Full-automatic thrust calibration system of rocket engine

Abstract

The utility model provides a full-automatic thrust calibration system for a rocket engine. The full-automatic thrust calibration system at least comprises a controller, a thrust frame, a standard force providing module, a standard force sensor, a working force sensor and an NI data acquisition case system, the thrust frame is used for receiving standard force and forming working force; the standard force providing module is connected with the controller and outputs required standard force to the thrust frame under the control of the controller; the standard force sensor is installed on the thrust frame and used for measuring the standard force output by the standard force providing module and feeding back the measurement result to the controller. The working force sensor is mounted on the thrust frame and is used for measuring the working force of the thrust frame; and the NI data acquisition case system is in communication connection with the working force sensor and the controller and is used for receiving an acquisition signal of the controller and sending the acquired signal to the controller after acquiring measurement data of the working force sensor.

Description

TECHNICAL FIELD

[0001] The utility model relates to space launch vehicle technical field especially relates to a rocket engine full automatic thrust calibration system. BACKGROUND

[0002] The traditional liquid rocket engine ground test thrust calibration system is not high in automation degree, and the standard force is usually determined manually. The manual determination process is very tedious and the determination result is subjective and arbitrary, which brings certain uncertainty to the whole thrust calibration system.

[0003] Therefore, it is urgent to provide a thrust calibration system capable of realizing full automation and high calibration precision. UTILITY MODEL CONTENT

[0004] To solve the above technical problems, the utility model provides a rocket engine full automatic thrust calibration system, which realizes full automation of thrust calibration work and improves the precision and stability of the liquid rocket engine thrust calibration system.

[0005] The utility model provides a rocket engine full automatic thrust calibration system at least includes: controller, thrust frame, standard force providing module, standard force sensor, working force sensor and NI data acquisition machine box system, thrust frame is used for receiving standard force and forms working force, standard force providing module is connected with the controller, under the control of the controller, the required standard force is given to the thrust frame, standard force sensor is installed in the thrust frame, is used for measuring the standard force that the standard force providing module exports, and the measurement result is fed back to the controller, working force sensor is installed in the thrust frame, is used for measuring the working force of the thrust frame, NI data acquisition machine box system is connected with the working force sensor and the controller communication, is used for receiving the acquisition signal of the controller, and after gathering the measured data of the working force sensor, the gathered signal is sent to the controller.

[0006] In an embodiment, the standard force providing module includes at least an adjusting mechanism and an execution mechanism; the adjusting mechanism adjusts the size of the standard force under the control of the controller, and drives the execution mechanism to transmit the adjusted standard force to the thrust frame after acting on the standard force sensor.

[0007] In an embodiment, the adjusting mechanism is a servo valve, and the execution mechanism is an oil cylinder; the servo valve adjusts the opening under the control of the controller, thereby controlling the oil amount entering the oil cylinder, and the oil cylinder pushes the standard force to act on the standard force sensor and transmit to the thrust frame.

[0008] In one embodiment, the NI data acquisition chassis system comprises a Labview thrust calibration module, which automatically calculates a calibration formula after collecting all data of the working force sensor.

[0009] In one embodiment, the controller is a PLC.

[0010] In one embodiment, the controller is a single-chip microcomputer or a DCS distributed control system.

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

[0013] In one embodiment, the PLC is set to run all standard force set values three times in a cycle, and the Labview thrust calibration module collects measurement data of 21 working force sensors.

[0014] In any one of the above embodiments, the standard force sensor and the working force sensor are selected from the same type and specification of sensors.

[0015] In one embodiment, the movable frame is uniformly distributed with a plurality of working force sensors.

[0016] The rocket engine full-automatic thrust calibration system and calibration method provided by the utility model have at least one of the following beneficial effects:

[0017] Firstly, 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.

[0018] Secondly, the utility model innovatively uses the OPC technology to realize the bidirectional communication between the PLC program and the Labview program, realizes the automatic adjustment of the calibration parameters and the automatic matching of the calibration scheme, and greatly improves the calibration efficiency and accuracy.

[0019] Thirdly, the utility model realizes the full automation of the thrust calibration work, significantly improves the precision and stability of the liquid rocket engine thrust calibration system compared with manual calibration, and also reduces the labor input.

[0020] After reading the specific embodiments and viewing the drawings, those skilled in the art will realize additional features and advantages. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical solutions of the embodiments of the present application or the prior art, the drawings needed in the embodiments will be briefly introduced as follows. Obviously, the drawings in the following description only constitute some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained without creative labor on the basis of these drawings.

