Composite jump takeoff system for heavy gyroplane with jump takeoff capability

A rotorcraft, heavy-duty technology, applied in the direction of aircraft, rotorcraft, motor vehicles, etc., can solve the problems of inapplicability, limited rotor inertia, etc., achieve the effect of convenient processing, increase the jumping height, and simplify the structure of the transmission system

Inactive Publication Date: 2015-10-07
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, during traditional jumping, the kinetic energy stored in the pre-rotation is in the rotor. Due to the limited inertia of the rotor, the stored energy is generally only suitable for light autogyro jumping.
For paddle disc load greater than 10kg / m 2 The medium and heavy rotorcraft cannot be used for this form of jumping

Method used

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  • Composite jump takeoff system for heavy gyroplane with jump takeoff capability
  • Composite jump takeoff system for heavy gyroplane with jump takeoff capability

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Embodiment Construction

[0012] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0013] A compound jumping system for a heavy-duty jumpable autorotor aircraft, the structure of which is as follows: figure 1 , 2 As shown, the end of the output shaft of the engine 1 is connected with the tail vector propulsion duct 4 through the friction clutch 3, the first helical bevel gear 2 is arranged on the output shaft of the engine 1, the second helical bevel gear 5 and the first helical bevel gear The bevel gear 2 meshes, and the second helical bevel gear 5 changes the transmission direction of the engine 1; the output end of the second helical bevel gear 5 is connected with the third helical cylindrical gear 7 through an electromagnetic clutch 6, and here it is divided into two ways of transmission: the first In one transmission, the third helical spur gear 7 meshes with the fourth helical spur gear 8, the fourth helical spur gea...

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Abstract

The invention discloses a composite jump takeoff system for a heavy gyroplane with jump takeoff capability. The tail end of an output shaft of an engine is connected with a tail vectored thrusting duct through a sliding friction clutch; a first helical bevel gear is placed on the output shaft of the engine; a second helical bevel gear is engaged with the first helical bevel gear; an output end of the second helical bevel gear is connected with a third helical cylindrical gear through an electromagnetic clutch; the third helical cylindrical gear in a first path of transmission is engaged with a fourth helical cylindrical gear; the fourth helical cylindrical gear is connected with a fifth helical cylindrical gear through a spline shaft; the fifth helical cylindrical gear is engaged with a sixth helical cylindrical gear; the sixth helical cylindrical gear is connected with a main rotor through a main rotor shaft; the third helical cylindrical gear in a second path of transmission is connected with a seventh helical cylindrical gear through a spline shaft; the seventh helical cylindrical gear is engaged with an eighth helical cylindrical gear; and the eighth helical cylindrical gear is connected with a flywheel through an overrunning clutch. Through the adoption of the composite jump takeoff system for the heavy gyroplane with the jump takeoff capability, disclosed by the invention, the jump takeoff of the gyroplane can be achieved.

Description

technical field [0001] The invention belongs to the technical field of autorotor aircraft or multi-habitat vehicle transmission, and relates to a jump-type take-off system of a heavy-duty autorotor aircraft or multi-habitat vehicle capable of vertical take-off, in particular to a composite jumping system of a heavy-duty autorotor aircraft capable of flying . Background technique [0002] Autogyro aircraft (abbreviated as autogyro) is a rotor-type aviation aircraft that uses autorotor as the lifting surface and propeller thrust as the forward power. The rotor of the gyroplane provides lift and attitude control moments such as pitch and roll, so it is different from the helicopter that relies on the power of the engine to drive the rotor. It was still able to land safely with its rotor spinning. Rotorcraft has the characteristics of both helicopters and airplanes. It has good low-altitude and low-speed performance and safety. It is cheaper to manufacture, use and maintain th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/12
Inventor 徐彬项昌乐杨兴邦汪洋樊伟
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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