Universal flight control system signal monitoring and redundancy management technology

Abstract

The invention relates to a universal flight control system signal monitoring and redundancy management system, and aims to improve the reliability and safety of a flight control system. A flight control system plays a crucial role in aircraft design, and signal monitoring and redundancy management of the flight control system are key links for ensuring stable operation of the system. By comprehensively using the signal monitoring technology and the redundancy management module, the system can be used for the flight control system to monitor the signal state in real time, and when a fault or an abnormality occurs, the fault signal or equipment can be quickly isolated and processed, so that the normal operation of the flight control system is ensured. The core technology of the invention comprises the following aspects: 1, a signal monitoring technology: utilizing a multi-sensor fusion technology to collect input and output data of each key part in a flight control system in real time, including an attitude sensor, an accelerometer, a gyroscope and the like; data are collected and processed through heartbeat monitoring, signal threshold comparison, rewinding monitoring and other methods, and the signal state can be monitored in real time. 2, a redundancy management technology: based on a redundancy design concept, setting a multi-layer and multi-path signal transmission channel and a backup mechanism; when a certain signal channel or part breaks down, the system can automatically remove the fault channel, and continuity and reliability of the system are ensured.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft design, and in particular to a universal flight control system signal monitoring and redundancy management technology. Background Art

[0002] In the field of modern aviation, the flight control system (FCS) is the core component of the aircraft, responsible for real-time processing of flight data and controlling the movement of the aircraft. The reliability and stability of the FC system directly affect the safety of the aircraft and the success rate of mission execution. However, due to the operation of the aircraft in various complex environments, the FC system faces a variety of potential failure risks, including hardware failures, software defects, and interference from the external environment. How to monitor and detect various signals in the system in real time and discover potential faults in a timely manner is the key to improving system reliability. Although the existing signal monitoring technology can collect and process signals, the accuracy and real-time performance in fault detection and anomaly identification still need to be improved.

[0003] In response to these problems, the present invention proposes a universal flight control system signal monitoring and redundancy management technology. This technology combines real-time multi-signal monitoring and redundancy management. The present invention can effectively deal with various fault conditions of the flight control system signal source data and ensure the stability and safety of the aircraft in complex environments. This technology has broad application prospects. Summary of the invention

[0004] The purpose of the present invention application is to provide a universal flight control system signal monitoring and redundancy management system, which effectively responds to various fault conditions of the flight control system signal source data by combining real-time multi-signal monitoring and redundancy management.

[0005] The present invention provides a universal flight control system signal monitoring and redundancy management system, which mainly includes:

[0006] Step 1: Set up redundant equipment to collect the relevant signals required by the flight control system, obtain the relevant device source status information, and start or stop the device source signal monitoring according to the device source status;

[0007] Step 2: The flight control system monitors the validity of the data source signal by setting heartbeat monitoring, threshold value voting and validity monitoring for the input signal;

[0008] Step 3: Voting on the monitoring signal based on the signal status;

[0009] Preferably, in step 1, the common devices include computers and sensors, the status information of the device source is monitored in real time by the hardware itself, and the status-related information is uploaded to the flight control system. When the device source status is normal, the flight control system normally obtains the device source acquisition result. When the device source status is faulty, the device source data acquisition is stopped.

[0010] Preferably, in step 2, the signal heartbeat monitoring is used to monitor the periodic refresh state of the periodic input signal. When the signal sending end periodically sends data to the receiving end, it also sends a periodic accumulated data. While receiving the data, the receiving end determines the fixed period accumulated counter value. When the counter value is not updated regularly or remains unchanged, it is determined that the transmission is invalid.

[0011] Preferably, in step 2, input signal threshold comparison and voting are set. When the absolute value of the difference between any signal source data of the same signal and at least one other signal source data is within the comparison threshold range, the signal source data can enter the next part for calculation. When the difference with all other signal source data exceeds the comparison threshold, the signal source data is regarded as a fault. If the threshold time is exceeded for 100ms, the signal source is latched.

[0012] Preferably, in step 2, the validity of the bus data is determined, and whether the signal is valid data or data under normal working conditions is defined according to the valid bit of the bus data; if the valid bit is invalid, the fault status determination will be latched.

[0013] Preferably, in step 3, if all four signal sources of the same signal are valid, the data are arranged from large to small and the average of the second largest and second smallest is selected as the voting value output. If three signal sources of the same signal are valid, the middle value is selected as the voting value output. If two signal sources of the same signal are valid, the average of the two signal source data is taken as the voting value output. If only one signal source of the same signal is valid or no signal source is valid, the data is identified as a fault state.

[0014] This application provides a universal flight control signal monitoring and redundancy management solution to ensure the stability and safety of the aircraft in complex environments. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 Flight control system signal monitoring and redundancy management implementation flow chart

[0016] Figure 2 Flight control system redundancy management flow chart DETAILED DESCRIPTION

[0017] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific implementation methods. It mainly includes:

[0018] Step 1: Set up redundant equipment to collect the relevant signals required by the flight control system, obtain the relevant device source status information, and start or stop the device source signal monitoring according to the device source status;

[0019] Step 2: The flight control system monitors the validity of the data source signal by setting heartbeat monitoring, threshold value voting and validity monitoring for the input signal;

[0020] Step 3: Voting on the monitoring signal based on the signal status;

[0021] The present invention performs signal validity judgment and redundant signal monitoring voting on the device source acquisition data through steps 1-3, and outputs the voting results to the flight control system, so as to effectively deal with various fault conditions of the signal source data of the flight control system. The following are detailed descriptions:

[0022] The present invention determines the device source hardware status information through step 1.

