CN112305936A - Satellite attitude and orbit control semi-physical simulation test method, system, device and storage medium - Google Patents
Satellite attitude and orbit control semi-physical simulation test method, system, device and storage medium Download PDFInfo
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Abstract
The application discloses a satellite attitude and orbit control semi-physical simulation test method, a system, a device and a storage medium, and the attitude and orbit information of a satellite to be tested is obtained; obtaining a test requirement based on attitude and orbit information of a satellite to be tested, and determining a test instruction; determining corresponding test instrument equipment and a corresponding satellite to be tested in the virtual resource configuration information according to the test instruction; controlling the corresponding test instrument equipment to execute the test instruction by using a driving function so as to enable the corresponding test instrument equipment to generate a test excitation signal; controlling the corresponding satellite to be tested to respond to the test excitation signal and the test instruction to perform testing by using the driving function so as to enable the corresponding satellite to be tested to generate a target signal; and determining whether the test is successful according to the target signal, removing the coupling of software and hardware in the satellite attitude and orbit control semi-physical simulation test system, and flexibly testing different test requirements, different types of instrument equipment and the satellite to be tested.
Description
Technical Field
The invention relates to the field of satellite testing, in particular to a satellite attitude and orbit control semi-physical simulation testing method, a satellite attitude and orbit control semi-physical simulation testing system, a satellite attitude and orbit control semi-physical simulation testing device and a satellite attitude and orbit control semi-physical simulation testing storage medium.
Background
The satellite attitude and orbit control system mainly completes the tasks of satellite orbit change and orbit entry, and in order to ensure the good performance of the satellite attitude and orbit control system and the safety of a flight test, the satellite attitude and orbit control system needs to be subjected to a ground simulation test of the system before the satellite is launched, and the function and the performance of the system are tested. From the development of simulation technology and the experience of domestic practical application, the satellite attitude and orbit control semi-physical simulation test system is an important means for designing and verifying the attitude and orbit control system, can effectively improve the development quality of the attitude and orbit control system, verifies the rationality and the completeness of the attitude and orbit control system scheme, shortens the development period and saves the cost.
The satellite product needs to go through a scheme design stage, a single-machine interface simulation stage, a system-level semi-physical simulation test stage, a whole satellite closed-loop desktop joint test semi-physical simulation stage, a launching area semi-physical test and other stages, and the test requirements of each stage on the test system are different. According to the existing system design method, corresponding hardware equipment is generally configured according to specific test requirements, and corresponding test software is written to complete test tasks of each stage, but in the prior art, the coupling degree between software and hardware of a test system is high, once the hardware is replaced, the software part also needs to be synchronously modified, and the system maintenance cost is high; for satellites of different models, the testing functions cannot be compatible, the testing systems matched with the satellites of different models need to be set, and for a usable testing system, software and hardware need to be developed again; in addition, the test requirements of satellite attitude and orbit control cannot be flexibly met, and when the test requirements change, the design of software and hardware of the system needs to be readjusted.
Disclosure of Invention
In order to solve the technical problems, the invention provides a satellite attitude and orbit control semi-physical simulation test method, a satellite attitude and orbit control semi-physical simulation test system, a satellite attitude and orbit control semi-physical simulation test device and a storage medium, which can remove the coupling of software and hardware in the satellite attitude and orbit control semi-physical simulation test system and flexibly test different test requirements, different models of instrument equipment and satellites to be tested.
In order to achieve the purpose of the application, the application provides a satellite attitude and orbit control semi-physical simulation test method, which comprises the following steps:
acquiring attitude and orbit information of a satellite to be detected;
determining test content based on attitude and orbit information of the satellite to be tested;
describing the test content by using a preset language to obtain test requirement information, wherein the test requirement information comprises a signal statement representing a test action of the virtual resource;
analyzing the signal statement to generate a test instruction;
determining corresponding test instrument equipment and a test component corresponding to the satellite to be tested in the virtual resource configuration information according to the test instruction;
controlling the corresponding test instrument equipment to execute the test instruction by using a driving function so as to enable the corresponding test instrument equipment to generate a test excitation signal;
controlling a test component corresponding to the satellite to be tested to respond to the test excitation signal and the test instruction to perform testing by using the driving function so as to enable the corresponding satellite to be tested to generate a target signal;
and determining a test result according to the target signal.
In another aspect, the present application further provides a satellite attitude and orbit control semi-physical simulation testing system, including:
the system comprises a physical interface layer and a plurality of hardware devices, wherein the physical interface layer is used for being physically connected with the hardware devices, and the hardware devices comprise a satellite to be tested and test instrument equipment;
a device driver layer for providing driver functions for the plurality of hardware devices;
the virtual instrument resource layer is used for mapping hardware equipment resources into virtual instrument resources for management;
a software application layer, configured to obtain attitude and orbit information of a satellite to be tested, determine test content based on the attitude and orbit information of the satellite to be tested, and describe the test content by using a preset language to obtain test requirement information, where the test requirement information includes a signal statement characterizing a test action of a virtual instrument, and analyzes the test requirement information to generate a test instruction, and determines, according to the test instruction, corresponding test instrument equipment and a test component corresponding to the satellite to be tested in virtual resource configuration information, and controls, by using a drive function, the corresponding test instrument equipment to execute the test instruction, so that the corresponding test instrument equipment generates a test excitation signal, and controls, by using the drive function, the test component corresponding to the satellite to be tested to respond to the test excitation signal and the test instruction to perform a test, so that the corresponding satellite to be tested generates a target signal, and a test result is determined according to the target signal;
and the user interface is used for establishing interaction between the user and the software application layer.
