CN109240327B - Method for identifying flight phase of fixed-wing aircraft - Google Patents

Abstract

The invention relates to a method for identifying the flight phase of a fixed-wing aircraft, which is used for identifying and dividing the flight phase of the flight process based on relevant flight parameters in flight parameter data. The method comprises the steps of firstly processing and smoothing data, then solving first-order and second-order derivation of the air pressure altitude to time, solving inflection points of a curve, respectively taking the first inflection point and the last inflection point as a flying starting point and a landing point, respectively further identifying the ground flying state and the air flying state according to the flying starting point and the landing point, and finally completely identifying stages of flight preparation, taxiing, taking off, climbing, cruising, maneuvering flying, descending, approaching, landing, re-flying and the like. The flight phase identification method is based on data acquired by flight parameters, carries out flight phase identification on the fixed-wing aircraft, and provides basic data for deep analysis of the flight parameter data and aircraft maintenance guarantee.

Description

Method for identifying flight phase of fixed-wing aircraft

Technical Field

The invention belongs to the technical field of avionics, and relates to a flight phase identification method based on flight parameter data.

Background

Under the background that the utilization value of the flight parameter data is higher and higher, the flight parameter data is deeply utilized, and the identification of the flight phase of the airplane is the basis for deep data analysis. Particularly in the field of flight parameter data interpretation and flight parameter data mining, flight phase identification is a problem to be dealt with first. The flight phase identification is influenced by multiple factors such as external environment, flight control and the like, so that the boundary conditions among the phases are not fixed, the airplane phase identification is difficult, and particularly the flight phase identification of military airplanes is more difficult.

The patent provides a flight phase identification method of a fixed wing aircraft, which utilizes the characteristics of an air pressure altitude curve in the flight process to calculate the first and second derivatives of the curve to time, calculates the air pressure altitude inflection point according to the derivative, firstly identifies the ground and air states of the aircraft by utilizing the first and last inflection points, and then utilizes other parameter information to carry out detailed division on each phase in the flight process, and finally realizes accurate identification on the phases of flight preparation, taxiing, taking off, climbing, cruising, maneuvering flight, descending, approaching, landing, re-flying and the like.

Disclosure of Invention

The purpose of the invention is as follows:

researching a method capable of obtaining the main flight parameters in the flight parameter data, such as: the method comprises the steps of identifying and dividing flight stages of flight preparation, gliding, taking-off, climbing, cruising, descending, approaching, landing, re-flying and the like in the whole flight process of the airplane from data, and providing a basis for deep analysis of flight parameter data and troubleshooting of the airplane.

The technical scheme is as follows:

a method for identifying the flight phase of a fixed-wing aircraft is characterized by comprising the following steps:

the method comprises the following steps: extracting flight parameter data and processing the flight parameter data;

step two: and (3) calculating the derivative and the inflection point of the air pressure height data curve: smoothing the air pressure height data by using a mean value filtering method, respectively solving a first derivative and a second derivative of the air pressure height data on a time variable, and forming a first derivative sequence and a second derivative sequence; then, according to the position of the maximum value of the second derivative sequence, obtaining inflection points of the air pressure height curve, and recording relative time points corresponding to the inflection points;

step three: identifying a takeoff phase and a landing phase;

step four: identifying initial climbing and approaching stages;

step five: identifying the flight preparation, taxiing phases of the ground:

step six: identifying stages of climbing, descending, cruising, maneuvering flight and the like in the air;

step seven: and identifying a missed approach stage.

In the first step, the flight parameter data is extracted and processed to realize; extracting data of air pressure altitude, pitch angle, roll angle, radio altitude, indicated airspeed and engine high-pressure rotor rotating speed from data recorded by flight parameter equipment, and forming a one-dimensional array by the data of each parameter according to a time sequence; because the sampling rates of all parameters are different, in order to facilitate processing and maintain the characteristics of data, the data needs to be processed into data of one sampling point per second; and for the parameter with the sampling rate larger than 1, carrying out weighted average on the sampling point data of each second to form new data at the moment. And for the parameter with the sampling rate less than 1, linearly calculating new data at the current moment according to the data of the front and rear sampling points by adopting a linear interpolation method.

In the third step, the identification method of the takeoff phase and the landing phase comprises the following steps: according to the time sequence of the inflection points of the air pressure altitude curve, extracting a first inflection point and a last inflection point in the step two, wherein the first inflection point corresponds to a flying point and the last inflection point corresponds to a landing point; then, with time as a reference, searching forward a critical time point indicating that the airspeed is 60km/h from the moment corresponding to the departure point, wherein the point is the starting point of the takeoff stage, and searching backward a critical time point with the radio height greater than 10m from the moment corresponding to the departure point, wherein the point is the ending point of the takeoff stage; and finally, searching a critical point with the pitch angle larger than 1 degree forwards from the moment corresponding to the landing point, wherein the critical point is the starting point of the landing stage, and searching a critical point indicating that the airspeed is reduced to 60km/h backwards from the moment corresponding to the landing point, wherein the moment is the finishing point of the landing stage.

