Tilt rotor aircraft adopting parallel coaxial dual rotors

A coaxial dual-rotor and tilt-rotor technology, which can be used in rotorcraft, aircraft, motor vehicles, etc., and can solve problems such as small footprint

Inactive Publication Date: 2010-11-03
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This kind of tilt rotor aircraft has a relatively compact structure and a small footprint when parked, which solves the negative impact of the wings on t

Method used

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  • Tilt rotor aircraft adopting parallel coaxial dual rotors
  • Tilt rotor aircraft adopting parallel coaxial dual rotors
  • Tilt rotor aircraft adopting parallel coaxial dual rotors

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Embodiment Construction

[0036] See figure 1 , figure 2 , image 3 , Figure 4 , Figure 5 , Figure 6 , as shown, its specific implementation is as follows:

[0037] The present invention adopts the tilt rotor aircraft of parallel coaxial double rotors, adopts the design of conventional aerodynamic layout; it is composed of fuselage 1, wing 2, horizontal stabilizer 7 of empennage, elevator 8, vertical stabilizer 14, Rudder 15, pitch control tail rotor system 6 (including tail rotor blade 16, tail rotor hub 17, tail rotor shaft 18, tail rotor pitch change mechanism 19), wingtip small wheel 11, landing gear 12, power system (engine ) 24 and fuel system 25, clutch 26 of transmission system, gear box 27, transmission shaft 28, rotor system 9 (including rotor blade 20, rotor hub 21, rotor shaft 22, rotor pitch change mechanism 23), rotor nacelle 10. The tilting system 29 is composed; the wing 2 is installed in the middle section of the fuselage 1, the empennage and the pitch control tail rotor syst...

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Abstract

The invention relates to a tilt rotor aircraft adopting parallel coaxial dual rotors, which comprises a fuselage, wings, an empennage, a pitch control scull system, a landing gear, a power and fuel system, a transmission system, a rotor system, a rotor nacelle and a tilt system, wherein the wings are arranged at the center section of the fuselage; the empennage and the pitch control scull system are arranged at the tail of the fuselage; the landing gear is positioned at the belly of the fuselage; the power and fuel system is arranged inside the center section of the fuselage and is connected with the rotor system and the pitch control scull system through the wings and the transmission system in the fuselage; the rotor system is arranged on the rotor nacelle at the tip of the wings; partial wing which is fixedly connected with the rotor nacelle and simultaneously can tilt is arranged at the inner side of the rotor nacelle; and the tilt system is arranged in the wings and is connected with the rotor nacelle and the partial wing which can tilt. The tilt rotor aircraft is mainly characterized by adopting the pitch control scull system, the parallel coaxial dual rotors and the partialwing which can tilt to realize flight status transformation and conventional taxiing and landing, thereby improving the forward speed and the propulsive efficiency.

Description

(1) Technical field: [0001] The invention relates to a tilt rotor aircraft, in particular to a tilt rotor aircraft adopting parallel coaxial double rotors. The invention belongs to the technical field of vertical take-off and landing aircraft and aviation vehicle design. (two) background technology: [0002] In order to design an aircraft that has both the vertical take-off and landing performance of a helicopter and the high-speed, long-range performance of a fixed-wing aircraft, humans have proposed various vertical take-off and landing aircraft, including compound helicopters, equipped with thrust vectoring engines or Lift powered jet aircraft, rotary wing aircraft, tilt ducted propeller aircraft, tilt rotor aircraft, etc. For specific information, please refer to the paper published by American scholar Rob Ransone: An Overview of VSTOLAircraft and Their Contributions (An Overview of VSTOLAircraft and Their Contributions, paper number: AIAA-2002-5976). [0003] Due to i...

Claims

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Application Information

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IPC IPC(8): B64C27/02B64C27/08B64C27/52
Inventor 吴大卫胡继忠
Owner BEIHANG UNIV
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