초록 ▼

A method of processing revolution to revolution blade track height and timing data so that mechanical and dynamic stability, maladjustments, and defects are discovered in a rotor with a plurality of blades on a vertical lift aircraft. Tracking devices collect blade track height and timing data. That

A method of processing revolution to revolution blade track height and timing data so that mechanical and dynamic stability, maladjustments, and defects are discovered in a rotor with a plurality of blades on a vertical lift aircraft. Tracking devices collect blade track height and timing data. That data are processed into track and lead-lag data sets. Data set values are sorted maximum to minimum, or in reverse order, to remove the chaotic character of the collected data, thereby adding coherence and linearity to it. Defects and maladjustments are found by analyzing processed aircraft flight condition data combined in various ways. Only ground and hover flight condition analysis is required. Data collection and analysis is very rapid and the analysis output is presented graphically. The analyzed data are available moments after collection. Significant operational, safety, and cost saving are achieved.

대표청구항 ▼

The invention claimed is: 1. A method of processing blade tracking height and timing (lead-lag) data for a plurality of 50 or more revolutions of a rotor with a plurality of blades to detect defects, if any, in at least one rotor with a plurality of blades of a rotary wing or tilt rotor aircraft, wh

The invention claimed is: 1. A method of processing blade tracking height and timing (lead-lag) data for a plurality of 50 or more revolutions of a rotor with a plurality of blades to detect defects, if any, in at least one rotor with a plurality of blades of a rotary wing or tilt rotor aircraft, where a defect corresponds to a fault or failure, including maladjustments, of any part of the rotor with a plurality of blades, comprising:a. tracking data are collected and stored in a computer for each revolution of a rotor with a plurality of blades, and for each of one or a plurality of steady state flight conditions of the aircraft under test, for determining average track height and absolute lead-lag values for each revolution of the rotor with a plurality of blades and segregating the values into data sets of track height and lead-lag;b. using the computer to sort the stored track heights and lead-lag data sets; whereini. each data set of a rotor with a plurality of blades is sorted so the values of the individual blade track height or lead-lag, are arranged from maximum value to minimum value, or in reverse order;ii. the distribution of values of each individual blade track height or lead-lag places anomalous or major variations values at its extremes;iii. the distribution of individual blade track height or lead-lag reveals the motion of the blades on a rotor with a plurality of blades and the motion is defined by the variation about median values;c. the collected data and sorted data are stored separately so that the collected data are preserved and sorted data are used to analyze the condition of the rotor with a plurality of blades; whereini. the slope of the distribution of track height data defines the relative power necessary to drive each individual blade and blade tendencies to climb or dive on a rotor with a plurality of blades;ii. the distribution of the lead-lag data defines the effectiveness of the damping system and the drag and weight imbalance in the lateral plane of rotation of a rotor with a plurality of blades;iii. the distribution of individual blade track heights or lead-lag of individual blades of a rotor with a plurality of blades are compared one to another in either track height or lead lag or in combination to determine the dynamic tendencies of the blades or rotor, rotor component interactions, rotor or blades anomalous behavior, and defects of the rotor with a plurality of blades;d. the distribution data of track heights and lead-lag are displayed graphically for use in maintenance or the safe operation of the aircraft.