CN111459049A - Semi-physical simulation method and system - Google Patents
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- CN111459049A CN111459049A CN202010176337.3A CN202010176337A CN111459049A CN 111459049 A CN111459049 A CN 111459049A CN 202010176337 A CN202010176337 A CN 202010176337A CN 111459049 A CN111459049 A CN 111459049A
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- 238000004364 calculation method Methods 0.000 claims abstract description 60
- 238000005259 measurement Methods 0.000 claims abstract description 43
- 238000012795 verification Methods 0.000 abstract description 10
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- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B17/00—Systems involving the use of models or simulators of said systems
- G05B17/02—Systems involving the use of models or simulators of said systems electric
Abstract
The embodiment of the application discloses a semi-physical simulation method and a semi-physical simulation system, wherein the method comprises the following steps: the non-standard sphere infrared radiation simulation module receives flight parameters sent by the simulation calculation module, and the flight parameters are calculated and generated by the simulation calculation module according to a control instruction of the satellite-borne calculation module; calculating and generating non-standard sphere infrared radiation simulation information according to the flight parameters; and sending the infrared radiation simulation information of the non-standard sphere to an infrared earth sensitive module so that the infrared earth sensitive module generates measurement information and sends the measurement information to a satellite-borne calculation module. The problem that the simulation precision of infrared radiation characteristics of a simplified standard sphere is not high is solved, the high-precision infrared radiation characteristics simulation is realized, and the verification capability of an attitude control system is improved.
Description
Technical Field
The embodiment of the application relates to the technical field of simulation, in particular to a semi-physical simulation method and system.
Background
In the on-orbit operation stage of the satellite platform, an earth sensor is generally adopted to detect the infrared radiation energy of the earth, and the pitch angle and the roll angle of the platform relative to the local vertical line of the earth are obtained by combining the calculation of the orbit height. Closed-loop verification of various functions and performances of the earth sensor is one of key works of a semi-physical simulation system. In the satellite ground test semi-physical simulation test process, an earth simulator is adopted to simulate the infrared radiation characteristic of the earth according to different orbit heights and attitude information of a satellite platform, and provide light excitation information for an earth sensor.
In a semi-physical simulation test, in order to meet the requirement of the novel high-precision earth sensor on earth infrared radiation signal simulation, a non-standard sphere infrared radiation simulation method needs to be adopted to replace an original simplified standard sphere infrared radiation simulation method, the infrared radiation characteristic simulation of the high-precision earth simulator is realized, and the verification capability of the semi-physical simulation on a satellite attitude control system is improved.
Disclosure of Invention
Therefore, the embodiment of the application provides a semi-physical simulation method and system, the problems that the simulation precision of infrared radiation characteristics of a simplified standard sphere is not high and the like are solved, a non-standard sphere infrared radiation simulation method is designed, high-precision infrared radiation characteristic simulation is achieved, and the verification capability of an attitude control system is improved.
In order to achieve the above object, the embodiments of the present application provide the following technical solutions:
according to a first aspect of an embodiment of the present application, a semi-physical simulation method is provided, the method including:
the non-standard sphere infrared radiation simulation module receives flight parameters sent by the simulation calculation module, and the flight parameters are calculated and generated by the simulation calculation module according to a control instruction of the satellite-borne calculation module;
calculating and generating non-standard sphere infrared radiation simulation information according to the flight parameters;
and sending the infrared radiation simulation information of the non-standard sphere to an infrared earth sensitive module so that the infrared earth sensitive module generates measurement information and sends the measurement information to a satellite-borne calculation module.
Optionally, the non-standard sphere infrared radiation simulation module is configured to realize simulation of a non-standard sphere infrared radiation signal, and includes an analog input module, a non-standard sphere infrared radiation calculation module, and an analog output module.
Optionally, the generating of the nonstandard spherical infrared radiation simulation information according to the flight parameter calculation includes:
the analog input module receives the flight parameters and sends the flight parameters to the non-standard body infrared radiation calculation module; the non-standard body infrared radiation calculation module calculates the flight parameters to obtain non-standard sphere infrared radiation simulation information, and sends the non-standard sphere infrared radiation simulation information to the simulation output module;
the sending of the non-standard sphere infrared radiation simulation information to an infrared earth-sensitive module comprises:
and the analog output module sends the infrared radiation analog information of the non-standard sphere to an infrared earth sensitive module.
