CN115755655A - Control method, device and equipment for testing, launching and controlling process of aerospace equipment - Google Patents
Control method, device and equipment for testing, launching and controlling process of aerospace equipment Download PDFInfo
- Publication number
- CN115755655A CN115755655A CN202310029913.5A CN202310029913A CN115755655A CN 115755655 A CN115755655 A CN 115755655A CN 202310029913 A CN202310029913 A CN 202310029913A CN 115755655 A CN115755655 A CN 115755655A
- Authority
- CN
- China
- Prior art keywords
- module
- test
- flow
- popup
- instruction
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P90/00—Enabling technologies with a potential contribution to greenhouse gas [GHG] emissions mitigation
- Y02P90/02—Total factory control, e.g. smart factories, flexible manufacturing systems [FMS] or integrated manufacturing systems [IMS]
Landscapes
- Testing Of Individual Semiconductor Devices (AREA)
Abstract
The invention provides a method, a device and equipment for controlling a test, launch and control flow of space equipment, wherein the method comprises the following steps: acquiring a test, launch and control flow for testing the space equipment, wherein the test, launch and control flow comprises the following steps: the system comprises a starting module and at least one flow module, wherein the flow module encapsulates at least one part of test instructions of the test, launch and control flow; when the instruction executed by the starting module is detected, executing the test instruction corresponding to the first flow module according to the first flow module pointed by the starting module to obtain a test result; the scheme of the invention realizes more convenient and visual configuration, perfects each condition in the process execution through the multi-branch configuration structure, and increases the control capability of the tester on the measurement and control process.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a method, a device and equipment for controlling a test, launch and control flow of aerospace equipment.
Background
Before and after the carrier rocket is ignited to fly, the measurement and launch control system needs to execute each flow strictly according to time and sequence, and performs system inspection, power-off control and the like on the carrier rocket to judge whether the rocket system can be ignited and launched normally, can fly normally and the like. Under the scenario, the measurement and launch control system needs to match the execution sequence and execution time of the process and execute the next execution action according to the execution result.
In the traditional implementation of the measurement, launch and control process control, in order to reduce the design difficulty, there are generally two implementation modes of process configuration:
the method is characterized in that pure codes are used for realizing that the power failure and state check of each power supply after the carrier rocket is launched from the initial network communication check to the master command and finally ignited for flight are completely carried out in the codes in series flow, and the communication control is carried out on the rocket and the ground system in sequence; however, the code reuse rate is not high, testers of different systems need different test flows and different configuration attributes, all test flows of each system need to be compiled and code maintenance is needed, the test cost and the coding time are increased, and the later maintenance workload is huge;
the other is that all needed control instructions and state judgment are divided into independent small modules which are placed in a list, and the small modules are manually selected from the list to another list according to a specific transmitting flow in sequence; however, the flow can only be executed in sequence, and after the current module fails to execute, only the whole flow can be stopped or a certain specified operation can be completed, and flexible abnormal branching cannot be realized.
Disclosure of Invention
The technical problem to be solved by the invention is to provide a method, a device and equipment for controlling a test, launch and control process of aerospace equipment, which solve the problem that the test, launch and control process cannot be flexibly configured, realize more convenient and visual configuration, perfect each condition in the process execution through a multi-branch configuration structure, and increase the control capability of a tester on the test, launch and control process.
In order to solve the technical problems, the technical scheme of the invention is as follows:
a control method for a test, launch and control process of aerospace equipment comprises the following steps:
acquiring a test, launch and control flow for testing the aerospace equipment, wherein the test, launch and control flow comprises the following steps: the system comprises a starting module and at least one flow module, wherein the flow module encapsulates at least one part of test instructions of the test, launch and control flow;
and when the instruction executed by the starting module is detected, executing the test instruction corresponding to the first flow module according to the first flow module pointed by the starting module to obtain a test result.
Optionally, the method for controlling the testing, launching and controlling process of the aerospace device further includes:
executing the test instruction of the branch flow module of at least one judgment module according to the test result; alternatively, the first and second electrodes may be,
and executing the test instruction corresponding to the second flow module according to the second flow module pointed by the first flow module.
Optionally, according to the test result, executing the test instruction of the at least one judgment module includes:
and when the test result meets the judgment condition of at least one judgment module pointed by the first flow module, executing the test instruction of the branch flow module corresponding to the judgment module.
Optionally, the judgment condition of the judgment module includes a boolean judgment condition, a character string, or an expression judgment condition.
Optionally, the method for controlling the testing, launching and controlling process of the aerospace device further includes:
and if the flow module is configured with a popup module, controlling the execution of the test instruction of the flow module according to the configuration instruction of the popup module.
