Signal receiving device and method of rocket engine digital collecting and editing device
By designing the signal receiving device of the digital editor of the rocket engine, the problem of data susceptible to interference and difficult processing during the hot test drive of the rocket engine is solved, and efficient collection and processing of the rocket engine test drive data is achieved, and the accuracy and reliability of the test are improved.
Patent Information
- Application Number
- CN202411843083.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-13
- Publication Date
- 2025-03-21
AI Technical Summary
During the hot test run of the rocket engine, the parameter measurement data is easily disturbed and data processing is difficult, especially because the program operation mode is difficult to convert due to high collection frequency and large data volume.
A signal receiving device for a digital editor of a rocket engine is designed, including a measurement and control transceiver device, a system power supply, a host computer and a console. Through an embedded controller, a serial instrument control module and a C series digital module, the digital signal acquisition and processing of rocket engine test run data is realized, and the data is processed by sampling frequency compression.
It avoids data fluctuations caused by long-distance transmission of simulated quantities, combines data acquisition procedures and fault diagnosis procedures, improves the accuracy and reliability of the rocket engine hot test test, and meets the needs of hot test data collection for large rocket engines.
Smart Images
Figure CN119668170A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to a signal receiving device and method, and in particular to a signal receiving device and method for a rocket engine digital editor. Background Art
[0002] There is a direct connection between the digital data acquisition and editing signal receiving device and the rocket engine. It can obtain the digital signal from the rocket engine end without adding a signal conditioner, realize data collection of important measurement parameters, and cooperate with the front-end FPGA hardware and host computer software to complete parameter collection, fault diagnosis, processing and analysis during the hot test of the rocket engine.
[0003] The parameter measurement of the rocket engine hot test process is mainly carried out by the measurement and control system. The commonly used methods currently include the following steps: 1) Install sensors at the measurement point of the rocket engine; 2) Use multiple single cables to connect the sensors to the measurement adapter cabinet; 3) Use bundled cables to connect the measurement adapter cabinet and the signal conditioner; 4) The signal conditioner conditions, amplifies, and converts the analog signal into a digital signal; 5) The digital signal is input to the acquisition device; 6) Use software at the host computer corresponding to the acquisition device to collect and process data. However, due to the long-distance transmission of analog signals, this method is susceptible to interference.
[0004] The parameter measurement of the rocket engine hot test process can also be carried out by telemetry measurement, which is mainly carried out by the digital acquisition system. The commonly used method flow is: 1) Install sensors at the measuring point of the rocket engine; 2) Install digital acquisition near the load-bearing frame; 3) Transmit digital signals by wired or wireless means; 4) Receive digital signals to the acquisition device; 5) Use software at the host computer corresponding to the acquisition device for data acquisition and processing. In comparison, this method avoids the long-distance transmission of analog quantities, but the data acquisition program and fault diagnosis program of the commonly used telemetry measurement method are run separately, and because the acquisition frequency required for the rocket engine hot test process is extremely high, it is difficult to convert the program segment operation mode after the recorded data volume is too large, and the data processing is difficult. Summary of the invention
[0005] The purpose of the present invention is to solve the problem that the data collected by the parameter measurement device in the existing rocket engine hot test process is easily interfered or difficult to process, and to provide a signal receiving device and method for a rocket engine digital data collector.
[0006] To achieve the above purpose, the technical solution provided by the present invention is:
[0007] A signal receiving device for a rocket engine digital acquisition and editing device, which is special in that:
[0008] It includes a measurement and control transceiver device, and a system power supply, a host computer and a control console electrically connected to the measurement and control transceiver device;
[0009] The measurement and control transceiver device includes an embedded controller, a serial instrument control module and a C series digital module arranged on the embedded controller, and a terminal block connected to the embedded controller; the terminal block is used to connect the rocket engine; the embedded controller is electrically connected to the host computer, and the C series digital module is electrically connected to the host computer and the control console respectively;
[0010] The serial instrument control module is used to receive the digital signal collected by the digital acquisition and editing device, and the C series digital module is used to receive the command signal issued by the console and send it to the host computer; the host computer is used to control the embedded controller to collect the digital signal according to the command signal and process the digital signal;
[0011] The system power supply is used to supply power to the measurement and control transceiver device.
