A distributed test system for an electric propulsion system of an aircraft

Abstract

The embodiment of the specification discloses an airplane electric propulsion system distributed test system, the system comprises a laboratory bench and a thrust bench; wherein the laboratory bench comprises a fuselage simulation part and a wing simulation part, the wing simulation part has a space for installing the thrust bench; the laboratory bench further comprises a device cabin for installing a measured airborne device, a test power supply system, a simulation and data acquisition module; the thrust bench comprises a wing surface simulation part, a thrust bench body, a movable tooling and a data acquisition and communication control system; the bench body comprises a force bearing frame, height adjusting devices are arranged on both sides of the force bearing frame; the movable tooling is used for installing a measured electric propulsion system.

Description

Technical Field

[0001] This application relates to the field of aircraft testing technology, and in particular to a distributed testing system for an aircraft electric propulsion system. Background Technology

[0002] With the promotion of the green aircraft concept, various forms of electric aircraft replacing traditional fuel-powered aircraft have begun to emerge. As a crucial system in electric aircraft, the electric propulsion system plays a vital role in their development, but it also presents new challenges. For electric aircraft, a key technical challenge is how to realistically verify the functional design of the electric propulsion system on the ground, adapting to real-time changes in the aircraft's flight conditions, and ensuring that the test conditions are as similar as possible to the airborne environment.

[0003] Furthermore, since electric propulsion systems utilize electric power and are powered by ducted fans and other propulsion devices, addressing safety and electromagnetic interference issues during ground integration testing presents a significant technical challenge. Existing experimental verification platforms for electric propulsion systems mostly test only a single type, a single motor, or a single propulsion method, making it difficult to fully verify the overall performance of the propulsion system in a multi-system integrated environment.

[0004] Due to the characteristics of strong wind fields, strong electric fields, and strong magnetic fields in thrust tests, thrust systems and their test rigs are rarely deeply integrated with laboratory test platforms and other system components and equipment. This results in the need to build separate flight scenarios, real-time simulations, external excitations, data acquisition, visual simulations, and airframe structures for the electric propulsion system under test and its test system, increasing construction costs.

[0005] Patent document CN119551214A discloses an integrated test bench for aircraft systems, which interconnects communication signals based on the existing construction of power system test benches, electric bird test benches, copper bird test benches, and iron bird test benches. Although it demonstrates the full integration of some test data and bus interfaces of different aircraft systems, the integration level of the interconnected test benches is low, and it cannot provide the test benches with the conditions for conducting joint tests under unified integrated real airborne cables, real power supply cables, real EWIS environment, real airborne power supply environment, and real mechanical motion environment.

[0006] In particular, the aforementioned literature describes the testing methods and systems for traditional fuel-powered aircraft, and the power system only has the controller in hardware-in-the-loop form of a mini-rig test bench, without involving actual power plant testing.

[0007] Patent document CN118220528A discloses a durability testing method and system for an aircraft electric propulsion system. Based on the operational characteristics of the electric aircraft it serves, it establishes a load spectrum for electric propulsion system testing and outlines the methods and required systems for testing electric propulsion systems at various flight stages. However, this document focuses on system-level testing of electric propulsion systems, conducting tests only on a single type of motor propulsion. It cannot provide testing conditions for electric propulsion systems in a fully integrated aircraft scenario, nor can it verify the functionality and response of the electric propulsion system, especially the power unit, under ambient conditions in other tested aircraft systems. Summary of the Invention

[0008] This specification provides a distributed test system for an aircraft electric propulsion system, which addresses the technical problem of how to conduct distributed experiments on an aircraft electric propulsion system and improve the test results.

[0009] To address the aforementioned technical problems, the embodiments in this specification provide the following technical solutions: This specification provides an embodiment of a distributed test system for an aircraft electric propulsion system, the system including a laboratory test bench and a thrust test bench; The laboratory test bench includes a fuselage simulation section and a wing simulation section, wherein the wing simulation section has space for mounting the thrust test bench; The laboratory test bench also includes an equipment bay for installing the airborne equipment under test, a test power system, and a simulation and data acquisition module. The thrust test bench includes a wing surface simulation unit, a thrust test bench body, movable tooling, and a data acquisition and communication control system. The platform includes a load-bearing frame, and height adjustment devices are provided on both sides of the load-bearing frame; The movable fixture is used to install the electric propulsion system under test.

