Airplane adjusting instruction monitoring and alarming method and system

Abstract

The invention belongs to the technical field of flight control, and particularly relates to a method and a system for monitoring and alarming an aircraft adjusting instruction. The method comprises the following steps: S1, collecting an automatic balancing signal; s2, acquiring a corresponding threshold value according to the type of the automatic trimming signal; s3, when the automatic trimming signal exceeds the corresponding threshold value, timing is carried out; and S4, when the timing of any automatic trimming signal exceeds a set value, sending out an alarm signal. According to the invention, a regulation fault can be monitored in time, and a pilot can handle the fault in time.

Description

Technical Field

[0001] The present application belongs to the field of flight control technology, and in particular relates to an aircraft efficiency control instruction monitoring and warning method and system. Background Art

[0002] As a flight control method, the trim function issues trim commands manually or automatically to reduce the pilot's operating burden and improve the safety and economy of flight. The trim function includes two working modes: manual trim and automatic trim. In the manual trim mode, the pilot operates the trim button to issue a manual trim command; in the automatic trim mode, the automatic flight control device generates and outputs an automatic trim command based on the control law solution result. The trim command is logically synthesized by the trim command logic switching device to drive the trim electric mechanism to work.

[0003] As a way to assist flight, the trim function continuously outputs trim control commands for a long time, which may cause a significant change in the aircraft's attitude. The components that implement the trim function are mostly mechanical structures, which are greatly affected by the environment. For example, buttons may stick, and signal lines may short-circuit or break. In this case, the trim signal output is abnormal, and the aircraft may quickly undergo a large and unexpected attitude change. If it is not handled in time, it will be detrimental to flight safety. If the trim command is directly restricted, it will affect the trim control function, and then cause a large degree of change to the flight control system itself. Summary of the invention

[0004] In order to solve the above problems, the present application provides an aircraft adjustment instruction monitoring and alarm method and system to avoid the generation of unexpected adjustment instructions due to signal failure or false triggering, which may cause drastic changes in the aircraft's attitude and endanger flight safety.

[0005] The first aspect of the present application provides an aircraft efficiency adjustment instruction monitoring and warning method, which mainly includes:

[0006] Step S1, collecting automatic balancing signals;

[0007] Step S2, obtaining a corresponding threshold value according to the type of the automatic balancing signal;

[0008] Step S3, timing when the automatic balancing signal exceeds its corresponding threshold value;

[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 comprises:

[0011] Step S11, using resistor current limiting and transient suppression diode to suppress spike surge of the collected automatic balancing signal;

[0012] Step S12: The photoelectric coupler performs level isolation conversion on the automatic balancing signal.

[0013] Preferably, in step S2, different types of automatic trim signals are collected through different channels, and the types of automatic trim signals include pitch-up trim signal, pitch-down trim signal, left tilt trim signal, right tilt trim signal, left yaw trim signal and right yaw trim signal.

[0014] Preferably, in step S3, sampling timing starts after the efficiency control signal changes from off to on and continues to exceed the start timing threshold, and the sampling period is 3ms.

[0015] Preferably, in step S3, timing is performed 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 the present application provides an aircraft efficiency adjustment instruction monitoring and warning system, which mainly includes:

[0018] A signal acquisition module, used for collecting automatic trim signals;

[0019] A threshold value acquisition module, used to acquire a corresponding threshold value according to the type of the automatic balancing signal;

[0020] A threshold value acquisition module, used for timing when the automatic balancing signal exceeds its corresponding threshold value;

[0021] The alarm signal generating module is used to send out an alarm signal when the timing of any automatic trim signal exceeds a set value.

[0022] Preferably, the signal acquisition module includes:

[0023] A surge suppression unit is used to suppress the spike surge of the collected automatic trim signal by using resistor current limiting and transient suppression diode;

[0024] The level isolation conversion unit is used to perform level isolation conversion on the automatic balancing signal by means of a photoelectric coupler.

