CN114877760B - Polarity testing method and system for spacecraft - Google Patents
Polarity testing method and system for spacecraft Download PDFInfo
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Abstract
The invention provides a polarity testing method and system for a spacecraft, wherein the method comprises the following steps: acquiring real-time state data of a part to be tested through at least one acquisition device arranged on the part to be tested of the spacecraft; filtering the real-time state data to obtain a processing result; and carrying out polarity test processing on the processing result according to a preset polarity test starting instruction and a preset polarity test threshold of preset control equipment to obtain a polarity test result. The scheme of the invention can realize automatic polarity test discrimination, effectively avoid potential quality hidden danger, improve product reliability, generate corresponding effective test data and have traceability.
Description
Technical Field
The invention relates to the technical field of testing of spacecrafts, in particular to a method and a system for testing the polarity of a spacecraft.
Background
At present, the mainstream carrier rocket needs to be subjected to rocket overall test after the overall assembly work is finished, the overall test mainly examines the coordination and matching among all systems of the carrier rocket and comprehensively examines the overall performance, reliability and flight indexes of the carrier rocket, and the test technology is related to the comprehensiveness and accuracy of rocket performance index examination and is a key technology for objectively evaluating the performance of the rocket.
The polarity test is an important index assessment item in the overall test stage of the carrier rocket system, and the polarity test is mainly used for assessing whether a servo system and a final-repair attitude control correction system correctly respond to an instruction of a carrier rocket attitude control system and timely and accurately correcting the attitude of the rocket body. During the existing polarity test, manual qualitative judgment is mainly carried out by observing the motion of an execution part of a servo system and the opening and closing conditions of an electromagnetic valve of a final correction attitude control correction system, and multimedia shooting recording is carried out;
however, there are several problems in that the tester can observe the movement track of the execution component and/or listen to the opening and closing sound of the electromagnetic valve to judge on site: firstly, the capability of testers is uneven, the risks of misjudgment and missed judgment are observed, and the reliability of a product cannot be guaranteed; secondly, the recording method cannot generate test data, which is not beneficial to the review and comparison of product test data; then, the multimedia image data has poor recording effect and limited reference value; finally, for the carrier rocket with the booster provided with the servo system, the observation of the test phenomenon is more complex, the motion trail of the execution part of each booster servo system needs to be interpreted in a correlation mode, the number and the capability of observers have higher requirements, and the motion trail of the execution part of each booster servo system cannot be recorded in the same image by multimedia shooting.
Disclosure of Invention
The invention aims to provide a method and a system for testing the polarity of a spacecraft. The polarity testing method has the advantages that automatic polarity testing discrimination is realized, potential quality hidden danger is effectively avoided, product reliability is improved, corresponding effective testing data can be generated, and traceability is realized.
In order to solve the technical problems, the technical scheme of the invention is as follows:
a method of polarity testing of a spacecraft, comprising:
acquiring real-time state data of a part to be tested through at least one acquisition device arranged on the part to be tested of the spacecraft;
filtering the real-time state data to obtain a processing result;
and carrying out polarity test processing on the processing result according to a preset polarity test starting instruction and a preset polarity test threshold of preset control equipment to obtain a polarity test result.
Optionally, the filtering the real-time status data to obtain a processing result includes:
and carrying out interference data filtering processing on the real-time state data to obtain a processing result.
Optionally, according to a preset polarity test start instruction and a preset polarity test threshold of a preset control device, performing polarity test processing on the processing result to obtain a polarity test result, including:
and when a preset polarity test starting instruction of preset control equipment is received, under the condition that the processing result is judged to be larger than a preset polarity test threshold value, carrying out polarity test processing on the processing result according to a polarity test data range to obtain a polarity test result.
Optionally, the performing polarity test processing on the processing result according to the polarity test data range to obtain a polarity test result includes:
comparing the processing result with a polarity test data range, and if the processing result is in the polarity test data range, obtaining a polarity test result qualified in the polarity test; otherwise, obtaining the polarity test result which is unqualified in polarity test.
Optionally, the polarity test data range is formed according to a maximum error value between a feature point of real-time state data acquired in real time and standard judgment data, where the standard judgment data is data that reaches a preset polarity test standard for the first time.
Optionally, when the processing result is judged to be greater than the preset polarity test threshold, the method further includes:
and if a recording instruction for recording the real-time state data sent by a preset terminal device is received, recording the real-time state data according to the recording instruction.