In another aspect, the present application further provides a satellite attitude and orbit control semi-physical simulation testing apparatus, including:
the information acquisition module is used for acquiring attitude and orbit information of the satellite to be detected;
the instruction generation module is used for determining test contents based on the attitude and orbit information of the satellite to be tested; describing the test content by using a preset language to obtain test requirement information, wherein the test requirement information comprises a signal statement representing the test action of the virtual instrument; analyzing the test requirement information to generate a test instruction;
the hardware equipment determining module is used for determining corresponding testing instrument equipment and a testing component corresponding to the satellite to be tested in the virtual resource configuration information according to the testing instruction;
the excitation signal generation module is used for controlling the corresponding test instrument equipment to execute the test instruction by using a driving function so as to enable the corresponding test instrument equipment to generate a test excitation signal;
the target signal generation module is used for controlling a test component corresponding to the satellite to be tested to respond to the test excitation signal and the test instruction to test by using the drive function so as to enable the corresponding satellite to be tested to generate a target signal;
and the test result analysis module is used for determining a test result according to the target signal.
In another aspect, the present application further provides a computer-readable storage medium, where at least one instruction or at least one program is stored in the storage medium, and the at least one instruction or the at least one program is loaded and executed by a processor to implement the above-mentioned satellite attitude and orbit control semi-physical simulation testing method.
The application has the following beneficial effects:
the attitude and orbit information of the satellite to be detected is obtained; determining test content based on attitude and orbit information of the satellite to be tested; describing the test content by using a preset language to obtain test requirement information, wherein the test requirement information comprises a signal statement representing the test action of the virtual instrument; analyzing the signal statement to generate a test instruction; determining corresponding test instrument equipment and a test component corresponding to the satellite to be tested in the virtual resource configuration information according to the test instruction; controlling the corresponding test instrument equipment to execute the test instruction by using a driving function so as to enable the corresponding test instrument equipment to generate a test excitation signal; controlling a test component corresponding to the satellite to be tested to respond to the test excitation signal and the test instruction to perform testing by using the driving function so as to enable the corresponding satellite to be tested to generate a target signal; and determining a test result according to the target signal, so that the coupling of software and hardware in the satellite attitude and orbit control semi-physical simulation test system can be eliminated, and flexible tests can be performed on different test requirements, different types of instrument equipment and satellites to be tested.
Drawings
In order to more clearly illustrate the technical solutions of the present application, the drawings needed for the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
Fig. 1 is a schematic view of an application scenario of a satellite attitude and orbit control semi-physical simulation test according to an embodiment of the present application;
fig. 2 is a flowchart of a satellite attitude and orbit control semi-physical simulation testing method according to an embodiment of the present application;
fig. 3 is a flowchart illustrating analyzing a signal statement to generate a test instruction according to an embodiment of the present disclosure;
FIG. 4 is a flowchart of creating a device driver layer according to another embodiment of the present application;
fig. 5 is a flowchart illustrating a test content being described by using a predetermined language to obtain test requirement information according to an embodiment of the present application;
fig. 6 is a flowchart of creating a virtual device resource layer according to an embodiment of the present disclosure;
fig. 7 is a flowchart of a satellite attitude and orbit control semi-physical simulation testing method according to another embodiment of the present application;
FIG. 8 is a flowchart for constructing a software application layer according to an embodiment of the present application;
fig. 9 is a schematic structural diagram of a satellite attitude and orbit control semi-physical simulation testing system according to an embodiment of the present application;
fig. 10 is a schematic structural diagram of a satellite attitude and orbit control semi-physical simulation testing apparatus according to an embodiment of the present application.
Detailed Description
In order to make those skilled in the art better understand the technical solutions in the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. 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 application.
It should be noted that the terms "first," "second," and the like in the description and claims of the present invention and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the invention described herein are capable of operation in sequences other than those illustrated or described 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 server 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 order to implement the technical solution of the present application, so that more engineering workers can easily understand and apply the present application, the working principle of the present application will be further described with reference to specific embodiments.
The method can be applied to the field of satellite attitude and orbit control semi-physical simulation test, and the method can be used for carrying out a system ground simulation test on the satellite attitude and orbit control system before the satellite is launched, and checking the function and the performance of the satellite attitude and orbit control system. Referring to fig. 1, fig. 1 is a schematic view of an application scenario provided in an embodiment of the present application, as shown in fig. 1, the application scenario may at least include a satellite attitude and orbit control semi-physical simulation test system 01 and a satellite 02 to be tested, the satellite attitude and orbit control semi-physical simulation test system 01 may be installed in an actual physical standalone, and the satellite 02 to be tested may be satellites of different models or dynamic models of satellites. In some embodiments of the present disclosure, the satellite 02 to be tested may be connected to the satellite attitude and orbit control semi-physical simulation test system 01 through a network cable or an optical fiber, and the satellite attitude and orbit control semi-physical simulation test system 01 may perform attitude and orbit control semi-physical simulation test on the satellite 02 to be tested.
A satellite attitude and orbit control semi-physical simulation test method of the present application is introduced below, and fig. 2 is a flowchart of a satellite attitude and orbit control semi-physical simulation test method provided in an embodiment of the present application, where the method may include:
s11: and acquiring attitude and orbit information of the satellite to be detected.
Specifically, the attitude and orbit information of the satellite to be tested may include current attitude information and orbit information of the satellite to be tested, and in some embodiments, the current attitude and orbit information of the satellite to be tested may include attitude and orbit information sent by a dynamic model sensor of the satellite.
S13: and determining test content based on attitude and orbit information of the satellite to be tested.
Specifically, the attitude and orbit information of the satellite to be measured includes attitude information and orbit information of the satellite to be measured, the attitude information of the satellite refers to space pointing state information where the satellite operates on the orbit, and the orbit information of the satellite refers to flight trajectory information of the satellite. In one specific embodiment, the Test content may be that a signal with a voltage of 115V, a frequency of 400HZ, and a maximum current of 2A is applied to a point J32-3-a23 of a UUT (Unit Under Test). Namely, J32-3-A23 points of a UUT (Unit Under Test) are required to execute the signal with loading voltage of 115V, frequency of 400HZ and maximum current of 2A.
S15: and describing the test content by using a preset language to obtain test requirement information, wherein the test requirement information represents a signal statement of the test action of the virtual instrument.
