Wing variable type vertical take-off and landing aircraft

A vertical take-off and landing aircraft, aircraft technology, applied in the field of aircraft, can solve the problems of inflexible flight, difficult purchase and parking, maintenance, high energy consumption, etc.

Pending Publication Date: 2019-07-26
杨德合
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] At present, many aircraft in the world cannot take off and land vertically, and need a long runway or water surface to take off and land. However, aircraft that can take off and land vertically either consume too much energy during flight, or consume too much energy during takeoff and landing. It cannot even take off with full load, or it is not flexible when flying, so the aircraft is not safe and reliable enough, thus restricting the popularization and application of the aircraft. Purchase and parking, maintenance

Method used

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  • Wing variable type vertical take-off and landing aircraft
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  • Wing variable type vertical take-off and landing aircraft

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Embodiment 1

[0035] The structure of the variable-wing vertical take-off and landing aircraft described in the present invention not only has the characteristics of fixed-wing aircraft, but also has the characteristics of rotary-wing aircraft.

[0036] Such as Figure 1-1 to Figure 3-5As shown, it is the single main rotor aircraft of the variable-wing vertical take-off and landing aircraft according to the present invention. Propeller 6 and wheeled landing gear 7. The specific structure and connection relationship of the constituent elements are:

[0037] Described main rotor 1 is connected with fuselage 4 as the main rotor of common single main rotor helicopter, and traction propeller 3 is rotatably connected with fuselage 4 through shaft, and left and right empennage 5 is connected as left and right main fixed-wing aircrafts On both sides of fuselage 4 tail, tail anti-torque propeller 6 is connected with fuselage 4 tail upper side as common single main rotor helicopter, and wheeled lan...

Embodiment 2

[0044] Such as Figure 2-1 to Figure 3-5 As shown, it is the left and right double main rotor aircraft of the variable-wing vertical take-off and landing aircraft according to the present invention, and the components include main rotor 1, circular fixed wing 2, traction propeller 3, fuselage 4, left and right empennage 5 and wheeled landing gear7. The difference between Embodiment 2 and Embodiment 1 is that there are two main rotors 1 in this embodiment, which are respectively installed on both sides of the fuselage; and there is no tail anti-torque propeller 6, and the specific structure and connection relationship of the components are as follows:

[0045] There are two main rotors 1, and the two main rotors 1 are respectively installed on the left and right sides of the fuselage 4 like the left and right double main rotor aircraft. The left and right main fixed-wing aircrafts are connected on both sides of the fuselage 4, and the wheeled landing gear 7 is connected with t...

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Abstract

The invention relates to a wing variable type vertical take-off and landing aircraft. The wing variable type vertical take-off and landing aircraft has the characteristics of a fixed wing aircraft, also has the characteristics of a rotary-wing aircraft, and is an aircraft combining the advantages of the fixed wing aircraft and the rotary-wing aircraft into a whole. According to the wing variable type vertical take-off and landing aircraft, a rotary-wing propeller used in vertical take-off and landing of the aircraft is changed to a fixed-wing or a part of the fixed wing when flying or glidingand can provide lifting force for the aircraft when flying or gliding even without rotating, full loading ground sliding take-off and landing can be achieved through the aircraft, full loading vertical take-off and landing can also be achieved through the aircraft, compared with an ordinary aircraft, the situation that energy consumption is increased due to the fact that the vertical take-off andlanding performance is provided is avoided, according to the wing variable type vertical take-off and landing aircraft, the voyage time of the aircraft is long, hovering can be achieved, the flying process is stable, flying is flexible, and the safety factor is higher.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to a variable-wing vertical take-off and landing aircraft. Background technique [0002] At present, many aircraft in the world cannot take off and land vertically, and need a long runway or water surface to take off and land. However, aircraft that can take off and land vertically either consume too much energy during flight, or consume too much energy during takeoff and landing. It cannot even take off with full load, or it is not flexible when flying, so the aircraft is not safe and reliable enough, thus restricting the popularization and application of the aircraft. Buy and park and maintain. Contents of the invention [0003] The purpose of this invention is to provide a kind of variable-wing type vertical take-off and landing aircraft, and this aircraft both has the feature of fixed-wing aircraft, also has the feature of rotary-wing aircraft. [0004] The technical soluti...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/06B64C3/38B64C11/34
CPCB64C27/06B64C3/38B64C11/34
Inventor 杨德合杨凤影
Owner 杨德合
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