[0023] In step 1, the common devices include computers and sensors. The status information of the device source is monitored in real time by the hardware itself. Sensor_signal is used to indicate the current device source hardware status and upload the status information in real time. When Sensor_signal = 1, it means that the current device source hardware status is intact, and the flight control system obtains the acquisition results of the device source normally. When Sensor_signal = 0, it means that the current device source hardware is in a fault state, the device source data acquisition is stopped, and the device source hardware status cannot be restored to normal later.

[0024] The present invention determines the validity of the data collected by the equipment source through step 2.

[0025] Step 2 further comprises the following steps:

[0026] Step 2.1: When the device source hardware is in normal state, set the signal heartbeat monitoring for the collected data to monitor the periodic refresh state of the periodic signal. When the signal sender periodically sends data to the receiver, it also sends a periodically accumulated data PeriodAcc_Sender. The heartbeat monitoring rule is that PeriodAcc_Sender is +1 every period according to the sending period. When the receiver receives data, the built-in heartbeat monitoring solution module accumulates the PeriodAcc_Receiver according to the same rule and determines whether the fixed period cumulative counter value PeriodAcc_Sender is consistent with PeriodAcc_Receiver. When the counter value is not updated according to the rule every period or remains unchanged, it is determined that the data transmission is invalid and the data validity is set to 0.

[0027] Step 2.2: When each device source heartbeat monitoring is in normal state, set the input signal threshold comparison module. When the absolute value of the difference between any signal source data of the same signal and at least one other signal source data is within the comparison threshold range, that is, , the signal source data can enter the next part for calculation. When the difference with all other signal source data exceeds the comparison threshold The signal source data is considered to be faulty, and the data transmission is judged to be invalid and the data validity is set to 0. If the threshold time is exceeded for 100ms, the signal is in a fault state and the data validity is set to 0.

[0028] Step 2.3: Determine the validity of the bus data. The valid bit SSM of the bus data defines whether the signal is valid data or data in a normal working state. If the valid bit SSM is invalid, the signal is in a fault state and the data validity is set to 0.

[0029] The present invention performs redundancy management on the collected data through step 3.

[0030] Step 3.1: If all four signal sources of the same signal are valid, arrange the data from largest to smallest and select the average of the second largest and second smallest values ​​as the voting value output. If three signal sources of the same signal are valid, select the middle value as the voting value output. If two signal sources of the same signal are valid, take the average of the two signal source data as the voting value output. If only one signal source of the same signal is valid or no signal source is valid, the data is considered to be in a fault state.

[0031] This application provides a universal flight control signal monitoring and redundancy management solution to ensure the stability and safety of the aircraft in complex environments.

[0032] The beneficial effects of the present invention are:

[0033] Compared with the traditional dual-redundancy or single-redundancy flight control system redundancy management scheme, the multi-redundancy design increases the stability and safety of the system.

[0034] When a single data source fails, the fault can be quickly identified through the signal monitoring design solution, and the data collected by the faulty data source can be isolated from the data collected by the normal data source through the redundancy management solution to prevent the subsequent flight control system from using the faulty data.

Claims

1. A universal flight control system signal monitoring and redundancy management technology, characterized in that The following steps are involved: Step 1: Set up redundant devices to collect the relevant signals required by the flight control system, obtain the relevant device source status information, and start or stop the device source signal monitoring according to the device source status; Step 2: The flight control system monitors the validity of the data source signal by setting heartbeat monitoring, threshold value voting and validity monitoring for the input signal; Step 3: Voting on the monitoring signal based on the signal status.

2. The universal flight control system signal monitoring and redundancy management technology according to claim 1, characterized in that: In step 1, the common devices include computers and sensors. The status information of the device source is monitored in real time by the hardware itself, and the status-related information is uploaded to the flight control system. When the device source status is normal, the flight control system normally obtains the acquisition result of the device source. When the device source status is faulty, the device source data acquisition is stopped.

3. The universal flight control system signal monitoring and redundancy management technology according to claim 1, characterized in that: In step 2, the signal heartbeat monitoring is set to monitor the periodic refresh status of the periodic input signal. When the signal sending end periodically sends data to the receiving end, it also sends a periodic accumulated data. While receiving the data, the receiving end determines the fixed period accumulated counter value. When the counter value is not updated regularly or remains unchanged, it is determined that the transmission is invalid.

4. The universal flight control system signal monitoring and redundancy management technology according to claim 1, characterized in that: In step 2, set the input signal threshold comparison and voting. When the absolute value of the difference between any signal source data of the same signal and at least one other signal source data is within the comparison threshold range, the signal source data can enter the next part for calculation. When the difference with all other signal source data exceeds the comparison threshold, the signal source data is regarded as a fault. If the threshold time exceeds 100ms, the signal source is latched.

5. The universal flight control system signal monitoring and redundancy management technology according to claim 1, characterized in that: In step 2, the validity of the bus data is determined, and whether the signal is valid data or data under normal working conditions is defined according to the valid bit of the bus data; if the valid bit is invalid, the fault status determination will be latched.

6. The universal flight control system signal monitoring and redundancy management technology according to claim 1, characterized in that: In step 3, if all four signal sources of the same signal are valid, the data is arranged from large to small and the average of the second largest and second smallest is selected as the voting value output. If three signal sources of the same signal are valid, the middle value is selected as the voting value output. If two signal sources of the same signal are valid, the average of the two signal source data is taken as the voting value output. If only one signal source of the same signal is valid or no signal source is valid, the data is considered to be in a fault state.

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