-injector system represented by a central hole (f) cut in a separating grid (12), the synchronous starting system consisting of an assembly of structurally and functionally integrated mechano-pyrotechnic elements, said assembly consisting of an initiating pyrotechnic device (F) and the ducts of the injector unit (E) and of the combustion chamber (B) with a solid charge component (C) and a reaction nozzle (D), the initiating pyrotechnic device (F) being a hot gas generator consisting of an electric initiator (G), a spacer (21) and a pyrotechnic charge (22), located in an annular chamber (q) confined by the cylindrical inner wall of the combustion chamber (B), the outer cylindrical wall of the transfer chamber (g), the frontal wall (a), common to the tank (3) and the combustion chamber (B) and the transverse separating grid (12). |
