CN113525703A - Method and device for monitoring aircraft signals - Google Patents
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- CN113525703A CN113525703A CN202111035643.6A CN202111035643A CN113525703A CN 113525703 A CN113525703 A CN 113525703A CN 202111035643 A CN202111035643 A CN 202111035643A CN 113525703 A CN113525703 A CN 113525703A
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- 238000009825 accumulation Methods 0.000 claims description 34
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
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- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
A method and apparatus for monitoring aircraft signals is disclosed. The method comprises the following steps: receiving a discrete signal as a redundancy signal for a flight control system; determining a frequency of the received discrete signal; determining a monitoring mode for the discrete signal based on a frequency of the received discrete signal; and monitoring whether the discrete signal indicates an anomaly based on the determined monitoring mode.
Description
Technical Field
Aspects of the present disclosure relate to civil aviation, and more particularly, to a method and apparatus for monitoring aircraft signals.
Background
The civil aircraft is a vehicle for carrying people, the safety of the civil aircraft is very important, and the transmission of signals on the civil aircraft has a very important influence on the safety. With the continuous development of fly-by-wire and digital computers, information interaction among various systems is mostly transmitted through a bus, and a key signal generally uses a discrete signal as redundancy and is monitored by comparing with a digital signal so as to improve reliability.
Due to the simplicity of processing, the discrete signal is widely applied to a civil aircraft flight control system, and even when a complex digital computer fails, the discrete signal can still complete partial functions. The expression is generally expressed in the following different physical states, and the expression forms include GROUND/OPEN, 28V/0V, and the like.
The civil aircraft flight control system is used as one of input for realizing functions after monitoring and voting signals to meet safety requirements. The correct signal monitoring can prevent the influence of the wrong signal on the next module, thereby effectively improving the system safety.
The traditional flight control system is simple in discrete signal monitoring, each discrete signal change is counted and monitored, the monitor is triggered when the number of times of each discrete signal change exceeds a certain number, and the simple monitoring logic can cause system false alarm in a specific scene.
Relevant tests show that when the air-ground state of any wheel-load discrete signal of one flight frame is converted for more than a certain number of times or the left and right wheel-load discrete signals are inconsistent for more than a certain time, the wheel-load discrete monitor is triggered, so that the flight control is not dispatched. And the airplane can be grounded for multiple times in the multiple landing continuous process, the state conversion of the wheel load signals occurs, the flight test data show that the ground transition of the airplane is frequent, the accumulated number of the wheel load discrete signal air-ground conversion times exceeds the maximum value after multiple times of grounding, and the flight control system considers that multiple landing continuous belongs to one flight frame, so that the alarm of the flight control system is triggered. Similarly, the accelerator lever discrete signal monitor has the same problem, and any accelerator lever discrete signal state of the same flight level is converted for more than a certain number of times, so that the monitor can be triggered, and the flight control system is triggered to alarm information after the airplane lands on the ground.
Accordingly, there is a need for an efficient aircraft signal monitoring method and apparatus.
Disclosure of Invention
The present invention is directed to a method and apparatus for monitoring aircraft signals.
According to an embodiment of the invention, there is provided a method for monitoring aircraft signals, the method comprising:
receiving a discrete signal as a redundancy signal for a flight control system;
determining a frequency of the received discrete signal;
determining a monitoring mode for the received discrete signals based on the frequency of the discrete signals; and
monitoring whether the discrete signals indicate an anomaly based on the determined monitoring mode.
Wherein determining the frequency of the received discrete signal may comprise: it is determined whether the received discrete signal is high frequency or low frequency.
Wherein determining the monitoring mode for the received discrete signals based on their frequencies may comprise: using a comparison-based monitoring mode when the received discrete signal is low frequency; and using a monitoring mode based on the accumulation/subtraction count when the received discrete signal is high frequency.
Wherein using the comparison-based monitoring mode may include: comparing a first redundancy signal of the discrete signals with a second redundancy signal of the discrete signals; and triggering an alarm when the time when the first redundancy signal is inconsistent with the second redundancy signal exceeds a set value.
Wherein using the accumulation/subtraction count based monitoring mode may include: accumulating/decrementing the state changes of the discrete signals; and triggering an alarm when the result of the accumulation/subtraction count exceeds a monitoring threshold.
