Optoelectronic load ground detection and avionics simulation system and method based on fc point-to-point

Abstract

The present application relates to avionics ground test, photoelectric load production debugging technical field, especially to a kind of photoelectric load ground detection and avionics simulation system and method based on FC point-to-point, with simulation control host computer as core, replace complex exchange avionics network by FC point-to-point direct connection, under the condition of no real avionics equipment, no switch, the behavior of avionics node required by photoelectric load, communication timing and instruction logic are completely simulated, to simplify the physical connection logic simulation complete complex avionics network to the whole communication behavior of photoelectric load, while through image acquisition module real-time recycling image or video data stream, realize control flow+image or video data stream double closed loop.The system supports test configuration, instruction sending, data monitoring, record playback, automatic criterion, fault location and test report generation, constitute complete photoelectric load ground detection system.

Description

Technical Field

[0001] This invention belongs to the field of avionics ground testing and optoelectronic payload production and debugging technology, and in particular relates to a ground testing and avionics simulation system and method for optoelectronic payloads based on FC point-to-point. Background Technology

[0002] Fiber Channel (FC), as a high-speed information exchange network, is used for data interaction between airborne equipment. Its advantages, such as high performance, low latency, and strong anti-interference capabilities, have led to its widespread use within avionics systems. Optoelectronic payloads are a crucial component of modern military aircraft combat systems and are vital sensing devices for UAVs and spacecraft. During the production and commissioning phase, it is essential to fully verify the various functions of the optoelectronic payload, its communication interface with the avionics system, and its dynamic performance under simulated mission scenarios. While FC communication replaces traditional communication methods such as RS232, RS422, and ARINC429, it introduces new technical challenges during the production and commissioning of optoelectronic payloads. Traditional communication methods allow for simple and independent testing by directly connecting a computer to the optoelectronic payload under test via an adapter unit. However, FC communication commissioning, due to its complex protocol and data interaction with each unit in the avionics system through a switch, is isolated from the complete avionics system and switch environment. This makes independent and comprehensive commissioning and efficient testing of the optoelectronic payload difficult. Typically, it requires waiting for the actual avionics equipment to be ready, preventing independent and parallel functional verification early in the assembly process of the optoelectronic payload, thus becoming a key bottleneck in production and commissioning. Meanwhile, existing technical solutions typically place optoelectronic payloads in a switched network and do not specifically design for link establishment, multi-node timing simulation, and command and image synchronization closed loop in FC point-to-point direct connection mode, which cannot meet the independent testing needs of the production front end.

[0003] In existing technologies, Chinese Patent Publication CN109842534B, "A Device Testing and Verification Method Based on a Switched FC Simulation Card," proposes using a multi-port FC simulation card, a switch, and an FC tester to achieve point-to-point direct connection to multiple devices under test. This is a switched simulation architecture, lacking a protocol-scalable configuration library, a dual closed-loop system for FC commands and image data streams, the ability to quickly adapt to multiple payload models, and support for early independent parallel debugging of optoelectronic payloads, still relying on switch networking. Chinese Patent Publication CN103248537B, "A Hybrid Avionics System Tester Based on FC-AE-1553," proposes a testing method for avionics systems with multiple different protocols. It is mainly used to test integrated, multi-protocol hybrid complete systems, rather than a specialized, lightweight simulation testing solution for production front-end applications or to replace complex environments. It cannot achieve single-payload verification outside the avionics system and does not support early debugging. Chinese patent publication CN112217567B, "A Multi-Node Simulation Method for FC Bus," utilizes an optical switch matrix and an external optical switch to enable a single FC simulation board to time-division multiplex multiple device nodes. This primarily addresses the issues of high resource consumption and complex operation of simulation boards in system-level integration testing, allowing for the construction of more complex simulation network topologies with fewer hardware resources, thus optimizing the system testing environment. However, it still relies on an external switch and cannot achieve switchless point-to-point independent testing.

[0004] The following technical problems are commonly found in existing technical solutions: 1. High environmental dependence, unable to achieve independent debugging: Existing technologies rely on building complete and expensive real avionics systems or dedicated hardware test instruments for testing. Environment construction is difficult and costly. Complete avionics systems are expensive and bulky, making them difficult to deploy flexibly in ordinary production workshops or laboratories. Testing resources are scarce, which seriously restricts the production pace.

[0005] 2. The testing efficiency is low. The testing depends on the availability of the entire avionics system. It is impossible to independently and in parallel debug individual optoelectronic payloads. The test scenarios are limited by real equipment and it is difficult to cover all boundary conditions and abnormal operating conditions.

[0006] 3. Difficult fault location and lengthy troubleshooting cycle: When communication failures or command execution errors occur, due to the many network links, it is difficult to quickly locate the root cause of the problem in the complex real avionics network, resulting in a long troubleshooting cycle and affecting production efficiency.

[0007] 4. Rigid protocol adaptation and insufficient production line flexibility: Existing hardware-based dedicated testers have fixed protocols and interfaces that are difficult to quickly adapt to the different FC application layer protocols of various optoelectronic load models. Once the product is updated or the communication protocol changes, it is often necessary to adjust the hardware or carry out in-depth software development, resulting in low reuse rate of test equipment and a lack of flexibility in production lines to cope with multi-model, small-batch production modes. Summary of the Invention

[0008] In view of this, the present invention aims to provide a ground detection and avionics simulation system and method for optoelectronic payloads based on FC point-to-point connection. Through point-to-point direct connection and supplemented by accurate multi-node behavior simulation, it proves that effective verification can be completed without complex switching networks during the production and commissioning stage of optoelectronic payloads.