In the fourth step, the identification method of the initial climbing and approaching stage comprises the following steps: firstly, extracting a second inflection point obtained in the second step according to the time sequence, wherein the inflection point corresponds to an initial climbing end point, and determining the initial climbing stage by taking an end point of a takeoff stage calculated in the third step as a starting point of initial climbing; then, an inflection point of the barometric altitude is searched forward from the start point of landing in step three, and the inflection point corresponds to an approaching start point, and the approaching end point is the start point of landing.

In the fifth step, the method for identifying the flight preparation and the taxiing stage on the ground comprises the following steps: recording from the beginning of data to the starting point of a takeoff phase, wherein the time interval is a ground phase before takeoff and comprises two phases of flight preparation and taxiing; searching for the starting moment with the continuous airspeed of more than 5km/h for 3 seconds from the data record, wherein the time point is a dividing point of a flight preparation stage and a pre-takeoff taxiing stage, the time point from the data start is the flight preparation stage, the time point is the starting point of the flight preparation stage and the pre-takeoff stage, and the time period is the pre-takeoff taxiing stage; and recording or indicating the airspeed less than or equal to 0km/h from the end point of the landing stage to the end of the data, wherein the time period is the taxiing stage after landing.

In the sixth step, the identification method for the climbing, descending, cruising and maneuvering flight stages in the air comprises the following steps:

in the flight stage from the initial climbing end to the approaching starting point, the time period is divided into a plurality of subintervals according to inflection point information of the barometric altitude curve, each interval corresponds to a flight state, and climbing, descending, cruising and maneuvering flight in the air can occur in the stage according to different flight conditions;

climbing recognition: when the first derivative of the air pressure height is larger than 0, the pitch angle is in the range of [ 0-30 ] degrees, and the roll angle is in the range of +/-30 degrees, the climbing stage is determined;

a descending stage, namely when the first derivative of the air pressure height is less than 0, the pitch angle is in the range of [ -30-0 ] degrees, and the roll angle is in the range of +/-30 degrees, the descending stage is performed;

and (3) cruising: when the first derivative of the air pressure height is equal to 0, the pitch angle is within the range of +/-10 degrees, and the roll angle is within the range of +/-30 degrees, indicating that the airspeed change rate is within +/-20 km/h as a cruising stage;

a maneuvering flight phase: when the flight state is not in the three states, the maneuver flight phase is determined.

In the seventh step, the identification method of the missed approach stage comprises the following steps:

checking whether a time period that the difference value of the air pressure height and the air pressure height of the departure point is less than 200m exists between the initial climbing end point and the approach starting point identified in the fourth step, and if the time period does not exist, no re-flying stage exists; if the time interval exists and the engine speed is changed from small to large in the time interval, the fly-back action is considered, and the fly-back phase starts with the engine speed change rate as positive until the first derivative of the air pressure height is greater than 0 and lasts for 10 times.

Description of the drawings:

FIG. 1 is a schematic view of a barometric altitude map and an inflection point thereof during flight.

Has the advantages that:

the invention provides a method for identifying a flight phase of a fixed-wing aircraft, which can identify the flight phase of the aircraft according to part of flight parameters acquired by flight parameters, provides basic data for deep analysis of the flight parameters and fault interpretation of aircraft equipment, and has the following main beneficial effects:

a) provide the basis for the analysis of flight parameter data

The flight parameter data analysis can be performed in-depth analysis on the flight data by combining the flight state of the airplane, so that technical support is provided.

b) Providing support for aircraft equipment fault diagnosis

The fault diagnosis of the airplane equipment is closely related to the use state of the airplane, and the use state of the airplane provides a precondition for the fault diagnosis of the airplane equipment, so that the flight phase of the airplane is a precondition for carrying out the fault diagnosis of the equipment.

c) Providing support for improving flight technique

The flight phase is a precondition for identifying and judging the flight action, and provides technical support for identifying and evaluating the flight action.

The implementation mode is as follows:

the method for identifying the flight phase of the fixed-wing aircraft is implemented according to the following steps:

the method comprises the following steps: extracting and processing flight parameters data

And downloading the data in the flight parameter recording equipment and restoring. And extracting the original data of parameters such as air pressure altitude, pitch angle, roll angle, radio altitude, indicated airspeed, engine high-pressure rotor rotating speed and the like from the reduced flying parameter data, and forming a one-dimensional array according to the time sequence. And forming a new data value for multiple sampling points of each parameter within one second by adopting a weighted average or linear interpolation method, so that each parameter only has data of one sampling point within each second.