Optionally, the measurement information is generated by resolving according to the nonstandard sphere infrared radiation simulation information when the infrared earth sensitivity module receives a measurement instruction; the measurement instruction is sent by the satellite-borne computing module.
According to a second aspect of embodiments of the present application, there is provided a semi-physical simulation system, the system including:
the simulation input module is used for receiving flight parameters sent by the simulation calculation module, and the flight parameters are generated by the simulation calculation module according to the control instruction of the satellite-borne calculation module;
the non-standard sphere infrared radiation calculation module is used for calculating and generating non-standard sphere infrared radiation simulation information according to the flight parameters;
and the analog output module is used for sending the infrared radiation analog information of the non-standard sphere to the infrared earth sensitive module so that the infrared earth sensitive module generates measurement information and sends the measurement information to the satellite-borne calculation module.
Optionally, the analog input module is specifically configured to: receiving the flight parameters and sending the flight parameters to the non-standard body infrared radiation calculation module;
the non-standard body infrared radiation calculation module is specifically used for: calculating the flight parameters to obtain nonstandard spherical infrared radiation simulation information, and sending the nonstandard spherical infrared radiation simulation information to a simulation output module;
the analog output module is specifically configured to: and sending the infrared radiation simulation information of the non-standard sphere to an infrared earth sensitive module.
Optionally, the measurement information is generated by resolving according to the nonstandard sphere infrared radiation simulation information when the infrared earth sensitivity module receives a measurement instruction; the measurement instruction is sent by the satellite-borne computing module.
In summary, the embodiment of the present application provides a semi-physical simulation method and system, where a nonstandard spherical infrared radiation simulation module receives flight parameters sent by a simulation computation module, and the flight parameters are generated by the simulation computation module according to a control instruction of a satellite-borne computation module; calculating and generating non-standard sphere infrared radiation simulation information according to the flight parameters; and sending the infrared radiation simulation information of the non-standard sphere to an infrared earth sensitive module so that the infrared earth sensitive module generates measurement information and sends the measurement information to a satellite-borne calculation module. The problem that the simulation precision of infrared radiation characteristics of a simplified standard sphere is not high is solved, the high-precision infrared radiation characteristics simulation is realized, and the verification capability of an attitude control system is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It should be apparent that the drawings in the following description are merely exemplary, and that other embodiments can be derived from the drawings provided by those of ordinary skill in the art without inventive effort.
The structures, ratios, sizes, and the like shown in the present specification are only used for matching with the contents disclosed in the specification, so that those skilled in the art can understand and read the present invention, and do not limit the conditions for implementing the present invention, so that the present invention has no technical significance, and any structural modifications, changes in the ratio relationship, or adjustments of the sizes, without affecting the functions and purposes of the present invention, should still fall within the scope of the present invention.
Fig. 1 is a schematic flowchart of a semi-physical simulation method according to an embodiment of the present application;
FIG. 2 is a schematic diagram of an embodiment of semi-physical simulation provided in an embodiment of the present application;
fig. 3 is a block diagram of a semi-physical simulation system according to an embodiment of the present application.
Detailed Description
The present invention is described in terms of particular embodiments, other advantages and features of the invention will become apparent to those skilled in the art from the following disclosure, and it is to be understood that the described embodiments are merely exemplary of the invention and that it is not intended to limit the invention to the particular embodiments disclosed. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Fig. 1 shows a schematic flow diagram of a semi-physical simulation method provided by an embodiment of the application, which solves the problems that the simulation precision is not high by using a simplified standard sphere infrared radiation characteristic, and the like, and designs a non-standard sphere infrared radiation simulation method to realize high-precision infrared radiation characteristic simulation and meet the verification requirements of an attitude control system. The method comprises the following steps:
step 101: the non-standard sphere infrared radiation simulation module receives flight parameters sent by the simulation calculation module, and the flight parameters are calculated and generated by the simulation calculation module according to a control instruction of the satellite-borne calculation module.
