CN106503317B - Energy supply test system based on V-I curve simulation technology - Google Patents
Energy supply test system based on V-I curve simulation technology Download PDFInfo
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Abstract
The invention is suitable for the field of improvement of aircraft electrical performance testing technology, and provides an energy supply testing system based on a V-I curve simulation technology, which comprises a main control module, an STK module, a testing system module, an information configuration module and a V-I curve calculation module, wherein the main control module is respectively connected with the STK module, the testing system module, the information configuration module and the V-I curve calculation module for bidirectional communication; and the main control module is used for being responsible for displaying the V-I curve of each satellite, switching the working modes and transferring data among the modules. The invention provides a more convenient, accurate and efficient V-I curve simulation method by utilizing satellite attitude and orbit information and a real-time calculation mode while keeping the original method, and effectively solves the problems of the original software technology in the satellite orbit-entering process and the complex task execution.
Description
Technical Field
The invention belongs to the field of improvement of aircraft electrical performance testing technologies, and particularly relates to an energy supply testing system based on a V-I curve simulation technology.
Background
In order to verify whether the design and manufacture of the satellite energy component can meet the technical requirements, in the power module test, the simulated flight test and the thermal test in the satellite ground test process, the output of the ground solar array simulator is controlled by a V-I curve simulation technology to simulate the solar energy supply condition of the satellite during in-orbit work, so that the design of the satellite energy component is verified.
At present, the V-I curve simulation technology calculates the time of the satellite entering and exiting the earth shadow in the orbit period according to the information of the satellite in the orbit, the attitude and the like, so as to control the ground solar matrix simulator to simulate the solar energy supply condition of the satellite in the orbit period by full power or partial power output. In general, in order to verify the energy supply capacity of the satellite under the limit condition, the earth shadow time is the maximum in the life cycle, and the earth shadow time square array simulator stops outputting.
The existing V-I curve simulation software control method is based on the maximum earth shadow time of a satellite in an orbit period, and controls a solar array simulator to output with periodic fixed power. Therefore, the existing V-I curve simulation software control method mainly has the following defects:
1. the satellite has a more complex charging and discharging process from launching to stable orbit entering, the period is influenced by a plurality of factors such as separation angular velocity, and the like, and a more complex dynamic change process can appear in the output of the satellite solar sailboard in the period under different conditions, so that the existing V-I curve simulation software simulation method cannot quickly and accurately verify;
2. when a satellite executes a task in orbit, the solar panel is output with aperiodic power due to more attitude changes, the traditional V-I curve simulation software control cannot simulate the solar panel, and therefore the energy supply capacity of the solar panel cannot be verified;
3. with the development of the satellite parallel test technology, the existing software can only face the test task of one satellite at a time and cannot simultaneously simulate a plurality of satellites.
Disclosure of Invention
The invention aims to provide an energy supply testing system based on a V-I curve simulation technology, and aims to solve the technical problems.
The invention is realized in such a way, the energy supply testing system based on the V-I curve simulation technology comprises a main control module, an STK module, a testing system module, an information configuration module and a V-I curve calculation module, wherein the main control module is respectively connected with the STK module, the testing system module, the information configuration module and the V-I curve calculation module for bidirectional communication; the main control module is used for being responsible for displaying a V-I curve of each satellite, switching working modes and transferring data among the modules; the STK module is used for communicating with the STK through a CONNECT module calling the STK; the test system module is used for being responsible for interaction among test systems, and the functions at least comprise the steps of obtaining satellite telemetry from the test system, performing telemetry analysis and sending a V-I curve to power supply and distribution software in the test system for power output according to different working modes; the information configuration module is used for configuring basic information of the software; and the V-I curve calculation module is used for calculating the V-I curve of each square matrix simulator of each satellite.
The further technical scheme of the invention is as follows: the main control module comprises three working modes, namely a document mode, an STK mode and a remote measuring mode, and the main control module completes the test of the whole energy supply system through the switching of the three modes.
The further technical scheme of the invention is as follows: when the main control module is switched to a document mode, the V-I curve calculation module reads a pre-configured V-I curve file in an appointed folder; and the CONNECT module in the STK module sends the satellite attitude and the orbit information to the STK for display.
