A control method and system for a launch vehicle engine boost system

Abstract

The present application discloses a control method and system for a booster system of a launch vehicle engine, wherein the control method includes the following steps: collecting pressure data; making a rational judgment on the collected pressure data; if the rational judgment is passed, making a validity judgment on the pressure data; making a comprehensive calculation on the pressure data according to the validity judgment result and the rational judgment result; judging whether the result after the comprehensive calculation is valid; if the result after the comprehensive calculation is valid, performing a closed boost control; if the result after the comprehensive calculation is invalid, performing a boost valve opening and closing control according to a preset valve action sequence. The present application also makes a reasonable threshold judgment and data fusion on the data of redundant sensors, and when one sensor fails, it can ensure the correctness of the boost calculation and the correct opening and closing of the boost valve. Under extreme conditions, the boost system can be guaranteed to work within the normal range by fixing the boost timing. Thereby improving the reliability of the boost control system of the launch vehicle.

Description

Technical Field

[0001] The present application relates to the field of rockets, and in particular, to a control method and system for a launch vehicle engine boosting system. Background Art

[0002] At present, when the booster system of the launch vehicle acquires input data, a single sensor or multiple sensors are used to take the average value. For the single sensor mode: the collected sensor data is calculated, and then the closed boost control is performed according to the calculation result (when the pressure value is lower than the lower line, the boost valve is opened, and when it is higher than the upper line, the boost valve is closed); for the multiple sensor mode: multiple sensor data are collected, and then the average value of multiple sensor values ​​is calculated, and then the closed boost control is performed according to the calculation result, which improves the control reliability compared with the single sensor. When the booster system of the launch vehicle acquires input data, for the single sensor mode: when the sensor works normally, the closed boost control can be performed normally; when the sensor is abnormal, the correctness of the data cannot be judged due to the lack of other comparison sensors, resulting in incorrect calculation results and abnormal boost control. For the multiple sensor mode: when a single sensor is abnormal, when multiple sensor values ​​are calculated, the error of a single sensor will be transmitted to the averaged result, affecting the accuracy of boost control. For example, when the abnormal value deviation of a single sensor is large, it may also cause abnormal boost control. At the same time, under extremely harsh conditions, when all sensors fail, the entire boost system will not work properly.

[0003] Therefore, how to provide a method for completing boost control under normal operating conditions or when a sensor is abnormal has become an urgent problem to be solved in the art. Summary of the invention

[0004] The present application proposes a control method for a launch vehicle engine boost system, comprising the following steps: collecting pressure data; conducting a rationality judgment on the collected pressure data to determine whether it passes; if the rationality judgment passes, conducting a validity judgment on the pressure data; performing a comprehensive calculation on the pressure data based on the validity judgment result and the rationality judgment result; determining whether the result after the comprehensive calculation is valid; if the result after the comprehensive calculation is valid, performing closed boost control; if the result after the comprehensive calculation is invalid, performing a boost valve opening and closing control according to a preset valve action sequence.

[0005] In the control method of the boost system of a launch vehicle engine as described above, three pressure sensors are used to simultaneously collect pressure data.

[0006] In the control method of the boost system of a launch vehicle engine as described above, the rationality judgment of the collected pressure data includes judging whether the pressure data collected by each pressure sensor is within the measuring range of the sensor; if it is within the measuring range, it is considered that the rationality judgment of the pressure data has passed; if it is not within the measuring range, it is considered that the rationality judgment of the pressure data has failed.

[0007] In the control method of the boost system of a launch vehicle engine as described above, the pressure data of the path that fails the rationality judgment is set as invalid data, and after completing the rationality judgment, the three paths of pressure data are comprehensively calculated.

[0008] In the control method of the launch vehicle engine boost system as described above, the validity judgment of the pressure data includes judging whether the number of valid data in the pressure data collected by each sensor is greater than 5; if it is greater than 5, performing least square filtering on the pressure data; if it is less than 5, setting the pressure data to invalid data.

[0009] A control system for a carrier rocket engine boosting system, specifically comprising: an acquisition unit, a rationality judgment unit, an effectiveness judgment unit, a comprehensive calculation unit, a result judgment unit, a closed boost control unit and a boost valve opening and closing control unit; the acquisition unit is used to acquire pressure data; the rationality judgment unit is used to perform rationality judgment on the acquired pressure data to determine whether it passes; if the rationality judgment passes, the effectiveness judgment unit performs effectiveness judgment on the pressure data; the comprehensive calculation unit is used to perform comprehensive calculation on the pressure data according to the effectiveness judgment result and the rationality judgment result; the result judgment unit is used to determine whether the result after comprehensive calculation is valid; if the result after comprehensive calculation is valid, the closed boost control unit performs closed boost control; if the result after comprehensive calculation is invalid, the boost valve opening and closing control unit performs boost valve opening and closing control according to a preset valve action sequence.

