Liquid rocket engine adjustment calculation method and device based on XML parsing and storage

Abstract

The application discloses a liquid rocket engine adjustment calculation method based on XML analysis and storage, and specifically comprises the following steps: step 1, collecting engine information and engine component data required for adjustment calculation; step 2, selecting an XML file corresponding to the type of the engine for adjustment calculation; step 3, obtaining an adjustment calculation configuration file; step 4, storing engine information, a calculation target value, external parameters, engine component data, a calculation initial value, a result and a parameter envelope value element into the XML file; step 5, analyzing the XML file obtained in step 4 to obtain an adjustment calculation solving initial value; step 6, obtaining a calculation result of the calculation target value, the external parameters and the solving initial value; step 7, storing the calculation result obtained in step 6 into the XML file obtained in step 4; and step 8, judging whether the data is within a data envelope range. The method solves the problems of complicated data processing and incompatible formats in the prior art, and improves calculation efficiency and accuracy.

Description

Technical Field

[0001] This invention belongs to the field of liquid rocket engine overall system adjustment calculation technology, specifically involving a liquid rocket engine adjustment calculation method based on XML parsing and storage, and also involving a liquid rocket engine adjustment calculation device based on XML parsing and storage. Background Technology

[0002] As a crucial component of space launch vehicles, the performance and reliability of liquid rocket engines directly determine the success or failure of launch missions. During the design, production, and maintenance of liquid rocket engines, adjustments and calculations are performed to ensure the engine's performance meets the requirements of the space launch vehicle. The accuracy of these calculations directly impacts engine performance and is an indispensable step before the liquid rocket engine is put into use.

[0003] Adjustment calculations typically involve large amounts of complex data and information, making data and information storage and management a major challenge. Currently, liquid rocket engine adjustment calculation systems mostly employ self-developed software or mathematical calculation software. Self-developed software stores data in TXT files, while mathematical calculation software writes data into the calculation code in array form. This results in poor readability and scalability of the calculated data, a lack of flexibility, and makes it difficult for researchers to quickly and accurately identify the engine parameters represented by the data. A significant amount of time is spent checking the accuracy of input data during adjustment calculations and result verification, leading to low computational efficiency. These problems not only increase the complexity of the calculations but may also lead to decreased calculation accuracy and even affect the final performance of the engine. Traditional, inefficient liquid rocket engine adjustment calculation methods are ill-suited to the demands of large-scale production and delivery of liquid rocket engines for frequent space launches. Traditional adjustment calculation devices are limited by data parsing and storage methods, resulting in complex operation, poor user experience, and difficulty in quickly mastering their use.

[0004] In conclusion, developing an adjustment calculation method and device capable of efficiently parsing and storing complex data and information is of great significance for improving the research and development efficiency of liquid rocket engines. Summary of the Invention

[0005] The first objective of this invention is to provide a liquid rocket engine adjustment calculation method based on XML data parsing, which solves the problems of cumbersome data processing and incompatible formats in the prior art, and improves calculation efficiency and accuracy.

[0006] A second objective of this invention is to provide a liquid rocket engine adjustment calculation device based on XML data parsing.

[0007] The first technical solution adopted in this invention is a liquid rocket engine adjustment calculation method based on XML parsing and storage, which includes the following steps:

[0008] Step 1: Collect and adjust the engine information and engine component data required for the calculation;

[0009] Step 2: Select and adjust the XML file corresponding to the calculated engine type;

[0010] Step 3: Obtain the adjustment calculation configuration file;

[0011] Step 4: Store the engine information, calculated target value, external parameters, engine component data, initial calculation value and result, and parameter envelope value elements into an XML file;

[0012] Step 5: Parse the XML file obtained in Step 4 to obtain the initial values ​​for adjustment and calculation;

[0013] Step 6: Obtain the calculation results of the target value, external parameters, and initial values;

[0014] Step 7: Store the calculation results obtained in Step 6 into the XML file obtained in Step 4;

[0015] Step 8: Determine if the data is within the data envelopment range.

[0016] The invention is further characterized in that:

[0017] In step 1, engine data and information required for adjustment calculations are collected by consulting engine matching lists and test reports;

[0018] Engine data includes test results of engine components and structural parameters. Engine information includes the model and code of the engine, as well as the component serial number and test date.

[0019] In step 2, the corresponding XML file is selected from the preset XML file library according to the engine model;

[0020] The selected XML file format is " "For different types of rocket engines, there are corresponding XML files. It is necessary to select the XML file that matches the target engine type to ensure the correctness of parsing and storage operations."

[0021] The XML file contains elements such as "engine information", "calculated target value", "external parameter", "engine component data", "calculated initial value and result", and "parameter envelope value".

[0022] in:

[0023] "Engine Information" includes "Engine Model", "Engine Code", and "Component Information"; among which, "Component Information" includes "Component Serial Number" and "Test Date";

[0024] The “target value calculation” includes “operating conditions” and “mixing ratio”;

[0025] "External parameters" include "oxidizer and fuel inlet temperature", "oxidizer and fuel inlet pressure", and "ambient pressure".

