Solar Panel Deployment Research Articles

Environmental payback periods of multi-crystalline silicon photovoltaics in the United States – How prioritizing based on environmental impact compares to solar intensity

As global climate change is becoming a more pervasive issue, the environmental impact of electricity production is once again in the spotlight. In the context of global climate change it is critical to focus on shifting towards more sustainable electricity production methods, which meet the electricity demand without contributing significantly to the environmental footprint. Using photovoltaic (PV) systems as an alternative to conventional grid electricity is one potential option, which is beneficial as it is less resource intensive during the use phase than conventional electricity sources. However, environmental impacts are still generated during the raw materials and manufacturing life cycle phases of the PV. Life-cycle assessment (LCA) and environmental payback period (EPBP) were used to quantify the time it takes to recoup the environmental impacts due to production of solar PV compared to the environmental impacts of the current electricity grid. An EPBP analysis of all 50 states in the United States was performed to evaluate changes due to differences in solar potential, electricity mix, and impact category. The goal of this paper is to compare how the deployment of solar panels would change if environmental payback prioritization was considered compared to simply considering solar intensity.

Study of the specific energy of universal electrode materials for hybrid ultra-high-volume capacitor systems

The article discusses specific energy of universal electrode materials based on Busofit for ultra-high-volume capacitor systems and hybrid ultra-high-volume capacitor systems based on LiCoO2 and MnO2, which can be used in as sources of pulsed power in satellite solar panel deployment systems and emergency door opening systems and emergency platforms in airliners, including the Airbus 380 jumbo jet. The electroimpulse metallization of electrode materials and dependence of specific energy on weight of LiCoO2 and MnO2 was described. It was shown that hybrid ultra-high-volume capacitor systems increase its energy intensity up to 5,5 times compared with UCS.

Identification of chaotic phenomena in a flexible deployable solar panel with multiple clearances

Deployable solar panels are widely used in spacecraft, and the dynamic characteristics of the deployment process directly affect the accuracy, stability, and reliability of the deployment. The flexibility and hinge clearance of a solar panel are important factors affecting the dynamic characteristics of the deployment system. The finite element method (FEM) was used to deal with the deformations of the solar panel. A dynamic model of the deployment process of a flexible solar panel with multiple clearances was established by combining the Lagrange equation with the FEM. The dynamic characteristics of solar panel deployment with multiple clearances and flexibility coupling were analyzed through a numerical solution, and the chaotic phenomena caused by clearances were identified. The results show that reasonably matching the clearance and flexibility of the system structure could quickly stabilize the collision force, improve the system life, and effectively improve the stability of the solar panel deployment process. Chaotic phenomena could be induced by the deployment velocity in a certain range, and the boundary value of the range changed with different clearance radii. The velocity variation law inducing chaotic phenomena also varied with the radius of clearance. This research provides important guidance for the optimum design and manufacturing of deployable solar panel mechanisms.

Interactive design and advanced manufacturing of double solar panel deployment mechanism for CubeSat, part 1: electronics design

Recently, CubeSats have been in the first instance of research with fast time development and low cost manufacturing. Moreover, the capability of CubeSats increases and more complex design are planned. Therefore, an Interactive Virtual Manufactory includes: design, assembly, integration and prototyping is required to engineering objectives and increase in performance and quality. However, some limitations concerning data storage, mostly is the available on-board power, therefore a strong life-time. In this paper, the part one of design and realization of a novel deployable solar panel mechanism for CubeSats platforms will be presented with height performances. In addition, a measurement benchmark has been designed to investigate the micro-steeper motor during the deployment. Furthermore, in the development, an interactive design methodology has been implemented, thus, time, cost and risk have reduced. In particular, this work intends to explore the interaction between structure and control board discipline on CubeSats, a numerical analysis has been achieved, in order to build, manufacture and qualify the product developed. The results are presented as well; a prototype of the system has been realized for a 1U Cubesat, consisting of two deployable solar panel systems, the preliminary experimental results are very satisfactory, moreover, an excellent robustness and effectiveness has been achieved in micro-stepper motor control, the preliminary test results suggest that the proposed system will be able to meet the mission requirements. Finally, better performance with our proposed methodology has been achieved through integrate an interactive virtual prototyping in product design.

