CN107273575B - Satellite task autonomous design method and system for quick response requirements - Google Patents
Satellite task autonomous design method and system for quick response requirements Download PDFInfo
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Abstract
The embodiment of the invention discloses a satellite task autonomous design method and a satellite task autonomous design system for a quick response requirement, wherein the method comprises the following steps: acquiring a first design parameter and a second design parameter by analyzing task requirements and index parameters of a satellite task; selecting and merging the platform shared component and the platform special component based on the first design parameter; selecting a platform component to be loaded into the platform shared component and the platform special component to form a platform simulation model; selecting and assembling a load sharing component and a load supply special component based on the second design parameter; assembling a load sharing assembly and a load special assembly, selecting a load component from a load software library and loading the load component into the load sharing assembly and the load special assembly to form a load simulation model; combining a platform simulation model and a load simulation model to generate a satellite simulation model; carrying out a virtual test on the satellite simulation model; and carrying out digital test on the satellite simulation model passing the virtual test, and evaluating the application efficiency of the satellite simulation model.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a satellite task autonomous design method and system for quick response requirements.
Background
The satellite generally includes: satellite platform and satellite load; the satellite load is carried on the satellite platform. In the prior art, the satellite has long development period and low efficiency, and the development cost is high due to the long development period and the low efficiency. Particularly, for the satellite with the requirement of quick response, the method has strict requirements on the development period of the satellite, and the design period of the satellite is shortened through a reasonable task design method, so that the development period is shortened, the development cost is reduced, and the quick response capability of the satellite is improved.
Disclosure of Invention
In view of this, embodiments of the present invention are expected to provide a method and a system for autonomous design of a satellite for meeting a demand for fast response, so as to solve the problems of long task design period and long satellite development period.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
the first aspect of the embodiments of the present invention provides an autonomous design method for a satellite task oriented to a quick response requirement, including:
acquiring a first design parameter of a satellite platform and a second design parameter of a satellite load by analyzing task requirements and index parameters of a satellite task;
selecting a platform common component from the common component subsystem and providing a platform specific component by the specific subsystem based on the first design parameter;
assembling the platform common assembly and the platform special assembly, selecting a platform component from a platform software library, and loading the platform component into the platform common assembly and the platform special assembly to form a platform simulation model of the satellite platform;
based on the second design parameter, selecting a load-sharing component from the shared-component subsystem and providing a load-specific component by the dedicated subsystem;
assembling the load sharing assembly and the load special assembly, selecting a load member from a load software library, and loading the load member into the load sharing assembly and the load special assembly to form a load simulation model for forming the satellite load;
combining the platform simulation model and the load simulation model to generate a satellite simulation model;
performing a virtual test on the satellite simulation model;
and carrying out digital test on the satellite simulation model passing the virtual test, and evaluating the application efficiency of the satellite simulation model to obtain an evaluation result.
Based on the above scheme, the method further comprises:
when the satellite simulation model fails to pass the satellite virtual test, respectively carrying out a load virtual test on the load model and a platform virtual test on the platform model, and determining an abnormal model which causes the virtual test to fail, wherein the abnormal model is the platform model and/or the load model;
and sequentially adjusting at least one of the software component, the special component and the shared component of the exception model according to the preset priority.
Based on the above scheme, the method further comprises:
carrying out corresponding virtual tests on the adjusted model;
assembling the model passing the virtual experiment into the satellite virtual platform;
and carrying out the satellite virtual test again on the satellite virtual platform.
Based on the above scheme, the sequentially adjusting at least one of the software component, the dedicated component and the shared component of the exception model according to the preset priority includes:
adjusting the software component at a first priority;
adjusting the application specific component with a second priority;
adjusting the shared components at a third priority;
wherein the first priority is higher than the second priority;
the second priority is higher than the third priority.
Based on the above scheme, the method further comprises:
selecting an orbit scheme of the satellite according to the task requirements and the index parameters;
judging whether the track corresponding to the track scheme meets the task requirement or not;
the method for obtaining the first design parameter of the satellite platform and the second design parameter of the satellite load by analyzing the task requirement and the index parameter of the satellite task comprises the following steps:
and analyzing the task requirement, the index parameter and the track scheme to obtain the first design parameter and the second design parameter.