[0026] "Engine component data" includes "generator", "thrust chamber", "turbo pump", and "valve actuator"; among which, "generator" includes "injector flow resistance coefficient"; "thrust chamber" includes "injector flow resistance coefficient" and "thrust chamber throat diameter"; "turbo pump" includes "pump characteristics", "turbine characteristics", and "turbine flow area".

[0027] The "Initial values ​​and results" include "flow parameters", "pressure parameters", "temperature parameters", "power parameters" and "efficiency parameters".

[0028] The “Parameter Envelope Value” includes “Input Envelope” and “Result Envelope”. The “Input Envelope” includes “Pump Head Envelope”, “Pump Efficiency Envelope”, and “Turbine Efficiency Envelope”. The “Result Envelope” includes “Operating Condition”, “Mix Ratio”, “Turbine Pump Speed”, “Generator Chamber Pressure”, “Thrust Chamber Pressure”, and “Throttling Element Parameters”.

[0029] Step 3 specifically involves using LINQ to XML technology to parse the XML file selected in Step 2, thereby obtaining the specified elements, sub-elements, and attributes in the XML file, and using the parsed XML file as the adjustment calculation configuration file.

[0030] In step 4, LINQ to XML technology is used to modify the specified elements, sub-elements and attributes in the XML file so that the "engine information" and "engine component data" in the XML file are consistent with the engine information and engine component data collected in step 1. In addition, according to the overall requirements of rocket propulsion, the target values ​​of the calculation conditions and mixture ratio in the XML file are adjusted to be consistent with the requirements of the overall rocket propulsion conditions and mixture ratio.

[0031] The modified engine information and engine component data will be stored in " "In the format file, the XML file may be the same file as or a different file from the XML file in step 2."

[0032] In step 5, the "Initial values ​​and results" element in the XML file obtained in step 4 is parsed using LINQ to XML technology. The calculation results of the previous engine adjustment contained in the XML file are used as the initial values ​​required for this adjustment calculation.

[0033] In step 7, the specified elements, sub-elements, and attributes in the XML file are modified using LINQ to XML technology, so that the "initial values ​​and results" in the XML file obtained in step 4 are consistent with the calculation results described in step 6.

[0034] Step 8 specifically involves parsing the "parameter envelope value" in the XML file using LINQ to XML technology, and determining whether the "pump characteristics", "turbine characteristics" data and the calculation results obtained in step 6 are within the historical data envelope range.

[0035] The judgment criteria are as follows:

[0036] The judgment is made based on the display of curves showing "Oxidizer Pump Head", "Oxidizer Pump Power", "Fuel Pump Head", "Fuel Pump Power", and "Turbine Efficiency" according to the "Pump Characteristics" and "Turbine Characteristics" data. Specifically:

[0037] If all curves are displayed completely, the "pump characteristics" and "turbine characteristics" data in the XML file are determined to be within the historical data network range; if any curve is not displayed completely, the "pump characteristics" and "turbine characteristics" data in the XML file are determined to be outside the historical data network range.

[0038] The second technical solution adopted in this invention is a liquid rocket engine adjustment calculation device based on XML parsing and storage, implemented using the above method, specifically including:

[0039] The interface module is used to display the parsed XML data and information on the interface, and to edit the XML elements that need to be modified in the interface;

[0040] The XML file manipulation module completes the parsing and storage of the XML file;

[0041] The mathematical model module constructs a mathematical model of the liquid rocket engine based on its type, adjustment calculation theory, and extracted data.

[0042] The solution module stores the equation-solving algorithms and performs calculations based on the engine target performance, initial values, and input parameters.

[0043] The analysis module determines whether the calculation results are within the historical data envelopment range and displays the analysis results in tabular form, highlighting cases where the analysis results exceed the envelopment.

[0044] The beneficial effects of this invention are:

[0045] (1) Efficient data parsing and storage: The method of the present invention stores and parses parameter data in XML format, which significantly improves the efficiency and flexibility of data processing.

[0046] (2) Dynamic adjustment capability: The method of the present invention supports dynamic updating and real-time adjustment of parameters to adapt to complex calculation needs.

[0047] (3) High-precision calculation: The method of the present invention is based on the adjustment calculation of the structured data model, which improves the calculation accuracy and reliability.

[0048] (4) Good scalability: The scalability of the XML method of the present invention enables the device to adapt to the adjustment calculation requirements of different types of liquid rocket engines.

[0049] (5) The method of the present invention utilizes the good scalability and flexibility of XML to store the complex liquid rocket engine data relationship in a tree structure. During the adjustment calculation process, the XML file is dynamically parsed and updated in real time to solve the problems of cumbersome data processing and incompatible formats in the prior art, thereby improving the calculation efficiency and accuracy.

[0050] (5) The method of the present invention has good practicality and can provide strong support for the design and optimization of liquid rocket engines.

[0051] (7) Visual output: The visual report generated by the device of the present invention facilitates engineers to quickly analyze and optimize engine performance. Attached Figure Description

[0052] Figure 1 This is a schematic diagram of the method flow of this invention application;

[0053] Figure 2 This is a schematic diagram of the XML file structure for an example.

