| 摘要 |
The guidance system for a rocket propelled progectile travelling at relatively low speeds uses an arrangement of fins at the rear adjacent to the discharge point of the propellant gases. These rear fins consist of inclined blades acting as spoilers to control the direction of flight and wing blades to cause rotation of the gas jet to produce a spin about the central axis. Three spoiler blades are arranged symmetrically around the jet nozzle and controlled by a system for producing swing about an axis at right angles to the central axis, for steering. |