Specifically, the preset Language may include ATLAS (abstract Test Language for All Systems) or ATML (Automatic Test Markup Language).
In a specific embodiment, when the Test content is UUT (Unit Under Test), the SIGNAL with the VOLTAGE of 115V, the frequency of 400HZ, and the maximum CURRENT of 2A is applied at point J32-3-a23, the Test requirement information obtained by describing the Test content with ATLAS may be "APPLY, AC SIGNAL, VOLTAGE 115V, FREQ 400HZ, CURRENT MAX 2A, CNX HI J32-3-a 23".
In the embodiment of the specification, the test requirement information does not relate to specific hardware equipment, only describes specific test requirements, and can achieve the purpose of separating the coupling of software and hardware by abstracting the test requirements. The ATLAS language is a signal-oriented test language, and a test flow written by the ATLAS language does not contain information of specific hardware equipment and only describes test requirements, so that the target test requirements can be described by using the ATLAS language, and equipment independence can be achieved.
S17: and analyzing the signal statement to generate a test instruction.
In some embodiments, as shown in fig. 3, analyzing the signal statement to generate the test instruction may include:
s171: and performing lexical analysis on the signal sentences to extract a plurality of keywords in the signal sentences.
Specifically, the keywords in the signal sentence may include an action keyword, a signal descriptive keyword, a noun modification keyword, and a signal information descriptive keyword. The action keyword refers to a single action sentence or a multi-action sentence, the descriptive keyword is used for describing a signal, such as a DC signal, an AC signal, etc., and the noun-modified keyword is used for describing a noun-modified word, for example, a current, voltage, electric quantity, etc. modified word corresponding to the DC signal. A noun may be described by a number of modifiers. Whether the values of the keywords in the signal sentences meet the conditions or not means whether test actions can be found in the action keywords or not, and whether the values of the descriptive keywords, the name word modification language keywords and the object connection information descriptive keywords all accord with virtual instrument resources or not.
S173: and determining whether a plurality of keywords in the signal statement all meet respective corresponding conditions based on the virtual resources.
Specifically, the virtual resource may include resource information such as a virtual instrument name, a virtual resource name, a signal type, and a virtual instrument characteristic parameter. The virtual resource is a set of virtual instruments created by the plant class and related attribute resources of the virtual instruments. Determining whether the plurality of keywords in the signal sentence satisfy the respective corresponding conditions means to check whether the action keyword in the signal sentence can find a test action, such as "connect", "disconnect", and "request", to check whether resources of the description signal corresponding to the signal descriptive keyword, such as "direct current signal" and "impedance signal", can be found from the virtual resource, to check whether modification resources of the signal corresponding to the nameword modification keyword, such as "voltage" and "current", can be found from the virtual resource, and to check whether resources of the description signal corresponding to the signal information descriptive keyword, such as "maximum value" and "minimum value", can be found from the virtual resource. When the test action corresponding to the action keyword in the signal sentence can be found, the resource of the description signal corresponding to the signal descriptive keyword, the modification resource of the signal corresponding to the nominal modification keyword, and the resource of the description signal corresponding to the signal information descriptive keyword can be found in the virtual resource, that is, the result shows that the plurality of keywords in the signal sentence all satisfy the respective corresponding conditions.
S175: if so, the signal statement is transformed into an intermediate code.
In particular, the intermediate code is an internal representation of the signal statement in a variety of forms, such as inverse Polish, Quaternary, ternary, and Tree. The intermediate code is an equivalent internal representation code that transforms the signal statements into test instructions.
S177: the intermediate code is transformed into test instructions.
Specifically, the test instruction is an executable code and is a binary code that can be directly executed by the hardware device, and the test instruction includes a code related to the target virtual instrument and the test parameter corresponding to the target virtual instrument.
S19: and determining corresponding test instrument equipment and a test component corresponding to the satellite to be tested in the virtual resource configuration information according to the test instruction.
Specifically, the virtual resource configuration information is configuration information generated when a virtual instrument resource layer is pre-constructed, and the virtual resource configuration information may include hardware device information, a virtual instrument name, a virtual resource name, a signal type, a virtual instrument characteristic parameter, physical channel information, and connection point information corresponding to each hardware device. For example, in one virtual resource configuration information, there may be four hardware devices corresponding to four virtual resources, respectively, in the first virtual resource, the "DAQ simulation input # 1" is a description of a virtual instrument name of the first hardware device, physical channel information of the virtual instrument is "Dev 1/ai 0", a maximum value of characteristic parameters of the virtual instrument is 10, a minimum value of the characteristic parameters is-10, and a signal type is "Modifier". The test instruction comprises codes related to a target virtual instrument and test parameters corresponding to the target virtual instrument, the virtual resource configuration information can comprise the test parameters corresponding to the target virtual instrument and the target virtual instrument, corresponding test instrument equipment and a test component corresponding to the satellite to be tested can be determined based on the virtual resource configuration information, the determined test instrument equipment is an object generating an excitation signal, and the determined test component corresponding to the satellite to be tested is an object receiving the excitation signal.
S21: and controlling the corresponding test instrument equipment to execute the test instruction by using the driving function so as to enable the corresponding test instrument equipment to generate the test excitation signal.
Specifically, the driver function is a function created when the device driver layer is previously constructed.
For example, a test system is connected to a hardware device having a plurality of Power sources, which are Power source a, Power source B, Power source C, and Power source D, where Power source D is described as "DC Power" and the Power source used in the test instruction is "DC Power". And obtaining a Power supply D corresponding to the DC Power according to the virtual resource configuration information, and controlling the Power supply D to execute a corresponding test instruction through a drive function of the Power supply D so that the Power supply D generates a test excitation signal.
S23: and controlling a corresponding to-be-tested part of the to-be-tested satellite to respond to the test excitation signal and the test instruction to test by using the drive function so as to enable the to-be-tested satellite to generate a target signal.