[0022] Figure 1 is a whole schematic diagram of the full-automatic thrust calibration system of the embodiment of the present application.

[0023] Figure 2 is a structural schematic diagram of the thrust frame part of the embodiment of the present application. DETAILED DESCRIPTION

[0024] In order to make the purpose, technical solutions and advantages of the present application more clear, the features and exemplary embodiments of each aspect of the present application will be described in detail below. It should be understood that the specific embodiments described herein are only configured to explain the present application, for exemplary description 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.

[0025] 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.

[0026] 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 members which are not explicitly listed or inherent to the structure, component. Without more limitation, the elements defined by the statement "including" do not exclude the presence of other same elements in the article or device including the elements.

[0027] Spatially relative terms such as "under", "below", "lower", "above", "upper", "on", "over", "side", and the like, are used for ease of description to explain the positioning of one element relative to a second element. The terms are intended to encompass different orientations of the device in addition to the orientation depicted in the figures. For example, "above" can encompass both orientations where the element is above the second element and where the element is below the second element. Similarly, "on" can encompass both orientations where the element is on the second element and where the element is on the second element. Moreover, the terms "first", "second", and the like, are used herein not only to designate one element from another, but also to designate one of multiple elements. Like terms are used to designate like elements throughout the description.

[0028] The utility model can be implemented by those skilled in the art without some of these specific details. The following description of the embodiments is only to provide a better understanding of the utility model by showing examples of the utility model.

[0029] Because the engine model of the test vehicle is different, the pipeline and the gravity center are different, so the thrust calibration needs to be done before each ignition heat test. In order to improve the accuracy and stability of the thrust calibration system and reduce the manual participation, the utility model provides a full-automatic thrust calibration system of a rocket engine for automatically determining whether the standard force of the liquid rocket engine inclined platform thrust calibration system is in place, reducing manual operation and improving the efficiency of thrust calibration.

[0030] Referring to Figure 1 The full-automatic thrust calibration system of the rocket engine 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 and a NI data acquisition machine box system 6. 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 needs to be explained that the controller 1 is in bidirectional communication with the NI data acquisition machine box system 6.

[0031] In the embodiment, the standard force sensor 4 and the working force sensor 5 are both installed on the thrust frame 2. The standard force sensor 4 is installed on one 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 utility model 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.

[0032] Specifically, when the full-automatic thrust calibration system is used for thrust calibration, the controller 1 reads the required standard force set value, and outputs a standard force signal to the standard force providing module 3, the standard force providing module 3 applies the standard force to the standard force sensor 4 and transmits to the thrust frame 2, and then the thrust frame 2 acts on the working force sensor 5. The standard force sensor 4 feeds back the detection result to the controller 1, and the controller 1 sends a collection signal to the NI data acquisition machine box system 6 after determining that the standard force reaches, the NI data acquisition machine box system 6 collects the detection data of the working force sensor 5 after receiving the collection signal, and sends a completion signal to the controller 1 after the collection is completed, and the controller 1 continues to read the next standard force set value and executes after receiving the completion signal. This cycle continues until the NI data acquisition machine box system 6 completes the data collection of all working force sensors 5, automatically calculates the calibration formula, and the thrust calibration work is completed.

[0033] Meanwhile refer 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 act on the standard force sensor 4 after adjusting the standard force, and then transmits 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 given standard force PID system.

[0034] When the full-automatic thrust calibration system of the embodiment is used for calibration, the controller 1 reads in turn according to the preset standard force preset value, and outputs a signal to the servo valve 31, and controls the oil entering the oil cylinder 32 by controlling the opening of the servo valve 31. 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.

[0035] 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 the 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 by the oil cylinder 32 pushing the top rod 33, and then the standard force sensor 4 acts on the movable frame 22, and the movable frame 22 forms a working force after receiving the standard force and acts on the working force sensor 5.

[0036] 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, it starts to acquire the measurement data of each working force sensor 5, and sends the acquired signal to the controller 1 after the acquisition is completed. After the NI data acquisition chassis system 6 acquires the working force measurement data, the average value is calculated and saved, which is used for subsequent calculation of the calibration formula.

[0037] In the above embodiment, in order to distinguish the force applied by the push rod and the force received by the movable frame, the force applied by the push rod is referred to as the standard force, and the force applied by the movable frame on the working force sensor is referred to as the working force.

