CN116680507B - Method, system and device for automatically determining combustion time of solid rocket engine - Google Patents
Method, system and device for automatically determining combustion time of solid rocket engine Download PDFInfo
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Abstract
The application discloses a method, a system, electronic equipment and a storage medium for automatically determining the combustion time of a solid rocket engine. The method solves the technical problem of larger calculation error of the existing rocket engine combustion time tb in the related technology, can be used as an artificial double tangent method to be applied to solid rocket engine combustion speed test, avoids calculation error caused by human factors, improves calculation stability, improves calculation processing efficiency, realizes automation and intellectualization of a data processing process, and has more accurate processing result.
Description
Technical Field
The application belongs to the technical field of solid rocket engine testing, and particularly relates to a method, a system and a device for automatically determining the combustion time of a solid rocket engine.
Background
In the technical field of solid rocket engine testing, the calculation of the combustion time tb of the solid rocket engine has a direct influence on the accuracy of the grain combustion speed, and also has an important influence on the calculation of a series of parameters including the pressure ram, the total ram, the average thrust and the like.
In the related technology, the existing method for determining the combustion time tb through the P-t curve is mainly based on the principle of an artificial double tangent method, namely, the tangent line of a stable section and the tangent line of a descending section are obtained, and the moment corresponding to the intersection point of the bisector of the two tangent angles and the P-t curve is taken as the combustion termination moment.
Aiming at the technical problem of larger error in solving the existing rocket engine combustion time tb in the related art, no effective solution is proposed yet.
Disclosure of Invention
Therefore, an embodiment of the present application is to provide a method, an apparatus, an electronic device, and a storage medium for automatically determining a combustion time of a solid rocket engine, which aim to solve at least one problem existing in the prior art.
To achieve the above object, in a first aspect, the present application provides a method for automatically determining a combustion time of a solid rocket engine, including:
scanning and collecting a pressure signal P of an engine combustion chamber at a preset speed, and performing noise reduction treatment on the pressure signal P to obtain a pressure time curve S1;
Taking a preset interval as a step length, solving a fitting curve of the middle point of each preset interval on the pressure time curve S1 by using a least square method, and taking the slope of the fitting curve as the approximate derivative of the middle point of the corresponding interval to obtain a first derivative curve S2 of the interval;
Acquiring extreme points with the offset of 0 point exceeding a preset value from the first derivative curve S2, wherein the first maximum value is corresponding to a transverse sitting mark of x 0, if the distance between the first minimum value and the first maximum value is smaller than the preset percentage of the whole length of the first derivative curve S 2, the second minimum value is corresponding to the transverse sitting mark of x 1, and if not, the first minimum value is corresponding to the transverse sitting mark of x 1;
Acquiring a continuous target interval meeting preset conditions on the first derivative curve S2, and marking the maximum interval range as [ x 2,x3 ], and marking the interval closest to x 1 as [ x 4,x5 ];
Average pressure intensity within the interval [5x 2-4,5x3 ] is calculated on the pressure time curve S1 And determining a combustion start time t 1;
On the pressure-time curve S1, in the interval The inner average selects 11 data points, a polynomial fitting is used for obtaining a fitting curve of the group of data points and obtaining a midpoint tangent l 1 of the fitting curve, 5x 1 -3 is used as the midpoint of the pressure time curve S1, 11 data points close to the midpoint are selected, and a polynomial fitting is used for obtaining a fitting curve of the group of data points and obtaining a midpoint tangent l 2;
Obtaining a combustion termination time t 2 at a time corresponding to the intersection point of the angular bisectors of the tangent line l 1 and the tangent line l 2 and the curve S 1;
And calculating the combustion time according to the combustion starting time t 1 and the combustion ending time t 2.
In one embodiment, the calculating the combustion time according to the combustion start time t 1 and the combustion end time t 2 includes: the combustion time is obtained by subtracting the combustion start time t 1 from the combustion end time t 2.
In one embodiment, the preset rate is n points/second, the preset interval is 5, the preset value is 0.005, the preset percentage is 10%, the preset condition is an interval in which the first condition and the second condition are met simultaneously, wherein the first condition is a value within + -0.003, and the second condition is a value within an interval [ x 0,x1 ].