Specifically, the test system may establish a connection with the satellite to be tested through the driving function, and the test instrument device generates the test excitation signal and then sends the test excitation signal to the corresponding component to be tested of the satellite to be tested, where the component to be tested corresponding to the satellite to be tested responds to the test excitation signal and the test instruction to perform a test.
S25: and determining a test result according to the target signal.
Specifically, the target signal generated by the satellite to be tested is sent to the test system, the test system end determines whether the test content is met according to the feedback target signal, and if the test content is met, the test is successful.
In the embodiment, hardware equipment resources are abstracted into virtual instrument resources, attitude and orbit information of the satellite to be tested is obtained, and test contents are determined based on the attitude and orbit information of the satellite to be tested; describing test contents by using a preset language to obtain test requirement information, wherein the test requirement information comprises a signal statement representing the test action of the virtual instrument; analyzing the signal statement to generate a test instruction; determining corresponding test instrument equipment and a test component corresponding to the satellite to be tested in the virtual resource configuration information according to the test instruction; controlling the corresponding test instrument equipment to execute the test instruction by using the driving function so as to enable the corresponding test instrument equipment to generate a test excitation signal; controlling a test component corresponding to the satellite to be tested to respond to the test excitation signal and the test instruction by using the drive function to test so as to enable the corresponding satellite to be tested to generate a target signal; the test method has no binding requirement on connected hardware equipment, and when the test requirements are different and the test instrument equipment or the satellite to be tested is changed, new test can be carried out only by changing the virtual resource configuration information and the driving function.
In order to implement the testing method in the above embodiment, before testing the satellite to be tested by using the testing apparatus, the apparatus driver layer, the virtual apparatus resource layer, and the software application layer need to be preset. In some embodiments, as shown in FIG. 4, the device driver layer may be created using the following steps:
s101: a factory class module is created.
S103: and acquiring the routing information of the system, the signal information of the virtual resource and the hardware equipment information by using the factory type module.
Specifically, the routing information of the system refers to topology information around the system network and a routing metric value recorded with a path, and a routing protocol and static routing can be realized by using the routing information of the system. The signal information of the virtual resource is obtained in the process of acquiring the test resource from the hardware device resource, and the signal information of the virtual resource includes a signal, a description of the signal, and a description of the signal information, for example, the signal information of the virtual resource may include a characteristic parameter of a power supply in the hardware device resource, where the characteristic parameter is that the power supply can supply 28V and 10A current, and then the signal information of the virtual resource corresponding to the power supply is DC-28V-10A. The hardware device information refers to the type, name and characteristic parameters of the hardware device.
And S105, creating routing resources, signal resources and virtual resources based on the routing information of the system, the signal information of the virtual resources and the hardware equipment information.
Specifically, after the factory type module acquires the routing information of the system, the signal information of the virtual resource and the hardware device information, the routing resource, the signal resource and the virtual resource are created, and the creation of the multiple resources is a basis for the subsequent operation of the multiple resources by other types of modules. The completion of the creation of the routing resources, signal resources, and virtual resources indicates that the test system has completed initialization. The routing resource represents a connection information resource in the current test system, the signal resource is a resource integrated by signal information of the virtual resource, and the virtual resource represents attributes related to a virtual instrument after the hardware equipment is virtualized, wherein the attributes can include a virtual instrument name, a virtual resource name, a signal type and a virtual instrument characteristic parameter.
S107: and creating a subclass module based on the routing resources, the signal resources and the virtual resources, wherein the subclass module comprises a sensing class module, a source class module and a routing class module.
S109: and generating a plurality of driving functions by using the sensing module, the source module and the routing module, and respectively packaging the driving functions.
Specifically, the driver function is used to establish data interaction between the system and external hardware devices.
In another embodiment, the subclass module may further include a signal class module and a hardware device resource class module, as shown in fig. 5, the obtaining of the test requirement information by describing the test content with the preset language may include:
s151: and extracting target test resources required by the test from the hardware equipment resources by using the hardware equipment resource class module, wherein the target test resources can comprise hardware equipment resources and target signal resources.
Specifically, the hardware device resource module generates signal information during the process of extracting target test resources required by the test from the hardware device resources. The signal information generated here is the signal information of the virtual resource acquired by the plant class module.
S153: and describing the target hardware equipment resource and the target signal resource into a signal statement by using the hardware equipment resource class module.
Specifically, the hardware device resource class module describes a signal statement by using a preset language, wherein the signal statement comprises a plurality of signal statements
S155: and packaging the signal statement by using a signal type module to obtain the test requirement information.
Specifically, the signal class module is configured to encapsulate signal statements, where the signal statements include seven single-action statements and seven multi-action statements. The single-action statements collectively comprise a SETUP statement, a CONNECT statement, a DISCONNECT statement, an ARM statement, a FETCH statement, a CHANGE statement, and a RESET statement. The function of each statement is as follows:
(1) SETUP statement: a test instrument is assigned and an initial setup of the instrument is performed, with which signals are generated or received. Therefore, the function of the SETUP statement corresponds to the driving function of the instrument, which is equivalent to the initialization function of the instrument.
(2) CONNECT statement: the pins of the device under test are connected to a SOURCE, SENSOR or LOAD type test instrument. The CONNECT statement corresponds to the function of the matrix switch part in the test system.
(3) DISCONNECT statement: the pins of the device under test are disconnected from the SOURCE, SENSOR or LOAD type test equipment. The DISCONNECT statement is used in combination with the CONNECT statement, and needs to be disconnected after the test is completed, so that the resource release function is realized.
(4) ARM statement: the function of the ARM statement is to cause a SENSOR type instrument to perform a measurement action, the timing and time of the measurement is described in the statement feature field, and the measurement result is retrieved by the subsequent FETCH statement. In the test system, the ARM statement is only for the SENSOR type instrument, and the corresponding instrument driver function functionally corresponds to the instrument start test function.
(5) FETCH statement: waiting for the measurement triggered by the ARM statement or initate statement to complete and storing it in a variable or array depending on how many measurements are. The FETCH statement and the ARM statement are matched for use, and the function of a data reading function is achieved.
