CN117239892A - Energy system of airship capable of being reconstructed independently and airship - Google Patents
Energy system of airship capable of being reconstructed independently and airship Download PDFInfo
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Abstract
The application relates to the technical field of photovoltaic devices of aircrafts, and discloses an energy system of an autonomous reconfigurable airship and the airship, wherein the energy system of the airship comprises: a photovoltaic array; the reconstruction calculation module is used for calculating a reconstruction serial-parallel structure of the photovoltaic array according to the flight state and the irradiation intensity; the difference value between the total irradiation intensity of the photovoltaic modules in any row and the irradiation intensity of the photovoltaic modules in other rows in the serial-parallel structure after the reconstruction of the photovoltaic array is not more than a preset difference value threshold; the reconstruction control module is used for generating a reconstruction signal of the series-parallel connection construction circuit according to the reconstruction series-parallel connection structure of the photovoltaic array; and the series-parallel connection construction circuit is used for responding to the reconstruction signal to construct a series-parallel connection structure of the photovoltaic assembly in the photovoltaic array. The system reconstruction method has the advantages that the system reconstruction is simple, accurate and rapid, so that the problem that the output power of the aircraft photovoltaic array is greatly reduced due to mismatch loss is solved, and the power supply capacity and the power supply stability of the photovoltaic array are improved.
Description
Technical Field
The application relates to the technical field of photovoltaic energy of aircrafts, in particular to an energy system of an autonomous reconfigurable airship and the airship.
Background
In recent years, stratospheric flying platforms, mainly solar aircraft, airships (such as stratospheric airships) and high-altitude balloons, have been developed at a rapid pace. Compared with solar aircrafts and high-altitude balloon, the airship has maneuverability, maneuverability and long-time altitude maintenance capability, and simultaneously has the large load capacity which the two aircrafts do not have, and is more suitable for executing tasks such as regional residence, ground monitoring, communication relay and the like. In order to meet the long-endurance flight requirement, the airship needs to continuously supply power to the on-board power system and the propulsion system through the circulating energy system, and the power supply capacity and the power supply stability of the circulating energy system are important for improving the wind resistance capacity of the airship and prolonging the endurance of the airship.
Mismatch loss caused by uneven irradiation distribution can seriously affect the output power of the photovoltaic array, and local hot spots can seriously occur to cause the ablation of the solar panel. For ground photovoltaic systems, random shading is a major factor in causing uneven irradiation; however, for the photovoltaic array, since the solar panels are arranged along the surface of the airship body in a conformal manner, the whole is a curved surface, and the irradiation intensity at different positions at each moment is different, the mismatch loss is continuously present and time-varying, which can seriously reduce the output power of the photovoltaic array, and the wind resistance residence and the maneuverability of the airship are reduced. How to eliminate the influence of mismatch loss on the output power of the photovoltaic array through topological structure optimization is a key problem for improving the power supply capacity and the power supply stability of a circulating energy system, and the problem and the solution have not been proposed at present.
Disclosure of Invention
The application provides an energy system of an airship capable of being autonomously reconfigured and the airship, which are used for effectively solving the problem of mismatch loss of a photovoltaic array and eliminating the reduction of output power of the photovoltaic array caused by the mismatch loss and the misleading effect of multiple MPP points of a P-V curve on an MPPT algorithm.
In a first aspect, there is provided an energy system for an autonomously reconfigurable airship, comprising:
the photovoltaic array comprises a plurality of photovoltaic modules which are arranged on the surface of the airship in an array manner, and the shape of each photovoltaic module is adapted to the surface of the airship;
the reconstruction calculation module is used for acquiring the flight state of the airship and the irradiation intensity on the photovoltaic array, and calculating the reconstruction serial-parallel structure of the photovoltaic array according to the flight state and the irradiation intensity; the difference value between the total irradiation intensity of the photovoltaic modules in any row and the irradiation intensity of the photovoltaic modules in other rows in the serial-parallel structure after the photovoltaic array is reconstructed is not greater than a preset difference value threshold;
the reconstruction control module is connected with the reconstruction calculation module and is used for generating a reconstruction signal of a series-parallel connection construction circuit according to the reconstruction series-parallel connection structure of the photovoltaic array;
and the series-parallel connection construction circuit is connected with each photovoltaic module in the photovoltaic array and is used for responding to the reconstruction signals to construct a series-parallel connection structure of the photovoltaic modules in the photovoltaic array.
