CN112613187A - Ground accompanying device of spacecraft power supply and distribution system - Google Patents
Ground accompanying device of spacecraft power supply and distribution system Download PDFInfo
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Abstract
The invention belongs to the technical field related to a spacecraft power supply and distribution system, and discloses a ground accompanying device of the spacecraft power supply and distribution system, which comprises: the remote measurement interface module is used for acquiring the on-orbit power supply and distribution data of the spacecraft in real time in a measurement and control arc section of the spacecraft, and transmitting the on-orbit power supply and distribution data at the initial moment as an initial value to the spacecraft power supply and distribution system model for simulation; the spacecraft power supply and distribution system model is used for simulating a power supply and distribution system of the spacecraft according to the received on-orbit power supply and distribution data to obtain simulated power supply and distribution data; and the simulation intervention module is used for comparing the on-orbit power supply and distribution data with the corresponding simulation power supply and distribution data, and if the error between the on-orbit power supply and distribution data and the corresponding simulation power supply and distribution data exceeds a preset range, the on-orbit power supply and distribution data at the corresponding moment is used as an initial value of the spacecraft power supply and distribution system model for simulation calculation. The method and the device can realize accurate simulation of the non-measurement and control arc section, and meet the monitoring requirement of the non-measurement and control arc section.
Description
Technical Field
The invention belongs to the technical field related to a spacecraft power supply and distribution system, and particularly relates to a ground accompanying device of the spacecraft power supply and distribution system.
Background
The power supply and distribution system of the spacecraft is a key subsystem for generating, storing, changing, regulating and distributing electric energy of the spacecraft, and is the heart and blood of the spacecraft. With the development of complex spacecraft models represented by deep space exploration and manned space, the complexity of power supply and distribution systems is continuously increased, whether the power supply and distribution systems can reliably and continuously provide stable energy for the spacecraft is critical to the success or failure of space missions, and therefore, the deep research on the power supply and distribution state of the spacecraft power supply and distribution systems in flight is of great significance.
Chinese patent CN201710453230 provides a modeica model-based spacecraft energy system model construction method, which decomposes and constructs a spacecraft power supply and distribution system based on a modeica language, and simulates the spacecraft power supply and distribution system. As shown in fig. 1, the energy system model constructed by the energy system model construction method includes a solar cell array model, a storage battery module model, a PCU model, a main distributor and a load, all the devices are established based on a highly simulated modecia model, and include all design information of a single device, but the devices are used for inputting an initial value to realize off-line simulation at present, the simulation process is asynchronous with the real process, in addition, the simulation calculation time is shorter and is far lower than the time interval of receiving data in the simulation solving process, so the error accumulation in the gradual calculation process is larger, and the simulation error is larger when the simulation time is longer, the real power supply and distribution state is difficult to reflect.
Therefore, the prior art still lacks effective digital means to intervene in comprehensively mastering the state of a power supply and distribution system of a spacecraft, and a ground worker in a measurement and control arc section can acquire the power supply and distribution information of the power supply and distribution system of the spacecraft by receiving the information sent by the spacecraft in the operation process of the spacecraft, but cannot acquire the corresponding power supply and distribution information when the spacecraft runs to a non-measurement and control arc section, for example, signals are shielded by the earth, and the prior art cannot realize the real-time monitoring of the whole period of the spacecraft, so that the design of the ground accompanying flying device capable of acquiring the whole period power supply and distribution state of the power supply and distribution system of the spacecraft is of great significance.
Disclosure of Invention
Aiming at the defects or improvement requirements of the prior art, the invention provides a ground accompanying device of a spacecraft power supply and distribution system, which simulates the acquired on-orbit power supply and distribution data of a measurement and control arc section by using a preset time step length, realizes synchronization of the simulation process and the real process of a spacecraft, corrects parameters in a spacecraft power supply and distribution model by a simulation intervention module to obtain a model capable of accurately simulating the operation state of the spacecraft, further can realize accurate simulation of a non-measurement and control arc section, and meets the monitoring requirement of the non-measurement and control arc section.
To achieve the above object, according to one aspect of the present invention, there is provided a ground accompanying device of a spacecraft power supply and distribution system, the device including a spacecraft power supply and distribution system model, a telemetry interface module, and a simulation intervention module, wherein: the remote measuring interface module is in communication connection with the spacecraft and is used for acquiring on-orbit power supply and distribution data of the spacecraft in real time in a measurement and control arc section of the spacecraft and transmitting the on-orbit power supply and distribution data at an initial moment to the spacecraft power supply and distribution system model for simulation; the spacecraft power supply and distribution system model is used for simulating a power supply and distribution system of a spacecraft according to the received on-orbit power supply and distribution data at the initial moment and preset time step lengths so as to obtain simulated power supply and distribution data at a plurality of moments, wherein the preset time step lengths are consistent with the time intervals of the telemetry interface module for obtaining the on-orbit power supply and distribution data, and then the simulation process of the spacecraft power supply and distribution system model corresponds to the operation process of the spacecraft; the simulation intervention module is used for comparing the simulation power supply and distribution data with the on-orbit power supply and distribution data corresponding to the moment, and if the error between the simulation power supply and distribution data and the on-orbit power supply and distribution data corresponding to the moment exceeds a preset range, the on-orbit power supply and distribution data corresponding to the moment is used as the initial value of the spacecraft power supply and distribution system model for simulation calculation so as to ensure the simulation accuracy of the spacecraft power supply and distribution system model and further ensure the simulation accuracy of the spacecraft power supply and distribution state in the non-measurement and control arc section.