(6) The CHANGE statement: some characteristic values of the test requirements are changed during the UUT test. The CHANGE statement requires a little attention in use, and can be used only after the SETUP statement or the FETCH statement is used.
(7) RESET statement: resetting a test instrument to an unassigned state allows it to be reused by a SETUP statement or a multi-action statement. The function of the RESET statement plays a role in resource release and corresponds to an instrument closing function in an instrument driving function. SIGNAL class module, RESOURCE hardware equipment RESOURCE class module, SENSOR sensing class module, SOURCE SOURCE class module and ROUTING class module.
The multi-action statements mainly include an APPLY statement, a REMOVE statement, a MEASURE statement, a MONITOR statement, a VERIFY statement, a READ statement and an INITIATE statement. The APPLY statement is used in conjunction with the SETUP statement and the CONNECT statement, but the order of use is different for different types of instruments, and is only for the SOURCE type and the LOAD type of instruments. The REMOVE statement is a cooperative use of the DSICONNECT statement and the RESET statement, and is supported for all three types of instruments. The MEASURE statement only aims at the SENSOR type instrument, is used in combination with SETUP, CONNECT, ARM, FETCH, DSICONNECT and RESET statements, and is a finished test action. The MONITOR statement involves the use of an event monitoring statement, but is functionally identical to the MEASURE statement, so in the test platform, the MONITOR statement is replaced with the MEASURE statement. The VERIFY statement differs from the MEASURE statement in that the FETCH statement is followed immediately by a COMPARE statement, but the COMPARE statement does not belong to a one-action statement, the function performed is to COMPARE the data read back, the function of the comparison part in the test platform is additionally performed with a separate part, and therefore the VERIFY statement is also replaced by the MEASURE statement. The READ completes the function of data reading, is the matching use of ARM statement and FETCH statement, and is only directed to the SENSOR type instrument. The INITIATE statement is functionally the same as the ARM statement, but adds the function of event monitoring, so the platform replaces the INITIATE statement with the ARM statement.
In another embodiment, as shown in fig. 6, the method may further include creating a virtual instrument resource layer, which is as follows:
s201: and converting hardware equipment into a virtual instrument, wherein the hardware equipment comprises test instrument equipment and a satellite to be tested.
S203: and acquiring the device resource names of the test instrument device and the satellite to be tested, and the virtual instrument name, the virtual resource name, the signal type, the characteristic parameter of the virtual instrument, the physical channel information and the connection point information which are respectively corresponding to the test instrument device and the satellite to be tested.
Specifically, when describing hardware equipment resources, the test system converts actual hardware equipment into a virtual instrument, and then describes a virtual instrument name, a virtual resource name, a signal type, a virtual instrument characteristic parameter, physical channel information and connection point information corresponding to the virtual hardware equipment through a configuration file. To write the information that will be used in the test action. For example, a hardware device resource configuration is performed on a certain SENSOR _ DAQ type hardware device, the hardware device may specifically be a PCI-6220, specifically, a third-party file editing tool may be used to configure or modify a hardware device resource, in a configuration file, a physical channel name of the hardware device needs to be consistent with a name configured when the hardware device is converted into a virtual instrument, if the PCI-6220 (a type of data acquisition card) is configured as a Dev1 when the hardware device is converted into a virtual instrument, then in the virtual resource configuration information, the physical channel corresponding to the PCI-6220 needs to be correctly identified by adding a Dev1, for example: the physical channel corresponding to PCI-6220 analog input channel ai0 should be Dev1/ai 0.
S205: and constructing virtual resource configuration information based on the virtual instrument name, the virtual resource name, the signal type, the virtual instrument characteristic parameter, the physical channel information and the connection point information which are respectively corresponding to the test instrument equipment and the satellite to be tested.
Specifically, the virtual resource configuration information may include hardware device information, a virtual instrument name, a virtual instrument device name, a signal type, a virtual instrument characteristic parameter, physical channel information, and connection point information corresponding to each hardware device.
In this embodiment, as shown in fig. 7, before controlling the corresponding test equipment to execute the test instruction by using the driving function to make the corresponding test equipment generate the test excitation signal, the method further includes:
s211: and acquiring state information of the routing resource, the signal resource and the virtual resource.
Specifically, the execution of the single-action statements and the multi-action statements may cause the state of the virtual resources, such as the routing resources, the signaling resources, and the virtual resources, in the test system to change, and the change has a certain order.
S213: and judging whether the state information of the routing resource, the signal resource and the virtual resource meets the target state transition relation.
Specifically, the state transition relationship of the routing resource, the signal resource, the virtual resource and other virtual resources refers to the execution sequence of the signal statement. The signal statements may describe a source, sensor, etc. type of instrument. For signal statements of different types of instruments, the state transition of the virtual resources is also different.
S215: and if so, executing a corresponding test instruction, and updating the state of the resource with changed state in the routing resource, the signal resource and the virtual resource to generate new state information.
Specifically, when a certain type of virtual resource performs state transition, the state transition of the type of virtual resource is triggered by the execution of each signal statement, and after the execution of one signal statement is completed, the state of the type of virtual resource is changed from the previous state to the current state, and in the test system, the state is always monitored, and the state information of the type of virtual resource is updated in time to generate new state information.
In a further embodiment, as shown in fig. 8, before transforming the signal statement into an intermediate code, the method may further include:
s181: and acquiring the description of the connection information of the hardware equipment and the system required by the test, and determining whether the route is successfully connected.
Specifically, whether the route is successfully connected is determined according to the description of the connection information of the hardware equipment and the system required by the test. When the route connection is successful, the system carries out connection error prompt. The process of determining whether the route is successfully connected is a process of searching available test resources and verifying the link feasibility of the available test resources by the test system according to the route information.
S183: and if the connection is successful, determining whether the parameters described in the signal statement exceed a preset range.