In the above scheme, the series-parallel connection construction circuit comprises a plurality of switch assemblies corresponding to the photovoltaic assemblies one by one, each switch assembly is connected between the photovoltaic assembly and the reconstruction control module, and the series-parallel connection construction circuit controls the connection relation of each switch assembly according to the reconstruction signals.
In the above scheme, the switch assembly comprises a first switch, a second switch and a composite switch contact; the first switch is connected with the positive electrode of the photovoltaic module, the second switch is connected with the negative electrode of the photovoltaic module, and the composite switch contact comprises a plurality of positive electrode contacts, a plurality of negative electrode contacts and a common contact; and the first switch and the second switch respectively respond to the connection of the reconstruction signal and different contacts of the compound switch to construct a series-parallel structure after the reconstruction of the photovoltaic component.
In the above scheme, the number of the composite switch contacts is positively correlated with the number of the photovoltaic modules in the photovoltaic module circuit connected in series to the maximum, wherein the number of the composite switch contacts is 2x+1, the composite switch contacts comprise X positive electrode contacts, X negative electrode contacts and 1 positive and negative electrode common contact, and the number of the photovoltaic modules in the photovoltaic module circuit connected in series to the maximum is X.
In the scheme, the series-parallel connection construction circuit is connected with the photovoltaic module through the power output cable.
In the above scheme, the energy device of the airship further comprises an energy storage battery pack, the energy storage battery pack is connected with the series-parallel connection construction circuit, and a DC/DC converter is connected between the energy storage battery pack and the series-parallel connection construction circuit.
In the scheme, the DC/DC converter is connected with the series-parallel connection construction circuit through the power supply communication composite cable.
In the above scheme, the reconstruction calculation module is configured to obtain solar irradiation intensity and a flight state of the airship in a preset period;
performing difference comparison on the solar irradiation intensity of the current period and the solar irradiation intensity of the previous period, and performing difference comparison on the flight state of the current period and the flight state of the previous period;
if the difference comparison result of the solar irradiation intensity is larger than a preset first threshold value and/or the difference comparison result of the flight state is larger than a second preset threshold value, calculating a reconstruction serial-parallel structure of the photovoltaic module of the photovoltaic array according to the solar irradiation intensity in the current period, and generating a control instruction of a reconstruction control module.
In the above scheme, the P-V curve of the photovoltaic array after reconstruction optimization exhibits a single MPP point characteristic.
In a second aspect, there is provided an airship comprising:
an airship body;
the airship body is provided with:
the irradiation intensity acquisition module is used for acquiring the irradiation intensity on the photovoltaic module;
the combined inertial navigation is used for collecting the flight state of the airship;
and the energy system of the airship capable of being automatically reconfigured.
According to the scheme of the energy system of the airship capable of being automatically reconstructed and the airship, the reconstruction serial-parallel structure of the photovoltaic array can be calculated according to the flight state and the irradiation intensity through the reconstruction calculation module, the reconstruction structure enables the photovoltaic array to have optimal output power, namely, the difference value between the total irradiation intensity of the photovoltaic modules in any row in the serial-parallel structure after the reconstruction of the photovoltaic array and the irradiation intensity of the photovoltaic modules in other rows is not larger than a preset difference value threshold, then, the reconstruction control module generates a reconstruction signal of a serial-parallel construction circuit according to the reconstruction serial-parallel structure of the photovoltaic array, and finally the serial-parallel construction circuit responds to the reconstruction signal to construct the serial-parallel structure of the photovoltaic modules in the photovoltaic array. Therefore, the output characteristic of the photovoltaic array is optimal for the current state, namely mismatch loss is minimized. According to the energy system of the airship, the control instruction of the reconstruction control module can be determined according to the current solar irradiation intensity, the flight state of the airship and the array reconstruction optimization, the reconstruction signal of the series-parallel connection construction circuit is generated according to the control instruction, and the photovoltaic assembly is controlled to form an optimal series or parallel connection structure according to the reconstruction signal. The photovoltaic array is simply, accurately and quickly reconstructed through the reconstruction control module, so that the output power reaches the optimal state, and the P-V curve of the array shows the single MPP point characteristic.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the description of the embodiments of the present application will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a block diagram of an energy system of an autonomously reconfigurable airship according to one embodiment of the application;
FIG. 2 is a schematic diagram of a circuit connection structure of a reconstruction module of an energy system of an autonomous reconfigurable airship according to one embodiment of the application;
FIG. 3 is a schematic diagram of the circuit connections of the TCT structure of a pre-and post-reconstruction alignment of a photovoltaic array of an energy system of an autonomously reconfigurable airship according to one embodiment of the application;
FIG. 4 is a schematic view of an airship according to one embodiment of the application;
the attached drawings are used for identifying and describing:
the energy storage device comprises an airship body 101, a photovoltaic array 102, a photovoltaic module 1021, a reconstruction calculation module 103, a photovoltaic array reconstruction module 104, a power supply communication composite cable 105, an airship pod 106, an irradiation intensity acquisition module 107, a combined inertial navigation 108, a DC/DC converter 201, an energy storage battery pack 202, a load 203, a reconstruction control module 301, an anode bus 302, a cathode bus 303, a composite switch contact 304, a second switch 305 and a first switch 306.
