A test device, test method and system for testing a testbed measurement and control system

Abstract

The test device for testing the test-bed measurement and control system is applied between real missile body engine related modules and subsystems of a liquid rocket engine test measurement and control system, and comprises a multi-way switch, an analog module and a processor. The processor has various communication interfaces, and realizes functions such as hardware remote transmission and distributed acquisition control through the communication interfaces. The multi-way switch is connected with the analog module and the processor. The multi-way switch and the analog module interact with an engineer station through the processor. The engineer station is used to generate instructions required by the test device. The analog module of the test device is used to realize simulation of real missile body engine related modules. The test device can be used to complete all functional debugging, automatic testing, process testing and reliability testing of the liquid rocket engine test measurement and control system, and has functions such as automation, modularization and flexibility, and can realize distributed control.

Description

Technical Field

[0001] This application relates to the field of liquid rocket engine testing, and in particular to a testing device, testing method and system for testing a test bench control system. Background Technology

[0002] Ground testing of liquid rocket engines is a crucial step in the rocket development process, verifying performance, reliability, and safety. The process is complex, covering the entire chain from system preparation to data verification. While the specific procedures may vary depending on the test type and objective, core components include test preparation, system integration and testing, and ignition testing. This test system allows for functional and performance verification by module and function, thereby improving the reliability and safety of the test and control system and ensuring its stable operation.

[0003] The liquid rocket engine test and control system is a large-scale and complex system with a long construction period. It is technologically advanced, reliable, and fully functional, possessing versatility, advanced technology, and scalability. The test bench control system mainly includes: propellant control system, engine control system, thrust measurement system, steady-state measurement system, dynamic measurement system, telemetry system, emergency shutdown system, oscillation system, and thrust adjustment system. Traditional testing methods for liquid rocket engine test and control systems primarily rely on manual operation and component-by-component testing. For example, manual signal sources and process calibrators are used to simulate sensor signals point-by-point for loading, or the control loop is verified by physically connecting real loads. This method suffers from drawbacks such as low efficiency, long preparation time, insufficient test coverage, high risk of human error, and poor safety. Especially for complex scenarios such as multi-stage parallel engine tests and reusable engines, traditional methods struggle to achieve rapid and systematic verification. There is an urgent need for a testing method that reduces manual intervention / operation, saves time and effort, improves the test preparation, debugging, and integration construction cycles of the control system, and features rapid, flexible, and adaptable switching. Summary of the Invention

[0004] This application proposes a testing device, testing method, and system for testing a test bench control system, which realizes automated, integrated, and modular testing, and can efficiently, accurately, and safely complete the full-chain testing and verification of complex test bench control systems.

[0005] In the first aspect, this application discloses a testing device for testing a test bench control system. The testing device is applied between a real rocket engine-related module and a liquid rocket engine test control system. The real rocket engine-related module is a rocket engine valve or an electrically detonating tube.

[0006] The liquid rocket engine test and control system is used to test relevant modules of a real rocket engine.

[0007] The testing device is used to simulate the relevant modules of the real rocket engine. The testing device is equipped with a multi-way switch, a simulation module connected to the multi-way switch, and a processor. The processor has various communication interfaces, and the engineer station controls the testing device in a distributed manner through the communication interfaces.

[0008] The test device controls a multiplexer to switch between the liquid rocket engine test and control system and the valves or electro-explosive tubes of the actual rocket engine; the liquid rocket engine test and control system includes an engine control system and a propellant control system.

[0009] The simulation module is a load simulation circuit, which includes multiple load equivalent elements connected in parallel. These multiple load equivalent elements are used to simulate the resistive load of a real rocket engine valve or an electric detonator.

[0010] When testing the engine control system or propellant control system, the engineer station controls a multiplexer to connect the load simulation circuit to the control channel output of the engine control system or propellant control system. The engineer station remotely controls the programmable power supply of the engine control system or propellant control system to provide voltage to the load simulation circuit. The engineer station collects the actual voltage across the equivalent load element. If the difference between the actual voltage and the voltage provided by the programmable power supply is within a preset threshold range, then the control channel function of the engine control system or propellant control system is normal.

[0011] Secondly, this application discloses another testing device for testing the test bench telemetry and control system. This testing device is used between a real rocket engine-related module and a liquid rocket engine test telemetry and control system; the real rocket engine-related module is a real rocket telemetry transmission device.

[0012] The liquid rocket engine test and control system is used to test relevant modules of a real rocket engine.

[0013] The testing device is used to simulate the relevant modules of the real rocket engine. The testing device is equipped with a multi-way switch, a simulation module connected to the multi-way switch, and a processor. The processor has various communication interfaces, and the engineer station controls the testing device in a distributed manner through the communication interfaces.

[0014] The test device controls a multiplexer to switch between the liquid rocket engine test and control system and the actual rocket telemetry and transmission equipment; the liquid rocket engine test and control system is a ground-based telemetry system.

[0015] The simulation module consists of multiple digital signal simulation circuits. Each digital signal simulation circuit is used to simulate the simulated data packets of a real rocket telemetry transmission device. The simulated data packets meet a preset data frame format.

[0016] During testing of the ground telemetry system, the engineer station controls a multiplexer to connect a digital signal analog circuit to a signal input channel of the ground telemetry system. The digital signal analog circuit sends analog data packets that meet a preset data frame format to a signal input channel of the ground telemetry system according to a specific timing sequence. The telemetry and control system compares the data of the parsed analog data packets with the data of the analog data packets initially sent by the digital signal analog circuit. If the data frame formats are consistent, the signal input channel of the ground telemetry system is functioning normally.

[0017] Thirdly, this application discloses another testing device for testing a test bench control system. This testing device is used between real rocket engine-related modules and a liquid rocket engine test control system; the real rocket engine-related modules are various sensors of the real rocket body.

[0018] The liquid rocket engine test and control system is used to test relevant modules of a real rocket engine.

[0019] The testing device is used to simulate the relevant modules of the real rocket engine. The testing device is equipped with a multi-way switch, a simulation module connected to the multi-way switch, and a processor. The processor has various communication interfaces, and the engineer station controls the testing device in a distributed manner through the communication interfaces.

[0020] The testing device controls a multiplexer to switch between the liquid rocket engine test and control system and various sensors on the actual rocket body; the liquid rocket engine test and control system is a measurement system, which includes a thrust measurement system, a steady-state measurement system, a dynamic measurement system, and an emergency shutdown system;

[0021] The simulation module consists of multiple voltage simulation loops. Each voltage simulation loop is used to simulate the output signals of various sensors of the real rocket engine. The output signals are standard voltage values.

[0022] When testing the measurement system, the engineer station controls a multiplexer to connect a voltage analog circuit to a signal input channel of the corresponding measurement system. The measurement system reads the actual voltage value collected on that channel. If the error between the actual voltage value and the standard voltage value is within a preset threshold, it is determined that the wiring of the signal input channel of the measurement and control system is correct.

