A method and system for monitoring and alerting of aircraft performance command

Abstract

The application belongs to the technical field of flight control, and particularly relates to a method and system for monitoring and alarming of an aircraft efficiency adjustment instruction. The method comprises the following steps: S1, collecting an automatic trimming signal; S2, obtaining a corresponding threshold value according to the type of the automatic trimming signal; S3, timing when the automatic trimming signal exceeds the corresponding threshold value; and S4, issuing an alarm signal when the timing of any automatic trimming signal exceeds a set value. The application can timely monitor the efficiency adjustment failure, and is beneficial to the timely disposal of the pilot.

Description

Technical Field

[0001] This application belongs to the field of flight control technology, and specifically relates to a method and system for monitoring and alarming aircraft tuning commands. Background Technology

[0002] Trim control, as a flight control method, allows for manual or automatic issuance of trim commands, reducing the pilot's workload and improving flight safety and economy. Trim control includes two modes: manual and automatic. In manual mode, the pilot issues manual trim commands by pressing a trim button; in automatic mode, the automatic flight control unit generates and outputs automatic trim commands based on the control law calculation results. The trim commands are logically synthesized by a trim command logic switching device, driving the trim electric mechanism.

[0003] As an auxiliary flight function, trim control outputs trim control commands continuously for extended periods, which can cause significant changes in aircraft attitude. The components implementing trim control are mostly mechanical structures, highly susceptible to environmental influences; for example, buttons may stick together, and signal lines may experience short circuits or open circuits. In such situations, abnormal trim signal output can lead to rapid and significant unexpected attitude changes in the aircraft, which, if not addressed promptly, can jeopardize flight safety. Directly restricting trim commands would affect the trim control function, consequently requiring substantial modifications to the flight control system itself. Summary of the Invention

[0004] To address the aforementioned issues, this application provides an aircraft tuning command monitoring and alarm method and system to prevent unexpected tuning commands from being generated due to signal malfunctions or accidental triggering, which could cause drastic changes in aircraft attitude and endanger flight safety.

[0005] The first aspect of this application provides a method for monitoring and alarming aircraft tuning commands, mainly including:

[0006] Step S1: Acquire automatic balancing signals;

[0007] Step S2: Obtain the corresponding threshold value according to the type of automatic balancing signal;

[0008] Step S3: When the automatic balancing signal exceeds its corresponding threshold value, timing is started;

[0009] Step S4: When the timing of any automatic balancing signal exceeds the set value, an alarm signal is issued.

[0010] Preferably, step S1 further includes:

[0011] Step S11: Use resistor current limiting and transient suppression diodes to suppress spike surges in the acquired automatic balancing signal;

[0012] Step S12: The automatic balancing signal is level isolated and converted by the optocoupler.

[0013] Preferably, in step S2, different types of automatic balancing signals are acquired through different channels. The types of automatic balancing signals include upward balancing signals, downward balancing signals, left tilt balancing signals, right tilt balancing signals, left skew balancing signals, and right skew balancing signals.

[0014] Preferably, in step S3, sampling timing begins after the tuning control signal changes from off to on and continues to exceed the start timing threshold, with a sampling period of 3ms.

[0015] Preferably, in step S3, timing is started when the automatic balancing signal of two consecutive sampling periods exceeds its corresponding threshold value.

[0016] Preferably, in step S4, the set value is 0.5s-2s.

[0017] The second aspect of this application provides an aircraft tuning command monitoring and alarm system, mainly comprising:

[0018] The signal acquisition module is used to acquire automatic balancing signals;

[0019] The threshold value acquisition module is used to obtain the corresponding threshold value according to the type of automatic balancing signal;

[0020] The threshold value acquisition module is used to perform timing when the automatic balancing signal exceeds its corresponding threshold value;

[0021] The alarm signal generation module is used to issue an alarm signal when the timing of any automatic balancing signal exceeds a set value.

[0022] Preferably, the signal acquisition module includes:

[0023] The surge suppression unit is used to suppress spike surges in the acquired automatic balancing signal using resistor current limiting and transient suppression diodes;

[0024] The level isolation conversion unit is used to perform level isolation conversion on the automatic balancing signal by the optocoupler.

[0025] Preferably, in the threshold acquisition module, different types of automatic trim signals are acquired through different channels. These automatic trim signals include pitch trim signals, droop trim signals, left tilt trim signals, right tilt trim signals, left yaw trim signals, and right yaw trim signals.

