An airborne satellite communication equipment fault detection method, device, equipment and medium

Abstract

The application discloses an airborne satellite communication equipment fault detection method and device, equipment and medium, and relates to the field of satellite communication. The method comprises the following steps: acquiring position information reported by all airborne satellite communication equipment of an airborne satellite system within a preset time; determining a beam signal fault area and an interference fault area according to the position information; if no position information reported by the current airborne satellite communication equipment is received within the preset time, it is determined that the current airborne satellite communication equipment is faulty, in the case that the remaining area in the beam coverage area, except the beam signal fault area and the interference fault area, is rain-free. It can be seen that the fault detection of the airborne satellite communication equipment is realized by combining multiple airborne satellite communication equipment; and in the process of fault detection, layered detection and judgment are adopted, that is, the judgment of the beam signal fault and the judgment of the interference fault are performed first, and then the judgment of the fault of the airborne satellite communication equipment itself is performed, so that the fault can be effectively detected.

Description

Technical Field

[0001] This application relates to the field of satellite communications, and in particular to a method, apparatus, equipment and medium for fault detection of airborne satellite communication equipment. Background Technology

[0002] Unlike traditional satellite systems, high-throughput airborne satellite systems serve airborne satellite communication equipment through dense spot beams. High-throughput airborne satellite communication equipment may malfunction during use.

[0003] Currently, common fault detection methods for airborne satellite communication equipment include Built-in Test (BIT), such as detecting anomalies in current and voltage; or using Built-in Test Equipment (BITE) for fault detection, which can detect faults in modems, antennas, and cables. However, in practice, airborne satellite communication systems may experience faults in the airborne satellite communication equipment, satellite signal, or interference. Currently, there is no method to isolate satellite signal faults from airborne satellite communication equipment faults, making it impossible to determine whether the communication fault originates from the equipment itself, the satellite signal, or interference; thus, effective fault detection for airborne satellite communication equipment is not possible.

[0004] Therefore, how to detect faults in airborne satellite communication equipment is a technical problem that urgently needs to be solved by people in this field. Summary of the Invention

[0005] The purpose of this application is to provide a method, apparatus, equipment, and medium for detecting faults in airborne satellite communication equipment.

[0006] To address the aforementioned technical problems, this application provides a fault detection method for airborne satellite communication equipment, applied to an airborne satellite system comprising multiple airborne satellite communication devices. Each beam emitted by the airborne satellite system corresponds to one or more of the aforementioned airborne satellite communication devices. The method is applied at a ground-based end and includes:

[0007] Obtain the location information reported by all airborne satellite communication devices of the airborne satellite system within a preset time period; wherein, the location information includes at least the three-dimensional location information of the airborne satellite communication devices and the number of the beam to which the airborne satellite communication devices belong;

[0008] Based on the location information, determine the areas of beam signal failure and interference failure;

[0009] If, within the beam coverage area, excluding the areas with beam signal failure and interference failure, the remaining area is rain-free, and if no location information is received from the current airborne satellite communication equipment within the preset time, then the current airborne satellite communication equipment is determined to be faulty.

[0010] Preferably, the area where the beam signal is faulty is identified includes:

[0011] Obtain the location information reported by the airborne satellite communication equipment within the preset time period;

[0012] The faulty beam is determined based on the location information; wherein, all the airborne satellite communication devices corresponding to the faulty beam have failed to report the corresponding location information;

[0013] Obtain the signal region corresponding to the faulty beam as the region where the beam signal is faulty.

[0014] Preferably, the area where the interference fault is acquired includes:

[0015] After detecting that each of the airborne satellite communication devices has started communicating with the ground terminal, the airborne satellite communication devices with communication abnormalities are identified; wherein, the airborne satellite communication devices with communication abnormalities are those that have experienced communication interruptions and whose communication has been restored.

[0016] Obtain the first location information reported by each of the aforementioned airborne satellite communication devices when communication is interrupted and the second location information reported when communication is restored;

[0017] Obtain a circular area with the first position corresponding to the three-dimensional position information in the first position information of each of the aforementioned communication anomalies and the second position corresponding to the three-dimensional position information in the second position information as the diameter, and the midpoint between the first position and the second position as the center.

[0018] Find the intersection of all circular regions;

[0019] After removing the region with the beam signal fault from the intersection region, the remaining region is taken as the region with the interference fault.

[0020] Preferably, the airborne satellite communication equipment malfunctions include: receiver malfunction, transmitter malfunction, modem malfunction, and antenna malfunction.

