| 摘要 |
The present invention provides an aircraft which has the capabilities of the vertical takeoff, landing, hovering operations and flying with supersonic speed utilizing the folding "S" rotorwing as a conventional helicopter rotating wing. After transition to forward flight, following the takeoff, the "C"-blades of the "S" rotor-wing are folded and become a wing of the "O" configuration. The axle of the rotor-wing is designed to be tilted in all directions. The aircraft utilizes two jet engines for rotating the rotor-wing and propulsive force, and four small rocket nozzles, installed on both sides at the front and at the rear of the fuselage, for yaw control at low speed.
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