[0009] To achieve the above objectives, the technical solution created by this invention is implemented as follows: A ground detection and avionics simulation system for optoelectronic loads based on FC point-to-point includes a simulation control host, a multimode two-core optical fiber, an image cable, and the optoelectronic load under test. One end of the multimode two-core optical fiber is connected to the simulation control host, and the other end is connected to the photoelectric load under test. One core of the multimode two-core optical fiber is used to send the encapsulated FC command data, and the other core is used to receive the real-time FC data returned by the photoelectric load under test. The simulation control host includes a human-machine interface, an avionics simulation module, an extensible protocol configuration module, a PCIe driver module, an FC communication adapter unit, and an image acquisition module. The FC communication adapter unit is installed on the motherboard of the simulation control host through the PCIe driver module. The image acquisition module is connected to the photoelectric load under test through the image cable. The extensible protocol configuration module includes protocol loading, frame structure extension, communication parameter extension, data mapping, and a protocol configuration library. The avionics simulation module includes FC link state machine simulation, multi-node timing simulation, and avionics unit simulation. The avionics unit simulation includes a mission unit, integrated inertial navigation system, navigation fusion, health management, system time management, and display and control unit. The FC link state machine simulation is used to realize the initialization, heartbeat maintenance, and reconnection states of the FC link, so that the tested optoelectronic payload perceives link behavior consistent with the real avionics system. The multi-node timing simulation is used to configure the FC address, message ID, transmission period, and priority of each virtual node. When the transmission time of a virtual node arrives, the control command generation of that node is triggered. When multiple virtual nodes are triggered simultaneously, a priority-based preemptive method is used to send commands sequentially, allowing a single physical link to logically carry the behavior of multiple virtual nodes. When the avionics simulation module receives the simulated data types, parameters, and scenarios sent by the human-machine interface, it generates high-level control commands for the optoelectronic payload that conform to the protocol. Then, it calls the currently loaded protocol configuration file in the extensible protocol module to map the logical commands into data structures with specific field definitions that meet the requirements of the current tested payload, and then transmits them to the FC communication adapter unit.

[0010] As an optional approach, the multi-node timing simulation employs a high-precision timer, configuring an independent trigger time offset and transmission jitter range for each virtual avionics node, so that the issuance times of commands from each node are not completely synchronized, thus closely resembling the real environment.

[0011] As an optional solution, the extensible protocol configuration module includes protocol loading, frame structure extension, communication parameter extension, data mapping, and protocol configuration library. The protocol loading is used so that when the operator selects the photoelectric load to be measured on the human-machine interface, the system automatically loads the corresponding protocol file from the protocol configuration library. The frame structure extension is used to expand support for adding or deleting fields, adjusting bit width and offset, defining structures, and adapting to various custom protocols. The communication parameter extension is used to support the setting of FC address, message ID, heartbeat period, and timeout retransmission mechanism; The data mapping is used to automatically map upper-level simulation commands to protocol fields. The protocol configuration library stores communication protocol parameters for multiple payload models in a structure file, supporting add, edit, and delete operations.

[0012] As an optional solution, the FC communication adapter unit includes: an optical transceiver module and an FPGA data protocol encapsulation. The optical transceiver module is used to convert the FC transmitted and received data between optical signals and electrical signals. The FPGA data protocol encapsulation is used to encapsulate the data into standard FC-AE-ASM protocol data, buffer the protocol frames, shape the traffic, and drive the FC network controller.

[0013] As an optional solution, the image acquisition module acquires image or video stream data returned by the photoelectric load in real time and uploads it to the human-machine interface. The human-machine interface performs correlation analysis on the returned image data and image annotation information with the sent instructions based on a unified timestamp to verify the accuracy of the load action and response delay. When a target position of the returned image data is clicked on the returned image display interface, a tracking instruction is generated based on the target position and sent to the photoelectric load under test, realizing closed-loop control with the photoelectric load control instruction.

[0014] As an optional solution, the message structure of the standard FC-AE-ASM protocol data includes a fixed frame header, a payload data area, and a fixed frame tail. The fixed frame header includes a general FC frame header and a specific ASM frame header. The length of the payload data area is determined according to the actual protocol situation. The fixed frame tail contains CRC checksum information.

[0015] As an optional solution, the measured photoelectric load conforms to the standard FC communication protocol interface, which is used to receive and parse the FC command frames sent by this system, perform actions such as servo motion and imaging sensor control, and encapsulate the status data into FC response frames and image data and send them back to the system.

