Integrated electronic system based on unification of internal and external ethernet buses

Abstract

The application provides a comprehensive electronic system based on Ethernet internal and external bus unification, comprising: an internal exchange module and an external exchange module; the internal exchange module is connected with a plurality of functional modules inside the comprehensive electronic system respectively, and constitutes a star topology internal bus network, which is used for information interaction and internal clock synchronization between the modules inside the comprehensive electronic system; the external exchange module is connected with the internal exchange module, and is used for information interaction and external clock synchronization between the comprehensive electronic system and external single machines; the internal bus and the external bus both adopt time-triggered Ethernet as a unified bus protocol. The comprehensive electronic system provided by the application has a gigabit bus bandwidth, internal and external bus unification, simple architecture, and high expandability of the equipment.

Description

Technical Field

[0001] This invention belongs to the technical field of launch vehicle electrical systems, specifically relating to an integrated electronic system based on a unified Ethernet internal and external bus. Background Technology

[0002] With the development of computer technology, microelectronics technology, automatic control technology, and software technology, electronic technology has undergone significant changes. In the electrical systems of launch vehicles, the traditional discrete design approach results in excessive hardware redundancy, a large number of devices, numerous bus types, and difficulties in standardizing interfaces. When some individual hardware components need modification or interface relationships change, redesign is required. Furthermore, modules are tightly integrated with the platform, leading to poor individual-unit scalability. Additionally, misalignment between the sending period and the receiving window of individual components within the system can cause frame loss during message transmission and reception.

[0003] Electrical systems are evolving towards integrated electronic systems. Currently, the aerospace field, both domestically and internationally, is adopting integrated electronic design concepts to improve performance, simplify system architecture, and accelerate development progress.

[0004] The design of the launch vehicle's electrical system adopts an integrated electronic design concept. Under the premise of ensuring reliability, and in accordance with the principle of optimal system configuration, all requirements and functions of the electrical system are integrated. System integration, functional integration, and component integration technologies are employed to integrate and synthesize disparate electronic equipment, effectively and fully utilizing information from various subsystems and devices. This improves the reusability of hardware, software, and especially computer management resources, thereby achieving the goal of system miniaturization and optimal platform design.

[0005] Time-triggered Ethernet (TTE) is a data bus technology based on Ethernet, offering high bandwidth and strong scalability. By adding a time-triggered protocol to Ethernet, TTE bus technology ensures reliable and real-time data transmission, leading to its rapid development in the aerospace field.

[0006] Patent document CN121247104A discloses an integrated satellite electronic system. However, this solution fails to address the issues of inconsistent internal and external bus protocols, low bandwidth (i.e., the data transmission bottleneck caused by the CAN bus being only 1Mbps), and the frame loss problem caused by the asynchronous clocks inside and outside the system due to the "time-rushing slot" in message transmission and reception.

[0007] This problem urgently needs to be solved. Summary of the Invention

[0008] In view of the shortcomings of the prior art, the purpose of this invention is to provide an integrated electronic system based on the unified Ethernet internal and external bus.

[0009] According to the present invention, a unified integrated electronic system based on Ethernet internal and external buses includes: an internal switching module and an external switching module; the internal switching module is connected to multiple functional modules within the integrated electronic system to form a star-topology internal bus network for information interaction and internal clock synchronization between modules within the integrated electronic system. The external switching module is connected to the internal switching module and is used for information exchange and external clock synchronization between the integrated electronic system and external single units; Both the internal bus and the external bus use Time-Triggered Ethernet as a unified bus protocol.

[0010] Preferably, the internal switching module participates in the clock synchronization within the integrated electronic system, and the external switching module participates in the clock synchronization between the integrated electronic system and external single units. The internal switching module and the external switching module work together to align the clock inside the integrated electronic system with the clock of the external single unit on the time axis.

[0011] Preferably, the time-triggered Ethernet is compatible with ordinary network data streams, AFDX data streams, and TTE network data streams on the same network platform; in the integrated electronic system, master control and measurement messages use TT messages or RC messages, and video messages use best-effort Ethernet messages.

[0012] Preferably, the multiple functional modules include a high-speed processing module, a main control module, and a power supply module; the integrated electronic system uses a standardized backplane for internal bus message interaction, and the high-speed processing module, the main control module, and the power supply module use a universal interface that can receive information from the rocket-borne inertial navigation system, ground telemetry and control, analog and digital quantities of the entire rocket measurement system, and ground power supply.

[0013] Preferably, the power module provides power to the integrated electronic system; The high-speed processing module performs fault diagnosis according to a predetermined frame format. The fault diagnosis includes determining whether three or more of the following parameters exceed the preset range: the pressure after the oxygen pump, the pressure before the thrust chamber methane injection, the pressure before the thrust chamber oxygen injection, and the pressure before the generator methane injection. If the result is yes, an engine abnormality is detected, and an emergency shutdown signal is issued; if the result is no, no action is taken.