[0021] Preferably, detecting the current airborne satellite communication equipment malfunction includes:

[0022] If no locking signal is found in the receiving link, the receiver is determined to be faulty; wherein, the receiving link is the link through which the current airborne satellite communication equipment receives signals transmitted from the ground.

[0023] If the locking signal is present in the receiving link, the receiver is determined to be normal; if the receiver locks and demodulates the signal, the transmitter is determined to be faulty.

[0024] After determining that the receiver or transmitter is faulty, the modem fault is detected;

[0025] If the modem self-test is fault-free, the antenna fault is detected by ground-based static satellite connection test.

[0026] Preferably, detecting the antenna fault includes:

[0027] If, after determining that the receiver is faulty, the current airborne satellite communication equipment is detected to have locked onto the downlink signal on the ground, then the antenna tracking is determined to be faulty; if the current airborne satellite communication equipment fails to lock onto the downlink signal on the ground, then the antenna receiver is determined to be faulty.

[0028] If, after determining that the transmitter is faulty, it is detected that the current airborne satellite communication equipment is communicating with the ground terminal, then it is determined that the antenna receiver is tracking faulty.

[0029] If, after determining that the transmitter is faulty, it is detected that the current airborne satellite communication equipment is locked to the downlink signal on the ground and the current airborne communication equipment is unable to communicate with the ground terminal, then the antenna transmitter is determined to be faulty.

[0030] Preferably, after determining the region of the beam signal fault and the region of the interference fault, the method further includes:

[0031] Information about the areas with beam signal failure and interference failure is transmitted to the airborne satellite communication equipment via other communication links between the aircraft and the ground terminal; wherein, the other airborne satellite communication equipment refers to links other than the link between the airborne satellite communication equipment and the ground terminal.

[0032] To address the aforementioned technical problems, this application also provides an airborne satellite communication equipment fault detection device, applied to an airborne satellite system comprising multiple airborne satellite communication devices, wherein each beam emitted by the airborne satellite system corresponds to one or more of the airborne satellite communication devices, the device being applied at a ground end, and the device comprising:

[0033] The first acquisition module is used to acquire the location information reported by all the airborne satellite communication devices of the airborne satellite system within a preset time period; wherein, the location information includes at least the three-dimensional location information of the airborne satellite communication devices and the number of the beam to which the airborne satellite communication devices belong;

[0034] The first determining module is used to determine the area of ​​beam signal failure and the area of ​​interference failure based on the location information.

[0035] The second acquisition module is used to acquire the beam coverage area of ​​the airborne satellite system;

[0036] The second determining module is used to determine that the current airborne satellite communication equipment is faulty if, within a preset time, the remaining area of ​​the beam coverage area excluding the area of ​​beam signal failure and the area of ​​interference failure is rain-free.

[0037] To address the aforementioned technical problems, this application also provides an airborne satellite communication equipment fault detection device, comprising:

[0038] Memory, used to store computer programs;

[0039] A processor is used to implement the steps of the above-described airborne satellite communication equipment fault detection method when executing the computer program.

[0040] To address the aforementioned technical problems, this application also provides a computer-readable storage medium storing a computer program, which, when executed by a processor, implements the steps of the aforementioned airborne satellite communication equipment fault detection method.

[0041] This application provides a fault detection method for airborne satellite communication equipment, applied to an airborne satellite system comprising multiple airborne satellite communication devices. Each beam emitted by the airborne satellite system corresponds to one or more airborne satellite communication devices. The method is applied at the ground end and includes: acquiring position information reported by all airborne satellite communication devices within a preset time period; wherein the position information includes at least the three-dimensional position information of the airborne satellite communication devices and the beam number to which the airborne satellite communication devices belong; determining the area of ​​beam signal fault and the area of ​​interference fault based on the position information; if, within the beam coverage area excluding the areas of beam signal fault and interference fault, the remaining area is rain-free, and if no position information reported by the current airborne satellite communication device is received within the preset time period, then the current airborne satellite communication device is determined to be faulty. It can be seen that this method achieves fault detection of airborne satellite communication equipment by combining multiple airborne satellite communication devices; and in the fault detection process, a layered detection and judgment method is adopted, that is, first judging beam signal faults and interference faults, and then judging the faults of the airborne satellite communication devices themselves, thus enabling effective fault detection.