PRELIMINARY THERMAL CONTROL DESIGN ANALYSIS OF LAPAN SAR-MICROSATELLITE DEPLOYABLE SOLAR ARRAY PANEL USING ONE NODAL METHODE

LAPAN SAR-Microsatellite is the first LAPAN micro satellite being developed and planned to carry a Synthetic Aperture Radar (SAR) payload. Different from optical satellites that have been developed, LAPAN SAR-Microsatellite requires a lot more power. Solar array panels are needed to generate solar radiation into electrical energy which is used by all of subsystem satellite as energy to turn on and turn off all of components. More larger the area of solar array panel, more greater to the energy obtanied. Therefore, the needed of deployable solar array panel is a must caused by the dimension of the main body structur (MBS) are not large enough. Solar cells will experience a decrease in efficiency if they experience excessive heat. If there is a decrease in efficiency in the solar cell, it will have an impact on the decrease in power produced. The purpose of this study is to conduct thermal design on solar panels to maintain temperature according to their working temperature. Calculations are carried out on the temperature of solar array panel with various optical properties in the upper and lower panel that best which will be use using one nodal analysis methode According to the calculation result from all of the designs passive thermal control system on this study show that Design-5 is the best thermal control design which can be used for LAPAN SAR-microsatellite deployable solar array panel which α=0.24 at the top and ε=0.9 at the bottom surface of solar array panel.

Stochastic parallel extreme artificial hydrocarbon networks: An implementation for fast and robust supervised machine learning in high-dimensional data

Artificial hydrocarbon networks (AHN) – a supervised learning method inspired on organic chemical structures and mechanisms – have shown improvements in predictive power and interpretability in comparison with other well-known machine learning models. However, AHN are very time-consuming that are not able to deal with large data until now. In this paper, we introduce the stochastic parallel extreme artificial hydrocarbon networks (SPE-AHN), an algorithm for fast and robust training of supervised AHN models in high-dimensional data. This training method comprises a population-based meta-heuristic optimization with defined individual encoding and objective function related to the AHN-model, an implementation in parallel-computing, and a stochastic learning approach for consuming large data. We conducted three experiments with synthetic and real data sets to validate the training execution time and performance of the proposed algorithm. Experimental results demonstrated that the proposed SPE-AHN outperforms the original-AHN method, increasing the speed of training more than 10,000x times in the worst case scenario. Additionally, we present two case studies in real data sets for solar-panel deployment prediction (regression problem), and human falls and daily activities classification in healthcare monitoring systems (classification problem). These case studies showed that SPE-AHN improves the state-of-the-art machine learning models in both engineering problems. We anticipate our new training algorithm to be useful in many applications of AHN like robotics, finance, medical engineering, aerospace, and others, in which large amounts of data (e.g. big data) is essential.

Integration of Sun PV Electricity in Centralized Heating Systems

Abstract During the experimental research, an algorithm was developed as a guide for the introduction of solar panels (PV) in centralized heat supply (CHS) companies and a SWOT analysis of the developed algorithm action blocks was performed. SWOT analysis was carried out for a project implemented in practise and, as a result of which the centralized heat supply system uses solar power with a total capacity of 30 kW. We found that in Latvia, the areas that are suitable for solar panels are several times higher than those required by the systems. Main tasks of the work: to analyse and study available literature and information on solar PV integration into CHS; analyse available solar PV power generation equipment and technologies; develop a roadmap for easy and understandable deployment of solar panels in the company.

System Level Modelling of Batteries in Spacecraft Power System in Multiple Source and Multiple Load Configuration