[0010] In the control system of the launch vehicle engine boosting system as described above, the acquisition unit uses three pressure sensors to simultaneously acquire pressure data.

[0011] In the control system of the launch vehicle engine boosting system as described above, the rationality judgment unit performs rationality judgment on the collected pressure data, including judging whether the pressure data collected by each pressure sensor is within the measuring range of the sensor; if it is within the measuring range, it is considered that the rationality judgment of the pressure data has passed; if it is not within the measuring range, it is considered that the rationality judgment of the pressure data has failed.

[0012] In the control system of the launch vehicle engine boosting system as described above, the rationality judgment unit sets the pressure data that fails the rationality judgment as invalid data, and the comprehensive calculation unit performs comprehensive calculation on the three pressure data after completing the rationality judgment.

[0013] In the control system of the launch vehicle engine boosting system as described above, the validity judgment unit judges the validity of the pressure data, including judging whether the number of valid data in the pressure data collected by each sensor is greater than 5; if it is greater than 5, performing least square filtering on the pressure data; if it is less than 5, setting the pressure data of this channel as invalid data.

[0014] This application has the following beneficial effects:

[0015] The control method of the booster system of the launch vehicle engine proposed in this application can simultaneously perform reasonable threshold judgment and data fusion on the data of redundant sensors. When one of the sensors fails, the correctness of the boost calculation and the correct opening and closing of the boost valve can be guaranteed. Under extreme conditions, the boost timing can be fixed to ensure that the booster system still works within the normal range. Thereby improving the reliability of the booster control system of the launch vehicle. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0017] Figure 1 is a flow chart of a control method for a launch vehicle engine boost system provided in accordance with an embodiment of the present application;

[0018] Figure 2 It is a schematic diagram of the internal structure of the control system of the launch vehicle engine boost system provided according to the embodiment of the present application. DETAILED DESCRIPTION

[0019] The following is a clear and complete description of the technical solutions in the embodiments of the present application in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present application.

[0020] The present application proposes a control method and system for a booster system of a launch vehicle engine. By judging the rationality of the collected 3-way pressure sensor data, judging the number of valid data, and performing a least squares filtering operation, the error and fluctuation of the measurement data can be reduced, and finally the median of the 3-way filtered data is taken as the calculation result. When the calculation result is valid, closed boost control is performed. When the calculation result is invalid, the boost valve opening and closing control is performed according to the preset valve action sequence. This ensures that the pressure value of the booster system of the launch vehicle is kept within the normal working range.

[0021] Embodiment 1

[0022] like Figure 1 As shown, a control method for a booster system of a launch vehicle engine is specifically provided, which includes the following steps:

[0023] Step S110: collecting pressure data.

[0024] Three pressure sensors are used to collect pressure data simultaneously.

[0025] Step S120: Perform rationality judgment on the collected pressure data to determine whether it passes.

[0026] The rationality judgment includes judging whether the pressure data collected from the three channels are within the sensor range.

[0027] If the pressure data collected by the sensor is within the sensor range, it is considered that the rationality judgment is passed, and step S130 is executed. Otherwise, the pressure data collected by the sensor is set as invalid data. After being set as invalid data, step S140 is executed.

[0028] For example, if the front-end range of the digital sensor is 0-1Mpa, and the pressure data value obtained is greater than 1Mpa, or the pressure data value is less than 0Mpa, the pressure data collected by the sensor is not within the sensor range, and it is considered that the rationality judgment has not passed, and the pressure data is set as invalid data. If the pressure data value obtained is between 0 and 1Mpa, it is considered that the pressure data rationality judgment has passed.

[0029] Step S130: determining the validity of the pressure data.

[0030] The effectiveness of the pressure data collected by each sensor is judged.

[0031] Specifically, it is determined whether the number of valid data in the pressure data collected by each sensor is greater than 5. If the number of valid data in the pressure data collected by the sensor is greater than 5, the pressure data is least square filtered to reduce the error and fluctuation of the measurement data.