The invention also provides a polarity test system of a spacecraft, comprising:
the system comprises at least one acquisition device arranged on a part to be tested of the spacecraft, and a control unit, wherein the acquisition device is used for acquiring real-time state data of the part to be tested;
the central controller is electrically connected with the at least one acquisition device and is used for receiving the real-time state data of the to-be-tested part, filtering the real-time state data to obtain a processing result, and sending the processing result to the data processing subsystem according to a preset polarity test starting instruction and a preset polarity test threshold;
and the data processing subsystem is electrically connected with the central controller and is used for carrying out polarity test processing on the processing result according to the polarity test data range to obtain a polarity test result.
Optionally, the at least one acquisition device comprises at least one of:
a gyroscope externally connected with a first part to be tested of a servo system of the spacecraft;
and the pressure sensor and/or the electromagnetic sensor is/are externally connected with a second part to be tested of the final attitude control correction system of the spacecraft.
The present invention also provides a computing device comprising: a processor, a memory storing a computer program which, when executed by the processor, performs the method as described above.
The invention also provides a computer-readable storage medium storing instructions which, when executed on a computer, cause the computer to perform the method as described above.
The scheme of the invention at least comprises the following beneficial effects:
acquiring real-time state data of a part to be tested through at least one acquisition device arranged on the part to be tested of the spacecraft; filtering the real-time state data to obtain a processing result; performing polarity test processing on the processing result according to a preset polarity test starting instruction and a preset polarity test threshold of preset control equipment to obtain a polarity test result; the polarity testing method has the advantages that automatic polarity testing discrimination is realized, potential quality hidden danger is effectively avoided, product reliability is improved, corresponding effective testing data can be generated, and traceability is realized.
Drawings
Fig. 1 is a schematic flow chart of a polarity testing method of a spacecraft in an embodiment of the invention;
FIG. 2 is a schematic diagram of a transformation relationship between a mounting reference coordinate system and a gyroscope body coordinate system according to an embodiment of the present invention;
FIG. 3 is a schematic view of the installation structure of a gyroscope and a rocket rudder shaft in the embodiment provided by the invention;
FIG. 4 is a schematic diagram of a display interface of an industrial personal computer in an embodiment of the present invention;
FIG. 5 is a schematic diagram of the connection between a gyroscope and an industrial personal computer in an embodiment of the present invention;
fig. 6 is a block diagram of a polarity testing system for a spacecraft in accordance with an exemplary embodiment of the present invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
As shown in fig. 1, an embodiment of the present invention provides a polarity testing method for a spacecraft, including:
and step 13, carrying out polarity test processing on the processing result according to a preset polarity test starting instruction and a preset polarity test threshold of preset control equipment to obtain a polarity test result.
In the embodiment, the real-time state data of the to-be-tested part obtained by at least one acquisition device is filtered to obtain a processing result, the filtering processing is preferably processed by an integer stabilizer, and the polarity test processing is performed on the processing result according to a preset polarity test starting instruction and a preset polarity test threshold of preset control equipment to obtain a polarity test result; the polarity testing method has the advantages that automatic polarity testing discrimination is realized, potential quality hidden dangers are effectively avoided, product reliability is improved, corresponding effective testing data can be generated, and traceability is achieved.
Wherein the parts to be tested of the spacecraft comprise: an execution part of the servo system; an electromagnetic valve of the final correction attitude control correction system; the execution part of the servo system comprises: the air rudder, the gas rudder and the engine jet pipe; the acquisition device comprises: a gyroscope, a pressure sensor, and an electromagnetic induction sensor; preferably, the gyroscope
The device is arranged on the air rudder, the gas rudder and the engine spray pipe and is used for testing the motion conditions of the parts to be tested; the gyroscope is an angle detection device which uses a momentum moment sensitive shell of a high-speed revolving body to rotate around one or two axes which are orthogonal to a rotation axis relative to an inertia space, and in the embodiment, the gyroscope is selected to measure an execution component which can generate relative motion when a polarity test is carried out on an air rudder, a gas rudder, an engine spray pipe and the like; compared with other sensors for measuring motion conditions, such as an angular displacement sensor or a distance measurement sensor, the gyroscope is more convenient to mount and does not need to acquire relative position changes.