[0014] Preferably, the integrated electronic system further includes a navigation module, which outputs the current position information of the launch vehicle in real time.

[0015] Preferably, the integrated electronic system further includes a main control function module, which receives messages from external RS422 and CAN digital interfaces and has external interfaces, enabling online data binding and modification of network configuration files during ground debugging.

[0016] Preferably, the integrated electronic system further includes a high-speed processing module, which collects analog and digital signals from sensors, non-electrical contact messages from thermistor sensors and other systems, stores and diagnoses faults according to a predetermined frame format, and decides whether to issue an emergency shutdown signal based on the judgment criteria. The high-speed processing module receives rapid and gradual change messages from the entire rocket, performs real-time monitoring, and provides a high-frequency signal interface to realize the transmission of rocket-to-ground telemetry signals.

[0017] Preferably, the integrated electronic system further includes a timing drive module and a solenoid valve acquisition module. The timing drive module drives the solenoid valve, and the solenoid valve acquisition module acquires the real-time status of the solenoid valve during operation and feeds it back to the timing drive module via an internal bus.

[0018] Preferably, the CPU or FPGA of each module inside the integrated electronic system is programmed with a TTE IP core, which has the ability to participate in clock synchronization; the external bus adopts a dual-channel cascaded star architecture.

[0019] Compared with the prior art, the present invention has the following beneficial effects: 1. This invention adopts standardized modular design, universal bus technology, and scalable design concept, which solves the problems of multiple types of single units on launch vehicles, complex architecture, and difficulty in standardization.

[0020] 2. The integrated electronic system provided by this invention has gigabit bus bandwidth, unified internal and external buses, simple architecture, and high scalability.

[0021] 3. This invention achieves true unification of internal and external bus protocols and bandwidth by using Time Triggered Ethernet (TTE) as a unified bus for the entire system, and utilizes its time triggering mechanism to achieve precise synchronization between internal and external clocks, thereby significantly improving the system's real-time performance, reliability, and scalability. Attached Figure Description

[0022] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a schematic diagram of the system architecture provided for the present invention; wherein, SLOT represents a slot in the integrated electronic chassis; Figure 2 This is a schematic diagram of the information flow provided by the present invention; Figure 3 This is a schematic diagram of the module dimensions provided by the present invention; in the diagram, the unit of measurement is millimeters. Figure 4This is a schematic diagram of the single-board dimensions provided by the present invention; in the figure, the unit of measurement is millimeters. Detailed Implementation

[0023] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0024] The purpose of this invention is to propose an integrated electronic system based on Ethernet with unified internal and external buses, thereby simplifying the overall electrical system architecture, reducing the number of individual units and cable weight, and improving the scalability of the integrated electronic system.

[0025] This invention provides an integrated electronic system based on a unified Ethernet internal and external bus. This integrated electronic system is applied to the next-generation electrical architecture of launch vehicles, integrating functions such as navigation, flight control, high-speed information processing, and time-triggered power distribution. Time-triggered Ethernet (TTE), as a high-real-time and high-reliability bus technology, is used for high-speed and reliable message transmission. It can be used not only for communication between individual units on the rocket but also for communication between modules within the integrated electronic system. The integrated electronic system is the core unit of each level of electronic system on the rocket. It can control battery power supply and distribution; receive inertial navigation information and send commands to control the servo system and attitude control engine; receive measurement messages of analog and digital quantities and solenoid valve status throughout the rocket; and also interact with ground-based measurement and control equipment.

[0026] Specifically, this invention proposes a unified integrated electronic system based on Ethernet internal and external buses, comprising a main control module, a high-speed processing module, an internal and external switching module, a solenoid valve acquisition module, a timing drive module, and a power supply module. The main control module primarily handles control-type messages, while the high-speed processing module primarily receives and processes measurement-type messages. All modules have internal CPUs / FPGAs programmed with TTE IP cores, enabling them to participate in internal clock synchronization. The internal switching module not only participates in internal clock synchronization but also in external clock synchronization of the integrated electronic system, thereby achieving alignment between the internal and external clocks.

[0027] In integrated electronic systems, both control and measurement information are transmitted via an internal bus. The TTE internal bus possesses time-deterministic and reliable data exchange fault tolerance capabilities. Integrated electronic systems exhibit diverse integration forms, with product forms depending on system requirements, and often involve distributed multi-master data transmission. In modularly integrated electronic systems, the internal bus enables rapid assembly and testing. Its large internal bus data communication bandwidth can meet the needs of multi-module integration and expansion upgrades.