AbstractIn present day spacecraft applications, power system uses solar arrays as the primary source of power generation and rechargeable Lithium ion batteries as secondary source of power. In normal orbits, during sunlit period, solar arrays support the power requirement from all the subsystems and payloads along with the charge power requirement of batteries. During eclipse period, entire load should be supported by batteries. In addition to the eclipse support, starting from launch pad to till deployment of solar panels, all loads will be on batteries. Contingency loads should also be taken care by batteries. So, battery sizing is very critical part in designing the power system of spacecraft. In multiple source and multiple load configuration where two or more batteries are connected to same Spacecraft power bus, current sharing between the batteries is expected, which needs to be considered for optimized sizing and designing of batteries. The scenario becomes complex with additional constraints namely some loads can come on one battery and not on others or vice versa. Even in a configuration where potential difference exists between batteries, current sharing will start as soon as this difference vanishes. A system level simulation model is developed, using network equations, to analyze in‐circuit performance of batteries in multiple source and multiple load power system. The simulation model uses actual current sharing and predicts State of Charge (SOC) of each battery from which Open Circuit Voltage (OCV) is derived. This OCV of batteries is used periodically for finding actual current sharing which runs in a loop for analyzing battery performance in multisource system. Currently a configuration in which two batteries are connected to two buses, which are paralleled and having different loads, is simulated. Optimized battery sizing, actual current sharing and SOC of each battery are derived. This model can also be extended to a system where more than two batteries are present. Two different approaches are used for simulation and results are compared. The developed generic model has features to use in multiple battery configuration.

Eu:CROPIS AIV Program: Challenges and Solutions for a Spin-Stabilized Satellite Containing Biology

Eu:CROPIS is DLR’s first mission of the Compact Satellite Program. Its primary payload focuses on the research of closed-loop biological, regenerative life support systems, in a simulated gravitational environment of the Moon and Mars over months at a time. This is achieved by rotation of the satellite around its central body axis, using only magnetic torquers as actuators. A secondary payload (“PowerCells”) by the NASA Ames Research Center also utilizes the artificial gravity to conduct growth experiments on genetically modified organisms (GMOs). These payloads and the system design imposed constraints which affected the Assembly Integration and Verification (AIV) program in various ways and created challenges for the relatively small team to find solutions for. The paper to be presented will address the different aspects of the AIV program. This includes the verification of different critical components like the newly developed CFRP pressure vessel containing the primary payload and the Micrometeoroid and Debris Protection Shield, which protects it. Both items went through rigorous testing, including high-velocity impact tests, to ensure their reliability in orbit. Various other aspects concerning the biology had to be taken into account during AIV campaigns: due to the presence of degradable components within the primary payload, a late access capability had to be implemented in order to exchange biology as well as chemistry in cases of launch delays. To allow these operations as close as six months prior to launch, a highly flexible and streamlined acceptance test campaign was developed. A major impact on test planning and logistics was the fact that the secondary payload “PowerCells” contains GMOs, which European and German regulations restrict to be handled exclusively in especially certified laboratories (biosafety level 1 (BSL-1)). Thus, the use of external test facilities for the flight model campaign was not feasible as no European test center is certified to BSL-1. In consequence, the clean room facilities of the DLR Institute of Space Systems had to be certified to BSL-1 and new test infrastructure had to be procured in a short time frame to cover for acceptance testing. The design of the satellite and nature of the attitude control subsystem required limits on the magnetic momentum of the system and every unit it contains. A test flow incorporating the magnetic property measurement of each unit and a final system-level test in an external facility had to be devised, which enabled budgeting and projection of expected measurement results on the system level. Furthermore, the moments of inertia had to be measured precisely in order to have a stable spinning axis enabling a stable gravity simulation. Finally, the functionality had to be verified for each unit and for the system which required that several small test campaigns had to be conducted, like a solar panel deployment test and extensive software testing. A tight link to the operations teams of the German Space Operations and Control Center during such tests and beyond finally ensures the operability of the overall system in the operational phase.

Parameters optimization design of tape spring considering fatigue performance

As a crucial part of micro-satellite, the spatial deployable mechanism has the direct effects on satellite performance and success or failure of flight mission. With requirements of lightless and low cost for satellite, the tape spring hinges are widely used for their simple structural form, high reliability of deployment, high-driving performance and accurate positioning in deployable mechanism. Strain energy stored in the folding process of tape spring hinge is transformed into kinetic energy to achieve the deployment of solar panels. When in full deployment, the tape spring hinge can realize self-locking based on its critical moment. Tape spring is the crucial component of a novel space deployable structure that applied to solar panels. Its full deployment determines the normal function of satellite in space. Mechanical properties, steady-state moment and fatigue life, are observed in folding and deploying processes, which are affected by geometric parameters. Influences of thickness, subtended angle, radius and length on the fatigue life of tape spring are carried out to through numerical simulations so as to ensure a multi folding and deploying cycles for tape spring hinge. Results show that thickness has the greatest influence on the fatigue life, subtended angle and radius are second, and the influence of length on fatigue life is relatively small. On the basis, the optimal model is established based on response surface methodology with the thickness and radius as design variables, steady moment as constraint, and fatigue life as optimization objective. By using genetic algorithm to solve the model, optimal design is obtained within the constraint, and then the optimal design is remodeled and simulated, and the obtained results indicate the accuracy of the optimal design. This research could be a reference for the stability design of space deployable structures.