[0023] Fourthly, this application provides another testing device for testing a test bench control system, wherein the testing device is applied between a real rocket engine-related module and a liquid rocket engine test control system; the real rocket engine-related module is a real rocket engine or a swing servo mechanism;

[0024] The liquid rocket engine test and control system is used to test relevant modules of a real rocket engine.

[0025] The testing device is used to simulate the relevant modules of the real rocket engine. The testing device is equipped with a multi-way switch, a simulation module connected to the multi-way switch, and a processor. The processor has various communication interfaces, and the engineer station controls the testing device in a distributed manner through the communication interfaces.

[0026] The test device controls a multiplexer to switch between the liquid rocket engine test and control system and the actual rocket engine or gyratory servo mechanism; the liquid rocket engine test and control system consists of a gyratory system and a thrust adjustment system.

[0027] The simulation module is a digital bus simulation circuit used to simulate the physical parameters of the engine or oscillating servo mechanism of a real rocket body, and to generate data packets that meet the preset communication protocol from the physical parameters.

[0028] When testing the sway system and thrust adjustment system, the engineering workstation controls a multiplexer to connect the digital bus analog circuit to a signal input channel of the corresponding sway system or thrust adjustment system. The sway system and thrust adjustment system parse the data packets according to a preset communication protocol. The engineering workstation compares the physical parameters parsed by the sway system and thrust adjustment system with the original physical parameters of the digital bus analog circuit. If the data frame formats of the two are consistent, the sway system and thrust adjustment system are functioning normally.

[0029] In one embodiment, the hardware configuration of the testing device includes:

[0030] NI host chassis, model PXIe-1084 host chassis;

[0031] The processor is a PXIE-8861 processor and also has a Modbus TCP interface;

[0032] The multiplexer is model CPCI-3722;

[0033] The analog signal acquisition board, model PXI4302, is used to acquire the voltage across the equivalent load element.

[0034] In one embodiment, when testing a ground telemetry system, the hardware configuration of the testing device includes:

[0035] NI host chassis, model PXIe-1084 host chassis;

[0036] The processor is a PXIE-8861 processor and also has a Modbus TCP interface;

[0037] The multiplexer is model CPCI-3722;

[0038] The digital signal analog circuit uses a PXIe-8433 communication card.

[0039] In one embodiment, when testing the measurement system, the hardware configuration of the testing device is as follows:

[0040] NI host chassis, model PXIe-1084 host chassis;

[0041] The processor is a PXIE-8861 processor and also has a Modbus TCP interface;

[0042] The multiplexer is model CPCI-3722;

[0043] The voltage simulation circuit uses the analog output board CPCI-3204 and the analog thermocouple board CPCI-4132.

[0044] In one embodiment, when testing the swing system and thrust adjustment system, the hardware configuration of the testing device is as follows:

[0045] NI host chassis, model PXIe-1084 host chassis;

[0046] The processor is a PXIE-8861 processor and also has a Modbus TCP interface;

[0047] The multiplexer is model CPCI-3722;

[0048] The digital bus analog circuit is a CPCI-2142 communication card, and the data packets meet the 1553B bus communication protocol.

[0049] Fifthly, this application also discloses a test system for testing a test bench control system, including an engineer station and several test devices as described above. The engineer station includes test management software and network switching equipment. The engineer station is connected to one or more test devices through the network switching equipment to form a distributed test network. The test management software is responsible for test process arrangement, test parameter configuration, test command issuance, real-time data monitoring and collection, and automatic analysis and report generation of test results.

[0050] In a sixth aspect, this application also discloses a test method for testing a test bench control system: the test device is applied between a real rocket engine-related module and a liquid rocket engine test control system, the liquid rocket engine test control system having multiple subsystems, the multiple subsystems being used to test the real rocket engine-related module;

[0051] The testing device includes a multiplexer, a simulation module, and a processor. The multiplexer is connected to the simulation module and the processor. The multiplexer and the simulation module interact with the engineering workstation through the processor. The engineering workstation is used to generate the instructions required by the testing device. The simulation module of the testing device is used to simulate multiple subsystems of the liquid rocket engine test and control system.

[0052] The multiplexer switches the measurement state according to the instructions issued by the engineer station. The measurement state includes normal measurement state and verification measurement state.

[0053] When the multi-channel switch is switched to the normal measurement state, the actual rocket engine-related modules are directly connected to the corresponding subsystems, realizing the test state of normal connection between the rocket engine-related modules and the corresponding subsystems.

[0054] When the multiplexer is switched to verification measurement mode, the test device simulates the actual rocket engine-related modules. At this time, the test device is disconnected from the actual rocket engine-related modules, and the simulation module inside the test device is directly connected to the corresponding subsystem. The simulation module simulates the physical parameters of the actual rocket engine-related modules or generates data packets that meet a preset communication protocol. The physical parameters or data packets are input to the corresponding subsystem. The subsystem obtains the received physical parameters or the physical parameters obtained from the data packets parsed by the subsystem. The subsystem compares the physical parameters obtained by the subsystem with the initial physical parameters of the simulation module. The comparison result determines whether the function of the subsystem is normal. The communication protocol of the initial physical parameters of the simulation module is the same as the communication protocol used by the subsystem, which is configured through the test management software.

[0055] The beneficial effects of this invention include:

[0056] Improve testing efficiency and automation: Achieve one-click automated testing, replacing a large number of tedious manual operations and records, and significantly shortening the system integration and test preparation cycle.

[0057] By employing modular, platform-based, and network-based design principles, we construct a high-performance, highly operable test, experimental data acquisition, and business management system to reduce personnel input and improve testing efficiency.

[0058] Enhanced test safety: By simulating real actuators with equivalent loads, the control logic and safety interlocks can be fully verified in advance without starting the real engine or process system, thus avoiding the risk of safety accidents caused by testing.

[0059] It enables functions such as direct issuance of test tasks, automatic data upload, and direct issuance and automatic import of test processes into the testing equipment terminal. Previously, these operations required manual operation. Through the information system, these operations are automatically realized, achieving automated debugging, reducing manual intervention, reducing human error, greatly improving testing efficiency, and enabling rapid delivery. Attached Figure Description

[0060] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For those skilled in the art, other drawings can be obtained based on these drawings.

[0061] Figure 1 This is a hardware architecture diagram of the test system provided in the embodiments of this application.

[0062] Figure 2 This is a flowchart of the testing method provided in the embodiments of this application.

[0063] Figure 3 This application provides an architecture diagram for testing an engine control system.

[0064] Figure 4 This application provides an architecture diagram for testing a ground telemetry system.

[0065] Figure 5 This application provides an architecture diagram for testing a thrust measurement system.

[0066] Figure 6 This application provides an architecture diagram for testing a steady-state measurement system.

[0067] Figure 7 This application provides an architecture diagram for testing a dynamic measurement system.

[0068] Figure 8 This application provides an architecture diagram for testing an emergency shutdown system.

[0069] Figure 9 The present application provides an architecture diagram for testing a swing system.