Step 102: and calculating and generating non-standard sphere infrared radiation simulation information according to the flight parameters.
Step 103: and sending the infrared radiation simulation information of the non-standard sphere to an infrared earth sensitive module so that the infrared earth sensitive module generates measurement information and sends the measurement information to a satellite-borne calculation module.
In one possible implementation, the non-standard sphere infrared radiation simulation module is used for realizing simulation of a non-standard sphere infrared radiation signal and comprises an analog input module, a non-standard sphere infrared radiation calculation module and an analog output module.
In a possible implementation manner, in step 102, the analog input module receives the flight parameters and sends the flight parameters to the non-standard body infrared radiation calculation module; the non-standard body infrared radiation calculation module calculates the flight parameters to obtain non-standard sphere infrared radiation simulation information, and the non-standard sphere infrared radiation simulation information is sent to the simulation output module.
In a possible implementation manner, in step 103, the analog output module sends the non-standard spherical infrared radiation analog information to an infrared earth-sensitive module.
In a possible implementation manner, when the infrared earth sensing module receives a measurement instruction, the measurement information is generated by resolving according to the non-standard spherical infrared radiation simulation information; the measurement instruction is sent by the satellite-borne computing module.
In order to make the semi-physical simulation method provided by the embodiment of the present application clearer, a detailed description is now made with reference to fig. 2.
Fig. 2 shows a schematic diagram of a semi-physical simulation flywheel simulation system, which includes an on-board computation module 201, a simulation computation module 202, a nonstandard sphere infrared radiation simulation module 203, and an infrared earth sensitivity module 207. The nonstandard sphere infrared radiation simulation module 203 comprises a simulation input module 204, a nonstandard sphere infrared radiation calculation module 205 and a simulation output module 206.
The satellite-borne computing module 201 outputs a control instruction to the simulation computing module 202, the simulation computing module 202 generates flight parameters through internal computing and sends the flight parameters to the nonstandard spherical infrared radiation simulation module 203, and after the flight parameters are received by the analog input module 204 in the nonstandard spherical infrared radiation simulation module 203 and are processed through the nonstandard spherical infrared radiation computing module 205, the analog output module 206 outputs analog information. The analog information is provided as input to the infrared earth-sensitive module 207, which performs internal calculation to generate measurement information.
After the infrared earth sensitive module 207 receives the measurement instruction of the satellite-borne computing module 201, the infrared earth sensitive module 207 generates measurement information by using the analog information as input, so as to form a closed loop and complete the verification of the satellite attitude control system by the semi-physical simulation.
The satellite-borne computing module 201 is used for providing input instruction information to the simulation computing module 202, providing measurement instruction information to the infrared earth sensitivity module 207, and collecting and outputting measurement information.
The simulation calculation module 202 takes the output of the satellite-borne calculation module 201 as input, generates flight parameters through calculation, and provides the flight parameters as input to the nonstandard spherical infrared radiation simulation module 203.
The nonstandard sphere infrared radiation simulation module 203 realizes simulation of the nonstandard sphere infrared radiation signal by combining the internal simulation input module 204, the nonstandard sphere infrared radiation calculation module 205 and the simulation output module 206, and outputs simulation information.
The infrared earth sensing module 207 takes the analog information output by the nonstandard sphere infrared radiation analog module 203 as input, generates measurement information and provides the measurement information to the satellite-borne computing module 201 to form a closed loop, and thus semi-physical simulation is completed.
The semi-physical simulation system can improve the precision of infrared radiation simulation in semi-physical simulation, meet the high-precision detection requirement of the infrared earth sensor and complete the verification of the semi-physical simulation test in the satellite ground test process. The verification capability of the semi-physical simulation on the satellite attitude control system is improved.
In summary, the embodiment of the present application provides a semi-physical simulation method, where a nonstandard spherical infrared radiation simulation module receives a flight parameter sent by a simulation calculation module, and the flight parameter is generated by the simulation calculation module according to a control instruction of a satellite borne calculation module; calculating and generating non-standard sphere infrared radiation simulation information according to the flight parameters; and sending the infrared radiation simulation information of the non-standard sphere to an infrared earth sensitive module so that the infrared earth sensitive module generates measurement information and sends the measurement information to a satellite-borne calculation module. The problem that the simulation precision of infrared radiation characteristics of a simplified standard sphere is not high is solved, a non-standard sphere infrared radiation simulation method is designed, high-precision infrared radiation characteristic simulation is achieved, and the verification capability of an attitude control system is improved.