[0054] Figure 3 This is a schematic diagram of the device structure according to the present invention application;

[0055] Figure 4 This is an example diagram of an XML file from an embodiment of the present invention;

[0056] Figure 5 Example diagram of the configuration interface for an embodiment of the present invention;

[0057] Figure 6 This is a characteristic curve of the oxidant pump head in Embodiment 1 of the present invention;

[0058] Figure 7 This is a characteristic curve of the oxidant pump power in Embodiment 1 of the present invention;

[0059] Figure 8 This is a characteristic curve of the fuel pump head in Embodiment 1 of the present invention;

[0060] Figure 9 This is a characteristic curve of the fuel pump power in Embodiment 1 of the present invention.

[0061] Figure 10 This is a characteristic curve of turbine efficiency in Embodiment 1 of the present invention. Detailed Implementation

[0062] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments.

[0063] This invention provides a liquid rocket engine adjustment calculation method based on XML parsing and storage. The flowchart of this method is shown below. Figure 1 It includes the following steps:

[0064] Step 1: Collect and adjust the engine information and engine component data required for the calculation;

[0065] In step 1, engine data and information required for adjustment calculations are collected by consulting engine matching lists and test reports;

[0066] Engine data includes test results of engine components and structural parameters. Engine information includes the model and code of the engine, as well as the component serial number and test date.

[0067] Step 2: Select and adjust the XML file corresponding to the calculated engine type;

[0068] In step 2, based on the engine model, the corresponding XML file is selected from a pre-defined XML file library. The structured nature of XML files allows data and information to be stored in a tree structure, facilitating parsing and access. The collected data and information can be stored in different XML nodes.

[0069] The selected XML file format is " "For different types of rocket engines, there are corresponding XML files. It is necessary to select the XML file that matches the target engine type to ensure the correctness of parsing and storage operations."

[0070] XML file structure as follows Figure 2 As shown, the XML file contains elements such as "engine information", "calculated target value", "external parameters", "engine component data", "calculated initial value and result", and "parameter envelope value".

[0071] in:

[0072] "Engine Information" includes "Engine Model", "Engine Code", and "Component Information"; among which, "Component Information" includes "Component Serial Number" and "Test Date";

[0073] The “target value calculation” includes “operating conditions” and “mixing ratio”;

[0074] "External parameters" include "oxidizer and fuel inlet temperature", "oxidizer and fuel inlet pressure", and "ambient pressure".

[0075] "Engine component data" includes "generator", "thrust chamber", "turbo pump", and "valve actuator"; among which, "generator" includes "injector flow resistance coefficient"; "thrust chamber" includes "injector flow resistance coefficient" and "thrust chamber throat diameter"; "turbo pump" includes "pump characteristics", "turbine characteristics", and "turbine flow area".

[0076] The "Initial values ​​and results" include "flow parameters", "pressure parameters", "temperature parameters", "power parameters" and "efficiency parameters".

[0077] The “Parameter Envelope Value” includes “Input Envelope” and “Result Envelope”. The “Input Envelope” includes “Pump Head Envelope”, “Pump Efficiency Envelope”, and “Turbine Efficiency Envelope”. The “Result Envelope” includes “Operating Condition”, “Mix Ratio”, “Turbine Pump Speed”, “Generator Chamber Pressure”, “Thrust Chamber Pressure”, and “Throttling Element Parameters”.

[0078] Step 3: Obtain the adjustment calculation configuration file;

[0079] Step 3 specifically involves using LINQ to XML technology to parse the XML file selected in Step 2, thereby obtaining the specified elements, sub-elements, and attributes in the XML file, and using the parsed XML file as the adjustment calculation configuration file.

[0080] Step 4: Store the engine information, calculated target value, external parameters, engine component data, initial calculation value and result, and parameter envelope value elements into an XML file;

[0081] In step 4, LINQ to XML technology is used to modify the specified elements, sub-elements and attributes in the XML file so that the "engine information" and "engine component data" in the XML file are consistent with the engine information and engine component data collected in step 1. In addition, according to the overall requirements of rocket propulsion, the target values ​​of the calculation conditions and mixture ratio in the XML file are adjusted to be consistent with the requirements of the overall rocket propulsion conditions and mixture ratio.

[0082] The modified engine information and engine component data will be stored in " "In the format file, the XML file may be the same file as or a different file from the XML file in step 2."

[0083] Step 5: Parse the XML file obtained in Step 4 to obtain the initial values ​​for adjustment and calculation;

[0084] In step 5, the "Initial values ​​and results" element in the XML file obtained in step 4 is parsed using LINQ to XML technology. The calculation results of the previous engine adjustment contained in the XML file are used as the initial values ​​required for this adjustment calculation.

[0085] Step 6: Substitute the calculated target value, external parameters, and initial values ​​obtained in Step 5 into the engine mathematical model to perform calculations and obtain the calculation results;

[0086] Step 7: Store the calculation results obtained in Step 6 into the XML file obtained in Step 4;

[0087] In step 7, the specified elements, sub-elements, and attributes in the XML file are modified using LINQ to XML technology, so that the "initial values ​​and results" in the XML file obtained in step 4 are consistent with the calculation results described in step 6.

