Aircraft capable of vertically taking off and landing at high speed

A high-speed aircraft and vertical take-off and landing technology, applied in the field of aviation aircraft, can solve problems such as doubts about the application prospects of aerodynamic interference and poor dynamic stability, and achieve the effects of improving safety factor and practicability, reducing structural weight, and reducing aerodynamic interference

Inactive Publication Date: 2013-12-18
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Compared with the typical American V-22 "Osprey", due to the poor dynamic stability of this type of aircraft in the transitional

Method used

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  • Aircraft capable of vertically taking off and landing at high speed
  • Aircraft capable of vertically taking off and landing at high speed
  • Aircraft capable of vertically taking off and landing at high speed

Examples

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Example Embodiment

[0017] The present invention will be described below in conjunction with specific embodiments:

[0018] This embodiment is a high-speed unmanned verification aircraft that can take off and land vertically. The total designed take-off weight of the aircraft is 600kg; the set conversion speed is 50m / s, and the flight altitude in the conversion state is 500 meters; Pitch characteristics, in the transition phase, the ratio of lift generated by the main wing and the horizontal tail is 5:1.

[0019] The high-speed unmanned verification aircraft capable of vertical take-off and landing in this embodiment includes a fuselage 1, a main wing 5, a horizontal tail 6, a vertical tail 8 and a power system. The main wings are symmetrically installed on both sides of the middle section of the fuselage, and the horizontal tail is symmetrical. Installed on both sides of the rear of the fuselage. The power system consists of a turboshaft engine, a lift fan and two propellers. The lift fan 2 is conne...

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Abstract

The invention provides an aircraft capable of vertically taking off and landing at high speed. The aircraft comprises an aircraft body, a main wing, a horizontal tail, a vertical tail and a power system, wherein the power system consists of a turbo-shaft engine, a lift fan and two propellers; the lift fan is connected to the middle of the front end of the aircraft body through a main beam; an openable and closable cover plate is arranged on the upper part of the lift fan; an openable and closable flow guide blade grid is arranged on the lower part of the lift fan; the two propellers are arranged at two ends of the horizontal tail through a rotation mechanism which penetrates through the horizontal tail; the rotation mechanism drives the two propellers to synchronously rotate. By virtue of the aircraft, the lift fan adopts a pair of propellers rotating oppositely; the reaction torque can be self-balanced without a complicated reaction torque device, so that the structural weight of the lift fan is reduced; the flow guide blade grid is arranged on the lower part of the lift fan and can rotate along a rotary shaft of the blade grid; the direction of lift force is changed by changing the direction of air flow through the deflection of the blade grid; vertical taking-off and landing lift force can be provided, and partial thrust force during transition can be provided.

Description

technical field [0001] The invention relates to the technical field of aviation aircraft, in particular to a high-speed aircraft capable of vertical take-off and landing. Background technique [0002] Since the take-off and landing of fixed-wing aircraft requires a certain sliding distance to be realized, a relatively open take-off and landing field and a long runway are required. The construction of landing sites is expensive, time-consuming, and easily destroyed during wartime. Therefore, people hope to have a kind of aviation vehicle that can take off and land in narrow space always. Along with the birth of helicopter, this demand of people is satisfied to a certain extent. However, due to the asymmetric airflow of the rotor in the forward flight environment of the helicopter, the maximum forward flight speed of the helicopter is affected by the compressibility of the forward blades and the airflow separation of the backward blades. The maximum cruising speed of a conve...

Claims

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Application Information

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IPC IPC(8): B64C29/02B64C27/22
Inventor 邓阳平高正红史振兴田力王斑刘凯王力黄晶
Owner NORTHWESTERN POLYTECHNICAL UNIV
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