CN115186779A - Method, system and equipment for constructing rocket high-altitude flight test health monitoring system - Google Patents
Method, system and equipment for constructing rocket high-altitude flight test health monitoring system Download PDFInfo
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- CN115186779A CN115186779A CN202211112817.9A CN202211112817A CN115186779A CN 115186779 A CN115186779 A CN 115186779A CN 202211112817 A CN202211112817 A CN 202211112817A CN 115186779 A CN115186779 A CN 115186779A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
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Abstract
The invention relates to the technical field of aerospace, and provides a method, a system and equipment for constructing a rocket high-altitude flight test run health monitoring system. The construction method of the rocket high-altitude flight test run health monitoring system comprises the following steps: training and constructing a basic model of the high-altitude flight test run health monitoring system based on the architecture of the health monitoring system of the ground high-model test run platform and pre-accumulated ground high-model test run data; acquiring real-time data of high-altitude flight test run of the liquid rocket; and after the liquid rocket returns to the ground, inputting real-time data of high-altitude flight test run into the basic model, comparing the real-time data with pre-accumulated ground high-mode test run data, and updating a corresponding data envelope range to form a high-altitude flight test run health monitoring system. The invention can realize the construction of the high-altitude flight test health monitoring system and the continuous optimization of the system, thereby realizing the real-time monitoring of the real situation of the high-altitude flight test of the liquid rocket.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a method, a system and equipment for constructing a rocket high-altitude flight test run health monitoring system.
Background
At present, a high-modulus test bed is adopted on the ground for carrying out a high-altitude simulation test on a liquid rocket engine, and the test condition is monitored in real time through a health monitoring system of the high-modulus test bed in the test process. Because the high-altitude flight test run environment is different from the ground environment, the high-altitude environment is more complex, and the health monitoring system of the ground high-model test run platform cannot accurately monitor the real condition of the high-altitude flight test run.
Therefore, it is necessary to design a health monitoring system for high-altitude flight test run of liquid rockets.
Disclosure of Invention
The invention provides a construction method, a system and equipment of a rocket high-altitude flight test run health monitoring system, which can realize the construction of the liquid rocket high-altitude flight test run health monitoring system, thereby realizing the real-time monitoring of the real conditions of the liquid rocket high-altitude flight test run.
The invention provides a construction method of a rocket high-altitude flight test health monitoring system, which comprises the following steps:
training and constructing a basic model of the high-altitude flight test run health monitoring system based on the architecture of the health monitoring system of the ground high-model test run platform and pre-accumulated ground high-model test run data;
acquiring real-time data of high-altitude flight test run of the liquid rocket;
and after the liquid rocket returns to the ground, inputting the real-time data of the high-altitude flight test run into the basic model, comparing the real-time data with the pre-accumulated ground high-mode test run data, and updating a corresponding data envelope range to form a high-altitude flight test run health monitoring system.
According to the construction method of the rocket high-altitude flight test run health monitoring system provided by the invention, the step of training and constructing a basic model of the high-altitude flight test run health monitoring system based on the architecture of the health monitoring system of the ground high-model test run platform and pre-accumulated ground high-model test run data specifically comprises the following steps:
classifying the pre-accumulated ground high-modulus test run data, and at least dividing test run data of a tested engine of the liquid rocket, operation data of a ground high-modulus test run platform and power system data in the launching process of the liquid rocket;
at least correspondingly establishing a tested engine health monitoring module, an on-arrow test bed health monitoring module and a power system health monitoring module by utilizing the classification data;
and integrating the tested engine health monitoring module, the rocket test bed health monitoring module and the power system health monitoring module to construct the basic model.
According to the construction method of the rocket high-altitude flight test run health monitoring system provided by the invention, before the liquid rocket returns to the ground, the method further comprises the following steps:
correspondingly inputting the real-time data of the high-altitude flight test run into the tested engine health monitoring module, the rocket test run platform health monitoring module and the power system health monitoring module of the basic model;
according to preset conditions, the health monitoring module of the tested engine, the health monitoring module of the test bed on the rocket and the health monitoring module of the power system respectively and correspondingly judge whether the tested engine, the test bed on the rocket and the power system are in a healthy state in the high-altitude flight test process of the liquid rocket;
and determining to continue the trial run or stop returning according to the health state judgment result.