The further technical scheme of the invention is as follows: when the main control module is switched to the STK mode, the V-I curve calculation module acquires information from the STK from the main control module and calls DLL of each satellite to perform curve calculation; and the CONNECT module in the STK module acquires the included angle between sunlight and each satellite sailboard from the STK and feeds the included angle back to the main control module.
The further technical scheme of the invention is as follows: when the main control module is switched to a telemetry mode, the V-I curve calculation module acquires telemetry parameters from a test system, calls a DLL (delay locked loop) to calculate a V-I curve and feeds the V-I curve back to the main control module; and the CONNECT module in the STK module sends the satellite attitude and the orbit information to the STK for display.
The further technical scheme of the invention is as follows: the basic configuration in the information configuration module comprises satellite code number, satellite sailboard information, square matrix simulator number, square matrix simulator output safety configuration, test system network interface information and STK interface information.
The invention has the beneficial effects that: the invention provides a more convenient, accurate and efficient V-I curve simulation method by utilizing satellite attitude and orbit information and a real-time calculation mode while keeping the original method, and effectively solves the problems of the original software technology in the satellite orbit-entering process and the complex task execution.
Drawings
Fig. 1 is a block diagram of an energy supply testing system based on a V-I curve simulation technique according to an embodiment of the present invention.
FIG. 2 is a flowchart of document pattern curve simulation according to an embodiment of the present invention.
Fig. 3 is a flow chart of telemetry mode curve simulation provided by an embodiment of the present invention.
Fig. 4 is a flow chart of a simulation of an STK mode curve according to an embodiment of the present invention.
Detailed Description
Fig. 1 shows an energy supply testing system based on a V-I curve simulation technology, which includes a main control module, an STK module, a testing system module, an information configuration module, and a V-I curve calculation module, where the main control module is respectively connected to the STK module, the testing system module, the information configuration module, and the V-I curve calculation module for bidirectional communication; the main control module is used for being responsible for displaying a V-I curve of each satellite, switching working modes and transferring data among the modules; the STK module is used for communicating with the STK through a CONNECT module calling the STK; the test system module is used for being responsible for interaction among test systems, and the functions at least comprise the steps of obtaining satellite telemetry from the test system, performing telemetry analysis and sending a V-I curve to power supply and distribution software in the test system for power output according to different working modes; the information configuration module is used for configuring basic information of the software; and the V-I curve calculation module is used for calculating the V-I curve of each square matrix simulator of each satellite.
The main control module comprises three working modes, namely a document mode, an STK mode and a remote measuring mode, and the main control module completes the test of the whole energy supply system through the switching of the three modes.
When the main control module is switched to a document mode, the V-I curve calculation module reads a pre-configured V-I curve file in an appointed folder; and the CONNECT module in the STK module sends the satellite attitude and the orbit information to the STK for display.
When the main control module is switched to the STK mode, the V-I curve calculation module acquires information from the STK from the main control module and calls DLL of each satellite to perform curve calculation; and the CONNECT module in the STK module acquires the included angle between sunlight and each satellite sailboard from the STK and feeds back the included angle to the main control module.
When the main control module is switched to a telemetry mode, the V-I curve calculation module acquires telemetry parameters from a test system, calls a DLL (delay locked loop) to calculate a V-I curve and feeds the V-I curve back to the main control module; and the CONNECT module in the STK module sends the satellite attitude and the orbit information to the STK for display.
The basic configuration in the information configuration module comprises satellite code numbers, satellite number, satellite sailboard information, square matrix simulator number, square matrix simulator output safety configuration, test system network interface information and STK interface information.
The main control module is mainly responsible for displaying a V-I curve of each satellite, switching three working modes (a document mode, an STK mode and a remote measuring mode) and data transfer among the modules.
The information configuration module is a basic configuration for software, and at least comprises satellite code numbers, satellite number (at most three), satellite sailboard information, square matrix simulator number, square matrix simulator output safety configuration, test system network interface information, STK interface information and the like.
And the V-I curve calculation module is responsible for calculating the V-I curve of each square matrix simulator of each satellite. Acquiring a current working mode and square matrix information through a main control module, and reading a pre-configured V-I curve file in a specified folder when the working mode is a text mode; when the working mode is the STK mode, the information from the STK is obtained from the main control module and DLL of each satellite is called for curve calculation; when the telemetry mode is selected, telemetry parameters are obtained from the test system and the DLL is invoked to calculate the V-I curve. The module feeds back the V-I curve to the main frame.
