A full-automatic thrust calibration system and method for a rocket engine

Abstract

The application provides a full-automatic rocket engine thrust calibration system and a calibration method, which at least comprises a thrust frame, a standard force providing module, a standard force sensor, a working force sensor, a NI data acquisition machine box system and an OPC server. The thrust frame is used for receiving a standard force and forming a working force; the standard force providing module is connected with a controller, and outputs a required standard force to the thrust frame under the control of the controller; the standard force sensor is installed on the thrust frame, and is used for detecting the standard force output by the standard force providing module and feeding back a detection result to the controller; the working force sensor is installed on the thrust frame, and is used for detecting the working force of the thrust frame; the NI data acquisition machine box system is in communication connection with the working sensor and the controller. The OPC server is installed on the data acquisition machine box system, and is used for realizing bidirectional communication between the data acquisition machine box system and the controller.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of rocket engine, in particular to a full-automatic thrust calibration system and calibration method of rocket engine. BACKGROUND

[0002] The traditional ground test thrust calibration system of liquid rocket engine has low automation degree, and the standard force is usually determined by manual. The process of manual determination is very tedious and the determination result is subjective, which brings uncertainty to the whole thrust calibration system.

[0003] Therefore, it is urgent to provide a thrust calibration system and calibration method which can realize full automation and has high calibration precision. SUMMARY

[0004] To solve the above technical problems, the present application provides a full-automatic thrust calibration system and calibration method of rocket engine, which realizes the full automation of the thrust calibration system, improves the precision and stability of the liquid rocket engine thrust calibration system, further improves the efficiency of the liquid rocket engine thrust calibration system, and saves the manual input of the traditional thrust calibration work.

[0005] In one aspect, the present application provides a full-automatic thrust calibration system of rocket engine, which comprises at least a thrust frame, a standard force providing module, a standard force sensor, a working force sensor, a NI data acquisition machine box system and an OPC server. The thrust frame is used for receiving standard force and forming working force; the standard force providing module is connected with a controller, and outputs the required standard force to the thrust frame under the control of the controller; the standard force sensor is installed on the thrust frame, and is used for detecting the standard force output by the standard force providing module and feeding back the detection result to the controller; the working force sensor is installed on the thrust frame, and is used for detecting the working force of the thrust frame; the NI data acquisition machine box system is in communication connection with the working sensor and the controller; and the OPC server is installed on the data acquisition machine box system.

[0006] After the calibration starts, the controller outputs the standard force signal to the standard force providing module, the standard force providing module applies the standard force to the standard force sensor and transmits it to the thrust frame; the standard force sensor feeds back the detection result to the controller, the controller determines that the standard force reaches and sends the acquisition signal to the NI data acquisition machine box; the NI data acquisition machine box system receives the acquisition signal of the controller through the OPC server, acquires the detection data of the working force sensor, and sends the completion signal to the controller through the OPC server after the acquisition is completed.

[0007] Further, the standard force providing module comprises at least an adjusting mechanism and an executing mechanism; the adjusting mechanism adjusts the size of the standard force under the control of the controller, and drives the executing mechanism to apply the adjusted standard force to the standard force sensor and then to the thrust frame.

[0008] Further, the adjusting mechanism is a servo valve, and the executing mechanism is an oil cylinder; the servo valve adjusts the opening degree under the control of the controller, thereby controlling the oil amount entering the oil cylinder; the oil cylinder pushes the top rod to apply the standard force to the standard force sensor and then to the thrust frame.

[0009] In one embodiment, the NI data acquisition machine box system comprises a Labview thrust calibration module which automatically calculates the calibration formula after collecting data of all the working force sensors.

[0010] In one embodiment, the controller is a PLC.

[0011] In one embodiment, the thrust frame comprises a fixed frame and a movable frame, the movable frame is installed on the fixed frame through a spring plate; the standard force sensor and the working force sensor are installed on the movable frame.

