| 摘要 |
The idea of the invention is that the aircraft comprises takeoff and landing wings that are the main aerodynamic elements producing a lift at all stages of takeoff and landing. In cruising flight, the takeoff and landing wings take the flight configuration of a cruise missile to reduce the drag coefficient of the aircraft to a minimum possible and, as a result, save considerable quantities of fuel in the cruising configuration. Each takeoff and landing wing has an invariable cross-section and is provided with two rows of slots to improve resistance to the loss of airflow on the outer surface of the wing. The slots on the outside of the takeoff and landing wing are closed with flaps. This wing design is capable of generating a lift at angles of attack ranging from 1° to 90°. The takeoff and landing wings of the aircraft are unfolded at takeoff. As the aircraft climbs, the takeoff and landing wings are lowered into the folded position with a rise in the basic speed. When the takeoff and landing wings are lowered fully into their folded position, the basic speed of the aircraft is sufficient for flying using the horizontal nose and tail stabilizers only, whereupon the aircraft is accelerated to cruising speed. When the takeoff and landing wings are folded, they are fixed in the folded position by fuselage locks. In preparation for landing, the basic speed of the aircraft is lowered to a permissible level for airflow to be maintained, whereupon the takeoff and landing wings are released from the fuselage locks fixing them in the lowered position and raised to their landing position as the basic speed of the aircraft is reduced to the landing speed. The actuators of the locks fixing the takeoff and landing wings in the lowered position are located in the airtight zone of the fuselage and have mechanisms to force the locks open in emergency, while the incoming airflow contributes to movement of the takeoff and landings wings to their landing position, for which reason the aircraft of this design is safer to operate. The twin-section rudder surfaces of the vertical nose and tail fins function as yaw rudders and spoilers. This aircraft design is an optimal choice for developing supersonic aircraft and subsonic aircraft operating at Mach numbers of 0.95 to 0.99. The claimed aircraft design is suitable for aircraft operating from aircraft carriers and for development of piloted space shuttles.
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