[0088] Step 8: Determine if the data is within the data envelopment range.

[0089] Step 8 specifically involves parsing the "parameter envelope value" in the XML file using LINQ to XML technology, and determining whether the "pump characteristics", "turbine characteristics" data and the calculation results obtained in step 6 are within the historical data envelope range.

[0090] The judgment criteria are as follows:

[0091] The judgment is made based on the display of curves showing "Oxidizer Pump Head", "Oxidizer Pump Power", "Fuel Pump Head", "Fuel Pump Power", and "Turbine Efficiency" according to the "Pump Characteristics" and "Turbine Characteristics" data. Specifically:

[0092] If all curves are displayed completely, the "pump characteristics" and "turbine characteristics" data in the XML file are determined to be within the historical data network range; if any curve is not displayed completely, the "pump characteristics" and "turbine characteristics" data in the XML file are determined to be outside the historical data network range.

[0093] This invention also provides a liquid rocket engine adjustment calculation device based on XML parsing and storage. A schematic diagram of the device is shown below. Figure 3 ,include:

[0094] The interface module is used to display the parsed XML data and information on the interface, and to edit the XML elements that need to be modified in the interface;

[0095] The XML file manipulation module completes the parsing and storage of the XML file;

[0096] The mathematical model module constructs a mathematical model of the liquid rocket engine based on its type, adjustment calculation theory, and extracted data.

[0097] The solution module stores the equation-solving algorithms and performs calculations based on the engine target performance, initial values, and input parameters.

[0098] The analysis module determines whether the calculation results are within the historical data envelopment range and displays the analysis results in tabular form, highlighting cases where the analysis results exceed the envelopment.

[0099] Example 1

[0100] Taking the adjustment calculation of a certain gas generator cycle engine as an example, the engine is a multi-thrust pump-driven engine. The main components of the engine include an oxidizer pump, a fuel pump, a gas generator, and four thrust chambers. One turbopump supplies propellant to the four thrust chambers.

[0101] The liquid rocket engine adjustment calculation method based on XML parsing and storage includes the following steps:

[0102] Step 1: Collect and adjust the engine data and information required for the calculation;

[0103] In step 1, engine data and information required for adjustment calculations are collected by consulting engine matching lists and test reports;

[0104] The engine data includes test results of engine components and structural parameters. The engine information includes the model and code of the engine, as well as the component serial numbers and test dates of the oxidizer pump, fuel pump, gas generator, and four thrust chambers.

[0105] Step 2: Select and adjust the XML file corresponding to the engine type; the structured nature of XML files allows data and information to be stored in a tree structure, which is convenient for parsing and access.

[0106] The XML file structure selected in this embodiment is as follows: Figure 4 As shown, the XML file contains nodes for "Engine Information", "Calculated Target Values", "External Parameters", "Engine Component Data", "Initial Calculation Values ​​and Results", and "Parameter Envelope Values".

[0107] Figure 4 The "Engine Information" node in the XML file can be seen, which includes the engine model, code, and component serial numbers and test dates of the oxidizer pump, fuel pump, gas generator, and four thrust chambers;

[0108] Figure 4The “Calculate Target Value” node in the XML file shows that the operating condition value is “100%” and the mixing ratio value is “1.95”.

[0109] Figure 4 The “External Parameters” node in the XML file shows that the oxidant inlet temperature is 288.15K, the fuel inlet temperature is 288.15K, the oxidant inlet pressure is 0.471MPa, the fuel inlet pressure is 0.284MPa, and the ambient pressure is 0.101325MPa.

[0110] Figure 4 The XML file contains nodes for "Engine Component Data", "Initial Calculation Values ​​and Results", and "Parameter Envelope Values". Due to the large number of attributes in these nodes, they will not be described in detail here.

[0111] Step 3: Obtain the adjustment calculation configuration file;

[0112] Step 3 specifically involves using LINQ to XML technology to parse the XML file selected in Step 2, thereby obtaining the specified elements, sub-elements, and attributes in the XML file, and using the parsed XML file as the adjustment calculation configuration file.

[0113] Step 4: Store engine data, calculated target values, and engine component data in an XML file;

[0114] In step 4, LINQ to XML technology is used to modify the specified elements, sub-elements and attributes in the XML file so that the "engine data" and "engine information" in the XML file are consistent with the engine data and engine information collected in step 1. In addition, according to the overall requirements of rocket propulsion, the target values ​​of the calculation conditions and mixture ratio in the XML file are adjusted to be consistent with the requirements of the overall rocket propulsion.

[0115] Figure 5 This is the configuration interface for this embodiment. In this embodiment, the elements, sub-elements, and attributes obtained after parsing the XML file are displayed in the configuration interface, and changes can be made in the configuration interface. The configuration interface of this embodiment displays the "engine data", "engine information", and "calculated target value" information of the XML file.