In one embodiment, the determining the combustion start time t 1 includes: on the pressure time curve S 1, the nearest is found in the interval [0,5x 0 ]The point corresponding time is determined as the combustion start time t 1.
In one embodiment, the obtaining the first derivative curve S2 of the interval by using the slope of the fitted curve as the approximate derivative of the midpoint of the corresponding interval includes: the slope of the fitting curve is taken as the approximate derivative of the midpoint of the corresponding interval to obtain a first derivative curve S2 of the interval, wherein the calculation formula of the approximate derivative is as follows
In a second aspect, the present application also provides a system for automatically determining the combustion time of a solid rocket engine, comprising:
the first module is used for scanning and collecting a pressure signal P of a combustion chamber of the engine at a preset speed, and carrying out noise reduction treatment on the pressure signal P to obtain a pressure time curve S1;
The second module is used for obtaining a fitting curve of the middle point of each preset interval on the pressure time curve S1 by using a least square method by taking the preset interval as a step length, and obtaining a first derivative curve S2 of the interval by taking the slope of the fitting curve as the approximate derivative of the middle point of the corresponding interval;
A third module, configured to obtain, on the first derivative curve S2, all extreme points with offset from 0 points exceeding a preset value, where a first maximum of the class corresponds to a transverse sitting mark x 0, and if a distance between the first minimum of the class and the first maximum of the class is smaller than a preset percentage of an overall length of the first derivative curve S 2, a second minimum of the class corresponds to a transverse sitting mark x 1, and if not, the first minimum of the class corresponds to a transverse sitting mark x 1;
A fourth module, configured to obtain a continuous target interval meeting a preset condition on the first derivative curve S2, and record a maximum interval range as [ x 2,x3 ], and a interval closest to x 1 as [ x 4,x5 ];
a fifth module for calculating average pressure intensity in the interval [5x 2-4,5x3 ] on the pressure time curve S1 And determining a combustion start time t 1;
a sixth module for, on said pressure time curve S1, in the interval The inner average selects 11 data points, a polynomial fitting is used for obtaining a fitting curve of the group of data points and obtaining a midpoint tangent l 1 of the fitting curve, 5x 1 -3 is used as the midpoint of the pressure time curve S1, 11 data points close to the midpoint are selected, and a polynomial fitting is used for obtaining a fitting curve of the group of data points and obtaining a midpoint tangent l 2;
A seventh module, configured to obtain a combustion termination time t 2 at a time corresponding to an intersection point of the angular bisectors of the tangent line l 1 and the tangent line l 2 and the curve S 1;
And an eighth module, configured to calculate a combustion time according to the combustion start time t 1 and the combustion end time t 2.
In one embodiment, the calculating the combustion time according to the combustion start time t 1 and the combustion end time t 2 includes: the combustion time is obtained by subtracting the combustion start time t 1 from the combustion end time t 2.
In one embodiment, the preset rate is n points/second, the preset interval is 5, the preset value is 0.005, the preset percentage is 10%, the preset condition is an interval in which the first condition and the second condition are met simultaneously, wherein the first condition is a value within + -0.003, and the second condition is a value within an interval [ x 0,x1 ].
In a third aspect, the present application also provides an electronic device comprising a memory and a processor, the memory having stored therein a computer program which, when executed by the processor, causes the processor to perform the steps of the method of automatically determining the combustion time of a solid rocket engine.
In a fourth aspect, the present application also provides a computer readable storage medium having stored thereon a computer program which, when executed by a processor, causes the processor to perform the steps of the method of automatically determining the combustion time of a solid rocket engine.