[0016] A ground-based electro-optical load detection and avionics simulation method based on FC point-to-point, applied to the aforementioned FC point-to-point electro-optical load ground-based detection and avionics simulation system, the method comprising: Step S1: System Construction and Initialization S1.1: Physical connection: Using a single standard multimode two-core optical fiber, the optical transceiver module interface of the FC communication adapter unit is directly connected to the FC device interface of the photoelectric load under test to establish a point-to-point physical link. The image acquisition module is connected to the photoelectric load under test using an image cable to receive the real-time output image or video data of the photoelectric load under test. S1.2: Logic initialization, start the simulation control host and human-machine interface, select the model of the payload under test through the drop-down menu of the human-machine interface, and the system automatically loads the corresponding matching avionics system protocol configuration file from the protocol configuration library. The avionics system protocol configuration file includes the type, address identifier, etc. of the FC-AE-ASM protocol and the specific structure of the variable data payload area. After the avionics system protocol configuration file is loaded, the system drives the FC communication adapter unit to complete self-test and establish a port-level connection with the optoelectronic payload under test to complete link synchronization. Step S2: Test Simulation and Instruction Generation S2.1: Scenario Configuration. In the human-machine interface of the simulation control host, a test scenario is selected or edited. The test scenario includes at least the simulated aircraft platform state parameters, the desired optoelectronic payload operating mode, the additional parameters for the desired optoelectronic payload operating mode, and the simulated target parameters. The aircraft platform state parameters include flight altitude, speed, position, and attitude angle. The desired optoelectronic payload operating mode includes wide-area imaging, area imaging, area monitoring, automatic tracking, and manual search. The additional parameters include scanning method, scanning start angle, and scanning end angle. The simulated target parameters include target longitude, latitude, and altitude. S2.2: Logic calculation. The avionics simulation module calculates and generates high-level control commands that conform to avionics specifications in real time based on the scenario script. It simulates the actual flight state parameters of the aircraft based on the selected scenario script. The high-level control commands include at least the optoelectronic payload working mode and sensor control commands. The optoelectronic payload working modes include wide-area imaging, area imaging, area surveillance, and automatic tracking. The sensor control commands include imaging mode, optical lens zoom, infrared cooler switch, and laser ranging. S2.3: Command Generation: Real-time calculated high-level control commands conforming to avionics specifications are sent to the FC communication adapter unit through the PCIe driver module; Step S3: Command Injection and Load Response S3.1: Protocol encapsulation, the FPGA data protocol encapsulation in the FC communication adapter unit encapsulates the received instructions into one or more complete FC frame sequences according to the preset avionics network FC-AE-ASM protocol; the encapsulation process includes adding frame headers, instruction data payloads, and calculating CRC check codes; S3.2: Command transmission: The encapsulated FC frame sequence is buffered and traffic shaped by the FPGA protocol processing engine, and then converted into a serial optical signal conforming to the FC-FS protocol specification by the FC network controller and transmitted. S3.3: Physical transmission, the serial optical signal is transmitted to the FC interface of the photoelectric load under test through the point-to-point physical link; S3.4: Load execution, the FC interface board of the photoelectric load under test receives and parses the FC frame, extracts the valid control command data, drives its own servo mechanism and imaging sensor to perform corresponding actions, and the image data or video data generated by the execution of the photoelectric load under test is transmitted in real time through the image cable according to the system configuration, for subsequent acquisition; Step S4: Data Recycling and Status Monitoring S4.1: Data feedback, the photoelectric load under test encapsulates the execution result into a response FC frame, the response data includes load status information, and the image data or video data of the photoelectric load under test returns real-time image data through the image cable; S4.2: Signal reception and conversion. The optical signal transmitted back by the photoelectric load under test is converted into an electrical signal by the optical module of the FC communication adapter unit. The FPGA data protocol engine parses the FC frame data, extracts the data payload area, and uploads it to the simulation control host through the PCIe bus. The image data or video data is acquired and processed by the image acquisition module and then uploaded to the human-machine interface. S4.3: Real-time processing and display: The simulation control host synchronously parses and decodes the timestamps of the FC-returned data and image data, updates the load status parameters in real time on the human-machine interface, and dynamically displays the image and video streams to form a visual monitoring system. Step S5: Validation Analysis and Report Generation S5.1: Data recording and synchronization. The system uses timestamps as a basis to synchronously record all downlink sent command FC frames, uplink received response FC frames, and calculated simulation environment parameters, forming a complete and traceable test log. S5.2: Performance analysis and judgment. The test management module automatically analyzes the load performance based on preset criteria and determines whether the test item passes or fails. S5.3: Report generation and fault indication, automatically generating structured test reports; if a communication CRC error, response timeout, or performance deviation is detected, the system will issue an alarm on the human-machine interface and locate the fault to one of the three components—the simulation control host, the multimode two-core optical fiber, or the photoelectric load under test—based on a simplified point-to-point physical link topology.

[0017] As an optional approach, the preset criteria include the error tolerance of angle command and feedback, image quality index, and communication delay threshold.

