A launcher electronic control system based on PCL and its system

Abstract

The present application discloses a launcher electric control method and system based on PCL, wherein the launcher electric control system based on PCL includes: a power supply and distribution unit, multiple controllers, multiple switches and multiple host computers; wherein the power supply and distribution unit is connected to multiple controllers to supply power to the multiple controllers; multiple controllers are connected to the host computer through a CAN bus and multiple switches, multiple controllers collect sensor data on the CAN bus, and transmit the sensor data to the host computer after logical processing, and also feed back the status data of the CAN bus to the test, launch and control system; multiple controllers can also receive instructions from the test, launch and control system through multiple switches. The present application is a dual-redundancy design of the PLC electric control system, which can adapt to extreme environments such as high temperature and strong wind. The dual-redundancy design can ensure that when any line or any equipment fails, it will not affect the activity of the entire launcher, and has high stability and high reliability.

Description

Technical Field

[0001] The present application relates to the field of rockets, and in particular, to a PCL-based launch pad electronic control method and system. Background Art

[0002] Against the background of normalized launch of carrier rockets, the development trend of rocket launchers is gradually moving towards low cost, high reliability and low failure rate. This trend is mainly reflected in the following aspects: 1. With the advancement of technology, especially the development of reusable technology, the cost of rocket launch has been greatly reduced. For example, SpaceX's Falcon 9 rocket has achieved 260 repeated launches through the recycling and reuse of the first stage, which fully reflects the economic value of reuse capability. In addition, the Starship project aims to achieve full reuse of the first and second stages of the carrier rocket, further improve the carrying efficiency and reduce costs. 2. In order to improve the reliability of the launch, the launcher system is becoming more intelligent. my country's first smart launch site system was born at the 9A station of the Taiyuan Satellite Launch Center. As the "super brain" of the launch site, this system realizes digitization, automation and intelligence through the software platform, which enhances the reliability and safety of the equipment. 3. Safety and stability are also important directions for the development of launchers. Taking the Long March 2F Yao 19 carrier rocket as an example, its reliability assessment value has been increased to 0.9904. By continuously eliminating weak links and optimizing technical status, the high safety of the launch is ensured. 4. With the development of commercial aerospace, cost-effectiveness has become an important consideration in the design of launch pads. Through technological innovation and process optimization, the cost of non-manned aerospace (such as satellite manufacturing and rocket manufacturing) is decreasing, while the performance is improving. The technological development of rocket launch pads is rapidly moving towards low cost, high reliability and low failure rate to meet the needs of normalized launches and ensure the successful execution of space missions. The control system of a single-carrier rocket launch pad is a complex system engineering, especially the electronic control system. Any minor changes may involve adaptive changes in many aspects. This poses a challenge to the reliability and stability of the control system. The launch pad control system needs to work in various harsh environments, such as high temperature, low temperature, strong wind, strong electromagnetic interference, etc. During the launch process, the system needs to respond quickly to various emergencies, such as abnormal rocket attitude, engine failure, etc., to ensure the safety and success of the launch. And rocket launch is a high-risk activity, and the control system must have a high degree of safety and reliability to prevent any situation that may lead to launch failure or accident.

[0003] Therefore, how to provide a launcher electronic control system that reduces costs while ensuring system performance has become an urgent problem to be solved in the field. Summary of the invention

[0004] The present application proposes a launcher electronic control system based on PCL, which specifically includes: a power supply and distribution unit, multiple controllers, multiple switches and multiple host computers; wherein the power supply and distribution unit is connected to the multiple controllers to provide power to the multiple controllers; the multiple controllers are connected to the host computer through a CAN bus and multiple switches for communication, the multiple controllers collect sensor data on the CAN bus, and transmit the sensor data to the host computer after logical processing, and also feed back the status data of the CAN bus to the test, launch and control system; the multiple controllers can also receive instructions from the test, launch and control system through multiple switches.

