Method and system for predicting and calculating pre-launch temperature of carrier rocket component
By establishing a heat conduction simulation model and environmental tests to obtain the thermal diffusion coefficient, we established a temperature change relationship model for launch vehicle components, which solved the problem of temperature change trends of launch vehicle components and pre-launch temperature prediction, and achieved fast and accurate temperature prediction. Improved the reliability and safety of space launch activities.
Patent Information
- Application Number
- CN202411366269.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-29
- Publication Date
- 2025-01-24
Smart Images
Figure CN119358222A_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the field of space launch vehicles, and in particular to a method and system for predicting the pre-launch temperature of launch vehicle components. Background Art
[0002] Some components of launch vehicles, especially key equipment such as liquid engines, escape solid engines and servo mechanisms, have strict protection requirements for ambient temperature. For example, the first-stage liquid engine of the CZ-2F launch vehicle must ensure that the temperature of the propellant in the fuel and oxidizer start valve delivery pipelines meets the requirements (the temperature of unsymmetrical dimethylhydrazine is 1°C to 25°C, the temperature of nitrogen tetroxide is 5°C to 20°C, and the temperature difference between the two propellants is no more than 5°C), and the temperature of the engine tail compartment is no less than 0°C.
[0003] In manned space launch missions, zero-window launch must be ensured. According to the operating specifications and launch plan, the air supply duct of the fairing environment air conditioning is withdrawn within -60 minutes, and the rotating platform is opened at the latest within -30 minutes. In an extremely low temperature environment, the temperature change trend of some key components of the carrier rocket after the tower is opened and the temperature value before launch become the key factors affecting the commander's decision on whether the launch can be carried out. In the traditional mode, experience is mainly used to judge whether the launch can be carried out, or the temperature of some key components of the carrier rocket is guaranteed by taking sufficient insulation measures to ensure the smooth launch of the carrier rocket. However, there is currently no scientific and effective way to solve the temperature change trend of these components of the carrier rocket and the problem of temperature prediction before launch.
[0004] Therefore, how to effectively solve the temperature change trend of launch vehicle components and the pre-launch temperature prediction is a technical problem that technical personnel in this field urgently need to solve. Summary of the invention
[0005] The present application provides a method and system for predicting and calculating the temperature of a launch vehicle component before launch, so as to quickly predict and calculate the temperature and change trend of the launch vehicle component.
[0006] In order to solve the above technical problems, this application provides the following technical solutions:
[0007] A method for predicting and calculating the temperature of a launch vehicle component before launch, comprising the following steps: step S110, establishing a heat conduction simulation model of a launch vehicle component; step S120, conducting an environmental test on the launch vehicle component in a laboratory, and obtaining the thermal diffusion coefficient of the heat conduction simulation model through the environmental test; step S130, establishing a relationship model between the temperature change of the launch vehicle component and the propellant temperature and ambient temperature of the launch vehicle tank based on the obtained thermal diffusion coefficient of the heat conduction simulation model; step S140, inputting the ambient temperature and propellant temperature monitored before launch into the relationship model, thereby predicting and calculating the temperature of the launch vehicle component at any time.
[0008] In the method for predicting and calculating the pre-launch temperature of a launch vehicle lower component as described above, it is preferred that the launch vehicle lower component is the engine tail compartment of the launch vehicle.
[0009] In the method for predicting and calculating the pre-launch temperature of a launch vehicle component as described above, it is preferred that the temperature of the tail compartment of the launch vehicle engine is not less than 0°C.
[0010] The method for calculating the pre-launch temperature prediction of a launch vehicle lower component as described above, wherein preferably, environmental testing is performed on the launch vehicle lower component, comprising the following steps: step S121, dividing the launch vehicle lower component into a plurality of test areas; step S122, irradiating the starting point of the test area with a high-intensity short-time energy pulse; step S123, recording the temperature change over time at the end point of the test area; step S124, calculating the thermal diffusion coefficient of the material of the test area based on the measured temperature change data in combination with the length from the starting point to the end point of the test area; step S125, superimposing and averaging the thermal diffusion coefficients of the materials in all the test areas to obtain the thermal diffusion system of the launch vehicle lower component.