Development of Pogo Pin-Based Holding and Release Mechanism for Deployable Solar Panel of CubeSat

CubeSats are revolutionary to the space industry and are transforming space exploration which enables the next generation of scientists and engineers to complete all phases of space missions. Deployable solar panels have been widely used for the generation of enough power in CubeSats due to their limited volume area for solar cell integration. In general, the cable cutting release mechanism have been used in 1U-3U small satellites because of its simplicity and low cost. However, this mechanism has a low constraint force and is unable to apply constraints along the in-plane and out-of-plane directions. In this study, for the improvement of the conventional cable cutting mechanism, a spring-loaded pogo pin-based nichrome burn wire holding and release mechanism (HRM) was proposed and fabricated. The pogo pin constitutes an immensely attractive function for the holding and release mechanism of solar panels because it works as an electrical interface to provide power, a separation spring to initiate the reaction force to deploy the panels, and a status switch to determine deployments. In addition, the proposed mechanism guarantees the loading capability along the in-plane and out-of-plane directions of solar panels, the synchronous release of multiple panels, and a handling simplicity that differentiates it from the conventional mechanism. The design feasibility, structural safety, and reliability of the mechanism were verified through functionality tests and launch and on-orbit environmental tests. The proposed pogo pin-based holding and release mechanism would be equally applicable for other CubeSat deployable appendages.

Comparison of Solar Radiation Torque and Power Generation of Deployable Solar Panel Configurations on Nanosatellites

Nanosatellites, like CubeSat, have begun completing advanced missions that require high power that can be obtained using deployable solar panels. However, a larger solar array area facing the Sun increases the solar radiation torque on the satellite. In this study, we investigated solar radiation torque characteristics resulting from the increased area of solar panels on board the CubeSats. Three common deployable solar panel configurations that are commercially available were introduced and their reference missions were established for the purpose of comparison. The software algorithms used to simulate a variety of orbit scenarios are described in detail and some concerns are highlighted based on the results obtained. The solar power generation of the respective configurations is provided. The findings are useful for nanosatellite developers in predicting the characteristics of solar radiation torques and solar power generation that will be encountered when using various deployable solar panels, thus helping with the selection of a suitable configuration for their design.

Development of 6 U CubeSat’s Deployable Solar Panel with Burn Wire Triggering Holding and Release Mechanism

In the present work, a deployable solar panel based on a burn wire triggering holding and release mechanism was developed for use of 6 U CubeSat. The holding and release mechanism was designed based on a nichrome burn wire cutting method widely used for CubeSat applications. However, it provides a high loading capability, reliable wire cutting, multiplane constraints, and handling simplicity during the tightening process of wire. A demonstration model of a printed circuit board-based solar panel stiffened by a high-pressure fiberglass-laminated G10 material was fabricated and tested to validate the effectiveness of the design and functionality of the mechanism under various test conditions. The structural safety of the solar panel combined with the mechanism in a launch vibration environment was verified through sine and random vibration tests at qualification level.

FINITE ELEMENT MODELING OF LAPAN-A5/CHIBASAT DEPLOYABLE SOLAR PANEL COMPOSITE PLATE

LAPAN-A5/ChibaSat, that will carry synthetic aperture radar payload, requires a lot more power generation capacity, compared to its predecessor. Therefore, its solar panel will be deployed in orbit to ensure maximum sun exposure. Since the deployable system requires solar panel plate that lightweight and strong, honeycomb composite material is selected. The selection of such material requires special treatment in the satellite structural stiffness calculation. The objective of the research is to find simple stiffness model of the plate, so that later it can be integrated with the total satellite structural model and used by launch authority in its total vehicle modal analysis. The modeling used finite element software, and the simplified honeycomb model is validated using standar plate stiffnes problem. After model validation, the boundary condition as in the LAPAN-A5/ChibaSat deployable system is imposed. The result shows that the stiffness of the deployable solar panel plate has met the launch requirement of PSLV’s auxiliary payload. Therefore, the design mode can be used in the development of LAPAN-A5/ChibaSat.