[0012] Another aspect of the present application provides a full-automatic thrust calibration method of a rocket engine, which uses the full-automatic thrust calibration system of the rocket engine in any of the above embodiments to calibrate the thrust, and comprises at least the following steps:

[0013] Step one, the controller PLC pre-sets a plurality of standard force set values;

[0014] Step two, the PLC program is started, and the Labview thrust calibration program in the NI data acquisition machine box system is run simultaneously;

[0015] Step three, the PLC runs the first standard force set value, outputs a signal to the servo valve, controls the oil amount entering the oil cylinder by controlling the opening degree of the servo valve, the oil cylinder pushes the top rod to apply the standard force to the standard force sensor and then to the movable frame, and the standard force sensor feeds back the measured first standard force measurement value to the PLC;

[0016] Step four, after the PLC determines that the first standard force measurement value reaches, the signal of reaching is transmitted to the Labview thrust calibration program in the NI data acquisition machine box system through the OPC server;

[0017] Step five, after the Labview thrust calibration program in the NI data acquisition machine box system receives the signal of reaching, the data acquisition of one working force sensor is completed, and the signal of having collected is sent to the PLC through the OPC server;

[0018] Step six, the PLC receives the "has collected" signal and automatically runs the second standard force set value;

[0019] Step seven, repeat steps three, four, five and six until the PLC runs each standard force set value in turn, and the Labview thrust calibration program collects all working force sensor measurement values and automatically calculates the calibration formula, and the thrust calibration work is completed.

[0020] Further, the PLC program is preset with 0kN, 200kN, 400kN, 500kN, 600kN, 700kN and 800kN seven standard force set values.

[0021] Further, the method for the PLC to determine that the first standard force measurement value "reaches" is that the first standard force measurement value is stable within the set value ±0.2kN range for 15s, and the PLC program can determine that the first standard force measurement value "reaches".

[0022] Further, the PLC runs 0kN, 200kN, 400kN, 500kN, 600kN, 700kN and 800kN seven standard force set values in turn, and after the Labview thrust calibration program completes data collection of the seven working force sensors, the above steps are repeated for two more cycles, until the Labview thrust calibration program completes data collection of the 21 working force sensors, and automatically calculates the calibration formula, and the thrust calibration work is completed.

[0023] The rocket engine full-automatic thrust calibration system and calibration method provided by the application have at least one of the following beneficial effects:

[0024] First, the rocket engine full-automatic thrust calibration system and calibration method solve the deficiencies of the existing system in terms of measurement accuracy and automation degree, and improve the performance and reliability of the calibration system.

[0025] Second, the application innovatively uses OPC technology to realize bidirectional communication between the PLC program and the Labview program, realize automatic adjustment of the calibration parameters and automatic matching of the calibration scheme, greatly improve the calibration efficiency and accuracy, and reduce manual intervention.

[0026] Third, the application realizes full automation of the thrust calibration work, and significantly improves the precision and stability of the liquid rocket engine thrust calibration system compared with manual calibration.

[0027] After reading the detailed description and viewing the drawings, those skilled in the art will recognize additional features and advantages. BRIEF DESCRIPTION OF DRAWINGS

[0028] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed in the embodiments. Obviously, the drawings described below only illustrate some of the embodiments of the present application, and for those skilled in the art, other drawings can also be obtained from these drawings without creative effort.

[0029] Figure 1 is a whole schematic diagram of the full-automatic thrust calibration system of the embodiment of the present application.

[0030] Figure 2 is a structural schematic diagram of the thrust frame part of the embodiment of the present application.

[0031] Figure 3 is a flow chart of the full-automatic thrust calibration method of the present application. DETAILED DESCRIPTION

[0032] The features and exemplary embodiments of various aspects of the present application will be described in detail below, in order to make the purposes, technical solutions and advantages of the present application more clear, the following will further describe the present application in combination with the drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present application, for exemplary illustration of the principles of the present application, and are not configured to limit the present application. In addition, the structural members in the drawings are not necessarily drawn to scale. For example, the size of some structural members in the drawings can be enlarged for other structural members or regions, to help understand the embodiments of the present application.

