CN110502057B - Current equalizing method of spacecraft solar power adjusting module without current detection - Google Patents
Current equalizing method of spacecraft solar power adjusting module without current detection Download PDFInfo
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- CN110502057B CN110502057B CN201910604753.6A CN201910604753A CN110502057B CN 110502057 B CN110502057 B CN 110502057B CN 201910604753 A CN201910604753 A CN 201910604753A CN 110502057 B CN110502057 B CN 110502057B
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05F—SYSTEMS FOR REGULATING ELECTRIC OR MAGNETIC VARIABLES
- G05F1/00—Automatic systems in which deviations of an electric quantity from one or more predetermined values are detected at the output of the system and fed back to a device within the system to restore the detected quantity to its predetermined value or values, i.e. retroactive systems
- G05F1/10—Regulating voltage or current
- G05F1/625—Regulating voltage or current wherein it is irrelevant whether the variable actually regulated is ac or dc
Abstract
The invention provides a current equalizing method of a spacecraft solar power adjusting module without current detection, which comprises the following steps: s1, designing solar power adjusting modules which run in parallel; s2, indirectly extracting the output current quantity of the solar power adjusting modules running in parallel; and S3, current sharing control, wherein the current sharing control only exists in a voltage stabilizing mode of the solar power adjusting module by utilizing the characteristic of a power curve of the solar battery, and the solar array works at the right side of the maximum power point of the power curve in the voltage stabilizing mode, so that the output power balance, namely current balance, can be controlled by controlling the working point voltage of the solar battery array, and the current sharing is completed. The invention has the beneficial effects that: the method for directly introducing the working voltage of the solar array is adopted to realize current sharing control, and the output current of the solar power adjusting module does not need to be detected, so that a complex current detection circuit can be avoided, the current sharing control is simple and reliable, and the cost is relatively low.
Description
Technical Field
The invention relates to a spacecraft power supply system, in particular to a current equalizing method of a spacecraft solar power adjusting module without current detection.
Background
The spacecraft power supply system mostly adopts a power generation mode of a solar cell array to obtain energy, the power of the solar cell array is processed by a power adjusting module and then is output to a bus, and for a high-power solar power generation system, the low-power solar power adjusting module runs in parallel to provide high-power output for the bus.
The small-power systems are operated in parallel, so that the practical application has more advantages, on one hand, the small-power systems are easy to integrate and debug, and the large-power output can be realized through parallel connection; on the other hand, the single module connected in parallel fails, and the normal work of other power supply modules is not influenced, so that the reliability of the whole system is greatly improved.
Although the advantage of parallel operation of low-power systems is obvious, a problem exists in the parallel operation of the low-power systems, namely, all modules which cannot be connected in parallel in actual production are completely consistent, so that after the modules are connected in parallel, the current distribution is uneven due to different external characteristics, the system is easily damaged due to long-term overload caused by more bearing current with good external characteristics, and the output current is less when the external characteristics are poor, so that the system is lightly loaded or even unloaded, the effect cannot be exerted, the load of the whole parallel system is inconsistent, the cold and hot are uneven, and finally, the reliability of the whole system is reduced, the service life is shortened or the whole system cannot work.
Therefore, an effective current sharing method must be adopted in a multi-path parallel system to ensure the current balance of each module and improve the reliability and stability of the system.
Generally, to achieve current balance, it is necessary to detect the current value of each module, and dynamically adjust the current value by negative feedback control methods such as droop control, so as to finally achieve output current uniformity. High-precision current detection usually uses a method of connecting a sampling resistor or a Hall device in series, and compared with voltage detection, the current detection has the defects of complex circuit, low reliability under extreme environments, high cost, poor safety and the like.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a current sharing method for a spacecraft solar power regulating module without current detection, so that the defects of complex circuit, high cost and poor reliability caused by current amount detection compared with voltage amount detection in the current sharing control process of the solar power regulating modules running in parallel are overcome, and more concise current sharing control is realized.
The invention provides a current equalizing method of a spacecraft solar power adjusting module without current detection, which comprises the following steps:
s1, designing solar power adjusting modules which run in parallel, wherein the solar power adjusting modules are used for realizing solar power adjustment, adopting buck-boost conversion, and enabling the voltage of a working point of a solar array to be higher than the voltage of a bus or lower than the voltage of the bus; when the solar power is rich, the solar power adjusting module works in a voltage stabilization state, so that the solar array works on the right side of the maximum power point of a power curve;
s2, the output current amount of the solar power adjusting modules running in parallel is indirectly extracted, because the solar power adjusting modules are directly connected in parallel, the output voltage of each solar power adjusting module is the same, if the current of each solar power adjusting module is consistent, the output power of each solar power adjusting module is consistent, for a solar array, the output power of each solar power adjusting module is consistent, the working point voltage of the solar array is consistent, and the output current amount detection of the solar power adjusting modules is converted into input voltage amount detection;
and S3, current sharing control, wherein the current sharing control only exists in a voltage stabilizing mode of the solar power adjusting module by utilizing the characteristic of a power curve of the solar battery, and the solar array works at the right side of the maximum power point of the power curve in the voltage stabilizing mode, so that the output power balance, namely current balance, can be controlled by controlling the working point voltage of the solar battery array, and the current sharing is completed.