Optionally, the execution of the test instruction of the flow module is controlled according to the configuration instruction of the pop-up window module, where the execution includes at least one of the following:
the popup module is a waiting flow module, and controls a test instruction of the flow module to be in a state of waiting for execution according to a waiting instruction preset in the waiting flow module;
the popup module is an emergency pause module, and controls the test instruction of the flow module to be in a pause state according to a pause instruction configured in advance in the emergency pause module;
the popup module is an emergency stop module, and controls the test instruction of the flow module to be in a stop state according to a stop instruction configured in advance in the emergency stop module;
the popup module is a popup selection branch module, and controls the test instruction of the flow module to trigger a branch selection popup window according to a popup selection instruction configured in the popup selection branch module in advance;
the popup module is a popup repeating module, and controls the test instruction of the flow module to repeatedly trigger the popup window according to a popup repeating instruction preset in the popup repeating module;
the popup module is a popup continuation module, and controls the test instruction of the flow module to trigger a continuous execution window according to a popup continuation instruction configured in advance in the popup continuation module;
the popup module is a popup stopping module and controls the flow module to be in a stopping state after the execution of the test instruction is finished according to a popup stopping instruction configured in advance in the popup stopping module;
the popup module is a popup countdown module, and controls the test instruction of the flow module to be continuously executed after the countdown instruction is executed according to a countdown instruction configured in the popup countdown module in advance.
Optionally, the test, launch and control flow further includes an end module, and the method further includes:
and when detecting the instruction executed by the ending module of the test, launch and control flow, ending the test, launch and control flow.
The invention also provides a control device for the testing, launching and controlling process of the space equipment, which comprises the following steps:
the acquisition module is used for acquiring a test, launch and control process for testing the space equipment, and the test, launch and control process comprises the following steps: the system comprises a starting module and at least one flow module, wherein the flow module encapsulates at least one part of test instructions of the test, launch and control flow;
and the processing module is used for executing the test instruction corresponding to the first flow module according to the first flow module pointed by the starting module when detecting the instruction executed by the starting module, so as to obtain a test result.
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 present 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:
according to the scheme, the testing, launching and controlling process for testing the space equipment is obtained, and comprises the following steps: the system comprises a starting module and at least one flow module, wherein the flow module encapsulates at least one part of test instructions of the test, launch and control flow; when the instruction executed by the starting module is detected, executing the test instruction corresponding to the first flow module according to the first flow module pointed by the starting module to obtain a test result; the problem that the measurement and control process cannot be flexibly configured is solved, visual configuration is simply, conveniently and visually realized, all conditions occurring in process execution are perfected through a multi-branch configuration structure, and the control capability of a tester on the measurement and control process is improved.
Drawings
Fig. 1 is a schematic flow chart of a control method of a test, launch and control flow of an aerospace device according to an embodiment of the invention;
FIG. 2 is a schematic diagram of a first test flow in an embodiment of the present invention;
FIG. 3 is a schematic diagram of a second test flow in an embodiment of the present invention;
FIG. 4 is a schematic diagram of a third test flow in an embodiment of the present invention;
FIG. 5 is a schematic diagram of a leakage check process according to an embodiment of the present invention;
fig. 6 is a schematic structural diagram of a control device of a measurement, launch and control flow of the aerospace device according to the embodiment of the 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 method for controlling a test, launch and control process of an aerospace device, including:
and step 12, when detecting the instruction executed by the starting module, executing the test instruction corresponding to the first flow module according to the first flow module pointed by the starting module to obtain a test result.
In the embodiment of the invention, the test and launch control flow is obtained and comprises the starting module and at least one flow module, wherein the starting module is used for controlling the operation of the test and launch control flow, so that when an instruction executed by the starting module is detected, the corresponding test instruction is executed according to the first flow module pointed by the starting module to obtain a test result, wherein a part of test instructions of the test and launch control flow are packaged in the first flow module.
It should be noted that, in order to meet the requirements of the test, launch and control flow on flexible configuration, at least a part of the test instructions of the test, launch and control flow are packaged in the starting module and/or the flow module; the starting module is necessary to exist in the configuration of the test and launch control flow, only one starting module can be configured in a group of test and launch control flows and is used as a starting point for executing the test and launch control flow, and when the test and launch control flow is operated, the starting point (the starting module) is determined, and then the next module is locked by searching the direction from the starting module; the bottom layer of the process module is a single process, such as ignition, power on/off, mode setting and the like, and attribute configuration can be performed, such as changing the process name, the IP address of a sender, the on-off state and the like, and detailed attribute configuration can enable a user to flexibly configure according to needs.
