Rudder-controlled jet double-rotor aircraft

Abstract

The invention discloses a rudder-controlled jet double-rotor aircraft and belongs to the technical field of an aircraft. The rudder-controlled jet double-rotor aircraft consists of a power cabin, an upper rotor, a lower rotor, a power device, a rudder controlling device, bearing wheel trains, a load cabin and the like. The upper rotor is located above the power cabin and the lower rotor is locatedunder the power cabin. Nozzles of a rudder controlling system are located between the upper rotor and the lower rotor and are distributed on the outer circumference of the power cabin. Bearing wheeltrains are distributed on the upper and lower circumference of the power cabin and maintain contact with the upper and lower rotors to bear axial load of the upper and lower rotors. The power device drives the upper rotor and the lower rotor to rotate with equal speed in the opposite direction and lift power and location and pose controlling thrust required by an aircraft are produced, size and direction of the controlling thrust are changed by a rudder machine. The rudder-controlled jet double-rotor aircraft has high engine driven performance and facilitates control of flight and landing in complex space; meanwhile, the rudder controlling device is simple in mechanism, compact in structure and has the independent power cabin and load cabin, and is high in safety.

Description

technical field [0001] The invention belongs to the technical field of rotorcraft, in particular to a rudder-controlled jet dual-rotor aircraft. Background technique [0002] A rotorcraft is an aircraft that controls the lift and maneuverability of the aircraft by changing the lift of the rotor and the pitch of the blades. It has stronger maneuverability than a fixed-wing aircraft. It does not require a runway for take-off and landing, and can take off and land vertically, fly at low speed or Hover, adapted to fly in complex spaces. The main rotor and power unit of a general rotorcraft are located in the middle and front of the load compartment, and the tail rotor is located at the tail of the load compartment. The cantilever length of the main rotor is large, the carrying capacity is small, and the flight resistance is large. To control the air attitude and maneuverability of the aircraft, the structure is complex and the cost is high. At the same time, the power compartm...

AI Technical Summary

Problems solved by technology

[0003] In order to overcome the disadvantages of the existing rotorcraft, such as small rotor bearing capacity and poor maneuverability control sensitivity and accuracy, the present invention provides a rudder-controlled jet dual-rotor aircraft

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