After zero calibration is carried out on the gyroscope and an execution component of the servo system, the angular speed and the angle of the execution component of the servo system moving along the axis are measured and converted into corresponding real-time state data;
the pressure sensor and/or the electromagnetic induction sensor are/is arranged on the electromagnetic valve of the final correction attitude control correction system and used for testing the opening and closing conditions of the electromagnetic valve; during polarity test, the pressure sensor can collect the wind pressure generated by gas ejected from the final repair spray pipe, and the change state of the wind pressure is used as real-time state data; the electromagnetic induction sensor can acquire the magnetic leakage quantity generated when the electromagnetic valve is opened, and the change state of the magnetic leakage quantity is used as real-time state data; the judgment of the opening and closing conditions of the electromagnetic valve can be realized according to the collected real-time state data of the wind pressure and the magnetic leakage quantity;
in addition, in an optional embodiment of the invention, the vibration condition of the final repair spray pipe can be measured through a vibration sensor, and the vibration quantity is used as real-time state data to realize polarity test;
the collecting equipment can provide real-time and accurate real-time state data for polarity test.
It should be noted that the polarity test is used for testing whether the spacecraft control system verifies that attitude control is correctly executed, the polarity test is an important index assessment item in the overall test stage of the spacecraft, and generally, flight loss can be directly caused by the polarity error of the spacecraft; specifically, a test result is obtained mainly by qualitatively judging the motion condition of an execution component of a servo system of the spacecraft and the opening and closing condition of an electromagnetic valve of a final correction attitude control correction system.
Here, a description is given of the mounting process of the gyroscope:
the gyroscope is arranged on an execution part of a servo system, and because the gyroscope is an inertial device, the requirement on working conditions is high in the using process, if the installation position of the gyroscope on a part to be tested exceeds an allowable range, the data generated in the testing process can generate a coupling phenomenon to influence the effectiveness of real-time state data, and here, the position of the gyroscope according to the following conditions are explained:
as shown in fig. 2, the origin of the coordinate system is located at the center of mass of the gyroscope, and the coordinate system of the gyroscope measurement body is
，
Shaft edge
The accelerometer of (a) is in a forward direction,
is axially arranged at
And an accelerometer of
In-plane determined by the accelerometer and
the axis is vertical, and under the condition that the installation error of the gyroscope is not considered, the coordinate system of the gyroscope is parallel to the coordinate system of the part to be tested;
the mounting reference coordinate system in fig. 2
Usually, the installation reference coordinate system should be set
Measuring body coordinate system with gyroscope
Are arranged to coincide, but in some cases, it is impossible to coincide the two, and therefore, a reference coordinate system is installed
Measuring body coordinate system with gyroscope
The conversion between the reference coordinate system and the gyroscope body coordinate system can be expressed by three Euler angles, and the symbol of the conversion angle and the rotation sequence of the installation reference coordinate system to the gyroscope body coordinate system are set
(ii) a The installation reference coordinate system is a coordinate system determined by an installation reference surface and an azimuth reference surface;
in addition, in the embodiment of the invention, in order to break through the limitation of the installation requirement of the gyroscope, a reference coordinate system can be installed
Measuring body coordinate system with gyroscope
Performing angle deviation calculation to obtain an angle deviation value; further, angle deviation compensation is carried out to obtain an available test coordinate model; in the test process, the angle output variable quantity of any axis is collected, and the data interference of other axes can be avoided, so that a motion track curve with higher accuracy of an execution part of the servo system can be obtained;
the gyroscope arranged in the way realizes the universality of the polarity testing method on the spacecraft, has wider application scenes and improves the practicability; in addition, the polarity test is carried out through the gyroscope, the pressure sensor, the electromagnetic induction sensor, the vibration sensor and the like, and the obtained polarity test result is high in accuracy, low in cost and high in practicability.
In an optional embodiment of the present invention, step 12 includes:
and 121, filtering the interference data of the real-time state data to obtain a processing result.
In this embodiment, the filtering process is preferably implemented based on an integer stabilizer, and the filtering process is performed on interference data caused by vibration or electromagnetism, for example, and the interference data is filtered to the greatest extent, so as to obtain data with higher accuracy as a processing result, so as to make the polarity test more effective.
In an optional embodiment of the present invention, step 13 includes:
and step 131, when a preset polarity test starting instruction of preset control equipment is received and the processing result is judged to be greater than a preset polarity test threshold, performing polarity test processing on the processing result according to a polarity test data range to obtain a polarity test result.