In addition, it should be noted that, when the measurement and control process is configured or modified, in order to implement visual configuration, the starting module and/or the process module may be placed in an interface, and then modules having execution relations are connected according to the process direction; the starting module and/or the flow module can be visualized into different shapes for indication, for example, the starting module is circular, the flow module is rectangular, and the like, the visualization of the execution relation among the modules can be realized through the connection of single arrows, and when an instruction executed by the starting module is detected, the execution sequence of the test and issue control flow can be visually checked according to the direction of the starting module to obtain a test result.
In an optional embodiment of the present invention, the method for controlling a test, launch and control process of an aerospace device further includes:
step 13, executing the test instruction of the branch flow module of at least one judgment module according to the test result; alternatively, the first and second liquid crystal display panels may be,
and 14, executing the test instruction corresponding to the second flow module according to the second flow module pointed by the first flow module.
In the embodiment of the invention, the test instruction of the branch flow module of at least one judgment module can be carried out according to the test result, so that the branching of the test, launch and control flow can be realized; specifically, at least one judging module is added behind a first flow module to realize a multi-branch structure, after the previous first flow module is executed, the previous first flow module is matched with the criterion in the judging module according to the test result, and if the matching is successful, the flow module behind the judging module is executed;
or, executing the test instruction corresponding to the second flow module according to the second flow module pointed by the first flow module, that is, after the previous first flow module is executed, the next flow module (the second flow module) is directly operated without judging the test result, and the second flow module is internally packaged with the test instruction.
In an optional embodiment of the present invention, step 13 includes:
step 131, when the test result meets the judgment condition of at least one judgment module pointed by the first flow module, executing the test instruction of the branch flow module corresponding to the judgment module.
The judgment condition of the judgment module comprises a Boolean judgment condition, a character string or an expression judgment condition.
In the embodiment of the invention, the judgment module can input the judgment condition in a self-defined way, the judgment condition can be a Boolean judgment condition, a character string or an expression judgment condition, and the judgment condition is determined according to the flow module pointing to the judgment module; the judgment condition may be a text condition such as "success", "failure", ">1", "=3", or may be another expression, and the present application is not limited thereto.
It should be noted that, in order to implement flexible configuration of the test, launch and control flow, at least one judgment module is arranged at the pointing position of the first flow module, the judgment module points to the second flow module (as a branch flow module), and the judgment module is connected with the first flow module, so that after the execution of the first flow module is completed, the test result is compared with the judgment condition of the judgment module, and the second flow module pointed by the judgment module is executed under the condition that the judgment condition is met.
As shown in fig. 2, in a specific embodiment, fig. 2 is a first test flow, and when an instruction executed by a start module is detected, the first test flow executes a test instruction corresponding to the first flow module according to the first flow module pointed by the start module to obtain a first test result;
when the first test result meets the judgment condition of success, executing a test instruction corresponding to the third flow module to obtain a second test result;
when the first test result meets the judgment condition of 'failure', executing a test instruction corresponding to the second flow module to obtain a third test result;
the judgment condition of the judgment module in the first test flow is a Boolean judgment condition, a judgment expression is packaged in the judgment module, and when the first test result meets the judgment expression, the judgment condition of success or failure can be met, so that multi-branch configuration of the test flow is realized.
As shown in fig. 3, in another specific embodiment, fig. 3 is a second test flow, when an instruction executed by a start module is detected, the first process module pointed by the start module executes a test instruction corresponding to the first process module to obtain a fourth test result;
when the first test result is 1, executing a test instruction corresponding to the third flow module to obtain a fifth test result;
when the first test result is 2, executing a test instruction corresponding to the second flow module to obtain a sixth test result;
when the first test result is 3, executing a test instruction corresponding to the fourth flow module to obtain a seventh test result, so that multi-branch configuration of the test flow is realized;
the judgment condition of the judgment module in the first test flow is an expression judgment condition, a boolean judgment expression is packaged in the judgment module and is used for judging whether the fifth test result executes the next flow of the corresponding judgment module, and multi-branch configuration of the test flow is realized.
In an optional embodiment of the present invention, the method for controlling a test, launch and control process of an aerospace device further includes:
and step 16, if the flow module is configured with a popup module, controlling the execution of the test instruction of the flow module according to the configuration instruction of the popup module.
In the embodiment of the invention, because the execution of the test and launch control process may need to be affected externally to realize the process control in the aerospace field, the execution of the test instruction of the process module is controlled according to the configuration instruction of the popup module by configuring the popup module for the process module, so that the external regulation of the test and launch control process can be realized.
