Patent ID: 9487308
Filing Date: 2016-11-08
CPC Classification: B64G,F42B

Claim Text:
1. An aerospace system, comprising: a launch vehicle having a first end and a second end generally opposite the first end, the launch vehicle being elongated along a vehicle axis extending between the first end and the second end and having an external, outwardly facing surface; an annular element fixedly attached to the launch vehicle, the annular element having an external, inwardly facing surface radially spaced apart from, and extending at least partially circumferentially around, the vehicle axis, the annular element having a first edge surface facing a first direction along the vehicle axis and a second edge surface facing a second direction along the vehicle axis, the second direction being opposite the first direction; a propulsion system directly attached to the launch vehicle and having at least one nozzle positioned toward the first end of the launch vehicle to launch the launch vehicle; and a controller in communication with the launch vehicle and programmed with instructions that, when executed, direct the launch vehicle in the first direction during vehicle ascent, and direct the launch vehicle in the second direction during vehicle descent.