Trapezoid layout tandem tilt wing aircraft and tilting mechanism thereof

Abstract

The invention discloses a trapezoid layout tandem tilt wing aircraft and a tilting mechanism thereof. Tandem wing layout, trapezoidal power system arrangement, multiple control surfaces and electric power system differential combination control are adopted, so the aircraft integrates vertical takeoff and landing functions and high-speed hover performance advantages, and also has the long-enduranceand long-range characteristics of a fixed wing aircraft and the hovering and vertical takeoff and landing characteristics of a helicopter. The vertical takeoff and landing and the air fixed wing modecruising are completed through the tilting wing layout, so the requirements for a taking off and landing place are reduced, and the cruising efficiency is improved; the trapezoid dynamic system layout can improve the efficiency of propellers; the roots of wings and a fuselage are fused, and the tilting sections of the wings and the fuselage section fused wing roots are connected and rotate relative to each other, so the mounting and positioning precision of the wings is improved; and the multi-control surface layout of the wings makes the control surfaces on the wings generate the rudder effect by using rotor wake during the vertical takeoff and landing, and attitude control participating in the vertical take-off and landing state reduces the control surfaces of a vertical fin, so the structural efficiency is improved.

Description

technical field [0001] The invention relates to the field of aviation aircraft, in particular to a trapezoidal layout tandem tilting wing aircraft and a tilting mechanism thereof. Background technique [0002] Among the existing aircraft, fixed-wing aircraft can cruise at high speed but need to use the runway to take off and land; helicopters can take off and land vertically and hover in the air, but their cruise performance and loading performance are poor, and it is difficult to improve the range and endurance. The vertical take-off and landing (VTOL) aircraft, as an aircraft capable of vertical take-off and landing, hovering in the air, and long-range, long-endurance cruise, demonstrates its application value. [0003] Most of the current vertical take-off and landing aircraft are tilt-rotor aircraft. The airflow interference between the wing and the rotor installed at the tip of the tiltrotor aircraft is strong, and the airflow of the rotor is blocked by the wing during...

AI Technical Summary

Problems solved by technology

[0004] In the invention patent CN106516080A, there is a tilting-wing aircraft with aerodynamic layout and tilting mechanism and a detection method for whether the wings are loose. It adopts the tilting-wing layout in which the front and rear power devices are staggered, but it has the following disadvantages: 1 .The tilting wing and the fuselage are directly tilted at the root of the wing, and there is no transition section between the wing and the fuselage to cause airflow interference between the wing and the fuselage; 2. Although the layout of the front and rear power plants is staggered, the airflow interference between the rotors The requirement for the rotor spacing is also limited by the length of the wingspan, which does not take into account the spacing requirements of the power plant; 3. The patent does not take into account the effect of the rudder surface, and the tilting wing is different from the tilting rotor and multi-rotor aircraft. The upright wing is a big drag plate for attitude control during take-off and landing, and the effect of differential control of the attitude by motors alone is very poor.

[0005] In the invention patent CN205440867U, "a tiltable wing aircraft" is disclosed, which adopts a tandem quadrilateral power device to arrange the tilting wing layout, but its front and rear power devices are arranged in a quadrilateral, causing the power device on the rear wing to be in the front The area affected by the wake flow of the power unit reduces the efficiency of the rear power unit; it adopts a double vertical rudder surface arrangement and lacks a vertical stabilizer, resulting in poor lateral stability of the aircraft; the tilting wing and the fuselage are directly tilted at the root of the wing, and the wing No fuselage transitions to cause airflow disturbance between wing and fuselage

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