[0010] Preferably, the laboratory bench also includes cable trays for mounting test cables and / or actual test cables.

[0011] Preferably, the wing surface simulation section includes one or more of the following structures: upper and lower wing surface airfoil skin structure, communication / energy cable and trough structure, test maintenance structure, and test operation lighting structure.

[0012] Preferably, the thrust platform further includes a fixing device and / or a moving device and / or a positioning device for positioning with the laboratory platform.

[0013] Preferably, the movable fixture includes a fixed fixture connected to the electric propulsion system under test, and a fixed groove and force sensor connected to the thrust test platform.

[0014] Preferably, the wing simulation unit is also equipped with a separation surface cable management box, which provides convenient interface switching for close-range / long-range integration of laboratory test bench and thrust test bench, as well as distributed communication management during long-distance testing.

[0015] Preferably, the separation surface cable management box provides an electric propulsion device power supply cable interface, an electric propulsion system controller communication interface, a sensor and data acquisition system communication interface, a signal photoelectric conversion device, and a 5G signal receiving and conversion device.

[0016] Preferably, the data acquisition and communication control system includes a force sensor, sensor data cable, control cable of the electric propulsion system under test, power supply cable of the electric propulsion system under test, and cable junction box of the separation surface.

[0017] Preferably, the split-face cable junction box provides an energy interface and switching function, a communication interface and switching function, and a communication management function.

[0018] Preferably, the separation surface cable junction box includes an FPGA integrating a heterogeneous multi-core system-on-a-chip. The processor integrated on the FPGA performs packing and unpacking of data packets for the electric propulsion system, data status detection of the data link, and intelligent scheduling switching according to a pre-programmed scheduling program.

[0019] The above-described at least one technical solution adopted in the embodiments of this specification can achieve the following beneficial effects: The above technical solution can be used for equipment integration and distributed system integration testing of aircraft with electric propulsion systems. It enables remote integration of the electric propulsion system with other airborne equipment during thrust testing, preventing adverse effects from electromagnetic interference, high-speed airflow, noise, and thermal effects on other airborne equipment, test devices, and personnel during electric propulsion system operation. Simultaneously, it allows for integrated testing of the electric propulsion system with other tested equipment in an onboard configuration, enabling tests such as cable signal continuity and in-situ installation accessibility. Under both remote and in-situ integration modes, it provides comprehensive testing and verification functions, including thrust testing, cable continuity testing, signal command logic testing, and electromagnetic interference testing of the aircraft electric propulsion system. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of this specification or the prior art, the drawings used in the description of the embodiments of this specification or the prior art will be briefly described below. Obviously, the drawings used in some embodiments of this application are only described below. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1This is a schematic diagram of the architecture of the distributed test system for the aircraft electric propulsion system provided in the embodiments of this specification.

[0022] Figure 2 yes Figure 1 A bird's-eye view Figure 2 Showing Figure 1 A part of the structure.

[0023] Figure 3 This is a schematic diagram of the thrust platform in the lowered state in the embodiments of this specification.

[0024] Figure 4 yes Figure 3 The left-hand viewpoint.

[0025] Figure 5 This is a schematic diagram of the thrust platform foot cup and casters in the embodiments of this specification.

[0026] Figure 6 This is a schematic diagram of the principle of a split-surface cable junction box. Detailed Implementation

[0027] To enable those skilled in the art to better understand the technical solutions in this specification, the technical solutions in the embodiments of this specification will be clearly and completely described below with reference to the accompanying drawings. Obviously, the embodiments involved in the specific implementation are only a part of the embodiments of this application, and not all of the embodiments. All other embodiments obtained by those skilled in the art based on the embodiments in the specific implementation without creative effort should fall within the protection scope of this application.

[0028] This specification provides an embodiment of a distributed test system for an aircraft electric propulsion system, the system including a laboratory test bench and a thrust test bench; The laboratory test bench includes a fuselage simulation section and a wing simulation section, wherein the wing simulation section has space for mounting the thrust test bench; The laboratory test bench also includes an equipment bay for installing the airborne equipment under test, a test power system, and a simulation and data acquisition module. The thrust test bench includes a wing surface simulation unit, a thrust test bench body, movable tooling, and a data acquisition and communication control system. The platform includes a load-bearing frame, and height adjustment devices are provided on both sides of the load-bearing frame; The movable fixture is used to install the electric propulsion system under test.