[0018] Compared with the prior art, the present invention can achieve the following beneficial effects: This invention provides a ground detection and avionics simulation system and method for optoelectronic payloads based on FC point-to-point connections. With a simulation control host as the core, it replaces the complex switched avionics network with FC point-to-point direct connections. Under conditions where no real avionics equipment or switches are available, it fully simulates the avionics node behavior, communication timing, and command logic required for the optoelectronic payload. It simulates all communication behaviors of a complete complex avionics network for the optoelectronic payload using simplified physical connection logic. The system adapts to different payload FC-AE-ASM protocols through an extensible protocol configuration module. The avionics simulation module simulates nodes such as the mission aircraft, integrated inertial navigation system, navigation data fusion, health management unit, system time management, and display and control unit, generating high-level control commands. These commands are sent to the FC communication adaptation unit via a PCIe driver module, where the FPGA performs FC frame encapsulation, flow shaping, and optoelectronic conversion to establish full-duplex point-to-point communication with the payload. Simultaneously, the image acquisition module collects image or video data streams in real time, achieving a dual closed loop of control flow and image or video data stream. The system supports test configuration, command sending, data monitoring, record playback, automatic judgment, fault location, and test report generation, forming a complete ground-based detection system for photoelectric loads. Attached Figure Description

[0019] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments and descriptions of the invention are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 The structural block diagram of the FC point-to-point photoelectric load ground detection and avionics simulation system described in the embodiment of the present invention; Figure 2 A schematic diagram of the message structure in the FC point-to-point photoelectric payload ground detection and avionics simulation system described in the embodiment of the present invention; Figure 3This is a schematic diagram of the test workflow of the FC point-to-point photoelectric load ground detection and avionics simulation method described in the embodiments of the present invention.

[0020] Explanation of reference numerals in the attached figures: Simulation control host 1, multimode two-core optical fiber 2, image cable 3, photoelectric load under test 4, human-machine interface 11, avionics simulation module 12, scalable protocol configuration module 13, PCIe driver module 14, FC communication adapter unit 15, image acquisition module 16. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and do not constitute a limitation thereof.

[0022] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other.

[0023] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art will understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0024] The invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0025] like Figure 1 As shown in the embodiment of the present invention, the ground detection and avionics simulation system for photoelectric load based on FC point-to-point includes a simulation control host 1, a multimode two-core optical fiber 2, an image cable 3, and the photoelectric load under test 4. One end of the multimode two-core optical fiber 2 is connected to the simulation control host 1, and the other end is connected to the photoelectric load under test 4. One core of the multimode two-core optical fiber 2 is used to send the encapsulated FC command data, and the other core is used to receive the real-time FC data returned by the photoelectric load under test 4. The simulation control host 1 includes a human-machine interface 11, an avionics simulation module 12, an expandable protocol configuration module 13, a PCIe driver module 14, an FC communication adapter unit 15, and an image acquisition module 16. The FC communication adapter unit is installed on the motherboard of the simulation control host 1 through the PCIe driver module 14. The image acquisition module 16 is connected to the photoelectric load under test 4 through the image cable 3. The expandable protocol configuration module 13 includes protocol loading, frame structure extension, communication parameter extension, data mapping, and protocol configuration library. The avionics simulation module 12 includes FC link state machine simulation, multi-node timing simulation, and avionics unit simulation. The avionics unit simulation includes a mission unit, integrated inertial navigation, navigation fusion, health management, system time management, and display and control unit. The FC link state machine simulation is used to realize the initialization, heartbeat maintenance, and reconnection states of the FC link, so that the measured optoelectronic payload 4 perceives link behavior consistent with the real avionics system. The multi-node timing simulation is used to configure the FC address, message ID, transmission period, and priority of each virtual node. When the transmission time of a virtual node arrives, the control command of that node is triggered. When multiple virtual nodes are triggered simultaneously, the command is sent sequentially in a priority-based preemptive manner, so that a single physical link logically carries the behavior of multiple virtual nodes. When the avionics simulation module 12 receives the simulated data types, parameters, and scenarios sent by the human-machine interface 11, it generates high-level control commands for the optoelectronic payload that conform to the protocol. Then, it calls the currently loaded protocol configuration file in the extensible protocol module to map the logical commands into data structures with specific field definitions that meet the requirements of the current tested payload, and then transmits them to the FC communication adapter unit 15.

[0026] In some embodiments, the multi-node timing simulation employs a high-precision timer to configure an independent trigger time offset and transmission jitter range for each virtual avionics node, so that the issuance times of commands from each node are not completely synchronized, in order to closely resemble the real environment.

[0027] In some embodiments, the extensible protocol configuration module 13 includes protocol loading, frame structure extension, communication parameter extension, data mapping, and a protocol configuration library. The protocol loading is used so that when an operator selects the photoelectric load 4 to be measured on the human-machine interface 11, the system automatically loads the corresponding protocol file from the protocol configuration library. The frame structure extension is used to expand support for adding or deleting fields, adjusting bit width and offset, defining structures, and adapting to various custom protocols. The communication parameter extension is used to support the setting of FC address, message ID, heartbeat period, and timeout retransmission mechanism; The data mapping is used to automatically map upper-level simulation commands to protocol fields. The protocol configuration library stores communication protocol parameters for multiple payload models in a structure file, supporting add, edit, and delete operations.

[0028] In some embodiments, the FC communication adapter unit 15 includes: an optical transceiver module and an FPGA data protocol encapsulation. The optical transceiver module is used to convert FC transmitted and received data between optical signals and electrical signals. The FPGA data protocol encapsulation is used to encapsulate data into standard FC-AE-ASM protocol data, buffer the protocol frames, shape the traffic, and drive the FC network controller.