In this embodiment, in order to achieve universality of the criterion database and eliminate a time error generated in operation, a preset polarity test threshold is set for the polarity test, and only when a preset polarity test start instruction of the preset control device is received and the processing result is greater than the preset polarity test threshold, the polarity test processing is performed on the processing result, and the processing result and the polarity test result are collected and recorded. The setting of the preset polarity test threshold value realizes the comparability of the processing result with the criterion database.
In an optional embodiment of the present invention, in step 131, performing polarity test processing on the processing result according to the polarity test data range to obtain a polarity test result, where the polarity test processing includes:
step 1311, comparing the processing result with a polarity test data range, and if the processing result is within the polarity test data range, obtaining a polarity test result qualified in a polarity test; otherwise, obtaining the polarity test result which is unqualified in polarity test.
The polarity test data range is formed according to the maximum error value between the characteristic point of real-time state data acquired in real time and standard judgment data, and the standard judgment data is data which reaches a preset polarity test standard for the first time.
In the embodiment, correct data acquired for the first time is used as a standard criterion for the polarity test of the spacecraft of the type, when the polarity test is subsequently performed on the spacecraft of the same type, an error range is set, a polarity test data range can be obtained according to the marking criterion and the error range, a processing result is compared with the polarity test data range, the processing result in the polarity test data range is qualified in the polarity test, otherwise, the polarity test data range is unqualified, and the automatic interpretation function of the polarity test is realized;
in addition, it should be noted that the standard judgment data is stored in the criterion database after the data first reaches the preset polarity test standard, so that the standard judgment data and the processing result are compared when the polarity test is subsequently performed on the same type of spacecraft.
In an optional embodiment of the present invention, in the step 13, when it is determined that the processing result is greater than the preset polarity test threshold, the method further includes:
step 132, if a recording instruction for recording the real-time status data sent by a preset terminal device is received, recording the real-time status data according to the recording instruction.
In this embodiment, when it is determined that the processing result is greater than the preset polarity test threshold, the preset terminal device sends a recording instruction of real-time status data, and at this time, the real-time status data is recorded and may be stored in the data storage module;
in addition, it should be noted that, when it is determined that the processing result is less than or equal to the preset polarity test threshold, the preset terminal device sends a recording instruction of the real-time status data, at this time, even if a preset polarity test start instruction of the preset control device is received, the real-time status data is collected, at this time, only the real-time status data is collected, but the real-time status data is not recorded, that is, the collected real-time status data is not stored in the data storage module.
In a specific embodiment, as shown in fig. 3, the rotation directions of 4 rudder shafts on the rocket are measured by gyroscopes, wherein 4 gyroscopes are respectively installed on the rudder shafts of the rocket, fig. 3 shows a rudder 3 arranged between a third quadrant III and a fourth quadrant IV of the rocket, a rudder 4 arranged between a first quadrant I and a fourth quadrant IV, a rudder 1 arranged between the first quadrant I and a second quadrant II of the rocket, and a rudder 2 arranged between the second quadrant II and the third quadrant III. Each rudder shaft is provided with 1 gyroscope, the rudder can rotate clockwise or anticlockwise around the shaft, and the gyroscope can measure the rotation direction and angle of the rudder; the gyroscope is externally connected to a rudder shaft of the rocket, is detachable and is convenient to use;
the gyroscope sends the measured real-time state data to an industrial personal computer (preset terminal equipment) through an RS485 interface, and the industrial personal computer processes, judges and displays the data;
the display of the industrial control all-in-one machine is explained as follows:
as shown in fig. 4, a display interface of the all-in-one industrial control machine can be automatically fully paved when being opened, and the interface specifically includes: the product number to which the part to be tested belongs; a test result indication; an indication of calibration; starting a recording instruction; view data indications; a plot schematic for each rudder; setting a preset polarity test threshold value of each rudder;
wherein the X-axis of the plot of each rudder is time(s) and the Y-axis is angle (°); the calibration instruction is used for recording the initial value of the output of each rudder sensor or zero clearing; the starting record instruction is used for indicating that the background starts to record data, but a curve diagram of the rudder cannot be generated (namely, a preset polarity test starting instruction is received, real-time state data is acquired, but real-time state data is not recorded); the preset polarity test threshold setting of each rudder is a condition for starting to generate a curve, the curve is started to be generated when the sensor data (real-time state data) is detected to be larger than the preset polarity test threshold, the preset polarity test threshold setting is used for debugging products, and after the debugging is finished, the content is not displayed on an interface; the data viewing indication is used for indicating that the main interface is closed and popping up a data display interface;
the schematic diagram of the tested curves of the 4 rudders is shown in fig. 2, the test cycle of each rudder is 96s, 12 sections of broken lines are provided, the amplitude of each section of broken line is plus or minus 16 degrees, and the cycle is 8 s;
the method for judging the test result comprises the following steps: and (3) judging the 1 st s-7 th s of each broken line, wherein the numerical value is increased or decreased progressively, if the 8 broken lines are consistent with the curve corresponding to the correct data acquired for the first time, the corresponding rudder test result passes, if the results of the 4 rudders pass, the test result indicates to give an indication that the rudder test passes, and if not, the indication that the rudder test does not pass is given. The test data is usually stored in the background, the test results of a certain number of products can be stored, and the test results are automatically covered when the test results exceed the test results; the test results of the product that may be saved depend on the computer resources.