[0042] In addition, this application also provides an airborne satellite communication equipment fault detection device, an airborne satellite communication equipment fault detection equipment, and a computer-readable storage medium, which have the same or corresponding technical features as the airborne satellite communication equipment fault detection method mentioned above, and have the same effect. Attached Figure Description

[0043] To more clearly illustrate the embodiments of this application, the accompanying drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0044] Figure 1 A schematic diagram of spot beam coverage for a high-throughput airborne satellite system provided in this application embodiment;

[0045] Figure 2 A flowchart illustrating a fault detection method for airborne satellite communication equipment provided in this application embodiment;

[0046] Figure 3 This is a schematic diagram of a beam signal fault area in an interference region provided in an embodiment of this application;

[0047] Figure 4 A structural diagram of an airborne satellite communication equipment fault detection device provided in an embodiment of this application;

[0048] Figure 5A structural diagram of an airborne satellite communication equipment fault detection device provided in another embodiment of this application;

[0049] Figure 6 This is a schematic diagram of an airborne satellite communication system provided in an embodiment of this application. Detailed Implementation

[0050] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of this application.

[0051] The core of this application is to provide a method, apparatus, equipment, and medium for detecting faults in airborne satellite communication equipment.

[0052] Satellite communication failures may include faults in the satellite communication equipment itself, satellite communication failures, or failures caused by interference. To isolate satellite communication equipment failures, this application proposes a satellite communication equipment failure detection method. It should be noted that this application addresses the scenario of failure isolation for high-throughput airborne satellite communication equipment. High-throughput airborne satellite systems serve airborne satellite communication equipment through dense spot beams. Figure 1 A schematic diagram of spot beam coverage for a high-throughput airborne satellite system provided in an embodiment of this application.

[0053] To enable those skilled in the art to better understand the present application, the present application will be further described in detail below with reference to the accompanying drawings and specific embodiments. The present application provides a fault detection method for airborne satellite communication equipment, applicable to an airborne satellite system containing multiple airborne satellite communication devices. Each beam emitted by the airborne satellite system corresponds to one or more airborne satellite communication devices. This method is applied at the ground end. Figure 2 A flowchart of a fault detection method for airborne satellite communication equipment provided in this application embodiment is shown below. Figure 2 As shown, the method includes:

[0054] S10: Obtain the location information reported by all airborne satellite communication devices of the airborne satellite system within a preset time period;

[0055] The location information includes at least the three-dimensional location information of the airborne satellite communication equipment and the number of the beam to which the airborne satellite communication equipment belongs.

[0056] Typically, a single beam contains anywhere from a few to dozens of aircraft equipped with airborne satellite communication equipment. When reporting their positions to the ground, each airborne satellite communication device obtains real-time positioning information from the aircraft's Inertial Reference System (IRS) or other positioning systems such as the Global Positioning System (GPS) via the avionics interface, and then transmits this position information to the ground processing system. The position information includes the airborne satellite communication device's three-dimensional position information (altitude, longitude, latitude), the beam number to which the device belongs, and may also include the aircraft registration number and Universal Time Coordinated (UTC). It should be noted that airborne satellite communication devices can report positions in two ways: first, when communication is normal, they may report position information every T time intervals (e.g., 5 minutes); second, when communication is interrupted, they report both the position information at the time of interruption and the position information at the time of communication restoration.

[0057] S11: Determine the areas of beam signal failure and interference failure based on location information.

[0058] First, the detection of beam signal faults is explained. Specifically, identifying the area of ​​beam signal faults includes: determining the faulty beam based on location information; wherein, all airborne satellite communication equipment corresponding to the faulty beam has failed to report the corresponding location information; and obtaining the signal area corresponding to the faulty beam as the area of ​​beam signal fault.

[0059] In beam signal fault detection, for any given beam, assuming a preset time Tb, if no position information is received within Tb (e.g., beam diameter 700km, aircraft speed 700km / h, Tb not exceeding 1 hour), a beam signal fault is determined; otherwise, no beam signal fault is determined. The length of the preset time Tb is not limited. Typically, the length of Tb is related to the number of airborne satellite communication devices within the beam; the more airborne satellite communication devices, the smaller Tb can be, thus enabling the detection of beam fault information within a shorter timeframe. After determining a beam signal fault, the signal area corresponding to the faulty beam is considered the area of ​​the beam signal fault.