[0029] The following is combined Figure 1 and Figure 2 The distributed test system for aircraft electric propulsion is further illustrated through examples: In this example, the distributed test system for the aircraft electric propulsion system includes a laboratory rig (hereinafter referred to as the "laboratory rig") of the same size as the background aircraft and arranged indoors, and an independent thrust rig for the electric propulsion system (hereinafter referred to as the "thrust rig") that can be moved and arranged indoors or outdoors. There may be one or more thrust rigs, as is the case in this embodiment. The laboratory rig and the thrust rig are described below: Laboratory bench A laboratory test bench is a test system that simulates aircraft structure, integrates airborne system equipment and test simulation equipment, and provides test communication and testing functions. Because mechanical system tests, especially load tests, require a solid foundation and rigidity from the laboratory test bench, it is preferred to fix the laboratory test bench to the foundation of the test environment (or, if necessary, an independent foundation).

[0030] The laboratory test bench includes a platform that simulates the structure of an aircraft, particularly the wing and fuselage structures. The portion of the platform simulating the wing structure is called the wing simulation section, and the portion simulating the fuselage structure is called the fuselage simulation section. The wing simulation section has space for mounting the thrust test bench, and it also includes positioning holes and a separation surface cable management box that are integrated in situ with the laboratory test bench.

[0031] The split-face cable management box provides convenient interface switching for near-distance / long-distance integration of the laboratory test bench and the thrust test bench, as well as distributed communication management during long-distance testing. The interfaces provided by the split-face cable junction box for the laboratory test bench and the thrust test bench include: an electric propulsion device power supply cable interface (aviation connector), an electric propulsion system controller communication interface (bus interface), a sensor and data acquisition system communication interface, a signal photoelectric conversion device, and a 5G signal receiving and conversion device.

[0032] The laboratory test bench also includes cable trays for installing test cables and / or cables of the equipment under test, equipment bays and brackets for installing the airborne equipment under test, test power systems, and test management simulation and data acquisition systems.

[0033] Thrust test bench A thrust test bench is a mobile test system that can be fixed in various ways and has test communication and test functions, and can be used to install the electric propulsion system under test.

[0034] The thrust test bench includes a wing surface simulation structure (i.e., the wing surface simulation part), the thrust test bench body, the movable fixture of the electric propulsion system under test (hereinafter referred to as "movable fixture" or "movable test bench body"), and the data acquisition and communication control system.

[0035] The wing surface simulation section includes one or more of the following structures: upper and lower wing surface airfoil skin structure, communication / power cable and trough structure, test maintenance structure, and test operation lighting structure. In this example, the wing surface simulation section includes upper and lower wing surface airfoil skin structure, communication / power cable and trough structure, test maintenance cover (belonging to the test maintenance structure), and test operation lighting (belonging to the test operation lighting structure).

[0036] As an example, the wing surface simulation section is a hollow structure using composite materials or sheet metal. It provides simulation of the leading edge skin structure, shape, and stiffness of the aircraft wing, creating a consistent flow field environment for the electric propulsion system's intake. The interior of the wing surface simulation section uses metal reinforcing ribs or stiffeners to maintain the wing surface shape and form the cable trays for internal communication / power cables. The upper skin features a test and maintenance access cover, and internal test operation lighting illuminates the locations where cable laying, connection, and inspection are required.

[0037] The thrust platform includes a C-shaped load-bearing frame, with adjustable lifting devices (height adjustment mechanisms) on both sides of the frame. The height of the thrust platform is controlled by a screw-motor, hydraulic strut, or other type of lifting device on both sides of the load-bearing frame, facilitating the alignment of the platform height with the laboratory platform's wing surfaces (reference). Figure 3 Meanwhile, when conducting temporary, remote, or off-site thrust tests, if there are few fixed conditions at the site, the height of the thrust platform can be reduced by lowering the platform itself, thereby reducing the rotational torque generated on the platform during the thrust test. Preferably, when conducting thrust tests with the platform height reduced, it should be ensured that the site is clean and there is no possibility of foreign objects being drawn into the duct of the electric propulsion system.