Step two: derivation and inflection point of air pressure height data curve

And smoothing the air pressure height data by using a mean value filtering method, respectively solving a first derivative and a second derivative of the air pressure height data on a time variable, and forming a first derivative sequence and a second derivative sequence. Then, according to the position of the maximum value of the second derivative sequence, the inflection points of the air pressure height curve are obtained, and the relative time point corresponding to each inflection point is recorded, so that the whole flight process can be divided into a plurality of stages.

Step three: identifying takeoff and landing phases

And (4) extracting the first inflection point and the last inflection point in the step (II) according to the time sequence of the inflection points of the air pressure altitude curve, wherein the first inflection point corresponds to a flying point, and the last inflection point corresponds to a landing point.

Then, on the basis of time, searching a critical time point indicating that the airspeed is 60km/h from the moment corresponding to the departure point forward, wherein the point is the starting point of the takeoff phase, and searching a critical time point with the radio height of more than 10m from the moment corresponding to the departure point backward, wherein the point is the ending point of the takeoff phase.

And finally, searching a critical point with the pitch angle larger than 1 degree forwards from the moment corresponding to the landing point, wherein the critical point is the starting point of the landing stage, and searching a critical point indicating that the airspeed is reduced to 60km/h backwards from the moment corresponding to the landing point, wherein the moment is the finishing point of the landing stage.

Step four: identifying initial climb, approach phases

Firstly, extracting a second inflection point obtained in the second step according to the time sequence, wherein the inflection point corresponds to an initial climbing end point, and determining the initial climbing stage by taking an end point of a takeoff stage calculated in the third step as a starting point of initial climbing; then, an inflection point of the barometric altitude is searched forward from the start point of landing in step three, and the inflection point corresponds to an approaching start point, and the approaching end point is the start point of landing.

Step five: identifying ground flight preparation and taxiing phases

The time interval is the ground stage before takeoff and comprises two stages of flight preparation and taxiing. And searching for the starting moment with the continuous airspeed of more than 5km/h from the beginning of data recording, wherein the time point is a dividing point of a flight preparation stage and a pre-takeoff taxiing stage, the time point from the beginning of data is the flight preparation stage, the time point is the starting point of the takeoff stage, and the time period is the pre-takeoff taxiing stage. And recording or indicating the airspeed less than or equal to 0km/h from the end point of the landing stage to the end of the data, wherein the time period is the taxiing stage after landing.

Step six: identifying phases of climbing, descending, cruising, maneuvering flight, etc. in the air

The method comprises the steps of identifying a flight stage from the initial climbing end to the approaching starting point, dividing the time period into a plurality of sub-intervals according to inflection point information of an air pressure altitude curve, wherein each interval corresponds to a flight state, and climbing, descending, cruising, maneuvering flight and the like in the air can possibly occur in the stage according to different flight conditions.

Climbing recognition: and when the first derivative of the air pressure height is greater than 0, the pitch angle is in the range of [ 0-30 ] degrees, and the roll angle is in the range of +/-30 degrees, the climbing stage is determined.

And a descending stage, namely when the first derivative of the air pressure height is less than 0, the pitch angle is in the range of [ -30-0 ] degrees, and the roll angle is in the range of +/-30 degrees.

And (3) cruising: when the first derivative of the barometric altitude is equal to 0 and the pitch angle is within a range of +/-10 degrees and the roll angle is within a range of +/-30 degrees, the cruise phase is indicated as the airspeed change rate of +/-20 km/h.

A maneuvering flight phase: when the flight state is not in the three states, the maneuver flight phase is determined.

Step seven: identifying missed approach phases

And checking whether a time period with the difference value between the air pressure height and the air pressure height of the departure point being less than 200m exists between the initial climbing end point and the approaching starting point identified in the fourth step, and if the time period does not exist, not having a missed approach stage. If the time interval exists and the engine speed is changed from small to large in the time interval, the fly-back action is considered, and the fly-back phase starts with the engine speed change rate as positive until the first derivative of the air pressure height is greater than 0 and lasts for 10 times.