The second aspect of the embodiments of the present invention provides an autonomous design system for a satellite task oriented to a fast response requirement, which includes a reconfiguration subsystem, a shared component subsystem, a dedicated component subsystem, a software subsystem, a testing subsystem, and a testing and evaluating subsystem:
the shared component subsystem is used for providing shared components, wherein the shared components comprise: a platform sharing assembly for a satellite platform and a load sharing assembly for a satellite load;
the application specific component subsystem is configured to provide an application specific component, wherein the application specific component comprises: a platform specific component for the satellite payload and a payload specific component for the satellite payload;
a software subsystem for providing software components, the software may include: a load member for the satellite load and a platform member for the satellite platform;
the reconstruction subsystem is used for obtaining a first design parameter of the satellite platform and a second design parameter of the satellite load by analyzing task requirements and index parameters of the satellite task; selecting a platform common component from the common component subsystem based on a first design parameter; assembling the platform common assembly and the platform special assembly provided by the special subsystem, selecting a platform component from a platform software library of the software subsystem, and loading the platform component into the platform common assembly and the platform special assembly to form a platform simulation model of the satellite platform; selecting a load sharing component from the sharing component subsystem based on a second design parameter; assembling the load sharing assembly and the load special assembly, selecting a load component from a load software library of the software subsystem, loading the load component into the load sharing assembly and the load special assembly, and forming a load simulation model for forming the satellite load; combining the platform simulation model and the load simulation model to generate a satellite simulation model;
the test subsystem is used for carrying out virtual test on the satellite simulation model;
and the testing and evaluating subsystem is used for carrying out digital testing on the satellite simulation model passing through the virtual test and evaluating the application efficiency of the satellite simulation model so as to obtain an evaluation result.
Based on the above scheme, the test subsystem is further configured to, when the satellite simulation model fails the satellite virtual test, perform a load virtual test on the load model and perform a platform virtual test on the platform model, respectively, and determine an abnormal model that causes the virtual test to fail, where the abnormal model is the platform model and/or the load model;
and the reconstruction subsystem is also used for sequentially adjusting at least one of a software component, a special component and a shared component of the abnormal model according to the preset priority.
Based on the scheme, the test subsystem is also used for carrying out corresponding virtual tests on the adjusted model;
the reconstruction subsystem is further used for assembling the model passing the virtual test into the satellite virtual platform;
and the test subsystem is also used for carrying out the satellite virtual test again on the satellite virtual platform.
Based on the above scheme, the reconfiguration sub-system is specifically configured to adjust the software component with a first priority; adjusting the application specific component with a second priority; adjusting the shared components at a third priority; wherein the first priority is higher than the second priority; the second priority is higher than the third priority.
Based on the above-mentioned scheme, the method,
the reconstruction subsystem is further used for selecting an orbit scheme of the satellite according to the task requirements and the index parameters; judging whether the track corresponding to the track scheme meets the task requirement or not;
the reconstruction subsystem is specifically configured to analyze the task demand, the index parameter, and the trajectory plan to obtain the first design parameter and the second design parameter.
The method and the system for independently designing the quick response satellite task uniformly analyze the task requirements and index parameters of the satellite task, then obtain design parameters for respectively designing a satellite platform and a satellite load, select a common component, design special software and select software components based on the design parameters to form a platform model of the satellite platform and a load model of the satellite load, finally assemble the platform model into the satellite model, and perform virtual test and digital test on the satellite model, thereby obtaining the satellite model meeting the virtual test and the digital test.
Drawings
Fig. 1 is a schematic flowchart of a first autonomous design method for a satellite mission oriented to a demand for quick response according to an embodiment of the present invention;
FIG. 2 is a flowchart illustrating a second method for autonomous design of a satellite mission oriented to a demand for quick response according to an embodiment of the present invention;
FIG. 3 is a schematic structural diagram of an autonomous design system for a satellite mission oriented to a demand for quick response according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of an autonomous design system for a satellite mission oriented to a demand for quick response according to a third embodiment of the present invention.
Detailed Description
The technical solution of the present invention is further described in detail with reference to the drawings and the specific embodiments of the specification.
As shown in fig. 1, the present embodiment provides an autonomous design method for a satellite mission facing a fast response requirement, including:
step S110: acquiring a first design parameter of a satellite platform and a second design parameter of a satellite load by analyzing task requirements and index parameters of a satellite task;
step S111: selecting a platform common component from the common component subsystem and providing a platform specific component by the specific subsystem based on the first design parameter;
step S121: assembling the platform common assembly and the platform special assembly, selecting a platform component from a platform software library, and loading the platform component into the platform common assembly and the platform special assembly to form a platform simulation model of the satellite platform;
step S112: based on the second design parameter, selecting a load-sharing component from the shared-component subsystem and providing a load-specific component by the dedicated subsystem;
step S122: assembling the load sharing assembly and the load special assembly, selecting a load member from a load software library, and loading the load member into the load sharing assembly and the load special assembly to form a load simulation model for forming the satellite load;
step S130: combining the platform simulation model and the load simulation model to generate a satellite simulation model;
step S140: performing a virtual test on the satellite simulation model;
step S150: and carrying out digital test on the satellite simulation model passing the virtual test, and evaluating the application efficiency of the satellite simulation model to obtain an evaluation result.
The embodiment provides an autonomous design method of a satellite task oriented to a quick response requirement, which can be executed in an autonomous design system of a satellite task oriented to a quick response requirement. The system comprises a reconstruction subsystem, a shared component subsystem, a special component subsystem, a software subsystem, a test subsystem and a test and evaluation subsystem. After the system receives the satellite tasks, all subsystems in the system can automatically analyze the satellite tasks and execute the autonomous design of the satellite model.