According to the construction method of the rocket high-altitude flight test run health monitoring system provided by the invention, the step of respectively and correspondingly judging whether the tested engine, the rocket test run platform and the power system are in a healthy state in the liquid rocket high-altitude flight test run process according to the preset conditions comprises the following steps:
the tested engine health monitoring module, the rocket test run platform health monitoring module and the power system health monitoring module respectively compare corresponding real-time data of the high-altitude flight test run with corresponding preset safety values, and when the real-time data of the high-altitude flight test run are within the range of the preset safety values, the health state is judged to be output; and when the real-time data of at least one high-altitude flight test run exceeds the preset safety value, judging that the output is in an abnormal state.
According to the construction method of the rocket high-altitude flight test health monitoring system provided by the invention, the step of determining to continue test run or stop returning according to the health state judgment result specifically comprises the following steps:
if the output is in a healthy state, determining to continue to test the vehicle;
and if the output is in an abnormal state and the real-time data of the high-altitude flight test run does not reach an explosion critical value, determining to continue the test run, and when the real-time data of at least one high-altitude flight test run reaches the explosion critical value, starting the emergency shutdown operation of the tested engine by the liquid rocket, stopping the operation of the test run table on the rocket, and returning to the ground through the power system, wherein the explosion critical value is larger than the preset safety value.
According to the construction method of the rocket high-altitude flight test run health monitoring system provided by the invention, after the liquid rocket returns to the ground, the real-time data of the high-altitude flight test run is input into the basic model and compared with the pre-accumulated ground high-model test run data, and the corresponding data envelope range is updated to form the high-altitude flight test run health monitoring system, which specifically comprises the following steps:
after the liquid rocket returns to the ground, correspondingly inputting the real-time data of the high-altitude flight test run into the tested engine health monitoring module, the rocket test run platform health monitoring module and the power system health monitoring module of the basic model, correspondingly comparing the real-time data with the pre-accumulated ground high-model test run data, and updating the data envelope ranges in the tested engine health monitoring module, the rocket test run platform health monitoring module and the power system health monitoring module according to the comparison result to form the high-altitude flight test run health monitoring system.
According to the construction method of the rocket high-altitude flight test run health monitoring system provided by the invention, the step of updating the corresponding data envelope range specifically comprises the following steps: the corresponding data envelope range is expanded or reduced.
According to the construction method of the rocket high-altitude flight test run health monitoring system provided by the invention, after the high-altitude flight test run health monitoring system is formed, the method further comprises the following steps:
acquiring real-time data of multiple high-altitude flight test runs of the liquid rocket;
and after the liquid rocket returns to the ground every time, inputting the real-time data of the liquid rocket in each high-altitude flight test run into the basic model, comparing and updating the real-time data with the data in the basic model, and optimizing the basic model.
The invention also provides a construction system of the rocket high-altitude flight test run health monitoring system, which comprises the following steps:
the building module is used for training and building a basic model of the high-altitude flight test run health monitoring system based on the architecture of the health monitoring system of the ground high-modulus test run platform and pre-accumulated ground high-modulus test run data;
the acquisition module is used for acquiring real-time data of high-altitude flight test run of the liquid rocket;
and the forming module is used for inputting the real-time data of the high-altitude flight test run into the basic model after the liquid rocket returns to the ground, comparing the real-time data with the pre-accumulated ground high-mode test run data, updating a corresponding data envelope range and forming the high-altitude flight test run health monitoring system.
The invention also provides electronic equipment which comprises a memory, a processor and a computer program which is stored on the memory and can run on the processor, wherein the processor realizes the construction method of the rocket high-altitude flight test run health monitoring system when executing the program.
According to the construction method, the system and the equipment of the rocket high-altitude flight test run health monitoring system, a basic model of the high-altitude flight test run health monitoring system is trained and constructed through the architecture of the health monitoring system based on the ground high-modulus test run platform and the pre-accumulated ground high-modulus test run data; and the real-time data of the high-altitude flight test run of the liquid rocket is acquired, and after the liquid rocket returns to the ground, the real-time data of the high-altitude flight test run is input into the basic model and compared with the pre-accumulated ground high-modulus test run data, and the corresponding data envelope range is updated, so that the high-altitude flight test run health monitoring system is formed. Therefore, the high-altitude flight test run health monitoring system is constructed by utilizing the basic framework of the health monitoring system of the ground high-modulus test run and the actual data of the high-altitude flight test run, and the continuous optimization of the system can be realized, so that the real condition of the high-altitude flight test run of the liquid rocket is monitored in real time.