[0116] The modified engine information and engine component data will be stored in " "In the format file, the XML file may be the same file as or a different file from the XML file in step 2."

[0117] Step 5: Parse the XML file obtained in Step 4 to obtain the initial values ​​for adjustment and calculation;

[0118] In step 5, the "Initial values ​​and results" element in the XML file obtained in step 4 is parsed using LINQ to XML technology. The calculation results of the previous engine adjustment contained in the XML file are used as the initial values ​​required for this adjustment calculation.

[0119] Step 6: Substitute the calculated target value, external parameters, and initial values ​​obtained in Step 5 into the engine mathematical model for calculation to obtain the calculation results. Some of the calculation results in this embodiment are shown in Table 1.

[0120] Table 1

[0121]

[0122] Step 7: Store the calculation results obtained in Step 6 into the XML file obtained in Step 4;

[0123] In step 7, the specified elements, sub-elements, and attributes in the XML file are modified using LINQ to XML technology, so that the "initial values ​​and results" in the XML file obtained in step 4 are consistent with the calculation results described in step 6.

[0124] Step 8: Determine if the data is within the data envelopment range.

[0125] Step 8 specifically involves parsing the "parameter envelope value" in the XML file using LINQ to XML technology, and determining whether the "pump characteristics", "turbine characteristics" data and the calculation results obtained in step 6 are within the historical data envelope range.

[0126] Figures 6 to 10 The curves of "oxidizer pump head", "oxidizer pump power", "fuel pump head", "fuel pump power", and "turbine efficiency" plotted based on the "pump characteristics" and "turbine characteristics" data of this embodiment are derived from... Figures 6 to 10 As can be seen, all curves are displayed completely, indicating that the "pump characteristics" and "turbine characteristics" data in the XML file are within the input envelope range.

[0127] The envelope analysis of the calculation results in this embodiment is shown in Table 2. In the calculation results of this embodiment, the operating condition, mixture ratio, turbopump speed, generator chamber pressure, thrust chamber pressure, oxidizer cavitation A coefficient, and fuel cavitation A coefficient are all between their respective lower and upper envelope limits. Therefore, "Envelope" is displayed in the analysis results column. The oxidizer cavitation margin in the calculation results is 0.3294, and the fuel cavitation margin is 0.3796, which exceed their respective upper envelope limits. Therefore, "Exceeding Upper Envelope" is displayed in the analysis results columns for oxidizer cavitation margin and fuel cavitation margin, and is highlighted.

[0128] Table 2

[0129]

[0130] The method of this invention utilizes the excellent scalability and flexibility of XML to store complex liquid rocket engine data relationships in a tree structure. During the adjustment calculation process, the XML file is dynamically parsed and updated in real time to solve the problems of cumbersome data processing and incompatible formats in the prior art, thereby improving calculation efficiency and accuracy.

[0131] Example 2

[0132] A liquid rocket engine adjustment calculation method based on XML parsing and storage includes the following steps:

[0133] Step 1: Collect the required engine information and engine component data;

[0134] Step 2: Select and adjust the XML file corresponding to the calculated engine type;

[0135] Step 3: Obtain the adjustment calculation configuration file;

[0136] Step 4: Store the engine information, calculated target value, external parameters, engine component data, initial calculation value and result, and parameter envelope value elements into an XML file;

[0137] Step 5: Parse the XML file obtained in Step 4 to obtain the initial values ​​for adjustment and calculation;

[0138] Step 6: Obtain the calculation results of the target value, external parameters, and initial values;

[0139] Step 7: Store the calculation results obtained in Step 6 into the XML file obtained in Step 4;

[0140] Step 8: Determine if the data is within the data envelopment range.

[0141] Example 3

[0142] A liquid rocket engine adjustment calculation method based on XML parsing and storage includes the following steps:

[0143] Step 1: Collect the required engine information and engine component data;

[0144] In step 1, engine data and information required for adjustment calculations are collected by consulting engine matching lists and test reports;

[0145] Engine data includes test results of engine components and structural parameters. Engine information includes the model and code of the engine, as well as the component serial number and test date.

[0146] Step 2: Select and adjust the XML file corresponding to the calculated engine type;

[0147] Step 3: Obtain the adjustment calculation configuration file;

[0148] Step 4: Store the engine information, calculated target value, external parameters, engine component data, initial calculation value and result, and parameter envelope value elements into an XML file;

[0149] Step 5: Parse the XML file obtained in Step 4 to obtain the initial values ​​for adjustment and calculation;

[0150] Step 6: Obtain the calculation results of the target value, external parameters, and initial values;

[0151] Step 7: Store the calculation results obtained in Step 6 into the XML file obtained in Step 4;

[0152] Step 8: Determine if the data is within the data envelopment range.

[0153] Example 4

[0154] A liquid rocket engine adjustment calculation method based on XML parsing and storage includes the following steps:

[0155] Step 1: Collect the required engine information and engine component data;

[0156] In step 1, engine data and information required for adjustment calculations are collected by consulting engine matching lists and test reports;

[0157] Engine data includes test results of engine components and structural parameters. Engine information includes the model and code of the engine, as well as the component serial number and test date.