[0005] The PCL-based launcher electronic control system as described above, wherein the power supply and distribution unit includes a power module, an AP distribution cabinet, a power system power supply, and multiple CP cabinets; the power module connects the power to the AP distribution cabinet; the AP distribution cabinet transmits the connected power to the electronic control system power supply in one route; the power system power supply divides the transmitted power into n routes, which are respectively distributed to CP1 cabinet, CP2 cabinet to CPn cabinet; CP1 cabinet, CP2 cabinet to CPn cabinet respectively supply power to multiple controllers.

[0006] The PCL-based launcher electronic control system as described above also includes multiple power conversion modules and redundant power modules; the external 380V power supply is provided to the multiple power conversion modules through the AP distribution cabinet, and the multiple power conversion modules perform power conversion and aggregate the allocated power to the redundant power module. The redundant power module outputs the aggregated power to the power system power supply, and the power system power supply divides the allocated power into n routes, which are respectively distributed to CP1 cabinet, CP2 cabinet to CPn cabinet.

[0007] In the PCL-based launcher electronic control system as described above, the number of power conversion modules is 2.

[0008] As described above, the PCL-based launcher electronic control system, wherein the multiple controllers include controller 1, controller 2 to controller n; CP1 cabinet supplies power to controller 1, CP2 cabinet supplies power to controller 2, and so on, CPn cabinet supplies power to controller n.

[0009] The PCL-based launcher electronic control system as described above, wherein the CAN bus includes a CAN0 bus and a CAN1 bus; the host computer includes a host computer A and a host computer B; multiple switches include a CAN-to-Ethernet switch A and a CAN-to-Ethernet switch B; multiple controllers transmit processed data to the CAN0 and CAN1 buses, and the CAN0 and CAN1 buses transmit data to the host computer A and the host computer B. At the same time, the host computers A and B communicate with the test, launch and control system through Ethernet. The host computers A and B convert the Ethernet data sent by the test, launch and control system through the CAN-to-Ethernet switch A and the CAN-to-Ethernet switch B respectively, form CAN data and send it to the CAN0 and CAN1 buses, and transmit the data to multiple controllers through the CAN bus.

[0010] As described above, in the PCL-based launcher electronic control system, each controller includes a main controller and a redundant controller, the main controller 1 and the redundant controller 1 are PLC central control controllers, and the main controllers 2 to n and the redundant controllers 2 to n are PLC sub-control controllers.

[0011] As described above, in the PCL-based launcher electronic control system, the PLC sub-controller performs simple collection and output of sensor data, the PLC central control controller performs logical processing and status storage on the collected sensor data, and sends the processed sensor data to multiple host computers.

[0012] The PCL-based launcher electronic control system as described above, wherein the interface of the upper computer includes a process control interface, a single-step debugging interface and a status display interface; the process interface is used to control the continuous action of the launcher; the single-step debugging interface is used to control each valve and relay on the entire launcher system; the status display interface is used to convert the data sent from the PLC central control controller and display it on the interface, so as to observe the status information of each device.

[0013] A PCL-based launcher electronic control method comprises the following steps: sensor data signals DI and AI are respectively connected to the input ports of a PLC sub-controller; the PLC sub-controller collects sensor data and sends the collected sensor data to a CAN bus; the PLC central control controller collects sensor data sent by the PLC sub-controller from the CAN bus and performs logic processing on the sensor data; the PLC central control controller transmits the sensor data AO, DO and process data after the logic processing to the CAN bus; the PLC sub-controller reads the sensor data AO, DO and process data processed by the PLC central control controller from the CAN0 bus and sends them to a host computer, which performs data conversion and displays them in the host computer interface; the host computer performs Ethernet communication with a test, launch and control system, the host computer receives instructions from the test, launch and control system and sends them to the PLC central control controller, and the PLC central control controller controls the relevant actions of the launcher.

[0014] This application has the following beneficial effects:

[0015] This application is a dual-redundancy design of the PLC electric control system, which can adapt to extreme environments such as high temperature and strong wind. The dual-redundancy design adopted can ensure that when any line or any equipment fails, it will not affect the activity of the entire launcher, and has high stability and high reliability. At the same time, the overall control logic of the host computer, central control, and sub-control has powerful fault detection and diagnosis capabilities, so as to timely discover and repair potential problems before launch. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present application. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.