[0011] A temperature prediction calculation system for a carrier rocket component before launch, comprising: a simulation model establishment module, an environmental test module, a coefficient calculation module, a relationship model establishment module, a temperature sensor and a prediction calculation module; the simulation model establishment module establishes a heat conduction simulation model of a carrier rocket component; the environmental test module performs an environmental test on the carrier rocket component in a laboratory, and the coefficient calculation module obtains the thermal diffusion coefficient of the heat conduction simulation model through the environmental test; the relationship model establishment module establishes a relationship model between the temperature change of the carrier rocket component and the propellant temperature and the ambient temperature of the carrier rocket tank according to the obtained thermal diffusion coefficient of the heat conduction simulation model; the temperature sensor monitors the ambient temperature and the propellant temperature before launch, and the prediction calculation module inputs the monitored ambient temperature and the propellant temperature before launch into the relationship model, thereby predicting and calculating the temperature of the carrier rocket component at any time.
[0012] The pre-launch temperature prediction and calculation system for a launch vehicle lower component as described above, wherein preferably, the launch vehicle lower component is the engine tail compartment of the launch vehicle.
[0013] In the above-mentioned pre-launch temperature prediction and calculation system for launch vehicle components, it is preferred that the temperature of the tail compartment of the launch vehicle engine is not lower than 0°C.
[0014] The pre-launch temperature prediction calculation system for launch vehicle lower components as described above, wherein preferably, the environmental test module includes: a division module, a radiation module, a recording module, a calculation module and a superposition module; the division module divides the launch vehicle lower components into multiple test areas; the radiation module uses a high-intensity short-time energy pulse to radiate the starting point of the test area; the recording module records the temperature change of the end point of the test area over time; the calculation module can calculate the thermal diffusion coefficient of the material of the test area based on the measured temperature change data combined with the length from the starting point to the end point of the test area; the superposition module superimposes and averages the thermal diffusion coefficients of the materials in all the test areas to obtain the thermal diffusion system of the launch vehicle lower components.
[0015] Compared with the above-mentioned background technology, the present application can quickly predict and calculate the temperature and change trend of the launch vehicle components (for example, the engine tail compartment), confirm whether the launch vehicle components meet the launch window temperature conditions, and provide decision-making basis for commanders, thereby avoiding the failure of the launch vehicle launch due to the temperature of the launch vehicle components not meeting the launch requirements, thereby improving the reliability and safety of space launch activities. BRIEF DESCRIPTION OF THE DRAWINGS
[0016] In order to more clearly illustrate the embodiments of the present invention 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 invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.
[0017] Figure 1 It is a flow chart of the method for predicting the pre-launch temperature of a launch vehicle component provided by the present application;
[0018] Figure 2 It is a flow chart of environmental testing of launch vehicle components provided by the present application;
[0019] Figure 3 It is a schematic diagram of a pre-launch temperature prediction calculation system for launch vehicle components provided by the present application. DETAILED DESCRIPTION
[0020] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be interpreted as limiting the present invention.
[0021] Embodiment 1
[0022] like Figure 1As shown, the present application provides a method for calculating the temperature prediction of a launch vehicle component before launch, comprising the following steps:
[0023] Step S110, establishing a heat conduction simulation model of launch vehicle components;
[0024] In the present application, the launch vehicle component used for pre-launch temperature prediction may refer to the engine tail compartment of the launch vehicle. The engine tail compartment of the launch vehicle has strict temperature protection requirements, for example: the temperature of the engine tail compartment of the launch vehicle is not lower than 0°C. Therefore, a heat conduction simulation model of the engine tail compartment of the launch vehicle may be established here.