[0026] Preferably, in the threshold acquisition module, sampling and timing begin after the tuning control signal changes from off to on and continues to exceed the start timing threshold, with a sampling period of 3ms.

[0027] Preferably, in the threshold acquisition module, timing is started when the automatic balancing signal for two consecutive sampling periods exceeds its corresponding threshold value.

[0028] Preferably, in the alarm signal generation module, the set value is 0.5s-2s.

[0029] This application enables timely monitoring of tuning malfunctions, which helps pilots to take prompt action. Attached Figure Description

[0030] Figure 1 This is a flowchart of a preferred embodiment of the aircraft performance control command monitoring and alarm method of this application. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0032] The first aspect of this application provides a method for monitoring and alarming aircraft tuning commands, such as... Figure 1 As shown, the method includes:

[0033] Step S1: Acquire automatic balancing signals;

[0034] Step S2: Obtain the corresponding threshold value according to the type of automatic balancing signal;

[0035] Step S3: When the automatic balancing signal exceeds its corresponding threshold value, timing is started;

[0036] Step S4: When the timing of any automatic balancing signal exceeds the set value, an alarm signal is issued.

[0037] This application proposes a device capable of signal acquisition and logical judgment to achieve performance monitoring and issue alarms to pilots. The device collects and monitors trim signals and outputs comprehensive alarm information.

[0038] In some alternative implementations, step S1 further includes:

[0039] Step S11: Use resistor current limiting and transient suppression diodes to suppress spike surges in the acquired automatic balancing signal;

[0040] Step S12: The automatic balancing signal is level isolated and converted by the optocoupler.

[0041] In this embodiment, surge suppression and isolation conversion are performed by the input signal interface circuit for signal acquisition. This application uses physical components to implement the aforementioned aircraft tuning command monitoring and alarm method. While ensuring reliability, it achieves small size and light weight, without affecting the aircraft's weight characteristics. These physical components include a housing, a circuit board (including a power supply circuit, input signal interface circuit, microprocessor circuit, and alarm signal output circuit), electrical connectors, and ground wires. Therefore, the power consumption of the product is limited to the power supply circuit, input signal interface circuit, microprocessor circuit, and alarm signal output circuit, resulting in low total power consumption and no burden on the aircraft's power consumption.

[0042] In some optional implementations, in step S2, different types of automatic trim signals are acquired through different channels. The types of automatic trim signals include upward trim signals, downward trim signals, left tilt trim signals, right tilt trim signals, left skew trim signals, and right skew trim signals.

[0043] In this embodiment, for threshold monitoring, the microprocessor circuit performs time threshold monitoring and logical judgment. The software resides in the microprocessor, samples and filters each signal after circuit processing, performs on-time timing and threshold judgment for each signal, and obtains the continuous alarm status of the signal.

[0044] In some optional implementations, in step S3, sampling timing begins after the tuning control signal changes from off to on and continues to exceed the start timing threshold, with a sampling period of 3ms.

[0045] In this embodiment, based on the characteristics of the input signal, the software samples the input signal for a period of 3ms, with at least four sampling points per frame. The acquired channel balancing control signals are timed separately. Timing begins when the modulation control signal changes from off to on, and the duration exceeds the computer's start-time threshold. When the modulation control signal is off, the counter is reset to zero, and the timer is limited to prevent overflow.

[0046] In some alternative implementations, in step S3, timing is performed when the automatic balancing signal for two consecutive sampling periods exceeds its corresponding threshold value.

[0047] In this embodiment, the input signal is filtered, and the signal is considered valid when the sampling signals of two consecutive cycles are consistent. This includes starting the timing when the automatic balancing signal of two consecutive sampling cycles exceeds its corresponding threshold value, and stopping the timing when the automatic balancing signal of two consecutive sampling cycles is lower than its corresponding threshold value. In other words, interference of less than 6ms in the input signal is effectively suppressed to prevent the continuous connection timing caused by interference signals from being interrupted when the modulation control command is continuously turned on.

[0048] In some alternative implementations, the set value in step S4 is 0.5s-2s.

[0049] In this embodiment, the present application considers the percentage of the control stick displacement and control surface displacement occupied by the control mechanism's authority, the movement speed of the control mechanism, the aircraft's aerodynamic characteristics, and the pilot's reaction and control operation time after receiving the alarm information. Taking all these factors into account, the alarm threshold, i.e., the setting value of step S4, is 0.5s to 2s.