[0033] The orientation words appearing in the following description are the directions shown in the drawings, and are not limited to the specific structure of the embodiments of the present application. In the description of the present application, it should be noted that, unless otherwise specified, the terms "mounting", "connecting", "connecting" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be directly connected, or indirectly connected through an intermediate medium. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0034] In addition, the terms "including", "containing", "having" or any other variant thereof are intended to cover non-exclusive inclusion, so that the inclusion of a series of element structures or components not only includes those elements, but also includes other elements not explicitly listed or inherent in the structure, component. Without more limitation, the elements defined by the sentence "including" do not exclude the presence of other same elements in the article or device including the elements.

[0035] Spatially relative terms such as "under", "below", "lower", "above", "upper", "higher", and the like, are used for ease of description to explain the positioning of one element relative to a second element. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in addition to the orientation depicted in the figures. For example, if a device described is turned over, elements described as "under" or "below" other elements would then be oriented "upper" or "above" the other elements. Likewise, if devices are turned over, elements described as "on" would then be oriented "off" devices. Thus, the spatially relative terms are intended to encompass all possible orientations of the devices described. Also, terms such as "first", "second", and the like, are used to describe various elements, regions, sections, etc. and are not intended to be limiting. Like terms are to be understood to have a like meaning unless otherwise indicated.

[0036] The present application can be implemented without some of these specific details for the benefit of the skilled person. The following description of embodiments is merely intended to provide a better understanding of the application by showing examples of the application.

[0037] Because the engine model, pipeline and gravity center of the trial vehicle are different, the thrust calibration needs to be done before each ignition hot test. In order to improve the accuracy and stability of the thrust calibration system and reduce the manual participation, the present application provides a full-automatic thrust calibration system for rocket engine, which is used to automatically determine whether the standard force of the liquid rocket engine inclined table thrust calibration system is in place, reduces the manual work and improves the efficiency of the thrust calibration.

[0038] Referring to Figure 1 The present application provides a full-automatic thrust calibration system for rocket engine, which at least includes a controller 1, a thrust frame 2, a standard force providing module 3, a standard force sensor 4, a working force sensor 5, a NI data acquisition machine box system 6 and an OPC server. The controller 1 is in communication connection with the standard force providing module 3, the standard force sensor 4 and the NI data acquisition machine box system 6 respectively, and the NI data acquisition machine box system 6 is in communication connection with the working force sensor 5. It is necessary to point out that the OPC server is installed in the data acquisition machine box system, and the controller 1 and the NI data acquisition machine box system 6 are in bidirectional communication through the OPC server.

[0039] In the embodiment, the standard force sensor 4 and the working force sensor 5 are both installed in the thrust frame 2. The standard force sensor 4 is installed on the side of the thrust frame 2 close to the standard force providing module 3, and the working force sensor 5 is installed on the other side. In the process of thrust calibration, the standard force providing module 3 applies the standard force on the standard force sensor 4, and the standard force sensor 4 transmits the standard force to the thrust frame 2, and the thrust frame 2 acts on the working force sensor 5. Therefore, in order to distinguish the force applied by the standard force providing module 3 and the force acting on the working force sensor 5 by the thrust frame 2, the present application calls the force applied by the standard force providing module 3 as the standard force, and calls the force acting on the working force sensor 5 by the thrust frame 2 as the working force.

[0040] Specifically, when using the full-automatic thrust calibration system of the present application to calibrate thrust, the controller 1 reads the required standard force set value and outputs a standard force signal to the standard force providing module 3, which applies a standard force to the standard force sensor 4 and transmits it to the thrust frame 2, which in turn applies it to the working force sensor 5. The standard force sensor 4 feeds back the detection result to the controller 1, which sends a collection signal to the NI data acquisition chassis system 6 after determining that the standard force has been reached. The NI data acquisition chassis system 6 receives the collection signal from the controller 1 through the OPC server and starts collecting the detection data of the working force sensor 5. After the collection is completed, it sends a completion signal to the controller 1 through the OPC server, and the controller 1 continues to read the next standard force set value and execute after receiving the completion signal. This cycle continues until the NI data acquisition chassis system 6 completes the data collection of all working force sensors 5, automatically calculates the calibration formula, and the thrust calibration work is completed.