As a further improvement of the present invention, in step S1, the solar power adjusting module adopts a Buck-Boost topology, the solar cell array is adjusted to the bus in a Boost mode or adjusted to the bus in a Buck mode, and when the solar power is insufficient, the solar power adjusting module works in a maximum power tracking state, so that the solar array works at a maximum power point of a power curve; when the solar power is rich, the solar power adjusting module works in a voltage stabilization state, so that the solar array works on the right side of the maximum power point of the power curve.
As a further improvement of the present invention, in step S2, when the solar power conditioning modules operate at the maximum power point, each solar power conditioning module outputs maximum power, and there is no current sharing problem, so the current sharing problem only relates to the voltage stabilizing operating mode, and in the voltage stabilizing operating mode, the output power is balanced when the output current of each solar power conditioning module is balanced, and further the input power of each solar power conditioning module is balanced, and on the right side of the maximum power point of the power curve when the solar array operates at the power curve, there is a fixed monotonic function relationship between the output power and the operating point voltage of the solar array, and based on the monotonic function relationship, the detection of the output current of the solar power conditioning module is converted into the detection of the input voltage.
As a further improvement of the present invention, in step S3, when the output voltage of the solar array is higher than the maximum power point voltage, the solar array operates on the right side of the maximum power point of the power curve, and the higher the output voltage of the solar array, the lower the output power, and when the output voltage of the solar array is higher, the reference voltage of the solar power regulating module is increased, that is, the feedforward from the output voltage of the solar array to the reference voltage of the solar power regulating module is introduced, and the reference voltage value of each solar power regulating module is solved through linear transformation of the output voltage of the solar array, so as to achieve power balance and output current sharing of each solar power regulating module.
The invention has the beneficial effects that: the method for directly introducing the working voltage of the solar array is adopted to realize current sharing control, and the output current of the solar power adjusting module does not need to be detected, so that a complex current detection circuit can be avoided, the current sharing control is simple and reliable, and the cost is relatively low.
Drawings
FIG. 1 is a block diagram of spacecraft solar power conditioning modules operating in parallel.
Fig. 2 is a topological circuit diagram of a solar power conditioning module.
Fig. 3 is a power curve of a solar cell.
Detailed Description
The invention is further described with reference to the following description and embodiments in conjunction with the accompanying drawings.
A current equalizing method for a spacecraft solar power regulating module without current detection comprises the following steps:
s1, designing solar power adjusting modules which run in parallel, wherein the solar power adjusting modules are used for realizing solar power adjustment, adopting buck-boost conversion, and enabling the voltage of a working point of a solar array to be higher than the voltage of a bus or lower than the voltage of the bus; when the solar power is rich, the solar power adjusting module works in a voltage stabilization state, so that the solar array works on the right side of the maximum power point of a power curve;
s2, the output current amount of the solar power adjusting modules running in parallel is indirectly extracted, because the solar power adjusting modules are directly connected in parallel, the output voltage of each solar power adjusting module is the same, if the current of each solar power adjusting module is consistent, the output power of each solar power adjusting module is consistent, for a solar array, the output power of each solar power adjusting module is consistent, the working point voltage of the solar array is consistent, and the output current amount detection of the solar power adjusting modules is converted into input voltage amount detection;
and S3, current sharing control, wherein the current sharing control only exists in a voltage stabilizing mode of the solar power adjusting module by utilizing the characteristic of a power curve of the solar battery, and the solar array works at the right side of the maximum power point of the power curve in the voltage stabilizing mode, so that the output power balance, namely current balance, can be controlled by controlling the working point voltage of the solar battery array, and the current sharing is completed.
In step S1, the solar power adjusting module adopts a Buck-Boost topology, the solar cell array is adjusted to the bus in a Boost mode or adjusted to the bus in a Buck mode, and when the solar power is insufficient, the solar power adjusting module works in a maximum power tracking state to enable the solar cell array to work at a maximum power point of a power curve; when the solar power is rich, the solar power adjusting module works in a voltage stabilization state, so that the solar array works on the right side of the maximum power point of the power curve.