According to the method, the system, the electronic equipment and the storage medium for automatically determining the combustion time of the solid rocket engine, the actual pressure-time curve of the propellant test run of the solid rocket engine is firstly obtained, the pressure value P is subjected to noise reduction treatment, then the pressure is subjected to derivative calculation point by point to obtain an approximate first derivative curve, the combustion termination time and the combustion stability are determined according to conditions on the approximate first derivative curve, finally the combustion start time is determined by substituting the pressure-time curve, and further the combustion time is determined. The method solves the technical problem of larger calculation error of the existing rocket engine combustion time tb in the related technology, can be used as an artificial double tangent method to be applied to solid rocket engine combustion speed test, avoids calculation error caused by human factors, improves calculation stability, improves calculation processing efficiency, realizes automation and intellectualization of a data processing process, and has more accurate processing result.
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The accompanying drawings, which are included to provide a further understanding of the application, are incorporated in and constitute a part of this specification. The drawings and their description are illustrative of the application and are not to be construed as unduly limiting the application. In the drawings:
FIG. 1 is a flow chart of an implementation of a method for automatically determining the combustion time of a solid rocket engine according to an embodiment of the present application;
FIG. 2 is a schematic diagram of the main modules of the system for automatically determining the combustion time of a solid rocket engine according to the embodiment of the present application;
FIG. 3 is a diagram of an exemplary system architecture to which embodiments of the present application may be applied;
fig. 4 is a schematic diagram of a computer system suitable for use in implementing an embodiment of the application.
Detailed Description
In order that those skilled in the art will better understand the present application, a technical solution in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in which it is apparent that the described embodiments are only some embodiments of the present application, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the present application without making any inventive effort, shall fall within the scope of the present application.
It should be noted that the terms "first," "second," and the like in the description and the claims of the present application and the above figures are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate in order to describe the embodiments of the application herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
In the present application, the terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal" and the like indicate an azimuth or a positional relationship based on that shown in the drawings. These terms are only used to better describe the present application and its embodiments and are not intended to limit the scope of the indicated devices, elements or components to the particular orientations or to configure and operate in the particular orientations.
Also, some of the terms described above may be used to indicate other meanings in addition to orientation or positional relationships, for example, the term "upper" may also be used to indicate some sort of attachment or connection in some cases. The specific meaning of these terms in the present application will be understood by those of ordinary skill in the art according to the specific circumstances.
In addition, the term "plurality" shall mean two as well as more than two.
It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other. The application will be described in detail below with reference to the drawings in connection with embodiments.
Fig. 1 shows an implementation flow of a method for automatically determining combustion time of a solid rocket engine according to an embodiment of the present application. For convenience of explanation, only the portions related to the embodiments of the present application are shown, and the details are as follows:
a method for automatically determining the combustion time of a solid rocket engine, comprising the steps of:
s101: scanning and collecting a pressure signal P of an engine combustion chamber at a preset speed, and performing noise reduction treatment on the pressure signal P to obtain a pressure time curve S1;
S102: taking a preset interval as a step length, solving a fitting curve of the middle point of each preset interval on the pressure time curve S1 by using a least square method, and taking the slope of the fitting curve as the approximate derivative of the middle point of the corresponding interval to obtain a first derivative curve S2 of the interval;
S103: acquiring extreme points with the offset of 0 point exceeding a preset value from the first derivative curve S2, wherein the first maximum value is corresponding to a transverse sitting mark of x 0, if the distance between the first minimum value and the first maximum value is smaller than the preset percentage of the whole length of the first derivative curve S 2, the second minimum value is corresponding to the transverse sitting mark of x 1, and if not, the first minimum value is corresponding to the transverse sitting mark of x 1;
s104: acquiring a continuous target interval meeting preset conditions on the first derivative curve S2, and marking the maximum interval range as [ x 2,x3 ], and marking the interval closest to x 1 as [ x 4,x5 ];
S105: average pressure intensity within the interval [5x 2-4,5x3 ] is calculated on the pressure time curve S1 And determining a combustion start time t 1;
s106: on the pressure-time curve S1, in the interval The inner average selects 11 data points, a polynomial fitting is used for obtaining a fitting curve of the group of data points and obtaining a midpoint tangent l 1 of the fitting curve, 5x 1 -3 is used as the midpoint of the pressure time curve S1, 11 data points close to the midpoint are selected, and a polynomial fitting is used for obtaining a fitting curve of the group of data points and obtaining a midpoint tangent l 2;
S107: obtaining a combustion termination time t 2 at a time corresponding to the intersection point of the angular bisectors of the tangent line l 1 and the tangent line l 2 and the curve S 1;
s108: and calculating the combustion time according to the combustion starting time t 1 and the combustion ending time t 2.