Detailed Description
The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are some, but not all embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
The terms "first," "second," "third," and "fourth" and the like in the description and in the claims and drawings are used for distinguishing between different objects and not necessarily for describing a particular sequential or chronological order. Furthermore, the terms "comprise" and "have," as well as any variations thereof, are intended to cover a non-exclusive inclusion. For example, a process, method, system, article, or apparatus that comprises a list of steps or elements is not limited to only those listed steps or elements but may include other steps or elements not listed or inherent to such process, method, article, or apparatus.
Reference herein to "an embodiment" means that a particular feature, result, or characteristic described in connection with the embodiment may be included in at least one embodiment of the application. The appearances of such phrases in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments. Those of skill in the art will explicitly and implicitly appreciate that the embodiments described herein may be combined with other embodiments.
The photovoltaic array carried by the airship is a curved solar array, the laying area is large, the curvature is also large, the irradiation intensity received at each position at the same time is greatly different and is similar to the local shadow of the ground photovoltaic array, and the difference is that the 'local shadow' of the photovoltaic array continuously exists and the characteristic of the 'local shadow' also changes along with the change of the attitude angle of the airship. Such "partial shading" can not only affect the output power of the photovoltaic modules in the shading, but can also result in a reduction in the output power of other modules, which is known as a "mismatch loss" effect. The mismatch loss can greatly reduce the output power of the photovoltaic array, and meanwhile, the P-V curve can be caused to present a multi-MPP characteristic, so that challenges are brought to an MPPT searching algorithm, the MPPT searching algorithm is easy to sink into local optimum, and further the output power of the photovoltaic array is further reduced. The above problems can be solved by the series-parallel reconstruction of the photovoltaic array in the following embodiments.
Referring to fig. 1 to 3, fig. 1 is an energy system of an airship capable of autonomous reconfiguration according to an embodiment of the application, including: the photovoltaic array 102, the reconstruction calculation module and the photovoltaic array reconstruction module 104, wherein the photovoltaic array reconstruction module 104 comprises a reconstruction control module 301 and a series-parallel connection construction circuit.
The photovoltaic array 102 comprises a plurality of photovoltaic modules 1021 arranged on the surface of the airship in an array manner, and the shape of the photovoltaic modules 1021 is adapted to the surface of the airship;
the reconstruction calculation module is used for acquiring the flight state of the airship and the irradiation intensity on the photovoltaic array 102, and calculating the reconstruction serial-parallel structure of the photovoltaic array 102 according to the flight state and the irradiation intensity; wherein, the difference value between the total irradiation intensity of the photovoltaic modules 1021 in any row and the irradiation intensity of the photovoltaic modules 1021 in other rows in the serial-parallel structure after the photovoltaic array reconstruction is not more than a preset difference value threshold;
the reconstruction control module 301 is connected with the reconstruction calculation module and is used for generating a reconstruction signal of the series-parallel connection construction circuit according to the reconstruction series-parallel connection structure of the photovoltaic array 102;
and the series-parallel connection construction circuit is connected with each photovoltaic module 1021 in the photovoltaic array 102 and is used for responding to the reconstruction signal to construct a series-parallel connection structure of the photovoltaic modules 1021 in the photovoltaic array 102.