In an alternative embodiment of the present invention, step 16 includes at least one of:
step 161, the popup module is a waiting process module, and controls the test instruction of the process module to be in a state of waiting for execution according to a waiting instruction configured in advance in the waiting process module;
step 162, the popup module is an emergency pause module, and the test instruction of the flow module is controlled to be in a pause state according to a pause instruction configured in advance in the emergency pause module;
step 163, the popup module is an emergency stop module, and controls the test instruction of the flow module to be in a stop state according to a stop instruction configured in advance in the emergency stop module;
step 164, the popup module is a popup selection branch module, and the test instruction of the flow module is controlled to trigger a branch selection popup window according to a popup selection instruction configured in advance in the popup selection branch module;
165, the popup module is a popup repeating module, and the test instruction of the flow module is controlled to repeatedly trigger the popup window according to a popup repeating instruction configured in advance in the popup repeating module;
step 166, the popup module is a popup continuation module, and the test instruction of the flow module is controlled to trigger a continuous execution window according to a popup continuation instruction configured in advance in the popup continuation module;
167, the popup module is a popup stop module, and the popup stop module controls the flow module to stop after the execution of the test instruction is completed according to a popup stop instruction configured in advance in the popup stop module;
and 168, controlling the test instruction of the flow module to be continuously executed after the execution of the countdown instruction is finished according to a countdown instruction configured in the popup countdown module in advance by the popup module.
In an embodiment of the present invention, the pop-up window module includes at least one of: a waiting process module; an emergency pause module; an emergency stop module; a popup window selection branch module; a pop-up window repeating module; a pop-up window continuing module; a pop-up window stop module; a pop-up window countdown module;
each pop-up window module is described below:
1) The waiting process module can be used for pausing when the current process module is executed continuously after the current process module is executed successfully; in the process of pausing, a tester can execute other test and launch control items, if the state or data of the test and launch control equipment needs to be judged manually, and after the state and the data are both correct, the tester clicks to confirm to execute the test and launch control items downwards. The waiting process module can configure display contents (such as a text content 'the current process has been carried out to a target stage' and the like), when the process is executed to the module, a popup window is carried out and the configured display contents are displayed, the popup window simultaneously comprises at least one button (such as a 'confirm' button, a 'cancel' button and the like), when a click instruction generated by the button is not received, the testing and issuing control process is always paused in the waiting process module, and the waiting process module realizes the pause function of the testing and issuing control module;
2) The emergency pause module is different from the waiting process module in that the waiting process module is a pause between two process modules, and the emergency pause module cannot guarantee whether the process module is paused between the two process modules or stopped in one process module; the emergency pause module is used for monitoring whether the state of pause is changed outside in real time by adding an external interface in a flow module code; for example, when the time for realizing the process in one process module is too long or an emergency pause is required between two process modules, the emergency pause of the current process can be carried out through the external emergency pause;
3) The emergency stop module can be triggered under the condition that the test, launch and control process needs to be stopped emergently, for example, the emergency stop module is used for preventing emergencies in the early stage of rocket launch and in the process of checking and preparing; once the emergency stop of the flow needing to be tested, sent and controlled occurs, an external interface can be added through the flow module, whether the external part has the state change of the stop or not is monitored in real time, and the emergency stop is carried out;
4) And a popup window selection branch module: because the flow with multiple selection branches can be configured for the test-launch control flow through the embodiment of the invention, the selection of the branches can be performed in a popup window form after the required flow or the known flow configured with the branches is performed, and the popup window displays the module names of all judgment modules connected under the flow, so that the timely selection can be made according to the test state of the current equipment or other factors;
5) The pop-up window repeating module is preferably applied to the judging module, common judgment in the judging module is generally judgment of success and failure of an execution result, if a special flow module is not configured after the current flow is successfully executed, the pop-up window repeating module can be directly executed downwards by default, but the pop-up window repeating module can be selected, continued and stopped if the execution fails, the pop-up window repeating module has a repeating function, the repeating function can realize that the current flow is executed again after the current flow fails, and certainly, if the execution result fails, the repeating flow can be selected again until the execution position is successful; it should be noted that the pop-up window repeating module may repeatedly execute the sequentially executed measurement and launch control flow in the sequentially executed measurement and launch control flow, but if the pop-up window repeating module is disposed on a branch of the flow configuration, the flow on the branch is repeated;
6) The popup window continuing module can be used for popup window after the execution result of the flow module is failure, and can choose to ignore the result of the current flow execution failure and continue to execute downwards, if the flow module has a branch of the judging module and the judging condition is success or failure, the branch corresponding to the judging result can be chosen to continue to execute;
7) The popup stop module is used for stopping selection after the execution of the flow module fails, and can realize immediate stop after the current flow fails, and is different from the emergency stop module in that the popup stop module stops the flow module when the current flow is executed and the next flow module does not start, rather than directly stopping the inside of the single flow module;
8) The popup countdown module is used for executing the next flow module after the execution of the single flow module is finished for a specified time, setting flow countdown according to actual conditions and adding a countdown attribute to the flow module with the required countdown function; when the execution of the current flow module is finished, the popup window can count down, and when the count down reaches zero, the popup window is automatically closed to continue the next flow module.