[0029] In some embodiments, the image acquisition module 16 acquires image or video stream data returned by the photoelectric load in real time and uploads it to the human-machine interface 11. The human-machine interface 11 performs correlation analysis on the returned image data and image annotation information with the sent instructions based on a unified timestamp to verify the accuracy of the load action and response delay. When a target position of the returned image data is clicked on the returned image display interface, a tracking instruction is generated based on the target position and sent to the tested photoelectric load 4 to achieve closed-loop control with the photoelectric load control instruction.

[0030] In some embodiments, the message structure of the standard FC-AE-ASM protocol data includes a fixed frame header, a payload data area, and a fixed frame tail. The fixed frame header includes an FC general frame header and an ASM specific frame header. The length of the payload data area is determined according to the actual protocol situation. The fixed frame tail contains CRC checksum information.

[0031] Combination Figure 2 As shown in this embodiment, specifically, the message structure of the FC-AE-ASM protocol data consists of an FC general frame header, an ASM specific frame header, a payload data area, and a CRC checksum, defining the standard frame format and length.

[0032] In some embodiments, the measured photoelectric load 4 conforms to the standard FC communication protocol interface, and is used to receive and parse the FC command frames sent by the system, perform actions such as servo motion and imaging sensor control, and encapsulate the status data into FC response frames and image data and send them back to the system.

[0033] In some embodiments, the FC-AE-ASM protocol can be replaced with the FC-AE-1553 protocol, which can be quickly supported by changing the extensible protocol configuration library and FPGA logic.

[0034] In some embodiments, the FPGA in the FC communication adapter unit 15 can be replaced with a dedicated FC protocol chip to work with an embedded processor to achieve the same protocol encapsulation and forwarding functions.

[0035] This invention provides a ground-based detection and avionics simulation system for optoelectronic payloads based on FC point-to-point connections. With a simulation control host as its core, it replaces the complex switched avionics network with FC point-to-point direct connections. Under conditions where no real avionics equipment or switches are available, it fully simulates the behavior of avionics nodes, communication timing, and command logic required by the optoelectronic payload. It simulates all communication behaviors of a complete complex avionics network to the optoelectronic payload using simplified physical connection logic. The system adapts to different payload FC-AE-ASM protocols through an extensible protocol configuration module. The avionics simulation module simulates nodes such as the mission aircraft, integrated inertial navigation system, navigation data fusion, health management unit, system time management, and display and control unit, generating high-level control commands. These commands are sent to the FC communication adaptation unit via a PCIe driver module, where the FPGA performs FC frame encapsulation, flow shaping, and optoelectronic conversion, establishing full-duplex point-to-point communication with the payload. Simultaneously, the image acquisition module collects image or video data streams in real time, achieving a dual closed loop of control flow and image or video data stream. The system supports test configuration, command transmission, data monitoring, recording and playback, automatic criterion judgment, fault location, and test report generation, forming a complete ground-based detection system for optoelectronic payloads.

[0036] Accordingly, combined Figure 3 As shown, combined with Figure 3 As shown in the diagram, this embodiment of the invention provides a schematic diagram of the overall workflow of a point-to-point electro-optical payload ground detection and avionics simulation method. The diagram shows, in the order of execution, five core steps: system construction and initialization, test simulation and command generation, command injection and payload response, data retrieval and status monitoring, and verification analysis and report generation. It fully presents the entire process from physical connection, protocol configuration, scenario simulation, command issuance, payload execution, data feedback to automatic testing and fault location. This diagram reflects the logical execution path and closed-loop detection mechanism of this method.