[0017] Figure 1 It is a schematic diagram of the internal structure of a launcher electronic control system based on PCL provided in an embodiment of the present application;

[0018] Figure 2 It is a schematic diagram of the internal structure of a power supply and distribution unit in a launcher electric control system based on PCL provided in an embodiment of the present application;

[0019] Figure 3 It is a flow chart of a PCL-based launcher electronic control method provided according to an embodiment of the present application. DETAILED DESCRIPTION

[0020] The following is a clear and complete description of the technical solutions in the embodiments of the present application in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present application.

[0021] The present application proposes a launcher electric control system based on PCL, which can ensure stable operation in various harsh environments, such as high temperature, low temperature, strong electromagnetic interference, etc. in the launcher control system. Photoelectric isolation is used between the internal circuit and the external circuit to reduce signal interference. At the same time, anti-interference measures are taken for each module, so the anti-interference ability of the whole system is greatly increased. In addition, since PLC has flexible programming capabilities and scalable hardware structure. By writing different programs, PLC can adapt to different launcher control system requirements, improving the flexibility and scalability of the system. Since PLC also has a self-diagnosis function, when a module fails, the faulty module can be quickly located and replaced, thereby restoring the normal operation of the system. PLC usually has a strong network communication capability, and can exchange data and remotely monitor with other devices and systems. In the launcher control system, PLC can be connected to other control systems, monitoring equipment, etc. through the network to realize real-time transmission and sharing of data, thereby improving the stable network communication capability of the system.

[0022] Embodiment 1

[0023] like Figure 1 As shown, this embodiment provides a launcher electronic control system based on PCL, which includes a power supply and distribution unit, multiple controllers, multiple switches and multiple host computers.

[0024] The power supply and distribution unit is connected to multiple controllers to provide power to the multiple controllers.

[0025] Among them Figure 2 The figure shows the specific structure of the power supply and distribution unit, which includes power modules (transmitter site power supply and emergency power supply), AP distribution cabinet, power station distribution box, electric control system power supply (not shown in the figure), multiple CP cabinets, air conditioning system and spare.

[0026] The power distribution box of the power station is responsible for supplying power to the launch site power devices such as the erection cylinder motor. The air conditioning system is responsible for ensuring the temperature inside the rocket fairing. The backup includes other electrical equipment at the launch site.

[0027] The power module is used to connect the power supply to the AP power distribution cabinet.

[0028] The power supply module includes the launch site power supply and the emergency power supply. The launch site power supply and the emergency power supply are 380V / 50Hz.

[0029] The AP power distribution cabinet divides the incoming power into four routes, distributing the power to the power station distribution box, the electric control system power supply, the air conditioning system and the backup.

[0030] The electric control system power supply divides the allocated power into n routes and distributes them to CP1 cabinet, CP2 cabinet to CPn cabinet respectively.

[0031] Among them, the CP1 cabinet, CP2 cabinet to CPn cabinet will distribute the power to controller 1, controller 2 to controller n respectively.

[0032] It is worth noting that there is a one-to-one power supply relationship between the CP cabinets and the controllers. The CP1 cabinet supplies power to the controller 1, the CP2 cabinet supplies power to the controller 2, and so on. The CPn cabinet supplies power to the controller n.

[0033] In this embodiment, the power supply and distribution unit adopts two power outputs. The solid and dotted arrows in the figure represent the two power outputs, thereby ensuring that even if any power supply is lost, it will not affect the operation of the power supply and distribution unit.

[0034] The power supply of the electric control system can also receive external 380V power supply. The external 380V power supply is given to two power conversion modules (not shown in the figure) through the AP distribution cabinet. The two power conversion modules convert the 220V voltage into 24V voltage for power supply. The two 24V voltages are aggregated through the redundant power supply module (not shown in the figure) and output to the power supply of the power supply system. The power supply of the power supply system divides the allocated power into n routes and distributes them to CP1 cabinet, CP2 cabinet to CPn cabinet respectively.