[0012] Furthermore, the output end of the system power supply is connected to the power supply interface on the embedded controller and the serial instrument control module, and the output voltage of the system power supply is 28V.
[0013] Furthermore, the embedded controller is provided with eight CompactRIO controller slots for inserting external modules, the serial instrument control module and the C series digital module are respectively connected to two of the CompactRIO controller slots, and the remaining CompactRIO controller slots are reserved.
[0014] Further, the embedded controller is a fanless embedded controller of model cRIO-9035;
[0015] The embedded controller is provided with an RS232 serial reserved port, an RS485 serial reserved port, an RJ45 Gigabit Ethernet interface and a DC power interface, wherein the RS232 serial reserved port and the RS485 serial reserved port are reserved ports, the RJ45 Gigabit Ethernet interface is used to connect to a host computer, and the DC power interface is used to connect to a system power supply.
[0016] Furthermore, the model of the serial instrument control module is NI9871.
[0017] Furthermore, the model of the C series digital module is NI9401.
[0018] At the same time, the present invention also provides a signal receiving method of a rocket engine digital acquisition device, which is based on the signal receiving device of the rocket engine digital acquisition device, and its special feature is that it includes the following steps:
[0019] Step 1: Send a command signal to the C series digital module through the console, and the C series digital module sends the command to the host computer. The host computer controls the embedded controller to start collecting digital signals of rocket engine test data through the serial instrument control module;
[0020] Step 2: The embedded controller sends the collected digital signal to the host computer, which processes the digital signal and determines whether it is abnormal. If the data is abnormal, it stops receiving the signal; if the data is not abnormal, it executes step 3;
[0021] Step 3: After a preset time, obtain the first result data;
[0022] Step 4: The host computer processes the first result data and compresses its sampling frequency to obtain the second result data;
[0023] Step 5: The host computer uses the second result data to draw a test data chart of the rocket engine to complete signal reception.
[0024] Further, in step 3, the first result data is a binary file m stored in a matrix form, wherein each element of the matrix represents a rocket engine test parameter variable, each row of the matrix represents a sampling data, and all rocket engine test parameter variables are stored using the same variable type.
[0025] Furthermore, in step 3, the variable types include integer, single-precision floating point and double-precision floating point.
[0026] Further, in step 4.1, the file size S of the first result data binary file m is obtained, in bytes;
[0027] Step 4.2, calculate N = S / sizeof (a ij ), where N is the number of rows in the matrix of the binary file m, a ij is the element of the matrix, i represents the row of the matrix, j represents the column of the matrix; sizeof(a ij ) is a function to obtain the size of each matrix element variable type, and the unit of its return value is Byte;
[0028] Step 4.3, set a for loop to select the data of the binary file m, the selection rules are 1) select the kth row, 2) select every Z-1 rows downward; the number of executions of the for loop is X, X = N / Z, k is the preset number of selected rows;
[0029] Step 4.4: Delete the unselected rows in the binary file m, complete the compression of the binary file m, and obtain the second result data.
[0030] Compared with the prior art, the present invention has the following beneficial effects:
[0031] 1. The signal receiving device of the rocket engine digital acquisition and editing device provided by the present invention adopts a universal, miniaturized, lightweight and integrated design concept. By building the rocket engine digital acquisition and editing device system signal receiving hardware and host computer software, it realizes the measurement parameter data collection, key parameter fault diagnosis and post-test data processing during the rocket engine test process, avoiding the use of analog long-distance transmission for test data collection of conventional measurement and control systems, and does not need to be subjected to analog-to-digital conversion, amplification and other operations through a signal conditioner. Digital quantity information is directly transmitted through a telemetry cable, avoiding data fluctuations caused by long-distance transmission of analog signals;
[0032] 2. The signal receiving device of the rocket engine digital data acquisition device provided by the present invention combines the data acquisition program and fault diagnosis program of the previous rocket engine hot test telemetry acquisition system into one software for display and processing. After the test, the data recording frequency can be adjusted to output large data volume files, thereby comprehensively improving the accuracy and reliability of the rocket engine hot test test and meeting the current needs for hot test data collection of large rocket engines.