[0037] Specifically, this embodiment of the invention also provides a method for ground detection and avionics simulation of electro-optical payloads based on FC point-to-point, applied to the aforementioned FC point-to-point ground detection and avionics simulation system for electro-optical payloads. The method includes: Step S1: System Construction and Initialization S1.1: Physical connection: Using a single standard multimode two-core optical fiber, the optical transceiver module interface of the FC communication adapter unit is directly connected to the FC device interface of the photoelectric load under test to establish a point-to-point physical link. The image acquisition module is connected to the photoelectric load under test using an image cable to receive the real-time output image or video data of the photoelectric load under test. S1.2: Logic initialization, start the simulation control host and human-machine interface, select the model of the payload under test through the drop-down menu of the human-machine interface, and the system automatically loads the corresponding matching avionics system protocol configuration file from the protocol configuration library. The avionics system protocol configuration file includes the type, address identifier, etc. of the FC-AE-ASM protocol and the specific structure of the variable data payload area. After the avionics system protocol configuration file is loaded, the system drives the FC communication adapter unit to complete self-test and establish a port-level connection with the optoelectronic payload under test to complete link synchronization. Step S2: Test Simulation and Instruction Generation S2.1: Scenario Configuration. In the human-machine interface of the simulation control host, a test scenario is selected or edited. The test scenario includes at least the simulated aircraft platform state parameters, the desired optoelectronic payload operating mode, the additional parameters for the desired optoelectronic payload operating mode, and the simulated target parameters. The aircraft platform state parameters include flight altitude, speed, position, and attitude angle. The desired optoelectronic payload operating mode includes wide-area imaging, area imaging, area monitoring, automatic tracking, and manual search. The additional parameters include scanning method, scanning start angle, and scanning end angle. The simulated target parameters include target longitude, latitude, and altitude. S2.2: Logic calculation. The avionics simulation module calculates and generates high-level control commands that conform to avionics specifications in real time based on the scenario script. It simulates the actual flight state parameters of the aircraft based on the selected scenario script. The high-level control commands include at least the optoelectronic payload working mode and sensor control commands. The optoelectronic payload working modes include wide-area imaging, area imaging, area surveillance, and automatic tracking. The sensor control commands include imaging mode, optical lens zoom, infrared cooler switch, and laser ranging. S2.3: Command Generation: Real-time calculated high-level control commands conforming to avionics specifications are sent to the FC communication adapter unit through the PCIe driver module; Step S3: Command Injection and Load Response S3.1: Protocol encapsulation, the FPGA data protocol encapsulation in the FC communication adapter unit encapsulates the received instructions into one or more complete FC frame sequences according to the preset avionics network FC-AE-ASM protocol; the encapsulation process includes adding frame headers, instruction data payloads, and calculating CRC check codes; S3.2: Command transmission: The encapsulated FC frame sequence is buffered and traffic shaped by the FPGA protocol processing engine, and then converted into a serial optical signal conforming to the FC-FS protocol specification by the FC network controller and transmitted. S3.3: Physical transmission, the serial optical signal is transmitted to the FC interface of the photoelectric load under test through the point-to-point physical link; S3.4: Load execution, the FC interface board of the photoelectric load under test receives and parses the FC frame, extracts the valid control command data, drives its own servo mechanism and imaging sensor to perform corresponding actions, and the image data or video data generated by the execution of the photoelectric load under test is transmitted in real time through the image cable according to the system configuration, for subsequent acquisition; Step S4: Data Recycling and Status Monitoring S4.1: Data feedback, the photoelectric load under test encapsulates the execution result into a response FC frame, the response data includes load status information, and the image data or video data of the photoelectric load under test returns real-time image data through the image cable; S4.2: Signal reception and conversion. The optical signal transmitted back by the photoelectric load under test is converted into an electrical signal by the optical module of the FC communication adapter unit. The FPGA data protocol engine parses the FC frame data, extracts the data payload area, and uploads it to the simulation control host through the PCIe bus. The image data or video data is acquired and processed by the image acquisition module and then uploaded to the human-machine interface. S4.3: Real-time processing and display: The simulation control host synchronously parses and decodes the timestamps of the FC-returned data and image data, updates the load status parameters in real time on the human-machine interface, and dynamically displays the image and video streams to form a visual monitoring system.

[0038] Step S5: Validation Analysis and Report Generation S5.1: Data recording and synchronization. The system uses timestamps as a basis to synchronously record all downlink sent command FC frames, uplink received response FC frames, and calculated simulation environment parameters, forming a complete and traceable test log. S5.2: Performance analysis and judgment. The test management module automatically analyzes the load performance based on preset criteria and determines whether the test item passes or fails. S5.3: Report generation and fault indication, automatically generating structured test reports; if a communication CRC error, response timeout, or performance deviation is detected, the system will issue an alarm on the human-machine interface and locate the fault to one of the three components—the simulation control host, the multimode two-core optical fiber, or the photoelectric load under test—based on a simplified point-to-point physical link topology.

[0039] As an optional approach, the preset criteria include the error tolerance of angle command and feedback, image quality index, and communication delay threshold.

[0040] Referring to Table 1, for ease of understanding, a comparison between the FC point-to-point photoelectric load ground detection and avionics simulation method in this embodiment of the invention and the prior art is provided.

[0041]

[0042] Table 1 The ground detection and avionics simulation method for FC point-to-point photoelectric loads provided in this embodiment of the invention has the following beneficial effects. 1. Independent debugging of optoelectronic payloads without relying on real avionics systems: The point-to-point FC direct connection replaces complex networking, allowing for independent debugging of optoelectronic payloads in the early stages of production and assembly.

[0043] 2. Low cost and flexible deployment: No need to network with multiple devices, simple hardware, quick setup in the laboratory, suitable for small-batch production.

[0044] 3. High testing efficiency: It can independently complete full-function testing of optoelectronic payloads, and multiple sets of this system can be deployed to test multiple optoelectronic payloads in parallel, thereby increasing production capacity.

[0045] 4. Intuitive fault location and quick troubleshooting: The point-to-point topology eliminates intermediate links, allowing for rapid identification of faults as local to the system, fiber optic link, or the tested optoelectronic load, thus shortening troubleshooting time.

[0046] 5. Configurable protocol, flexible adaptation to multiple models: It can be adapted to different optoelectronic payloads through scalable protocol configuration without changing the hardware, resulting in high equipment reuse rate and low iteration cost.

[0047] This invention addresses the often-overlooked scenario of early independent production and commissioning of FC-based optoelectronic payloads. It proposes a ground-based detection and avionics simulation method for FC-based point-to-point optoelectronic payloads. This method is a complete solution from problem and structure to implementation. Through its core design—a switchless point-to-point approach, scalable protocol, dual command + image closed loop, and rapid fault location with a simplified topology—it provides crucial support for efficient and low-cost production and commissioning of optoelectronic payloads, both in engineering and economic terms. The method has been validated through practical use and applied in the production, commissioning, and testing phases of multiple project models. The results demonstrate its feasibility and effectiveness, meeting the ground-based detection requirements of optoelectronic payloads.

