CN108830010B - Simulation device and method for stratosphere long-endurance aerostat energy system - Google Patents
Simulation device and method for stratosphere long-endurance aerostat energy system Download PDFInfo
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Abstract
The embodiment of the invention provides a simulation device and a simulation method for an energy system of a stratospheric long-endurance aerostat, wherein the device comprises the following components: the output of each solar cell array simulator is respectively connected with one input of the energy conversion module; each electronic load is connected with one input of the energy conversion module respectively; the battery pack is connected with one input of the battery management unit and the energy conversion module respectively; the simulation control module is respectively connected with the solar cell array simulator, the electronic load, the energy conversion module and the battery management unit through the data bus. The device provided by the embodiment of the invention can adjust the energy input and power requirements of the energy system in real time according to the illumination conditions and various flight conditions, and can verify the energy matching, optimization and balance among all components of the energy system through simulation operation, thereby providing more complete experimental and test conditions for the flight of the stratospheric long-endurance aerostat in the near space.
Description
Technical Field
The embodiment of the invention relates to the technical field of long-endurance aerostat energy power, in particular to a simulation device and a simulation method of a stratospheric long-endurance aerostat energy system.
Background
The stratosphere long-endurance aerostat is a near space vehicle lighter than air, has a flying height of about 20km, can stay in the sky for a long time at fixed points, is suitable for being used as a novel information platform for broadband communication, high-precision earth observation, regional early warning and the like, and is currently becoming a research hotspot at home and abroad. In order to realize long-term residence of the stratosphere long-endurance aerostat, sustainable and cyclic energy supply is needed, and photovoltaic cyclic energy is the only way to adopt in view of environmental conditions in the adjacent space. Because the flying working conditions of the long-endurance aerostat in the near space are complex and changeable, different flying tasks such as fixed point, attitude determination, cruising, spiraling, flight path, wind resistance flying and the like have different energy demands, and meanwhile, the factors such as long residence time, random abrupt change of external wind fields, day and night replacement and the like also have higher requirements on an energy system.
The simulation of the existing energy system generally comprises two methods of pure mathematics, physical model simulation and full physical simulation. Pure model simulation research often cannot obtain results close to actual running or even has a huge difference from the actual running results because some models in the system are not accurate enough or are difficult to build. And the experiment research is carried out by adopting a real object, the research and development period is relatively longer and the cost is higher.
Therefore, there is a need for a simulation device for a stratospheric long-endurance aerostat energy system to solve the above-mentioned problems in the prior art.
Disclosure of Invention
In order to solve the above problems, embodiments of the present invention provide a simulation apparatus and method for a stratospheric long-endurance aerostat energy system that overcomes or at least partially solves the above problems.
In a first aspect, an embodiment of the present invention provides a simulation apparatus for a stratospheric long-endurance aerostat energy system, including:
the system comprises an energy generation module, an energy conversion module, an energy storage module, an energy consumption module and a simulation control module;
the energy generation module comprises a plurality of solar cell array simulators, and the output of each solar cell array simulator is respectively connected with one input of the energy conversion module;
the energy consumption module comprises a plurality of electronic loads, and each electronic load is respectively connected with one input of the energy conversion module;
the energy storage module comprises a battery pack and a battery management unit, wherein the battery pack is connected with one input of the battery management unit and one input of the energy conversion module respectively;
the simulation control module is respectively connected with the solar cell array simulator, the electronic load, the energy conversion module and the battery management unit through a data bus.
The embodiment of the invention also provides a simulation method of the stratosphere long-endurance aerostat energy system, which comprises the following steps:
generating a power parameter table and a flight power time table of the solar cell based on the solar irradiation condition, the solar cell voltage and the current parameter table set in the simulation control module;
if the battery pack is confirmed to have no fault, connecting the high-voltage battery pack to an energy conversion module, and detecting the power-on state of the energy conversion module;
and if the power-on state of the energy conversion module is normal, starting a solar cell array simulator according to the power parameter table of the solar cell, and starting an electronic load according to the flight power time table so as to simulate.