The photovoltaic array 102 includes a plurality of photovoltaic modules 1021 arranged on the surface of the airship, and the shape of the photovoltaic modules 1021 is adapted to the surface of the airship, i.e. the photovoltaic array 102 includes a plurality of photovoltaic modules 1021 arranged along the shape of the airship.
The flight state comprises information such as pitch angle, yaw angle, roll angle and ground speed.
It will be appreciated that the flight status of the airship may be obtained by the combination inertial navigation device 108 of the airship itself, and the irradiation intensity on the photovoltaic array 102 may be obtained by an irradiation intensity collection device mounted on the airship. The method can also be that the flight state and the solar irradiation intensity of the airship are obtained by monitoring the airship by a third party, namely the reconstruction calculation module obtains the flight state and the irradiation intensity from the third party.
It is understood that the series-parallel configuration of the photovoltaic array 102 is herein an electrical connection configuration of the photovoltaic modules 1021, rather than the physical location of the photovoltaic modules 1021 in the photovoltaic array 102. The reconstructed photovoltaic array 102 adopts a TCT structure (a fully connected structure, total Cross tie). In a TCT configuration, the output power of the photovoltaic array 102 may be maximized if the total irradiance and current in the different rows are close. This principle is referred to as the "irradiance equalization" (irradiance equalization) criterion for TCT-configured photovoltaic arrays 102. Thus, the primary goal of TCT-configured solar array reconstruction is to equalize the available power for each row, i.e., avoid mismatch losses by adjusting the photovoltaic module 1021 position (electrical position) for each row. Criteria for optimal reconstruction matrix: in the TCT topological structure, if the matrix dimension is m rows and n columns, the optimal irradiation matrix is the minimum difference between the maximum value and the minimum value of the sum of the row irradiance of m rows, namely the uniformity of the sum of the row irradiance is the best.
The reconstruction calculation module determines a reconstructed serial-parallel structure of the photovoltaic array 102 according to the flight state and the irradiation intensity, where the reconstructed serial-parallel structure is required to meet the above standard of the optimal reconstruction matrix, that is, a difference between the total irradiation intensity of the photovoltaic modules 1021 in any row in the serial-parallel structure after the reconstruction of the photovoltaic array and the irradiation intensities of the photovoltaic modules 1021 in other rows is not greater than a preset difference threshold. Here, it is preferable that the irradiation intensities of the respective rows of the photovoltaic modules 1021 have no difference, but may not be made, so that the preset difference threshold may be determined according to actual conditions (experience) as long as the control difference is within the preset difference threshold.
In some embodiments, as shown in fig. 2, the serial-parallel connection construction circuit includes a plurality of switch assemblies in one-to-one correspondence with the photovoltaic assemblies 1021, each switch assembly being connected between the photovoltaic assemblies 1021 and the reconstruction control module 301, and the serial-parallel connection construction circuit controlling the connection relationship of each switch assembly according to the reconstruction signal.
Each photovoltaic module 1021 corresponds to one switch module, so that each photovoltaic module 1021 can be controlled independently, that is, the serial-parallel topology of the photovoltaic array 102 can be configured flexibly.
In some embodiments, as shown in fig. 2, the switch assembly includes a first switch 306, a second switch 305, and a composite switch contact 304; the first switch 306 is connected with the positive electrode of the photovoltaic module 1021, the second switch 305 is connected with the negative electrode of the photovoltaic module 1021, and the composite switch contact 304 comprises a plurality of positive electrode contacts, a plurality of negative electrode contacts and a common contact; the first switch 306 and the second switch 305 respectively respond to the connection of the reconstruction signal and different contacts of the composite switch, and a serial-parallel structure of the reconstructed photovoltaic module 1021 is constructed.