[0041] Referring to Figure 1 and Figure 2 In one embodiment, the standard force providing module 3 at least includes an adjusting mechanism and an executing mechanism. The adjusting mechanism adjusts the size of the standard force under the control of the controller and drives the executing mechanism to apply the adjusted standard force to the standard force sensor 4 and then to the thrust frame 2. Among them, the adjusting mechanism can be a servo valve 31, the executing mechanism can be an oil cylinder 32, and the working force sensor 5 is a signal feedback mechanism. Therefore, the controller 1, the servo valve 31, the oil cylinder 32 and the working force sensor 5 together constitute a PID system for a given standard force.

[0042] When using the full-automatic thrust calibration system of the present embodiment to calibrate, the controller 1 reads the preset standard force value in sequence and outputs a signal to the servo valve 31, which controls the opening of the servo valve 31 to control the amount of oil entering the oil cylinder 32. The oil cylinder pushes the top rod 33 to act on the standard force sensor 4 of the thrust frame 2, and the standard force sensor 4 measures the pressure in real time and feeds back the measurement value to the controller 1.

[0043] In the above embodiment, the thrust frame 2 includes a fixed frame 21 and a movable frame 22, the movable frame 22 is installed on the fixed frame 21 through a spring plate 23, and the standard force sensor 4 and the working force sensor 5 are installed on the movable frame 22. Among them, the standard force sensor 4 is installed on one side of the movable frame 22 close to the oil cylinder 32, and the working force sensor 5 is installed on the other side of the movable frame 22. It needs to be particularly pointed out that the standard force is applied to the standard force sensor 4 through the oil cylinder 32 pushing the top rod 33, and then the standard force sensor 4 acts on the movable frame 22. After the movable frame 22 receives the standard force, it forms a working force and acts on the working force sensor 5.

[0044] In order to increase the calibration accuracy and precision, a plurality of working force sensors 5 can be arranged on the movable frame 22, and each working force sensor 5 is uniformly distributed on the movable frame 22, so as to ensure the comprehensiveness of the action force detection data. Specifically, when the NI data acquisition chassis system 6 receives the acquisition signal of the controller 1, the measurement data of each working force sensor 5 is started to be acquired, and after the acquisition is completed, the acquired signal is sent to the controller 1. After the NI data acquisition chassis system 6 acquires each working force measurement data, the average value is calculated and saved, and the average value is used for subsequent calculation of the calibration formula.

[0045] In one embodiment, the NI data acquisition chassis system includes a Labview thrust calibration module (also referred to as a Labview thrust calibration program), and the Labview thrust calibration module communicates with the controller through OPC technology. When the Labview thrust calibration module acquires all the data of the working force sensor, the calibration formula is automatically calculated.

[0046] In the above embodiment, the PLC can be selected as the controller of the system, and the DCS (Distributed Control System), the single-chip microcomputer and the like can be selected as the controller of the system.

[0047] In addition, the standard force sensor and the working force sensor in the embodiment of the application can adopt a new type of sensor with high precision, high sensitivity and temperature compensation function, so as to reduce the influence of environmental factors on the measurement result and improve the measurement precision.

[0048] The above embodiments can be combined with each other, and have corresponding technical effects.

[0049] Referring to Figure 3 The application further provides a full-automatic thrust calibration method of a rocket engine. The thrust calibration is performed by using the full-automatic thrust calibration system of the rocket engine in any one of the above embodiments, and the PLC is selected as the controller. The method at least includes the following steps:

[0050] S10, the controller PLC pre-sets a plurality of standard force set values.

[0051] S20, the PLC program is started, and the Labview thrust calibration program in the NI data acquisition chassis system is run.

[0052] S30, the PLC runs the first standard force set value, outputs a signal to the servo valve, controls the oil amount entering the oil cylinder by controlling the opening degree of the servo valve, the oil cylinder drives the top rod to apply the standard force to the standard force sensor and transmit to the movable frame, and the standard force sensor feeds back the first standard force measurement value measured to the PLC.

