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Coaxial helicopter capable of reducing kinetic energy loss of spin forced landing

A coaxial helicopter, kinetic energy technology, applied in the field of aircraft, can solve problems such as unreachable lift, increased loss, and low blade speed

Pending Publication Date: 2021-07-23
SANGAIR TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] When the current helicopter is forced to land, because the blades are connected to the power output end of the motor, and the motor does not provide power during the forced landing, a magnetic damping will be generated. This damping is to reversely drive the electrons after the blades rotate. Generated when the inner rotor rotates, the kinetic energy of the blade is lost. The magnetic damping will reduce the utilization rate of the kinetic energy of the blade using the airflow to rotate, increase the loss, and make the blade speed low during forced landing, which cannot reach the speed of the blade for safe forced landing The resulting lift, causing damage to the helicopter

Method used

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  • Coaxial helicopter capable of reducing kinetic energy loss of spin forced landing
  • Coaxial helicopter capable of reducing kinetic energy loss of spin forced landing
  • Coaxial helicopter capable of reducing kinetic energy loss of spin forced landing

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Embodiment Construction

[0023] The internal motor and the blade assembly of the coaxial helicopter that reduces the loss of kinetic energy of the spin forced landing of the present invention are arranged on the one-way bearing, and the power can be normally transmitted to the upper rotor assembly and the lower rotor assembly when the motor power is output, and when the power is lost, the spin forced landing During the stage, the one-way bearing disconnects the hard connection between the output of the power motor and the rotor assembly, so as to reduce the kinetic energy loss caused by the magnetic damping of the motor during the spin forced landing stage, better maintain the speed of the blade, and achieve the requirements for a safe forced landing. lift, thereby reducing the damage to the helicopter.

[0024] see figure 1 , the coaxial helicopter that reduces the kinetic energy loss of spin ditching includes a fuselage 10, an upper rotor assembly 1, a lower rotor assembly 2, a central shaft 3, a ro...

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Abstract

The invention provides a coaxial helicopter capable of reducing kinetic energy loss of spin forced landing. The helicopter comprises an upper rotor assembly, a lower rotor assembly, a central shaft and a rotation driving assembly, the central shaft penetrates through the upper rotor assembly and the lower rotor assembly, the upper rotor assembly comprises an upper blade assembly, the lower rotor assembly comprises a lower blade assembly, and the rotation driving assembly is connected with the central shaft. The rotation driving assembly drives the upper paddle assembly and the lower paddle assembly to rotate and comprises a motor, a speed reduction assembly and at least two one-way bearings, the motor is connected with the speed reduction assembly, and the speed reduction assembly is connected between the upper paddle assembly and the lower paddle assembly. One-way bearings are respectively arranged between the motor and the upper paddle assembly and between the motor and the lower paddle assembly, and by adopting the structure and utilizing the one-way rotation property of the one-way bearings, the one-way bearings enable rigid connection between the power output motor and the rotor wing assembly to be disconnected in a power loss spinning forced landing stage; therefore, kinetic energy loss caused by magnetic damping of the motor in the spin forced landing stage is reduced.

Description

technical field [0001] The invention relates to the field of aircraft, in particular to a coaxial helicopter which reduces the loss of kinetic energy of spin forced landing. Background technique [0002] When the current helicopter is forced to land, because the blades are connected to the power output end of the motor, and the motor does not provide power during the forced landing, a magnetic damping will be generated. This damping is to reversely drive the electrons after the blades rotate. Generated when the inner rotor rotates, the kinetic energy of the blade is lost. The magnetic damping will reduce the utilization rate of the kinetic energy of the blade using the airflow to rotate, increase the loss, and make the blade speed low during forced landing, which cannot reach the speed of the blade for safe forced landing The resulting lift can cause damage to the helicopter. Contents of the invention [0003] The main purpose of the present invention is to provide a kind...

Claims

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Application Information

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IPC IPC(8): B64C27/10B64C27/12B64C27/68B64C27/59
CPCB64C27/10B64C27/12B64C27/59B64C27/68
Inventor 罗君
Owner SANGAIR TECH
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