The positive output end of each photovoltaic module 1021 is connected with a first switch 306 (positive switch), the negative output end of each photovoltaic module 1021 is connected with a second switch 305 (negative switch), the first switch 306 and the second switch 305 are single-pole multi-throw switches, and the photovoltaic modules 1021 can be switched between the positive bus 302 and the negative bus 303 in any row through the switching of the first switch 306 (positive switch) and the second switch 305 (negative switch) on the composite switch contact 304. If the total number of photovoltaic modules 1021 is N, the total number of switches used by the switch matrix is 2N. The design satisfies the requirement of arbitrary row switching of the photovoltaic module 1021, and simultaneously has the advantages of minimum total switching number, minimum complexity and weight of the reconstruction device, minimum volume of the device, and easy carrying on the airship body.
In some embodiments, the number of the composite switch contacts 304 is in positive correlation with the number of photovoltaic modules 1021 in the largest series of photovoltaic module 1021 circuits, wherein the number of the composite switch contacts 304 is 2x+1, including X positive contacts, X negative contacts, and 1 positive and negative common contacts, and the number of photovoltaic modules 1021 in the largest series of photovoltaic module 1021 circuits is X.
The number of the composite switch contacts 304 is determined by the number of series components of the photovoltaic array 102, and if the number of series components is X, the number of switch contacts is 2x+1. In fig. 3, the number of the photovoltaic arrays 102 connected in series is 4, and the number of the composite switch contacts 304 is 7, wherein the front 3 contacts are positive contacts, the rear 3 contacts are negative contacts, the middle contacts are positive and negative common contacts, and the contact numbers are sequentially 1-7. The reconstruction control module 301 obtains the optimal configuration control signal obtained by the reconstruction calculation module 103 through a communication cable, solves the signal into a control signal corresponding to the anode and the cathode of each photovoltaic module 1021, transmits the control signal to the anode switch and the cathode switch through an internal communication cable, and realizes that the photovoltaic modules 1021 move-between any rows in the array through the connection of the switches and the corresponding contacts. For example, the calculated photovoltaic module 1021 should be moved to the third row of the photovoltaic array 102, and then the control amount of the switch of the photovoltaic module 1021 output by the reconstruction control module 301 is [3,4].
In one application scenario, as shown in fig. 3, the TCT structure of the photovoltaic array 102 has a number of rows of 4, in this case,there are 5 buses, each contact of the composite switch contact 304 is connected with one bus (multiple contacts of one composite switch may be connected with the same bus), and the first switch 306 and the second switch 305 are respectively contacted with different contacts of the composite switch contact 304, so that the photovoltaic module 1021 is switched in different rows. As in fig. 3, the numerals (820, 700, 800, 500, 440, etc.) on the photovoltaic module 1021 refer to the irradiation intensity of the photovoltaic module 1021, e.g., the irradiation intensity is 820W/m before the serial-parallel structure is reconstructed 2 The photovoltaic module 1021 is located in the first row and first column of the TCT structure, and after the serial-parallel structure is reconfigured, the photovoltaic module 1021 is located in the first row and first column of the TCT structure. As shown in fig. 3, after the serial-parallel structure is reconfigured, the irradiation intensities of all rows in the 4-row photovoltaic modules 1021 of the TCT structure, that is, the 4-parallel structure, are equal (optimal state) in the 4-row photovoltaic modules 1021. It should be noted that the TCT structure of the present application is not limited to the structure of fig. 4, and the number of rows and columns is not necessarily equal.
In some embodiments, the series-parallel build circuit is connected to the photovoltaic module 1021 through a power output cable.
Each photovoltaic module 1021 in the on-board photovoltaic array 102 is directly connected with the series-parallel connection construction circuit through a power output cable, and the power output end of the series-parallel connection construction circuit is connected to an inverter in the airship pod 106 through the power supply communication composite cable 105 to supply power for on-board equipment.
In some embodiments, the energy device of the airship further comprises an energy storage battery 202 and a DC/DC converter 201, the energy storage battery 202 being connected to the series-parallel build-up circuit through the DC/DC converter 201.
The output end of the series-parallel connection construction circuit is output to a DC/DC converter 201 positioned in the airship pod 106 through a power supply communication composite cable 105, the DC/DC converter 201 is used for transforming output, the power supply of a load 203 is realized through a high-voltage bus, and the redundant electric energy is stored in an energy storage battery pack 202.
In some embodiments, the photovoltaic device of the airship body further comprises an energy storage battery 202, the energy storage battery 202 being connected to the output of the photovoltaic array reconstruction module 104 for storing the electrical energy output by the photovoltaic array 102.