[0035] Multiple controllers are connected to the host computer through the CAN bus and multiple switches. Multiple controllers collect sensor data on the CAN bus, transmit the sensor data to the host computer after logical processing, and also feed back the status data of the CAN bus to the measurement, launch and control system; multiple controllers can also receive instructions from the measurement, launch and control system through multiple switches.

[0036] The multiple controllers are connected via CAN bus communication.

[0037] The multiple switches include a CAN-to-Ethernet switch A and a CAN-to-Ethernet switch B, and the CAN-to-Ethernet switch A and the CAN-to-Ethernet switch B are connected to the CAN bus respectively.

[0038] The multiple host computers include host computer A and host computer B.

[0039] The CAN bus includes the CAN0 bus and the CAN1 bus. The CAN bus uses redundant communication, and the failure of any one bus does not affect the system operation. The two buses send and receive data packets at the same time, and detect the bus heartbeat status at the same time, so as to make timely diagnosis of bus failures.

[0040] Specifically, multiple controllers transmit processed data to the CAN0 and CAN1 buses, and the CAN0 and CAN1 buses transmit the data to the host computer A and the host computer B. At the same time, the host computers A and B communicate with the measurement, launch and control system through Ethernet. The host computer converts the Ethernet data sent by the measurement, launch and control system through CAN to Ethernet switch A and CAN to Ethernet switch B respectively, forms CAN data and sends it to the CAN0 and CAN1 buses, and transmits the data to multiple controllers through CAN0 and CAN1.

[0041] CAN to Ethernet switch A and CAN to Ethernet switch B work at the same time. If any switch fails or any network cable is disconnected, network communication will not be affected. Both CAN to Ethernet switches A and B have dual Ethernet ports and dual CAN ports, and can read and write data from two CAN buses at the same time. Both Ethernet ports can be connected to host computers A and B.

[0042] Further, refer to Figure 1 , where CAN-to-Ethernet switch A is connected to host computer A for communication, and CAN-to-Ethernet switch B is connected to host computer B.

[0043] Based on the above, this embodiment designs all controllers redundantly, and each controller includes a main controller and a redundant controller. Controller 1 includes main controller 1 and redundant controller 1, controller 2 includes main controller 2 and redundant controller 2, and so on, controller n includes main controller n and redundant controller n.

[0044] This embodiment takes into account that the entire system is an overall coordinated control relationship, so the system mode of central control and sub-control is adopted, and controller 1 (including main control 1 and redundant controller 1) is defined as PLC central control controller, and the remaining controllers are defined as PLC sub-control controllers (including main controller 2-n and redundant controller 2-n except controller 1). That is, the PLC central control controller includes the main PLC central control controller (i.e. main controller 1) and the redundant PLC central control controller (i.e. redundant controller 1), and the PLC sub-control controller includes the main PLC sub-control controller (i.e. main controller 2-n) and the redundant PLC sub-control controller (i.e. redundant controller 2-n).

[0045] The PLC sub-controller performs simple collection and output of sensor data. The PLC central control controller performs logical processing and status storage on the collected sensor data, and sends the processed sensor data to multiple host computers. This central control and sub-control method can unify command, have a clear control logic structure, and is not prone to conflicts or control conflicts.

[0046] Specifically, data is transmitted between the PLC sub-controller and the PLC central controller via the CAN bus, wherein the main controller 2-n outputs the collected sensor data to the CAN0 bus, and the main controller 1 collects and performs logical processing on the sensor data output to the CAN0 bus by the main controller 2-n. The redundant controller 2-n outputs the collected sensor data to the CAN1 bus, and the redundant controller 1 collects and performs logical processing on the sensor data output to the CAN1 bus by the redundant controller 2-n. The main controller 1 and the redundant controller 1 send the sensor data after logical processing to the host computers A and B.

[0047] The upper computer interface is divided into process control interface, single-step debugging interface and status display interface; the main function of the process interface is to control the continuous action of the launch pad, mainly for special actions during launch missions; the main function of the single-step debugging interface is to control every valve and relay on the entire launch pad system, mainly for equipment inspection work before launch; the main function of the status display interface is to convert the data sent by the PLC central control controller and display it on the interface, so that the status information of each device can be observed in real time.