In one embodiment, the calculating the combustion time according to the combustion start time t 1 and the combustion end time t 2 includes: the combustion time is obtained by subtracting the combustion start time t 1 from the combustion end time t 2.
In one embodiment, the preset rate is n points/second, the preset interval is 5, the preset value is 0.005, the preset percentage is 10%, the preset condition is an interval in which the first condition and the second condition are met simultaneously, wherein the first condition is a value within + -0.003, and the second condition is a value within an interval [ x 0,x1 ].
In one embodiment, the determining the combustion start time t 1 includes: on the pressure time curve S 1, the nearest is found in the interval [0,5x 0 ]The point corresponding time is determined as the combustion start time t 1.
In one embodiment, the obtaining the first derivative curve S2 of the interval by using the slope of the fitted curve as the approximate derivative of the midpoint of the corresponding interval includes: the slope of the fitting curve is taken as the approximate derivative of the midpoint of the corresponding interval to obtain a first derivative curve S2 of the interval, wherein the calculation formula of the approximate derivative is as follows
In a specific embodiment, the method for automatically determining the combustion time of the solid rocket engine provided by the embodiment of the application comprises the following steps:
Step 1: scanning and collecting a pressure signal P of a combustion chamber of the engine at the rate of n points/second, and performing noise reduction treatment on the signal to obtain a pressure-time curve S 1 after treatment;
Step 2: taking 5 as interval step length on the processed pressure-time curve, utilizing a least square method to obtain a midpoint fitting curve in each interval, taking the slope of the curve as the approximate derivative of the midpoint of the interval to obtain an approximate first derivative curve S 2, wherein the calculation formula of the approximate derivative of the point is
Step 3: on the curve S 2 obtained in the step 2, all extreme points with the offset of 0 being more than 0.005 are obtained, and the first maximum value corresponds to the transverse sitting mark as x 0. If the distance between the first such minimum value and the first such maximum value is smaller than 10% of the overall length of the curve S 2, the second such minimum value corresponds to the transverse sitting mark x 1, and if not, the first such minimum value corresponds to the transverse sitting mark x 1;
Step 4: on a curve S 2, acquiring a value which meets the condition 1 simultaneously to be within +/-0.003; condition 2 is a continuous interval within the interval [ x 0,x1 ], where the largest interval range is denoted as [ x 2,x3 ], and the interval closest to x 1 is denoted as [ x 4,x5 ];
Step 5: on curve S 1, average pressure intensity within the calculation interval [5x 2-4,5x3 ] And determines the combustion start time t 1 based on this by finding the closest/>, within the interval [0,5x 0 ], at S 1 The corresponding moment of the point is t 1;
Step 6: on curve S 1, in the interval The inner average selects 11 data points, a polynomial fitting is utilized to obtain a set of data point fitting curves, 3-5 steps are generally adopted as appropriate, a midpoint tangent l 1 is obtained, 5x 1 -3 is taken as a midpoint, a polynomial fitting is utilized to obtain the set of data point fitting curves from 11 adjacent data points, the order is consistent with the order, and a midpoint tangent l 2 is obtained;
Step 7: the corresponding time t 2 of the intersection point of the angular bisector of the tangent line l 1,l2 and the curve S 1 is the combustion termination time;
Step 8: combustion time tb=t 2-t1.
In another embodiment, step 3 may further be: and (2) acquiring extreme points with the offset of 0 exceeding 0.005 from the curve s obtained in the step (2), wherein the first maximum value is marked as x 0, and the corresponding moment of the x 0 on the P-t curve is approximate ignition peak moment t 0. If the distance between the first type minimum value and the first type maximum value is smaller than 10% of the whole length of the curve s, the corresponding moment of the second type minimum value x 2 on the P-t curve is approximate ignition peak moment t 1, and if not, the corresponding moment of the first type minimum value x 1 on the P-t curve is approximate ignition peak moment t 1.