Drawings
In order to more clearly illustrate the technical solutions of the present invention or the related art, the drawings required to be used in the description of the embodiments or the related art are briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic flow chart of a method for constructing a rocket high-altitude flight test run health monitoring system provided by the invention;
FIG. 2 is a block diagram of the architecture of the underlying model provided by the present invention;
FIG. 3 is a block diagram of a construction system of a rocket high-altitude flight test run health monitoring system provided by the invention;
fig. 4 is a block diagram of an electronic device provided in the present invention.
Reference numerals:
210: a health monitoring module of the tested engine; 220: a health monitoring module of a test bed on an arrow;
230: a power system health monitoring module;
310: building a module; 320: an acquisition module; 330: forming a module;
410: a processor; 420: a communication interface; 430: a memory; 440: a communication bus.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings, and it is obvious that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description herein, references to the description of "one embodiment," "a specific example," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of an embodiment of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
The construction method, system and device of the rocket high-altitude flight test run health monitoring system of the invention are described below with reference to fig. 1-4. Wherein, the rocket for high-altitude flight test run is generally a liquid rocket.
According to the embodiment of the first aspect of the invention, referring to fig. 1, the method for constructing the rocket high-altitude flight test run health monitoring system mainly comprises the following steps:
s100, training and constructing a basic model of the high-altitude flight test run health monitoring system based on the architecture of the health monitoring system of the ground high-modulus test run platform and pre-accumulated ground high-modulus test run data.
S200, acquiring real-time data of high-altitude flight test of the liquid rocket.
S300, after the liquid rocket returns to the ground, inputting real-time data of high-altitude flight test run into the basic model, comparing the real-time data with pre-accumulated ground high-mode test run data, and updating a corresponding data envelope range to form a high-altitude flight test run health monitoring system.
The construction method of the rocket high-altitude flight test run health monitoring system provided by the embodiment of the invention constructs the high-altitude flight test run health monitoring system by utilizing the basic framework of the health monitoring system of the ground high-model test run and the actual data of the high-altitude flight test run, and can realize the continuous optimization of the system, thereby realizing the real-time monitoring of the real condition of the liquid rocket high-altitude flight test run.
According to an embodiment of the invention, the step of training and constructing a basic model of the high-altitude flight test run health monitoring system based on the architecture of the health monitoring system of the ground high-modulus test run platform and pre-accumulated ground high-modulus test run data specifically comprises the following steps:
classifying the pre-accumulated ground high-modulus test run data, and at least dividing the test run data of the tested engine of the liquid rocket, the running data of the ground high-modulus test run platform and the power system data in the launching process of the liquid rocket.
And at least establishing a tested engine health monitoring module 210, an arrow test bed health monitoring module 220 and a power system health monitoring module 230 correspondingly by using the classification data.
The engine health monitoring module 210 to be tested, the arrow test bed health monitoring module 220 and the power system health monitoring module 230 are integrated to construct a basic model, as shown in fig. 2.
In a specific example, when the liquid rocket is used for high-altitude flight test, the liquid rocket generally comprises a power system for providing flight power, a tested engine for high-altitude flight test and a test bed carried on the liquid rocket, namely a test bed on the rocket, wherein the structure of the test bed can be the same as that of a ground high-modulus test bed, so that the pre-accumulated ground high-modulus test data can be effectively utilized to establish the corresponding health monitoring module; in addition, in the high-altitude flight test run process, faults in the test mainly come from devices such as a tested engine, a power system, a test run platform on an arrow and the like, so that the real-time monitoring of the test run process of the main devices can be realized by establishing the health monitoring module.
According to one embodiment of the invention, before the liquid rocket returns to the ground, the method further comprises the following steps:
real-time data of high-altitude flight test run are correspondingly input into a tested engine health monitoring module 210, an arrow test run platform health monitoring module 220 and a power system health monitoring module 230 of a basic model, namely, the real-time data of a tested engine in the high-altitude flight test run process is input into the tested engine health monitoring module 210, the real-time data of the arrow test run platform is input into the arrow test run platform health monitoring module 220, and the real-time data of the power system is input into the power system health monitoring module 230.