According to another embodiment of the invention, there is provided an apparatus for monitoring aircraft signals, the apparatus comprising:
a discrete signal receiving unit that receives a discrete signal as a redundancy signal for a flight control system;
a frequency determination unit that determines a frequency of the received discrete signal;
a monitoring mode determination unit that determines a monitoring mode for the received discrete signals based on frequencies of the discrete signals; and
a monitor mode execution unit that monitors whether the discrete signals indicate an abnormality based on the determined monitor mode.
Wherein the frequency determination unit may determine whether the received discrete signal is a high frequency or a low frequency.
Wherein the monitoring mode determination unit determines the monitoring mode for the discrete signals by: using a comparison-based monitoring mode when the received discrete signal is low frequency; and using a monitoring mode based on the accumulation/subtraction count when the received discrete signal is high frequency.
Wherein the monitoring mode execution unit executes the comparison-based monitoring mode by: comparing a first redundancy signal of the discrete signals with a second redundancy signal of the discrete signals; and triggering an alarm when the time when the first redundancy signal is inconsistent with the second redundancy signal exceeds a set value.
Wherein the monitoring mode execution unit executes the accumulation/subtraction count-based monitoring mode by: accumulating/decrementing the state changes of the discrete signals; and triggering an alarm when the result of the accumulation/subtraction count exceeds a monitoring threshold.
The present invention may also provide a computer-readable medium having stored thereon instructions for monitoring aircraft signals, which when executed by a processor, cause the processor to: receiving a discrete signal as a redundancy signal for a flight control system; determining a frequency of the received discrete signal; determining a monitoring mode for the received discrete signals based on the frequency of the discrete signals; and monitoring whether the discrete signals indicate an anomaly based on the determined monitoring mode.
Wherein determining the frequency of the received discrete signal may comprise: it is determined whether the received discrete signal is high frequency or low frequency.
Wherein determining the monitoring mode for the received discrete signals based on their frequencies may comprise: using a comparison-based monitoring mode when the received discrete signal is low frequency; and using a monitoring mode based on the accumulation/subtraction count when the received discrete signal is high frequency.
Wherein using the comparison-based monitoring mode may include: comparing a first redundancy signal of the discrete signals with a second redundancy signal of the discrete signals; and triggering an alarm when the time when the first redundancy signal is inconsistent with the second redundancy signal exceeds a set value.
Wherein using the accumulation/subtraction count based monitoring mode may include: accumulating/decrementing the state changes of the discrete signals; and triggering an alarm when the result of the accumulation/subtraction count exceeds a monitoring threshold.
Drawings
FIG. 1 is a block diagram of an apparatus for monitoring aircraft signals according to an embodiment of the invention.
Fig. 2 is a logic diagram of an up/down counter according to an embodiment of the present invention.
FIG. 3 is a flow diagram of a method for monitoring aircraft signals according to an embodiment of the invention.
FIG. 4 is a monitoring logic diagram in accordance with an embodiment of the present invention.
Detailed Description
The present invention will be further described with reference to the following specific examples and drawings, but the scope of the present invention should not be limited thereto.
Aiming at the defects and shortcomings of the prior art and solving the problem that the traditional signal monitoring of the flight control system of the civil aircraft causes the false alarm of the system in a specific scene, the invention provides a method for hybrid monitoring of the discrete signals of the flight control system and related equipment.
Fig. 1 is a block diagram of an apparatus 100 for monitoring aircraft signals according to an embodiment of the invention. The apparatus 100 may include a discrete signal receiving unit 110, a frequency determining unit 120, a monitoring mode determining unit 130, and a monitoring mode performing unit 140.
The discrete signal receiving unit 110 receives a discrete signal as a redundancy signal for the flight control system. In one example, the discrete signal receiving unit 110 receives discrete signals such as a wheel-mounted discrete signal, a throttle lever discrete signal, a wheel speed discrete signal, a slat discrete signal, and the like. Flight control system discrete signals can be divided into high and low frequencies, for example, a wheel-borne signal less than 1/10 Hz (hertz) is divided into low frequencies and a discrete signal greater than 1/10 Hz is divided into high frequencies. Other classification approaches are also possible. Such a classification may be predefined in the device 100.