In an optional embodiment of the present invention, the test, launch and control flow further includes an end module, and the method further includes:
and step 17, when detecting that the instruction executed by the ending module of the test and launch control flow is detected, ending the test and launch control flow.
In the embodiment of the invention, the test, launch and control flow further comprises an ending module, a plurality of ending modules can be configured in a group of test, launch and control flows to serve as the end point of the execution of the test, launch and control flows, when the test, launch and control flows are operated, the test, launch and control flows can be completed after the execution reaches the end point (the ending module), and the test, launch and control flows are ended.
As shown in fig. 4, in a specific embodiment, fig. 4 is a third test flow, and when an instruction executed by the start module is detected, the first process module pointed by the start module executes a test instruction corresponding to the first process module to obtain an eighth test result;
executing the test instruction corresponding to the first flow module according to the second flow module pointed by the first flow module to obtain a ninth test result, and meanwhile, because a popup module and an interface popup are arranged in the second flow module, if the 'confirmation' is selected, the branch of success (pointing to a third flow module) is taken, and if the 'cancellation' is selected, the branch of failure (pointing to a seventh flow module) is taken;
if "determine" is selected: executing the test instruction corresponding to the third flow module to obtain a tenth test result, and executing the test instruction corresponding to the fourth flow module according to the fourth flow module pointed by the third flow module to obtain an eleventh test result; when the eleventh test result is successful, executing a fifth flow module; otherwise, the interface pops "continue", "repeat", "stop";
when the eleventh test result is successful, executing a test instruction corresponding to the fifth flow module to obtain a twelfth test result, wherein a popup countdown module is configured in the fifth flow module, and after the execution of the fifth flow module is completed, a countdown function is executed according to a preset countdown duration; after the countdown is finished, executing a test instruction corresponding to the sixth flow module according to the sixth flow module pointed by the fifth flow module to obtain a thirteenth test result, and ending the third test flow;
when the eleventh test result is failure, the interface pops "continue", "repeat", "stop"; if 'continue' is selected, executing a fifth flow module; if 'repeat' is selected, the pointed eighth flow module is executed, and the whole abnormal branch is repeated due to the abnormal branch, namely the eighth flow module is executed and then the fourth flow module is executed, and judgment is carried out again according to the result of the fourth flow module; if stop is selected, the process is directly ended;
if "cancel" is selected: executing the test instruction corresponding to the seventh flow module to obtain a fourteenth test result, and ending the third test flow;
as can be seen from the third test flow, the test, launch and control flow of the space equipment in the embodiment of the invention can flexibly configure the flow as required, can provide a complete test flow for a carrier rocket, is visual in configuration process, is simpler, more convenient and more intuitive, and has control capability on the test flow.
As shown in fig. 5, in another specific embodiment, fig. 5 shows a test, launch and control flow of electrical leakage inspection of a launch vehicle, when an instruction executed by a flow starting module is detected, ground ethernet communication interface inspection is performed according to a flow module pointed by the flow starting module, after the ground ethernet communication interface inspection is completed, ground integrated combined self-inspection flow and ground integrated combined self-inspection execution result query are sequentially performed, a query result is determined, and if the query result fails, the ground integrated combined self-inspection flow is returned until the query result succeeds; if the success is achieved, further obtaining ground power supply control parameters;
then, sequentially carrying out ground comprehensive power output control, + M1 bus power-up control, M1 electric leakage detection, core three-level instrument battery ground electric leakage detection, core one-level instrument battery ground electric leakage detection, safety battery ground electric leakage detection and initiating explosive battery ground electric leakage detection; the flow modules are sequentially executed, when any one flow module fails to execute or is checked to be wrong, the corresponding flow module is stopped by the popup window stopping module after being executed, so that whether the execution needs to be continued or not can be selected, and when an instruction needing to be continuously executed is received, the execution can be continued;
when the detection of the leakage of the initiating explosive device battery is finished, the M1 leakage detection and the M1 bus output are sequentially closed, and the detection of the M1 bus output flow is finished, so that the detection of the leakage of the carrier rocket is finished;
the modules are packaged with codes and/or test instructions of corresponding functions, the sequence of the flow modules can be adjusted according to actual test requirements, code maintenance cost and test time are reduced, and difficulty and time of test system development are reduced.