The shared component subsystem can provide shared components which can be used by different satellites; the special component subsystem can be used for designing special components meeting individual requirements according to the individual requirements of different satellites. The software subsystem may include: and the software library stores software components which are written in advance for various functions possibly to be acquired in the satellite.
And the reconstruction subsystem is used for assembling the special assembly and the common assembly into a corresponding satellite platform and a satellite load, loading a software component selected from the software library into the corresponding assembly, completing the assembly of the satellite model and obtaining the satellite model.
The common component subsystem may include a database that stores parameters and description information relating to various common components. The relevant parameters may include: structural parameters describing the corresponding shared components and functional parameters describing the functions that the corresponding shared components can realize. The structural parameters may include: physical size parameters, electric parameters such as voltage and current required to be supplied during working, and the like. The functional parameters may include: what functionality can be achieved. Generally, the common components correspond to physical hardware, and basic software, such as an operating system, is installed to provide a physical device for implementing specific functions.
In this embodiment, the database further stores the description information, and the description information may include: the common component is specific identification information in the common component subsystem, such as component number, component name, component usage description, and other various information.
The shared component subsystem provides a retrieval interface, and the retrieval interface can be used for a builder of the satellite to query the shared component through keyword index according to the task requirement or index parameter of the current satellite.
The task requirement is a work task which indicates that the corresponding satellite task needs to be completed by the satellite, and the index requirement can be a parameter which indicates the completion quality or completion degree of the work task which needs to be completed.
In some embodiments, the satellite system may also be an intelligent building system, a building task is built for a satellite which is built automatically, the building task is split, keywords are extracted automatically based on the task splitting, and the shared component subsystem automatically searches to determine the currently required shared component. The common components selected for this satellite may be one or more.
The special component subsystem can be used for providing operations such as generation and construction of special components for specific requirements of different satellites, for example, redesigning a circuit meeting requirements according to subtasks needing to be completed at present or utilizing a plurality of module devices to complete special components with specific functions.
In some embodiments, when the number or frequency of repeated use of a specific component reaches a threshold, the specific component can be packaged into a common component to form related information of the corresponding common component, and the common component subsystem is configured into the common component for the next satellite building. The common components provided by the common component subsystem in this embodiment may be: the method includes the steps that the method is configured in advance based on input of workers, or the method can be automatically generated according to a shared component generation strategy in a satellite building process, specifically, for example, a shared component subsystem is connected with a special component subsystem, the special component generated by the special component subsystem is set as a standby component of a shared component, and then the shared component is automatically generated according to the occurrence frequency and/or frequency of the standby components achieving the same function.
In some embodiments, the software subsystem may include a standardized component library, which may be used to provide various written software and/or programs that may be directly applied to various components that provide an application-level build and installation environment for the satellite, such as a basic operating system, without modification or with modification of only individual parameters.
For example, the standardized component library stores standardized components, which can be used for detection procedures of sensitive parameter detection of various sensors. The detection program is edited, and when the current satellite is built, various parameters such as detection period, detection signal strength and the like can be added to the detection program according to the index parameters of the current satellite, so that the detection program can be directly loaded into the corresponding sensor for use. Here, the sensor may include: the star sensor, the gyroscope, the magnetometer, the Global Positioning System (GPS) receiver and the sun sensor can detect the attitude and the orbit of the satellite. The gesture may include: attitude angular rate, attitude angle, etc. of the satellite. The track may include: flight acceleration of the satellite, orbit, etc.
In this embodiment, the satellite system further includes: and (5) reconstructing the subsystem. The reconfiguration sub-system 140 here may be a sub-system that connects each selected common component, or a specially constructed dedicated component.
In this embodiment, the reconstruction subsystem includes: and a core control component. The core control component here may be one or more servers, which may serve as a master control device for the satellite.
In this embodiment, the common component provided by the common component subsystem and the dedicated component provided by the dedicated subsystem 120 may be directly or indirectly connected to the core control component. The direct connection here may include: establishing a transmission link directly with the core control component, where the transmission link is not relayed by other relay components, and the method may include: a wireless link or a wired link. The indirect connection includes: a common component or a dedicated component connected to the core control component by other components.
In this embodiment, the reconfiguration sub-system, after obtaining each component, connects each component according to the structural information and the index parameter of the satellite to form an internal network of the satellite, and configures an external communication interface for the internal network, where the external communication interface is used for the satellite to communicate with other devices as a whole, for example, to communicate with other satellites or communicate with a ground satellite monitoring center.
