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A Design Method of Helicopter Dry Running Power Spectrum

A design method, helicopter technology, applied in design optimization/simulation, instruments, geometric CAD, etc., can solve problems such as catastrophic accidents, reducer damage, loss of transmission power, etc., to achieve the effect of improving safety

Active Publication Date: 2022-04-22
CHINA HELICOPTER RES & DEV INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] There is a possibility of oil leakage during the use of the helicopter reducer, and even light leakage in serious cases. When the oil pressure is lower than the allowable minimum working pressure, the main reducer will enter a dry running state, causing the reducer to be damaged in a short time. Loss of ability to transfer power, causing catastrophic accidents

Method used

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Embodiment Construction

[0024] An embodiment of the present invention provides a method for designing a helicopter dry-running power spectrum, the method comprising:

[0025] (1) Determine the typical flight profile of transmission system lubrication failure, covering all possible flight states during return or landing, mainly including forward flight, simulated autorotation and landing.

[0026] (2) Determine the duration and specific flight parameters of each flight state in the flight profile:

[0027] The total flight time for a Category A rotorcraft dry run is 30 minutes. in:

[0028] ①Forward flight state: maintain the flight time with the maximum gross weight and the minimum torque necessary for the most effective flight state for 29 minutes and 25 seconds, the maximum gross weight is the maximum take-off weight in the weight envelope, the flight altitude is the preset altitude, and the temperature is the temperature The maximum temperature in the envelope, the flight speed is the most favor...

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Abstract

The invention belongs to the technical field of helicopter design and discloses a method for designing a power spectrum of a helicopter in dry operation. Including: when the main reducer of the helicopter has a lubrication failure, determine the three flight states of the helicopter; determine the flight parameters of each flight state in the three flight states of the helicopter; determine the corresponding flight state according to the flight parameters of each flight state. According to the flight performance calculation model corresponding to each flight state, calculate the required power of the main reducer, main rotor blade, and tail rotor blade in the corresponding flight state; The required power of blades and tail rotor blades is used as the dry-running power spectrum of the helicopter to ensure the ability to continue flying when the main reducer is dry-running due to lubricating oil failure, and to improve the safety of the helicopter.

Description

technical field [0001] The invention belongs to the technical field of helicopter design, in particular to a method for designing a helicopter dry-running power spectrum. Background technique [0002] There is a possibility of oil leakage during the use of the helicopter reducer, and even light leakage in serious cases. When the oil pressure is lower than the allowable minimum working pressure, the main reducer will enter a dry running state, causing the reducer to be damaged in a short time. The function of transmitting power is lost, causing catastrophic accidents. [0003] In order to ensure the survivability of the helicopter, China Civil Aviation Regulations CCAR-29 stipulates that the dry running time of the reducer of the rotor drive system of a category A rotorcraft is not less than 30 minutes. When the main reducer of the helicopter has a failure or failure of the lubricating oil system, a suitable minimum power spectrum that can satisfy the safe return or landing ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F30/20G06F119/02
CPCG06F30/15G06F30/20G06F2119/02
Inventor 陈瑞吴文敏徐玉貌徐朝梁刘文琦
Owner CHINA HELICOPTER RES & DEV INST
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