Therefore, the method for automatically determining the combustion time of the solid rocket engine provided by the embodiment of the application comprises the steps of firstly obtaining an actual pressure-time curve of a solid rocket engine propellant test run, secondly carrying out noise reduction treatment on a pressure value P, then carrying out derivative calculation on the pressure point by point to obtain an approximate first derivative curve, determining the combustion termination time and the combustion stability section on the approximate first derivative curve according to conditions, and finally determining the combustion start time after substituting the pressure-time curve, thereby determining the combustion time. The method solves the technical problem of larger calculation error of the existing rocket engine combustion time tb in the related technology, can be used as an artificial double tangent method to be applied to solid rocket engine combustion speed test, avoids calculation error caused by human factors, improves calculation stability, improves calculation processing efficiency, realizes automation and intellectualization of a data processing process, and has more accurate processing result.
Fig. 2 is a schematic diagram of main modules of an automatic determining combustion time system of a solid rocket engine according to an embodiment of the present application, and for convenience of explanation, only the parts related to the embodiment of the present application are shown, which is described in detail below:
An automatic determination solid rocket engine combustion time system 200 comprising:
a first module 201, configured to scan and collect a pressure signal P of an engine combustion chamber at a preset rate, and perform noise reduction processing on the pressure signal P to obtain a pressure time curve S1;
A second module 202, configured to calculate a fitted curve of a midpoint of each preset interval on the pressure time curve S1 by using a least square method with the preset interval as a step length, and obtain a first derivative curve S2 of the interval by using a slope of the fitted curve as an approximate derivative of the midpoint of the corresponding interval;
A third module 203, configured to obtain, on the first derivative curve S2, all extreme points with offset from 0 point exceeding a preset value, where a first maximum of the class corresponds to a abscissa mark x 0, and if a distance between the first minimum of the class and the first maximum of the class is smaller than a preset percentage of an overall length of the first derivative curve S 2, a second minimum of the class corresponds to an abscissa mark x 1, and if not, the first minimum of the class corresponds to an abscissa mark x 1;
A fourth module 204, configured to obtain a continuous target interval meeting a preset condition on the first derivative curve S2, and record a maximum interval range as [ x 2,x3 ], and a interval closest to x 1 as [ x 4,x5 ];
A fifth module 205 for calculating average pressure intensity within the interval [5x 2-4,5x3 ] on the pressure time curve S1 And determining a combustion start time t 1;
A sixth module 206 for, on said pressure time curve S1, in the interval The inner average selects 11 data points, a polynomial fitting is used for obtaining a fitting curve of the group of data points and obtaining a midpoint tangent l 1 of the fitting curve, 5x 1 -3 is used as the midpoint of the pressure time curve S1, 11 data points close to the midpoint are selected, and a polynomial fitting is used for obtaining a fitting curve of the group of data points and obtaining a midpoint tangent l 2;
A seventh module 207, configured to obtain a combustion termination time t 2 at a time corresponding to an intersection point of the angular bisectors of the tangent line l 1 and the tangent line l 2 and the curve S 1;
An eighth module 208 is configured to calculate a combustion time according to the combustion start time t 1 and the combustion end time t 2.
In one embodiment, the calculating the combustion time according to the combustion start time t 1 and the combustion end time t 2 includes: the combustion time is obtained by subtracting the combustion start time t 1 from the combustion end time t 2.
In one embodiment, the preset rate is n points/second, the preset interval is 5, the preset value is 0.005, the preset percentage is 10%, the preset condition is an interval in which the first condition and the second condition are met simultaneously, wherein the first condition is a value within + -0.003, and the second condition is a value within an interval [ x 0,x1 ].
It should be noted that, the automatic determining solid rocket engine combustion time system according to the embodiment of the present application configures the method for automatically determining solid rocket engine combustion time corresponding to the embodiment of the present application, and other embodiments of the automatic determining solid rocket engine combustion time system correspond to all embodiments of the method for automatically determining solid rocket engine combustion time, which is not described herein.
