A combined-wing aircraft

Abstract

The invention discloses a combined-wing aircraft belonging to the technical field of aircrafts. The aircraft includes a fuselage, a rotor, fixed wings, a power distributor, a supercharger, rudder control nozzles and a drive shaft. The rotor, the power splitter and the supercharger are arranged above the fuselage. A support wheel of the rotor is arranged on the circular orbit of the supercharger. The fixed wings are arranged on both sides of the fuselage and below the rotor. The rudder control nozzles are arranged on the fixed wing on both sides of the fuselage and at the tail of the fuselage,and the drive shaft is connected to the power distributor and a power device in the fuselage. The power distributor drives the rotor and an impeller of the supercharger to rotate reversely at non-equal speeds to generate a pulling force and a high-speed airflow required by the aircraft. The high-speed airflow is ejected from the nozzles to generate an aerodynamic force, and the rudder control nozzles change the size, distribution and direction of the aerodynamic force to realize the attitude control of the aircraft. The combined-wing aircraft of the invention has advantages of both rotor aircrafts and fixed wing aircrafts, is capable of short take-off and landing and is capable of raising the flight efficiency. A power train and a rudder control system mechanism are simple, and are compactin structure and high in reliability.

Description

[0001] Technical field: [0002] The invention belongs to the technical field of aircraft, and in particular relates to an aircraft with combined wings. [0003] Background technique: [0004] Rotary-wing helicopters have stronger maneuverability than fixed-wing aircraft. They do not need a runway for take-off and landing. They can take off and land vertically, fly at low speed or hover, and adapt to flying in complex spaces. The general rotor helicopter rotor cantilever length is large, the carrying capacity is small, the flight resistance is large, and the empennage and the complex pitch control mechanism are required to control the aerial attitude and maneuverability of the aircraft, the structure is complex and the cost is high. The wings of fixed-wing aircraft can generate a lot of lift when flying at high speed, and have the characteristics of large carrying capacity and high flight efficiency, but they have the disadvantage of not being able to take off and land at short...

AI Technical Summary

Problems solved by technology

[0006] In order to overcome the shortcomings of the existing rotorcraft with complicated rotor control mechanism, large rotor cantilever length, and small load-carrying capacity, and give full play to the advantages of fixed-wing aircraft, the present invention provides a combined-wing aircraft, which has a simple transmission mechanism and high sensitivity of the control mechanism , with the advantages of both rotor and fixed-wing aircraft, it can realize vertical take-off and landing, efficient level flight, hovering in the air, flexible steering and other functions

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