The real-time data of the tested engine can comprise: parameters such as the rotating speed of the turbine pump, the pumping pressure of the turbine pump and the surrounding microgravity; real-time data of a test bed on an arrow may include: operating current and voltage, surrounding microgravity and other parameters, and test run normal or abnormal state data; real-time data for the powered system may include: the flow rate of propellants such as oxidizers and combustion agents, the propulsion speed, the track running data and other parameters.
Correspondingly inputting real-time data of high-altitude flight test run into a tested engine health monitoring module 210, an arrow test run platform health monitoring module 220 and a power system health monitoring module 230 of a basic model, and respectively and correspondingly judging whether a tested engine, an arrow test run platform and a power system in the high-altitude flight test run process of the liquid rocket are in a healthy state or not according to preset conditions by the tested engine health monitoring module 210, the arrow test run platform health monitoring module 220 and the power system health monitoring module 230; and determining to continue the trial run or stop returning according to the health state judgment result.
According to an embodiment of the present invention, the steps of respectively and correspondingly judging whether the engine to be tested, the arrow test bed and the power system are in a healthy state in the high-altitude flight test run process of the liquid rocket according to preset conditions by using the engine to be tested health monitoring module 210, the arrow test bed health monitoring module 220 and the power system health monitoring module 230 specifically include:
the engine health monitoring module 210, the rocket test run platform health monitoring module 220 and the power system health monitoring module 230 respectively compare the corresponding real-time data of high-altitude flight test runs with corresponding preset safety values, and when the real-time data of the high-altitude flight test runs are within the range of the preset safety values, the real-time data are judged to be in a healthy state; and when the real-time data of at least one high-altitude flight test run exceeds a preset safety value, judging that the output is in an abnormal state.
And determining to continue the test run or stop returning according to the health state judgment result, specifically comprising:
if the output is the health state, the trial run is determined to be continued, so that more space trial run data are taken as much as possible, and the final high-altitude flight trial run health monitoring system can reflect the normal trial run state more truly.
And if the output is in an abnormal state and the real-time data of the high-altitude flight test run does not reach the explosion critical value, determining to continue the test run and collecting test run data continuously, and when the real-time data of at least one high-altitude flight test run reaches the explosion critical value, starting the emergency shutdown operation of the tested engine by the liquid rocket, stopping the operation of the test run platform on the rocket, and returning the test run platform to the ground through the power system, wherein the explosion critical value is larger than a preset safety value.
It can be understood that, because the environmental conditions of the air test run and the ground high-modulus test run are greatly different, there may exist a situation that the normal data of the air test run is judged to be an abnormal state after being input into the basic model of the high-altitude flight test run health monitoring system, and the abnormal state is not a real state at this time. Thus, the present invention further determines: in the process of real-time monitoring of air test run, if the monitoring result is output and displayed that the test run system does not touch an explosion bottom line, namely an explosion critical value, or does not reach the boundary condition of emergency shutdown, the current test run process is considered to be abnormal in operation but does not need to be interfered, and the test run can be continued.
If the real-time data of one or more dimensions reach an explosion critical value, a shutdown program of the tested engine is automatically started, the rocket-mounted test bed enters a gradually-stopped working state, the whole liquid rocket is recovered, and the rocket-mounted test bed and the tested engine are carried to return to the ground so as to ensure the safety.
According to one embodiment of the invention, after the liquid rocket returns to the ground, the real-time data of the high-altitude flight test run is input into the basic model and compared with the pre-accumulated ground high-mode test run data, and the corresponding data envelope range is updated to form the high-altitude flight test run health monitoring system, which specifically comprises the following steps:
after the liquid rocket returns to the ground, the real-time data of the high-altitude flight test run are correspondingly input into the tested engine health monitoring module 210, the rocket test run table health monitoring module 220 and the power system health monitoring module 230 of the basic model, and are correspondingly compared with the pre-accumulated ground high-modulus test run data, and according to the comparison result, the data envelope ranges in the tested engine health monitoring module 210, the rocket test run table health monitoring module 220 and the power system health monitoring module 230 are updated, so that the high-altitude flight test run health monitoring system is formed.
According to an embodiment of the present invention, the step of updating the corresponding data envelope range specifically includes: the corresponding data envelope range is expanded or reduced.
