CN116353838A - Oscillation monitoring method for monitoring aircraft control surface - Google Patents
Oscillation monitoring method for monitoring aircraft control surface Download PDFInfo
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- CN116353838A CN116353838A CN202211714064.9A CN202211714064A CN116353838A CN 116353838 A CN116353838 A CN 116353838A CN 202211714064 A CN202211714064 A CN 202211714064A CN 116353838 A CN116353838 A CN 116353838A
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Abstract
The invention provides an oscillation monitoring method for monitoring a control surface of an aircraft, which comprises the following steps: step one, identifying the oscillation frequency of a controlled object servo electrohydraulic valve; selecting an actuator model monitoring threshold and monitoring time according to the oscillation frequency; and thirdly, monitoring the control surface according to the monitoring threshold and time. The invention realizes real-time monitoring of the motion condition of the control surface, can prevent the action frequency of the control surface from exceeding the normal range, and reduces the negative influence of the vibration of the control surface on the structural stability of the aircraft; the threshold parameters of the EHSV monitor are adjusted according to different oscillation frequencies, so that the EHSV monitor can be suitable for different working condition scenes, accurate monitoring of an actuator control electronic device system is realized, and the safety and stability of the system are improved.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to an oscillation monitoring method for monitoring a control surface of an aircraft.
Background
The fly-by-wire control system of the fixed wing aircraft comprises a health monitoring system for monitoring each actuator subsystem. Current health monitoring systems focus on monitoring components to identify component failures or signs of component failures that may occur.
The current implementation mode of the health monitoring system in the fly-by-wire control system of the fixed wing aircraft is to collect feedback data through the associated sensors to perform monitoring so as to realize the purpose of monitoring the monitored object or component. For example, ailerons are control surfaces attached to the trailing edge of an aircraft wing for controlling the pitch angle by varying the lift on the wing, thereby controlling the aircraft in roll motion. Determining whether an aileron control system has failed or is likely to fail is particularly important for aircraft operation. In the case of fuselage or wing resonances, the aileron control surface oscillations at certain frequencies and at sufficient amplitude may cause excessive fatigue or failure of the aircraft structure. Oscillations may occur if a component of the aileron control system fails or operates improperly.
The oscillation frequency is identified only by the control surface position signal, and the influence of the position signal of the actuator on the control surface oscillation is ignored. Under the motion condition, the control surface is provided with a plurality of oscillation frequencies, and the influence of different frequencies on the structural stability of the control surface is different, so that the aim of accurately monitoring the actuator control electronic device system cannot be achieved by the existing method.
Disclosure of Invention
In view of this, the embodiments of the present disclosure provide an oscillation monitoring method for monitoring a control surface of an aircraft, so as to achieve the purpose of accurately monitoring an actuator control electronic device system.
The embodiment of the specification provides the following technical scheme: a vibration monitoring method for monitoring a control surface of an aircraft comprises the following steps:
step one, identifying the oscillation frequency of a controlled object servo electrohydraulic valve;
selecting an actuator model monitoring threshold and monitoring time according to the oscillation frequency;
and thirdly, monitoring the control surface according to the monitoring threshold and time.
Further, the first step includes: and the control electronic device responds to the control instruction to send a command to the actuator so as to control the control surface, and the data feedback acquisition system acquires a control surface position error signal.
Further, the first step further includes: when the control surface error signal exceeds the error threshold value, the data feedback acquisition system acquires the position signal of the electro-hydraulic servo valve of the actuator, calculates the difference value between the model signal of the electro-hydraulic servo valve of the actuator and the position signal of the electro-hydraulic servo valve of the actuator, takes the oscillation period of the position signal as the three-time polarity inversion time if the difference value signal of the electro-hydraulic servo valve of the actuator continuously turns three times, and calculates the oscillation frequency of the signal according to the three-time polarity inversion time.
Further, the first step further includes: when the control surface error signal does not exceed the error threshold value, the default oscillation frequency is 0hz, and other monitors monitor the fault threshold value to select the fault threshold value corresponding to the frequency of 0 hz.
Further, the second step includes: if the oscillation frequency is greater than the frequency limit value, generating a fault indication and triggering a safety warning mode; and if the oscillation frequency is within the limit range of the oscillation frequency, selecting monitor parameters corresponding to the oscillation frequency by the monitoring time and the fault threshold value of the electro-hydraulic servo valve monitor of the actuator.
Further, the third step specifically comprises: selecting monitor parameters according to oscillation frequency, monitoring the absolute value of a difference value of an electro-hydraulic servo valve of an actuator, and generating a fault signal when the difference value exceeds a threshold value and the maintenance time exceeds the monitoring time by adopting an up-down counting method; and if the difference value does not exceed the threshold value or the maintenance time does not exceed the monitoring time, generating a normal signal.
Compared with the prior art, the beneficial effects that above-mentioned at least one technical scheme that this description embodiment adopted can reach include at least: the invention realizes real-time monitoring of the motion condition of the control surface, can prevent the action frequency of the control surface from exceeding the normal range, and reduces the negative influence of the vibration of the control surface on the structural stability of the aircraft; the threshold parameters of the EHSV monitor are adjusted according to different oscillation frequencies, so that the EHSV monitor can be suitable for different working condition scenes, accurate monitoring of an actuator control electronic device system is realized, and the safety and stability of the system are improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a flow chart of a method of monitoring oscillations of a control surface of an aircraft;
FIG. 2 is a flow chart for identifying oscillation frequencies;
FIG. 3 is a flow chart of control surface monitoring.
Detailed Description
Embodiments of the present application are described in detail below with reference to the accompanying drawings.