And the STK module is communicated with the STK by calling the CONNECT module of the STK, and when the STK mode is selected, the STK module acquires the included angle between sunlight and each satellite sailboard from the STK and feeds back the included angle to the main control module. In other modes, the module sends the satellite attitude and orbit information to the STK for display.
The test system module is responsible for interaction between the software and the test system, and at least has the functions of acquiring satellite telemetry, telemetry analysis and sending a V-I curve to power supply and distribution software in the test system for power output according to different working modes.
The working flows under the three working modes are respectively introduced as follows:
as shown in fig. 2, the V-I curve simulation method when the document mode is selected includes the steps of:
step 0: a login interface, which logs in to enter the main interface;
step 1: configuring information, namely configuring the code number and the number of the satellites, the code number and the number of the corresponding square matrix simulator, the output safety configuration of the square matrix simulator, the network interface information of the test system, the STK interface information and the like, and storing the configuration information into a specified configuration file;
step 2: selecting a mode, selecting a document mode, and initializing an interaction interface with the STK and the test system;
and step 3: selecting files which correspond to each satellite and contain curve information, and describing the satellite attitude, the orbit information and the V-I curve information of each square matrix according to a specified format;
and 4, step 4: at least checking whether the corresponding relation between the satellite and the square matrix and the output V-I curve of the square matrix meet the safety threshold value or not according to the configuration information, and returning to the step 3 if the corresponding relation does not meet the prompt error information;
and 5: waiting for a manual instruction;
step 6: sequentially extracting information in the document in a fixed period, sending V-I curve information to a test system for power output, and sending track information and the like to an STK (standard time keying) for real-time display;
and 7: judging whether manual intervention exists or the file playing is finished, if not, continuing to execute 6, and if so, executing 8 and ending
And 8: the transmission is ended.
Referring to fig. 3, a V-I curve simulation method when the telemetry mode is selected is described as follows, including the steps of:
step 0: a login interface, which logs in to enter the main interface;
step 1: configuring information, namely configuring the code number and the number of the satellites, the code number and the number of the corresponding square matrix simulator, the output safety configuration of the square matrix simulator, the network interface information of the test system, the STK interface information and the like, and storing the configuration information into a specified configuration file;
step 2: selecting a mode, selecting a remote measuring mode, and initializing an interaction interface with the STK and the test system;
and step 3: waiting for a manual instruction;
and 4, step 4: acquiring the telemetering information of each satellite from the test system, analyzing the telemetering information and extracting the required telemetering information;
and 5: calling a dynamic library (DLL) of each satellite calculation curve, calculating the output power of each satellite solar panel according to the required telemetering information, and calculating the V-I curve of each square matrix simulator by combining the configuration information of each satellite square matrix simulator;
step 6: transmitting the V-I curve information to a test system for power output and display on a main interface, and transmitting the track information and the like to an STK (standard time keying) for real-time display;
and 7: judging whether manual intervention exists, if not, continuing to execute 4, if so, executing 8 and ending
And 8: the transmission is ended.
FIG. 3 telemetry mode curve simulation flow chart
The method for simulating the V-I curve when the telemetry mode is selected is described below with reference to FIG. 4, and comprises the following steps:
step 0: a login interface, which logs in to enter the main interface;
step 1: configuring information, namely configuring the code number and the number of the satellites, the code number and the number of the corresponding square matrix simulator, the output safety configuration of the square matrix simulator, the network interface information of the test system, the STK interface information and the like, and storing the configuration information into a specified configuration file;
step 2: selecting a mode, selecting an STK mode, and initializing an interaction interface with the STK and a test system;
and step 3: waiting for a manual instruction;
and 4, step 4: starting STK simulation, and acquiring the vector included angle between each satellite sailboard and sunlight through a CONNECT interface;
and 5: calling a dynamic library (DLL) of each satellite calculation curve, and calculating each square matrix simulator V-I curve of each satellite according to each included angle and configuration information of each satellite square matrix simulator;
step 6: sending the V-I curve information to a test system for power output and displaying on a main interface;
and 7: judging whether manual intervention exists, if not, continuing to execute 4, if so, executing 8 and ending
And 8: the transmission is ended.