[0025] The heat conduction simulation model of the launch vehicle components is as follows:
[0026]
[0027] Wherein, x is the x coordinate of a point in space of the launch vehicle lower component; y is the y coordinate of a point in space of the launch vehicle lower component; z is the z coordinate of a point in space of the launch vehicle lower component; T is the temperature of a point in space of the launch vehicle lower component; t is time; The rate of change of temperature of a point in space of a launch vehicle component over time; is a mathematical symbol partial derivative; α is the thermal diffusion coefficient of the launch vehicle component, which is a measure of the rate at which the temperature disturbance at a certain point in the launch vehicle component is transmitted to another point, and is the ratio of the heat conduction capacity of the launch vehicle component material to the heat storage capacity of the material. The material of the launch vehicle component in this application is an inhomogeneous material, so the thermal diffusion coefficient α of the launch vehicle component is an uncertain coefficient. Therefore, a large number of environmental tests will be carried out on this component of the launch vehicle to obtain the thermal diffusion coefficient α of this component of the launch vehicle.
[0028] Step S120, performing environmental tests on launch vehicle components in a laboratory, and obtaining the thermal diffusion coefficient of the heat conduction simulation model through the environmental tests;
[0029] A large number of environmental tests are carried out on the launch vehicle components in the laboratory, and the results of each environmental test are input into the computer. A thermal diffusion coefficient is obtained through the result of each environmental test. The thermal diffusion coefficients obtained from all environmental tests are superimposed and averaged to obtain the thermal diffusion coefficient of the launch vehicle components. The obtained thermal diffusion system of the launch vehicle components is used as the thermal diffusion coefficient α of the simulation model.
[0030] The environmental test can be carried out by irradiating a first point of a launch vehicle lower component with pulsed light so that the point of the launch vehicle lower component absorbs the pulsed light irradiation energy, and at the same time using a detector to record the temperature change over time caused by the heat transferred to a second point of the launch vehicle lower component, thereby obtaining the thermal diffusion coefficient between the first point and the second point of the launch vehicle lower component.
[0031] Specifically, Figure 2 As shown in the figure, environmental testing of launch vehicle components includes the following steps:
[0032] Step S121, dividing the launch vehicle components into a plurality of test areas;
[0033] Step S122, irradiating the starting point of the tested area with a high-intensity short-time energy pulse;
[0034] Step S123, recording the change of the temperature of the end point of the tested area over time;
[0035] Step S124: Based on the measured temperature change data, the thermal diffusion coefficient of the material in the tested area can be calculated in combination with the length from the starting point to the end point of the tested area;
[0036] Step S125, superimpose and average the thermal diffusion coefficients of the materials in all the tested areas to obtain the thermal diffusion system of the launch vehicle components.
[0037] Step S130, establishing a relationship model between the temperature change of the launch vehicle components and the propellant temperature and ambient temperature of the launch vehicle tank according to the obtained thermal diffusion coefficient of the heat conduction simulation model;
[0038] After obtaining the thermal diffusion coefficient α of the launch vehicle component with uneven material, the computer establishes a relationship model between the temperature change of the launch vehicle component and the propellant temperature and ambient temperature of the launch vehicle tank based on the obtained thermal diffusion coefficient α as a heat conduction simulation model.
[0039] The relationship model between the temperature change of the launch vehicle components and the propellant temperature and ambient temperature of the launch vehicle tank is as follows:
[0040]
[0041] Wherein, x is the x coordinate of a point in space of the launch vehicle lower component; y is the y coordinate of a point in space of the launch vehicle lower component; z is the z coordinate of a point in space of the launch vehicle lower component; T is the temperature of a point in space of the launch vehicle lower component; t is time; The rate of change of temperature of a point in space of a launch vehicle component over time; is the mathematical symbol partial derivative; α is the thermal diffusion coefficient of the launch vehicle component; q is the heat flux density; k is the thermal conductivity; T推进剂 is the propellant temperature; T 环境 is the ambient temperature.
[0042] Since the temperature of the tail compartment of the launch vehicle engine is determined by the propellant temperature and the ambient temperature, the propellant temperature T is added to the relationship model. 推进剂 and ambient temperature T 环境 , so that more influencing factors can be considered when performing temperature prediction calculations, thereby improving the accuracy of temperature prediction calculations.