[0060] It should be noted that, in addition to acquiring the location information of airborne satellite communication equipment, the ground-based processing system also supports the location information of airborne satellite communication equipment from other manufacturers within the same satellite system. This is achieved by sharing information with the ground station system of the satellite system to obtain the beam area and communication status information of other manufacturers' airborne satellite communication equipment, thus effectively determining whether location information has been reported, thereby increasing the reliability of beam signal fault diagnosis. It can also be achieved through sharing 4D track tracking information from airlines. For example, if the aircraft's 4D track falls into a certain beam, but the airborne satellite communication equipment is not communicating normally, it is equivalent to determining that no location information has been reported.

[0061] After detecting beam signal faults, interference faults can be detected. Specifically, the areas of interference faults include: identifying airborne satellite communication devices with communication anomalies after communication between each airborne satellite communication device and the ground station is detected; wherein, airborne satellite communication devices with communication anomalies are those that experienced communication interruptions and then resumed communication; acquiring the first position information reported by each airborne satellite communication device with communication anomalies when communication was interrupted and the second position information reported when communication resumed; acquiring a circular area with the first position corresponding to the three-dimensional position information in the first position information and the second position corresponding to the three-dimensional position information in the second position information of each airborne satellite communication device with communication anomalies as the diameter and the midpoint between the first position and the second position as the center; acquiring the intersection area of ​​all circular areas; and after removing the areas with beam signal faults from the intersection area, the remaining area is taken as the area of ​​interference faults.

[0062] In implementation, firstly, for each airborne satellite communication device, a circle is drawn with the reported location information at the time of communication interruption and the location information at the time of communication recovery as its diameter, marked as the interference region B-XXX-TA within a certain time period, with registration number B-XXX; secondly, within time Tc, the intersection of all circles is calculated to obtain the interference region R. It should be noted that if the location information at the time of communication interruption and the location information at the time of communication recovery for a certain airborne satellite communication device contains a beam signal fault area, that area should be removed. Figure 3 This is a schematic diagram of a beam signal fault area in an interference region provided in an embodiment of this application, as shown below. Figure 3 As shown, after removing the beam fault area, the resulting interference areas are interference area 1 and interference area 2.

[0063] The above describes detecting beam fault signals to identify beam fault areas and detecting interference faults to identify interference areas. To enable airborne satellite communication equipment to distinguish between its own faults, beam faults, and interference, a preferred embodiment, after determining the areas of beam faults and interference faults, further includes: transmitting information about the beam fault areas and interference fault areas to the airborne satellite communication equipment via other communication links between the aircraft and the ground station; wherein, other airborne satellite communication equipment refers to links other than the communication link between the airborne satellite communication equipment and the ground station. These links could be established via communication links with the ground station, such as Air to Ground (ATG), L-Satellite Communication, or Aircraft Communications Addressing and Reporting System (ACARS), to transmit the beam fault information and interference fault information to the airborne satellite communication equipment.

[0064] S12: Obtain the beam coverage area of ​​the airborne satellite system;

[0065] S13: If the remaining area within the beam coverage area, excluding areas with beam signal failure and areas with interference failure, is rain-free, and if the location information reported by the current airborne satellite communication equipment is not received within a preset time, then the current airborne satellite communication equipment is determined to be faulty.

[0066] In step S11, the areas of beam signal failure and interference failure are obtained. If neither beam signal failure nor interference failure exists, the remaining area is the beam coverage area; if there is no beam signal failure but only interference failure, the remaining area is the intersection of the beam coverage area and the interference failure area; if there is a beam signal failure but no interference failure, the remaining area is the intersection of the beam coverage area and the beam signal failure area. If there is no rain in the remaining area, and no position information is received from the current airborne satellite communication equipment within a preset time, the current airborne satellite communication equipment is determined to be faulty.

[0067] The airborne satellite communication equipment fault detection method provided in this embodiment is applied to an airborne satellite system containing multiple airborne satellite communication devices. Each beam emitted by the airborne satellite system corresponds to one or more airborne satellite communication devices. This method is applied at the ground end and includes: acquiring the location information reported by all airborne satellite communication devices of the airborne satellite system within a preset time period; wherein, the location information includes at least the three-dimensional location information of the airborne satellite communication devices and the beam number to which the airborne satellite communication devices belong; determining the area of ​​beam signal fault and the area of ​​interference fault based on the location information; if, in the case that the remaining area of ​​the beam coverage area excluding the areas of beam signal fault and interference fault is rain-free, and if the location information reported by the current airborne satellite communication device is not received within the preset time period, then the current airborne satellite communication device is determined to be faulty. It can be seen that this method achieves fault detection of airborne satellite communication devices by combining multiple airborne satellite communication devices; and in the fault detection process, a layered detection and judgment method is adopted, that is, first judging beam signal faults and interference faults, and then judging the faults of the airborne satellite communication devices themselves, so as to effectively detect faults.