It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other. The invention will be described in detail below with reference to the drawings in connection with embodiments.
As shown in fig. 1 to 3, an embodiment of the present invention provides an oscillation monitoring method for monitoring a control surface of an aircraft, which specifically includes the following steps:
1. and continuously acquiring three beats of data of the control surface position error signal in a single task period by the data feedback acquisition system, and performing filtering processing. If the filtered control surface position error signal err_pos is in the error threshold (-err_th, +err_th) range, the default oscillation frequency f=0hz, and the fault threshold value and the monitoring time of an electro-hydraulic servo valve (EHSV) monitor of the actuator are selected as the frequency f 0 Corresponding fault threshold value set { Err_TH } f＝0 }. If the filtered control surface position error signal err_pos exceeds an error threshold, a control surface error overrun indication poser_gz=1 is generated.
2. When poser_gz=1, actuator EHSV position signal data is collected in a task cycle, and an EHSV model position signal is calculated depending on an EHSV position model according to an actual EHSV input command (actuator electrohydraulic servo valve position model signal is calculated by substituting a control command into the EHSV position model). Thereby obtaining a difference D between the EHSV position signal and the model position signal pos (the difference value of the position signals of the actuator electro-hydraulic servo valve is the difference value of the position signals of the actuator electro-hydraulic servo valve acquired by a data feedback acquisition system and the position model signals of the actuator electro-hydraulic servo valve calculated by an EHSV position model). Recording the time length t of 3 times of turning the polarity of the difference signal, and vibrating the position signalThe oscillation period t=t. Thus, the signal oscillation frequency f=1/t is calculated. If the oscillation frequency f>f limit (oscillation frequency limit value f) limit ) Then a fault indication f_gz=1 is generated and a security alert mode is triggered. If the oscillation frequency is within the oscillation frequency limit range (0, f TH ]If the EHSV monitor fault threshold and the monitoring time are within the threshold, the EHSV monitor fault threshold and the monitoring time are selected as Err-TH f＝1/t 、Tm f＝1/t 。
3. Comparing the difference between the position signals with the failure threshold value, if D pos >Err_TH f＝1/t Then cnt adds 1 itself, otherwise subtracts 1. When cnt>Tm f＝1/t Generating an electrohydraulic servo valve fault indication valid=0, otherwise maintaining the previous duty cycle. If cnt=0, then generating an electrohydraulic servo valve normal indication valid=1.
The invention realizes real-time monitoring of the motion condition of the control surface, can prevent the action frequency of the control surface from exceeding the normal range, and reduces the negative influence of the vibration of the control surface on the structural stability of the aircraft. The threshold parameters of the EHSV monitor are adjusted according to different oscillation frequencies, so that the EHSV monitor can be suitable for different working condition scenes, accurate monitoring of an actuator control electronic device system is realized, and the safety and stability of the system are improved.
The foregoing description of the embodiments of the invention is not intended to limit the scope of the invention, so that the substitution of equivalent elements or equivalent variations and modifications within the scope of the invention shall fall within the scope of the patent. In addition, the technical characteristics and technical scheme, technical characteristics and technical scheme can be freely combined for use.
Claims (6)
1. The oscillation monitoring method for monitoring the control surface of the aircraft is characterized by comprising the following steps of:
step one, identifying the oscillation frequency of a controlled object servo electrohydraulic valve;
selecting an actuator model monitoring threshold and monitoring time according to the oscillation frequency;
and thirdly, monitoring the control surface according to the monitoring threshold and time.
2. The method of claim 1, wherein the first step comprises: and the control electronic device responds to the control instruction to send a command to the actuator so as to control the control surface, and the data feedback acquisition system acquires a control surface position error signal.
3. The method of claim 2, wherein the step one further comprises:
when the control surface error signal exceeds the error threshold value, the data feedback acquisition system acquires the position signal of the electro-hydraulic servo valve of the actuator, calculates the difference value between the model signal of the electro-hydraulic servo valve of the actuator and the position signal of the electro-hydraulic servo valve of the actuator, takes the oscillation period of the position signal as the three-time polarity inversion time if the difference value signal of the electro-hydraulic servo valve of the actuator continuously turns three times, and calculates the oscillation frequency of the signal according to the three-time polarity inversion time.
4. The method of claim 3, wherein the first step further comprises:
when the control surface error signal does not exceed the error threshold value, the default oscillation frequency is 0hz, and other monitors monitor the fault threshold value to select the fault threshold value corresponding to the frequency of 0 hz.
5. The method for monitoring oscillations about a control surface of an aircraft according to claim 4, wherein said step two comprises:
if the oscillation frequency is greater than the frequency limit value, generating a fault indication and triggering a safety warning mode;
and if the oscillation frequency is within the limit range of the oscillation frequency, selecting monitor parameters corresponding to the oscillation frequency by the monitoring time and the fault threshold value of the electro-hydraulic servo valve monitor of the actuator.
6. The method for monitoring oscillation of a control surface of an aircraft according to claim 5, wherein the third step is specifically: selecting monitor parameters according to oscillation frequency, monitoring the absolute value of a difference value of an electro-hydraulic servo valve of an actuator, and generating a fault signal when the difference value exceeds a threshold value and the maintenance time exceeds the monitoring time by adopting an up-down counting method; and if the difference value does not exceed the threshold value or the maintenance time does not exceed the monitoring time, generating a normal signal.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211714064.9A CN116353838A (en) | 2022-12-29 | 2022-12-29 | Oscillation monitoring method for monitoring aircraft control surface |
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| CN202211714064.9A CN116353838A (en) | 2022-12-29 | 2022-12-29 | Oscillation monitoring method for monitoring aircraft control surface |
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