The connection relationship that the gyroscope sends the acquired real-time state data to the industrial personal computer through the RS485 interface is explained, as shown in FIG. 5, the Baud rate of the RS485 interface is set to be 9600bps (the optional range is 4800-23040 bps); the output rate is set to be 10Hz (the optional range is 0.2-200 Hz); setting the starting time of the rate gyro to be 1 s; the output content comprises: on-chip time, acceleration: 3-dimensional, angular velocity: 3-dimensional, magnetic field: 3-dimensional, angle: 3 dimension; the instruction flow comprises the following steps: setting a baud rate, resetting a course angle, and reading course angle data;
the industrial control all-in-one machine reads the data of the 4-path rate gyroscope and draws a curve schematic diagram as shown in figure 4 on an interface according to angle or angular speed information;
the following are the polarity test data for the 4 gyroscopes in the test process:
TABLE 1
As can be seen from table 1, real-time status data on 4 gyroscopes at different time stamps; the automatic polarity test judgment can be realized through the process, and compared with the traditional manual judgment mode, the polarity test judgment method has the advantages that the test data is more reliable and the traceability is higher.
The embodiment of the invention obtains the real-time state data of the part to be tested through at least one acquisition device arranged on the part to be tested of the spacecraft; filtering the real-time state data to obtain a processing result; carrying out polarity test processing on the processing result according to a preset polarity test starting instruction and a preset polarity test threshold of preset control equipment to obtain a polarity test result; the polarity testing method has the advantages that automatic polarity testing discrimination is realized, potential quality hidden danger is effectively avoided, product reliability is improved, corresponding effective testing data can be generated, and traceability is realized.
An embodiment of the present invention further provides a polarity testing system for a spacecraft, including:
the system comprises at least one acquisition device arranged on a part to be tested of the spacecraft, and a control unit, wherein the acquisition device is used for acquiring real-time state data of the part to be tested;
the central controller is electrically connected with the at least one acquisition device and is used for receiving the real-time state data of the to-be-tested part, filtering the real-time state data to obtain a processing result, and sending the processing result to the data processing subsystem according to a preset polarity test starting instruction and a preset polarity test threshold;
and the data processing subsystem is electrically connected with the central controller and is used for carrying out polarity test processing on the processing result according to the polarity test data range to obtain a polarity test result.
Optionally, the at least one acquisition device comprises at least one of:
a gyroscope externally connected with a first part to be tested of a servo system of the spacecraft;
and the pressure sensor and/or the electromagnetic sensor is/are externally connected with a second part to be tested of the final attitude control correction system of the spacecraft.
As shown in fig. 6, in a specific embodiment, the polarity testing system of the spacecraft is arranged on the polarity tester, and is composed of a data processing subsystem arranged inside the polarity tester, a central control stabilizing system and an information collecting system arranged outside the polarity tester, so as to respectively realize the functions of data collection, conversion processing, automatic discrimination and the like;
the system comprises an information acquisition system, a polarity test automatic discrimination system, a servo system and a final-repair attitude correction system, wherein the information acquisition system is used for acquiring information of the polarity test automatic discrimination system and mainly acquires data through a sensor (acquisition equipment), and the sensor is selected according to the servo system and the final-repair attitude correction system of the spacecraft; can be a gyroscope, a pressure sensor and an electromagnetic induction sensor;
the central control stabilizing system is used for realizing a central link function of information transmission of the information acquisition system and the data processing subsystem, and the central control stabilizing system comprises a central controller and a sensor data shaping stabilizer, specifically, an instruction of the data processing subsystem is transmitted to a sensor of the information acquisition system, and the instruction here includes, of course: presetting a polarity test starting instruction, a polarity test stopping instruction, a polarity test calibrating instruction and the like;
meanwhile, the central control stabilizing system carries out reshaping processing on the real-time state data of the information acquisition system through the sensor data reshaping stabilizer, interference data caused by vibration, electromagnetism and the like are filtered out, the reshaped data are transmitted to the instruction control module or the data real-time acquisition module of the data processing subsystem, and information interaction between the information acquisition system and the data processing subsystem is realized.