Preferably, the flight accompanying device further comprises a simulation prediction module, wherein the simulation prediction module is used for continuously calculating the simulation power supply and distribution data at the next moment in an iterative manner by taking the simulation power supply and distribution data calculated by the spacecraft power supply and distribution system model as an initial value so as to obtain the simulation power supply and distribution data at the multiple moments in advance and provide fault early warning when the deviation of the to-be-simulated operation data exceeds a preset threshold value.
Preferably, the accompanying device further comprises a triggering module for triggering the simulation forecasting module to actively acquire the simulation power supply and distribution data.
Preferably, the preset threshold value is obtained through historical data of the spacecraft power supply and distribution system during normal operation.
Preferably, the on-rail power supply and distribution data comprises the switch states and power consumption of all devices in the spacecraft power supply and distribution system, the voltage and current of a bus, the voltage and depth of discharge of a battery port, the true output voltage and current of a battery, and time; the simulated power supply and distribution data comprise the switch states and power consumption of all devices in the spacecraft power supply and distribution system, the voltage and current of a bus, the voltage and discharge depth of a port of a storage battery, the true output voltage and current of the battery and the corresponding time, which are obtained through simulation.
Preferably, the telemetry interface module transmits the on-orbit operation data by adopting a TCP/IP protocol or a UDP protocol, and analyzes the on-orbit operation data into a format required by the spacecraft power supply and distribution system model.
Preferably, the simulation intervention module further comprises a command receiving and converting module, wherein the command receiving module is configured to receive an external intervention command, and the converting module is configured to convert the external intervention command into a format recognizable by the spacecraft power supply and distribution system model, so as to modify parameters in the spacecraft power supply and distribution system model.
Preferably, the spacecraft power supply and distribution system model is created based on a Modelica language.
In general, compared with the prior art, the above technical solution conceived by the present invention provides a ground accompanying device for a spacecraft power supply and distribution system, which has at least the following beneficial effects:
1. the spacecraft power supply and distribution system model simulates a spacecraft power supply and distribution system according to the preset time step length to ensure the operation synchronism of the flight accompanying device and the spacecraft, the spacecraft power supply and distribution model simulates the power supply and distribution system and then enters the waiting time instead of the next simulation, and the simulation is carried out when the preset time step length is reached, so that the consistency with the real operation state of the spacecraft is ensured;
2. the simulation intervention module is used for timely intervening the simulation power supply and distribution data with larger errors in the measurement and control arc section according to the received on-orbit power supply and distribution data, so that iterative accumulation of errors is avoided, the simulation accuracy of the measurement and control arc section is further ensured, and higher simulation precision is further ensured when the non-measurement and control arc section is simulated;
3. the simulation prediction module in the application does not need to wait, and can timely perform simulation calculation according to simulated power supply and distribution data, so that the simulated power supply and distribution data at a plurality of subsequent moments can be predicted in advance, operation managers can know the operation states of the spacecraft at the plurality of subsequent moments in advance, and further, faults or abnormal working states which may occur in a spacecraft power supply and distribution system can be early warned, and the managers can make preparations in advance;
4. the flight accompanying device of the spacecraft power supply and distribution system is provided based on the spacecraft power supply and distribution system, and the real running state of the spacecraft power supply and distribution system can be comprehensively reflected by means of the simulated power supply and distribution data of the spacecraft power supply and distribution system model and the on-orbit power supply and distribution data obtained by receiving.
Drawings
FIG. 1 schematically illustrates a modular schematic of a power supply and distribution system model in an embodiment of the disclosure;
fig. 2 schematically illustrates a work flow diagram of a ground accompanying device of a spacecraft power distribution system in an embodiment of the present disclosure;
FIG. 3 schematically illustrates a workflow diagram of a telemetry interface module in an embodiment of the disclosure;
FIG. 4 schematically illustrates a workflow diagram of a simulation intervention module in an embodiment of the present disclosure;
FIG. 5 schematically illustrates a workflow diagram of a simulation prognostic module in an embodiment of the present disclosure.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
The invention provides a ground accompanying device of a spacecraft power supply and distribution system, which comprises a spacecraft power supply and distribution system model, a telemetry interface module and a simulation intervention module, as shown in figure 2.
