| 摘要 |
A rocket 100 comprising propulsion units 121 comprising a pivotable rocket motor 122 pivotable between stowed and deployed positions wherein outer geometry of the rocket is changed as the motor is moved, a spring assisted one time deployment mechanism 124 for moving the motor between the positions and a release mechanism 126 for releasing the deployment mechanism. The outer diameter of the rocket may be increased as the motor is moved to the deployed position. The motor may include a nozzle and combustion chamber. The propulsion units may be arranged in a tractor configuration. The deployment mechanism may include a spring 422 and the release mechanism may include a frangible nut 430 and may be non-explosive. The rocket may comprise a frame 110 with a load ring (112 fig 3) and the motor may comprise an axle pivot 410 extending through the load ring terminating in a motor mount (510 fig 6). The motor mount may include a spherical hard stop (610 fig 6). A launch system comprises a carrier aircraft defining an interface envelope (210 fig 2A) and the motor in the stowed position may fit within this envelope. |