Specifically, determining whether the parameter described in the signal statement exceeds a preset range is to determine the testing capability of each virtual resource signal of the test system, and specifically determine whether the setting of the testing capability of the signal in the source program exceeds a limited range.
S185: and if the signal statement does not exceed the preset range, determining whether the signal statement meets the target state transition relation.
S187: and when the signal statement meets the target state transition relation, executing the step of transforming the signal statement into a test instruction.
Specifically, the main purpose of determining whether the signal statement satisfies the target state transition relationship is to analyze the state transition in combination with the signal statement. Because the execution of the signal statement has a certain sequence and the state transition of the virtual resource is generated, when the state transition relation of the signal statement is checked, whether the state of the signal statement conforms to the state transition rule of the signal statement is mainly checked. For example, in the ATLAS signal statement, a CHANGE action is performed on a certain resource, the system prompts an error message "no signal found", please confirm that a preceding step, such as a setsu or an APPLY action, is established ", the CHANGE action in the state transition rule of the resource is preceded by the setsu action or the APPLY action, the resource performs the setsu action or the APPLY action, and the state of the resource is updated to the state after the setsu action or the APPLY action, so that the CHANGE action can be guaranteed to be normally performed.
In the embodiment, description of connection information of hardware equipment and a system required by testing is obtained, whether routing is successfully connected is determined, if the connection is successful, whether parameters described in a signal statement exceed a preset range is determined, if the connection is not successful, whether the signal statement meets a target state transition relation is determined, and syntax check is performed on the signal statement from three parties, so that syntax analysis on the signal statement is completed.
Another aspect of the present application further provides an embodiment of a satellite attitude and orbit control semi-physical simulation testing system, as shown in fig. 9, the system includes:
the physical interface layer 301 is configured to be physically connected to a plurality of hardware devices, where the plurality of hardware devices include a satellite to be tested and a test instrument device.
A device driver layer 303, configured to provide driver functions for a plurality of hardware devices.
And the virtual instrument layer 305 is configured to map hardware device resources to virtual instruments for management.
A software application layer 307, configured to obtain attitude and orbit information of a satellite to be tested, determine test content based on the attitude and orbit information of the satellite to be tested, and describe the test content by using a preset language to obtain test requirement information, where the test requirement information includes a signal statement representing a test action of a virtual resource, and analyzes the test requirement information to generate a test instruction, and determines, according to the test instruction, corresponding test instrument equipment and a test component corresponding to the satellite to be tested in virtual resource configuration information, and controls, by using a drive function, the corresponding test instrument equipment to execute the test instruction, so that the corresponding test instrument equipment generates a test excitation signal, and controls, by using the drive function, the test component corresponding to the satellite to be tested to respond to the test excitation signal and the test instruction to perform a test, so that the corresponding satellite to be tested generates a target signal, and a test result is determined according to the target signal.
A user interface 309 for establishing user interaction with the software application layer.
Another aspect of the present application provides an embodiment of a satellite attitude and orbit control semi-physical simulation testing apparatus, as shown in fig. 10, the apparatus may include:
the information acquisition module 401 is configured to acquire attitude and orbit information of the satellite to be detected.
An instruction generating module 403, configured to determine test content based on the attitude and orbit information of the satellite to be tested; describing the test content by using a preset language to obtain test requirement information, wherein the test requirement information comprises a signal statement representing a test action of the virtual resource; and analyzing the signal statement to generate a test instruction.
A hardware device determining module 405, configured to determine, according to the test instruction, a corresponding test instrument device and a test component corresponding to the satellite to be tested in the virtual resource configuration information.
And the excitation signal generating module 407 is configured to control the corresponding test instrument device to execute the test instruction by using the driving function, so that the corresponding test instrument device generates the test excitation signal.
And the target signal generating module 409 is configured to control the corresponding satellite to be tested to respond to the test excitation signal and the test instruction for testing by using the driving function, so that the corresponding satellite to be tested generates a target signal.
And the test result analysis module 411 is configured to determine a test result according to the target signal.
In addition, the apparatus may further include a device driver layer creation module, and specifically, the device driver layer creation module may include:
and the factory class creating unit is used for creating factory class modules.
And the first information acquisition unit is used for acquiring the routing information of the system, the signal information of the virtual resource and the hardware equipment information by using the factory class module.
And the resource creating unit is used for creating the routing resource, the signal resource and the virtual resource based on the routing information of the system, the signal information of the virtual resource and the hardware equipment information.
And the subclass creating unit is used for creating a subclass module based on the routing resources, the signal resources and the virtual resources, and the subclass module comprises a sensing module, a source module and a routing module.
And the driving function generating unit is used for generating a plurality of driving functions by utilizing the sensing module, the source module and the routing module and respectively packaging the plurality of driving functions.
Specifically, the apparatus may further include a virtual instrument layer creation module, and specifically, the virtual instrument layer creation module may include:
and the conversion unit is used for converting hardware equipment into a virtual instrument, wherein the hardware equipment comprises test instrument equipment and a satellite to be tested.
And the second information acquisition unit is used for acquiring the virtual instrument name, the virtual resource name, the signal type, the virtual instrument characteristic parameter, the physical channel information and the connection point information which respectively correspond to the test instrument equipment and the satellite to be tested.
And the virtual resource configuration information creating unit is used for constructing the virtual resource configuration information based on the virtual instrument name, the virtual resource name, the signal type, the virtual instrument characteristic parameter, the physical channel information and the connection point information which are respectively corresponding to the test instrument equipment and the satellite to be tested.
Specifically, the instruction generating module 403 may further include:
and the third information acquisition unit is used for extracting target test resources required by the test from the hardware equipment resources by using the hardware equipment resource class module, and the target test resources comprise target hardware equipment resources and target signal resources.
And the statement description unit is used for describing the target hardware equipment resource and the target signal resource into a signal statement by using the hardware equipment resource class module.
And the packaging unit is used for packaging the signal statements by using the signal class module to obtain the test requirement information.