[0053] S40, after the PLC determines that the first standard force measurement value "reaches", the "reached" signal is transmitted to the Labview thrust calibration program in the NI data acquisition box system through the OPC server.

[0054] S50, after the Labview thrust calibration program in the NI data acquisition box system receives the "reached" signal, data acquisition of the work force sensor is completed, and the "acquired" signal is sent to the PLC through the OPC server.

[0055] S60, after the PLC receives the "acquired" signal, the second standard force set value is automatically run.

[0056] S70, S30, S40, S50 and S60 are repeated until the PLC runs all the standard force set values in turn, and the Labview thrust calibration program acquires all the measurement values of the work force sensor and automatically calculates the calibration formula, and the thrust calibration work is completed.

[0057] In this embodiment, PLC is selected as the controller of the system. Before the calibration work starts, the PLC program presets seven standard force set values of 0kN, 200kN, 400kN, 500kN, 600kN, 700kN and 800kN. The embodiment of the application can use the oil cylinder to exert the standard force on the movable frame to simulate the thrust of the engine, use the Labview thrust calibration program to acquire the data on the work force sensor, and calculate the new calibration formula.

[0058] Meanwhile, refer to Figure 1 and Figure 2, specifically, the thrust calibration work starts, the PLC program is started, and the Labview thrust calibration program is run. The PLC reads the first standard force set value (0 kN) and outputs a signal to the servo valve 31. The oil amount entering the oil cylinder 32 is controlled by controlling the opening degree of the servo valve 31. The oil cylinder 32 pushes the top rod 33 to act on the standard force sensor 4 of the movable frame 22. The standard force sensor 4 measures the standard force provided by the top rod 33 and feeds back the measurement value (real-time feedback value) to the PLC. When the value of the standard force is stable within the acceptable fluctuation range (±0.2 kN) for 15 s, the PLC program determines that the first standard force measurement value “reaches”, and the “reached” signal is transmitted to the Labview thrust calibration program running in the NI data acquisition chassis system 6 through the OPC server. After receiving the “reached” signal from the PLC, the Labview thrust calibration program running in the NI data acquisition chassis system 6 completes the data acquisition and recording of the working force sensor 5, and sends the “collected” signal to the PLC through the OPC server. After receiving the “collected” signal from the Labview thrust calibration program, the PLC automatically runs the program of the second standard force set value (200 kN). The above steps are repeated until the PLC runs all the standard force set values in sequence, and the Labview thrust calibration program collects all the measurement values of the working force sensor and automatically calculates the calibration formula, and the thrust calibration work ends.

[0059] Further, in order to increase the accuracy and precision of the thrust calibration system, the PLC can be caused to run all the standard force set values repeatedly. For example, the PLC can be caused to run the 0 kN, 200 kN, 400 kN, 500 kN, 600 kN, 700 kN, and 800 kN standard force set values in sequence, and then run all the standard force set values twice, that is, a total of 21 standard force set values. After the Labview thrust calibration module collects the measurement data of the 21 working force sensors, the calibration formula is automatically calculated, and the thrust calibration work ends.

[0060] In the above embodiment, the standard force set value can be adjusted adaptively according to the engine model and working condition.

[0061] The above embodiments can be combined with each other, and have corresponding technical effects.

[0062] The above only describes the preferred embodiments of the present application and is not used to limit the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A fully automated thrust calibration system for a rocket engine, characterized in that, At least including: The thrust frame is used to receive standard forces and generate working forces; A standard force supply module, connected to a controller, outputs the required standard force to the thrust frame under the control of the controller; A standard force sensor, installed on the thrust frame, is used to detect the standard force output by the standard force supply module and feed the detection result back to the controller. A working force sensor is installed on the thrust frame to detect the working force of the thrust frame; The NI data acquisition chassis system is communicatively connected to the force sensor and the controller. An OPC server is installed in the data acquisition chassis system; The LabVIEW thrust calibration program is set in the NI data acquisition chassis system; The controller outputs a standard force signal to the standard force providing module, which applies the standard force to the standard force sensor and transmits it to the thrust frame. The standard force sensor feeds back the detection result to the controller. After determining that the standard force has been "reached," the controller sends a data acquisition signal to the NI data acquisition chassis system. The NI data acquisition chassis system receives the acquisition signal from the controller through the OPC server and acquires the detection data from the working force sensor. After acquisition, it sends a completion signal to the controller through the OPC server. After acquiring data from all working force sensors, the calibration formula is automatically calculated using the LabVIEW thrust calibration program.