[0070] Figure 10 The present application provides an architecture diagram for testing a thrust adjustment system. Detailed Implementation

[0071] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0072] The liquid rocket engine telemetry and control system is a large-scale and complex system. It includes subsystems such as the propellant control system, engine control system, thrust measurement system, steady-state measurement system, dynamic measurement system, telemetry system, emergency shutdown system, gyration system, and thrust adjustment system. Ground testing of liquid rocket engines is a crucial step in verifying performance, reliability, and safety during rocket development. The process is complex and needs to cover the entire chain from system preparation to data verification. While the process may vary depending on the type and objective of the test, the core components include test preparation, system integration, and ignition testing.

[0073] The testing device of this application is used to verify whether the function of the liquid rocket engine measurement and control system is normal. The testing device of this application has different testing functions, which can verify the performance of the corresponding engine measurement and control system, improve the reliability and safety of the test measurement and control system, and ensure the stable operation of the test measurement and control system.

[0074] like Figure 1 As shown, the test system of this application includes an engineering station 10, a network switching device, and multiple test devices 20. The engineering station uses LabVIEW software to achieve communication between the multi-level test devices through the network switching device. The test system of this application performs distributed control of the test devices through wired or wireless networks. The test system has modular, functional, and flexible features. Each test device is configured with different test functions. For example, some test devices perform tests on telemetry systems, while others perform tests on measurement systems. The engineering station remotely controls the combined use of multiple test devices through test management software. At the same time, the test devices are equipped with cards with synchronization and timing functions. The host computer can control the clock synchronization between two or more PXIe chassis, and realize synchronous acquisition and output through routing trigger signals.

[0075] This testing device can be used to complete all functional debugging, automatic testing, process testing, and reliability testing of the liquid rocket engine test and control system. It has functions such as automation, modularity, and flexibility, and can realize distributed control. It can quickly complete the functional verification and test process debugging verification of the test and control system, reduce manual intervention / operation, save time and effort, and improve the integration construction cycle, test preparation cycle, and debugging cycle of the test and control system. It has the characteristics of rapid, flexible, and flexible switching, which improves the system's reliability, safety, and accuracy.

[0076] The ground control and measurement system is a complex and critical component of a liquid rocket engine testing system. It is responsible for measuring, controlling, and monitoring various parameters of the liquid rocket engine during ground testing. This system not only needs to ensure the safety and reliability of the testing process but also needs to provide accurate data support to enable researchers to analyze and optimize engine performance.

[0077] The measurement system is responsible for collecting various parameters of the engine during the test, such as pressure, temperature, flow rate, and vibration. These parameters are crucial for evaluating the engine's performance. The control system, based on feedback from the measurement system, precisely controls various operations during the test, such as fuel supply, ignition, and thrust adjustment.

[0078] like Figures 1-8 As shown, the testing device of this application is used between the relevant modules of the actual rocket engine and the subsystems of the liquid rocket engine test and control system; the liquid rocket engine test and control system is used to test the relevant modules of the actual rocket engine.

[0079] The testing device of this application includes a multiplexer, a simulation module, and a processor. The processor has various communication interfaces, enabling functions such as long-distance hardware transmission and distributed data acquisition and control. The multiplexer is connected to the simulation module and the processor. The multiplexer and simulation module interact with an engineering workstation via the processor. The engineering workstation generates the instructions required by the testing device. The simulation module of the testing device simulates relevant modules of a real rocket engine. The processor interacts with the engineering workstation via a wired or wireless network. The processor is electrically connected to the multiplexer, and the multiplexer inside the testing device is electrically connected to the simulation module.

[0080] This application enables the measurement of various subsystems of a liquid rocket engine test and control system. These subsystems include an engine control system, a thrust measurement system, a steady-state measurement system, a dynamic measurement system, a telemetry system, an emergency shutdown system, a gyratory system, and a thrust adjustment system.

[0081] This application also discloses a test method for testing a test bench control system: the test device is applied between a real rocket engine-related module and a liquid rocket engine test control system. The liquid rocket engine test control system has multiple subsystems, which are used to test the real rocket engine-related modules.

[0082] The testing device includes a multiplexer, a simulation module, and a processor. The multiplexer is connected to the simulation module and the processor. The multiplexer and the simulation module interact with the engineering workstation through the processor. The engineering workstation is used to generate the instructions required by the testing device. The simulation module of the testing device is used to simulate multiple subsystems of the liquid rocket engine test and control system.

[0083] The multiplexer switches the measurement state according to the instructions issued by the engineer station. The measurement state includes normal measurement state and verification measurement state.

[0084] When the multi-channel switch is switched to the normal measurement state, the actual rocket engine-related modules are directly connected to the corresponding subsystems, realizing the test state of normal connection between the rocket engine-related modules and the corresponding subsystems.

[0085] When the multiplexer is switched to verification measurement mode, the test device simulates the actual rocket engine-related modules. At this time, the test device is disconnected from the actual rocket engine-related modules, and the simulation module inside the test device is directly connected to the corresponding subsystem. The simulation module simulates the physical parameters of the actual rocket engine-related modules or generates data packets that meet the preset communication protocol. The physical parameters or data packets are input to the corresponding subsystem. The subsystem obtains the received physical parameters or the physical parameters obtained from the data packets parsed by the subsystem. The subsystem compares the physical parameters obtained by the subsystem with the initial physical parameters of the simulation module. The comparison result determines whether the function of the subsystem is normal. The communication protocol of the initial physical parameters of the simulation module is the same as the communication protocol used by the oscillation system and the thrust adjustment system, and is configured through the test management software.

[0086] The engineering station is used to generate the instructions required by the testing device. The engineering station can select a working mode according to the user's testing objectives. It is configured with a remote automatic mode and a remote manual mode. In remote automatic mode, it obtains function instructions (such as selecting the subsystem to be tested, shutting down, or starting) by reading the built-in test program and then generates control instructions based on these instructions, which are then sent to the multiplexer of the testing device. In remote manual mode, the user manually selects the appropriate control instructions to send to the multiplexer of the testing device as needed.

[0087] The multiplexer switches the measurement state according to the instructions issued by the engineer station. The measurement state includes normal measurement state and verification measurement state. When the multiplexer switches to the normal measurement state, the actual rocket engine is directly connected to a certain subsystem, realizing the test state of normal connection between the rocket engine module and the corresponding subsystem. When the multiplexer switches to the verification measurement state, the liquid rocket engine test and control system is disconnected from the actual rocket engine module, and the simulation module inside the test device is directly connected to the liquid rocket engine test and control system.

[0088] See Figure 1-3 The first embodiment discloses a measuring device for simulating real rocket engine valves and electric detonators. The testing device controls a multiplexer to switch between the liquid rocket engine test and control system and the real rocket engine valves and electric detonators. When the multiplexer is in the normal measurement state, the testing device is not connected. The engine control system forms a control loop with the real rocket engine valves and electric detonators, and the propellant control system forms a control loop with the real rocket engine valves. The measurement of the rocket engine valves and electric detonators is achieved by acquiring the voltage of the control loop.

[0089] When the multiplexer is in the verification measurement state, the test device is connected. At this time, the multiplexer directly connects the test device to the engine control system or propellant control system, and the measurement device is used to test the engine control system and propellant control system. The simulation module of the measurement device is a load simulation circuit, including multiple parallel load equivalent elements and an analog signal acquisition card for acquiring the voltage of the load equivalent elements. The multiple load equivalent elements are used to simulate the resistive load of the valves and electro-explosive tubes of the actual rocket engine.