[0033] 3. The signal receiving method of the rocket engine digital sampler provided by the present invention converts the source file collected at a high frequency into a low-frequency text document through the sampling frequency compression method when processing data, so as to accurately obtain data that meets the needs of subsequent analysis, avoid data redundancy, and reduce the amount of data processing. BRIEF DESCRIPTION OF THE DRAWINGS
[0034] Figure 1 It is a schematic diagram of the composition of an embodiment of a signal receiving device of a rocket engine digital acquisition and editing device of the present invention;
[0035] Figure 2 This is a schematic diagram of the interface of the embedded controller in the embodiment of the signal receiving device of the rocket engine digital acquisition and editing device of the present invention;
[0036] Figure 3 It is a schematic diagram of the composition of the embedded controller in the embodiment of the signal receiving device of the rocket engine digital acquisition and editing device of the present invention;
[0037] Figure 4 This is a schematic diagram of the connection between the C series digital module and the host computer in the embodiment of the signal receiving device of the rocket engine digital acquisition and editing device of the present invention;
[0038] Description of reference numerals:
[0039] 1. Measurement and control transceiver; 2. System power supply; 3. Host computer; 4. Control console; 11. Embedded controller; 111. Serial instrument control module; 112. C series digital module; 6. CompactRIO controller slot; 7. RS232 serial reserved port; 8. RS485 serial reserved port; 9. RJ45 Gigabit Ethernet interface; 10. DC power interface. DETAILED DESCRIPTION
[0040] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.
[0041] A signal receiving device for a rocket engine digital acquisition and editing device, characterized in that:
[0042] It includes a measurement and control transceiver device 1, and a system power supply 2, a host computer 3 and a control console 4 electrically connected to the measurement and control transceiver device 1;
[0043] The measurement, control and transceiver device 1 includes an embedded controller 11, a serial instrument control module 111 and a C series digital module 112 arranged on the embedded controller 11, and a terminal block 12 connected to the embedded controller 11; the terminal block 12 is used to connect the rocket engine; the embedded controller 11 is electrically connected to the host computer 3, and the C series digital module 112 is electrically connected to the host computer 3 and the console 4 respectively; the serial instrument control module 111 is used to receive the digital signal collected by the digital acquisition device, and the C series digital module 112 is used to receive the command signal issued by the console 4; the system power supply 2 is used to power the measurement, control and transceiver device 1.
[0044] The output end of the system power supply 2 is connected to the power supply interface on the embedded controller 11 and the serial instrument control module 111 , and the output voltage of the system power supply 2 is 28V.
[0045] The embedded controller 11 is provided with eight CompactRIO controller slots 6 for inserting external modules, and the serial instrument control module 111 and the C series digital module 112 are arranged on two of the CompactRIO controller slots 6, and the remaining CompactRIO controller slots 6 are reserved. The CompactRIO controller slots 6 can also be inserted with external modules, and the external modules are equipped with FPGA and installed with the NI Linux Real-Time operating system. The embedded controller 11 is also provided with an RS232 serial reserved port 7, an RS485 serial reserved port 8, an RJ45 Gigabit Ethernet interface 9, a DC power interface 10 and other interfaces. The RJ45 Gigabit Ethernet interface is used for data communication with the host computer 3. The maximum load voltage of the DC power interface 10 is 30V.
[0046] In this embodiment, the embedded controller 11 is a fanless embedded controller of model cRIO-9035.
[0047] The serial instrument control module 111 is NI 9871. NI 9871 supports standard start bit, stop bit, and handshake settings. The interface uses an external power supply and can provide the highest compatibility and reliability under various serial port conditions.