[0043] Step 140, input the ambient temperature and propellant temperature monitored before launch into the relationship model, so as to predict and calculate the temperature of the launch vehicle components at any time;
[0044] The ambient temperature sensor can monitor the ambient temperature T after the fairing environment air conditioning air supply pipeline is withdrawn and the rotary platform is opened. 环境 The propellant temperature sensor monitors the propellant temperature T in the launch vehicle tank cabin. 推进剂 , and then the monitored ambient temperature T 环境 and the propellant temperature T in the launch vehicle tank compartment 推进剂 By inputting it into the above relationship model, the temperature of the launch vehicle component (the tail compartment of the launch vehicle engine) at that moment can be predicted and calculated.
[0045] Repeatedly monitor the ambient temperature T 环境 and the propellant temperature T in the launch vehicle tank compartment 推进剂 , thus predicting and calculating the temperature of the launch vehicle's main components (the tail compartment of the launch vehicle's engine) at any time, and then predicting and deriving the temperature change trend of the launch vehicle's main components based on the trend of the ambient temperature in the weather forecast.
[0046] The above-mentioned method for calculating the pre-launch temperature prediction of launch vehicle components is a calculation program that can be run in a computer.
[0047] Embodiment 2
[0048] like Figure 3 As shown, the present application provides a pre-launch temperature prediction calculation system 300 for launch vehicle components, including: a simulation model establishment module 310, an environmental test module 320, a coefficient calculation module 330, a relationship model establishment module 340, a temperature sensor 350 and a prediction calculation module 360.
[0049] The simulation model building module 310 builds a heat conduction simulation model of the launch vehicle components.
[0050] In the present application, the launch vehicle component used for pre-launch temperature prediction may refer to the engine tail compartment of the launch vehicle. The engine tail compartment of the launch vehicle has strict temperature protection requirements, for example: the temperature of the engine tail compartment of the launch vehicle is not lower than 0°C. Therefore, a heat conduction simulation model of the engine tail compartment of the launch vehicle may be established here.
[0051] The heat conduction simulation model of the launch vehicle components is as follows:
[0052]
[0053] Wherein, x is the x coordinate of a point in space of the launch vehicle lower component; y is the y coordinate of a point in space of the launch vehicle lower component; z is the z coordinate of a point in space of the launch vehicle lower component; T is the temperature of a point in space of the launch vehicle lower component; t is time; The rate of change of temperature of a point in space of a launch vehicle component over time; is a mathematical symbol partial derivative; α is the thermal diffusion coefficient of the launch vehicle component, which is a measure of the rate at which the temperature disturbance at a certain point in the launch vehicle component is transmitted to another point, and is the ratio of the heat conduction capacity of the launch vehicle component material to the heat storage capacity of the material. The material of the launch vehicle component in this application is an inhomogeneous material, so the thermal diffusion coefficient α of the launch vehicle component is an uncertain coefficient. Therefore, a large number of environmental tests will be carried out on this component of the launch vehicle to obtain the thermal diffusion coefficient α of this component of the launch vehicle.
[0054] The environmental test module 320 performs environmental tests on the components of the launch vehicle in the laboratory, and the coefficient calculation module 330 obtains the thermal diffusion coefficient of the heat conduction simulation model through the environmental test.
[0055] A large number of environmental tests are carried out on the launch vehicle components in the laboratory, and the results of each environmental test are input into the computer. A thermal diffusion coefficient is obtained through the result of each environmental test. The thermal diffusion coefficients obtained from all environmental tests are superimposed and averaged to obtain the thermal diffusion coefficient of the launch vehicle components. The obtained thermal diffusion system of the launch vehicle components is used as the thermal diffusion coefficient α of the simulation model.
[0056] The environmental test can be carried out by irradiating a first point of a launch vehicle lower component with pulsed light so that the point of the launch vehicle lower component absorbs the pulsed light irradiation energy, and at the same time using a detector to record the temperature change over time caused by the heat transferred to a second point of the launch vehicle lower component, thereby obtaining the thermal diffusion coefficient between the first point and the second point of the launch vehicle lower component.