[0048] The specific embodiments described above do not constitute a limitation on the scope of protection of this invention. Those skilled in the art should understand that various modifications, combinations, sub-combinations, and substitutions can be made according to design requirements and other factors. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this invention should be included within the scope of protection of this invention.

Claims

1. A ground-based photoelectric load detection and avionics simulation system based on FC point-to-point, characterized in that, Includes a simulation control host, multimode two-core optical fiber, image cable, and the photoelectric load under test; One end of the multimode two-core optical fiber is connected to the simulation control host, and the other end is connected to the photoelectric load under test. One core of the multimode two-core optical fiber is used to send the encapsulated FC command data, and the other core is used to receive the real-time FC data returned by the photoelectric load under test. The simulation control host includes a human-machine interface, an avionics simulation module, an extensible protocol configuration module, a PCIe driver module, an FC communication adapter unit, and an image acquisition module. The FC communication adapter unit is installed on the motherboard of the simulation control host through the PCIe driver module. The image acquisition module is connected to the photoelectric load under test through the image cable. The extensible protocol configuration module includes protocol loading, frame structure extension, communication parameter extension, data mapping, and a protocol configuration library. The avionics simulation module includes FC link state machine simulation, multi-node timing simulation, and avionics unit simulation. The avionics unit simulation includes a mission unit, integrated inertial navigation system, navigation fusion, health management, system time management, and display and control unit. The FC link state machine simulation is used to realize the initialization, heartbeat maintenance, and reconnection status of the FC link, so that the tested optoelectronic payload perceives link behavior consistent with the real avionics system. The multi-node timing simulation is used to configure the FC address, message ID, transmission period, and priority of each virtual node. When the transmission time of a virtual node arrives, the control command of that node is triggered. When multiple virtual nodes are triggered simultaneously, the command is sent sequentially in a priority-based preemptive manner, so that a single physical link logically carries the behavior of multiple virtual nodes. When the avionics simulation module receives the simulated data type, parameters, and scenario sent by the human-machine interface, it generates high-level control commands for the optoelectronic payload that conform to the protocol. Then, it calls the currently loaded protocol configuration file in the extensible protocol module to map the logical commands into a data structure with specific field definitions that meets the requirements of the current tested payload, and then transmits it to the FC communication adaptation unit.

2. The FC-based point-to-point photoelectric load ground detection and avionics simulation system according to claim 1, characterized in that, The multi-node timing simulation uses a high-precision timer to configure an independent trigger time offset and transmission jitter range for each virtual avionics node, so that the issuance times of commands from each node are not completely synchronized, in order to closely resemble the real environment.

3. The FC-based point-to-point photoelectric load ground detection and avionics simulation system according to claim 1, characterized in that, The extensible protocol configuration module includes protocol loading, frame structure extension, communication parameter extension, data mapping, and protocol configuration library. The protocol loading is used so that when the operator selects the photoelectric load to be measured on the human-machine interface, the system automatically loads the corresponding protocol file from the protocol configuration library. The frame structure extension is used to expand support for adding or deleting fields, adjusting bit width and offset, defining structures, and adapting to various custom protocols. The communication parameter extension is used to support the setting of FC address, message ID, heartbeat period, and timeout retransmission mechanism; The data mapping is used to automatically map upper-level simulation commands to protocol fields. The protocol configuration library stores communication protocol parameters for multiple payload models in a structure file, supporting add, edit, and delete operations.

4. The FC-based point-to-point photoelectric load ground detection and avionics simulation system according to claim 1, characterized in that, The FC communication adapter unit includes: an optical transceiver module and an FPGA data protocol encapsulation. The optical transceiver module is used to convert optical signals and electrical signals to each other for FC transmitted and received data. The FPGA data protocol encapsulation is used to encapsulate data into standard FC-AE-ASM protocol data, buffer the protocol frames, shape the traffic, and drive the FC network controller.

5. The FC-based point-to-point photoelectric load ground detection and avionics simulation system according to claim 1, characterized in that, The image acquisition module collects image or video stream data returned by the photoelectric load in real time and uploads it to the human-machine interface. The human-machine interface performs correlation analysis on the returned image data and image annotation information with the sent instructions based on a unified timestamp to verify the accuracy of the load action and response delay. When a target position of the returned image data is clicked on the returned image display interface, a tracking instruction is generated based on the target position and sent to the photoelectric load under test, realizing closed-loop control with the photoelectric load control instruction.

6. The FC-based point-to-point photoelectric load ground detection and avionics simulation system according to claim 4, characterized in that, The message structure of the standard FC-AE-ASM protocol data includes a fixed frame header, a payload data area, and a fixed frame tail. The fixed frame header includes a general FC frame header and a specific ASM frame header. The length of the payload data area is determined according to the actual protocol situation. The fixed frame tail contains CRC checksum information.

7. The FC-based point-to-point photoelectric load ground detection and avionics simulation system according to claim 1, characterized in that, The measured photoelectric load conforms to the standard FC communication protocol interface, which is used to receive and parse the FC command frames sent by this system, execute servo motion and imaging sensor control actions, and encapsulate the status data into FC response frames and image data and send them back to the system.