In step S2, when the solar power conditioning modules operate at the maximum power point, the solar power conditioning modules all output maximum power, and there is no current sharing problem, so the current sharing problem only relates to the voltage stabilizing operating mode, and in the voltage stabilizing operating mode, the output power of each solar power conditioning module is balanced when the output current of each solar power conditioning module is balanced, and further the input power of each solar power conditioning module is balanced, and when the solar array operates at the right side of the maximum power point of the power curve, there is a fixed monotonic function relationship between the output power and the operating point voltage of the solar array, and based on the monotonic function relationship, the detection of the output current of the solar power conditioning module is converted into the detection of the input voltage.
In step S3, when the output voltage of the solar array is higher than the maximum power point voltage, the solar array operates at the right side of the maximum power point of the power curve, and the output voltage of the solar array is higher and the output power is lower, and when the output voltage of the solar array is higher, the reference voltage of the solar power adjusting module is increased, that is, the feedforward from the output voltage of the solar array to the reference voltage of the solar power adjusting module is introduced, and the reference voltage value of each solar power adjusting module is solved through linear transformation of the output voltage of the solar array, so as to achieve power balance and output current equalization of each solar power adjusting module.
Example 1
1. Overall scheme design
As shown in fig. 1, according to the requirement of the engineering system, n solar power conditioning modules correspond to n solar power sub-arrays (i.e. solar arrays), and the goal of the system design is to control the output current I of the n solar power conditioning modules1～InIn accordance, fig. 1 is a block diagram of a solar power conditioning module for spacecraft operating in parallel.
2. Designing solar power conditioning module topology
As shown in fig. 2, a Buck-Boost solar power regulation module is designed, the solar power regulation module adopts a Buck-Boost topology, fig. 2 is a topological circuit diagram of the solar power regulation module, and the input and output relations are shown in the following formula:
wherein:
VOis the output voltage;
VINis the input voltage;
d is the duty ratio of the switching tube.
3. Designing operating point voltage of solar cell array
According to task requirements and design principles, current sharing control only exists in the situation that each power regulating module works in a voltage stabilizing mode, and the working voltage of the solar power sub-array is on the right side of the maximum power point of a power curve; the bus voltage of the design is 100V, and the working voltage range of the solar array under the voltage stabilization mode is 80-120V.
4. Control algorithm
Introducing the output voltage V of the solar arraygTo the power regulating voltage regulation module reference voltage VrefiTo achieve automatic power balancing and current sharing. In the design, under the voltage stabilizing mode, the solar array outputs a voltage VgIs in the range of 80-120V, the bus reference voltage is 100V, and V is setgReference voltage V to power conditioning module irefiThe linear transformation of (1) is as follows, where k is a scaling factor.
Vrefi＝100+k(Vg-80)
5. Current sharing Process
As shown in fig. 3, assuming that the output powers of the two power conditioning modules are unequal (the output power of the module 1 is higher than that of the module 2), and the output voltages of the two modules are bus voltages under the condition that the two modules are powered in parallel, the output current of the module 1 is greater than the output current of the module 2, and as can be seen from the output characteristic curve of the solar array, the output voltage of the solar array of the module 1 is less than the output voltage of the solar array of the module 2 (the solar array operates at the right side of the maximum power point). Then the module 1 regulated module reference voltage is less than the module 2 regulated module reference voltage and the duty cycle d1 generated by module 1 will be less than the duty cycle d2 generated by module 2. According to the output-input relation of the Buck-Boost converter, the input voltage of the module 1 is relatively increased, and the input voltage of the module 2 is relatively decreased. Under the voltage stabilization mode (the solar array works at the right side of the maximum power point), the output power of the module 1 is relatively reduced, the output power of the module 2 is relatively increased, and finally the output powers of the two modules are balanced, namely, the current is balanced, and the current equalization is completed.
The invention provides a current equalizing method of a spacecraft solar power adjusting module without current detection, which designs a solar power adjusting module capable of adjusting voltage, enables a solar array to work on the right side of the maximum power point of a power curve under a voltage stabilizing state, can reflect the state of output power by detecting the working voltage of the solar array due to the specific relation between the working voltage and the output power of the solar array, and realizes the equalizing control of the output power and the output current of the solar power adjusting module through a certain current equalizing control algorithm.
The spacecraft solar power regulating module current sharing method without current detection provided by the invention can realize current sharing control among all parallel modules under the condition of not detecting the current magnitude of the power module, greatly simplifies the engineering realization of current sharing control, designs the solar power regulating module, the indirect extraction of the module output current magnitude and the current sharing control algorithm among the modules, and has the advantages of simple and reliable system circuit, low cost and easy realization compared with the method adopting current detection.