Therefore, the system for automatically determining the combustion time of the solid rocket engine provided by the embodiment of the application firstly obtains an actual pressure-time curve of a solid rocket engine propellant test run, secondly carries out noise reduction treatment on a pressure value P, and then carries out derivative calculation on the pressure point by point to obtain an approximate first derivative curve, determines the combustion termination time and the combustion stability section on the approximate first derivative curve according to conditions, and finally returns to the pressure-time curve to determine the combustion start time so as to determine the combustion time. The method solves the technical problem of larger calculation error of the existing rocket engine combustion time tb in the related technology, can be used as an artificial double tangent method to be applied to solid rocket engine combustion speed test, avoids calculation error caused by human factors, improves calculation stability, improves calculation processing efficiency, realizes automation and intellectualization of a data processing process, and has more accurate processing result.
The embodiment of the application also provides electronic equipment, which comprises: one or more processors; and the storage device is used for storing one or more programs, and when the one or more programs are executed by the one or more processors, the one or more processors realize the method for automatically determining the combustion time of the solid rocket engine.
The embodiment of the application also provides a computer readable medium, on which a computer program is stored, which when executed by a processor, implements the method for automatically determining the combustion time of the solid rocket engine according to the embodiment of the application.
FIG. 3 illustrates an exemplary system architecture 300 for automatically determining a solid rocket engine combustion time method or apparatus to which embodiments of the present application may be applied.
As shown in fig. 3, the system architecture 300 may include terminal devices 301, 302, 303, a network 304, and a server 305. The network 304 is used as a medium to provide communication links between the terminal devices 301, 302, 303 and the server 305. The network 304 may include various connection types, such as wired, wireless communication links, or fiber optic cables, among others.
A user may interact with the server 305 via the network 304 using the terminal devices 301, 302, 303 to receive or send messages or the like. Various communication client applications, such as shopping class applications, web browser applications, search class applications, instant messaging tools, mailbox clients, social platform software, etc., may be installed on the terminal devices 301, 302, 303.
The terminal devices 301, 302, 303 may be a variety of electronic devices having a display screen and supporting web browsing, including but not limited to smartphones, tablets, laptop and desktop computers, and the like.
The server 305 may be a server providing various services, such as a background management server providing support for user messages sent to and from the terminal devices 301, 302, 303. The background management server can perform analysis and other processes after receiving the terminal equipment request, and feed back the processing result to the terminal equipment.
It should be noted that, the method for automatically determining the combustion time of the solid rocket engine provided by the embodiment of the present application is generally executed by the terminal device 301, 302, 303 or the server 305, and accordingly, the system for automatically determining the combustion time of the solid rocket engine is generally disposed in the terminal device 301, 302, 303 or the server 305.
It should be understood that the number of terminal devices, networks and servers in fig. 3 is merely illustrative. There may be any number of terminal devices, networks, and servers, as desired for implementation.
Referring now to FIG. 4, there is illustrated a schematic diagram of a computer system 400 suitable for use in implementing a terminal device or server in accordance with an embodiment of the present application. The computer system shown in fig. 4 is merely an example, and should not be construed as limiting the functionality and scope of use of embodiments of the present application.
As shown in fig. 4, the computer system 400 includes a Central Processing Unit (CPU) 401, which can perform various appropriate actions and processes according to a program stored in a Read Only Memory (ROM) 402 or a program loaded from a storage section 408 into a Random Access Memory (RAM) 403. In RAM 403, various programs and data required for the operation of system 400 are also stored. The CPU 401, ROM 402, and RAM 403 are connected to each other by a bus 404. An input/output (I/O) interface 405 is also connected to bus 404.
The following components are connected to the I/O interface 405: an input section 406 including a keyboard, a mouse, and the like; an output portion 407 including a Cathode Ray Tube (CRT), a Liquid Crystal Display (LCD), and the like, and a speaker, and the like; a storage section 408 including a hard disk or the like; and a communication section 409 including a network interface card such as a LAN card, a modem, or the like. The communication section 409 performs communication processing via a network such as the internet. The drive 410 is also connected to the I/O interface 405 as needed. A removable medium 411 such as a magnetic disk, an optical disk, a magneto-optical disk, a semiconductor memory, or the like is installed on the drive 410 as needed, so that a computer program read therefrom is installed into the storage section 408 as needed.