[0032] If the number of valid data in the pressure data collected by the sensor is less than 5, the pressure data of this channel is set as invalid data.

[0033] Through the above method, the validity of the pressure data collected by each sensor can be judged, so as to determine whether the pressure data collected by each sensor is invalid data or data that needs to be filtered, and the pressure data after least squares filtering and / or the pressure data set as invalid data can be comprehensively calculated.

[0034] Step S140: Comprehensively calculate the pressure data according to the effectiveness judgment result and the rationality judgment result.

[0035] After the validity determination of each channel of pressure data is completed, the corresponding invalid pressure data or the pressure data after filtering operation of each channel is integrated, and the middle value is taken as the result of the comprehensive calculation.

[0036] For example, the value of the pressure data collected by the first sensor after the least squares filtering operation is 1, the value of the pressure data collected by the second sensor after the least squares filtering operation is 2, and the value of the pressure data collected by the third sensor after the least squares filtering operation is 3, then 2 is the middle value as the result of the comprehensive calculation.

[0037] Step S150: Determine whether the result of the comprehensive calculation is valid.

[0038] If the comprehensive calculation result is not equal to -1, the result is considered valid, and step S160 is executed. If the comprehensive calculation result is equal to -1, the result is considered invalid, and step S170 is executed.

[0039] Step S160: Perform closed-loop supercharging control.

[0040] The closed boost control is as follows: when the pressure value is lower than the lower line, the boost valve is opened; when the pressure value is higher than the upper line, the boost valve is closed.

[0041] Step S170: performing opening and closing control of the boost valve according to the preset valve action sequence.

[0042] The preset valve action sequence is to open or close the valve at multiple fixed time points.

[0043] Embodiment 2

[0044] like Figure 2 As shown, this embodiment provides a control system for a carrier rocket engine boosting system, which specifically includes: a collection unit 210, a rationality judgment unit 220, a validity judgment unit 230, a comprehensive calculation unit 240, a result judgment unit 250, a closed boosting control unit 260 and a boosting valve opening and closing control unit 270.

[0045] The acquisition unit 210 is used to acquire pressure data.

[0046] Three pressure sensors are used to collect pressure data simultaneously.

[0047] The rationality determination unit 220 is used to perform rationality determination on the collected pressure data to determine whether it passes.

[0048] The rationality judgment includes judging whether the pressure data collected from the three channels are within the sensor range.

[0049] If the pressure data collected by the sensor is within the sensor range, it is considered that the rationality judgment is passed, and the validity judgment unit 230 is executed. Otherwise, the pressure data collected by the sensor is set as invalid data.

[0050] The validity determination unit 230 is used to perform validity determination on the pressure data.

[0051] The effectiveness of the pressure data collected by each sensor is judged.

[0052] Specifically, it is determined whether the number of valid data in the pressure data collected by each sensor is greater than 5. If the number of valid data in the pressure data collected by the sensor is greater than 5, the pressure data is least square filtered to reduce the error and fluctuation of the measurement data.

[0053] If the number of valid data in the pressure data collected by the sensor is less than 5, the pressure data of this channel is set as invalid data.

[0054] Through the above method, the validity judgment of the pressure data collected by each sensor can be completed, so as to determine whether the pressure data collected by the unrecorded sensor is invalid data or data that needs to be filtered.

[0055] The comprehensive calculation unit 240 is used to perform comprehensive calculation on the pressure data.

[0056] After the validity determination of each channel of pressure data is completed, the corresponding invalid pressure data or the pressure data after filtering operation of each channel is integrated, and the middle value is taken as the result of the comprehensive calculation.

[0057] For example, the value of the pressure data collected by the first sensor after the least squares filtering operation is 1, the value of the pressure data collected by the second sensor after the least squares filtering operation is 2, and the value of the pressure data collected by the third sensor after the least squares filtering operation is 3, then 2 is the middle value as the result of the comprehensive calculation.

[0058] The result judging unit 250 is used to judge whether the result after comprehensive calculation is valid.

[0059] If the comprehensive calculation result is not equal to -1, the result is considered valid, and the closed boost control unit 260 is executed. If the comprehensive calculation result is equal to -1, the result is considered invalid, and the boost valve opening and closing control unit 270 is executed.

[0060] The closed-loop supercharging control unit 260 is used to perform closed-loop supercharging control.

[0061] The closed boost control is as follows: when the pressure value is lower than the lower line, the boost valve is opened; when the pressure value is higher than the upper line, the boost valve is closed.