The simulation device and the method for the energy system of the stratospheric long-endurance aerostat, provided by the embodiment of the invention, can adjust the energy input and the power requirement of the energy system in real time according to the illumination condition and various flight working conditions, can verify the energy matching, optimization and balance among all components of the energy system through simulation operation, can realize the function and performance verification of the stratospheric long-endurance aerostat energy system on the ground, and provide more complete experimental and test conditions for the stratospheric long-endurance aerostat to fly in the near space.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the following description will briefly explain the drawings used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a simulation device of a stratospheric long-endurance aerostat energy system provided by an embodiment of the invention;
FIG. 2 is a CAN bus connection topology structure diagram of a simulation control module, a battery management unit and an energy conversion module provided by an embodiment of the invention;
fig. 3 is a topology structure diagram of an RS485 bus connection between a simulation control module and a solar array simulator provided by an embodiment of the present invention;
FIG. 4 is a schematic diagram of a topology structure of a connection between a simulation control module and a GPIB bus of an electronic load according to an embodiment of the present invention;
fig. 5 is a schematic flow chart of a simulation method of a stratospheric long-endurance aerostat energy system provided by an embodiment of the invention.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
At present, in the prior art, a simulation mode of pure mathematics, a physical model or a full-physical simulation mode is generally adopted for simulating a stratospheric long-endurance aerostat energy system, but the first mode is often not suitable for simulating an actual running result because some models in the system are not accurate enough or are difficult to suggest; the second approach has a longer development cycle and relatively high research costs. Therefore, the two modes in the prior art cannot realize the optimal matching of each component of the energy system, so that a set of semi-physical simulation device of the energy system applied to the stratospheric long-endurance aerostat is required to be established at present, the semi-physical simulation device is characterized in that a model is combined with actual operation equipment, the working characteristics of energy components are controlled by the model, the power output and the energy change are realized, and meanwhile, the actual energy components or controllable equipment is used for simulating the energy system components, so that the working process close to the actual operation is realized.
It can be understood that the semi-physical simulation method is applied to research the energy system, so that the problem of model precision in pure model simulation can be solved, the high cost and overlong development period caused by adopting hardware can be avoided, and the simulation method is high in reliability.
In view of the above situation, fig. 1 is a schematic structural diagram of a simulation device of a stratospheric long-endurance aerostat energy system according to an embodiment of the present invention, as shown in fig. 1, where the device includes:
an energy generation module, an energy conversion module 101, an energy storage module, an energy consumption module, and a simulation control module 102;
the energy generation module comprises a plurality of solar cell array simulators 103, and the output of each solar cell array simulator 103 is respectively connected with one input of the energy conversion module 101;
the energy consumption module comprises a plurality of electronic loads 104, and each electronic load 104 is respectively connected with one input of the energy conversion module 101;
the energy storage module comprises a battery pack 105 and a battery management unit 106, wherein the battery pack 105 is respectively connected with one input of the battery management unit 106 and the energy conversion module 101;
the simulation control module 102 is respectively connected with the solar array simulator 103, the electronic load 104, the energy conversion module 101 and the battery management unit 106 through a data bus.
Specifically, it can be understood that the simulation device for the stratospheric long-endurance aerostat energy system provided by the embodiment of the invention is mainly used for simulation verification of functions and performances of the stratospheric long-endurance aerostat energy system. The device mainly comprises an energy generation module, an energy conversion module 101, an energy storage module, an energy consumption module and a simulation control module 102.
It can be understood that the energy generating module is mainly used for simulating the generation of energy, and the main energy applied in the stratospheric long-endurance aerostat energy system is solar energy, so the energy generating module provided by the embodiment of the invention is composed of a plurality of solar cell array simulators 103, preferably, the energy generating module provided by the embodiment of the invention comprises 10 solar cell array simulators, and referring to fig. 1, the output power of each solar cell array simulator 103 can reach more than 2.5 Kw. It should be noted that, the number and the output power of the solar array simulators 103 provided in the embodiment of the present invention are only preferred, and the embodiment of the present invention is not limited thereto. Further, the power output characteristics of the solar cell array can be simulated by the solar cell array simulator 103, thereby providing an energy source for the simulated energy system.