The frequency determination unit 120 determines the frequency of the received discrete signal. In an example, the frequency determination unit 120 determines that the received discrete signal is a wheel-borne signal that is less than 1/10 Hz, i.e., the wheel-borne signal is low frequency (e.g., based on a predefined classification). In another example, the frequency determination unit 120 determines that the received discrete signal is a discrete signal greater than 1/10 Hz, i.e., the discrete signal is high frequency (e.g., based on a predefined classification).
The monitoring mode determination unit 130 determines a monitoring mode for such discrete signals based on the frequency of the received discrete signals. As an example, when the monitoring mode determination unit 130 determines that the received discrete signal is a low frequency, a monitoring mode based on comparison is used. Because the flight control system signals all have redundancy, comparison and monitoring can be carried out between discrete signals serving as redundancy signals. For comparative monitoring of discrete signals, the time of inconsistency between these signals may be monitored. Using the comparison-based monitoring mode may include comparing a first redundancy signal to a second redundancy signal in the received discrete signals (e.g., for a wheelload signal less than 1/10 Hz, the comparison threshold for the disagreement of the two wheelload signals is a set value of 10 seconds, which is an inverse relationship to 1/10 Hz); when the time when the two redundancy signals are inconsistent exceeds a set value, the corresponding monitor can be triggered, so that the flight control system is triggered to alarm. As another example, when the monitoring mode determination unit 130 determines that the received discrete signal is a high frequency, a monitoring mode based on the accumulation/subtraction count is used. The state of the discrete signal may change, for example, the state transition of the discrete signal in the space of the wheel is carried. The monitoring mode based on the accumulation/subtraction count can comprise the steps of accumulating/subtracting the state change of the received discrete signal, and when the result of the accumulation/subtraction count exceeds a monitoring threshold, the corresponding monitor can be triggered, so that the flight control system is triggered to alarm. Different monitoring thresholds may also be set for different frequencies at high frequencies. In addition, in some cases, the comparison-based monitoring mode and the accumulation/subtraction count-based monitoring mode are not mutually exclusive, and thus the accumulation/subtraction count-based monitoring mode may be used in addition to or instead of the selected comparison-based monitoring mode.
The monitoring mode performing unit 140 monitors whether the discrete signal indicates an abnormality based on the determined monitoring mode. The supervisor mode execution unit 140 may include a comparator and an up/down counter. A monitoring mode based on comparison may be performed using the comparator, and a monitoring mode based on an up/down count may be performed using the up/down counter. In addition, the up/down counter may also be active, but not essential (or vice versa) when using a comparator for comparison monitoring. In this case, there is a relationship between the parameter design of the comparator and the parameter design of the up/down counter.
Fig. 2 is a logic diagram 200 of an up/down counter according to an embodiment of the present invention. The logic of the counter is that the discrete signal state changes, the constant rate accumulation counter is started, and the counter is increased by 1 every time the constant rate accumulation counter changes; if the discrete signal remains constant for a certain time, the down-count counter will start at a constant rate (which may be different from the up-count rate) until the counter is reduced to 0. By selecting the fast accumulation count and the slow accumulation count, the oscillation fault detection function can be realized; the fast accumulation rate is less than the change rate of the sporadic stray event, and robustness aiming at the sporadic stray event is realized. If the accumulation/subtraction counter reaches a certain value or threshold, the monitor is triggered to trigger the flight control system to alarm.