[0068] The above embodiments identified the faults of the airborne satellite communication equipment itself. In practice, in order to more accurately detect the faults of the airborne satellite communication equipment itself, the preferred implementation is that the faults of the airborne satellite communication equipment include: receiver faults, transmitter faults, modem faults, and antenna faults of the airborne satellite communication equipment.

[0069] Specifically, detecting faults in current airborne satellite communication equipment includes:

[0070] If no locking signal is found in the receiving link, the receiver is determined to be faulty; where the receiving link is the link through which the current airborne satellite communication equipment receives signals transmitted from the ground.

[0071] If a lock-in signal is present in the receiving link, the receiver is considered to be functioning normally; if the receiver locks in and demodulates the signal, the transmitter is considered to be faulty.

[0072] After determining that the receiver or transmitter is faulty, the modem is then tested for faults.

[0073] If the modem self-test is successful, antenna faults are detected through ground-based static satellite connection tests.

[0074] The detection of receiver channel faults in airborne satellite communication equipment specifically involves detecting receiver faults. After obtaining information on beam signal faults and interference faults, and provided the airborne satellite communication equipment is not located within the beam signal fault and interference area and there is no rain, it is determined whether the receiver is properly locked onto the signal. If there is no downlink lock signal, the receiver is considered faulty.

[0075] After diagnosing receiver malfunctions, the next step is to detect malfunctions in the airborne satellite communication equipment's transmission channel. Specifically, this involves detecting malfunctions in the airborne satellite communication equipment's transmitter. If the receiver locks and demodulates, the malfunction is determined to be in the transmitter.

[0076] Then, modem malfunctions are diagnosed. If a receive or transmit channel failure occurs, the modem can be replaced from the aircraft and tested in a laboratory (in a laboratory environment, the modem management unit communicates directly with the ground master station via intermediate frequency signals, without the need for an airborne satellite antenna) to verify its functionality. If the modem is found to be faulty in the laboratory, it is determined to be a modem malfunction; otherwise, the airborne satellite antenna malfunction is diagnosed.

[0077] When a receiver or transmitter channel failure occurs, further assessment is performed through ground-based geostationary satellite connection testing. Antenna fault detection includes: after determining a receiver fault, if the current airborne satellite communication equipment is detected to have locked onto a downlink signal on the ground, then an antenna tracking fault is determined; if the current airborne satellite communication equipment fails to lock onto a downlink signal on the ground, then an antenna receiver fault is determined.

[0078] If, after determining that the transmitter is faulty, it is detected that the onboard satellite communication equipment is communicating with the ground, then the antenna receiver tracking is faulty.

[0079] If, after a transmitter malfunction is identified, the current airborne satellite communication equipment is found to be locked on a downlink signal on the ground and is unable to communicate with the ground, then the antenna transmitter malfunction is determined.

[0080] Specifically, if a receiving channel failure occurs, and the airborne satellite communication equipment can lock onto the downlink signal on the ground, then the airborne satellite antenna tracking is faulty (e.g., aging), and the airborne satellite antenna needs to be recalibrated.

[0081] If a receiving channel failure occurs and the airborne satellite communication equipment cannot lock onto the downlink signal on the ground, then the airborne satellite antenna receiver is faulty and the receiving antenna array needs to be replaced.

[0082] If a transmission channel failure occurs, and the transmitter is still able to communicate with the satellite ground station system, then the transmission channel failure is caused by an antenna receiver tracking failure.

[0083] If a transmission channel failure occurs, and the airborne satellite communication equipment can lock onto the downlink signal on the ground but cannot communicate with the satellite ground station system, then the airborne satellite antenna transmitter is faulty and the transmitting antenna array needs to be replaced.

[0084] The method provided in this embodiment identifies faults in the airborne satellite communication equipment itself, including receiver faults, transmitter faults, modem faults, and antenna faults. This allows for a more accurate determination of the location of the fault and enables more precise detection of the airborne satellite communication equipment faults.

[0085] The above embodiments have described the fault detection method for airborne satellite communication equipment in detail. This application also provides an airborne satellite communication equipment fault detection device and corresponding embodiments thereof. It should be noted that this application describes the embodiments of the device part from two perspectives: one is based on the functional module, and the other is based on the hardware.