[0038] In one embodiment, the NI data acquisition chassis system includes a Labview thrust calibration module (also referred to as a Labview thrust calibration program), which communicates with the controller through OPC technology. When the Labview thrust calibration module acquires all the data of the working force sensor, it automatically calculates the calibration formula.

[0039] In the above embodiment, PLC can be selected as the controller of the system, or DCS (Distributed Control System), single-chip microcomputer, etc. can be selected as the controller of the system.

[0040] In one 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 oil cylinder is used to apply standard force on the movable frame to simulate the thrust of the engine, and the Labview thrust calibration program is used to acquire the data on the working force sensor to calculate a new calibration formula.

[0041] Meanwhile, refer to Figure 1 and Figure 2, specifically, the thrust calibration work starts, starts the PLC program, and runs the Labview thrust calibration program at the same time. The PLC reads the first standard force set value and outputs a signal to the servo valve 31. The oil quantity 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 (±0.2kN) for 15s, the PLC program determines that the first standard force measurement value “reaches”, and transmits the “reached” signal to the Labview thrust calibration program running on the NI data acquisition machine box system 6 through OPC technology. After receiving the “reached” signal from the PLC, the Labview thrust calibration program running on the NI data acquisition machine box system 6 completes the data acquisition and recording of the working force sensor 5, and sends the “collected” signal to the PLC through OPC. After receiving the “collected” signal from the Labview thrust calibration program, the PLC automatically runs the program of the next standard force set value. 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 is completed.

[0042] Further, in order to increase the accuracy and precision of the thrust calibration system, the PLC can be made to run all the standard force set values repeatedly. For example, the PLC can be made to run the 0kN, 200kN, 400kN, 500kN, 600kN, 700kN, and 800kN seven standard force set values in sequence, and then repeat the above steps to run all the standard force set values twice, that is, a total of 21 standard force set value programs. 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 is completed.

[0043] In the above embodiment, the standard force set value can be adjusted adaptively according to the engine model and working condition.

[0044] The above embodiments can be combined with each other, and have corresponding technical effects.

[0045] The rocket engine full-automatic thrust calibration system of the utility model adopts PLC as the controller of the system, and realizes communication with the Labview program through OPC technology, completes the full automation of the thrust calibration work, not only improves the precision and stability of the liquid rocket engine thrust calibration system, but also further improves the efficiency of the liquid rocket engine thrust calibration system work, saves the artificial investment of the traditional thrust calibration work.

[0046] The above merely describes preferred embodiments of the present application and is not intended to limit the present application, and 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 by, At least comprising: a thrust frame for receiving a standard force and forming a working force; a standard force providing module connected with a controller, outputting a required standard force to the thrust frame under the control of the controller; a standard force sensor installed on the thrust frame for measuring the standard force output by the standard force providing module and feeding back the measurement result to the controller; a working force sensor installed on the thrust frame for measuring the working force of the thrust frame; a NI data acquisition machine box system in communication connection with the working force sensor and the controller for receiving the acquisition signal of the controller and sending the acquired signal to the controller after acquiring the measurement data of the working force sensor.

2. The fully automated thrust calibration system for a rocket engine of claim 1, wherein, The standard force providing module at least comprises 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 transmit the adjusted standard force to the thrust frame after the adjusted standard force acts on the standard force sensor.

3. The fully automated thrust calibration system for a rocket engine of claim 2, wherein, 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 and then controls the oil amount entering the oil cylinder, and the oil cylinder pushes the top rod to make the standard force act on the standard force sensor and be transmitted to the thrust frame.

4. The fully automated thrust calibration system for a rocket engine of claim 3, wherein, The NI data acquisition machine box system comprises a Labview thrust calibration module which automatically calculates the calibration formula after acquiring all the data of the working force sensor.

5. The fully automated thrust calibration system for a rocket engine of claim 4, wherein, The controller is a PLC.

6. The fully automated thrust calibration system for a rocket engine of claim 4, wherein, The controller is a single-chip microcomputer or a DCS distributed control system.

7. The fully automated thrust calibration system for a rocket engine of claim 5, wherein, The thrust frame comprises a fixed frame and a movable frame, and 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.

8. The fully automated thrust calibration system for a rocket engine of claim 7, wherein, Multiple working force sensors are evenly distributed on the movable frame.

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