Specifically, the instruction generating module 403 may further include:
and the keyword judgment unit is used for carrying out lexical analysis on the signal sentences and determining whether the values of the keywords in the signal sentences meet corresponding conditions.
And the information determining unit is used for determining the target virtual instrument and the test parameters based on the virtual resource configuration information when the values of the keywords all meet the corresponding conditions.
And the test instruction determining unit is used for determining a test instruction corresponding to the target virtual instrument according to the target virtual instrument and the test parameters.
Specifically, the apparatus may further include:
and the state information acquisition module is used for acquiring the state information of the routing resources, the signal resources and the virtual resources.
And the state transition relation judging module is used for judging whether the state information of the routing resources, the signal resources and the virtual resources meets the target state transition relation.
And the test instruction execution module is used for executing the test instruction which controls the corresponding test instrument equipment to execute by using the drive function.
And the state information updating module is used for updating the state of the resource with changed state in the routing resource, the signal resource and the virtual resource to generate new state information.
Specifically, the apparatus may further include:
and the routing information acquisition module is used for acquiring the description of the connection information of the hardware equipment and the system required by the test and determining whether the routing is successfully connected.
And the parameter judgment module is used for confirming whether the parameters described in the signal sentences exceed a preset range.
And the state transition relation confirming module is used for confirming whether the signal statement meets the target state transition relation.
In another aspect, the present application further provides an embodiment of a computer-readable storage medium, where at least one instruction or at least one program is stored in the storage medium, and the at least one instruction or the at least one program is loaded and executed by a processor to implement the satellite attitude and orbit control semi-physical simulation testing method in any of the above embodiments.
The attitude and orbit information of the satellite to be detected is obtained; determining test content based on attitude and orbit information of the satellite to be tested; describing the test content by using a preset language to obtain test requirement information, wherein the test requirement information comprises a signal statement representing a test action of the virtual resource; analyzing the signal statement to generate a test instruction; determining corresponding test instrument equipment and a test component corresponding to the satellite to be tested in the virtual resource configuration information according to the test instruction; controlling the corresponding test instrument equipment to execute the test instruction by using a driving function so as to enable the corresponding test instrument equipment to generate a test excitation signal; controlling a test component corresponding to the satellite to be tested to respond to the test excitation signal and the test instruction to perform testing by using the driving function so as to enable the corresponding satellite to be tested to generate a target signal; and determining a test result according to the target signal, so that the coupling of software and hardware in the satellite attitude and orbit control semi-physical simulation test system can be eliminated, and flexible tests can be performed on different test requirements, different types of instrument equipment and satellites to be tested.
In the description provided herein, numerous specific details are set forth. It is understood, however, that embodiments of the invention may be practiced without these specific details. In some instances, well-known methods, structures and techniques have not been shown in detail in order not to obscure an understanding of this description.
Similarly, it should be appreciated that in the foregoing description of exemplary embodiments of the invention, various features of the invention are sometimes grouped together in a single embodiment, figure, or description thereof for the purpose of streamlining the disclosure and aiding in the understanding of one or more of the various inventive aspects. However, the disclosed method should not be interpreted as reflecting an intention that: that the invention as claimed requires more features than are expressly recited in each claim. Rather, as the following claims reflect, inventive aspects lie in less than all features of a single foregoing disclosed embodiment. Thus, the claims following the detailed description are hereby expressly incorporated into this detailed description, with each claim standing on its own as a separate embodiment of this invention.
Those skilled in the art will appreciate that the modules in the device in an embodiment may be adaptively changed and disposed in one or more devices different from the embodiment. The modules or units or components of the embodiments may be combined into one module or unit or component, and furthermore they may be divided into a plurality of sub-modules or sub-units or sub-components. All of the features disclosed in this specification (including any accompanying claims, abstract and drawings), and all of the processes or elements of any method or apparatus so disclosed, may be combined in any combination, except combinations where at least some of such features and/or processes or elements are mutually exclusive. Each feature disclosed in this specification (including any accompanying claims, abstract and drawings) may be replaced by alternative features serving the same, equivalent or similar purpose, unless expressly stated otherwise.
Furthermore, those skilled in the art will appreciate that although embodiments described herein include some features included in other embodiments, not other features, combinations of features of different embodiments are meant to be within the scope of the invention and form different embodiments. For example, in the claims of the present invention, any of the claimed embodiments may be used in any combination.
The present invention may also be embodied as apparatus or system programs (e.g., computer programs and computer program products) for performing a portion or all of the methods described herein. Such programs implementing the present invention may be stored on computer-readable media or may be in the form of one or more signals. Such a signal may be downloaded from an internet website, provided on a carrier signal, or provided in any other form.
It should be noted that the above-mentioned embodiments illustrate rather than limit the invention, and that those skilled in the art will be able to design alternative embodiments without departing from the scope of the appended claims. In the claims, any reference signs placed between parentheses shall not be construed as limiting the claim. The word "comprising" does not exclude the presence of elements or steps or the like not listed in a claim. The word "a" or "an" preceding an element does not exclude the presence of a plurality of such elements. The invention may be implemented by means of hardware comprising several distinct elements, and by means of a suitably programmed computer. In the unit claims enumerating several systems, several of these systems may be embodied by one and the same item of hardware. The usage of the words first, second and third, etcetera do not indicate any ordering and these words may be interpreted as names.
Claims (10)
1. A satellite attitude and orbit control semi-physical simulation test method is characterized by comprising the following steps:
acquiring attitude and orbit information of a satellite to be detected;
determining test content based on attitude and orbit information of the satellite to be tested;
describing the test content by using a preset language to obtain test requirement information, wherein the test requirement information comprises a signal statement for representing the test action of a virtual instrument corresponding to the satellite to be tested;
analyzing the signal statement to generate a test instruction;
determining corresponding test instrument equipment and a test component corresponding to the satellite to be tested in the virtual resource configuration information according to the test instruction;
controlling the corresponding test instrument equipment to execute the test instruction by using a driving function so as to enable the corresponding test instrument equipment to generate a test excitation signal;
controlling a test component corresponding to the satellite to be tested to respond to the test excitation signal and the test instruction to perform testing by using the drive function so as to enable the satellite to be tested to generate a target signal;
and determining a test result according to the target signal.