[0158] Step 2: Select and adjust the XML file corresponding to the calculated engine type;

[0159] In step 2, the corresponding XML file is selected from the preset XML file library according to the engine model;

[0160] The selected XML file format is " "For different types of rocket engines, there are corresponding XML files. It is necessary to select the XML file that matches the target engine type to ensure the correctness of parsing and storage operations."

[0161] The XML file contains elements such as "engine information", "calculated target value", "external parameter", "engine component data", "calculated initial value and result", and "parameter envelope value".

[0162] in:

[0163] "Engine Information" includes "Engine Model", "Engine Code", and "Component Information"; among which, "Component Information" includes "Component Serial Number" and "Test Date";

[0164] The “target value calculation” includes “operating conditions” and “mixing ratio”;

[0165] "External parameters" include "oxidizer and fuel inlet temperature", "oxidizer and fuel inlet pressure", and "ambient pressure".

[0166] "Engine component data" includes "generator", "thrust chamber", "turbo pump", and "valve actuator"; among which, "generator" includes "injector flow resistance coefficient"; "thrust chamber" includes "injector flow resistance coefficient" and "thrust chamber throat diameter"; "turbo pump" includes "pump characteristics", "turbine characteristics", and "turbine flow area".

[0167] The "Initial values ​​and results" include "flow parameters", "pressure parameters", "temperature parameters", "power parameters" and "efficiency parameters".

[0168] The “Parameter Envelope Value” includes “Input Envelope” and “Result Envelope”. The “Input Envelope” includes “Pump Head Envelope”, “Pump Efficiency Envelope”, and “Turbine Efficiency Envelope”. The “Result Envelope” includes “Operating Condition”, “Mix Ratio”, “Turbine Pump Speed”, “Generator Chamber Pressure”, “Thrust Chamber Pressure”, and “Throttling Element Parameters”.

[0169] Step 3: Obtain the adjustment calculation configuration file;

[0170] Step 4: Store the engine information, calculated target value, external parameters, engine component data, initial calculation value and result, and parameter envelope value elements into an XML file;

[0171] Step 5: Parse the XML file obtained in Step 4 to obtain the initial values ​​for adjustment and calculation;

[0172] Step 6: Obtain the calculation results of the target value, external parameters, and initial values;

[0173] Step 7: Store the calculation results obtained in Step 6 into the XML file obtained in Step 4;

[0174] Step 8: Determine if the data is within the data envelopment range.

[0175] Example 5

[0176] A liquid rocket engine adjustment calculation method based on XML parsing and storage includes the following steps:

[0177] Step 1: Collect the required engine information and engine component data;

[0178] In step 1, engine data and information required for adjustment calculations are collected by consulting engine matching lists and test reports;

[0179] Engine data includes test results of engine components and structural parameters. Engine information includes the model and code of the engine, as well as the component serial number and test date.

[0180] Step 2: Select and adjust the XML file corresponding to the calculated engine type;

[0181] In step 2, the corresponding XML file is selected from the preset XML file library according to the engine model;

[0182] The selected XML file format is " "For different types of rocket engines, there are corresponding XML files. It is necessary to select the XML file that matches the target engine type to ensure the correctness of parsing and storage operations."

[0183] The XML file contains elements such as "engine information", "calculated target value", "external parameter", "engine component data", "calculated initial value and result", and "parameter envelope value".

[0184] in:

[0185] "Engine Information" includes "Engine Model", "Engine Code", and "Component Information"; among which, "Component Information" includes "Component Serial Number" and "Test Date";

[0186] The “target value calculation” includes “operating conditions” and “mixing ratio”;

[0187] "External parameters" include "oxidizer and fuel inlet temperature", "oxidizer and fuel inlet pressure", and "ambient pressure".

[0188] "Engine component data" includes "generator", "thrust chamber", "turbo pump", and "valve actuator"; among which, "generator" includes "injector flow resistance coefficient"; "thrust chamber" includes "injector flow resistance coefficient" and "thrust chamber throat diameter"; "turbo pump" includes "pump characteristics", "turbine characteristics", and "turbine flow area".

[0189] The "Initial values ​​and results" include "flow parameters", "pressure parameters", "temperature parameters", "power parameters" and "efficiency parameters".

[0190] The “Parameter Envelope Value” includes “Input Envelope” and “Result Envelope”. The “Input Envelope” includes “Pump Head Envelope”, “Pump Efficiency Envelope”, and “Turbine Efficiency Envelope”. The “Result Envelope” includes “Operating Condition”, “Mix Ratio”, “Turbine Pump Speed”, “Generator Chamber Pressure”, “Thrust Chamber Pressure”, and “Throttling Element Parameters”.

[0191] Step 3: Obtain the adjustment calculation configuration file;

[0192] Step 3 specifically involves using LINQ to XML technology to parse the XML file selected in Step 2, thereby obtaining the specified elements, sub-elements, and attributes in the XML file, and using the parsed XML file as the adjustment calculation configuration file.