The invention utilizes the satellite attitude and orbit information and a real-time calculation mode to more conveniently, accurately and efficiently simulate the V-I curve while keeping the original method, thereby effectively solving the problems of the original software technology in the satellite orbit-entering process and the complex task execution.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (6)
1. An energy supply test system based on a V-I curve simulation technology is characterized by comprising a main control module, an STK module, a test system module, an information configuration module and a V-I curve calculation module, wherein the main control module is respectively connected with the STK module, the test system module, the information configuration module and the V-I curve calculation module for bidirectional communication; the main control module is used for being responsible for displaying a V-I curve of each satellite, switching working modes and transferring data among the modules; the STK module is used for communicating with the STK through a CONNECT module calling the STK; the test system module is used for being responsible for interaction among test systems, and the functions at least comprise the steps of obtaining satellite telemetry from the test system, performing telemetry analysis and sending a V-I curve to power supply and distribution software in the test system for power output according to different working modes; the information configuration module is used for configuring basic information of the software; the V-I curve calculation module is used for calculating the V-I curve of each square matrix simulator of each satellite, acquiring the current working mode and the square matrix information through the main control module, and reading a pre-configured V-I curve file in a specified folder when the working mode is a text mode; when the working mode is the STK mode, the information from the STK is obtained from the main control module and DLL of each satellite is called for curve calculation; when the telemetry mode is selected, acquiring telemetry parameters from the test system and calling DLL to calculate a V-I curve, and feeding the V-I curve back to the main frame by the V-I curve calculation module; when the STK mode is selected, the CONNECT module in the STK module acquires the included angle between sunlight and each satellite sailboard from the STK and feeds back the included angle to the main control module;
the V-I curve simulation process when selecting a document mode includes the steps of:
step 0: a login interface, which logs in to enter the main interface;
step 1: configuring information, namely configuring the code number of the satellite, the number of the satellites, the code number of the square matrix simulator corresponding to the satellite, the number of the square matrix simulators, the output security configuration of the square matrix simulator, the network interface information of the test system and the STK interface information, and storing the configuration information into a specified configuration file; step 2: selecting a mode, selecting a document mode, and initializing an interaction interface with the STK and the test system;
and step 3: selecting files containing curve information corresponding to each satellite, wherein the files describe the satellite attitude, the orbit information and the V-I curve information of each square matrix according to a specified format;
and 4, step 4: at least checking whether the corresponding relation between the satellite and the square matrix and the output V-I curve of the square matrix meet the safety threshold value or not according to the configuration information, and if not, returning to the step 3;
and 5: waiting for a manual instruction;
and 6: sequentially extracting information in the document in a fixed period, sending the V-I curve information to a test system for power output, and sending the track information to an STK for real-time display;
and 7: judging whether manual intervention exists or the file playing is finished, if not, continuing to execute 6, and if so, finishing executing 8;
and 8: the transmission is ended.
2. The energy supply testing system of claim 1, wherein the main control module has three working modes, namely a document mode, an STK mode and a telemetry mode, and the main control module is switched among the three working modes to complete the testing of the whole energy supply system.
3. The system according to claim 2, wherein when the main control module switches to the document mode, the V-I curve calculation module reads a preconfigured V-I curve file in a designated folder; and the CONNECT module in the STK module sends the satellite attitude and the orbit information to the STK for display.
4. The energy supply testing system of claim 3, wherein when the master control module switches to the STK mode, the V-I curve calculation module obtains information from the STK from the master control module and calls DLL of each satellite for curve calculation.
5. The energy supply testing system of claim 4, wherein when the master control module switches to the telemetry mode, the V-I curve calculation module obtains telemetry parameters from the test system and invokes a DLL to calculate a V-I curve and feed the V-I curve back to the master control module; and the CONNECT module in the STK module sends the satellite attitude and the orbit information to the STK for display.
6. The energy supply testing system of claim 5, wherein the basic configuration in the information configuration module comprises a satellite code number, a satellite number, satellite windsurfing information, a matrix simulator number, a matrix simulator output security configuration, testing system network interface information, and STK interface information.
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| CN105659852B (en) * | 2009-12-10 | 2013-07-31 | 北京空间飞行器总体设计部 | A kind of satellite power supply and distribution test system based on LAN bus |
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