In particular, according to embodiments of the present disclosure, the processes described above with reference to flowcharts may be implemented as computer software programs. For example, embodiments of the present disclosure include a computer program product comprising a computer program embodied on a computer readable medium, the computer program comprising program code for performing the method shown in the flow chart. In such an embodiment, the computer program may be downloaded and installed from a network via the communication portion 409 and/or installed from the removable medium 411. The above-described functions defined in the system of the present application are performed when the computer program is executed by a Central Processing Unit (CPU) 401.
The computer readable medium shown in the present application may be a computer readable signal medium or a computer readable storage medium, or any combination of the two. The computer readable storage medium can be, for example, but not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or a combination of any of the foregoing. More specific examples of the computer-readable storage medium may include, but are not limited to: an electrical connection having one or more wires, a portable computer diskette, a hard disk, a Random Access Memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing. In the context of this document, a computer readable storage medium may be any tangible medium that can contain, or store a program for use by or in connection with an instruction execution system, apparatus, or device. In the present application, however, the computer-readable signal medium may include a data signal propagated in baseband or as part of a carrier wave, with the computer-readable program code embodied therein. Such a propagated data signal may take any of a variety of forms, including, but not limited to, electro-magnetic, optical, or any suitable combination of the foregoing. A computer readable signal medium may also be any computer readable medium that is not a computer readable storage medium and that can communicate, propagate, or transport a program for use by or in connection with an instruction execution system, apparatus, or device. Program code embodied on a computer readable medium may be transmitted using any appropriate medium, including but not limited to: wireless, wire, fiber optic cable, RF, etc., or any suitable combination of the foregoing.
The flowcharts and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of systems, methods and computer program products according to various embodiments of the present application. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that, in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams or flowchart illustration, and combinations of blocks in the block diagrams or flowchart illustration, can be implemented by special purpose hardware-based systems which perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.
The modules involved in the embodiments of the present application may be implemented in software or in hardware. The described modules may also be provided in a processor, for example, as: a processor includes a determination module, an extraction module, a training module, and a screening module. Where the names of the modules do not constitute a limitation on the module itself in some cases, the determination module may also be described as "module for determining a candidate set of users", for example.
The foregoing examples illustrate only a few embodiments of the application and are described in detail herein without thereby limiting the scope of the application. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the application, which are all within the scope of the application. Accordingly, the scope of protection of the present application is to be determined by the appended claims.
The above description is only of the preferred embodiments of the present application and is not intended to limit the present application, but various modifications and variations can be made to the present application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.
Claims (6)
1. A method for automatically determining the combustion time of a solid rocket engine, comprising:
scanning and collecting a pressure signal P of a combustion chamber of an engine at the speed of n points/second, and performing noise reduction treatment on the pressure signal P to obtain a pressure time curve S1;
Taking 5 as interval step length, utilizing a least square method to obtain a fitting curve of each interval midpoint on the pressure time curve S1, taking the curve slope of the fitting curve as the approximate derivative of the corresponding interval midpoint to obtain a first derivative curve S2 of the interval, wherein an approximate derivative calculation formula is as follows
Acquiring extreme points with the offset of more than 0.005 from the 0 point on the first derivative curve S2, wherein a first maximum value corresponds to a transverse sitting mark of x 0, if the distance between the first minimum value and the first maximum value is less than 10% of the whole length of the first derivative curve S 2, a second minimum value corresponds to a transverse sitting mark of x 1, and if not, the first minimum value corresponds to a transverse sitting mark of x 1;
acquiring a continuous target interval of which the value of the first derivative curve S2 is within +/-0.003 and within an interval [ X 0,X1 ] on the first derivative curve S2, and recording the maximum interval range as [ X 2,x3 ] and the interval closest to X 1 as [ X 4,x5 ];
average pressure intensity within the interval [5x 2-4,5x3 ] is calculated on the pressure time curve S1 And determining the combustion start time t 1, specifically, on the curve S 1, searching the nearest/> in the interval [0,5x 0 ]The corresponding moment of the point is t 1;
On the pressure-time curve S1, in the interval The inner average selects 11 data points, a polynomial fitting is used for obtaining a fitting curve of the data points and obtaining a midpoint tangent I 1 of the fitting curve, 5x 1 -3 is used as the midpoint of the pressure time curve S1, 11 data points close to the midpoint are selected, and a polynomial fitting is used for obtaining a fitting curve of the data points and obtaining a midpoint tangent I 2;
Obtaining a combustion termination time t 2 at a time corresponding to the intersection point of the angular bisectors of the tangent line I 1 and the tangent line I 2 and the curve S 1;
And calculating the combustion time according to the combustion starting time t 1 and the combustion ending time t 2.
