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A method for generating azimuth signal based on helicopter rotor speed

A technology of helicopter rotor and rotor speed, which is applied in the direction of aircraft parts, aircraft component testing, complex mathematical operations, etc., can solve the problems of signal loss, manpower, material resource waste, etc., to save manpower, avoid azimuth signal loss, and large-scale engineering applications value effect

Active Publication Date: 2022-05-31
CHINA HELICOPTER RES & DEV INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This method of obtaining the azimuth angle not only causes a certain waste of manpower and material resources, but also the obtained azimuth angle signal is often missing due to the test equipment.

Method used

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  • A method for generating azimuth signal based on helicopter rotor speed
  • A method for generating azimuth signal based on helicopter rotor speed
  • A method for generating azimuth signal based on helicopter rotor speed

Examples

Experimental program
Comparison scheme
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Embodiment 1

[0033] like figure 1 As shown, a method for generating an azimuth signal based on the rotor speed of a helicopter comprises the following steps:

[0034] S1: Obtain the rotor speed percentage; for a certain type of helicopter, during the rotor rotation process, the flight parameter system measures and records the actual main rotor speed and tail rotor speed in each state with a total of 16, and calculates the speed percentage in each state ; The data are shown in Table 1, and the speed change trend line is shown in figure 2 .

[0035] Table 1 Partial rotational speed data of a certain model

[0036] data serial number 1 2 3 4 5 6 7 8 Rotating speed(%) 4.0237 4.0237 4.0237 4.1331 4.1331 4.1331 4.1331 4.1331 data serial number 9 10 11 12 13 14 15 16 Rotating speed(%) 4.2346 4.2346 4.2346 4.2346 4.2346 4.2346 4.3518 4.3518

[0037] S2: Calculate the instantaneous rotational speed; by multiplying the rotational speed...

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Abstract

The invention belongs to the technical field of helicopter structure fatigue design, and particularly relates to a method for generating an azimuth angle signal based on the rotation speed of a helicopter rotor. Specifically, it includes the following steps: S1: obtain the rotor speed percentage; S2: calculate the instantaneous speed; S3: determine the speed data sampling rate and the load data sampling rate; S4: establish an azimuth initial sequence; S5: generate an azimuth signal. The invention is a method for generating an azimuth signal based on the rotation speed of the helicopter rotor, which does not need to test and refit the helicopter, saves a lot of manpower and material resources, and also avoids the phenomenon of loss of the azimuth signal caused by the failure of the test equipment. Load separation and extraction of characteristic parameters provide convenience and have great engineering application value.

Description

technical field [0001] The invention belongs to the technical field of helicopter structural fatigue design, and in particular relates to a method for generating an azimuth signal based on a helicopter rotor speed. Background technique [0002] Due to the structural characteristics of the helicopter, the periodic characteristics of the structural load are very obvious, generally an integer multiple of the rotor speed. For flight measured loads, the steady-state loads and dynamic loads in the measured loads can generally be separated according to the load cycle, and the separated loads can be used for rapid damage calculation of components, compilation of fatigue load spectrum and component life prediction. The reasonable load separation period should not be lower than the main wave period of the load, and can usually be determined according to the fundamental frequency period of the main load source, that is, the azimuth signal of the main rotor or tail rotor. [0003] The ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/60B64D43/00G06F17/11
CPCB64F5/60B64D43/00G06F17/11Y02T90/00
Inventor 陶宪斌汪振兴杨昌付裕曾玖海吴堂珍
Owner CHINA HELICOPTER RES & DEV INST