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a double propeller aircraft

A technology of aircraft and double propellers, which is applied in the field of aircraft, can solve the problems of inconvenient ultra-low speed or hovering flight, low safety and stability, and difficulty in short-distance take-off and landing, and achieves increased lift coefficient and reduced aspect ratio , Increase the effect of downwash airflow

Active Publication Date: 2017-12-29
BEIJING INST OF REMOTE SENSING EQUIP
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] Traditional aircraft need a runway to take off and land, cannot take off and land vertically, and are not convenient for ultra-low speed or hovering flight, and it is also difficult to take off and land in a short distance
Traditional helicopters have high energy consumption, low efficiency, low safety and stability

Method used

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Embodiment Construction

[0009] Now in conjunction with accompanying drawing the present invention is described in detail: a kind of double propeller aircraft comprises fuselage 1, left composite wing 2, right composite wing 3, empennage 4 and landing gear 5. The fuselage 1 is equipped with a control system and airborne equipment. The left compound wing 2 and the right compound wing 3 have the same structure, and they are symmetrically installed on the left and right sides of the fuselage 1. Empennage 4 is positioned at the tail of fuselage 1, and empennage 4 comprises horizontal empennage and vertical empennage. The horizontal tail includes a front fixed part and a rear movable part, and the horizontal tail plays the role of a horizontal stabilizer and pitch control; the vertical tail includes a front fixed part and a rear movable part, and the vertical tail plays the role of a vertical stabilizer and a rudder. Landing gear 5 adopts front three-point type wheeled structure. The concrete structure o...

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Abstract

The utility model relates to a dual-blade aircraft, which belongs to the technical field of aircraft, and comprises a fuselage, a left composite wing, a right composite wing, an empennage and a landing gear. The fuselage is equipped with a control system and airborne equipment. The left composite wing and the right composite wing have the same structure, and they are symmetrically installed on the left and right sides of the fuselage. Empennage is positioned at the afterbody of fuselage, and empennage comprises horizontal empennage and vertical empennage. The landing gear adopts wheel structure. The left compound wing comprises main wing, outer aileron, inner aileron, rotor and engine. Both the outer and inner ailerons can be deflected. The plane of rotation of the rotor is in a horizontal position. The rotor is located below the leading edge of the inner aileron, and when the rotor rotates, the flow field on the upper and lower surfaces of the blades will be improved, the downwash airflow will be increased, and the airflow separation on the upper surface of the blades will be delayed. The aircraft is safe, efficient and maneuverable.

Description

technical field [0001] A dual-blade aircraft belongs to the technical field of aircraft, in particular to a dual-blade aircraft. Background technique [0002] Traditional aircraft need a runway to take off and land, and cannot take off and land vertically. Traditional helicopters have high energy consumption, low efficiency, and low safety and stability. Contents of the invention [0003] The purpose of the invention is to overcome the above-mentioned shortcomings of traditional airplanes and helicopters, and invent a highly efficient, safe and stable dual-blade aircraft that is convenient for short-distance take-off and landing and vertical take-off and landing. [0004] A dual-blade aircraft comprises a fuselage, a left composite wing, a right composite wing, an empennage and a landing gear. The fuselage is equipped with a control system and airborne equipment. The left composite wing and the right composite wing have the same structure, and they are symmetrically ins...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C3/00B64D27/06
Inventor 王志成
Owner BEIJING INST OF REMOTE SENSING EQUIP
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