[0038] The thrust platform also includes fixing devices and / or moving devices (or moving traction devices) and / or positioning devices for positioning with the laboratory platform. Fixing devices include, for example, chemical anchors / ground anchors, steel cables, and foot cups; moving devices include, for example, wheels and traction rings; and positioning devices include, for example, positioning holes and positioning pins.

[0039] The thrust test stand is fixed in place to counteract the thrust generated relative to the ground by the thrust device being tested during the thrust test.

[0040] As an example, the push bench is moved between different locations using wheels and manual traction. The bearings of the push bench wheels should have a damping and speed-limiting effect through elastic speed reduction blocks to prevent excessive speed and potential hazards during transport. Both fixed and swivel casters can be used for the push bench. Swivel casters control direction, providing a small turning radius and torque when changing direction or moving the bench within the laboratory environment. Fixed casters stabilize the forward direction, ensuring the bench does not easily deviate from its intended path when moving in a straight line.

[0041] As an example, refer to Figure 4 The thrust platform's securing mechanism includes chemical anchors, steel cables, caster feet, and counterweights. When temporarily parking the thrust platform, the caster feet are lowered to detach the casters from the ground, ensuring stability and preventing wheel roll. An adjustable caster foot is installed on the side of each caster; when the adjusting nut is turned, the foot extends, lifting the caster off the ground. A level is used to ensure that each foot extends to the same length.

[0042] When conditions permit, the site for thrust testing can be equipped with ground rails or embedded parts with anchor bolt holes. Anchor bolts are used to pass through the anchor bolt holes of the thrust test platform and fix it to the ground rails / embedded parts of the thrust test site to ensure the stability of the thrust test platform during the thrust test.

[0043] When the thrust test bench is being moved, temporarily parked, or in a temporary testing area where anchor bolts are not available, the thrust test bench can be secured by threading steel cables through the anchor bolt holes and traction rings at the bottom. If the thrust is large and the steel cable fixation is insufficient to counteract the thrust generated by the thrust test bench, counterweights or sandbags can be hung at the bottom of the thrust test bench to ensure its stability.

[0044] The moving fixture includes a fixed fixture connected to the electric propulsion system under test, and a fixing slot and force sensor connected to the thrust test platform. The fixed fixture can be an earring-type fixture.

[0045] As an example, refer to Figure 5 The ear-shaped fixing fixture is bolted to the rotating joint of the electric propulsion system under test, ensuring that the electric propulsion system under test and the movable platform are a synchronously moving rigid body. A dovetail or roller-type linear bearing guide rail connects to the lifting platform of the thrust test bench, ensuring that the movable platform and the lifting platform only have relative displacement in the direction of the thrust measurement. The ball bearing guide rail within the dovetail groove reduces the friction between the movable platform and the lifting platform. One or more force sensors between the movable platform and the lifting platform measure the force between them and convert it into the thrust of the electric propulsion system under test.

[0046] The thrust test platform's data acquisition and communication control system includes force sensors, temperature sensors (configurable as needed), sensor data cables, control cables for the tested electric propulsion system, power cables for the tested electric propulsion system, and a separation surface cable junction box. The force sensors are positioned between the movable platform and the lifting platform, using a gapped ball joint to eliminate the influence of forces other than those in the thrust direction. The separation surface cable junction box uses a metal shell to form a Faraday cage, shielding against the significant electromagnetic interference generated by the electric propulsion system. The separation surface cable junction box provides energy interface and switching functions, communication interface and switching functions, and communication management functions.

[0047] Specifically, the function of the split-surface cable junction box is to accommodate both in-situ integration and remote integration configurations of the thrust test bench and the laboratory test bench. When the thrust test bench and the laboratory test bench are integrated in-situ, the junction boxes of the two benches can be directly connected via short cables (e.g., Figure 6 (As shown by the solid line). When the thrust test bench and the laboratory test bench are remotely integrated (for thrust testing), the thrust test bench can be powered by a power source near the thrust testing site. The control signals of the thrust test bench and the laboratory test bench (laboratory test bench flight control computer control commands / thrust commands from the simulation test environment / status information returned by the motor controller / sensor measurement information) are primarily integrated via low-latency, interference-resistant cables (such as fiber optics), or via a 5G private network or other local wireless network backup method, forming a low-latency, high-reliability remote integration method (e.g., Figure 6 (As shown by the dashed line).