[0057] Specifically, the environmental test module 320 includes: a division module 321 , a radiation module 322 , a recording module 323 , a calculation module 324 and a superposition module 325 .
[0058] The division module 321 divides the launch vehicle lower component into multiple test areas; the radiation module 322 uses a high-intensity short-time energy pulse to radiate the starting point of the test area; the recording module 323 records the temperature change of the end point of the test area over time; the calculation module 324 can calculate the thermal diffusion coefficient of the material in the test area based on the measured temperature change data and the length from the starting point to the end point of the test area; the superposition module 325 superimposes and averages the thermal diffusion coefficients of the materials in all the test areas to obtain the thermal diffusion system of the launch vehicle lower component.
[0059] The relationship model building module 340 builds a relationship model between the temperature change of the launch vehicle components and the propellant temperature and ambient temperature of the launch vehicle tank according to the thermal diffusion coefficient of the heat conduction simulation model.
[0060] After obtaining the thermal diffusion coefficient α of the launch vehicle component with uneven material, the computer establishes a relationship model between the temperature change of the launch vehicle component and the propellant temperature and ambient temperature of the launch vehicle tank based on the obtained thermal diffusion coefficient α as a heat conduction simulation model.
[0061] The relationship model between the temperature change of the launch vehicle components and the propellant temperature and ambient temperature of the launch vehicle tank is as follows:
[0062]
[0063] Wherein, x is the x coordinate of a point in space of the launch vehicle lower component; y is the y coordinate of a point in space of the launch vehicle lower component; z is the z coordinate of a point in space of the launch vehicle lower component; T is the temperature of a point in space of the launch vehicle lower component; t is time; The rate of change of temperature of a point in space of a launch vehicle component over time; is the mathematical symbol partial derivative; α is the thermal diffusion coefficient of the launch vehicle component; q is the heat flux density; k is the thermal conductivity; T 推进剂 is the propellant temperature; T 环境 is the ambient temperature.
[0064] Since the temperature of the tail compartment of the launch vehicle engine is determined by the propellant temperature and the ambient temperature, the propellant temperature T is added to the relationship model. 推进剂 and ambient temperature T 环境 , so that more influencing factors can be considered when performing temperature prediction calculations, thereby improving the accuracy of temperature prediction calculations.
[0065] The temperature sensor 350 monitors the ambient temperature and the propellant temperature before launch, and the prediction calculation module 360 inputs the ambient temperature and the propellant temperature monitored before launch into the relationship model, thereby predicting and calculating the temperature of the launch vehicle components at any time.
[0066] The ambient temperature sensor can monitor the ambient temperature T after the fairing environment air conditioning air supply pipeline is withdrawn and the rotary platform is opened. 环境 The propellant temperature sensor monitors the propellant temperature T in the launch vehicle tank cabin. 推进剂 , and then the monitored ambient temperature T 环境 and the propellant temperature T in the launch vehicle tank compartment 推进剂 By inputting it into the above relationship model, the temperature of the launch vehicle component (the tail compartment of the launch vehicle engine) at that moment can be predicted and calculated.
[0067] Repeatedly monitor the ambient temperature T 环境 and the propellant temperature T in the launch vehicle tank compartment 推进剂 , thus predicting and calculating the temperature of the launch vehicle's main components (the tail compartment of the launch vehicle's engine) at any time, and then predicting and deriving the temperature change trend of the launch vehicle's main components based on the trend of the ambient temperature in the weather forecast.
[0068] The above-mentioned simulation model building module 310, environmental test module 320, coefficient calculation module 330, relationship model building module 340 and prediction calculation module 360 are all program segments executed by the CPU, or hardware units with data processing capabilities.
[0069] This application can be used to quickly predict and calculate the temperature and change trend of carrier rocket components (for example, the engine tail compartment) in extreme environments before space launch, confirm whether the carrier rocket components meet the launch window temperature conditions, provide decision-making basis for commanders, avoid the failure of carrier rocket launch due to the temperature of carrier rocket components not meeting the launch requirements, and thus improve the reliability and safety of space launch activities.