The data processing subsystem plays a core role of the polarity testing system and comprises an instruction control module, a data real-time acquisition module, an automatic interpretation comparison module and a data storage and export module; the command control module is used for receiving real-time state data after the information acquisition system is shaped by the central control stabilization system before receiving a preset polarity test starting command of preset control equipment, and acquiring the real-time state data by the data real-time acquisition module; after a preset polarity test starting instruction of preset control equipment is received, real-time state data after the information acquisition system is shaped through the central control stabilizing system is not transmitted to the instruction control module any more, the data is acquired by the real-time data acquisition module, meanwhile, the real-time state data and standard judgment data are compared through the automatic interpretation comparison module to obtain a polarity test result, and the polarity test result is stored to the data storage and derivation module.
It should be noted that the system is a system corresponding to the method, and all the implementation manners in the method embodiment are applicable to the embodiment of the apparatus, and the same technical effect can be achieved.
Embodiments of the present invention also provide a computing device, comprising: a processor, a memory storing a computer program which, when executed by the processor, performs the method as described above. All the implementation manners in the above method embodiment are applicable to this embodiment, and the same technical effect can be achieved.
Embodiments of the present invention also provide a computer-readable storage medium storing instructions which, when executed on a computer, cause the computer to perform the method as described above. All the implementation manners in the above method embodiment are applicable to this embodiment, and the same technical effect can be achieved.
Those of ordinary skill in the art will appreciate that the various illustrative elements and algorithm steps described in connection with the embodiments disclosed herein may be implemented as electronic hardware or combinations of computer software and electronic hardware. Whether such functionality is implemented as hardware or software depends upon the particular application and design constraints imposed on the technical solution. Skilled artisans may implement the described functionality in varying ways for each particular application, but such implementation decisions should not be interpreted as causing a departure from the scope of the present invention.
It is clear to those skilled in the art that, for convenience and brevity of description, the specific working processes of the above-described systems, apparatuses and units may refer to the corresponding processes in the foregoing method embodiments, and are not described herein again.
In the embodiments provided in the present invention, it should be understood that the disclosed apparatus and method may be implemented in other ways. For example, the above-described apparatus embodiments are merely illustrative, and for example, the division of the units is only one logical division, and other divisions may be realized in practice, for example, a plurality of units or components may be combined or integrated into another system, or some features may be omitted, or not executed. In addition, the shown or discussed mutual coupling or direct coupling or communication connection may be an indirect coupling or communication connection through some interfaces, devices or units, and may be in an electrical, mechanical or other form.
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 units can be selected according to actual needs to achieve the purpose of the solution of the embodiment.
In addition, functional units in the embodiments of the present invention may be integrated into one processing unit, or each unit may exist alone physically, or two or more units are integrated into one unit.
The functions, if implemented in the form of software functional units and sold or used as a stand-alone product, may be stored in a computer readable storage medium. 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: various media capable of storing program codes, such as a U disk, a removable hard disk, a ROM, a RAM, a magnetic disk, or an optical disk.
Furthermore, it is to be noted that in the device and method of the invention, it is obvious that the individual components or steps can be decomposed and/or recombined. These decompositions and/or recombinations are to be regarded as equivalents of the present invention. Also, the steps of performing the series of processes described above may naturally be performed chronologically in the order described, but need not necessarily be performed chronologically, and some steps may be performed in parallel or independently of each other. It will be understood by those skilled in the art that all or any of the steps or elements of the method and apparatus of the present invention may be implemented in any computing device (including processors, storage media, etc.) or network of computing devices, in hardware, firmware, software, or any combination thereof, which can be implemented by those skilled in the art using their basic programming skills after reading the description of the present invention.