The energy conversion module 101 provided in the embodiment of the present invention is mainly used for converting the input power of the solar cell array, adjusting the charge and discharge power of the battery pack, and adjusting the driving power of the electronic load, and preferably, the energy conversion module 101 provided in the embodiment of the present invention can use the power supply controller to complete the above functions, and can be shown in fig. 1. It should be noted that, the embodiments of the present invention are not limited to the specific embodiments, and other entities or virtual devices capable of implementing the above functions may be used.
The energy storage module provided by the embodiment of the invention is mainly used for storing the energy of the solar cell array and can supplement the power required by a load by discharging when necessary. As shown in fig. 1, the energy storage module provided in the embodiment of the present invention includes a battery pack 105 and a battery management unit 106, and it is understood that the battery management unit 106 can monitor the working parameters of the battery pack 105, so as to control the charging and discharging processes of the battery pack 105.
Then, the embodiment of the invention can meet the energy supply in daytime through the solar array simulator 103, and can also meet the energy supply at night through the battery pack 105 at the same time, thereby realizing the real-time working condition simulation of the long-endurance aerostat energy power system.
The energy consumption module provided by the embodiment of the invention is mainly used for simulating the load consumption commonly used in long-endurance aerostats, the load consumption is generally electronic consumption, and mainly comprises fan consumption and motor consumption, and referring to fig. 1, the embodiment of the invention preferably provides two electronic loads 104 for simulating a propulsion motor and one electronic load 104 for simulating a fan, so that the power characteristics of the propulsion motor and the fan are simulated.
The simulation control module 102 provided by the embodiment of the invention is essentially an upper computer, and can integrate the functions of a solar cell array power generation model, a flight working condition power demand model, a data acquisition, display and analysis system and the like by pre-installing corresponding control software in the upper computer. The simulation control module 102 can be responsible for monitoring the simulation process, controlling the input energy and power of the simulation system through the power generation model of the solar cell, and adjusting the power of each simulation load in real time according to the power requirement of the flight mission. When in use, a user can directly perform corresponding operation on the upper computer, thereby completing the required simulation experiment.
On the basis of the above embodiment, fig. 2 is a topology diagram of a CAN bus connection between a simulation control module and a battery management unit and between the simulation control module and an energy conversion module, and as shown in fig. 2, the simulation control module 201 is connected to the battery management unit 202 and the energy conversion module 203 through a CAN bus.
Specifically, in the embodiment of the present invention, the energy conversion module 203 may be preferably a power controller, the simulation control module 201 may be preferably an upper computer, the battery management unit 202 and the energy conversion module 203 communicate with the simulation control module 201 through a CAN bus, and the simulation control module 201 may control the working mode of the energy conversion module 203, including opening and closing of a solar battery input channel and power output control, and receive telemetry parameters of the energy conversion module 203. The battery management unit 202 transmits information such as voltage, current, temperature, SOC and the like of the battery pack to the simulation control module 201 through the CAN bus, and the simulation control module 201 sends a control instruction to control on-off of the high-voltage power of the battery pack, so that the power-on process and the protection function are completed.
On the basis of the embodiment, the battery pack is formed by connecting a plurality of lithium batteries in series, each lithium battery is connected with the battery management unit through a signal wire, and the battery pack is connected with the energy conversion module through a high-voltage cable.
Specifically, the battery pack provided by the embodiment of the invention mainly adopts a mode of connecting a plurality of lithium ion batteries in series, and preferably, the embodiment of the invention adopts 78 single lithium ion batteries. It will be appreciated that lithium ion batteries are used because of their high energy density and good cycle life, thus providing long-term reliable charging and discharging for the simulation device, and low failure rates.