According to the embodiment of the invention, a test, launch and control process for testing the space equipment is obtained, and the test, launch and control process comprises the following steps: the system comprises a starting module and at least one flow module, wherein the flow module encapsulates part of test instructions of the test, launch and control flow; when the instruction executed by the starting module is detected, the test instruction corresponding to the first process module is executed according to the first process module pointed by the starting module to obtain a test result, so that the problem that the test, launch and control process cannot be flexibly configured is solved, visual configuration is more simply, conveniently and visually realized, each condition appearing in the process execution is perfected through a multi-branch configuration structure, and the control capability of a tester on the test, launch and control process is improved.
As shown in fig. 6, an embodiment of the present invention further provides a control device 60 for a measurement, launch and control process of an aerospace apparatus, including:
the obtaining module 61 is configured to obtain a test, launch and control procedure for testing the aerospace device, where the test, launch and control procedure includes: the system comprises a starting module and at least one flow module, wherein the flow module encapsulates at least one part of test instructions of the test, launch and control flow;
and the processing module 62 is configured to, when detecting that the start module is executed, execute the test instruction corresponding to the first flow module according to the first flow module pointed by the start module to obtain a test result.
Optionally, the processing module 62 is further configured to:
executing the test instruction of the branch flow module of at least one judgment module according to the test result; alternatively, the first and second electrodes may be,
and executing the test instruction corresponding to the second flow module according to the second flow module pointed by the first flow module.
Optionally, according to the test result, executing the test instruction of the at least one judgment module includes:
and when the test result meets the judgment condition of at least one judgment module pointed by the first flow module, executing the test instruction of the branch flow module corresponding to the judgment module.
Optionally, the judgment condition of the judgment module includes a boolean judgment condition, a character string, or an expression judgment condition.
Optionally, the processing module 62 is further configured to:
and if the flow module is configured with a popup module, controlling the execution of the test instruction of the flow module according to the configuration instruction of the popup module.
Optionally, the execution of the test instruction of the flow module is controlled according to the configuration instruction of the popup module, where the execution includes at least one of:
the popup module is a waiting process module, and controls the test instruction of the process module to be in a waiting state for execution according to a waiting instruction configured in advance in the waiting process module;
the popup module is an emergency pause module and controls the test instruction of the flow module to be in a pause state according to a pause instruction configured in the emergency pause module in advance;
the popup module is an emergency stop module and controls the test instruction of the flow module to be in a stop state according to a stop instruction configured in advance in the emergency stop module;
the popup module is a popup selection branch module, and controls the test instruction of the flow module to trigger a branch selection popup window according to a popup selection instruction configured in the popup selection branch module in advance;
the popup module is a popup repeating module, and controls the test instruction of the flow module to repeatedly trigger the popup window according to a popup repeating instruction preset in the popup repeating module;
the popup module is a popup continuation module, and controls the test instruction of the flow module to trigger a continuous execution window according to a popup continuation instruction configured in advance in the popup continuation module;
the popup module is a popup stopping module and controls the flow module to be in a stopping state after the execution of the test instruction is finished according to a popup stopping instruction configured in advance in the popup stopping module;
the popup module is a popup countdown module, and controls the test instruction of the flow module to be continuously executed after the countdown instruction is executed according to a countdown instruction configured in the popup countdown module in advance.
Optionally, the test, launch and control flow further includes an end module, and the processing module 62 is further configured to:
and when detecting the instruction executed by the ending module of the test, launch and control flow, ending the test, launch and control flow.
It should be noted that the apparatus is an apparatus corresponding to the above method, and all the implementations in the above method embodiment are applicable to the embodiment of the apparatus, and the same technical effects 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 that, when executed on a computer, cause the computer to perform the method as described above. All the implementation manners in the method embodiment are applicable to the 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 processor, storage medium, 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 containing program code for implementing the method or device. 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 (10)
1. A control method for a test, launch and control flow of aerospace equipment is characterized by comprising the following steps:
acquiring a test, launch and control flow for testing the aerospace equipment, wherein the test, launch and control flow comprises the following steps: the system comprises a starting module and at least one flow module, wherein the flow module encapsulates at least one part of test instructions of the test, launch and control flow;
and when the instruction executed by the starting module is detected, executing the test instruction corresponding to the first flow module according to the first flow module pointed by the starting module to obtain a test result.
