Patent ID: 7467762
Filing Date: 2008-12-23
Classification: F42B

Abstract:
1. An unmanned aerial vehicle system comprising; (a) a rocket having fins that cause said rocket to turn into any wind said rocket encounters during flight; (b) a separable payload section of said rocket; (c) a parafoil mechanically coupled to said payload section by a plurality of suspension lines; (d) a compartment of said rocket for containing said parafoil; (e) a control line for controlling the drag on a right side of said parafoil and a control line for controlling the drag on a second side of said parafoil, both of said control lines being coupled to a controller motor in said payload section said motor for pulling at once one or the other of said control lines; (f) a radio receiver in said payload section for input of guidance commands to said radio receiver; (g) a ground-based radio transmitter for input of guidance commands to said radio receiver; (h) a rocket motor for propelling said rocket, said rocket motor having a timed ejection charge for separating said payload section from said rocket; (i) a launch tube internally dimensioned to receive said rocket therein; (j) an ignition means for igniting said rocket motor, said means being affixed to said launch tube.