[0086] This embodiment provides an airborne satellite communication equipment fault detection device, which is applied to an airborne satellite system containing multiple airborne satellite communication devices. Each beam emitted by the airborne satellite system corresponds to one or more airborne satellite communication devices, and the device is applied at the ground end. Figure 4 A structural diagram of an airborne satellite communication equipment fault detection device provided in one embodiment of this application. Based on the functional modules, this embodiment includes:

[0087] The first acquisition module 10 is used to acquire the position information reported by all airborne satellite communication devices of the airborne satellite system within a preset time period; wherein, the position information includes at least the three-dimensional position information of the airborne satellite communication devices and the number of the beam to which the airborne satellite communication devices belong;

[0088] The first determining module 11 is used to determine the area of ​​beam signal failure and the area of ​​interference failure based on the location information;

[0089] The second acquisition module 12 is used to acquire the beam coverage area of ​​the airborne satellite system;

[0090] The second determining module 13 is used to determine that the current airborne satellite communication equipment is faulty if the remaining area of ​​the beam coverage area, excluding the area with beam signal failure and the area with interference failure, is rain-free within a preset time.

[0091] Since the embodiments of the apparatus and the method correspond to each other, please refer to the description of the embodiments in the method section for the embodiments of the apparatus, which will not be repeated here. Furthermore, it has the same beneficial effects as the airborne satellite communication equipment fault detection method mentioned above.

[0092] Furthermore, this embodiment also provides an airborne satellite communication equipment fault detection device, applied to an airborne satellite system containing multiple airborne satellite communication devices. Each beam emitted by the airborne satellite system corresponds to one or more airborne satellite communication devices. This device is applied to the airborne satellite communication equipment end; the device includes:

[0093] The reporting module is used to report location information to the ground terminal;

[0094] The receiving module is used to receive the detection results of beam signal failure areas, interference failure areas, and current airborne satellite communication equipment failures transmitted by the ground end. Among them, the beam signal failure areas and interference failure areas are determined by the ground end based on the position information reported by all airborne satellite communication equipment of the airborne satellite system within a preset time. The current airborne satellite communication equipment failure is determined by the ground end acquiring the beam coverage area of ​​the airborne satellite system. If the remaining area in the beam coverage area, excluding the beam signal failure areas and interference failure areas, is rain-free, and no position information reported by the current airborne satellite communication equipment is received within the preset time, the failure is determined.

[0095] Figure 5 This is a structural diagram of an airborne satellite communication equipment fault detection device provided in another embodiment of this application. This embodiment is based on a hardware perspective, such as... Figure 5 As shown, the airborne satellite communication equipment fault detection equipment includes:

[0096] Memory 20 is used to store computer programs;

[0097] The processor 21 is used to execute a computer program to implement the steps of the airborne satellite communication equipment fault detection method mentioned in the above embodiments.

[0098] The processor 21 may include one or more processing cores, such as a quad-core processor or an octa-core processor. The processor 21 may be implemented using at least one of the following hardware forms: Digital Signal Processor (DSP), Field-Programmable Gate Array (FPGA), or Programmable Logic Array (PLA). The processor 21 may also include a main processor and a coprocessor. The main processor, also known as the Central Processing Unit (CPU), is used to process data in the wake-up state; the coprocessor is a low-power processor used to process data in the standby state. In some embodiments, the processor 21 may integrate a Graphics Processing Unit (GPU), which is responsible for rendering and drawing the content to be displayed on the screen. In some embodiments, the processor 21 may also include an Artificial Intelligence (AI) processor, which is used to handle computational operations related to machine learning.

[0099] The memory 20 may include one or more computer-readable storage media, which may be non-transitory. The memory 20 may also include high-speed random access memory and non-volatile memory, such as one or more disk storage devices or flash memory devices. In this embodiment, the memory 20 is used to store at least the following computer program 201, which, after being loaded and executed by the processor 21, can implement the relevant steps of the airborne satellite communication equipment fault detection method disclosed in any of the foregoing embodiments. In addition, the resources stored in the memory 20 may also include an operating system 202 and data 203, and the storage method may be temporary or permanent storage. The operating system 202 may include Windows, Unix, Linux, etc. The data 203 may include, but is not limited to, the data involved in the aforementioned airborne satellite communication equipment fault detection method.

[0100] In some embodiments, the airborne satellite communication equipment fault detection device may further include a display screen 22, an input / output interface 23, a communication interface 24, a power supply 25, and a communication bus 26.

[0101] Those skilled in the art will understand that Figure 5 The structure shown does not constitute a limitation on the fault detection equipment for airborne satellite communication equipment and may include more or fewer components than shown.