[0193] Step 4: Store the engine information, calculated target value, external parameters, engine component data, initial calculation value and result, and parameter envelope value elements into an XML file;

[0194] Step 5: Parse the XML file obtained in Step 4 to obtain the initial values ​​for adjustment and calculation;

[0195] Step 6: Obtain the calculation results of the target value, external parameters, and initial values;

[0196] Step 7: Store the calculation results obtained in Step 6 into the XML file obtained in Step 4;

[0197] Step 8: Determine if the data is within the data envelopment range.

[0198] Example 6

[0199] A liquid rocket engine adjustment calculation method based on XML parsing and storage includes the following steps:

[0200] Step 1: Collect the required engine information and engine component data;

[0201] In step 1, engine data and information required for adjustment calculations are collected by consulting engine matching lists and test reports;

[0202] Engine data includes test results of engine components and structural parameters. Engine information includes the model and code of the engine, as well as the component serial number and test date.

[0203] Step 2: Select and adjust the XML file corresponding to the calculated engine type;

[0204] In step 2, the corresponding XML file is selected from the preset XML file library according to the engine model;

[0205] The selected XML file format is " "For different types of rocket engines, there are corresponding XML files. It is necessary to select the XML file that matches the target engine type to ensure the correctness of parsing and storage operations."

[0206] The XML file contains elements such as "engine information", "calculated target value", "external parameter", "engine component data", "calculated initial value and result", and "parameter envelope value".

[0207] in:

[0208] "Engine Information" includes "Engine Model", "Engine Code", and "Component Information"; among which, "Component Information" includes "Component Serial Number" and "Test Date";

[0209] The “target value calculation” includes “operating conditions” and “mixing ratio”;

[0210] "External parameters" include "oxidizer and fuel inlet temperature", "oxidizer and fuel inlet pressure", and "ambient pressure".

[0211] "Engine component data" includes "generator", "thrust chamber", "turbo pump", and "valve actuator"; among which, "generator" includes "injector flow resistance coefficient"; "thrust chamber" includes "injector flow resistance coefficient" and "thrust chamber throat diameter"; "turbo pump" includes "pump characteristics", "turbine characteristics", and "turbine flow area".

[0212] The "Initial values ​​and results" include "flow parameters", "pressure parameters", "temperature parameters", "power parameters" and "efficiency parameters".

[0213] The “Parameter Envelope Value” includes “Input Envelope” and “Result Envelope”. The “Input Envelope” includes “Pump Head Envelope”, “Pump Efficiency Envelope”, and “Turbine Efficiency Envelope”. The “Result Envelope” includes “Operating Condition”, “Mix Ratio”, “Turbine Pump Speed”, “Generator Chamber Pressure”, “Thrust Chamber Pressure”, and “Throttling Element Parameters”.

[0214] Step 3: Obtain the adjustment calculation configuration file;

[0215] Step 3 specifically involves using LINQ to XML technology to parse the XML file selected in Step 2, thereby obtaining the specified elements, sub-elements, and attributes in the XML file, and using the parsed XML file as the adjustment calculation configuration file.

[0216] Step 4: Store the engine information, calculated target value, external parameters, engine component data, initial calculation value and result, and parameter envelope value elements into an XML file;

[0217] In step 4, LINQ to XML technology is used to modify the specified elements, sub-elements and attributes in the XML file so that the "engine information" and "engine component data" in the XML file are consistent with the engine information and engine component data collected in step 1. In addition, according to the overall requirements of rocket propulsion, the target values ​​of the calculation conditions and mixture ratio in the XML file are adjusted to be consistent with the requirements of the overall rocket propulsion conditions and mixture ratio.

[0218] The modified engine information and engine component data will be stored in " "In the format file, the XML file may be the same file as or a different file from the XML file in step 2."

[0219] Step 5: Parse the XML file obtained in Step 4 to obtain the initial values ​​for adjustment and calculation;

[0220] Step 6: Obtain the calculation results of the target value, external parameters, and initial values;

[0221] Step 7: Store the calculation results obtained in Step 6 into the XML file obtained in Step 4;

[0222] Step 8: Determine if the data is within the data envelopment range.

Claims

1. A liquid rocket engine adjustment calculation method based on XML parsing and storage, characterized in that, Includes the following steps: Step 1: Collect the required engine information and engine component data; Step 2: Select and adjust the XML file corresponding to the calculated engine type; Step 3: Obtain the adjustment calculation configuration file; Step 4: Store the engine information, calculated target value, external parameters, engine component data, initial calculation value and result, and parameter envelope value elements into an XML file; Step 5: Parse the XML file obtained in Step 4 to obtain the initial values ​​for adjustment and calculation; Step 6: Obtain the calculation results of the target value, external parameters, and initial values; Step 7: Store the calculation results obtained in Step 6 into the XML file obtained in Step 4; Step 8: Determine if the data is within the data envelopment range.

2. The liquid rocket engine adjustment calculation method based on XML parsing and storage according to claim 1, characterized in that, In step 1, engine data and information required for adjustment calculations are collected by consulting engine matching lists and test reports; Engine data includes test results of engine components and structural parameters. Engine information includes the model, code, component serial number, and test date of the engine.