[0048] In the remote testing configuration (i.e., remote integration configuration), using fiber optics and optical reflection memory networks instead of direct cables can avoid signal attenuation caused by excessive distance when the thrust test bench and laboratory test bench are remotely integrated. At the same time, it can avoid signal interference from long cables caused by the huge electromagnetic interference generated by the operation of the electric propulsion system.

[0049] In the remote testing configuration, using the laboratory LAN / 5G private network signal as a hot backup can prevent signal interruption during the test due to repeated use of optical fiber and breakage. This ensures that test control commands can be continuously executed and avoids loss of control or damage to the electric propulsion system due to sudden interruption.

[0050] The hardware device (signal source switching tester) used to implement communication management functions in the split-plane cable junction box may include an FPGA integrating a heterogeneous multi-core system-on-a-chip (SoC). The processor integrated on the FPGA (such as an ARM processor) performs packing and unpacking of data packets (e.g., control commands, status detection data packets) for the electric propulsion system, and performs data status detection and intelligent scheduling switching between two heterogeneous data links (i.e., in-situ integrated configuration and remote integrated configuration) according to a pre-programmed scheduler.

[0051] As an example, the signal source switching tester transmits and receives optical signals from fiber optic connectors via the RGMII / SGMII / SerDes interface module integrated on the FPGA, which connects to the high-speed I / O interface inside the FPGA. It also transmits and receives wireless signals from Wi-Fi modules or 5G CPE devices via the PCIe interface integrated on the FPGA. The received data is stored and updated via DDR4 RAM or other flash memory firmware integrated on the FPGA, and can be downloaded to the test site.

[0052] The intelligent scheduling logic of the signal source switching tester periodically sends hardware-level probe frames (e.g., UDP packets of a specific format) to the other end of both the fiber optic and wireless links (aircraft-grade test bench or laboratory remote control). It also timestamps the data packets output by the signal source switching tester by adding send / receive timestamps. Delay and jitter are calculated via hardware. Simultaneously, signal strength data is directly read from the driver registers of the Wi-Fi module or 5G signal receiving module.

[0053] Under normal circumstances, data packets for remote communication are sent via the fiber optic channel by default due to its superior channel quality. If a complete fiber optic interruption (continuous packet loss) is detected, the state machine will automatically switch all traffic to the wireless channel within milliseconds, without intervention. If the fiber optic probe frame indicates that fiber optic communication has resumed, but the wireless signal strength shows a deterioration trend, all subsequent data packets destined for the fiber optic path will be redirected to the fiber optic channel after the data transition is complete. During the transition phase, the data processing program running on the SoC controls the data through interpolation or smoothing filtering of the two-channel data. If the fiber optic signal is interrupted and the wireless signal deterioration falls below a set threshold, an alarm will be continuously sent to the other end (aircraft-grade test bench or laboratory remote control). If there is no response to the alarm, an emergency stop command will be sent to the controller of the electric propulsion system under test.

[0054] The workflow of the aforementioned distributed test system for aircraft electric propulsion systems is as follows: The device under test (DUT) is mounted on the upper surface of the C-shaped load-bearing frame of the thrust test bench. The overlapping section of the laboratory test bench and the thrust test bench has a convex shape, and the DUT consists of the flight control system control surfaces / actuators / actuators and cables mounted on the trailing edge of the wing. The laboratory test bench and the thrust test bench are integrated in situ, fitted together, and positioned and secured using locating pins. This modular design allows the DUT and cables to be installed as close as possible to the structural configuration, providing a more realistic signal testing environment.

[0055] When the thrust test bench and the laboratory test bench are integrated, the wing surface simulation structures of the two test benches, especially the leading edge shape, are kept consistent, forming a smooth and continuous integrated structure. This facilitates integrated positioning inspection, in-situ installation of cables inside the wing box, and also serves as a demonstration effect.

[0056] The embodiments described in this specification can achieve the following beneficial effects: This specification's embodiments, through the reconfiguration and design of an electric propulsion thrust test bench and a laboratory test bench, enable the test bench and method to accommodate both integrated thrust testing and signal integration testing of electric propulsion systems. This verifies the physical interface and equipment installation accessibility of the electric propulsion system in an airborne integrated environment with components in the loop, verifies the design consistency of signal connectivity and system cross-linking logic, and verifies the performance of the critical safety system's EWIS / ERN. Simultaneously, it reduces the cost associated with excessively high strength and dynamic stiffness requirements for the laboratory test bench due to the need to suppress propulsion motor vibration, and minimizes the duplication of construction of experimental simulation equipment and support equipment.