[0102] The airborne satellite communication equipment fault detection device provided in this application includes a memory and a processor. When the processor executes the program stored in the memory, it can implement the following method: airborne satellite communication equipment fault detection method, with the same effect as above.

[0103] This application also provides an embodiment corresponding to a computer-readable storage medium. The computer-readable storage medium stores a computer program, which, when executed by a processor, implements the steps described in the above method embodiments (which may be a method corresponding to a ground-based terminal, a method corresponding to an airborne satellite communication device, or a method corresponding to both ground-based and airborne satellite communication devices).

[0104] It is understood that if the methods in the above embodiments are implemented as software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or all or part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and executes all or part of the steps of the methods described in the various embodiments of this application. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0105] The computer-readable storage medium provided in this application includes the aforementioned method for fault detection of airborne satellite communication equipment, and has the same effect.

[0106] To enable those skilled in the art to better understand the present application, the following description is provided in conjunction with the appendix. Figure 6 The present application will be further described in detail with reference to specific embodiments. Figure 6 This is a schematic diagram of an airborne satellite communication system provided in an embodiment of this application, such as... Figure 6 As shown, the system includes an airborne IRS system 30, an airborne satellite communication device 31, and a ground processing system 32. The airborne satellite communication device 31 includes a modem management unit and an airborne satellite antenna. The modem management unit includes an avionics interface module, a position reporting module, a beam fault receiving module, and an interference fault receiving module. The ground processing system 32 includes an airborne satellite communication device position information collection module, a fault analysis module, and a fault information distribution module.

[0107] The avionics interface module obtains real-time positioning information from the airborne IRS system 30 or other positioning systems such as GPS, and sends the position information to the ground processing system 32 through the position reporting module. The airborne equipment position information collection module of the ground processing system 32 collects the position information of multiple airborne satellite communication devices and sends it to the fault analysis module for fault analysis. Finally, the ground processing system 32 sends the fault information to the beam fault receiving module or interference fault receiving module in the airborne satellite communication device 31 through other airborne communication links between the aircraft and the ground (such as ATG, L-Satellite, ACARS, etc.).

[0108] The airborne satellite communication system provided in this embodiment achieves fault isolation and detection of airborne satellite communication equipment by combining multiple airborne satellite communication devices.

[0109] The foregoing has provided a detailed description of a fault detection method, apparatus, device, and medium for airborne satellite communication equipment provided in this application. The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the apparatus disclosed in the embodiments, since it corresponds to the method disclosed in the embodiments, the description is relatively simple; relevant parts can be referred to in the method section. It should be noted that those skilled in the art can make several improvements and modifications to this application without departing from the principles of this application, and these improvements and modifications also fall within the protection scope of the claims of this application.

[0110] It should also be noted that, in this specification, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

Claims

1. A method for fault detection in airborne satellite communication equipment, characterized in that, An airborne satellite system comprising multiple airborne satellite communication devices, wherein each beam emitted by the airborne satellite system corresponds to one or more of the airborne satellite communication devices, the method is applied at a ground end, and the method includes: Obtain the location information reported by all airborne satellite communication devices of the airborne satellite system within a preset time period; wherein, the location information includes at least the three-dimensional location information of the airborne satellite communication devices and the number of the beam to which the airborne satellite communication devices belong; Based on the location information, determine the areas of beam signal failure and interference failure; Obtain the beam coverage area of ​​the airborne satellite system; If, within the beam coverage area, excluding the area with the beam signal failure and the area with the interference failure, the remaining area is rain-free, and if no location information is received from the current airborne satellite communication equipment within the preset time, then the current airborne satellite communication equipment is determined to be faulty. The areas where the interference fault is located include: After detecting that each of the airborne satellite communication devices has started communicating with the ground terminal, the airborne satellite communication devices with communication abnormalities are identified; wherein, the airborne satellite communication devices with communication abnormalities are those that have experienced communication interruptions and whose communication has been restored. Obtain the first location information reported by each of the aforementioned airborne satellite communication devices when communication is interrupted and the second location information reported when communication is restored; Obtain a circular area with the first position corresponding to the three-dimensional position information in the first position information of each of the aforementioned communication anomalies and the second position corresponding to the three-dimensional position information in the second position information as the diameter, and the midpoint between the first position and the second position as the center. Find the intersection of all circular regions; After removing the region with the beam signal fault from the intersection region, the remaining region is taken as the region with the interference fault.