In this embodiment, the internal Network of the satellite may be a Network based on a Controller Area Network (CAN) bus. The topology structure of the internal network can be a bus network, a star network and the like. In order to improve the stability of the internal network, the internal network may be divided into a main network and a backup network from a logical level or from a physical level. When the main network of the satellite is normal, the main network is used for transmitting various data and instructions, the backup network is in a standby state, and when the main network of the satellite is abnormal, a part of sub-networks of the backup network or the whole backup network is switched to a working state to provide data transmission of an internal network. In this embodiment, the reconfiguration subsystem further provides a specific maintenance management policy applicable to the current internal network according to the currently established internal network and preset network maintenance policy information, so as to ensure the effectiveness of the internal network.
In a word, in the satellite system in this embodiment, through the division of the subsystems, the satellite can be built quickly according to the task requirements and index parameters of the satellite which needs to be built currently, and the satellite system has the characteristics of being fast in building rate, short in period, low in cost and the like.
In some embodiments, the common component subsystem comprises: a common component library; the common component library comprises at least one of:
a circuit board, comprising: a standardized interface;
the single machine comprises a standardized single machine and a non-standardized single machine; wherein the standardized single machine comprises: a standardized interface; the non-standardized single machine comprises: a non-standardized interface;
a communication component for performing internal communication of the satellite or the external communication;
the battery component is used for providing electric energy required by the satellite;
the reconfiguration subsystem is specifically configured to connect the standardized interface based on the internal interface of the satellite, and connect the non-standardized interface through an interface adapter or a communication protocol conversion.
In this embodiment the circuit board may include: various integrated circuit boards, such as Printed Circuit Boards (PCBs) and the like, which may perform certain functions, are typically unpackaged bare boards. For example, the circuit board of the transformer, here the transformer, may provide the variation of the voltage for the different components of the satellite.
The single machine may typically be a single device enclosed within a housing. The single device includes a housing and an assembled integrated structure located within the housing that can be combined to perform a particular operation.
In this embodiment, the housing of the single computer may be provided with interfaces for connecting other components, and the interfaces may be classified into standardized interfaces and non-standardized interfaces according to whether the interfaces are interfaces of a predetermined type. In the embodiment, all standardized interfaces support the same type of interface protocol, and can be connected with each other and correctly communicate.
In this embodiment, the non-standardized interface may not be compatible with the standardized interface in terms of hardware structure or the executed interface protocol, so that the reconfiguration subsystem 140 is required to reconfigure the interface. In this embodiment, the interface reconfiguration may include: successful communication between different non-standardized interfaces, or between non-standardized interfaces, is enabled through software setup or introduction of interface adapters. In this embodiment, the interface reconfiguration may further include: and loading a data conversion application from a non-standardized interface to a corresponding component, or loading the data conversion application on the interface adapter, and the like.
In this embodiment, the common component further includes other components, for example, a communication component, where the communication component may include: an antenna for an external network and/or the like. The antenna enables communication through transmission of wireless signals.
The power supply assembly may include: and the storage battery can store electric energy and provide required electric energy for the operation of the satellite.
The power supply assembly may further include: the photovoltaic module, photovoltaic module can be used to convert light energy into electric energy.
In some embodiments, the power supply component may further comprise: the storage battery is connected with the photovoltaic module through a connecting component; the photovoltaic module is used for converting light energy into electric energy and supplying power to the storage battery, and the storage battery provides an external power supply interface and supplies power to other components through the external power supply interface.
The photovoltaic module specifically can include: solar sailboards, and the like.
In some embodiments, the core control component comprises: the processor is used for the satellite affair management of the satellite, the calculation of the attitude and the flight orbit of the satellite, the measurement and control calculation between the satellite and the ground and the measurement and control calculation between the satellites; and the measurement and control transponder is used for carrying out measurement and control response.
The processor in this embodiment may be various computers with computing power, and the processor is mainly used for computing and processing various data, for example, performing various transaction management of satellite operation. For example, controlling the satellite to return various affairs management such as images or videos collected by the satellite to a control center on the ground at a predetermined time may further include: and monitoring the health condition of the satellite, returning health condition information to a ground monitoring center, and the like.
In this embodiment, the reconfiguration sub-system may be configured to determine a first design parameter for designing the satellite platform and a second design parameter for designing the satellite load according to the task requirement and the index parameter.
The first design parameter may include: platform structure parameters and platform function parameters; the second design parameter includes: structural parameters of the load and functional parameters of the load.
The platform structure parameters can describe information such as physical size, external mechanical structure and internal mechanical structure, internal network structure and external communication interface of the satellite platform, and can be used for selection and connection of each platform component forming the satellite platform.
The platform function parameter may be a parameter describing a function or a function combination parameter that the satellite platform needs to complete. For example, by failing to resolve the task requirements and index parameters of S110, which functions the satellite platform needs to execute in the task, and the execution timing between the functions, etc. are determined.
The load structure parameters of the satellite load can be used for describing the physical size, the external mechanical structure and the internal mechanical structure of the satellite load, the internal network structure, the external communication interface and the like, and can be used for selecting and connecting various components forming the satellite load.