The object of the invention is thus also achieved by a program or a set of programs running on any computing device. The computing device may be a general purpose device as is well known. The object of the invention is thus also achieved solely by providing a program product comprising program code for implementing the method or the apparatus. That is, such a program product also constitutes the present invention, and a storage medium storing such a program product also constitutes the present invention. It is to be understood that the storage medium may be any known storage medium or any storage medium developed in the future. It is further noted that in the apparatus and method of the present invention, it is apparent that each component or step can be decomposed and/or recombined. These decompositions and/or recombinations are to be regarded as equivalents of the present invention. Also, the steps of executing the series of processes described above may naturally be executed chronologically in the order described, but need not necessarily be executed chronologically. Some steps may be performed in parallel or independently of each other.
While the foregoing is directed to the preferred embodiment of the present invention, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (8)
1. A method for testing the polarity of a spacecraft, comprising:
acquiring real-time state data of a part to be tested through at least one acquisition device arranged on the part to be tested of the spacecraft;
filtering the real-time state data to obtain a processing result;
carrying out polarity test processing on the processing result according to a preset polarity test starting instruction and a preset polarity test threshold of preset control equipment to obtain a polarity test result;
wherein, according to the preset polarity test starting instruction and the preset polarity test threshold value of the preset control equipment, the polarity test processing is carried out on the processing result to obtain a polarity test result, which includes:
when a preset polarity test starting instruction of preset control equipment is received, under the condition that the processing result is judged to be larger than a preset polarity test threshold value, carrying out polarity test processing on the processing result according to a polarity test data range to obtain a polarity test result;
the polarity test data range is formed according to the maximum error value between the characteristic point of real-time state data acquired in real time and standard judgment data, and the standard judgment data is data which reaches a preset polarity test standard for the first time.
2. A method according to claim 1, wherein filtering the real-time status data to obtain a processing result comprises:
and carrying out interference data filtering processing on the real-time state data to obtain a processing result.
3. The method of claim 1, wherein the performing a polarity test on the processing result according to a polarity test data range to obtain a polarity test result comprises:
comparing the processing result with a polarity test data range, and if the processing result is within the polarity test data range, obtaining a polarity test result qualified in the polarity test; otherwise, obtaining the polarity test result which is unqualified in the polarity test.
4. The method for testing the polarity of a spacecraft according to claim 1, wherein if the processing result is judged to be greater than a preset polarity test threshold value, the method further comprises:
and if a recording instruction for recording the real-time state data sent by a preset terminal device is received, recording the real-time state data according to the recording instruction.
5. A polarity test system for a spacecraft, comprising:
the system comprises at least one acquisition device arranged on a part to be tested of the spacecraft, and a control unit, wherein the acquisition device is used for acquiring real-time state data of the part to be tested;
the central controller is electrically connected with the at least one acquisition device and is used for receiving the real-time state data of the to-be-tested part, filtering the real-time state data to obtain a processing result, and sending the processing result to the data processing subsystem according to a preset polarity test starting instruction and a preset polarity test threshold;
the data processing subsystem is electrically connected with the central controller and is used for carrying out polarity test processing on the processing result according to the polarity test data range to obtain a polarity test result;
wherein, according to the preset polarity test starting instruction and the preset polarity test threshold value of the preset control equipment, the polarity test processing is carried out on the processing result to obtain a polarity test result, which includes:
when a preset polarity test starting instruction of preset control equipment is received, under the condition that the processing result is judged to be larger than a preset polarity test threshold value, carrying out polarity test processing on the processing result according to a polarity test data range to obtain a polarity test result;
the polarity test data range is formed according to a maximum error value between a characteristic point of real-time state data acquired in real time and standard judgment data, and the standard judgment data is data which reaches a preset polarity test standard for the first time.
6. A polarity test system for a spacecraft as claimed in claim 5, wherein said at least one acquisition device comprises at least one of:
a gyroscope externally connected with a first part to be tested of a servo system of the spacecraft;
and the pressure sensor and/or the electromagnetic sensor is/are externally connected with a second part to be tested of the final attitude control correction system of the spacecraft.
7. A computing device, comprising: processor, memory storing a computer program which, when executed by the processor, performs the method of any of claims 1 to 4.
8. A computer-readable storage medium having stored thereon instructions which, when executed on a computer, cause the computer to perform the method of any one of claims 1 to 4.
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