[0090] When testing the engine control system and propellant control system, the engineer station connects the load simulation circuit to the control channel output of the engine control system by controlling the multiplexer switch. The engineer station remotely controls the programmable power supply of the engine control system or propellant control system to provide voltage to the load simulation circuit. The engineer station collects the actual voltage across the equivalent load element. If the difference between the actual voltage and the voltage provided by the programmable power supply is within a preset threshold range, the control channel function of the engine control system is normal.

[0091] The hardware configuration of the engineering workstation measuring device is as follows:

[0092] In the first embodiment of this application, when testing the engine control system and the propellant control system, the hardware configuration of the testing device includes:

[0093] The system includes an NI PXIe-1084 chassis, a CPCI-3722 multiplexer, a PXI-4302 analog input / output card, a PXIE-8861 processor, and a load equivalent element (a 50W wire-wound resistor). Among these components:

[0094] The main unit chassis is an 18-slot (including 17 mixed slots) PXIe high-performance test and measurement chassis. Its core function is to provide stable power supply, high-speed data interconnection, precise timing synchronization and efficient heat dissipation for various PXI / PXIe modules.

[0095] The processor, PXIE-8861, is responsible for running the test logic. It features dual Ethernet and RS485 communication interfaces, and supports TCP / IP, RS232, and RS485 communication protocols. It can also implement TCP / IP, Modbus TCP, and Modbus RTU communication protocols, enabling long-distance hardware transmission and distributed data acquisition and control via the network interface. This application utilizes the processor's Ethernet communication interface to achieve remote network communication between the industrial control host and the test device.

[0096] The multi-channel selection switch card, model CPCI-3722, serves as the core of signal routing, allowing output cards, acquisition cards, and load equivalents to be flexibly connected to different channels of the system under test.

[0097] The PXI-4302 data acquisition card is used to acquire the voltage across the equivalent load element.

[0098] The analog signal acquisition card uses the aforementioned PXI-4302 acquisition card, which has 32 channels and can acquire channel voltage parameters. The voltage to be measured is ±10V, and the sampling rate can reach 5KS / s.

[0099] In a specific application scenario of this application, the engine control system is electrically connected to the load equivalent element within the testing device via a multiplexer controlled by an engineer's workstation. Specifically, this includes a CPCI-3722 multiplexer card and wire-wound resistors. Each channel is connected to a set of wire-wound resistors, which are then connected to the control channel of the engine control system and the wire-wound resistors via a multiplexer switch. The selection is made via the multiplexer switch. The multiplexer card uses a CPCI-3722 multiplexer card. The load equivalent element is a 10-20 ohm 50W wire-wound resistor used to simulate engine valves. Another load equivalent element is a 1 ohm 50W wire-wound resistor used to simulate an electric detonator. Each channel of the CPCI-3722 multiplexer card is connected to a set of 50W wire-wound resistors connected in series, which are then connected to the control channel of the engine control system and the 50W wire-wound resistors via the CPCI-3722 multiplexer card. A PXI-4302 data acquisition card is connected in parallel across the load equivalent element to acquire the voltage across the load equivalent element. The engineer station remotely controls the engine control system with a programmable power supply that provides 5V to the load analog circuit. If the 5V voltage detected by the PXI-4302 data acquisition card for each load equivalent element matches the 5V value set by the programmable power supply, and the supply voltage and current are stable, then the engine control system's control channel function is normal, thus ensuring the reliable and stable control loop of the engine control system unit module. The PXI-4302 analog data acquisition card has 32 channels, capable of acquiring channel voltage parameters, with a measured voltage of ±10V, and a sampling rate of up to 5KS / s.

[0100] In a specific scenario, the load equivalent element used is consistent with the internal resistance of the engine solenoid valve. The power supply voltage is adjustable from 0-40V, supplying 0.5A-1A to the valve. The load equivalent element is selected as a 50W corrugated wire-wound resistor with a resistance of 10-20 ohms. Forty load equivalent elements are arranged in parallel, and the power supply model is selected as 40V, 40A.

[0101] The power supply is provided to the wire-wound resistor via the processor's DO control channel. The measured load equivalent element voltage is 1A, with 20 channels operating simultaneously, resulting in a total current of 20A. A multiplexer switch allows for single-channel, dual-channel, and 64-channel selection, enabling verification of the correctness and reliability of the engine solenoid valve control channels and facilitating rapid remote verification.

[0102] The engineer station of the test management software operates a multi-channel switch to perform channel testing, realizing the simulation of engine valves and electric detonators. It can test the electrical performance parameters of the control loop. The voltage of each channel detected by the PXI-4302 acquisition card is 5V, which is normal. This ensures the reliable and stable operation of the engine control system and process valve control, and the stable and reliable operation of the test bench control system and the controlled object on the test bench, thus achieving the system simulation effect.

[0103] The power supply for the engine control system in this application is connected to the processor module within the testing device. The processor module uses the aforementioned PXI8861 processor, equipped with dual Ethernet communication interfaces, an RS485 communication interface, and TCP / IP communication protocol. The device's Ethernet port not only enables remote network communication between the industrial control host and the PXI8861 processor but also features a Modbus TCP communication protocol network interface. This allows for remote operation of the power supply system during the preparation and comprehensive testing phases of the test and control system, and enables remote and precise voltage boosting / debossing of the system power supply, reducing the need for manual adjustments. This power supply utilizes remote control technology based on Modbus TCP network communication, enabling remote power settings.

[0104] It should be noted that during the testing of the propellant control system, this testing device was only used to simulate the valves of a real rocket engine; there was no electro-explosive tube. The simulation module was a 10-ohm 50W wire-wound resistor.

[0105] The testing equipment and procedures used for testing the propellant control system are exactly the same as those used for testing the engine control system, and will not be repeated here.

[0106] Reference Figure 4 As shown, the second embodiment of this application discloses a measuring device for simulating a real rocket telemetry transmission device.

[0107] The liquid rocket engine test and control system is a ground telemetry system. The simulation module consists of multiple digital signal simulation circuits. Each digital simulation circuit is used to simulate the simulated data packets of the real rocket telemetry transmission equipment. The simulated data packets meet the preset data frame format.

[0108] During testing of the ground telemetry system, the engineer station controls a multiplexer to connect a digital signal analog circuit to a signal input channel of the ground telemetry system. The digital signal analog circuit sends analog data packets that meet a preset data frame format to a signal input channel of the ground telemetry system according to a specific timing sequence. The telemetry and control system compares the data of the parsed analog data packets with the data of the analog data packets initially sent by the digital signal analog circuit. If the data frame formats are consistent, the signal input channel of the ground telemetry system is functioning normally.