FIG. 3 is a flow diagram of a method 300 for monitoring aircraft signals in accordance with an embodiment of the invention. The method 300 includes receiving a discrete signal for a flight control system as a redundancy signal, such as a wheel-borne discrete signal, a throttle lever discrete signal, a wheel speed discrete signal, a slat discrete signal, or the like, at 310. In one example, flight control system discrete signals may be split into high and low frequencies, for example, a wheel load signal less than 1/10 Hz (hertz) is split into a low frequency, and a discrete signal greater than 1/10 Hz is split into a high frequency. Other classification approaches are also possible. Such classification may be predefined prior to step 310. The method 300 next determines the frequency of the received discrete signal at 320. In one example, the received discrete signal is a wheel-borne signal that is less than 1/10 Hz, i.e., the wheel-borne signal is low frequency. In another example, the received discrete signal is a discrete signal greater than 1/10 Hz, i.e., the discrete signal is high frequency. The method 300 further includes determining a monitoring mode for the received discrete signal based on the frequency of such discrete signal at 330, and performing monitoring whether the discrete signal indicates an anomaly based on the determined monitoring mode at 340. As an example, a comparison-based monitoring mode is used when it is determined that the received discrete signal is low frequency. Because the flight control system signals all have redundancy, comparison and monitoring can be carried out between discrete signals serving as redundancy signals. For comparative monitoring of discrete signals, the time of inconsistency between these signals may be monitored. The comparison-based monitoring mode may include comparing a first redundancy signal with a second redundancy signal in the received discrete signals (e.g., for a wheel load signal less than 1/10 Hz, the comparison threshold for the inconsistency of the two wheel load signals is a set value of 10 seconds, which is inverse to 1/10 Hz), and in addition, when the time for the inconsistency of the two redundancy signals exceeds the set value, the corresponding monitor may be triggered, thereby triggering the flight control system alarm. As another example, a monitoring mode based on an accumulation/subtraction count is used when it is determined that the received discrete signal is high frequency. The state of the discrete signal may change, for example, the state transition of the discrete signal in the space of the wheel is carried. The monitoring mode based on the accumulation/subtraction count can comprise accumulating/subtracting the state change of the received discrete signal, and when the result of the accumulation/subtraction count exceeds a monitoring threshold, the monitor can be triggered, so that the flight control system is triggered to alarm. Different monitoring thresholds may also be set for different frequencies at high frequencies. In some examples, the comparison based monitoring mode and the accumulation/subtraction count based monitoring mode are not mutually exclusive, such that the accumulation/subtraction count based monitoring mode may be used in addition to the determined comparison based monitoring mode to monitor whether the discrete signals indicate an anomaly or the comparison based monitoring mode may be used in addition to the determined accumulation/subtraction count based monitoring mode to monitor whether the discrete signals indicate an anomaly.
Fig. 4 is a monitoring logic diagram 400 in accordance with an embodiment of the present invention. The method comprises the steps of firstly receiving a discrete signal used for a flight control system and serving as a redundancy signal, judging the frequency of the discrete signal of the flight control system, and dividing the frequency into a high frequency and a low frequency. If the frequency of the discrete signal is low (410), determining if the signal inconsistency time exceeds a set value (420); if yes, triggering the monitor to trigger the flight control system to alarm; otherwise, return to receiving the discrete signal. If the frequency of the discrete signal is high (430), determining if the discrete signal state has changed; if yes, the accumulation counter (450) is incremented by 1; otherwise, it is determined whether the discrete signal remains unchanged for a certain time. If the discrete signal remains unchanged for a certain time, the up-down counter (470) is started; otherwise, return to receiving the discrete signal. Setting monitoring thresholds under different frequencies through a counter, and determining whether the conversion times exceed the thresholds; if yes, triggering a monitor (490) to trigger a flight control system to alarm; otherwise, return to receiving the discrete signal.
The invention improves the original traditional flight control system signal monitoring method, and adopts the mixed design of the accumulation/subtraction counting monitoring mode and the comparison monitoring mode aiming at the discrete signals with different frequencies, thereby avoiding the situation that the traditional monitoring method causes the system to give an alarm by mistake in a specific scene, and ensuring the normal operation and the safe monitoring of the flight.
The various steps and modules of the methods and apparatus described above may be implemented in hardware, software, or a combination thereof. If implemented in hardware, the various illustrative steps, modules, and circuits described in connection with the disclosure may be implemented or performed with a general purpose processor, a Digital Signal Processor (DSP), an Application Specific Integrated Circuit (ASIC), a Field Programmable Gate Array (FPGA), or other programmable logic component, hardware component, or any combination thereof. A general purpose processor may be a processor, microprocessor, controller, microcontroller, or state machine, among others. If implemented in software, the various illustrative steps, modules, etc. described in connection with the disclosure may be stored on or transmitted over as one or more instructions or code on a computer-readable medium. A software module implementing various operations of the present disclosure may reside in a storage medium such as RAM, flash memory, ROM, EPROM, EEPROM, registers, hard disk, a removable disk, a CD-ROM, cloud storage, and the like. A storage medium may be coupled to the processor such that the processor can read information from, and write information to, the storage medium, and execute the corresponding program modules to perform the various steps of the present disclosure. Furthermore, software-based embodiments may be uploaded, downloaded, or accessed remotely through suitable communication means. Such suitable communication means include, for example, the internet, the world wide web, an intranet, software applications, cable (including fiber optic cable), magnetic communication, electromagnetic communication (including RF, microwave, and infrared communication), electronic communication, or other such communication means.
