Overall design of tilt-rotor aircraft

Abstract

The invention provides overall design of a tilt-rotor aircraft. According to the technical scheme, a wing arrangement structure and power distribution of the aircraft are provided. The aircraft comprises a fuselage, front wings, T-shaped emages, winglets and a rear wing. The ends of the front wings are provided with the winglets. The rear wing is connected with the main wings through a connecting plate and connected with the fuselage. The T-shaped emages are arranged on the rear portion of the whole aircraft. Three engines are further mounted and independently move. The included angles between the axial directions of the engines and the horizontal plane during vertical take-off and landing of the aircraft are 80-100 degrees. The rotating speeds and the angles of the engines are adjusted through a flight control system. The engines assist to control the posture of the aircraft. When the aircraft tilts, the engines forward rotate till the included angles between the axial directions of the engines and the horizontal plane are zero degree.

Description

technical field [0001] The invention belongs to the field of aircraft design, and in particular relates to the wing layout and power arrangement of the aircraft. Background technique [0002] Compared with conventional fixed-wing aircraft, the existing tilt-rotor aircraft has the advantages of less dependence on the runway, a longer flight distance than helicopters, and a higher maximum level flight speed. However, due to the limitations of the layout, there are still many disadvantages. From the perspective of the overall layout of the aircraft, since most conventional tiltrotors adopt a conventional layout, the following problems will arise: [0003] 1. Considering the actual adaptability to the site, conventional tiltrotors have a small wingspan and poor gliding performance. It is difficult to use the aircraft to glide and make an emergency landing after the engine stops in the air. [0004] 2. The smaller wingspan makes the wing area smaller, such as the Osprey transpor...

AI Technical Summary

Problems solved by technology

[0003] 1. Considering the actual adaptability to the site, conventional tiltrotors have a small wingspan and poor gliding performance. It is difficult to use the aircraft to glide and make an emergency landing after the engine stops in the air.

[0004] 2. The smaller wingspan makes the wing area smaller. For example, the Osprey transport aircraft (MV-22) has a wingspan of only 14 meters and a wing area of ​​28 square meters

[0006] 1. Rotors and wings shield each other to cause aerodynamic interference. For example, the interference of the wings of the Osprey transport aircraft (MV-22) causes a loss of 20%-30% of the lift in the hovering state, resulting in a much lower hovering efficiency. conventional helicopter

[0007] 2. The placement of the engine at the tip of the wing leads to problems such as complicated internal design of the wing, difficulty in fuel supply / power supply, and difficulty in transmission design

[0008] 3. The complex dynamics of the rotor placed on the wingtip during the tilting process lead to large dynamic loads and poor stability of the rotor and wing coupling

[0009] 4. Difficulties in flight control technology and control system design

[0010] 5. The distance between the two rotors is far, and the failure of one will have a serious impact on the stability of the aircraft. After the compensation system is installed, the transmission efficiency will be greatly lost.

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