2. The control method for the test, launch and control process of the aerospace device according to claim 1, further comprising:
executing the test instruction of the branch flow module of at least one judgment module according to the test result; alternatively, the first and second electrodes may be,
and executing the test instruction corresponding to the second flow module according to the second flow module pointed by the first flow module.
3. The method according to claim 2, wherein executing the test instruction of the at least one determining module according to the test result comprises:
and when the test result meets the judgment condition of at least one judgment module pointed by the first flow module, executing the test instruction of the branch flow module corresponding to the judgment module.
4. The control method of the measurement, issuance and control flow of the aerospace device according to claim 2, wherein the determination condition of the determination module includes a boolean determination condition, a character string, or an expression determination condition.
5. The control method for the measurement, launch and control process of the aerospace device according to claim 2, further comprising:
and if the flow module is configured with a popup module, controlling the execution of the test instruction of the flow module according to the configuration instruction of the popup module.
6. The control method for the test, launch and control process of the aerospace device according to claim 5, wherein the execution of the test instruction of the process module is controlled according to the configuration instruction of the pop-up window module, and the control method comprises at least one of the following steps:
the popup module is a waiting flow module, and controls a test instruction of the flow module to be in a state of waiting for execution according to a waiting instruction preset in the waiting flow module;
the popup module is an emergency pause module, and controls the test instruction of the flow module to be in a pause state according to a pause instruction configured in advance in the emergency pause module;
the popup module is an emergency stop module, and controls the test instruction of the flow module to be in a stop state according to a stop instruction configured in advance in the emergency stop module;
the popup module is a popup selection branch module, and controls a test instruction of the flow module to trigger a branch selection popup window according to a popup selection instruction configured in advance in the popup selection branch module;
the popup module is a popup repeating module, and controls the test instruction of the flow module to repeatedly trigger the popup window according to a popup repeating instruction preset in the popup repeating module;
the popup module is a popup continuation module, and controls the test instruction of the flow module to trigger a continuous execution window according to a popup continuation instruction configured in advance in the popup continuation module;
the popup module is a popup stopping module and controls the flow module to be in a stopping state after the execution of the test instruction is finished according to a popup stopping instruction configured in advance in the popup stopping module;
the popup module is a popup countdown module, and controls the test instruction of the flow module to be continuously executed after the countdown instruction is executed according to a countdown instruction configured in the popup countdown module in advance.
7. The method for controlling the measurement, launch and control process of the aerospace device according to claim 1, wherein the measurement, launch and control process further comprises an end module, and the method further comprises:
and when detecting the instruction executed by the ending module of the test, launch and control flow, ending the test, launch and control flow.
8. A control device for a testing, launching and control flow of space equipment is characterized by comprising:
the acquisition module is used for acquiring a test, launch and control process for testing the space equipment, and the test, launch and control process comprises the following steps: the system comprises a starting module and at least one flow module, wherein the flow module encapsulates at least one part of test instructions of the test, launch and control flow;
and the processing module is used for executing the test instruction corresponding to the first flow module according to the first flow module pointed by the starting module when the instruction executed by the starting module is detected, so as to obtain a test result.
9. A computing device, comprising: a processor, a memory storing a computer program which, when executed by the processor, performs the method of any one of claims 1 to 7.