Claims (2)

1. A method for identifying the flight phase of a fixed-wing aircraft is characterized by comprising the following steps:

the method comprises the following steps: extracting flight parameter data and processing the flight parameter data;

step two: and (3) calculating the derivative and the inflection point of the air pressure height data curve: smoothing the air pressure height data by using a mean value filtering method, respectively solving a first derivative and a second derivative of the air pressure height data on a time variable, and forming a first derivative sequence and a second derivative sequence; then, according to the position of the maximum value of the second derivative sequence, obtaining inflection points of the air pressure height curve, and recording relative time points corresponding to the inflection points;

step three: identifying a takeoff phase and a landing phase; according to the time sequence of the inflection points of the air pressure altitude curve, extracting a first inflection point and a last inflection point in the step two, wherein the first inflection point corresponds to a flying point and the last inflection point corresponds to a landing point; then, with time as a reference, searching forward a critical time point indicating that the airspeed is 60km/h from the moment corresponding to the departure point, wherein the point is the starting point of the takeoff stage, and searching backward a critical time point with the radio height greater than 10m from the moment corresponding to the departure point, wherein the point is the ending point of the takeoff stage; finally, searching a critical point with the pitch angle larger than 1 degree forwards from the moment corresponding to the landing point, wherein the point is the starting point of the landing stage, and searching a critical point indicating that the airspeed is reduced to 60km/h backwards from the moment corresponding to the landing point, wherein the moment is the ending point of the landing stage;

step four: identifying initial climbing and approaching stages; firstly, extracting a second inflection point obtained in the second step according to the time sequence, wherein the inflection point corresponds to an initial climbing end point, and determining the initial climbing stage by taking an end point of a takeoff stage calculated in the third step as a starting point of initial climbing; then, searching an inflection point of the air pressure altitude from the landing starting point in the third step forward, wherein the inflection point corresponds to an approaching starting point, and the approaching ending point is the landing starting point;

step five: identifying the flight preparation, taxiing phases of the ground: recording from the beginning of data to the starting point of a takeoff phase, wherein the time interval is a ground phase before takeoff and comprises two phases of flight preparation and taxiing; searching for the starting moment with the continuous airspeed of more than 5km/h for 3 seconds from the data record, wherein the time point is a dividing point of a flight preparation stage and a pre-takeoff taxiing stage, the time point from the data start is the flight preparation stage, the time point is the starting point of the flight preparation stage and the pre-takeoff stage, and the time period is the pre-takeoff taxiing stage; recording or indicating airspeed less than or equal to 0km/h from the end point of the landing stage to the end of data, wherein the time period is a gliding stage after landing;

step six: identifying stages of climbing, descending, cruising, maneuvering flight and the like in the air; in the flight stage from the initial climbing end to the approaching starting point, the time period is divided into a plurality of subintervals according to inflection point information of the barometric altitude curve, each interval corresponds to a flight state, and climbing, descending, cruising and maneuvering flight in the air can occur in the stage according to different flight conditions;

climbing recognition: when the first derivative of the air pressure height is larger than 0, the pitch angle is in the range of [0 to 30] degrees, and the roll angle is in the range of +/-30 degrees, the climbing stage is determined;

a descending stage, namely when the first derivative of the air pressure height is less than 0, the pitch angle is in the range of [ -30 to 0] degrees, and the roll angle is in the range of +/-30 degrees, the descending stage is performed;

and (3) cruising: when the first derivative of the air pressure height is equal to 0, the pitch angle is within the range of +/-10 degrees, and the roll angle is within the range of +/-30 degrees, indicating that the airspeed change rate is within +/-20 km/h as a cruising stage;

a maneuvering flight phase: when the flight state is not in the three states, the flight state belongs to a maneuvering flight stage;

step seven: identifying a missed approach stage; checking whether a time period that the difference value of the air pressure height and the air pressure height of the departure point is less than 200m exists between the initial climbing end point and the approach starting point identified in the fourth step, and if the time period does not exist, no re-flying stage exists; if the time interval exists and the engine speed is changed from small to large in the time interval, the fly-back action is considered, and the fly-back phase starts with the engine speed change rate as positive until the first derivative of the air pressure height is greater than 0 and lasts for 10 times.

2. The method for identifying the flight phase of the fixed-wing aircraft according to claim 1, wherein in the first step, the extracting and processing of the flight parameter data are implemented as; extracting data of air pressure altitude, pitch angle, roll angle, radio altitude, indicated airspeed and engine high-pressure rotor rotating speed from data recorded by flight parameter equipment, and forming a one-dimensional array by the data of each parameter according to a time sequence; because the sampling rates of all parameters are different, in order to facilitate processing and maintain the characteristics of data, the data needs to be processed into data of one sampling point per second; for the parameter with the sampling rate more than 1, carrying out weighted average on the sampling point data of each second to form new data at the moment; and for the parameter with the sampling rate less than 1, linearly calculating new data at the current moment according to the data of the front and rear sampling points by adopting a linear interpolation method.

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