[0048] The model of the C series digital module 112 is NI9401, and the C series digital module 112 is electrically connected to the host computer 3. The serial port set thereon can be directly accessed through the FPGA, so as to flexibly communicate with the serial device. Each port of the module is equipped with an independent buffer, which can save FPGA space and simplify programming. The C series digital module 112 is connected to the console 4 through a DB25 connector.
[0049] Based on the above device, this embodiment also provides a signal receiving method of a rocket engine digital acquisition and editing device, comprising the following steps:
[0050] Step 1: Send a command signal to the C series digital module 112 through the console 4, and the C series digital module 112 sends the command to the host computer 3. The host computer 3 controls the embedded controller 11 to start collecting digital signals of rocket engine test data through the serial instrument control module 111; the software used in the host computer 3 is Labview, and the digital signal receiving sampling frequency of this embodiment is 500Hz;
[0051] Step 2, the embedded controller 11 sends the collected digital signal to the host computer 3, the host computer 3 processes the digital signal and determines whether it is abnormal. If the data is abnormal, it stops receiving the signal; if the data is not abnormal, execute step 3;
[0052] Step 3, after a preset time, obtain the first result data; wherein the first result data is a binary file m stored in a matrix form, wherein each element of the matrix represents a rocket engine test parameter variable, each row of the matrix represents a sampling data, and all rocket engine test parameter variables are stored using the same variable type; wherein the variable types include integer, single-precision floating point and double-precision floating point;
[0053] Step 4: The host computer 3 processes the first result data and obtains the second result data after compressing its sampling frequency; the specific processing process is:
[0054] Step 4.1, obtaining the file size S of the first result data binary file m, in bytes;
[0055] Step 4.2, calculate N = S / sizeof (aij ), where N is the number of rows in the matrix of the binary file m, a ij is the element of the matrix, i represents the row of the matrix, j represents the column of the matrix; sizeof(a ij ) is a function to obtain the size of each matrix element variable type, and the unit of its return value is Byte;
[0056] Step 4.3, set a for loop to select the data of the binary file m, the selection rules are 1) select the kth row, 2) select every Z-1 row downward; the number of executions of the for loop is X, X=N / Z, k is the preset number of selected rows; in this embodiment, k is 1, and Z is 500;
[0057] Step 4.4, deleting the unselected rows in the binary file m, completing the compression of the binary file m, and obtaining the second result data;
[0058] Step 5: The host computer 3 draws a test data chart of the rocket engine using the second result data to complete signal reception.
[0059] It should be noted that. When processing hot test telemetry data, the problem of too high hardware acquisition frequency is often faced. For example, the file generated by a sampling frequency of 500Hz will result in a huge amount of data. The data processing software operation flow of this embodiment focuses on converting this high-frequency acquisition source file into a low-frequency text document file, specifically converting the 500Hz acquisition source file into a 1Hz text document file. After executing step 4, the compression of the sampling frequency from 500Hz to 1Hz is completed. Data that meets the needs of subsequent analysis can be accurately obtained, avoiding data redundancy and reducing the amount of data processing.
Claims
1. A signal receiving device for a rocket engine digital acquisition and editing device, characterized in that: It comprises a measurement and control transceiver device (1), and a system power supply (2), a host computer (3) and a control console (4) electrically connected to the measurement and control transceiver device (1); The measurement and control transceiver device (1) comprises an embedded controller (11), a serial instrument control module (111) and a C series digital module (112) arranged on the embedded controller (11), and a terminal block (12) connected to the embedded controller (11); the terminal block (12) is used to connect a rocket engine; the embedded controller (11) is electrically connected to a host computer (3), and the C series digital module (112) is electrically connected to the host computer (3) and a control console (4) respectively; The serial instrument control module (111) is used to receive digital signals collected by the digital acquisition and editing device, and the C series digital module (112) is used to receive the command signal issued by the control console (4) and send it to the host computer (3); the host computer (3) is used to control the embedded controller (11) to collect the digital signal according to the command signal, and process the digital signal; The system power supply (2) is used to supply power to the measurement, control and transceiver device (1).