In other examples, the step of updating the respective data envelope ranges further comprises: adjusting the boundary conditions of emergency shutdown of the test run data, and the like.
It should be noted that the real-time data of the high-altitude flight test run of the present invention includes test run parameters and test run states corresponding to the test run parameters. Specifically, in order to know the real high-altitude test run state, the acquired real-time data and the corresponding actual test run state record are required to be stored and labeled and are supplemented to the corresponding health monitoring module of the basic model, so that the effect of optimizing the model is achieved.
In general, the actual test run state can be divided into: normal test run or abnormal test run.
For example, when the values of parameters such as the turbo pump pressure of the tested engine and the microgravity around the tested engine collected in a certain period of time are all within the range of preset safety values. In this case, the test run is normal if it is not determined to be abnormal. That is to say, if the data collected in a certain time period does not cause an abnormal test run, the actual test run state in the time period is considered to be normal, and the parameter data collected in the time period is uniformly marked as "in normal test run" at the back, and is recorded and stored.
According to one embodiment of the invention, after the high-altitude flight test run health monitoring system is formed, the method further comprises the following steps:
acquiring real-time data of multiple high-altitude flight test runs of the liquid rocket;
after the liquid rocket returns to the ground every time, real-time data of each high-altitude flight test run of the liquid rocket are input into the basic model and are compared and updated with data in the basic model, and the basic model is optimized.
According to the embodiment of the invention, the actual data after each test run is returned to the ground is updated and supplemented into the basic model, so that the high-altitude flight test run health monitoring system can realize monitoring which is closer to the actual test run state, and continuous optimization of the system is realized.
The construction method of the rocket high-altitude flight test-run health monitoring system of the invention is further described with reference to a specific example, which substantially comprises the following steps:
(1) Based on the architecture of the health monitoring system of the ground high-modulus test bed and pre-accumulated ground high-modulus test data, a basic model of the high-altitude flight test health monitoring system is trained and constructed.
(2) The method comprises the steps of collecting real-time data of high-altitude flight test run of the liquid rocket, and storing the real-time data and corresponding test run state records.
(3) And respectively and correspondingly inputting the acquired real-time data into each health monitoring module of the basic model, and judging whether the current tested engine, the arrow test bed and the power system are in a healthy state or not by utilizing preset conditions in the basic model.
(4) And determining to continue the trial run or stop returning according to the health state judgment result.
(5) And after the liquid rocket returns to the ground, supplementing and inputting the acquired real-time data of the high-altitude flight test run into each health monitoring module of the basic model, comparing the acquired real-time data with pre-accumulated ground high-model test run data, and updating a corresponding data envelope range according to a comparison result so as to obtain the high-altitude flight test run health monitoring system.
(6) When the liquid rocket returns to the ground each time, real-time data of each high-altitude flight test run of the liquid rocket is input into the basic model, and the data is compared and updated with the data in the basic model, and the system is optimized.
The construction system of the rocket high-altitude flight test health monitoring system provided by the invention is described below, and the construction system described below and the construction method described above can be correspondingly referred to.
According to the embodiment of the second aspect of the invention, referring to fig. 3, the construction system of the rocket high-altitude flight test run health monitoring system provided by the invention mainly comprises: a build module 310, an acquisition module 320, and a form module 330. The building module 310 is mainly used for training and building a basic model of the high-altitude flight test run health monitoring system based on the architecture of the health monitoring system of the ground high-modulus test run platform and pre-accumulated ground high-modulus test run data; the acquisition module 320 is mainly used for acquiring real-time data of high-altitude flight test run of the liquid rocket; the forming module 330 is mainly used for inputting real-time data of high-altitude flight test run into the basic model after the liquid rocket returns to the ground, comparing the real-time data with pre-accumulated ground high-mode test run data, updating a corresponding data envelope range, and forming the high-altitude flight test run health monitoring system.
According to an embodiment of the third aspect of the present invention, referring to fig. 4, the present invention further provides an electronic device, which may include: a processor (processor) 410, a communication Interface 420, a memory (memory) 430 and a communication bus 440, wherein the processor 410, the communication Interface 420 and the memory 430 are communicated with each other via the communication bus 440. Processor 410 may invoke logic instructions in memory 430 to perform a method of constructing a rocket high altitude flight test health monitoring system, the method comprising: training and constructing a basic model of the high-altitude flight test run health monitoring system based on the architecture of the health monitoring system of the ground high-model test run platform and pre-accumulated ground high-model test run data; acquiring real-time data of high-altitude flight test run of the liquid rocket; and after the liquid rocket returns to the ground, inputting the real-time data of the high-altitude flight test run into the basic model, comparing the real-time data with the pre-accumulated ground high-mode test run data, and updating a corresponding data envelope range to form a high-altitude flight test run health monitoring system.