On the basis of the above embodiment, fig. 3 is a schematic diagram of an RS485 bus connection topology of a simulation control module and a solar cell array simulator according to the embodiment of the present invention, and as shown in fig. 3, the simulation control module 301 is connected with the solar cell array simulator 302 through an RS485 bus.
Specifically, the simulation control module 301 may be preferably an upper computer, where the simulation control module 301 and each solar cell array simulator 302 communicate through an RS485 bus, the simulation control module 301 is used as a master, and each solar cell array simulator 302 is used as a slave. The simulation control module 301 performs output control of the single solar cell array simulator 302 through the RS485 bus, so as to simulate actual solar cell array power change. The communication content between the solar array simulator 302 and the simulation control module 301 is ASCII code of operation commands, and each operation command has a response message.
On the basis of the above embodiment, fig. 4 is a schematic diagram of a GPIB bus connection topology between a simulation control module and an electronic load according to the embodiment of the present invention, and as shown in fig. 4, the simulation control module 401 is connected to the electronic load 402 through a GPIB bus.
Specifically, the simulation control module 401 may be preferably an upper computer, the communication mode between the electronic load 402 and the simulation control module 401 is a GPIB bus, and commands and responses are transmitted through SCPI instructions, where the simulation control module 401 gives consideration to the functions of a speaker, a controller and a listener, that is, the simulation control module 401 can send information to the electronic load 402, control the execution information of the electronic load 402 and receive the information sent by the electronic load 402, and each electronic load 402 has both the speaker function and the listener function, that is, each electronic load 402 can receive the information sent by the simulation control module 401 and also can feed back the information to the simulation control module 401. In addition, the embodiment of the invention can set the working modes of the electronic load 402 to be constant resistance, constant voltage, constant current and constant power modes respectively through commands, and set the size of the load parameters according to the working modes.
On the basis of the embodiment, the electronic load comprises a first type of electronic load simulating a motor and a second type of electronic load simulating a fan.
As can be seen from the foregoing embodiments, the electronic load provided in the embodiments of the present invention is mainly used for simulating the load power situation of the electronic device that may be generated by the stratospheric long-endurance aerostat. Generally, the system mainly comprises two situations of motor load and fan load, and the number of motors is generally more than that of fans, and then, preferably, referring to fig. 1, two electronic loads are provided to simulate the power characteristics of the motors, and one electronic load is provided to simulate the power requirement of the fans. It will be appreciated that the specific simulation object and the number of settings of the electronic load may be set according to the actual situation, which is not particularly limited in the embodiment of the present invention.
On the basis of the embodiment, the energy conversion module is a power supply controller, the power supply controller comprises a plurality of types of inputs, a first type of input of the power supply controller is connected with the solar array simulator through a cable, a second type of input of the power supply controller is connected with positive and negative electrode outputs of the battery pack through a high-voltage line, a third type of input of the power supply controller is connected with the electronic load through a cable, and a fourth type of input of the power supply controller is connected with the simulation control module through a CAN bus.
As shown in fig. 1, the energy conversion module provided in the embodiment of the present invention is preferably a power controller, and the power is supplied by an external 12V power supply. The power supply controller is provided with a plurality of inputs, such as x01-x14 in fig. 1, according to different input access objects, the input is divided into four types, the first type of input is connected with the solar array simulator through a cable, the second type of input is connected with the positive and negative output of the battery pack through a high-voltage line, the third type of input is connected with the electronic load through a cable, and the fourth type of input is connected with the simulation control module through a CAN bus, so that the electric connection of the whole simulation device is completed, and simulation experiments CAN be carried out through control instructions issued by the simulation control module.
Fig. 5 is a schematic flow chart of a simulation method of a stratospheric long-endurance aerostat energy system, which is provided by an embodiment of the invention, and as shown in fig. 5, the method includes:
501. generating a power parameter table and a flight power time table of the solar cell based on the solar irradiation condition, the solar cell voltage and the current parameter table set in the simulation control module;
502. if the battery pack is confirmed to have no fault, connecting the high-voltage battery pack to an energy conversion module, and detecting the power-on state of the energy conversion module;
503. and if the power-on state of the energy conversion module is normal, starting a solar cell array simulator according to the power parameter table of the solar cell, and starting an electronic load according to the flight power time table so as to simulate.