[0028] The integrated electronic system includes a main control module, a high-speed processing module, a power supply module, a navigation module, a solenoid valve acquisition module, and a timing drive module, all connected to the integrated electronic backplane via a bus network. The main control module's external interface receives digital signals from the rate gyroscope and pressure sensor, while the high-speed processing module reserves some digital transmission interfaces for ground debugging.

[0029] In other words, according to the present invention, a unified electronic system based on Ethernet internal and external buses is provided. The unified electronic system includes an internal switching module, an external switching module, a power supply module, a navigation module, a main control function module, a high-speed processing module, a solenoid valve acquisition module, and a timing drive module.

[0030] The internal switching module facilitates information exchange between modules within the integrated electronic system and generates internal clock synchronization.

[0031] The external exchange module is used for information exchange between the integrated electronic system and other external stand-alone devices, and for clock synchronization with external devices. The power supply module provides power to the integrated electronic system. The main control module integrates navigation and guidance calculations, attitude control, and data exchange functions.

[0032] High-speed processing module: Collects analog and digital signals from sensors, thermistor sensors, and non-electrical contact messages from other systems, stores them according to a predetermined frame format, and performs fault diagnosis. If three of the following four parameters—oxygen pump pre-pressure, thrust chamber methane pre-injection pressure, thrust chamber oxygen pre-injection pressure, and generator methane pre-injection pressure—are above or below a certain preset threshold, an engine malfunction is detected, and an emergency shutdown signal is issued. Interface conversion module: Used for downloading or uploading network planning configuration files during desktop testing.

[0033] Specifically, a standardized backplane, such as VPX or VNX, is used to exchange internal bus messages. The high-speed processing, main control, and power modules use a universal interface to receive information from the onboard inertial navigation system, ground telemetry and control, analog and digital quantities of the entire rocket measurement system, and ground power supply.

[0034] Specifically, both the internal and external buses adopt Time-Triggered Ethernet (TTE), which combines the advantages of time-triggered protocols and Ethernet technology. It can support ordinary network data streams, AFDX data streams, and TTE network data streams on the same network platform, providing higher security and a robust fault tolerance mechanism. The internal switching module generates the internal clock synchronization of the integrated electronic unit, which can be aligned with the clock synchronization of external units on the time axis. This prevents the "time slot rush" phenomenon in information interaction within the integrated electronic system, ensuring high reliability in message transmission and reception. In the integrated electronic system, master control and measurement messages use time / event-triggered (TT / RC) messages, while video messages use best-effort (BE) Ethernet messages.

[0035] See Figure 1 This is a schematic diagram of an integrated electronic system architecture based on a unified Ethernet internal and external bus according to an embodiment of the present invention. The integrated electronic system includes a solenoid valve acquisition module 1, an internal exchange module 2, a navigation module 3, a high-speed processing module 4, a timing drive module 5, a power supply module 6, a main control function module 7, and an external exchange module 8. The power supply module 6 receives 28V from a battery to power the integrated electronic system, providing +5V and ±15V power supply voltages to each module. The navigation module 3 outputs the current position information of the launch vehicle, which is provided to the main control function module 7 and the high-speed processing module 4 through the internal exchange module 2. The main control function module 7, as the core module for measurement and control of the integrated electronic system, receives messages from the inertial navigation system, the navigation module 3, and the high-speed processing module 4, and also receives external digital interfaces such as RS422 and CAN. This module has external interfaces, mainly used for online data binding and network configuration file modification during ground debugging.

[0036] The high-speed processing module 4 receives rapid and gradual change messages from the entire rocket for fault diagnosis and real-time monitoring, and provides a high-frequency signal interface for rocket-to-ground telemetry signal transmission. The timing drive module 5 drives the solenoid valve and receives real-time status feedback from the solenoid valve acquisition module 1. The solenoid valve acquisition module 1 collects the solenoid valve's operating status and feeds it back to the timing drive module 5 via the internal bus. The internal exchange module 2 is used for internal bus information interaction, coupling time-triggered messages and event-triggered messages for transmission, and distinguishing message priorities through a network scheduling table. The internal information flow of the integrated electronic system, such as... Figure 2 As shown.

[0037] The external exchange module 8 is used for data interaction between the integrated electronic system and external standalone devices such as inertial navigation systems and servo systems. The above is an introduction to the integrated electronic system of this invention.

[0038] refer to Figure 3 This is a schematic diagram of a single module. The module includes external structural components and internal board dimensions, such as... Figure 4 As shown. Because the integrated electronic system adopts a VNX architecture, the external structural dimensions of each module are uniform. Depending on their function, modules are connected to the backplane using 80, 200, and 400-pin connectors. The internal bus of this invention's integrated electronic system uses a star topology to connect each module via the backplane, while the external bus uses a dual-channel cascaded star topology to simulate the operating environment of the first and second stages of a launch vehicle.

