| 摘要 |
The invention relates to a reactive control system based on rocket micro motors with hybrid fuel, with tilting nozzles, intended to be used in a suborbital launcher for testing. According to the invention, the reactive control system comprises an oxidizer tank (1), the solid fuel rod with frontal combustion, it has an external shielding (2), a primary nozzle (3) for combustion gases, supplementary oxidizer injectors (4), a combustion chamber (5), four secondary tilting nozzles (6) with independent control surface deflection, so as to ensure the control of the suborbital testing launcher attitude. |