The invention provides a current equalizing method of a spacecraft solar power adjusting module without current detection, which is mainly characterized in that:
1. the solar power regulation module is designed, the maximum power tracking working mode and the output voltage stabilization working mode of the solar array can be realized by adopting voltage boosting and reducing control, and the solar array is controlled to work on the right side of the maximum power point of a working curve in the output voltage stabilization working mode.
2. The parallel operation characteristic of the solar power regulating modules is ingeniously utilized, the output current balance is converted into the input power balance, and the output current balance can be controlled by controlling the input power balance.
3. The characteristics of the working curve of the solar cell are ingeniously utilized, current sharing control only exists in a voltage stabilizing mode of the solar power adjusting module, the solar array works on the right side of the maximum power point of the working curve in the voltage stabilizing mode, and output power balance can be controlled by controlling the voltage of the working point of the solar array.
4. The feedforward from the output voltage of the solar array to the reference voltage of the power regulating module is introduced, and the reference voltage value of each module is solved through the linear transformation of the output voltage of the solar array, so that the power balance and the output current sharing of each solar power regulating module are realized.
The foregoing is a more detailed description of the invention in connection with specific preferred embodiments and it is not intended that the invention be limited to these specific details. For those skilled in the art to which the invention pertains, several simple deductions or substitutions can be made without departing from the spirit of the invention, and all shall be considered as belonging to the protection scope of the invention.
Claims (3)
1. A current equalizing method for a spacecraft solar power regulating module without current detection is characterized by comprising the following steps:
s1, designing solar power adjusting modules which run in parallel, wherein the solar power adjusting modules are used for realizing solar power adjustment, adopting buck-boost conversion, and enabling the voltage of a working point of a solar array to be higher than the voltage of a bus or lower than the voltage of the bus; when the solar power is rich, the solar power adjusting module works in a voltage stabilization state, so that the solar array works on the right side of the maximum power point of a power curve;
s2, the output current amount of the solar power adjusting modules running in parallel is indirectly extracted, because the solar power adjusting modules are directly connected in parallel, the output voltage of each solar power adjusting module is the same, if the current of each solar power adjusting module is consistent, the output power of each solar power adjusting module is consistent, for a solar array, the output power of each solar power adjusting module is consistent, the working point voltage of the solar array is consistent, and the output current amount detection of the solar power adjusting modules is converted into input voltage amount detection;
s3, current sharing control, wherein the current sharing control only exists in a voltage stabilizing mode of the solar power adjusting module by utilizing the characteristic of a power curve of the solar battery, and the solar array works at the right side of the maximum power point of the power curve in the voltage stabilizing mode, and the output power balance, namely current balance, can be controlled by controlling the working point voltage of the solar battery array, so that current sharing is completed;
in step S1, the solar power adjusting module adopts a Buck-Boost topology, the solar cell array is adjusted to the bus in a Boost mode or adjusted to the bus in a Buck mode, and when the solar power is insufficient, the solar power adjusting module works in a maximum power tracking state to enable the solar cell array to work at a maximum power point of a power curve; when the solar power is rich, the solar power adjusting module works in a voltage stabilization state, so that the solar array works on the right side of the maximum power point of the power curve.
2. The spacecraft solar power conditioning module current sharing method without current detection of claim 1, wherein: in step S2, when the solar power conditioning modules operate at the maximum power point, the solar power conditioning modules all output maximum power, and there is no current sharing problem, so the current sharing problem only relates to the voltage stabilizing operating mode, and in the voltage stabilizing operating mode, the output power of each solar power conditioning module is balanced when the output current of each solar power conditioning module is balanced, and further the input power of each solar power conditioning module is balanced, and when the solar array operates at the right side of the maximum power point of the power curve, there is a fixed monotonic function relationship between the output power and the operating point voltage of the solar array, and based on the monotonic function relationship, the detection of the output current of the solar power conditioning module is converted into the detection of the input voltage.
3. The spacecraft solar power conditioning module current sharing method without current detection of claim 1, wherein: in step S3, when the output voltage of the solar array is higher than the maximum power point voltage, the solar array operates at the right side of the maximum power point of the power curve, and the output voltage of the solar array is higher and the output power is lower, and when the output voltage of the solar array is higher, the reference voltage of the solar power adjusting module is increased, that is, the feedforward from the output voltage of the solar array to the reference voltage of the solar power adjusting module is introduced, and the reference voltage value of each solar power adjusting module is solved through linear transformation of the output voltage of the solar array, so as to achieve power balance and output current equalization of each solar power adjusting module.
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