[0062] The boost valve opening and closing control unit 270 is used to control the opening and closing of the boost valve according to a preset valve action sequence.

[0063] The preset valve action sequence is to open or close the valve at multiple fixed time points.

[0064] This application has the following beneficial effects:

[0065] The control method of the booster system of the launch vehicle engine proposed in this application can simultaneously perform reasonable threshold judgment and data fusion on the data of redundant sensors. When one of the sensors fails, the correctness of the boost calculation and the correct opening and closing of the boost valve can be guaranteed. Under extreme conditions, the boost timing can be fixed to ensure that the booster system still works within the normal range. Thereby improving the reliability of the booster control system of the launch vehicle.

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

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

Claims

1. A control method for a launch vehicle engine boost system, characterized in that: The following steps are involved: Collect pressure data; Conduct rationality judgment on the collected pressure data to determine whether it passes; If the rationality judgment is passed, the effectiveness judgment of the pressure data is carried out; Comprehensively calculate the pressure data based on the effectiveness judgment results and rationality judgment results; Determine whether the result after comprehensive calculation is valid; If the result after comprehensive calculation is valid, closed boost control is performed; If the result after comprehensive calculation is invalid, the boost valve opening and closing control is performed according to the preset valve action sequence.

2. The control method of the launch vehicle engine boost system according to claim 1, characterized in that: Use 3-way pressure sensors to collect pressure data simultaneously.

3. The control method of the launch vehicle engine boost system according to claim 2, characterized in that: The rationality judgment of the collected pressure data includes judging whether the pressure data collected by each pressure sensor is within the measuring range of the sensor; If it is within the measuring range, it is considered that the pressure data has passed the rationality judgment; If it is not within the measuring range, it is considered that the rationality judgment of the pressure data has failed.

4. The control method of the launch vehicle engine boost system according to claim 3, characterized in that: The pressure data that fails the rationality judgment is set as invalid data. After completing the rationality judgment, the 3-way pressure data are comprehensively calculated.

5. The control method of the launch vehicle engine boost system according to claim 1, characterized in that: The validity determination of the pressure data includes determining whether the number of valid data in the pressure data collected by each sensor is greater than 5; If it is greater than 5, the least squares filtering is performed on the pressure data of the route; If it is less than 5, the pressure data of this line will be set as invalid data.

6. A control system for a launch vehicle engine boost system, characterized in that: Specifically include: A collection unit, a rationality judgment unit, a validity judgment unit, a comprehensive calculation unit, a result judgment unit, a closed boost control unit, and a boost valve opening and closing control unit; A collection unit, used for collecting pressure data; A rationality judgment unit is used to judge the rationality of the collected pressure data and determine whether it passes; If the rationality judgment is passed, the validity judgment unit will judge the validity of the pressure data; A comprehensive calculation unit, used for comprehensively calculating the pressure data according to the effectiveness judgment result and the rationality judgment result; A result judgment unit, used to judge whether the result after comprehensive calculation is valid; If the result after comprehensive calculation is valid, the closed-type supercharging control unit performs closed-type supercharging control; If the result after comprehensive calculation is invalid, the boost valve opening and closing control unit performs the boost valve opening and closing control according to the preset valve action sequence.

7. The control system of the launch vehicle engine boost system according to claim 6, characterized in that: The acquisition unit uses 3-way pressure sensors to simultaneously collect pressure data.

8. The control system of the launch vehicle engine boost system according to claim 7, characterized in that: The rationality determination unit determines the rationality of the collected pressure data, including determining whether the pressure data collected by each pressure sensor is within the range of the sensor; If it is within the measuring range, it is considered that the pressure data has passed the rationality judgment; If it is not within the measuring range, it is considered that the rationality judgment of the pressure data has failed.

9. The control system of the launch vehicle engine boost system according to claim 8, characterized in that: The rationality judgment unit sets the pressure data of the channel that fails the rationality judgment as invalid data. After completing the rationality judgment, the comprehensive calculation unit performs comprehensive calculation on the 3-channel pressure data.

10. The control system of the launch vehicle engine boost system according to claim 1, characterized in that: The validity determination unit determines the validity of the pressure data, including determining whether the number of valid data in the pressure data collected by each sensor is greater than 5; If it is greater than 5, the least squares filtering is performed on the pressure data of the route; If it is less than 5, the pressure data of this line will be set as invalid data.

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