The numerical values given in the embodiments are only examples and do not limit the scope of the present invention. In addition, other components or steps not recited in the claims or specification of the invention may be present as a whole. Moreover, the singular reference of a component does not exclude the plural reference of such components.
It is also noted that the embodiments may be described as a process which is depicted as a flowchart, a flow diagram, a structure diagram, or a block diagram. Although a flowchart may describe the operations as a sequential process, many of the operations can be performed in parallel or concurrently. In addition, the order of the operations may be rearranged.
The disclosed methods, apparatus, and systems should not be limited in any way. Rather, the present disclosure encompasses all novel and non-obvious features and aspects of the various disclosed embodiments, both individually and in various combinations and sub-combinations with each other. The disclosed methods, apparatus, and systems are not limited to any specific aspect or feature or combination thereof, nor do any of the disclosed embodiments require that any one or more specific advantages be present or that a particular or all technical problem be solved.
The present invention is not limited to the above-mentioned embodiments, which are only illustrative and not restrictive, and those skilled in the art can make many modifications without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (10)
1. A method for monitoring aircraft signals, comprising:
receiving a discrete signal as a redundancy signal for a flight control system;
determining a frequency of the received discrete signal;
determining a monitoring mode for the discrete signal based on a frequency of the received discrete signal; and
monitoring whether the discrete signal indicates an anomaly based on the determined monitoring mode.
2. The method of claim 1, wherein determining the frequency of the received discrete signal comprises: it is determined whether the received discrete signal is high frequency or low frequency.
3. The method of claim 2, wherein determining a monitoring mode for the discrete signal based on the frequency of the received discrete signal comprises:
using a comparison-based monitoring mode when the received discrete signal is low frequency; and
when the received discrete signal is high frequency, a monitoring mode based on an accumulation/subtraction count is used.
4. The method of claim 3, wherein using the comparison-based monitoring mode comprises:
comparing a first redundancy signal in the discrete signals with a second redundancy signal in the discrete signals; and
and triggering an alarm when the time when the first redundancy signal is inconsistent with the second redundancy signal exceeds a set value.
5. The method of claim 3, wherein using the accumulation/countdown based monitoring mode comprises:
accumulating/decrementing the state change of the discrete signal; and
and triggering an alarm when the result of the accumulation/subtraction count exceeds a monitoring threshold.
6. An apparatus for monitoring aircraft signals, comprising:
a discrete signal receiving unit that receives a discrete signal as a redundancy signal for a flight control system;
a frequency determination unit that determines a frequency of the received discrete signal;
a monitoring mode determination unit that determines a monitoring mode for the discrete signal based on a frequency of the received discrete signal; and
a monitor mode execution unit that monitors whether the discrete signal indicates an abnormality based on the determined monitor mode.
7. The apparatus of claim 6, wherein the frequency determination unit determines whether the received discrete signal is high frequency or low frequency.
8. The apparatus of claim 7, wherein the monitoring mode determination unit determines the monitoring mode for the discrete signal by:
using a comparison-based monitoring mode when the received discrete signal is low frequency; and
when the received discrete signal is high frequency, a monitoring mode based on an accumulation/subtraction count is used.
9. The apparatus of claim 8, wherein the monitoring mode execution unit executes the comparison-based monitoring mode by:
comparing a first redundancy signal in the discrete signals with a second redundancy signal in the discrete signals; and
and triggering an alarm when the time when the first redundancy signal is inconsistent with the second redundancy signal exceeds a set value.
10. The apparatus of claim 8, wherein the monitoring mode performing unit performs the accumulation/subtraction count-based monitoring mode by:
accumulating/decrementing the state change of the discrete signal; and
and triggering an alarm when the result of the accumulation/subtraction count exceeds a monitoring threshold.
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