[0109] During the testing of the telemetry system, the engineer station controls the multiplexer to switch from the normal measurement state to the verification measurement state. In the verification measurement state, the ground telemetry system is disconnected from the actual rocket engine telemetry transmitting equipment, and the simulation module in the test device is connected to the liquid rocket engine test and control system. The digital signal simulation circuit used in the simulation module of this application is a communication board. The communication board is used to simulate the rocket engine telemetry transmitting equipment. The communication board is the PXIE-8433 communication card mentioned above, which is used to simulate the communication protocol of the telemetry system.

[0110] In this normal measurement state, the ground telemetry system is connected to the actual rocket engine telemetry transmitter. The communication bus between the rocket engine telemetry transmitter and the ground telemetry system uses RS422 bus communication mode, supporting full-duplex and differential operation modes without interference (TX+JX, RX+, RX). In the normal measurement state, the rocket engine telemetry transmitter is used to transmit relevant information such as sensor parameters and valve status on the rocket engine to the ground telemetry system through a preset communication protocol.

[0111] During the testing of the telemetry system, a PXIE-8433 communication card was used to simulate the telemetry transmitting equipment interface of the rocket engine. Communication interface matching tests were conducted to complete functional verification, effectively improving test preparation efficiency and reducing operational errors. The telemetry system was tested using its integrated multi-channel RS422 communication card PXIE-8433 and multiplexer CPCI-3722 to flexibly construct test connections. Specifically, the RS422 channels of the communication card were connected to the corresponding interfaces of the "telemetry system" under test via the multiplexer. In this configuration, the test device simulated the role of the "rocket body telemetry transmitting equipment interface."

[0112] The engineering workstation is equipped with test management software. Communication protocol parameters consistent with the rocket's telemetry transmitting equipment are configured in the test management software, including but not limited to baud rate, data bits, stop bits, checksum method, and specific data frame format and algorithm. During testing, the test management software controls the communication board to continuously or sequentially send pre-set simulated data packets to the telemetry system according to the set protocol. These data packets simulate real sensor parameters (such as pressure and temperature values) and valve status signals.

[0113] In the second embodiment of this application, the testing apparatus includes:

[0114] The NI PXIe-1084 host chassis has the same structure, function and purpose as the first embodiment, and will not be described again here.

[0115] The processor uses a PXIE-8861, which is responsible for running the test logic and realizing network communication through its integrated dual Ethernet ports, RS485 and other interfaces, which is the same as the first embodiment and will not be described again.

[0116] The CPCI-3722 multiplexer switch is the same as the first embodiment and will not be described again.

[0117] The digital signal analog circuit uses a PXIE-8433 communication board to simulate the analog data packets of a real rocket telemetry transmitting device. The analog data packets are communicated according to the RS422 communication protocol, which is as follows:

[0118] Baud rate: 115200Kbps;

[0119] Data format: 1 start bit, 8 data bits, 1 stop bit, no parity bit;

[0120] Response mode: Data frames are in bytes. Two-byte data are transmitted first, then the lower 8 bits. Bytes within a frame are sent continuously without intervals.

[0121] Data frame format: frame header, frame sequence number and parameter check bits, frame tail mode is sent to verify that the telemetry system unit functions normally.

[0122] The PXIE-8433 communication board sends simulated data packets that meet a preset data frame format to a signal input channel of the ground telemetry system according to a specific timing sequence. The engineer station compares the data of the simulated data packets parsed by the telemetry system with the data of the simulated data packets initially sent by the PXIE-8433 communication board. If the formats are consistent and both follow the preset data frame format, then the signal input channel of the ground telemetry system is functioning normally.

[0123] The PXIE-8433 communication board can perform simulation testing of telemetry communication protocols, and has the capability to match 4 RS422 communication interfaces. Through data protocol interface verification, it can realize the software and hardware matching test of the test bench telemetry system equipment.

[0124] The CPC3722 multiplexer and PXIE 8433 communication card of the test device in this application enable the switching connection between the rocket engine-related modules and the ground telemetry system. According to the relevant communication requirements, the data interface matching is completed. If the communication rate, data algorithm, and format are correctly matched, and the signal requirements of the ground telemetry system can be met by the test management software, it proves that the ground telemetry system is working normally.

[0125] Reference Figure 5-7 As shown, the third embodiment of this application discloses a measuring device for simulating various sensors of a real rocket body.

[0126] like Figure 2 as well as Figures 5-7 As shown, during the testing of the measurement system, the engineer station controls the multiplexer to switch from the normal measurement state to the verification measurement state. At this time, the simulation module is connected to the liquid rocket engine test and control system through the multiplexer. The liquid rocket engine test and control system is a measurement system, which includes a thrust measurement system, a steady-state measurement system, a dynamic measurement system, and an emergency shutdown system.

[0127] In this embodiment, the testing device controls a multiplexer to switch between the liquid rocket engine test and control system and various sensors on the actual rocket body. The simulation module accurately simulates the standard electrical signals output by various physical sensors; and injects the standard electrical signals into the measurement system under test, collects the measured values ​​of the measurement system and compares them with the standard electrical signals. If the deviation between the two is within the allowable error range, it automatically determines that the acquisition circuit of the measurement system is correctly connected, the wiring is correct, and the acquisition function is normal.

[0128] The simulation module consists of multiple voltage simulation loops. Each voltage simulation loop is used to simulate the output signals of various sensors of the actual rocket engine. The output signals are standard voltage values. When testing the measurement system, the engineer station controls a multiplexer to connect a voltage simulation loop to a signal input channel of the corresponding measurement system. The measurement system reads the actual voltage value collected on that channel. If the error between the actual voltage value and the standard voltage value is within a preset threshold, it is determined that the wiring of the signal input channel of the measurement and control system is correct.

[0129] During the test of the thrust measurement system, the simulation module simulates the engine's thrust, pressure, and speed. During the test of the dynamic measurement system, the simulation module simulates the engine's vibration, strain, and pulsating pressure. During the test of the steady-state measurement system, the simulation module simulates the engine's temperature and pressure. The power supply for the steady-state measurement system, the thrust measurement system, or the dynamic measurement system all communicate with the engineering workstation through the test device.

[0130] In the third embodiment of this application, the hardware configuration of the measuring device includes

[0131] The NI PXIe-1084 host chassis has the same structure, function and purpose as the first embodiment, and will not be described again here.

[0132] The CPCI-3722 multiplexer switch has the same structure, function and purpose as the first embodiment, and will not be described again here.

[0133] The voltage simulation circuit uses the PXI-4302 analog signal acquisition board to acquire the output signals of various sensors of the rocket engine with high precision.

[0134] The engineering workstation connects one channel of the PXI-4302 analog signal acquisition board to one signal input channel of the measurement system via a multiplexer, and remotely configures the analog signal acquisition board and the multiplexer channel.

[0135] Figure 5 This application describes a test apparatus for testing the thrust measurement system. The apparatus includes a CPCI-3204 analog output board and a CPCI-3722 multiplexer card. The CPCI-4132 card has four mV-level outputs, capable of testing 128 thermocouple sensors. The CPCI-3204 analog output cards have four volt (V)-level outputs, capable of providing 128 voltage output channels. The CPCI-3722 multiplexer card has eight switches, which are used to measure the thrust measurement system by switching the multiplexer.