The load function parameter can be a function or function combination parameter for describing the functions to be completed by the satellite load. For example, by failing to resolve the task requirements and index parameters of S110, which functions the satellite load needs to execute in the task, and the execution timing between the functions, etc. are determined.
However, neither the first design parameter nor the second design parameter is limited to the above examples, and for example, the second design parameter may further include: type parameters of the load type, etc.
When splitting the task requirement and the index parameter, the splitting may include: and attributing each subtask in the task requirement to a satellite platform and/or a satellite load so as to determine the design parameter of the task requirement, and decomposing the corresponding index parameter to the satellite platform or the satellite load based on the attribution of the subtask so as to determine the design parameter corresponding to the index parameter.
When the reconstruction subsystem carries out satellite platform and satellite load design, a circuit board list, circuit board parameters, a single machine list and single machine parameters for configuring the satellite platform and satellite word sum are determined according to the first design parameters and the second design parameters. The circuit board list records the required circuit board, and the circuit board parameters are performance parameters, structural parameters and the like of the circuit board. The structural parameters may include: volume and weight. The performance parameters may include: how large a signal such as voltage or current can be supported.
After the assembly of the satellite model is completed, carrying out virtual test on the satellite model; the satellite virtual experiment here may include: virtual mechanical test, virtual heat balance test and virtual noise test. The virtual mechanical test can be used for detecting parameters such as the strength of the corresponding satellite model for resisting external force and judging whether the satellite model meets mechanical requirements or not.
The virtual heat balance test is used for testing the heat balance of the satellite model when simulating the satellite to work, whether the satellite model can continuously keep a preset temperature to work and the like, and therefore whether the satellite model meets the corresponding heat balance requirement is judged.
And the virtual noise test is used for testing the anti-noise capability of the corresponding satellite model when the satellite model simulates the satellite to work, so as to determine whether the satellite model meets the anti-noise requirement.
Only if the currently designed satellite model meets these requirements, the satellite manufactured based on the currently designed satellite model can meet the various requirements.
The digital test in this embodiment is mainly used to load a virtual task to the satellite model, and perform a simulation test of the entire task on the satellite model. For example, flight anti-seismic and task execution simulation of the satellite model is performed. For example, in the three-dimensional model, flight demonstration is performed by simulating flight around the earth on the orbit determined in the orbit scheme by using each satellite model. For another example, a task of shooting a cloud picture at high altitude is simulated, and a test result of a digital test is obtained according to the test reflection of the satellite model.
In this embodiment, performance evaluation is also applied in the reverse direction, and in this embodiment, the performance evaluation may include: task satisfaction evaluation, task expansibility evaluation, reliability evaluation and the like.
In this embodiment, the task satisfaction evaluation may be a result of one or more digital tests on the virtual satellite model, and the completion degree of the simulation task is determined, so as to determine the task satisfaction evaluation.
In some cases, the satellite design may consider the task expansibility, and may improve the capability of the satellite to a certain extent in terms of the current task requirement, so in this embodiment, it may also be determined whether the satellite corresponding to the satellite model can perform a screen cabinet with parameters such as task expansion and expansion degree through an extremum test and the like.
The reliability assessment may be an assessment of the stability of the predetermined functions performed for various parts of the satellite.
In this embodiment, on one hand, the packaged common component is provided through the common subsystem, only the special subsystem is used for specially designing the special component, and the software subsystem selects various pre-programmed software components from the software library and directly loads the software components into the corresponding component, so that the determination period of the model of the satellite is greatly simplified, the determination efficiency of the model of the satellite is improved, and the development efficiency of the satellite is improved.
On the other hand, in the embodiment, the satellite platform and the satellite load of the satellite are developed in the system, and after the development is completed, the satellite platform and the satellite load are directly assembled into a satellite model for virtual test, digital test and application performance evaluation. On one hand, the system is developed by the same system, so that various problems caused by the fact that different systems respectively develop satellite loads and satellite platforms during subsequent docking are reduced, and the time required by development can also be reduced; on the other hand, the development in the same system can coordinate the development progress, the corresponding virtual test and digital test can be carried out by assembling the two parts of the satellite platform and the satellite load once the development is completed, the problem that the development period is delayed can be obviously reduced, the corresponding test and test can be carried out after the assembly is completed, other systems are not required to be transferred for testing or testing, the time consumption is reduced again, and the abnormal and timely adjustment can be carried out.
The embodiment provides a model file including model parameters and an evaluation file for performance evaluation after the obtained satellite model is output. The model file may be used for the production of satellites. The evaluation file may be used by the developer to determine the performance of the satellite.
Optionally, as shown in fig. 2, the method further includes:
step S160: when the satellite simulation model fails to pass the satellite virtual test, respectively carrying out a load virtual test on the load model and a platform virtual test on the platform model, and determining an abnormal model which causes the virtual test to fail, wherein the abnormal model is the platform model and/or the load model;
step S170: and sequentially adjusting at least one of the software component, the special component and the shared component of the exception model according to the preset priority.