2. The fully automatic thrust calibration system for rocket engines according to claim 1, characterized in that, The standard force providing module includes at least an adjustment mechanism and an execution mechanism; the adjustment mechanism adjusts the magnitude of the standard force under the control of the controller, and drives the execution mechanism to apply the adjusted standard force to the standard force sensor and then transmit it to the thrust frame.

3. The fully automatic thrust calibration system for rocket engines according to claim 2, characterized in that, The regulating mechanism is a servo valve, and the actuator is a hydraulic cylinder. The servo valve adjusts its opening under the control of the controller, thereby controlling the amount of oil entering the hydraulic cylinder. The hydraulic cylinder pushes the push rod to apply a standard force to the standard force sensor and transmit it to the thrust frame.

4. The fully automatic thrust calibration system for rocket engines according to claim 3, characterized in that, The controller is a PLC.

5. The fully automatic thrust calibration system for rocket engines according to claim 4, characterized in that, The thrust frame includes a fixed frame and a movable frame, with the movable frame mounted on the fixed frame via a spring plate; the standard force sensor and the working force sensor are mounted on the movable frame.

6. A fully automated thrust calibration method for a rocket engine, characterized in that, Thrust calibration using the fully automated rocket engine thrust calibration system according to any one of claims 1 to 5 includes at least the following steps: Step 1: The PLC controller presets multiple standard force settings; Step 2: Start the PLC program and simultaneously run the LabVIEW thrust calibration program in the NI data acquisition chassis system; Step 3: The PLC runs the first standard force set value and outputs a signal to the servo valve. By controlling the opening of the servo valve, the amount of oil entering the cylinder is controlled. The cylinder pushes the push rod to apply the standard force to the standard force sensor and transmit it to the moving frame. The standard force sensor feeds back the measured value of the first standard force to the PLC. Step 4: After the PLC determines that the first standard force measurement value has been "reached", it transmits the "reached" signal to the LabVIEW thrust calibration program in the NI data acquisition chassis system through the OPC server. Step 5: After receiving the "reached" signal, the LabVIEW thrust calibration program in the NI data acquisition chassis system completes one data acquisition from the working force sensor and sends the "acquired" signal to the PLC through the OPC server. Step 6: After receiving the "acquired" signal, the PLC automatically runs the second standard force setting value; Step 7: Repeat steps 3, 4, 5, and 6 until the PLC has sequentially run all the standard force settings, and the LabVIEW thrust calibration program has collected the measured values ​​of all working force sensors and automatically calculated the calibration formula. The thrust calibration work is then complete.

7. The fully automatic thrust calibration method for rocket engines according to claim 6, characterized in that, The PLC program presets seven standard force settings: 0kN, 200kN, 400kN, 500kN, 600kN, 700kN, and 800kN.

8. The fully automatic thrust calibration method for rocket engines according to claim 7, characterized in that, The method by which the PLC determines that the first standard force measurement value has been "reached" is as follows: if the first standard force measurement value remains stable within the set value ±0.2kN range for 15 seconds, the PLC program determines that the first standard force measurement value has been "reached".

9. The fully automatic thrust calibration method for rocket engines according to claim 8, characterized in that, The PLC sequentially runs seven standard force settings: 0kN, 200kN, 400kN, 500kN, 600kN, 700kN, and 800kN. After the LabVIEW thrust calibration program completes the data acquisition from the seven working force sensors, it repeats the above steps twice more until the LabVIEW thrust calibration program completes the data acquisition from all 21 working force sensors. Then, it automatically calculates the calibration formula, and the thrust calibration work is completed.

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