2. The method for fault detection of airborne satellite communication equipment according to claim 1, characterized in that, The areas where the beam signal fault is located include: The faulty beam is determined based on the location information; wherein, all the airborne satellite communication devices corresponding to the faulty beam have failed to report the corresponding location information; Obtain the signal region corresponding to the faulty beam as the region where the beam signal is faulty.

3. The method for fault detection of airborne satellite communication equipment according to claim 1 or 2, characterized in that, The airborne satellite communication equipment malfunctions include: receiver malfunction, transmitter malfunction, modem malfunction, and antenna malfunction.

4. The method for fault detection of airborne satellite communication equipment according to claim 3, characterized in that, Detecting faults in the current airborne satellite communication equipment includes: If no locking signal is found in the receiving link, the receiver is determined to be faulty; wherein, the receiving link is the link through which the current airborne satellite communication equipment receives signals transmitted from the ground. If the locking signal is present in the receiving link, the receiver is determined to be normal; if the receiver locks and demodulates the signal, the transmitter is determined to be faulty. After determining that the receiver or transmitter is faulty, the modem fault is detected; If the modem self-test is fault-free, the antenna fault is detected by ground-based static satellite connection test.

5. The airborne satellite communication equipment fault detection method according to claim 4, characterized in that, Detecting the antenna fault includes: If, after determining that the receiver is faulty, the current airborne satellite communication equipment is detected to have locked onto the downlink signal on the ground, then the antenna tracking is determined to be faulty; if the current airborne satellite communication equipment fails to lock onto the downlink signal on the ground, then the antenna receiver is determined to be faulty. If, after determining that the transmitter is faulty, it is detected that the current airborne satellite communication equipment is communicating with the ground terminal, then it is determined that the antenna receiver is tracking faulty. If, after determining that the transmitter is faulty, it is detected that the current airborne satellite communication equipment is locked to the downlink signal on the ground and the current airborne communication equipment is unable to communicate with the ground terminal, then the antenna transmitter is determined to be faulty.

6. The method for fault detection of airborne satellite communication equipment according to claim 1, characterized in that, After determining the areas of the beam signal fault and the interference fault, the method further includes: Information about the areas with beam signal failure and interference failure is transmitted to the airborne satellite communication equipment via other communication links between the aircraft and the ground terminal; wherein, the other airborne satellite communication equipment refers to links other than the link between the airborne satellite communication equipment and the ground terminal.

7. A fault detection device for airborne satellite communication equipment, characterized in that, An apparatus applicable to an airborne satellite system comprising multiple airborne satellite communication devices, wherein each beam emitted by the airborne satellite system corresponds to one or more of the airborne satellite communication devices, the apparatus being applied at a ground end, the apparatus comprising: The first acquisition module is used to acquire the location information reported by all the airborne satellite communication devices of the airborne satellite system within a preset time period; wherein, the location information includes at least the three-dimensional location information of the airborne satellite communication devices and the number of the beam to which the airborne satellite communication devices belong; The first determining module is used to determine the area of ​​beam signal failure and the area of ​​interference failure based on the location information; The second acquisition module is used to acquire the beam coverage area of ​​the airborne satellite system; The second determining module is used to determine that the current airborne satellite communication equipment is faulty if, within the preset time, the remaining area of ​​the beam coverage area excluding the area of ​​beam signal failure and the area of ​​interference failure is rain-free. The areas where the interference fault is located include: After detecting that each of the airborne satellite communication devices has started communicating with the ground terminal, the airborne satellite communication devices with communication abnormalities are identified; wherein, the airborne satellite communication devices with communication abnormalities are those that have experienced communication interruptions and whose communication has been restored. Obtain the first location information reported by each of the aforementioned airborne satellite communication devices when communication is interrupted and the second location information reported when communication is restored; Obtain a circular area with the first position corresponding to the three-dimensional position information in the first position information of each of the aforementioned communication anomalies and the second position corresponding to the three-dimensional position information in the second position information as the diameter, and the midpoint between the first position and the second position as the center. Find the intersection of all circular regions; After removing the region with the beam signal fault from the intersection region, the remaining region is taken as the region with the interference fault.

8. A fault detection device for airborne satellite communication equipment, characterized in that, include: Memory, used to store computer programs; A processor, configured to execute the computer program to implement the steps of the airborne satellite communication equipment fault detection method as described in any one of claims 1 to 6.

9. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a computer program that, when executed by a processor, implements the steps of the airborne satellite communication equipment fault detection method as described in any one of claims 1 to 6.

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