The remote measuring interface module is in communication connection with the spacecraft and is used for acquiring on-orbit power supply and distribution data of the spacecraft in real time in a measurement and control arc section of the spacecraft and transmitting the on-orbit power supply and distribution data at an initial moment as an initial value to the spacecraft power supply and distribution system model for simulation.
In the embodiment of the present disclosure, as shown in fig. 3, the telemetry interface module transmits the on-orbit power supply and distribution data by using a TCP/IP protocol or a UDP protocol, and analyzes the on-orbit power supply and distribution data into a format required by the spacecraft power supply and distribution system model.
The telemetry interface module comprises a subscription unit used for selecting corresponding data from the on-orbit power supply and distribution data according to simulation parameter requirements in the spacecraft power supply and distribution system model. The specific subscription unit acquires subscribed on-orbit power supply and distribution data through a TCP/IP protocol or a UDP protocol, unpacks a received on-orbit running data packet according to a telemetry outline data protocol specification, and analyzes a data frame format according to telemetry and equipment parameter association configuration so that the on-orbit power supply and distribution data are compatible with a spacecraft power supply and distribution system model.
The spacecraft power supply and distribution system model is used for simulating a power supply and distribution system of a spacecraft according to a preset time step to obtain simulated power supply and distribution data at multiple moments on the basis of the received on-orbit power supply and distribution data at the initial moment, wherein the preset time step is consistent with the time interval of the telemetry interface module for obtaining the on-orbit power supply and distribution data, and therefore the simulation process of the spacecraft power supply and distribution system model corresponds to the operation process of the spacecraft.
The on-orbit power supply and distribution data comprise the switch states and power consumption of all equipment in the spacecraft power supply and distribution system, the voltage and current of a bus, the voltage and discharge depth of a storage battery port, the true output voltage and current of a battery and time; the simulated power supply and distribution data comprise the switch states and power consumption of all devices in the spacecraft power supply and distribution system, the voltage and current of a bus, the voltage and discharge depth of a port of a storage battery, the true output voltage and current of the battery and the corresponding time, which are obtained through simulation.
After the spacecraft power supply and distribution system model obtains the on-orbit power supply and distribution data injected by the telemetry interface module, a solver in the spacecraft power supply and distribution system model starts to simulate, because the solving process is very short, the general preset time step length is far longer than the solving time, the solver solves the simulated power supply and distribution data, does not immediately carry out the next solving, but is in a waiting state, and carries out the next solving when waiting for the preset time step length, so that the consistency with the real running state of the spacecraft is realized.
The spacecraft power supply and distribution system model can be established based on a Modelica model, and due to the fact that the spacecraft power supply and distribution system is various in equipment form, the requirement cannot be met by adopting one establishing method, different establishing strategies can be adopted according to the equipment form, and for example, principle-based direct modeling is adopted for a model with a clear principle and mature mathematical expression of the model; for a model with unclear principle or immature mathematical expression of the model, modeling is performed by combining data of equipment or test data, simplification processing can be performed on the model with high complexity, and modeling can be performed in an empirical formula-based mode. The main key equipment in the spacecraft power supply and distribution system is ensured to be established in the spacecraft power supply and distribution system model, so that the spacecraft power supply and distribution system model can truly reflect the spacecraft power supply and distribution system in reality.
And the simulation intervention module is used for comparing the on-orbit power supply and distribution data with the simulation power supply and distribution data at the corresponding moment, and if the error between the on-orbit power supply and distribution data and the simulation power supply and distribution data at the corresponding moment exceeds a preset range, the simulation power supply and distribution data at the corresponding moment is used as an initial value input value to be solved in the spacecraft power supply and distribution model. In the embodiment of the disclosure, when the on-orbit power supply and distribution data and the corresponding simulated power supply and distribution data are compared and have deviation, input data in a spacecraft power supply and distribution system model is corrected by means of manual interference or mission plan interference. As shown in fig. 4, the interference data may be injected by way of manual interaction or a task plan instruction sequence, and the data converter converts the interference data into a manual interference instruction, and injects the manual interference instruction into the solver as an input state of the current solution to drive the simulation solution. The simulation intervention module further comprises a command receiving and converting module for receiving an external intervention command and converting the external command into a preset format so as to correct the input parameters in the power supply and distribution system model of the spacecraft.
Therefore, the input initial value of the spacecraft power supply and distribution system model can be corrected in the measurement and control arc section, error accumulation is avoided, the spacecraft power supply and distribution system model is enabled to be more matched with the operation state of the spacecraft, the simulation accuracy in the measurement and control arc section is guaranteed, and the simulation data in the non-measurement and control arc section is enabled to be more consistent with the true value.