2. A method for automatically determining a combustion time of a solid rocket engine as recited in claim 1, wherein said calculating a combustion time from said combustion start time t 1 and combustion end time t 2 comprises: the combustion time is obtained by subtracting the combustion start time t 1 from the combustion end time t 2.
3. A system for automatically determining the combustion time of a solid rocket engine, comprising:
The first module is used for scanning and collecting a pressure signal P of a combustion chamber of the engine at the speed of n points/second, and carrying out noise reduction treatment on the pressure signal P to obtain a pressure time curve S1;
A second module for obtaining a fitting curve of each interval midpoint on the pressure time curve S1 by using 5 as interval step length and utilizing a least square method, and obtaining a first derivative curve S2 of the interval by taking the curve slope of the fitting curve as the approximate derivative of the corresponding interval midpoint, wherein the approximate derivative calculation formula is as follows
A third module, configured to obtain, on the first derivative curve S2, all extreme points with offset from 0 point exceeding 0.005, where a first maximum corresponds to a abscissa mark x 0, if a distance between the first minimum and the first maximum is less than 10% of an overall length of the first derivative curve S 2, a second minimum corresponds to an abscissa mark x 1, and if not, the first minimum corresponds to an abscissa mark x 1;
A fourth module, configured to obtain, on the first derivative curve S2, a continuous target interval in which the value of the first derivative curve S2 is within ±0.003 and within an interval [ X 0,X1 ], and record a maximum interval range as [ X 2,x3 ], and record an interval closest to X 1 as [ X 4,x5 ];
A fifth module for calculating average pressure intensity in the interval [5x 2-4,5x3 ] on the pressure time curve S1 And determining the combustion start time t 1, specifically, on the curve S 1, searching the nearest/> in the interval [0,5x 0 ]The corresponding moment of the point is t 1;
a sixth module for, on said pressure time curve S1, in the interval The inner average selects 11 data points, a polynomial fitting is used for obtaining a fitting curve of the data points and obtaining a midpoint tangent I 1 of the fitting curve, 5x 1 -3 is used as the midpoint of the pressure time curve S1, 11 data points close to the midpoint are selected, and a polynomial fitting is used for obtaining a fitting curve of the data points and obtaining a midpoint tangent I 2;
A seventh module, configured to obtain a combustion termination time t 2 at a time corresponding to an intersection point of the angular bisectors of the tangent line I 1 and the tangent line I 2 and the curve S 1;
And an eighth module, configured to calculate a combustion time according to the combustion start time t 1 and the combustion end time t 2.
4. An automatically determining solid rocket engine combustion time system as recited in claim 3, wherein said calculating combustion time from said combustion start time t 1 and combustion end time t 2 comprises: the combustion time is obtained by subtracting the combustion start time t 1 from the combustion end time t 2.
5. An electronic device comprising a memory and a processor, the memory having stored therein a computer program which, when executed by the processor, causes the processor to perform the steps of the method of automatically determining the combustion time of a solid rocket engine of any one of claims 1-2.
6. A computer readable storage medium, characterized in that the computer readable storage medium has stored thereon a computer program which, when executed by a processor, causes the processor to perform the steps of the method for automatically determining the combustion time of a solid rocket engine according to any one of claims 1 to 2.
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