The output end of the series-parallel connection construction circuit is output to a DC/DC converter 201 positioned in the airship pod 106 through a power supply communication composite cable 105, the DC/DC converter 201 is used for transforming output, the power supply of a load 203 is realized through a high-voltage bus, and the redundant electric energy is stored in an energy storage battery pack 202.
In an embodiment, the reconstruction calculation module 103 is configured to obtain the solar irradiation intensity and the flight state of the airship body in a preset period;
performing difference comparison on the solar irradiation intensity of the current period and the solar irradiation intensity of the previous period, and performing difference comparison on the flight state of the current period and the flight 1 state of the previous period;
if the difference comparison result of the solar irradiation intensity is greater than a preset first threshold value and/or the difference comparison result of the flight state is greater than a second preset threshold value, generating a control instruction of the reconstruction control module 301 according to the solar irradiation intensity of the current period, the flight state of the current period and an output characteristic curve of the photovoltaic array 102 preset in the current period.
When the reconstruction calculation module 103 detects that the attitude angle of the airship changes greatly or the irradiation intensity changes along with the propulsion of the flight time, the above process is repeated, the optimal control signal is continuously output to the serial-parallel connection construction circuit, the real-time switch array reconstruction operation is performed, the real-time topology structure of the photovoltaic array 102 is updated, and the photovoltaic array 102 is ensured to be in an optimal output state in real time.
For example, the heading angle of the airship body changes 90 ° briefly or the local time is from 10 a.m.: 00 to 12:00, resulting in a change in the optimal series-parallel configuration of photovoltaic module 1021.
In this way, the connection relationship between the photovoltaic modules 1021 can be controlled through the serial-parallel connection construction circuit according to the actual scene, so that the serial-parallel connection topological structure of the photovoltaic modules 1021 can be realized, the photovoltaic modules 1021 of the photovoltaic array 102 can be fully utilized, the photovoltaic array 102 has optimal serial-parallel connection configuration, and the output power reaches the optimal state.
In one embodiment, the P-V curve of the photovoltaic array 102 after reconstruction optimization exhibits a single MPP point characteristic, with a maximum theoretical output power.
It can be seen that, in the above scheme, the reconstruction calculation module takes the flight state of the airship and the irradiation intensity data of the photovoltaic array 102 as input, calculates by an optimization program to obtain the optimal serial-parallel configuration of the photovoltaic module 1021, and transmits the optimal serial-parallel configuration to the photovoltaic array reconstruction module 104 through the communication composite cable. The photovoltaic array reconstruction module 104 performs a solution to the optimal serial-parallel configuration and completes the switching operation of the internal switch matrix. The power output ends of the photovoltaic modules 1021 are connected with the input end of the photovoltaic array reconstruction module 104 through power cables, and the serial-parallel topology structure of the photovoltaic modules 1021 is switched along with the switch array inside the photovoltaic array reconstruction module 104 to complete the topology structure update. The on-board photovoltaic array 102 is the optimal serial-parallel configuration in the current airship flight state, the output power reaches the optimal state, and the P-V curve of the array presents the single MPP point characteristic. The energy system in the scheme can solve the problem of mismatch loss of the photovoltaic array 102 caused by uneven irradiation distribution in the flying process of the airship, improve the integral output capacity and output stability of the photovoltaic array 102, optimize the output characteristics of the array, eliminate the multi-MPP point effect in the P-V curve and mislead the MPPT searching algorithm; the reconstruction device can realize the arrangement and recombination of any photovoltaic module 1021 by using only a limited single-pole multi-throw switch, has simple circuit and structural design, does not need additional large-scale moving parts to increase the complexity of an energy system, has minimum weight cost, and can effectively improve the power supply capacity of the airship body circulation energy system. If part of the photovoltaic modules 1021 fail, the failure modules can be reconfigured or isolated through the reconfiguration system, so that the reliability and the robustness of the circulating energy system are further improved.
Referring to fig. 4, fig. 4 is a schematic diagram of an airship according to an embodiment of the application, including:
an airship body 101;
the airship body 101 is provided with:
an irradiation intensity acquisition module 107 for acquiring irradiation intensity on the photovoltaic module 1021;
a combined inertial navigation 108 for collecting the flight status of the airship;
and the energy system of the airship capable of being automatically reconfigured.