And when the virtual test can not be passed, respectively carrying out corresponding virtual tests on the load model and the platform model, thereby positioning an abnormal point, and positioning whether the virtual test can not be passed to be the load model or the platform model. Therefore, the abnormal model is convenient to adjust the components, the connection among the components and the software components.
For example, the method further comprises:
carrying out corresponding virtual tests on the adjusted model;
assembling the model passing the virtual experiment into the satellite virtual platform;
and carrying out the satellite virtual test again on the satellite virtual platform.
After the abnormal model is adjusted, the virtual test needs to be performed again to ensure that the load model and/or the platform model assembled again on the satellite model are normal, so that the number of virtual tests is reduced.
Optionally, the sequentially adjusting at least one of the software component, the dedicated component, and the shared component of the exception model according to the preset priority includes:
adjusting the software component at a first priority;
adjusting the application specific component with a second priority;
adjusting the shared components at a third priority;
wherein the first priority is higher than the second priority;
the second priority is higher than the third priority.
The debugging software may include: and adjusting the injection parameters of the standardized part component, updating the code of the standardized part component and showing the version of the standardized part component.
The adjustment specific component comprises: adjusting the hardware of the special-purpose component, redesigning the special-purpose component, and adjusting the connection between the special-purpose component and other components.
The adjusting common component can comprise: replacing the shared component and adjusting the connection of the shared component and other components.
The first priority is higher than a second priority, which is higher than the third priority. Since the shared component is a basic component and is a hardware structure with a low error rate used by the satellite, the possibility of testing different components is low, and the debugging can be finally carried out. The dedicated components are specifically designed and may be better than the common components for tuning, with a slightly higher probability of failing the test relative to the common components. If the software adjustment, i.e. the adjustment of the standardized components, is possible, the satellite can meet the desired requirements, with low debugging costs, and therefore with the highest priority.
The method further comprises the following steps:
selecting an orbit scheme of the satellite according to the task requirements and the index parameters;
judging whether the track corresponding to the track scheme meets the task requirement or not;
the step S110 may include:
and analyzing the task requirement, the index parameter and the track scheme to obtain the first design parameter and the second design parameter.
In this embodiment, the track scheme may include: the orbit after the satellite has operated properly, and how to reach the parameters of the orbit.
Each satellite may have a specific task, and after the determination of the orbit scheme is completed, it is necessary to verify whether the orbit proposed in the orbit scheme can meet the task requirements of the satellite, and if so, the orbit scheme is accepted, and if not, the orbit scheme needs to be readjusted.
Once the orbit scheme of the satellite is determined, the design of the satellite platform and the satellite load is directly affected, so in step S110 of this embodiment, the first design parameter and the second design parameter are obtained based on the three information, i.e., the task requirement, the index parameter and the orbit scheme.
In this embodiment, the task requirement is a relevant parameter of a task that needs to be completed by the satellite, and the index parameter may include: a parameter indicative of a quality of a task to be completed; the index parameters may further include: the satellite itself needs to meet parameters of which performance requirements, which may include performance parameters of external impact resistance, noise resistance, and thermal balance. However, neither the task requirements nor the index parameters are limited to the above examples.
As shown in fig. 3, the present embodiment provides a satellite mission autonomous design system oriented to the demand of quick response, which includes a reconfiguration subsystem 110, a shared component subsystem 120, a dedicated component subsystem 130, a software subsystem 140, a testing subsystem 150, and a testing and evaluating subsystem 160:
the common component subsystem 120 is configured to provide a common component, wherein the common component comprises: a platform sharing assembly for a satellite platform and a load sharing assembly for a satellite load;
the application-specific component subsystem 130 is configured to provide application-specific components, wherein the application-specific components include: a platform specific component for the satellite payload and a payload specific component for the satellite payload;
a software subsystem 140 for providing software components, the software may include: a load member for the satellite load and a platform member for the satellite platform;
the reconstruction subsystem 110 is used for obtaining a first design parameter of a satellite platform and a second design parameter of a satellite load by analyzing task requirements and index parameters of a satellite task; selecting a platform common component from the common component subsystem based on a first design parameter; assembling the platform common assembly and the platform special assembly provided by the special subsystem, selecting a platform component from a platform software library of the software subsystem, and loading the platform component into the platform common assembly and the platform special assembly to form a platform simulation model of the satellite platform; selecting a load sharing component from the sharing component subsystem based on a second design parameter; assembling the load sharing assembly and the load special assembly, selecting a load component from a load software library of the software subsystem, loading the load component into the load sharing assembly and the load special assembly, and forming a load simulation model for forming the satellite load; combining the platform simulation model and the load simulation model to generate a satellite simulation model;
the test subsystem 150 is used for performing a virtual test on the satellite simulation model;
the testing and evaluating subsystem 160 is configured to perform a digital test on the satellite simulation model passing through the virtual test, and evaluate the application performance of the satellite simulation model to obtain an evaluation result.