Based on the same technical concept, an embodiment of the present application further provides a semi-physical simulation system, as shown in fig. 3, the system includes:
the simulation input module 301 is configured to receive the flight parameters sent by the simulation calculation module, where the flight parameters are generated by the simulation calculation module according to the control instruction of the satellite borne calculation module.
And the nonstandard sphere infrared radiation calculation module 302 is used for calculating and generating nonstandard sphere infrared radiation simulation information according to the flight parameters.
The analog output module 303 is configured to send the non-standard sphere infrared radiation analog information to the infrared earth-sensitive module, so that the infrared earth-sensitive module generates measurement information and sends the measurement information to the satellite-borne calculation module.
In a possible implementation, the analog input module 301 is specifically configured to: and receiving the flight parameters and sending the flight parameters to the non-standard body infrared radiation calculation module.
In a possible implementation, the non-standard body infrared radiation calculation module 302 is specifically configured to: and calculating the flight parameters to obtain nonstandard spherical infrared radiation simulation information, and sending the nonstandard spherical infrared radiation simulation information to a simulation output module.
In a possible implementation manner, the analog output module 303 is specifically configured to: and sending the infrared radiation simulation information of the non-standard sphere to an infrared earth sensitive module.
In a possible implementation manner, when the infrared earth sensing module receives a measurement instruction, the measurement information is generated by resolving according to the non-standard spherical infrared radiation simulation information; the measurement instruction is sent by the satellite-borne computing module.
In the present specification, each embodiment of the method is described in a progressive manner, and the same and similar parts among the embodiments are referred to each other, and each embodiment focuses on the differences from the other embodiments. Reference is made to the description of the method embodiments.
It is noted that while the operations of the methods of the present invention are depicted in the drawings in a particular order, this is not a requirement or suggestion that the operations must be performed in this particular order or that all of the illustrated operations must be performed to achieve desirable results. Additionally or alternatively, certain steps may be omitted, multiple steps combined into one step execution, and/or one step broken down into multiple step executions.
Although the present application provides method steps as in embodiments or flowcharts, additional or fewer steps may be included based on conventional or non-inventive approaches. The order of steps recited in the embodiments is merely one manner of performing the steps in a multitude of orders and does not represent the only order of execution. When an apparatus or client product in practice executes, it may execute sequentially or in parallel (e.g., in a parallel processor or multithreaded processing environment, or even in a distributed data processing environment) according to the embodiments or methods shown in the figures. The terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, the presence of additional identical or equivalent elements in a process, method, article, or apparatus that comprises the recited elements is not excluded.
The units, devices, modules, etc. set forth in the above embodiments may be implemented by a computer chip or an entity, or by a product with certain functions. For convenience of description, the above devices are described as being divided into various modules by functions, and are described separately. Of course, in implementing the present application, the functions of each module may be implemented in one or more software and/or hardware, or a module implementing the same function may be implemented by a combination of a plurality of sub-modules or sub-units, and the like. The above-described embodiments of the apparatus 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.
Those skilled in the art will also appreciate that, in addition to implementing the controller as pure computer readable program code, the same functionality can be implemented by logically programming method steps such that the controller is in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Such a controller may therefore be considered as a hardware component, and the means included therein for performing the various functions may also be considered as a structure within the hardware component. Or even means for performing the functions may be regarded as being both a software module for performing the method and a structure within a hardware component.
The application may be described in the general context of computer-executable instructions, such as program modules, being executed by a computer. Generally, program modules include routines, programs, objects, components, data structures, classes, etc. that perform particular tasks or implement particular abstract data types. The application may also be practiced in distributed computing environments where tasks are performed by remote processing devices that are linked through a communications network. In a distributed computing environment, program modules may be located in both local and remote computer storage media including memory storage devices.