The photovoltaic array 102 is arranged on the upper surface of the capsule body of the airship body 101 in a conformal manner, and the irradiation intensity acquisition module 107 is arranged in the middle of the photovoltaic array 102 and is used for monitoring the change of solar irradiation intensity. The photovoltaic array reconstruction module 104 is arranged in front of the photovoltaic array 102, each photovoltaic module 1021 in the photovoltaic array 102 is directly connected with the photovoltaic array reconstruction module 104 through a power output cable, and the power output end of the photovoltaic array reconstruction module 104 is connected to an inverter in the airship pod 106 through a power supply communication composite cable to supply power for the on-board equipment. The combined inertial navigation 108 and the reconstruction calculation module 103 are arranged in the airship pod 106, and the combined inertial navigation 108 is used for obtaining the flight state of the airship body 101, wherein the flight state comprises information such as a pitch angle, a yaw angle, a roll angle, a ground speed and the like. The reconstruction calculation module 103 is configured to receive and transmit data from each device of the airship.
The irradiation intensity acquisition module 107 transmits the voltage signal to the reconstruction calculation module 103 through the power supply communication composite cable 105 to be resolved into a digital signal. The combined inertial navigation 108 transmits attitude angle information such as pitch angle, yaw angle, roll angle and the like to the reconstruction calculation module 103 through a communication cable. The reconstruction calculation module 103 takes the data obtained by the two devices as input, obtains the optimal serial-parallel configuration of the photovoltaic module 1021 through an onboard optimization program, and transmits an optimal control signal to the serial-parallel construction circuit through a communication composite cable. The series-parallel connection construction circuit is used for resolving the control signals and completing the switching operation of the internal switch matrix. The power output ends of the photovoltaic modules 1021 are connected with the input ends of the series-parallel connection construction circuit through power cables, and the series-parallel connection topological structure of the photovoltaic modules 1021 is updated along with the switching of the switch arrays in the series-parallel connection construction circuit. The photovoltaic array 102 is the optimal serial-parallel configuration under the current airship flight state, the output power reaches the optimal state, and the P-V curve of the array presents the single MPP point characteristic. The output of the series-parallel build circuit is output to a DC/DC converter 201 located in the airship pod 106 via a power supply communication composite cable 105, transformed output is performed by the DC/DC converter 201, power is currently supplied to a load 203 by high voltage, and surplus electrical energy is stored in an energy storage battery pack 202.
It will be appreciated that the technical solution of the airship of the present embodiment includes the energy system described above, and therefore the airship of the present embodiment includes all the advantages of the energy system of the autonomous reconfigurable airship described above.
Those skilled in the art will appreciate that implementing all or part of the above described methods may be accomplished by way of a computer program stored on a non-transitory computer readable storage medium, which when executed, may comprise the steps of the embodiments of the methods described above. Any reference to memory, storage, database, or other medium used in embodiments provided herein may include non-volatile and/or volatile memory. The nonvolatile memory can include Read Only Memory (ROM), programmable ROM (PROM), electrically Programmable ROM (EPROM), electrically Erasable Programmable ROM (EEPROM), or flash memory. Volatile memory can include Random Access Memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in a variety of forms such as Static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double Data Rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous Link DRAM (SLDRAM), memory bus direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM), among others.
It will be apparent to those skilled in the art that, for convenience and brevity of description, only the above-described division of the functional units and modules is illustrated, and in practical application, the above-described functional distribution may be performed by different functional units and modules according to needs, i.e. the internal structure of the apparatus is divided into different functional units or modules to perform all or part of the above-described functions.
The above embodiments are only for illustrating the technical solution of the present application, and not for limiting the same; although the application 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 application, and are intended to be included in the scope of the present application.