In addition, the logic instructions in the memory may be implemented in the form of software functional units and may be stored in a computer readable storage medium when sold or used as a stand-alone product. Based on such understanding, the technical solution of the present invention may be embodied in the form of a software product, which is stored in a storage medium and includes instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute all or part of the steps of the method according to the embodiments of the present invention. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk or an optical disk, and other various media capable of storing program codes.
The above-described embodiments of the apparatus are merely illustrative, and the units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of the present embodiment. One of ordinary skill in the art can understand and implement it without inventive effort.
Through the above description of the embodiments, those skilled in the art will clearly understand that each embodiment can be implemented by software plus a necessary general hardware platform, and certainly can also be implemented by hardware. With this understanding in mind, the above-described technical solutions may be embodied in the form of a software product, which can be stored in a computer-readable storage medium such as ROM/RAM, magnetic disk, optical disk, etc., and includes instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute the methods described in the embodiments or some parts of the embodiments.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, and not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (10)
1. A construction method of a rocket high-altitude flight test run health monitoring system is characterized by comprising the following steps:
training and constructing a basic model of the high-altitude flight test run health monitoring system based on the architecture of the health monitoring system of the ground high-model test run platform and pre-accumulated ground high-model test run data;
acquiring real-time data of high-altitude flight test run of the liquid rocket;
and after the liquid rocket returns to the ground, inputting the real-time data of the high-altitude flight test run into the basic model, comparing the real-time data with the pre-accumulated ground high-mode test run data, and updating a corresponding data envelope range to form a high-altitude flight test run health monitoring system.
2. The method for constructing the rocket high-altitude flight test health monitoring system according to claim 1, wherein the step of training and constructing the basic model of the rocket high-altitude flight test health monitoring system based on the architecture of the health monitoring system of the ground high-altitude test bed and pre-accumulated ground high-altitude test data specifically comprises:
classifying the pre-accumulated ground high-modulus test run data, and at least dividing test run data of a tested engine of the liquid rocket, operation data of a ground high-modulus test run and power system data in the liquid rocket launching process;
at least correspondingly establishing a tested engine health monitoring module, a test bench on an arrow health monitoring module and a power system health monitoring module by utilizing the classification data;
and integrating the tested engine health monitoring module, the rocket test bed health monitoring module and the power system health monitoring module to construct the basic model.
3. A method of constructing a rocket high altitude ride test health monitoring system according to claim 2, further comprising the steps of, before the liquid rocket returns to the ground:
correspondingly inputting the real-time data of the high-altitude flight test run into the tested engine health monitoring module, the rocket test run platform health monitoring module and the power system health monitoring module of the basic model;
according to preset conditions, the health monitoring module of the tested engine, the health monitoring module of the test bed on the rocket and the health monitoring module of the power system respectively and correspondingly judge whether the tested engine, the test bed on the rocket and the power system are in a healthy state in the high-altitude flight test process of the liquid rocket;
and determining to continue the trial run or stop returning according to the health state judgment result.
4. A method for constructing a rocket high-altitude flight test run health monitoring system according to claim 3, wherein the step of respectively and correspondingly judging whether the tested engine, the rocket test run platform and the power system are in a healthy state in the liquid rocket high-altitude flight test run process according to preset conditions comprises the following steps:
the tested engine health monitoring module, the rocket test run platform health monitoring module and the power system health monitoring module respectively compare corresponding real-time data of the high-altitude flight test run with corresponding preset safety values, and when the real-time data of the high-altitude flight test run are within the range of the preset safety values, the health state is judged to be output; and when the real-time data of at least one high-altitude flight test run exceeds the preset safety value, judging that the output is in an abnormal state.