[0025] Preferably, in the threshold value acquisition module, different types of automatic trim signals are collected through different channels, and the types of automatic trim signals include pitch-up trim signal, pitch-down trim signal, left tilt trim signal, right tilt trim signal, left yaw trim signal and right yaw trim signal.

[0026] Preferably, in the threshold value acquisition module, sampling and timing start after the efficiency control signal changes from off to on and continues to exceed the start timing threshold, and the sampling period is 3ms.

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

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

[0029] This application can monitor efficiency adjustment failures in a timely manner, which is helpful for pilots to take timely measures. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a flow chart of a preferred embodiment of the aircraft efficiency adjustment instruction monitoring and warning method of the present application. DETAILED DESCRIPTION

[0031] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0032] The first aspect of the present application provides an aircraft efficiency adjustment instruction monitoring and warning method, such as Figure 1 As shown, the method includes:

[0033] Step S1, collecting automatic balancing signals;

[0034] Step S2, obtaining a corresponding threshold value according to the type of the automatic balancing signal;

[0035] Step S3, timing when the automatic balancing signal exceeds its corresponding threshold value;

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

[0037] In order to realize the adjustment efficiency monitoring mode and issue a warning to the pilot, the present application proposes a device that can collect signals and make logical judgments, collect and monitor the trim signals, and output comprehensive warning information.

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

[0039] Step S11, using resistor current limiting and transient suppression diode to suppress spike surge of the collected automatic balancing signal;

[0040] Step S12: The photoelectric coupler performs level isolation conversion on the automatic balancing signal.

[0041] In terms of signal acquisition, the input signal interface circuit of this embodiment completes the peak surge suppression and isolation conversion. This application adopts physical components to implement the above-mentioned aircraft efficiency adjustment instruction monitoring and warning method, which achieves small size and light weight under the premise of ensuring reliability, and will not affect the weight characteristics of the aircraft. The physical components include a box, a circuit board (including a power supply circuit, an input signal interface circuit, a microprocessor circuit, and an alarm signal output circuit), an electrical connector, a grounding wire, etc. It can be seen that the part of the product that generates power consumption only includes the power supply circuit, the input signal interface circuit, the microprocessor circuit, and the alarm signal output circuit. The total power consumption is small and does not burden the power consumption of the aircraft.

[0042] In some optional embodiments, in step S2, different types of automatic trim signals are collected through different channels, and the types of automatic trim signals include pitch-up trim signal, pitch-down trim signal, left tilt trim signal, right tilt trim signal, left yaw trim signal and right yaw trim signal.

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

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

[0045] In this embodiment, according to the characteristics of the input signal, the sampling period of the software for the input signal is 3ms, and each input signal has at least four sampling points. The collected channel balancing control signals are timed separately, and the timing starts when the effect control signal changes from disconnected to connected, and the duration exceeds the start timing threshold of the computer. When the effect control signal is disconnected, the counter is cleared, and the timer is limited to prevent overflow.

[0046] In some optional implementations, in step S3, timing is performed when the automatic balancing signal of 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 remain consistent, including timing when the automatic balancing signal of two consecutive sampling cycles exceeds its corresponding threshold value, and stopping timing when the automatic balancing signal of two consecutive sampling cycles is lower than its corresponding threshold value. That is, interference less than 6ms in the input signal is effectively suppressed to prevent the continuous connection timing from being interrupted by the interference signal when the efficiency control instruction is continuously connected.

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

[0049] In this embodiment, the present application considers the percentage of the control mechanism authority to the control stick displacement and the control surface displacement, the movement speed of the control mechanism, the aerodynamic characteristics of the aircraft, and the pilot's reaction and control operation time after receiving the warning information. After combining the above factors, the warning threshold, that is, the setting value of step S4, is 0.5s to 2s.

[0050] This application can monitor efficiency adjustment failures in a timely manner, which is helpful for pilots to take timely measures.

[0051] The second aspect of the present application provides an aircraft efficiency adjustment instruction monitoring and warning system corresponding to the above method, mainly comprising:

[0052] A signal acquisition module, used for collecting automatic trim signals;

[0053] A threshold value acquisition module, used to acquire a corresponding threshold value according to the type of the automatic balancing signal;

[0054] A threshold value acquisition module, used for timing when the automatic balancing signal exceeds its corresponding threshold value;

[0055] The alarm signal generating module is used to send out an alarm signal when the timing of any automatic trim signal exceeds a set value.