[0048] During the data conversion process, some data, such as KPa units, will be converted into MPa units for display. Some data, such as whether the device is online, will be indicated by a small light.

[0049] Embodiment 2

[0050] like Figure 3 As shown, the PCL-based launcher electronic control method implemented by the PCL-based launcher electronic control system of the first embodiment specifically includes the following steps:

[0051] Step S310: the PLC sub-controller collects sensor data and sends the collected sensor data to the redundant CAN bus.

[0052] Since the PLC sub-controller includes a main controller 2-n and a redundant controller 2-n, the main controller 2-n and the redundant controller 2-n both collect sensor data. The main controller 2-n sends the collected data to the CAN0 bus, and the redundant controller 2-n sends the collected data to the CAN1 bus.

[0053] Step S320: The PLC central control collects the sensor data sent by the PLC sub-controller from the CAN bus and performs logic processing on the sensor data.

[0054] The main controller 1 collects sensor data from the CAN0 bus for logic processing, and the redundant controller 1 collects sensor data from the CAN1 bus for logic processing.

[0055] The logical processing includes merging the data from multiple sensors or converting the units.

[0056] Step S330: The PLC central control transmits the sensor data AO, DO and process data after logical processing to the CAN bus.

[0057] The main controller 1 transmits the sensor data and process data after logic processing to the CAN0 bus, and the redundant main controller 1 transmits the sensor data and process data after logic processing to the CAN1 bus.

[0058] Step S340: The PLC sub-controller reads the sensor data AO, DO and process data processed by the PLC central controller from the CAN bus and sends it to the host computer, which converts the data and displays it in the host computer interface.

[0059] The main controller 2-n reads the processed sensor data AO, DO and process data transmitted by the main controller 1 from the CAN0 bus, and sends them to the host computer.

[0060] The redundant master controller 2-n reads the processed sensor data AO, DO and process data transmitted from the redundant master controller 1 from the CAN1 bus, and sends them to the host computer.

[0061] The host computer can obtain the status information of each device in the launcher through data conversion. During the data conversion process, some data, such as KPa units, will be converted into MPa units for display. Some data, such as whether the device is online, will be marked in the form of a small light.

[0062] The PLC central control controller can also receive command information sent by the host computer and control the relevant actions of the launcher.

[0063] At the same time, the host computer supports Ethernet communication with the test, launch and control system. The host computer receives instructions from the test, launch and control system and sends them to the PLC central control controller, which then controls the relevant actions of the launcher. At the same time, the overall status information of the launcher can also be sent to the test, launch and control system for real-time observation by the test, launch and control personnel.

[0064] This application has the following beneficial effects:

[0065] This application is a dual-redundancy design of the PLC electric control system, which can adapt to extreme environments such as high temperature and strong wind. The dual-redundancy design adopted can ensure that when any line or any equipment fails, it will not affect the activity of the entire launcher, and has high stability and high reliability. At the same time, the overall control logic of the host computer, central control, and sub-control has powerful fault detection and diagnosis capabilities, so as to timely discover and repair potential problems before launch.

[0066] Although the present application is described with reference to examples, this is for illustrative purposes only and is not intended to limit the present application, and changes, additions and / or deletions to the embodiments may be made without departing from the scope of the present application.

[0067] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any person skilled in the art who is familiar with the present technical field can easily think of changes or substitutions within the technical scope disclosed in the present application, which should be included in the protection scope of the present application. Therefore, the protection scope of the present application should be based on the protection scope of the claims.

Claims

1. A PCL-based launcher electronic control system, characterized in that: Specifically include: Power supply and distribution unit, multiple controllers, multiple switches and multiple host computers; The power supply and distribution unit is connected to multiple controllers to supply power to the multiple controllers; Multiple controllers are connected to the host computer through the CAN bus and multiple switches. Multiple controllers collect sensor data on the CAN bus, transmit the sensor data to the host computer after logical processing, and also feed back the status data of the CAN bus to the measurement, launch and control system; multiple controllers can also receive instructions from the measurement, launch and control system through multiple switches.