Claims (10)
1. An energy system for an autonomously reconfigurable airship, comprising:
the photovoltaic array comprises a plurality of photovoltaic modules which are arranged on the surface of the airship in an array manner, and the shape of each photovoltaic module is adapted to the surface of the airship;
the reconstruction calculation module is used for acquiring the flight state of the airship and the irradiation intensity on the photovoltaic array, and calculating the reconstruction serial-parallel structure of the photovoltaic array according to the flight state and the irradiation intensity; the difference value between the total irradiation intensity of the photovoltaic modules in any row and the irradiation intensity of the photovoltaic modules in other rows in the serial-parallel structure after the photovoltaic array is reconstructed is not greater than a preset difference value threshold;
the reconstruction control module is connected with the reconstruction calculation module and is used for generating a reconstruction signal of a series-parallel connection construction circuit according to the reconstruction series-parallel connection structure of the photovoltaic array;
and the series-parallel connection construction circuit is connected with each photovoltaic module in the photovoltaic array and is used for responding to the reconstruction signals to construct a series-parallel connection structure of the photovoltaic modules in the photovoltaic array.
2. The energy system of an autonomously reconfigurable airship of claim 1, wherein the series-parallel connection construction circuit includes a plurality of switching assemblies in one-to-one correspondence with the photovoltaic assemblies, each of the switching assemblies being connected between a photovoltaic assembly and the reconfiguration control module, the series-parallel connection construction circuit controlling a connection relationship of each of the switching assemblies according to the reconfiguration signal.
3. The energy system of an autonomously reconfigurable airship of claim 2, wherein the switch assembly comprises a first switch, a second switch, and a composite switch contact; the first switch is connected with the positive electrode of the photovoltaic module, the second switch is connected with the negative electrode of the photovoltaic module, and the composite switch contact comprises a plurality of positive electrode contacts, a plurality of negative electrode contacts and a common contact; and the first switch and the second switch respectively respond to the connection of the reconstruction signal and different contacts of the compound switch to construct a series-parallel structure after the reconstruction of the photovoltaic component.
4. The energy system of the autonomously reconfigurable airship of claim 3, wherein the number of the composite switch contacts is positively correlated with the number of the photovoltaic modules in a maximum series of photovoltaic module circuits, wherein the number of the composite switch contacts is 2x+1, including X positive contacts, X negative contacts and 1 positive and negative common contacts, and the number of the photovoltaic modules in the maximum series of photovoltaic module circuits is X.
5. The energy system of an autonomously reconfigurable airship of claim 1, wherein the series-parallel connection build circuit is connected to the photovoltaic module through a power output cable.
6. The energy system of an autonomously reconfigurable airship of claim 1, wherein the energy device of the airship further comprises an energy storage battery pack connected to the series-parallel connection build-up circuit, a DC/DC converter connected between the energy storage battery pack and the series-parallel connection build-up circuit.
7. The energy system of an autonomously reconfigurable airship of claim 6, wherein the DC/DC converter is connected to the series-parallel connection build circuit through a power communication composite cable.
8. The energy system of an autonomously reconfigurable airship according to claim 1, wherein the reconfiguration computing module is configured to acquire the solar irradiation intensity and the flight state of the airship at a preset period;
performing difference comparison on the solar irradiation intensity of the current period and the solar irradiation intensity of the previous period, and performing difference comparison on the flight state of the current period and the flight state of the previous period;
if the difference comparison result of the solar irradiation intensity is larger than a preset first threshold value and/or the difference comparison result of the flight state is larger than a second preset threshold value, calculating a reconstruction serial-parallel structure of the photovoltaic module of the photovoltaic array according to the solar irradiation intensity in the current period, and generating a control instruction of a reconstruction control module.
9. The energy system of an autonomously reconfigurable airship of claim 1, wherein the P-V curve of the reconfigured and optimized photovoltaic array exhibits a single MPP point characteristic.
10. An airship, comprising:
an airship body;
the airship body is provided with:
the irradiation intensity acquisition module is used for acquiring the irradiation intensity on the photovoltaic module;
the combined inertial navigation is used for collecting the flight state of the airship;
and, an energy system of an autonomously reconfigurable airship according to any one of claims 1 to 9.
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| CN103064459A (en) * | 2012-12-20 | 2013-04-24 | 浙江工业大学 | Reconfiguration optimization method of photovoltaic cell array completely reconfigurable electrical system |
| KR20170017585A (en) * | 2015-08-07 | 2017-02-15 | 한국과학기술원 | Reconfigurable method of photovoltaic array and vehicular photovoltaic system |
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