[0057] This specification's embodiments focus on the integrated verification of the electric propulsion system, a critical system for electric aircraft. It utilizes a single test system to address the full-aircraft laboratory testing and verification needs of multiple systems. Compared to separate thrust bench tests, it provides a more realistic flight simulation environment and a more complete hardware-in-the-loop verification scenario for the electric propulsion system. Furthermore, it exposes potential interface issues, cross-linking responses, and logic problems in the system's interconnections during on-board and ground testing, reducing the time and technical risks associated with model integration and development. Moreover, by controlling the verification environment of all important airborne components within a unified simulation stimulus environment, it effectively controls the development cycle and cost of the model.

[0058] The embodiments in this specification adopt a separable electric propulsion system thrust test stand design, separation surface design, and multi-test configuration design, which solves the technical problems of the electric propulsion system being difficult to integrate with other airborne systems due to wind field and safety protection requirements generated during testing.

[0059] The embodiments in this specification employ a low-latency, high-reliability dual-channel dissimilar remote test system and intelligent scheduling method to solve technical problems such as electromagnetic interference and test transmission reliability when integrating the thrust test bench and laboratory test bench of an electric propulsion system. The FPGA-based implementation provides a high-reliability, low-latency test communication architecture.

[0060] The embodiments in this manual employ various methods of fixing or mitigating the force on the test bench, such as ground rail-ground anchor, steel cable, foot cup, and lifting support, to adapt to different thrust test scenarios of electric propulsion systems.

[0061] The above description is merely an embodiment of this specification and is not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principle of this application should be included within the scope of the claims of this application.

Claims

1. A distributed test system for an aircraft electric propulsion system, characterized in that, The system includes a laboratory bench and a thrust bench; The laboratory test bench includes a fuselage simulation section and a wing simulation section, wherein the wing simulation section has space for mounting the thrust test bench; The laboratory test bench also includes an equipment bay for installing the airborne equipment under test, a test power system, and a simulation and data acquisition module. The thrust test bench includes a wing surface simulation unit, a thrust test bench body, movable tooling, and a data acquisition and communication control system. The platform includes a load-bearing frame, and height adjustment devices are provided on both sides of the load-bearing frame; The movable fixture is used to install the electric propulsion system under test.

2. The system as described in claim 1, characterized in that, The laboratory bench also includes cable trays for mounting test cables and / or actual test cables.

3. The system as described in claim 1, characterized in that, The wing surface simulation section includes one or more of the following structures: upper and lower wing surface airfoil skin structure, communication / energy cable and trunking structure, test maintenance structure, and test operation lighting structure.

4. The system as described in claim 1, characterized in that, The thrust platform also includes a fixing device and / or a moving device and / or a positioning device for positioning with the laboratory platform.

5. The system as described in claim 1, characterized in that, The movable fixture includes a fixed fixture connected to the electric propulsion system under test, as well as a fixed groove and a force sensor connected to the thrust test platform.

6. The system as described in claim 1, characterized in that, The wing simulation unit is also equipped with a separation surface cable management box, which provides convenient interface switching for close-range / long-range integration of laboratory test bench and thrust test bench, as well as distributed communication management during long-distance testing.

7. The system as described in claim 6, characterized in that, The separation surface cable management box provides an interface for the power supply cable of the electric propulsion device, a communication interface for the electric propulsion system controller, a communication interface for the sensor and data acquisition system, a signal photoelectric conversion device, and a 5G signal receiving and conversion device.

8. The system as described in claim 1, characterized in that, The data acquisition and communication control system includes a force sensor, sensor data cable, control cable of the electric propulsion system under test, power supply cable of the electric propulsion system under test, and cable junction box of the separation surface.

9. The system as described in claim 8, characterized in that, The split-face cable junction box provides energy interface and switching function, communication interface and switching function, and communication management function.

10. The system as described in claim 9, characterized in that, The separation surface cable junction box includes an FPGA integrating a heterogeneous multi-core system-on-a-chip. The processor integrated on the FPGA performs packing and unpacking of data packets for the electric propulsion system, data status detection of the data link, and intelligent scheduling switching according to a pre-programmed scheduling program.

Images