[0136] like Figure 5 As shown, this application uses a multiplexer CPCI-3722 to connect a channel of an analog output board CPCI-3204 to a signal input channel of the thrust measurement system under test. The test management software on the engineering workstation is configured to control the CPCI-3204 to output a precise DC voltage signal within the 0-10V range (e.g., 5V corresponds to 50% of the pressure range). Normal data values ​​from the thrust measurement system are simulated by the CPCI-3204 outputting a 0-10V voltage signal. If the thrust measurement system acquires a voltage value within the 0-10V range, it proves that the sensor circuit connection for acquiring engine thrust and pressure is correct, and the circuit wiring is correct.

[0137] Figure 6 This application describes a test apparatus for testing a steady-state measurement system. The apparatus includes CPCI-4132 analog thermocouple boards and CPCI-3722 multiplexer cards. Four CPCI-4132 analog thermocouple boards are configured, with mV-level output, capable of testing 128 thermocouple sensors. Four CPCI-3204 analog output cards are configured, with V-level output, capable of testing 128 pressure sensors (voltage output). Eight CPCI-3722 multiplexer cards are configured, allowing for measurement of the steady-state measurement system by switching multiplexers.

[0138] During the testing of the steady-state measurement system, the test management software on the engineering workstation controls the CPCI-3722 multiplexer to connect a channel of an analog thermocouple board CPCI-4132 to a temperature acquisition channel of the steady-state measurement system under test. After the test management software controls the CPCI-4132 to output a precise millivolt signal within ±10mV (e.g., a T-type thermocouple analog signal corresponding to a specific temperature value) to initiate the test, the test management software on the engineering workstation simultaneously reads the engineering values ​​(e.g., temperature values) acquired and converted by the steady-state measurement system under test on that channel via the communication network.

[0139] The test management software on the engineering workstation compares the measured values ​​with the standard electrical signal output from the CPCI-4132 analog thermocouple board. If the deviation is within the allowable error range (e.g., the acquisition voltage is within ±10mV tolerance), it automatically determines that the steady-state measurement system's acquisition circuit connection is correct, the wiring is correct, and the acquisition function is normal. Through polling with a multiplexer, testing of all temperature acquisition channels can be completed automatically.

[0140] like Figure 7 The diagram shows the test apparatus used in this application to test the dynamic measurement system. The hardware configuration is the same as that of the inference measurement system and will not be repeated here. The analog output board CPCI-3204 outputs a voltage signal (standard voltage) within the 0-10V range to the signal input channel of the dynamic measurement system. The engineer station reads the actual voltage value acquired by the dynamic measurement system on this channel. If the measurement system module acquires a voltage value within the 0-10V range, and the error between the two is within a preset threshold, it proves that the connection of the vibration, strain, and pulsating pressure sensor circuits in the dynamic measurement system module is correct, and the circuit wiring is correct.

[0141] like Figure 8 The image shows the test device used in this application to test the emergency shutdown system. The test device is equipped with an analog output board CPCI-3204, a CPCI-3722 multiplexer card, and a processor PXIe-8861. The processor's Ethernet interface supports the Modbus TCP protocol.

[0142] The system connects to the CPCI-3204 analog output board via a multiplexer. The CPCI-3204 simulates various standard signal sources and outputs multiple parameter types (sine wave, DC voltage, and frequency signals). Connected to the emergency shutdown system via a switch, it outputs pressure and engine speed parameters as required by the shutdown parameters, thus enabling functional testing of the entire emergency shutdown system. The CPCI-3204 analog output board provides 0-10V, 0-10mV, and 100mV voltage and frequency signals (e.g., 300Hz, 100mV) to simulate engine pressure, engine speed, and other parameters (for testing emergency shutdown conditions). After receiving the acquired signals, the measurement system checks the loop signals. If the data from each measurement channel is normal, the system's voltage and frequency signals are verified as correct.

[0143] The hardware configuration of the simulation module in the third embodiment of this application is as follows:

[0144] To meet the testing requirements of large-scale test benches for multiple parameters and high channel counts, the test device adopts a modular combination approach. The analog output board model CPCI-3204 (32-channel voltage output card) used in this application is configured with multiple analog output boards CPCI-3204 (e.g., 4 boards). Each board provides multiple voltage volt (V) level outputs, which can simulate a total of 128 standard voltage signals for simulating the outputs of pressure transmitters, vibration sensors, etc. The output range is adjustable (e.g., 0-10V, ±10V).

[0145] The analog thermocouple board is configured with multiple CPCI-4132 analog thermocouple boards (e.g., 4 boards), each providing multiple high-resolution millivolt (mV) level outputs, totaling 128 analog thermocouple (e.g., T-type, K-type) temperature sensor signals. Multiple CPCI-3722 multiplexers (e.g., 8 boards) are configured as a large signal routing matrix, flexibly switching the numerous channels of the aforementioned analog output boards to the corresponding input channels of the tested thrust, steady-state, or dynamic measurement system according to test case requirements.

[0146] The processor (PXIe-8861) and the main chassis (PXIe-1084) coordinate all boards to execute test sequences. Four CPCI-3204 analog output boards are configured, each with a volt (V) output, capable of supporting 128 channels of voltage output. Eight CPCI-3722 multiplexer cards are configured. By switching the multiplexers, the normal functioning of the thrust measurement system, steady-state measurement system, and dynamic measurement system is verified.

[0147] When measuring the emergency shutdown system, the structure, function, and testing methods of the test device used are completely consistent with those of the inference measurement system, and will not be repeated here.

[0148] In addition, to test dynamic response, programmable outputs of dynamic signals such as sine waves and step signals can simulate vibration or rapidly changing pressure. The test management software reads the voltage value or converted physical quantity value acquired by the measured system under test on this signal input channel. If the acquired value is within the allowable error range of 0-10V for DC signals, and the amplitude and frequency response of dynamic signals meet expectations, the system automatically determines that the acquisition circuit is correctly connected, the wiring is correct, and the static accuracy and dynamic response functions are normal.

[0149] Reference Figure 9-10 As shown, the fourth embodiment of this application discloses a measuring device for simulating the engine or oscillating servo mechanism of a real arrow body.

[0150] In this embodiment, the test device controls the multiplexer to switch between the liquid rocket engine test and control system and the rocket body's engine or sway servo mechanism. When the multiplexer is switched to the normal measurement state, the sway system is connected to the sway servo mechanism, or the thrust adjustment system is connected to the actual rocket body's engine. The sway system is used to control the swaying of the engine nozzle or thrust chamber, and the thrust adjustment system adjusts the propellant flow rate by collecting sensor parameters such as engine pressure and temperature to complete engine thrust control.

[0151] During normal measurement, the swaying system sends various control commands to the actual swaying servo mechanism through a preset communication protocol and obtains physical parameters such as engine pressure and temperature of the actual swaying servo mechanism. The thrust adjustment system sends various control commands to the actual engine through a preset communication protocol and obtains physical parameters such as engine pressure and temperature.