2. The method of claim 1, wherein before obtaining attitude and orbit information of the satellite under test, the method further comprises:
creating a factory class module;
acquiring routing information of a system, signal information of virtual resources and hardware equipment information by using the factory type module;
establishing routing resources, signal resources and virtual resources based on the routing information of the system, the signal information of the virtual resources and the hardware equipment information;
creating a subclass module based on the routing resources, the signal resources and the virtual resources, wherein the subclass module comprises a sensing class module, a source class module and a routing class module;
and generating a plurality of driving functions by utilizing the sensing module, the source module and the routing module, and respectively packaging the driving functions.
3. The method of claim 1, further comprising:
converting hardware equipment into a virtual instrument, wherein the hardware equipment comprises test instrument equipment and a satellite to be tested;
acquiring device resource names of the test instrument device and the satellite to be tested, virtual instrument names, virtual resource names, signal types, virtual instrument characteristic parameters, physical channel information and connection point information which respectively correspond to the test instrument device and the satellite to be tested;
and constructing the virtual resource configuration information based on the virtual instrument name, the virtual resource name, the signal type, the virtual instrument characteristic parameter, the physical channel information and the connection point information which are respectively corresponding to the test instrument equipment and the satellite to be tested.
4. The method of claim 2, wherein the subclass module further comprises: the system comprises a signal class module and a hardware equipment resource class module;
the description of the test content by using the preset language to obtain the test requirement information comprises the following steps:
extracting target test resources required by the test from the hardware equipment resources by using the hardware equipment resource class module, wherein the target test resources comprise target hardware equipment resources and target signal resources;
describing the target hardware equipment resource and the target signal resource into a signal statement by using the hardware equipment resource class module;
and packaging the signal statement by using the signal class module to obtain test requirement information.
5. The method of claim 2, wherein analyzing the signal statement to generate a test instruction comprises:
performing lexical analysis on the signal sentences, and extracting a plurality of keywords in the signal sentences;
determining whether a plurality of keywords in the signal statement all meet respective corresponding conditions based on the virtual resources;
if yes, converting the signal statement into an intermediate code;
transforming the intermediate code into test instructions.
6. The method of claim 2, wherein prior to controlling the respective test instrument device to execute the test instructions using the drive function to cause the respective test instrument device to generate the test stimulus signal, the method further comprises:
acquiring state information of the routing resource, the signal resource and the hardware equipment resource;
judging whether the state information of the routing resource, the signal resource and the hardware equipment resource meets a target state transition relation;
if yes, executing the corresponding test instrument equipment to execute the test instruction by using the drive function;
and updating the state of the routing resource, the signal resource and the resource with changed state in the hardware equipment resource to generate new state information.
7. The method of claim 5, wherein prior to transforming the signal statement into intermediate code, the method further comprises:
obtaining the description of the connection information of hardware equipment and a system required by the test, and determining whether the route is successfully connected;
if the connection is successful, determining whether the parameters described in the signal statement exceed a preset range;
if the signal statement does not exceed the preset range, determining whether the signal statement meets the target state transition relation;
and when the signal statement meets the target state transition relation, executing the step of transforming the signal statement into an intermediate code.
8. A satellite attitude and orbit control semi-physical simulation test system is characterized by comprising:
the system comprises a physical interface layer and a plurality of hardware devices, wherein the physical interface layer is used for being physically connected with the hardware devices, and the hardware devices comprise a satellite to be tested and test instrument equipment;
a device driver layer for providing driver functions for the plurality of hardware devices;
the virtual instrument resource layer is used for mapping hardware equipment resources into virtual instrument resources for management;
a software application layer, configured to obtain attitude and orbit information of a satellite to be tested, determine test content based on the attitude and orbit information of the satellite to be tested, and describe the test content by using a preset language to obtain test requirement information, where the test requirement information includes a signal statement characterizing a test action of a virtual instrument, and analyzes the test requirement information to generate a test instruction, and determines, according to the test instruction, corresponding test instrument equipment and a test component corresponding to the satellite to be tested in virtual resource configuration information, and controls, by using a drive function, the corresponding test instrument equipment to execute the test instruction, so that the corresponding test instrument equipment generates a test excitation signal, and controls, by using the drive function, the test component corresponding to the satellite to be tested to respond to the test excitation signal and the test instruction to perform a test, so that the corresponding satellite to be tested generates a target signal, and a test result is determined according to the target signal;
and the user interface is used for establishing interaction between the user and the software application layer.
9. A satellite attitude and orbit control semi-physical simulation testing device is characterized by comprising:
the information acquisition module is used for acquiring attitude and orbit information of the satellite to be detected;
the instruction generation module is used for determining test contents based on the attitude and orbit information of the satellite to be tested; describing the test content by using a preset language to obtain test requirement information, wherein the test requirement information comprises a signal statement representing a test action of the virtual resource; and analyzing the signal statement to generate a test instruction.
The hardware equipment determining module is used for determining corresponding testing instrument equipment and a testing component corresponding to the satellite to be tested in the virtual resource configuration information according to the testing instruction;
the excitation signal generation module is used for controlling the corresponding test instrument equipment to execute the test instruction by using a driving function so as to enable the corresponding test instrument equipment to generate a test excitation signal;
the target signal generation module is used for controlling a test component corresponding to the satellite to be tested to respond to the test excitation signal and the test instruction to test by using the drive function so as to enable the corresponding satellite to be tested to generate a target signal;
and the test result analysis module is used for determining a test result according to the target signal.
10. A computer-readable storage medium, wherein at least one instruction or at least one program is stored in the storage medium, and the at least one instruction or the at least one program is loaded and executed by a processor to implement the satellite attitude control semi-physical simulation test method according to any one of claims 1 to 7.
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