3. The liquid rocket engine adjustment calculation method based on XML parsing and storage according to claim 2, characterized in that, In step 2, the corresponding XML file is selected from the preset XML file library according to the engine model; The selected XML file format is " "For different types of rocket engines, there are corresponding XML files. It is necessary to select the XML file that matches the target engine type to ensure the correctness of parsing and storage operations." The XML file contains the elements "Engine Information", "Calculated Target Values", "External Parameters", "Engine Component Data", "Initial Calculation Values ​​and Results", and "Parameter Envelope Values". in: "Engine Information" includes "Engine Model", "Engine Code", and "Component Information"; among which, "Component Information" includes "Component Serial Number" and "Test Date"; "Calculate target value" includes "operating condition" and "mixing ratio"; "External parameters" include "oxidizer and fuel inlet temperature", "oxidizer and fuel inlet pressure", and "ambient pressure"; "Engine component data" includes "generator", "thrust chamber", "turbo pump", and "valve actuator"; among which, "generator" includes "injector flow resistance coefficient"; "thrust chamber" includes "injector flow resistance coefficient" and "thrust chamber throat diameter"; "turbo pump" includes "pump characteristics", "turbine characteristics", and "turbine flow area". "Initial values ​​and results" include "flow parameters", "pressure parameters", "temperature parameters", "power parameters" and "efficiency parameters"; The "Parameter Envelope Values" include "Input Envelope" and "Result Envelope". The "Input Envelope" includes: "Pump Head Envelope", "Pump Efficiency Envelope", and "Turbine Efficiency Envelope". The "Result Envelope" includes: "Operating Condition", "Mix Ratio", "Turbine Pump Speed", "Generator Chamber Pressure", "Thrust Chamber Pressure", and "Throttle Element Parameters".

4. The liquid rocket engine adjustment calculation method based on XML parsing and storage according to claim 3, characterized in that, Step 3 specifically involves using LINQ to XML technology to parse the XML file selected in Step 2, thereby obtaining the specified elements, sub-elements, and attributes in the XML file, and using the parsed XML file as the adjustment calculation configuration file.

5. The liquid rocket engine adjustment calculation method based on XML parsing and storage according to claim 4, characterized in that, In step 4, LINQ to XML technology is used to modify the specified elements, sub-elements and attributes in the XML file, so that the "engine information" and "engine component data" in the XML file are consistent with the engine information and engine component data collected in step 1. In addition, according to the overall requirements of rocket propulsion, the target values ​​of the calculation conditions and mixture ratio in the XML file are adjusted to be consistent with the requirements of the overall rocket propulsion conditions and mixture ratio. The modified engine information and engine component data will be stored in " "In the format file, the XML file may be the same file as or a different file from the XML file in step 2." 6. The liquid rocket engine adjustment calculation method based on XML parsing and storage according to claim 5, characterized in that, In step 5, the "Initial values ​​and results" element in the XML file obtained in step 4 is parsed using LINQ to XML technology. The calculation results of the previous engine adjustment contained in the XML file are used as the initial values ​​required for this adjustment calculation.

7. The liquid rocket engine adjustment calculation method based on XML parsing and storage according to claim 6, characterized in that, In step 7, the specified elements, sub-elements, and attributes in the XML file are modified using LINQ to XML technology, so that the "initial values ​​and results" in the XML file obtained in step 4 are consistent with the calculation results described in step 6.

8. The liquid rocket engine adjustment calculation method based on XML parsing and storage according to claim 7, characterized in that, Step 8 specifically involves parsing the "parameter envelope values" in the XML file using LINQ to XML technology, and determining whether the "pump characteristics", "turbine characteristics" data, and the calculation results obtained in step 6 are within the historical data envelope range. The judgment criteria are as follows: The judgment is made based on the display of the curves showing "Oxidizer Pump Head," "Oxidizer Pump Power," "Fuel Pump Head," "Fuel Pump Power," and "Turbine Efficiency" according to the "Pump Characteristics" and "Turbine Characteristics" data. Specifically: If all curves are displayed completely, the "pump characteristics" and "turbine characteristics" data in the XML file are determined to be within the historical data network range; if any curve cannot be displayed completely, the "pump characteristics" and "turbine characteristics" data in the XML file are determined to be outside the historical data network range.

9. A liquid rocket engine adjustment calculation device based on XML parsing and storage, implemented using the method described in claim 1, specifically comprising: The interface module is used to display the parsed XML data and information on the interface, and to edit the XML elements that need to be modified in the interface; The XML file manipulation module completes the parsing and storage of the XML file; The mathematical model module constructs a mathematical model of the liquid rocket engine based on its type, adjustment calculation theory, and extracted data. The solution module stores the equation-solving algorithms and performs calculations based on the engine target performance, initial values, and input parameters. The analysis module determines whether the calculation results are within the historical data envelopment range and displays the analysis results in tabular form, highlighting cases where the analysis results exceed the envelopment.

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