Optionally, the testing subsystem 150 is further configured to, when the satellite simulation model fails the satellite virtual test, perform a load virtual test on the load model and perform a platform virtual test on the platform model respectively, and determine an abnormal model causing the virtual test to fail, where the abnormal model is the platform model and/or the load model;
the reconfiguration sub-system 110 is further configured to sequentially adjust at least one of a software component, a dedicated component, and a shared component of the exception model according to a preset priority.
Further, the testing subsystem 150 is further configured to perform a corresponding virtual test on the adjusted model; the reconstruction subsystem 110 is further configured to assemble the model passing the virtual experiment into the satellite virtual platform; the testing subsystem 150 is further configured to perform the satellite virtual test again on the satellite virtual platform.
In some embodiments, the reconfiguration sub-system 110 is specifically configured to adjust the software components at a first priority; adjusting the application specific component with a second priority; adjusting the shared components at a third priority; wherein the first priority is higher than the second priority; the second priority is higher than the third priority.
In addition, the reconstruction subsystem 110 is further configured to select an orbit scheme of the satellite according to the task requirement and the index parameter; judging whether the track corresponding to the track scheme meets the task requirement or not; the reconstruction subsystem 110 is specifically configured to determine the first design parameter and the second design parameter according to the track scheme, the task requirement, and the index parameter.
Two specific examples are provided below in connection with any of the above embodiments:
example 1:
the example provides a satellite task autonomous design method for a quick response requirement, which includes:
the first step is as follows: receiving task requirements and index parameters input by a user from a human-computer interface;
the second step is that: analyzing task requirements and index parameters to form a component list and component parameters, and sending the component list and the component parameters to the shared component subsystem, the special component subsystem and the software subsystem, so as to select a shared component, a special component and a corresponding software component;
the third step: assembling components and loading software components;
the fourth step: carrying out virtual test on the assembled satellite model;
the fifth step: carrying out digital test on the satellite model passing the virtual test;
and a sixth step: application performance evaluation was performed.
And when the virtual test fails or the digital test fails in the fourth step and the fifth step, the reconstruction subsystem performs adjustment on the satellite model again.
Example 2:
as shown in fig. 4, the present example provides an autonomous design method of a satellite mission facing a demand for quick response, including:
step S1: analyzing task requirements and index parameters;
step S2: determining a track scheme based on the analysis result;
step S3: judging whether the track corresponding to the track scheme meets the task requirement, if not, returning to the step S2, and if so, entering the step S4:
step S4: determining design parameters of a satellite model;
step S5: selecting a component based on the design parameters; and selecting the optimal shared component and the most appropriate software component and the like through an objective optimization function.
Step S6: designing the special components based on the design parameters;
step S7: if the virtual test is not passed, the process proceeds to step S8, and if the test is passed, the process proceeds to step S9:
step S8: judging whether to reselect the shared component, if so, returning to the step S5, otherwise, returning to the step S6;
step S9: digital testing is performed.
Step S10: if the application efficiency evaluation is carried out through the digital test;
step S11: and outputting a model file of the satellite model and an evaluation result of the application performance evaluation.
In the several embodiments provided in the present application, it should be understood that the disclosed apparatus and method may be implemented in other ways. The above-described device embodiments are merely illustrative, for example, the division of the unit is only a logical functional division, and there may be other division ways in actual implementation, such as: multiple units or components may be combined, or may be integrated into another system, or some features may be omitted, or not implemented. In addition, the coupling, direct coupling or communication connection between the components shown or discussed may be through some interfaces, and the indirect coupling or communication connection between the devices or units may be electrical, mechanical or other forms.
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, that is, 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, all the functional units in the embodiments of the present invention may be integrated into one processing module, or each unit may be separately used as one unit, or two or more units may be integrated into one unit; the integrated unit can be realized in a form of hardware, or in a form of hardware plus a software functional unit.
Those of ordinary skill in the art will understand that: all or part of the steps for implementing the method embodiments may be implemented by hardware related to program instructions, and the program may be stored in a computer readable storage medium, and when executed, the program performs the steps including the method embodiments; and the aforementioned storage medium includes: a mobile storage device, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk or an optical disk, and other various media capable of storing program codes.