It can be understood that the above embodiment provides a simulation device for a stratospheric long-endurance aerostat energy system, and the corresponding embodiment of the invention also provides a simulation method for simulating the simulation device.
Specifically, under an initial condition, software installed in the simulation control module reads a solar irradiation condition set by a user, wherein the solar irradiation condition mainly comprises parameters such as latitude, date and time, the solar irradiation condition is input into a solar cell power model, a power parameter table of the solar cell is generated after the model is operated, the solar cell power model is a model established in the simulation control module in advance, and the user can complete corresponding power allocation values only by inputting corresponding parameters.
Then, the flight power schedule is read according to the requirements of the flight tasks, and it can be understood that the simulation control module adjusts the load power of the multi-energy system according to the current state of the long-endurance aerostat and the information such as the output torque of the motor system under different modes (ascending, accelerating, windward, fixed-point air-laying, cruising, decelerating and braking, descending and the like) through the requirement model of the flight working conditions, so that the power curve of the electronic load in the flight process can be obtained through the flight power schedule, and the power parameters of the electronic load are simulated.
And after the parameter setting is completed, the simulation control module reads the information of the battery pack monitored by the battery management unit, and after the fault-free state of the battery pack is confirmed, the high-voltage power of the battery pack is connected to the energy conversion module.
After the high-voltage power is connected to the energy conversion module, if the power on of the energy conversion module is normal, the solar cell array simulator is started, parameter setting is carried out according to a power parameter table of the solar cell, energy supply is completed, a power curve of an electronic load is set according to a flight power time table, and the electronic load is started, so that the simulation device of the stratospheric long-voyage aerostat energy system enters a simulation process, and a user records simulation data by observing a display result of the simulation control module.
On the basis of the above embodiment, the method further includes:
and if the battery pack is confirmed to have faults, generating alarm information, and carrying out maintenance and investigation according to the alarm information until the battery pack is confirmed to have no faults.
It can be understood that if a fault occurs in the battery pack during the simulation process or before the simulation starts, the simulation will fail or the simulation result is inaccurate, and for this problem, the method provided by the embodiment of the invention will detect the fault condition of the battery pack in real time, and if the fault occurs, generate alarm information in time, so as to perform overhaul and check according to the alarm information, for example: renewing the damaged battery therein or replacing the damaged line, etc., until the battery pack operates without malfunction.
On the basis of the foregoing embodiment, the power parameter table of the solar cell specifically includes:
maximum power point voltage, maximum power point current, open circuit voltage, and short circuit current of the solar array simulator.
It should be noted that, software installed in the simulation control module can control the setting power of the solar cell array simulator to be generated through the solar cell power generation power model according to the input parameters.
The input quantity of the solar cell model mainly comprises: altitude, month, date, latitude, flight attitude, position and curved shape of the solar cell on the surface of the long-endurance aerostat, solar cell conversion efficiency and area. In the embodiment of the invention, the solar cell surface is divided into k pieces by a numerical calculation method
Vector unit, calculate the unit radiation vector of time t according to the sun azimuth angle, altitude angle +.>
Will->
And->
Carrying out dot product to obtain unit orthographic radiation quantity of the ith area unit, summing the k dot products, and multiplying the k dot products by average solar radiation surface density, photoelectric conversion efficiency eta and comprehensive loss factor rho to obtain the power generation at the moment t:
and taking the generated power as the maximum power output of the solar cell array simulator, and determining the maximum power point voltage, the maximum current, the maximum open-circuit voltage and the maximum short-circuit current through the filling factor and the actual solar cell array voltage range.
