| 摘要 |
The invention relates to a rocket engine with free expansion nozzle to be used for space, military, civil and commercial purposes. The engine, as claimed by the invention, consists of a combustion chamber (3) having, at one end, a cylinder cover (1) which comprises some injectors (2) for a dominant liquid component (A), and, at the other end, a nozzle (4) with free expansion, carried out on a single central deflector wall (5), supported by means of some rods (6) and provided, when the propellant is liquid, with a second cylinder cover (7) having counterflow injectors (8) for a minority liquid component (B) circulated through the jacket of rods (6), the propelling force being transmitted to the structure of a vehicle by means of some lateral or rear supports (9' or 9"), which also make the liquid propellant circulate therethrough, in which case the whole double-walled structure incorporates some longitudinal reinforcing ribs. |