The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and all the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (6)
1. A satellite task autonomous design method facing to a quick response requirement is characterized by comprising the following steps:
acquiring a first design parameter of a satellite platform and a second design parameter of a satellite load by analyzing task requirements and index parameters of a satellite task;
selecting a platform common component from the common component subsystem and providing a platform specific component by the specific subsystem based on the first design parameter;
assembling the platform common assembly and the platform special assembly, selecting a platform component from a platform software library of a software subsystem, and loading the platform component into the platform common assembly and the platform special assembly to form a platform simulation model of the satellite platform;
based on the second design parameter, selecting a load-sharing component from the shared-component subsystem and providing a load-specific component by the dedicated subsystem;
assembling the load sharing assembly and the load special assembly, selecting a load component from a load software library of a software subsystem to load into the load sharing assembly and the load special assembly to form a load simulation model for forming the satellite load; wherein the software subsystem is to provide software components including the payload component for the satellite payload and the platform component for the satellite platform;
combining the platform simulation model and the load simulation model to generate a satellite simulation model;
performing a virtual test on the satellite simulation model;
carrying out digital test on the satellite simulation model passing the virtual test, and evaluating the application efficiency of the satellite simulation model to obtain an evaluation result;
when the satellite simulation model fails the virtual test, respectively performing a load virtual test on the load simulation model and a platform virtual test on the platform simulation model, and determining an abnormal model which causes the virtual test to fail, wherein the abnormal model is the platform simulation model and/or the load simulation model;
adjusting at least one of the software component, the special component and the shared component of the abnormal model in sequence according to a preset priority, comprising: adjusting the software component at a first priority; adjusting the application specific component with a second priority; adjusting the shared components at a third priority; wherein the first priority is higher than the second priority; the second priority is higher than the third priority.
2. The method of claim 1,
the method further comprises the following steps:
carrying out corresponding virtual tests on the adjusted model;
assembling the model passing the virtual test into the satellite simulation model;
and carrying out the virtual test again on the satellite simulation model.
3. The method according to claim 1 or 2,
the method further comprises the following steps:
selecting an orbit scheme of the satellite according to the task requirements and the index parameters;
judging whether the track corresponding to the track scheme meets the task requirement or not;
the method for obtaining the first design parameter of the satellite platform and the second design parameter of the satellite load by analyzing the task requirement and the index parameter of the satellite task comprises the following steps:
and analyzing the task requirement, the index parameter and the track scheme to obtain the first design parameter and the second design parameter.
4. An autonomous design system of satellite tasks facing to quick response requirements is characterized by comprising a reconstruction subsystem, a shared component subsystem, a special component subsystem, a software subsystem, a test subsystem and a test and evaluation subsystem:
the shared component subsystem is used for providing shared components, wherein the shared components comprise: a platform sharing assembly for a satellite platform and a load sharing assembly for a satellite load;
the application specific component subsystem is configured to provide an application specific component, wherein the application specific component comprises: a platform specific component for the satellite payload and a payload specific component for the satellite payload;
a software subsystem for providing software components, the software components may include: a load member for the satellite load and a platform member for the satellite platform;
the reconstruction subsystem is used for obtaining a first design parameter of the satellite platform and a second design parameter of the satellite load by analyzing task requirements and index parameters of the satellite task; selecting a platform common component from the common component subsystem based on a first design parameter; assembling the platform common assembly and the platform special assembly provided by the special subsystem, selecting a platform component from a platform software library of the software subsystem, and loading the platform component into the platform common assembly and the platform special assembly to form a platform simulation model of the satellite platform; selecting a load sharing component from the sharing component subsystem based on a second design parameter; assembling the load sharing assembly and the load special assembly, selecting a load component from a load software library of the software subsystem, loading the load component into the load sharing assembly and the load special assembly, and forming a load simulation model for forming the satellite load; combining the platform simulation model and the load simulation model to generate a satellite simulation model;
the test subsystem is used for carrying out virtual test on the satellite simulation model;
the testing and evaluating subsystem is used for carrying out digital testing on the satellite simulation model passing through the virtual test and evaluating the application efficiency of the satellite simulation model to obtain an evaluation result;
the test subsystem is further configured to, when the satellite simulation model fails the virtual test, perform a load virtual test on the load simulation model and perform a platform virtual test on the platform simulation model, respectively, and determine an abnormal model causing the virtual test to fail, where the abnormal model is the platform simulation model and/or the load simulation model;
the reconfiguration sub-system is further configured to sequentially adjust at least one of a software component, a dedicated component, and a shared component of the exception model according to a preset priority, and includes: adjusting the software component at a first priority; adjusting the application specific component with a second priority; adjusting the shared components at a third priority; wherein the first priority is higher than the second priority; the second priority is higher than the third priority.
5. The system of claim 4,
the test subsystem is also used for carrying out corresponding virtual tests on the adjusted model;
the reconstruction subsystem is also used for assembling the model passing the virtual test into the satellite simulation model;
and the test subsystem is also used for carrying out the virtual test again on the satellite simulation model.
6. The system of claim 4 or 5,
the reconstruction subsystem is further used for selecting an orbit scheme of the satellite according to the task requirements and the index parameters; judging whether the track corresponding to the track scheme meets the task requirement or not;
the reconstruction subsystem is specifically configured to analyze the task demand, the index parameter, and the trajectory plan to obtain the first design parameter and the second design parameter.
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