5. The method for constructing a rocket high-altitude flight test run health monitoring system according to claim 4, wherein the step of determining to continue the test run or stop returning according to the health state judgment result specifically comprises:
if the output is in a healthy state, determining to continue to test the vehicle;
and if the output is in an abnormal state and the real-time data of the high-altitude flight test run does not reach an explosion critical value, determining to continue the test run, and when the real-time data of at least one high-altitude flight test run reaches the explosion critical value, starting the emergency shutdown operation of the tested engine by the liquid rocket, stopping the operation of the test run table on the rocket, and returning to the ground through the power system, wherein the explosion critical value is larger than the preset safety value.
6. The method for constructing a rocket high-altitude flight test run health monitoring system according to claim 2, wherein after the liquid rocket returns to the ground, real-time data of the high-altitude flight test run is input into the basic model and compared with the pre-accumulated ground high-modulus test run data, a corresponding data envelope range is updated, and the step of forming the high-altitude flight test run health monitoring system specifically comprises the following steps:
after the liquid rocket returns to the ground, the real-time data of the high-altitude flight test run are correspondingly input into the tested engine health monitoring module, the rocket test run table health monitoring module and the power system health monitoring module of the basic model, and are correspondingly compared with the pre-accumulated ground high-model test run data, and according to the comparison result, the data envelope ranges in the tested engine health monitoring module, the rocket test run table health monitoring module and the power system health monitoring module are updated, so that the high-altitude flight test run health monitoring system is formed.
7. A method for constructing a rocket high altitude flight test run health monitoring system according to claim 1, wherein the step of updating the corresponding data envelope range specifically comprises: the corresponding data envelope range is expanded or reduced.
8. A method of constructing a rocket high altitude flight test run health monitoring system according to any one of claims 1-7, further comprising the steps of, after forming said high altitude flight test run health monitoring system:
acquiring real-time data of multiple high-altitude flight test runs of the liquid rocket;
and after the liquid rocket returns to the ground every time, inputting the real-time data of the liquid rocket in each high-altitude flight test run into the basic model, comparing and updating the real-time data with the data in the basic model, and optimizing the basic model.
9. A construction system of a rocket high-altitude flight test run health monitoring system is characterized by comprising the following components:
the building module is used for training and building a basic model of the high-altitude flight test run health monitoring system based on the architecture of the health monitoring system of the ground high-modulus test run platform and pre-accumulated ground high-modulus test run data;
the acquisition module is used for acquiring real-time data of high-altitude flight test run of the liquid rocket;
and the forming module is used for inputting the real-time data of the high-altitude flight test run into the basic model after the liquid rocket returns to the ground, comparing the real-time data with the pre-accumulated ground high-modulus test run data, updating a corresponding data envelope range and forming the high-altitude flight test run health monitoring system.
10. An electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, wherein the processor when executing the program implements a method of constructing a rocket high altitude flight trial health monitoring system as claimed in any one of claims 1 to 8.
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110017992A (en) * | 2019-05-16 | 2019-07-16 | 九州云箭(北京)空间科技有限公司 | A kind of liquid rocket dynamical system test run method and its device |
| US20200003444A1 (en) * | 2018-07-02 | 2020-01-02 | Carrier Corporation | Commissioning method and commissioning system |
| CN113155467A (en) * | 2021-01-19 | 2021-07-23 | 中国人民解放军63921部队 | Online health management method based on advanced shutdown of liquid rocket sublevel engine |
| CN113569472A (en) * | 2021-07-16 | 2021-10-29 | 中山大学 | Fault detection method, system, equipment and medium for liquid rocket engine |
| CN114459762A (en) * | 2020-12-25 | 2022-05-10 | 北京天兵科技有限公司 | Rocket engine health state diagnosis system and method |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20200003444A1 (en) * | 2018-07-02 | 2020-01-02 | Carrier Corporation | Commissioning method and commissioning system |
| CN110017992A (en) * | 2019-05-16 | 2019-07-16 | 九州云箭(北京)空间科技有限公司 | A kind of liquid rocket dynamical system test run method and its device |
| CN114459762A (en) * | 2020-12-25 | 2022-05-10 | 北京天兵科技有限公司 | Rocket engine health state diagnosis system and method |
| CN113155467A (en) * | 2021-01-19 | 2021-07-23 | 中国人民解放军63921部队 | Online health management method based on advanced shutdown of liquid rocket sublevel engine |
| CN113569472A (en) * | 2021-07-16 | 2021-10-29 | 中山大学 | Fault detection method, system, equipment and medium for liquid rocket engine |
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