2. The signal receiving device of the rocket engine digital acquisition and editing device according to claim 1 is characterized in that: The output end of the system power supply (2) is connected to the power supply interface on the embedded controller (11) and the serial instrument control module (111), and the output voltage of the system power supply (2) is 28V.
3. The signal receiving device of the rocket engine digital acquisition and editing device according to claim 2 is characterized in that: The embedded controller (11) is provided with eight CompactRIO controller slots (6) for inserting external modules, the serial instrument control module (111) and the C series digital module (112) are respectively connected to two of the CompactRIO controller slots (6), and the remaining CompactRIO controller slots (6) are in a reserved state.
4. The signal receiving device of the rocket engine digital acquisition and editing device according to claim 3 is characterized in that: The embedded controller (11) is a fanless embedded controller of model cRIO-9035; The embedded controller (11) is provided with an RS232 serial reserved port (7), an RS485 serial reserved port (8), an RJ45 Gigabit Ethernet interface (9) and a direct current power interface (10), wherein the RS232 serial reserved port (7) and the RS485 serial reserved port (8) are reserved ports, the RJ45 Gigabit Ethernet interface (9) is used for connecting to a host computer (3), and the direct current power interface (10) is used for connecting to a system power supply (2).
5. The signal receiving device of the rocket engine digital acquisition and editing device according to claim 4 is characterized in that: The model of the serial instrument control module (111) is NI9871.
6. The signal receiving device of the rocket engine digital acquisition and editing device according to claim 5 is characterized in that: The model of the C series digital module (112) is NI9401.
7. A signal receiving method for a rocket engine digital acquisition device, based on the signal receiving device for a rocket engine digital acquisition device according to any one of claims 1 to 6, characterized in that: The following steps are involved: Step 1: Sending a command signal to the C series digital module (112) through the control console (4), the C series digital module (112) sends the command to the host computer (3), and the host computer (3) controls the embedded controller (11) to start collecting digital signals of rocket engine test data through the serial instrument control module (111); Step 2, the embedded controller (11) sends the collected digital signal to the host computer (3), the host computer (3) processes the digital signal and determines whether it is abnormal. If the data is abnormal, it stops receiving the signal; if the data is not abnormal, it executes step 3; Step 3: After a preset time, obtain the first result data; Step 4, the host computer (3) processes the first result data and compresses its sampling frequency to obtain the second result data; Step 5: The host computer (3) uses the second result data to draw a test data chart of the rocket engine, thereby completing signal reception.
8. The signal receiving method of the rocket engine digital acquisition and editing device according to claim 7 is characterized in that: In step 3, the first result data is a binary file m stored in matrix form, wherein each element of the matrix represents a rocket engine test parameter variable, each row of the matrix represents a sampling data, and all rocket engine test parameter variables are stored using the same variable type.
9. The signal receiving method of the rocket engine digital acquisition and editing device according to claim 8 is characterized in that: In step 3, the variable types include integer, single-precision floating point and double-precision floating point.
10. The signal receiving method of the rocket engine digital acquisition and editing device according to claim 9 is characterized in that: Step 4 is as follows: Step 4.1, obtaining the file size S of the first result data binary file m, in bytes; Step 4.2, calculate N = S / sizeof (a ij ), where N is the number of rows in the matrix of the binary file m, a ij is the element of the matrix, i represents the row of the matrix, j represents the column of the matrix; sizeof(a ij ) is a function to obtain the size of each matrix element variable type, and the unit of its return value is Byte; Step 4.3, set a for loop to select the data of the binary file m, the selection rules are 1) select the kth row, 2) select every Z-1 rows downward; the number of executions of the for loop is X, X = N / Z, k is the preset number of selected rows; Step 4.4: Delete the unselected rows in the binary file m, complete the compression of the binary file m, and obtain the second result data.