[0050] This application enables timely monitoring of tuning malfunctions, which helps pilots to take prompt action.

[0051] The second aspect of this application provides an aircraft tuning command monitoring and alarm system corresponding to the above method, mainly including:

[0052] The signal acquisition module is used to acquire automatic balancing signals;

[0053] The threshold value acquisition module is used to obtain the corresponding threshold value according to the type of automatic balancing signal;

[0054] The threshold value acquisition module is used to perform timing when the automatic balancing signal exceeds its corresponding threshold value;

[0055] The alarm signal generation module is used to issue an alarm signal when the timing of any automatic balancing signal exceeds a set value.

[0056] In some alternative implementations, the signal acquisition module includes:

[0057] The surge suppression unit is used to suppress spike surges in the acquired automatic balancing signal using resistor current limiting and transient suppression diodes;

[0058] The level isolation conversion unit is used to perform level isolation conversion on the automatic balancing signal by the optocoupler.

[0059] In some optional implementations, in the threshold acquisition module, different types of automatic trim signals are acquired through different channels. These automatic trim signals include pitch trim signals, sag trim signals, left tilt trim signals, right tilt trim signals, left yaw trim signals, and right yaw trim signals.

[0060] In some optional implementations, in the threshold acquisition module, sampling and timing begin after the tuning control signal changes from off to on and continues to exceed the start timing threshold, with a sampling period of 3ms.

[0061] In some alternative implementations, timing is performed in the threshold acquisition module when the automatic balancing signal for two consecutive sampling periods exceeds its corresponding threshold value.

[0062] In some alternative implementations, the set value in the alarm signal generation module is 0.5s-2s.

[0063] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method for monitoring and alarming aircraft performance control commands, characterized in that, include: Step S1: Acquire automatic balancing signals; Step S2: Obtain the corresponding threshold value according to the type of automatic balancing signal; Step S3: When the automatic balancing signal exceeds its corresponding threshold value, timing is started; Step S4: When the timing of any automatic balancing signal exceeds the set value, an alarm signal is issued; Step S1 further includes: Step S11: Use resistor current limiting and transient suppression diodes to suppress spike surges in the acquired automatic balancing signal; Step S12: The automatic balancing signal is level isolated and converted by the optocoupler; In step S2, different types of automatic trim signals are acquired through different channels. The types of automatic trim signals include upward trim signal, downward trim signal, left tilt trim signal, right tilt trim signal, left skew trim signal, and right skew trim signal. In step S3, sampling timing begins after the modulation control signal changes from off to on and continues to exceed the start timing threshold, with a sampling period of 3ms. In step S3, timing begins when the automatic balancing signal for two consecutive sampling periods exceeds its corresponding threshold value; In step S4, the set value is 0.5s-2s.

2. An aircraft performance control command monitoring and alarm system, characterized in that, For implementing the aircraft performance tuning command monitoring and alarm method as described in claim 1, the system comprises: The signal acquisition module is used to acquire automatic balancing signals; The threshold value acquisition module is used to obtain the corresponding threshold value according to the type of automatic balancing signal; The threshold value acquisition module is used to perform timing when the automatic balancing signal exceeds its corresponding threshold value; The alarm signal generation module is used to issue an alarm signal when the timing of any automatic balancing signal exceeds a set value.

3. The aircraft performance tuning command monitoring and alarm system as described in claim 2, characterized in that, The signal acquisition module includes: The surge suppression unit is used to suppress spike surges in the acquired automatic balancing signal using resistor current limiting and transient suppression diodes; The level isolation conversion unit is used to perform level isolation conversion on the automatic balancing signal by the optocoupler.

4. The aircraft performance control command monitoring and alarm system as described in claim 2, characterized in that, In the threshold acquisition module, different types of automatic trim signals are acquired through different channels. The types of automatic trim signals include pitch trim signal, droop trim signal, left tilt trim signal, right tilt trim signal, left yaw trim signal, and right yaw trim signal.

5. The aircraft performance control command monitoring and alarm system as described in claim 2, characterized in that, In the threshold acquisition module, sampling and timing begin after the tuning control signal changes from off to on and continues to exceed the start timing threshold, with a sampling period of 3ms.

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