[0152] When the multiplexer is switched to the verification measurement state, the test device simulates the engine or oscillation servo mechanism of the real rocket body. At this time, the test device is disconnected from the engine or oscillation servo mechanism of the real rocket body, and the simulation module inside the test device is directly connected to the oscillation system and thrust adjustment system. In this embodiment, the simulation module is a digital bus simulation circuit, which is used to simulate the physical parameters of the engine / oscillation servo mechanism of the real rocket body and generate data packets that meet the preset communication protocol.

[0153] When testing the sway system and thrust adjustment system, the engineering workstation controls a multiplexer to connect the digital bus analog circuit to a signal input channel of the corresponding sway system or thrust adjustment system. The sway system and thrust adjustment system parse the data packets according to a preset communication protocol. The engineering workstation compares the physical parameters parsed by the sway system and thrust adjustment system with the original physical parameters of the digital bus analog circuit. If the data frame formats of the two are consistent, the sway system and thrust adjustment system are functioning normally.

[0154] In this embodiment, the digital bus analog circuit is a CPCI-2142 communication card, which adopts the 1553B bus communication protocol. The CPCI-2142 communication card transmits the aforementioned data packets to the swaying system and thrust adjustment system via the 1553B bus communication protocol. The swaying system and thrust adjustment system parse the data packets according to the 1553B bus communication protocol. The communication protocol of the initial physical parameters of the digital bus analog circuit is the same as the communication protocol used by the swaying system and thrust adjustment system, and is configured through the test management software.

[0155] The gyration system controls the engine / gyration servo mechanism via the 1553B bus protocol, while the thrust adjustment system controls flow and opening via the 1553B bus. Onboard parameters, status, and other relevant information are transmitted to the gyration and thrust adjustment systems via the communication bus. The test setup simulates the engine's gyration angle, required temperature, pressure, flow rate, and opening parameters to perform communication interface function matching tests, completing functional verification and effectively improving test preparation efficiency and reducing operational errors.

[0156] The testing device uses a hardware multiplexer (CPCI3722) and a CPCI-2142 communication card to switch connections between the rocket body equipment, the oscillation system module, and the thrust adjustment system. Data interface matching is completed according to relevant communication requirements. If the communication rate, data algorithm, and format are correctly matched, and the software control can meet the equipment requirements, then the system is functioning normally.

[0157] The hardware components of the testing apparatus in embodiments 1-4 above specifically include:

[0158] Communication cards: such as the PXIe-8433 communication card (multi-channel RS422), used to simulate the communication protocol of telemetry systems;

[0159] CPCI-2142 (1553B) is used for testing bus communication.

[0160] The Ethernet interface supports the Modbus TCP protocol, enabling remote control of the integrated programmable power supply within the test system to achieve automatic voltage rise and fall, used for simulating power supply change testing.

[0161] Analog thermocouple board: including CPCI-4132 (high-precision thermocouple signal analog card), which can output high-resolution micro voltage signals within ±100mV for simulating thermocouple sensors;

[0162] The CPCI-3204 analog output card (32-channel voltage output card) has an adjustable output range (e.g., 0-10V, ±10V) and is used to simulate standard voltage signals from transmitters such as pressure and vibration transmitters.

[0163] Analog signal acquisition board: such as PXI-4302, used for high-precision acquisition of circuit voltage.

[0164] The Ethernet interface of the test device in the above embodiments supports the Modbus TCP protocol. Modbus TCP is used to transmit power / PDU, realize intelligent power-off control, realize remote control, save manpower, and eliminate the need for front-end and back-end debugging, thus realizing system flexibility and modularity.

[0165] The simulation module of the test device can simulate the solenoid valves of liquid rocket engines, the telemetry transmission equipment interface of rocket engines, and emergency shutdown signals.

[0166] The core hardware platform of each test setup uses an NI PXIe chassis. For example... Figure 1 As shown, for large-scale test scenarios requiring multi-chassis collaboration, precise clock synchronization and synchronous trigger acquisition / output between multiple PXIe chassis can be achieved through timing and synchronization boards and routing trigger signals. Using an NI PXIe chassis and engineering workstation software, 32 channels are selected to output either DC voltage or frequency signals for verifying the configuration of each subsystem, thus saving test preparation time. The PXIe-8433, supporting dual redundant RS422 communication interfaces, is selected to complete the corresponding hardware communication tests.

[0167] The aforementioned highly integrated and automated testing process can perform rapid and accurate "check-ups" on up to hundreds of measurement channels at once, completely changing the inefficient traditional method of relying on manual wiring and verifying each channel individually using portable signal sources. This application not only greatly improves efficiency in the test preparation stage, but also objectively and quantitatively verifies the accuracy and reliability of the entire measurement and control system through the injection of high-precision standard signals, providing a prerequisite guarantee for the credibility of engine test data.

[0168] The testing system of the present invention includes an engineering station and several testing devices as described above. The engineering station includes test management software and network switching equipment. The engineering station is connected to one or more testing devices through the network switching equipment to form a distributed testing network. The test management software is responsible for test process arrangement, test parameter configuration, test command issuance, real-time data monitoring and collection, and automatic analysis and report generation of test results.

[0169] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

Claims

1. A testing device for testing a test bench control system, characterized in that: The testing device is used between real rocket engine-related modules and liquid rocket engine test and control systems; the real rocket engine-related modules are rocket engine valves or electric detonation tubes. The liquid rocket engine test and control system is used to test relevant modules of a real rocket engine. The testing device is used to simulate the relevant modules of the real rocket engine. The testing device is equipped with a multi-way switch, a simulation module connected to the multi-way switch, and a processor. The processor has various communication interfaces, and the engineer station controls the testing device in a distributed manner through the communication interfaces. The test device controls a multiplexer to switch between the liquid rocket engine test and control system and the valves or electro-explosive tubes of the actual rocket engine; the liquid rocket engine test and control system includes an engine control system and a propellant control system. The simulation module is a load simulation circuit, which includes multiple load equivalent elements connected in parallel. These multiple load equivalent elements are used to simulate the resistive load of a real rocket engine valve or an electric detonator. When testing the engine control system and / or propellant control system, the engineering workstation connects the load simulation circuit to the control channel output of the engine control system or propellant control system by controlling a multiplexer switch. The engineering workstation remotely controls the programmable power supply of the engine control system or propellant control system to provide voltage to the load simulation circuit. The engineering workstation collects the actual voltage across the equivalent load element. If the difference between the actual voltage and the voltage provided by the programmable power supply is within a preset threshold range, the control channel function of the engine control system or propellant control system is normal.