The flight accompanying device further comprises a simulation prediction module, as shown in fig. 5, wherein the simulation prediction module is used for acquiring the simulation power supply and distribution data, continuously and iteratively calculates the simulation power supply and distribution data at the next moment by taking the simulation power supply and distribution data as an initial value, and does not need to wait so as to obtain the simulation power supply and distribution data at the multiple moments in advance and provide fault early warning when the deviation of the to-be-simulated operation data exceeds a preset threshold value. The preset threshold value is obtained through historical data of the spacecraft power supply and distribution system during normal operation, and the iterative solution time can be set according to the actual time required to be predicted.
The simulation prediction module further comprises a triggering module used for triggering the simulation prediction module to actively acquire the simulation power supply and distribution data.
In summary, the ground accompanying device of the spacecraft power supply and distribution system disclosed by the application simulates by taking the on-orbit power supply and distribution data as an initial value, updates the solution value when the error between the simulation data and the on-orbit power supply and distribution data is large, realizes the solution accuracy of the spacecraft in the measurement and control arc section, further realizes the simulation accuracy of the non-measurement and control arc section, and can predict the running state of the spacecraft power supply and distribution system in advance through the simulation prediction module so as to obtain early warning in time.
It will be understood by those skilled in the art that the foregoing is only a preferred embodiment of the present invention, and is not intended to limit the invention, and that any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (8)
1. A ground accompanying device of a spacecraft power supply and distribution system, which is characterized by comprising a spacecraft power supply and distribution system model, a telemetry interface module and a simulation intervention module, wherein:
the remote measuring interface module is in communication connection with the spacecraft and is used for acquiring on-orbit power supply and distribution data of the spacecraft in real time in a measurement and control arc section of the spacecraft and transmitting the on-orbit power supply and distribution data at an initial moment to the spacecraft power supply and distribution system model for simulation;
the spacecraft power supply and distribution system model is used for simulating a power supply and distribution system of a spacecraft according to the received on-orbit power supply and distribution data at the initial moment and preset time step lengths so as to obtain simulated power supply and distribution data at a plurality of moments, wherein the preset time step lengths are consistent with the time intervals of the two on-orbit power supply and distribution data obtained by the telemetering interface module, and then the simulation process of the spacecraft power supply and distribution system model corresponds to the operation process of the spacecraft;
the simulation intervention module with telemetry interface module and spacecraft power supply and distribution system model communication connection are used for with simulation power supply and distribution data compare with the on-orbit power supply and distribution data that correspond moment, if both errors have exceeded the preset range then will the on-orbit power supply and distribution data that correspond moment are regarded as the initial value of spacecraft power supply and distribution system model carries out the emulation calculation, with the assurance the emulation accuracy of spacecraft power supply and distribution system model, and then guarantee the spacecraft is in the simulation accuracy of non-observing and controlling arc section to spacecraft power supply and distribution state.
2. The ground accompanying device according to claim 1, further comprising a simulation prediction module, wherein the simulation prediction module is configured to continuously iteratively calculate the simulated power supply and distribution data at the next time with the simulated power supply and distribution data calculated by the spacecraft power supply and distribution system model as an initial value, so as to obtain the simulated power supply and distribution data at the multiple times in advance and provide a fault warning when the deviation of the to-be-simulated operation data exceeds a preset threshold.
3. The ground companion flight device of claim 2 wherein the simulation prognostic module further comprises a triggering module for triggering the simulation prognostic module to actively acquire the simulated power supply and distribution data.
4. The ground accompanying device according to claim 2, wherein the preset threshold value is obtained from historical data of the spacecraft power distribution system during normal operation.
5. The ground companion flight device of claim 1 wherein the on-rail power distribution data includes switching states and power consumption of all devices in the spacecraft power distribution system, voltage and current of a bus, battery port voltage and depth of discharge, battery true output voltage and current, and time;
the simulated power supply and distribution data comprise the switch states and power consumption of all devices in the spacecraft power supply and distribution system, the voltage and current of a bus, the voltage and discharge depth of a port of a storage battery, the true output voltage and current of the battery and the corresponding time, which are obtained through simulation.
6. The ground accompanying flying device according to claim 1, wherein the telemetry interface module transmits the in-orbit operation data by using a TCP/IP protocol or a UDP protocol, and resolves the in-orbit operation data into a format required by the spacecraft power supply and distribution system model.
7. The ground accompanying device according to claim 1, wherein the simulation intervention module further comprises an instruction receiving and converting module, wherein the instruction receiving module is configured to receive an external intervention instruction, and the converting module is configured to convert the external intervention instruction into a format recognizable by the spacecraft power supply and distribution system model so as to implement modification of parameters in the spacecraft power supply and distribution system model.
8. The ground companion flight device of claim 1 wherein the spacecraft power distribution system model is created based on a Modelica language.
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