From the above description of the embodiments, it is clear to those skilled in the art that the present application can be implemented by software plus necessary general hardware platform. Based on such understanding, the technical solutions of the present application may be embodied in the form of a software product, which may be stored in a storage medium, such as a ROM/RAM, a magnetic disk, an optical disk, or the like, and includes several instructions for enabling a computer device (which may be a personal computer, a mobile terminal, a server, or a network device) to execute the method according to the embodiments or some parts of the embodiments of the present application.
The embodiments in the present specification are described in a progressive manner, and the same or similar parts among the embodiments are referred to each other, and each embodiment focuses on the differences from the other embodiments. The application is operational with numerous general purpose or special purpose computing system environments or configurations. For example: personal computers, server computers, hand-held or portable devices, tablet-type devices, multiprocessor systems, microprocessor-based systems, set top boxes, programmable electronic devices, network PCs, minicomputers, mainframe computers, distributed computing environments that include any of the above systems or devices, and the like.
The above-mentioned embodiments are further described in detail for the purpose of illustrating the invention, and it should be understood that the above-mentioned embodiments are only illustrative of the present invention and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (7)
1. A semi-physical simulation method, characterized in that the method comprises:
the non-standard sphere infrared radiation simulation module receives flight parameters sent by the simulation calculation module, and the flight parameters are calculated and generated by the simulation calculation module according to a control instruction of the satellite-borne calculation module;
calculating and generating non-standard sphere infrared radiation simulation information according to the flight parameters;
and sending the infrared radiation simulation information of the non-standard sphere to an infrared earth sensitive module so that the infrared earth sensitive module generates measurement information and sends the measurement information to a satellite-borne calculation module.
2. The method of claim 1, wherein the non-standard sphere infrared radiation simulation module is configured to perform simulation of a non-standard sphere infrared radiation signal and comprises an analog input module, a non-standard sphere infrared radiation calculation module, and an analog output module.
3. The method of claim 1 or 2, wherein said generating non-standard spherical infrared radiation simulation information from said flight parameter calculation comprises:
the analog input module receives the flight parameters and sends the flight parameters to the non-standard body infrared radiation calculation module; the non-standard body infrared radiation calculation module calculates the flight parameters to obtain non-standard sphere infrared radiation simulation information, and sends the non-standard sphere infrared radiation simulation information to the simulation output module;
the sending of the non-standard sphere infrared radiation simulation information to an infrared earth-sensitive module comprises:
and the analog output module sends the infrared radiation analog information of the non-standard sphere to an infrared earth sensitive module.
4. The method according to claim 1, wherein the measurement information is generated by resolving according to the nonstandard spherical infrared radiation simulation information when the infrared earth sensing module receives a measurement instruction; the measurement instruction is sent by the satellite-borne computing module.
5. A semi-physical simulation system, the system comprising:
the simulation input module is used for receiving flight parameters sent by the simulation calculation module, and the flight parameters are generated by the simulation calculation module according to the control instruction of the satellite-borne calculation module;
the non-standard sphere infrared radiation calculation module is used for calculating and generating non-standard sphere infrared radiation simulation information according to the flight parameters;
and the analog output module is used for sending the infrared radiation analog information of the non-standard sphere to the infrared earth sensitive module so that the infrared earth sensitive module generates measurement information and sends the measurement information to the satellite-borne calculation module.
6. The system of claim 5, wherein the analog input module is specifically configured to: receiving the flight parameters and sending the flight parameters to the non-standard body infrared radiation calculation module;
the non-standard body infrared radiation calculation module is specifically used for: calculating the flight parameters to obtain nonstandard spherical infrared radiation simulation information, and sending the nonstandard spherical infrared radiation simulation information to a simulation output module;
the analog output module is specifically configured to: and sending the infrared radiation simulation information of the non-standard sphere to an infrared earth sensitive module.
7. The system of claim 5, wherein the measurement information is generated by resolving according to the non-standard sphere infrared radiation simulation information when the infrared earth sensing module receives a measurement instruction; the measurement instruction is sent by the satellite-borne computing module.
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| CN114167751A (en) * | 2021-11-30 | 2022-03-11 | 东方红卫星移动通信有限公司 | Constellation semi-physical simulation system and simulation method |
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Application publication date: 20200728 |