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

[0057] A surge suppression unit is used to suppress the spike surge of the collected automatic trim signal by using resistor current limiting and transient suppression diode;

[0058] The level isolation conversion unit is used to perform level isolation conversion on the automatic balancing signal by means of a photoelectric coupler.

[0059] In some optional implementations, in the threshold value acquisition module, different types of automatic trim signals are collected through different channels, and the types of automatic trim signals include a pitch-up trim signal, a pitch-down trim signal, a left tilt trim signal, a right tilt trim signal, a left yaw trim signal, and a right yaw trim signal.

[0060] In some optional implementations, in the threshold value acquisition module, sampling and timing start after the efficiency control signal changes from off to on and continues to exceed the start timing threshold, and the sampling period is 3ms.

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

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

[0063] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An aircraft efficiency adjustment instruction monitoring and warning method, characterized in that: include: Step S1, collecting automatic balancing signals; Step S2, obtaining a corresponding threshold value according to the type of the automatic balancing signal; Step S3, timing when the automatic balancing signal exceeds its corresponding threshold value; Step S4: When the timing of any automatic balancing signal exceeds the set value, an alarm signal is issued.

2. The aircraft efficiency adjustment instruction monitoring and warning method according to claim 1, characterized in that: Step S1 further comprises: Step S11, using resistor current limiting and transient suppression diode to suppress spike surge of the collected automatic balancing signal; Step S12: The photoelectric coupler performs level isolation conversion on the automatic balancing signal.

3. The aircraft efficiency adjustment instruction monitoring and warning method according to claim 1, characterized in that: In step S2, different types of automatic trim signals are collected through different channels, and the types of automatic trim signals include pitch-up trim signal, pitch-down trim signal, left tilt trim signal, right tilt trim signal, left yaw trim signal and right yaw trim signal.

4. The aircraft efficiency adjustment instruction monitoring and warning method according to claim 1, characterized in that: In step S3, sampling timing starts after the efficiency control signal changes from off to on and continues to exceed the start timing threshold, and the sampling period is 3ms.

5. The aircraft efficiency adjustment instruction monitoring and warning method according to claim 1, characterized in that: In step S3, timing is performed when the automatic balancing signal of two consecutive sampling periods exceeds its corresponding threshold value.

6. The aircraft efficiency adjustment instruction monitoring and warning method according to claim 1, characterized in that: In step S4, the set value is 0.5s-2s.

7. An aircraft efficiency adjustment instruction monitoring and warning system, characterized in that: include: A signal acquisition module, used for collecting automatic trim signals; A threshold value acquisition module, used to acquire a corresponding threshold value according to the type of the automatic balancing signal; A threshold value acquisition module, used for timing when the automatic balancing signal exceeds its corresponding threshold value; The alarm signal generating module is used to send out an alarm signal when the timing of any automatic trim signal exceeds a set value.

8. The aircraft efficiency adjustment instruction monitoring and warning system according to claim 7, characterized in that: The signal acquisition module comprises: A surge suppression unit is used to suppress the spike surge of the collected automatic trim signal by using resistor current limiting and transient suppression diode; The level isolation conversion unit is used to perform level isolation conversion on the automatic balancing signal by means of a photoelectric coupler.

9. The aircraft efficiency adjustment instruction monitoring and warning system according to claim 7, characterized in that: In the threshold value acquisition module, different types of automatic trim signals are collected through different channels, and the types of automatic trim signals include pitch-up trim signal, pitch-down trim signal, left tilt trim signal, right tilt trim signal, left yaw trim signal and right yaw trim signal.

10. The aircraft efficiency adjustment instruction monitoring and warning system according to claim 7, characterized in that: In the threshold value acquisition module, sampling and timing start after the efficiency control signal changes from off to on and continues to exceed the start timing threshold, and the sampling period is 3ms.

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