2. A testing device for testing a test bench control system, characterized in that: The testing device is used between real rocket engine-related modules and liquid rocket engine test and control systems; the real rocket engine-related modules are real rocket telemetry transmission equipment. The liquid rocket engine test and control system is used to test relevant modules of a real rocket engine. The testing device is used to simulate the relevant modules of the real rocket engine. The testing device is equipped with a multi-way switch, a simulation module connected to the multi-way switch, and a processor. The processor has various communication interfaces, and the engineer station controls the testing device in a distributed manner through the communication interfaces. The test device controls a multiplexer to switch between the liquid rocket engine test and control system and the actual rocket telemetry and transmission equipment; the liquid rocket engine test and control system is a ground-based telemetry system. The simulation module consists of multiple digital signal simulation circuits. Each digital signal simulation circuit is used to simulate the simulated data packets sent by the actual rocket telemetry equipment. The simulated data packets meet the preset data frame format. During testing of the ground telemetry system, the engineer station controls a multiplexer to connect a digital signal circuit to a signal input channel of the ground telemetry system. The digital signal circuit sends simulated data packets that meet a preset data frame format to a signal input channel of the ground telemetry system according to a specific timing sequence. The telemetry system compares the data of the parsed simulated data packets with the data of the simulated data packets initially sent by the digital signal analog circuit of the test device. If the data frame formats are consistent, the signal input channel of the ground telemetry system is functioning normally.

3. A testing device for testing a test bench control system, characterized in that: The testing device is applied between real rocket engine-related modules and liquid rocket engine test and control systems; the real rocket engine-related modules are various sensors of the real rocket body. The liquid rocket engine test and control system is used to test relevant modules of a real rocket engine. The testing device is used to simulate the relevant modules of the real rocket engine. The testing device is equipped with a multi-way switch, a simulation module connected to the multi-way switch, and a processor. The processor has various communication interfaces, and the engineer station controls the testing device in a distributed manner through the communication interfaces. The testing device controls a multiplexer to switch between the liquid rocket engine test and control system and various sensors on the actual rocket body; the liquid rocket engine test and control system is a measurement system, which includes a thrust measurement system, a steady-state measurement system, a dynamic measurement system, and an emergency shutdown system; The simulation module consists of multiple voltage simulation loops. Each voltage simulation loop is used to simulate the output signals of various sensors of the real rocket engine. The output signals are standard voltage values. When testing the measurement system, the engineer station controls a multiplexer to connect a voltage analog circuit to a signal input channel of the corresponding measurement system. The measurement system reads the actual voltage value collected on that channel. If the error between the actual voltage value and the standard voltage value is within a preset threshold, it is determined that the wiring of the signal input channel of the measurement and control system is correct.

4. A testing device for testing a test bench control system, characterized in that: The testing device is applied between real rocket engine-related modules and liquid rocket engine test and control systems; the real rocket engine-related modules are real rocket engines or swing servo mechanisms. The liquid rocket engine test and control system is used to test relevant modules of a real rocket engine. The testing device is used to simulate the relevant modules of the real rocket engine. The testing device is equipped with a multi-way switch, a simulation module connected to the multi-way switch, and a processor. The processor has various communication interfaces, and the engineer station controls the testing device in a distributed manner through the communication interfaces. The test device controls a multiplexer to switch between the liquid rocket engine test and control system and the actual rocket engine or gyratory servo mechanism; the liquid rocket engine test and control system consists of a gyratory system and a thrust adjustment system. The simulation module is a digital bus simulation circuit used to simulate the physical parameters of the engine or oscillating servo mechanism of a real rocket body, and to generate data packets that meet the preset communication protocol from the physical parameters. When testing the sway system and thrust adjustment system, the engineering workstation controls a multiplexer to connect the digital bus analog circuit to a signal input channel of the corresponding sway system or thrust adjustment system. The sway system and thrust adjustment system parse the data packets according to a preset communication protocol. The engineering workstation compares the physical parameters parsed by the sway system and thrust adjustment system with the original physical parameters of the digital bus analog circuit. If the data frame formats of the two are consistent, the sway system and thrust adjustment system are functioning normally.

5. The testing apparatus as described in claim 1, characterized in that, When testing the engine control system and propellant control system, the hardware configuration of the testing device includes: NI host chassis, model PXIe-1084 host chassis; The processor is a PXIE-8861 processor and also has a Modbus TCP interface; The multiplexer is model CPCI-3722; The analog signal acquisition board is model PXI4302, which is used to acquire the voltage across the equivalent load element.

6. The testing apparatus as described in claim 2, characterized in that, When testing the ground telemetry system, the hardware configuration of the testing device includes: NI host chassis, model PXIe-1084 host chassis; The processor is a PXIE-8861 processor and also has a Modbus TCP interface; The multiplexer is model CPCI-3722; The digital signal analog circuit uses a PXIe-8433 communication card.

7. The testing apparatus as described in claim 3, characterized in that, When testing the measurement system, the hardware configuration of the testing device is as follows: NI host chassis, model PXIe-1084 host chassis; The processor is a PXIE-8861 processor and also has a Modbus TCP interface; The multiplexer is model CPCI-3722; The voltage loop analog circuit uses the analog output board CPCI-3204 and the analog thermocouple board CPCI-4132.

8. The testing apparatus as described in claim 3, characterized in that, When testing the swing system and thrust adjustment system, the hardware configuration of the testing device is as follows: NI host chassis, model PXIe-1084 host chassis; The processor is a PXIE-8861 processor and also has a Modbus TCP interface; The multiplexer is model CPCI-3722; The digital bus analog circuit is a CPCI-2142 communication card, and the data packets meet the 1553B bus communication protocol.

9. A test system for testing a test bench control system, comprising an engineer station and several test devices as described in any one of claims 1-8, wherein the engineer station includes test management software and network switching equipment, the engineer station is connected to one or more test devices through the network switching equipment to form a distributed test network, and the test management software is responsible for test process arrangement, test parameter configuration, test command issuance, real-time data monitoring and collection, and automatic analysis and report generation of test results.

10. A test method for testing a test bench control system: the test device is applied between a real rocket engine-related module and a liquid rocket engine test control system, the liquid rocket engine test control system having multiple subsystems, the multiple subsystems being used to test the real rocket engine-related module; The testing device includes a multiplexer, a simulation module, and a processor. The multiplexer is connected to the simulation module and the processor. The multiplexer and the simulation module interact with the engineering workstation through the processor. The engineering workstation is used to generate the instructions required by the testing device. The simulation module of the testing device is used to simulate multiple subsystems of the liquid rocket engine test and control system. The multiplexer switches the measurement state according to the instructions issued by the engineer station. The measurement state includes normal measurement state and verification measurement state. When the multi-channel switch is switched to the normal measurement state, the actual rocket engine-related modules are directly connected to the corresponding subsystems, realizing the test state of normal connection between the rocket engine-related modules and the corresponding subsystems. When the multiplexer is switched to verification measurement mode, the test device simulates the actual rocket engine-related modules. At this time, the test device is disconnected from the actual rocket engine-related modules, and the simulation module inside the test device is directly connected to the corresponding subsystem. The simulation module simulates the physical parameters of the actual rocket engine-related modules or generates data packets that meet a preset communication protocol. The physical parameters or data packets are input to the corresponding subsystem. The subsystem obtains the received physical parameters or the physical parameters obtained from the data packets parsed by the subsystem. The subsystem compares the physical parameters obtained by the subsystem with the initial physical parameters of the simulation module. The comparison result determines whether the function of the subsystem is normal. The communication protocol of the initial physical parameters of the simulation module is the same as the communication protocol used by the subsystem, which is configured through the test management software.

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