10. A computer-readable storage medium storing instructions that, when executed on a computer, cause the computer to perform the method of any one of claims 1 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310029913.5A CN115755655A (en) | 2023-01-09 | 2023-01-09 | Control method, device and equipment for testing, launching and controlling process of aerospace equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310029913.5A CN115755655A (en) | 2023-01-09 | 2023-01-09 | Control method, device and equipment for testing, launching and controlling process of aerospace equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115755655A true CN115755655A (en) | 2023-03-07 |
Family
ID=85348801
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310029913.5A Pending CN115755655A (en) | 2023-01-09 | 2023-01-09 | Control method, device and equipment for testing, launching and controlling process of aerospace equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115755655A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102724006A (en) * | 2012-06-18 | 2012-10-10 | 上海卫星工程研究所 | Rapid self-checking system and method of satellite comprehensive testing system |
| CN105426299A (en) * | 2015-10-10 | 2016-03-23 | 中国运载火箭技术研究院 | Workflow technology-based testing data real-time interpretation system |
| CN107729242A (en) * | 2017-10-12 | 2018-02-23 | 郑州云海信息技术有限公司 | A kind of automated testing method, system, device and computer-readable storage medium |
| CN112440283A (en) * | 2020-12-11 | 2021-03-05 | 深圳市越疆科技有限公司 | Robot pop-up window interaction method and device, robot and computer storage medium |
| CN113821018A (en) * | 2021-11-22 | 2021-12-21 | 星河动力(北京)空间科技有限公司 | Carrier rocket test system |
-
2023
- 2023-01-09 CN CN202310029913.5A patent/CN115755655A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102724006A (en) * | 2012-06-18 | 2012-10-10 | 上海卫星工程研究所 | Rapid self-checking system and method of satellite comprehensive testing system |
| CN105426299A (en) * | 2015-10-10 | 2016-03-23 | 中国运载火箭技术研究院 | Workflow technology-based testing data real-time interpretation system |
| CN107729242A (en) * | 2017-10-12 | 2018-02-23 | 郑州云海信息技术有限公司 | A kind of automated testing method, system, device and computer-readable storage medium |
| CN112440283A (en) * | 2020-12-11 | 2021-03-05 | 深圳市越疆科技有限公司 | Robot pop-up window interaction method and device, robot and computer storage medium |
| CN113821018A (en) * | 2021-11-22 | 2021-12-21 | 星河动力(北京)空间科技有限公司 | Carrier rocket test system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2113898A1 (en) | Training simulators for engineering projects | |
| CN107576518B (en) | Fan testing method, device and system | |
| CN110907882B (en) | Electric energy meter-oriented virtualization test method and system | |
| CN107102949A (en) | Application program off-line test method and instrument | |
| CN105699788A (en) | Power supply time sequence measurement method, oscilloscope and system thereof | |
| CN104156305A (en) | Application program testing method and device | |
| CN112925705B (en) | Unmanned-duty-based carrier rocket flight software acceptance method and system | |
| CN115755655A (en) | Control method, device and equipment for testing, launching and controlling process of aerospace equipment | |
| Canny et al. | Model-based testing of GUI applications featuring dynamic Instanciation of widgets | |
| RU2627935C2 (en) | Method and apparatus for developing an aircraft warnings and procedures control system | |
| CN109739767A (en) | A kind of human-computer interaction interface logic function test method and device | |
| US9201113B2 (en) | Systems and methods for performing redundancy tests on turbine controls | |
| CN106814728A (en) | A kind of assembly detection apparatus based on product power supply interface sequential logic | |
| US20140041465A1 (en) | Equipment test method and associated test tool and test system | |
| Heitmeyer et al. | Applying a formal requirements method to three NASA systems: Lessons learned | |
| CN114115187A (en) | General detection platform and detection method for automatic airplane driving control system | |
| CN113358968A (en) | Automatic testing method and system for engineering machinery product and readable storage medium | |
| CN110737211B (en) | Multifunctional semi-physical simulation test control system and method for guided weapons | |
| CN114090432A (en) | Method, system, device, electronic equipment and storage medium for simulation test | |
| CN116595811B (en) | Inspection method and device for rocket system | |
| US9116191B2 (en) | Voltage-drop testing system, voltage-drop control apparatus, and method thereof | |
| CN112444344A (en) | Aerostat airbag air tightness detection device and method | |
| CN110816886B (en) | LabVIEW-based machine wheel cooling device testing system and testing method thereof | |
| CN116699534B (en) | Air interference environment construction method, system and device based on take-off instruction response | |
| CN211785674U (en) | Switching system of position actuation control unit simulator |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information |
Address after: 264000 No.1, Haixiang Middle Road, Fengcheng Street, Haiyang City, Yantai City, Shandong Province Applicant after: Dongfang space technology (Shandong) Co.,Ltd. Applicant after: Oriental space technology (Beijing) Co.,Ltd. Applicant after: Oriental space (Xi'an) Aerospace Technology Co.,Ltd. Applicant after: Orient Space (Hainan) Technology Co.,Ltd. Address before: 710100 Room 403, 4th floor, Xi'an Science and technology Northwest Building, No. 532, Shenzhou Third Road, national civil aerospace industry base, Chang'an District, Xi'an City, Shaanxi Province Applicant before: Oriental space (Xi'an) Aerospace Technology Co.,Ltd. Applicant before: Dongfang space technology (Shandong) Co.,Ltd. Applicant before: Oriental space technology (Beijing) Co.,Ltd. Applicant before: Orient Space (Hainan) Technology Co.,Ltd. |
|
| CB02 | Change of applicant information |