[0039] The above describes a preferred embodiment of the present invention. Employing a unified integrated electronic system with internal and external buses in a launch vehicle can effectively reduce the number of individual units on board and improve their scalability. The proposed method does not conflict with existing integrated electronic systems and internal / external bus technologies; rather, it is a valuable supplement and optimization, laying a research foundation for the future development of intelligent launch vehicles.

[0040] Those skilled in the art will understand that, besides implementing the system and its various devices, modules, and units provided by this invention in the form of purely computer-readable program code, the same functions can be achieved entirely through logical programming of the method steps, making the system and its various devices, modules, and units of this invention function in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers. Therefore, the system and its various devices, modules, and units provided by this invention can be considered as a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; alternatively, the devices, modules, and units for implementing various functions can be considered as both software modules implementing the method and structures within the hardware component.

[0041] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A unified electronic system based on Ethernet internal and external buses, characterized in that, include: Internal switching module and external switching module; The internal switching module is connected to multiple functional modules within the integrated electronic system, forming a star-topology internal bus network for information exchange and internal clock synchronization between modules within the integrated electronic system. The external switching module is connected to the internal switching module and is used for information exchange and external clock synchronization between the integrated electronic system and external single units; Both the internal bus and the external bus use Time-Triggered Ethernet as a unified bus protocol.

2. The integrated electronic system based on a unified Ethernet internal and external bus as described in claim 1, characterized in that, The internal switching module participates in the clock synchronization within the integrated electronic system, and the external switching module participates in the clock synchronization between the integrated electronic system and external single units. The internal switching module and the external switching module work together to align the clock inside the integrated electronic system with the clock of the external single unit on the time axis.

3. The integrated electronic system based on a unified Ethernet internal and external bus as described in claim 1, characterized in that, The time-triggered Ethernet is compatible with ordinary network data streams, AFDX data streams, and TTE network data streams on the same network platform; in the integrated electronic system, master control and measurement messages use TT messages or RC messages, and video messages use best-effort Ethernet messages.

4. The integrated electronic system based on a unified Ethernet internal and external bus as described in claim 1, characterized in that, The multiple functional modules include a high-speed processing module, a main control module, and a power supply module. The integrated electronic system uses a standardized backplane for internal bus message interaction. The high-speed processing module, the main control module, and the power supply module use a universal interface, which can receive information from the onboard inertial navigation system, ground telemetry and control, analog and digital quantities of the entire rocket measurement system, and ground power supply.

5. The integrated electronic system based on a unified Ethernet internal and external bus as described in claim 4, characterized in that, The power module provides power to the integrated electronic system; The high-speed processing module performs fault diagnosis according to a predetermined frame format. The fault diagnosis includes determining whether three or more of the following parameters exceed the preset range: the pressure after the oxygen pump, the pressure before the thrust chamber methane injection, the pressure before the thrust chamber oxygen injection, and the pressure before the generator methane injection. If the result is yes, an engine abnormality is detected, and an emergency shutdown signal is issued; if the result is no, no action is taken.

6. The integrated electronic system based on a unified Ethernet internal and external bus as described in claim 1, characterized in that, The integrated electronic system also includes a navigation module, which outputs the launch vehicle's current position information in real time.

7. The integrated electronic system based on a unified Ethernet internal and external bus as described in claim 1, characterized in that, The integrated electronic system also includes a main control function module, which receives messages from external RS422 and CAN digital interfaces and has external interfaces, enabling online data binding and modification of network configuration files during ground debugging.

8. The integrated electronic system based on a unified Ethernet internal and external bus as described in claim 1, characterized in that, The integrated electronic system also includes a high-speed processing module, which collects analog and digital signals from sensors, thermistor sensors, and non-electrical contact messages from other systems, stores and diagnoses faults according to a predetermined frame format, and decides whether to issue an emergency shutdown signal based on the judgment criteria. The high-speed processing module receives rapid and gradual change messages from the entire rocket, performs real-time monitoring, and provides a high-frequency signal interface to realize the transmission of rocket-to-ground telemetry signals.

9. The integrated electronic system based on a unified Ethernet internal and external bus as described in claim 1, characterized in that, The integrated electronic system also includes a timing drive module and a solenoid valve acquisition module. The timing drive module drives the solenoid valve, and the solenoid valve acquisition module acquires the real-time status of the solenoid valve during operation and feeds it back to the timing drive module via an internal bus.

10. The integrated electronic system based on a unified Ethernet internal and external bus as described in claim 1, characterized in that, The CPU or FPGA of each module within the integrated electronic system is programmed with a TTE IP core, enabling it to participate in clock synchronization; the external bus adopts a dual-channel cascaded star architecture.

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