8. A ground detection and avionics simulation method for FC point-to-point optoelectronic loads, applied to the FC point-to-point optoelectronic load ground detection and avionics simulation system as described in any one of claims 1 to 7, characterized in that, The method includes: Step S1: System Construction and Initialization S1.1: Physical connection: Using a single standard multimode two-core optical fiber, the optical transceiver module interface of the FC communication adapter unit is directly connected to the FC device interface of the photoelectric load under test to establish a point-to-point physical link. The image acquisition module is connected to the photoelectric load under test using an image cable to receive the real-time output image or video data of the photoelectric load under test. S1.2: Logic initialization, start the simulation control host and human-machine interface, select the model of the payload under test through the drop-down menu of the human-machine interface, and the system automatically loads the corresponding matching avionics system protocol configuration file from the protocol configuration library. The avionics system protocol configuration file includes the type, address identifier and specific structure of the variable data payload area of ​​the FC-AE-ASM protocol. After the avionics system protocol configuration file is loaded, the system drives the FC communication adapter unit to complete self-test and establish a port-level connection with the optoelectronic payload under test to complete link synchronization. Step S2: Test Simulation and Instruction Generation S2.1: Scenario Configuration. In the human-machine interface of the simulation control host, a test scenario is selected or edited. The test scenario includes at least the simulated aircraft platform state parameters, the desired optoelectronic payload operating mode, the additional parameters for the desired optoelectronic payload operating mode, and the simulated target parameters. The aircraft platform state parameters include flight altitude, speed, position, and attitude angle. The desired optoelectronic payload operating mode includes wide-area imaging, area imaging, area monitoring, automatic tracking, and manual search. The additional parameters include scanning method, scanning start angle, and scanning end angle. The simulated target parameters include target longitude, latitude, and altitude. S2.2: Logic calculation. The avionics simulation module calculates and generates high-level control commands that conform to avionics specifications in real time based on the scenario script. It simulates the actual flight state parameters of the aircraft based on the selected scenario script. The high-level control commands include at least the optoelectronic payload working mode and sensor control commands. The optoelectronic payload working modes include wide-area imaging, area imaging, area surveillance, and automatic tracking. The sensor control commands include imaging mode, optical lens zoom, infrared cooler switch, and laser ranging. S2.3: Command Generation: Real-time calculated high-level control commands conforming to avionics specifications are sent to the FC communication adapter unit through the PCIe driver module; Step S3: Command Injection and Load Response S3.1: Protocol encapsulation, the FPGA data protocol encapsulation in the FC communication adapter unit encapsulates the received instructions into one or more complete FC frame sequences according to the preset avionics network FC-AE-ASM protocol; the encapsulation process includes adding frame headers, instruction data payloads, and calculating CRC check codes; S3.2: Command transmission: The encapsulated FC frame sequence is buffered and traffic shaped by the FPGA protocol processing engine, and then converted into a serial optical signal conforming to the FC-FS protocol specification by the FC network controller and transmitted. S3.3: Physical transmission, the serial optical signal is transmitted to the FC interface of the photoelectric load under test through the point-to-point physical link; S3.4: Load execution, the FC interface board of the photoelectric load under test receives and parses the FC frame, extracts the valid control command data, drives its own servo mechanism and imaging sensor to perform corresponding actions, and the image data or video data generated by the execution of the photoelectric load under test is transmitted in real time through the image cable according to the system configuration, for subsequent acquisition; Step S4: Data Recycling and Status Monitoring S4.1: Data feedback, the photoelectric load under test encapsulates the execution result into a response FC frame, the response data includes load status information, and the image data or video data of the photoelectric load under test returns real-time image data through the image cable; S4.2: Signal reception and conversion. The optical signal transmitted back by the photoelectric load under test is converted into an electrical signal by the optical module of the FC communication adapter unit. The FPGA data protocol engine parses the FC frame data, extracts the data payload area, and uploads it to the simulation control host through the PCIe bus. The image data or video data is acquired and processed by the image acquisition module and then uploaded to the human-machine interface. S4.3: Real-time processing and display: The simulation control host synchronously parses and decodes the timestamps of the FC-returned data and image data, updates the load status parameters in real time on the human-machine interface, and dynamically displays the image and video streams to form a visual monitoring system. Step S5: Validation Analysis and Report Generation S5.1: Data recording and synchronization. The system uses timestamps as a basis to synchronously record all downlink sent command FC frames, uplink received response FC frames, and calculated simulation environment parameters, forming a complete and traceable test log. S5.2: Performance analysis and judgment. The test management module automatically analyzes the load performance based on preset criteria and determines whether the test item passes or fails. S5.3: Report generation and fault indication, automatically generating structured test reports; if a communication CRC error, response timeout, or performance deviation is detected, the system will issue an alarm on the human-machine interface and locate the fault to one of the three components—the simulation control host, the multimode two-core optical fiber, or the photoelectric load under test—based on a simplified point-to-point physical link topology.

9. The method for ground detection and avionics simulation of photoelectric load based on FC point-to-point as described in claim 8, characterized in that, The preset criteria include the error tolerance of angle command and feedback, image quality index, and communication delay threshold.

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