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Calculation method for improving balancing convergence of rotor with large forward ratio

A calculation method and forward ratio technology, applied in design optimization/simulation, special data processing applications, instruments, etc., can solve problems such as difficulty in calculation of rotor trim with large forward ratio and variable speed, and achieve the effect of avoiding divergence problems.

Active Publication Date: 2020-12-08
CHINA HELICOPTER RES & DEV INST
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Problems solved by technology

[0004] Technical problem to be solved by the present invention: Propose an iterative calculation method for improving the convergence of large forward ratio rotor trim, which is used for large forward ratio variable speed rotor aeroelastic trim Calculation, to solve the difficult or even occurred problems of rotor trim calculation with large forward ratio and variable speed, and to determine the driver's control and rotor characteristics in the steady flight of the helicopter through simulation analysis in the design stage

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  • Calculation method for improving balancing convergence of rotor with large forward ratio
  • Calculation method for improving balancing convergence of rotor with large forward ratio
  • Calculation method for improving balancing convergence of rotor with large forward ratio

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Embodiment Construction

[0030] The calculation method for improving the convergence of rotor trim with large forward ratio involved in the present invention will be described in further detail below in conjunction with the accompanying drawings.

[0031] An iterative calculation method to improve the convergence of rotor trim with large forward ratio, such as figure 1 shown, including the following steps:

[0032] (1) Establish the rotor dynamics model. Establish the rotor aerodynamic model, consider the nonlinear elastic deformation of the blade flapping, shimmy, torsion and the nonlinear coupling relationship between them, and accurately describe the nonlinear motion of the elastic blade. The coordinate system of the elastic blade is as follows: figure 2 As shown, the geometric relationship between the blade deformed coordinate system E and the blade undeformed coordinate system B is obtained through coordinate transformation, including axial deformation u, shimmy deformation v, and flapping defo...

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Abstract

The invention belongs to the helicopter rotor design and theoretical modeling technology, discloses a calculation method for improving the balancing convergence of a rotor with a large forward ratio,wherein the method adopts a successive approximation method and a residual monitoring method to improve a rotor balancing calculation method, and is different from a traditional balancing iterative calculation method. According to the calculation method for improving the balancing convergence of the rotor with the large forward ratio, encryption division is carried out on forward ratio parameters,a successive approximation method is used for calculating and monitoring residual error changes in an iterative loop in real time, the calculation capacity of rotor trim is effectively expanded, thetrim solving precision is guaranteed, and the divergence problem in trimming iteration is effectively avoided in a large-advance-ratio state.

Description

technical field [0001] The invention belongs to the technology of helicopter rotor design and theoretical modeling, and relates to a calculation method for improving the convergence of trimming of a rotor with a large forward ratio. Background technique [0002] Rotor trim is one of the important links in the analysis and design phase of helicopters. It is of great significance in the analysis of helicopter aerodynamics, dynamics and flight mechanics to determine the cyclical steady-state characteristics of the helicopter and the pilot's manipulation by setting the target in a stable flight state. In the aeroelastic analysis of the rotor with large forward ratio and variable speed, the asymmetry of the paddle-disc airflow is aggravated, and the coupling effect between aerodynamic and structure increases, and weak control changes will bring about strong changes in aerodynamic and structural loads, making the calculation of trim more difficult. It is difficult to converge, so ...

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Application Information

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IPC IPC(8): G06F30/15G06F30/20G06F111/10G06F119/20
CPCG06F30/15G06F30/20G06F2111/10G06F2119/20Y02T90/00
Inventor 余智豪孟微周云宋彬胡和平邓旭东
Owner CHINA HELICOPTER RES & DEV INST
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