2. The PCL-based launcher electronic control system according to claim 1, characterized in that: The power supply and distribution unit includes power modules, AP distribution cabinets, power system power supplies, and multiple CP cabinets; The power module connects the power supply to the AP power distribution cabinet; The AP power distribution cabinet transmits the incoming power to the power supply of the electric control system in one path; The power supply system divides the transmitted power into n routes and distributes them to the CP1 cabinet, CP2 cabinet to CPn cabinet respectively; The CP1 cabinet, CP2 cabinet to CPn cabinet respectively supply power to multiple controllers.

3. The PCL-based launcher electronic control system according to claim 2, characterized in that: Also includes, multiple power conversion modules and redundant power modules; The external 380V power supply is supplied to multiple power conversion modules through the AP power distribution cabinet. The multiple power conversion modules perform power conversion and aggregate the allocated power to the redundant power module. The redundant power module outputs the aggregated power to the power supply system. The power supply system divides the allocated power into n routes and distributes them to CP1 cabinet, CP2 cabinet to CPn cabinet respectively.

4. The PCL-based launcher electronic control system according to claim 2, characterized in that: The number of power conversion modules is 2.

5. The PCL-based launcher electronic control system according to claim 4, characterized in that: The plurality of controllers include controller 1, controller 2 to controller n; The CP1 cabinet supplies power to controller 1, the CP2 cabinet supplies power to controller 2, and so on. The CPn cabinet supplies power to controller n.

6. The PCL-based launcher electronic control system according to claim 5, characterized in that: The CAN bus includes a CAN0 bus and a CAN1 bus; the host computer includes a host computer A and a host computer B; the multiple switches include a CAN to Ethernet switch A and a CAN to Ethernet switch B; Multiple controllers transmit the processed data to the CAN0 and CAN1 buses, and the CAN0 and CAN1 buses transmit the data to the host computer A and the host computer B. At the same time, the host computers A and B communicate with the test, launch and control system through Ethernet. The host computers A and B convert the Ethernet data sent by the test, launch and control system through the CAN to Ethernet switch A and the CAN to Ethernet switch B respectively, form CAN data and send it to the CAN0 and CAN1 buses, and transmit the data to multiple controllers through the CAN bus.

7. The PCL-based launcher electronic control system according to claim 6, characterized in that: Each controller includes a main controller and a redundant controller. The main controller 1 and the redundant controller 1 are PLC central control controllers, and the main controllers 2 to n and the redundant controllers 2 to n are PLC sub-control controllers.

8. The PCL-based launcher electronic control system according to claim 7, characterized in that: The PLC sub-controller performs simple collection and output of sensor data. The PLC central controller performs logical processing and status storage on the collected sensor data, and sends the processed sensor data to multiple host computers.

9. The PCL-based launcher electronic control system according to claim 8, characterized in that: The interface of the host computer includes the process control interface, the single-step debugging interface and the status display interface; The process interface is used to control the continuous movement of the launcher; The single-step debugging interface is used to control every valve and relay on the entire launcher system; The status display interface is used to convert the data sent by the PLC central controller and display it on the interface to observe the status information of each device.

10. A PCL-based launcher electronic control method, characterized in that: The following steps are involved: The sensor data signals DI and AI are connected to the input ports of the PLC sub-controller respectively; The PLC sub-controller collects sensor data and sends the collected sensor data to the CAN On the bus; The PLC central controller collects the sensor data sent by the PLC sub-controller from the CAN bus and performs logical processing on the sensor data; The PLC central controller transmits the sensor data AO, DO and process data after logical processing to the CAN bus; The PLC sub-controller reads the sensor data AO, DO and process data processed by the PLC central controller from the CAN0 bus and sends it to the host computer, which converts the data and displays it on the host computer interface; The host computer communicates with the test, launch and control system via Ethernet. The host computer receives instructions from the test, launch and control system and sends them to the PLC central control controller, which controls the relevant actions of the launcher.

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