According to the simulation device and the simulation method for the energy system of the stratospheric long-endurance aerostat, provided by the embodiment of the invention, the software model is combined with the hardware entity, the software is used for realizing the on-line adjustment of the input power of the energy system by controlling the solar array simulator, the power output of the solar array under different illumination, different latitude and different time can be simulated in real time, meanwhile, the working mode and the power requirement of an electronic load can be adjusted according to different flight tasks and flight working conditions, so that the bus voltage and the current output of a power supply controller can be monitored in real time under different power conditions, the charging and discharging processes of a battery pack can be monitored, the actual working process of the energy system in the whole flight tasks can be simulated, experimental basis is provided for parameter matching and energy balance of all parts of the energy system of the stratospheric long-endurance aerostat, and the functions and performances of the energy system can be tested.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (9)
1. A stratospheric long-endurance aerostat energy system simulation device, characterized by comprising:
the system comprises an energy generation module, an energy conversion module, an energy storage module, an energy consumption module and a simulation control module;
the energy generation module comprises a plurality of solar cell array simulators, and the output of each solar cell array simulator is respectively connected with one input of the energy conversion module;
the energy consumption module comprises a plurality of electronic loads, and each electronic load is respectively connected with one input of the energy conversion module;
the energy storage module comprises a battery pack and a battery management unit, wherein the battery pack is connected with one input of the battery management unit and one input of the energy conversion module respectively;
the simulation control module is respectively connected with the solar cell array simulator, the electronic load, the energy conversion module and the battery management unit through a data bus;
the energy conversion module is a power supply controller, the power supply controller comprises a plurality of types of inputs, a first type of input of the power supply controller is connected with the solar array simulator through a cable, a second type of input of the power supply controller is connected with positive and negative electrode outputs of the battery pack through a high-voltage line, a third type of input of the power supply controller is connected with the electronic load through a cable, and a fourth type of input of the power supply controller is connected with the simulation control module through a CAN bus.
2. The stratospheric long-endurance aerostat energy system simulation device of claim 1, wherein the simulation control module is connected with the battery management unit and the energy conversion module through a CAN bus.
3. The stratospheric long-endurance aerostat energy system simulation device of claim 2, wherein the battery pack is composed of a plurality of lithium batteries in series, each lithium battery is connected with the battery management unit through a signal line, and the battery pack is connected with the energy conversion module through a high-voltage cable.
4. The stratospheric long-endurance aerostat energy system simulation device of claim 1, wherein the simulation control module is connected with the solar array simulator through an RS485 bus.
5. The stratospheric long-endurance aerostat energy system simulation apparatus of claim 1, wherein the simulation control module is connected to the electronic load through a GPIB bus.
6. The stratospheric long-endurance aerostat energy system simulation apparatus of claim 5, wherein the electronic loads comprise a first type of electronic load that simulates a motor and a second type of electronic load that simulates a fan.
7. The simulation method of the stratosphere long-endurance aerostat energy system is characterized by comprising the following steps of:
generating a power parameter table and a flight power time table of the solar cell based on the solar irradiation condition, the solar cell voltage and the current parameter table set in the simulation control module;
if the battery pack is confirmed to have no fault, connecting the high-voltage battery pack to an energy conversion module, and detecting the power-on state of the energy conversion module;
if the power-on state of the energy conversion module is normal, starting a solar cell array simulator according to a power parameter table of the solar cell, and starting an electronic load according to the flying power time table so as to simulate;
the energy conversion module is a power supply controller, the power supply controller comprises a plurality of types of inputs, a first type of input of the power supply controller is connected with the solar array simulator through a cable, a second type of input of the power supply controller is connected with positive and negative electrode outputs of the battery pack through a high-voltage line, a third type of input of the power supply controller is connected with the electronic load through a cable, and a fourth type of input of the power supply controller is connected with the simulation control module through a CAN bus.
8. The method of claim 7, wherein the method further comprises:
and if the battery pack is confirmed to have faults, generating alarm information, and carrying out maintenance and investigation according to the alarm information until the battery pack is confirmed to have no faults.
9. The method according to claim 7, wherein the power parameter table of the solar cell specifically comprises:
maximum power point voltage, maximum power point current, open circuit voltage, and short circuit current of the solar array simulator.
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