[0070] It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above and that the invention can be implemented in other specific forms without departing from the spirit or essential features of the invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations falling within the meaning and scope of the equivalent elements of the claims be included in the invention. Any reference numeral in a claim should not be considered as limiting the claim to which it relates.
[0071] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.
Claims
1. A method for calculating the temperature prediction of a launch vehicle component before launch, characterized in that: The steps include: Step S110, establishing a heat conduction simulation model of launch vehicle components; Step S120, performing environmental tests on launch vehicle components in a laboratory, and obtaining the thermal diffusion coefficient of the heat conduction simulation model through the environmental tests; Step S130, establishing a relationship model between the temperature change of the launch vehicle components and the propellant temperature and ambient temperature of the launch vehicle tank according to the obtained thermal diffusion coefficient of the heat conduction simulation model; Step 140: Input the ambient temperature and propellant temperature monitored before launch into the relationship model, thereby predicting and calculating the temperature of the launch vehicle components at any time.
2. The method for calculating the pre-launch temperature of a launch vehicle component according to claim 1, characterized in that: The launch vehicle component is the engine tail compartment of the launch vehicle.
3. The method for calculating the temperature prediction of a launch vehicle component before launch according to claim 2, characterized in that: The temperature of the tail compartment of the carrier rocket engine shall not be lower than 0℃.
4. The method for calculating the pre-launch temperature of a launch vehicle component according to any one of claims 1 to 3, characterized in that: Environmental testing of launch vehicle components includes the following steps: Step S121, dividing the launch vehicle components into a plurality of test areas; Step S122, irradiating the starting point of the tested area with a high-intensity short-time energy pulse; Step S123, recording the change of the temperature of the end point of the tested area over time; Step S124: Based on the measured temperature change data, the thermal diffusion coefficient of the material in the tested area can be calculated in combination with the length from the starting point to the end point of the tested area; Step S125, superimpose and average the thermal diffusion coefficients of the materials in all the tested areas to obtain the thermal diffusion system of the launch vehicle components.
5. A pre-launch temperature prediction calculation system for launch vehicle components, characterized in that: include: Simulation model building module, environmental test module, coefficient calculation module, relationship model building module, temperature sensor and prediction calculation module; The simulation model building module builds the heat conduction simulation model of the launch vehicle components; The environmental test module conducts environmental tests on launch vehicle components in the laboratory, and the coefficient calculation module obtains the thermal diffusion coefficient of the heat conduction simulation model through environmental tests; The relationship model building module builds the relationship model between the temperature change of the launch vehicle components and the propellant temperature and ambient temperature of the launch vehicle tank according to the thermal diffusion coefficient of the heat conduction simulation model; The temperature sensor monitors the ambient temperature and propellant temperature before launch, and the predictive calculation module inputs the ambient temperature and propellant temperature monitored before launch into the relationship model, thereby predicting and calculating the temperature of the launch vehicle components at any time.
6. The pre-launch temperature prediction and calculation system for launch vehicle components according to claim 5, characterized in that: The launch vehicle component is the engine tail compartment of the launch vehicle.
7. The pre-launch temperature prediction and calculation system for launch vehicle components according to claim 6, characterized in that: The temperature of the tail compartment of the carrier rocket engine shall not be lower than 0℃.
8. The pre-launch temperature prediction and calculation system for launch vehicle components according to any one of claims 5 to 7, characterized in that: The environmental test module includes: division module, radiation module, recording module, calculation module and superposition module; The division module divides the launch vehicle components into multiple test areas; The radiation module uses high-intensity short-duration energy pulses to radiate the starting point of the tested area; The recording module records the change of the temperature of the end point of the tested area over time; The calculation module can calculate the thermal diffusion coefficient of the material in the tested area based on the measured temperature change data and the length from the starting point to the end point of the tested area; The superposition module superimposes and averages the thermal diffusion coefficients of the materials in all the tested areas to obtain the thermal diffusion system of the launch vehicle components.