Дискретные геометрические модели оценки степени затененности в гелиоэнергетике

Geometric simulation and its software for estimating the efficiency of deployment of solar panels on spacecraft and solar concentrators on the ground are considered in this work. Both the physical and mathematical set up of the problem for estimating the energy efficiency of solar panels, taking into account their shading both by each other and by other elements of a space station has been described in this paper. It has been shown that the known methods for mechanization and automation of such calculations are focused on objects of relatively simple geometric shapes (such as buildings), and are inefficient for objects of complex and diverse geometric shape, characteristic both for spacecraft themselves and their solar panels. Therefore, to solve this problem, a receptor (voxel) geometric model digitizing the computational space has been chosen. The receptor model’s uniqueness is that comparing the values of receptor codes allows easy determine the intersection of objects. Has been described a developed receptor geometric model for estimating the effective area of solar panels, taking into account their shading when the object (for example, a spacecraft) is illuminated by a flow of solar energy from a given direction. The essential difference between the developed receptor geometric model and the classical one is that the former is multiform, i.e. uses not the 2-digit code (0 and 1), but the 4-digit one (0, 1, 2 and 3). Has been demonstrated a software implementation of the described geometric model in C#, and a graphical shell developed for this problem, allowing see the obtained results’ numerical values. Have been provided examples of its implementation in solving of practical problems. The results of verification for the described receptor geometric model have been demonstrated. All this allows speak about efficiency of using receptor geometric models both in singular computation calculations and for creating the appropriate algorithmic, mathematical support and software for the corresponding CAD systems.

Thermally induced dynamics of deployable solar panels of nanosatellite

PurposeThis study aims to predict the types of thermally induced dynamics (TID) that can occur on deployable solar panels of a small form factor satellite, CubeSat which flies in low Earth orbit (LEO). The TID effect on the CubeSat body is examined.Design/methodology/approachA 3U CubeSat with four short-edge deployable solar panels is considered. Time historic temperature of the solar panels throughout the orbit is obtained using a thermal analysis software. The results are used in numerical simulation to find the structural response of the solar panel. Subsequently, the effect of solar panel motion on pointing the direction of the satellite is examined using inertia relief method.FindingsThe thermal snap motion could occur during eclipse transitions due to rapid temperature changes in solar panels’ cross-sections. In the case of asymmetric solar panel configuration, noticeable displacement in the pointing direction can be observed during the eclipse transitions.Research limitations/implicationsThis work only examines an LEO mission where the solar cells of the solar panels point to the Sun throughout the daylight period and point to the Earth while in shadow. Simplification is made to the CubeSat structure and some parameters in the space environment.Practical implicationsThe results from this work reveal several practical applications worthy of simplifying the study of TID on satellite appendages.Originality/valueThis work presents a computational method that fully uses finite element software to analyze TID phenomenon that can occur in LEO on a CubeSat which has commonly used deployable solar panels structure.

Cylindrical lens array concentrator with a nanonipple-array antireflective surface for improving the performances of solar cells

Nanoscale nipple array (NNA) structures have always been used in solar cells for the purpose of antireflection. However, most NNAs are fabricated on the planar surface of a film. Here, we report NNA structures are fabricated on the curved surface of a millimeter-scale cylindrical lens array concentrator (MCLAC) using the simple soft imprint method. The MCLAC concentrates all incoming sunlight to silicon surface of solar cells to overcome the reflection loss from finger electrodes. The NNAs on the surface of MCLAC can reduce the reflection loss at the lens–air interface and enhance the hydrophobicity of solar cell. Through applying the polymer multiscale AR coating consisting of NNAs and MCLAC(NNA–MCLAC) to commercial polycrystallinesilicon solar cells and optimizing the supporting layer height between MCLAC and silicon film, the power conversion efficiency (PCE) has been successfully improved from 18.60% to 19.52% under normal incidence, increased by 4.95%. Importantly, compared with the solar cell with the no structure planar coating, the relative PCE improvement ratio of the solar cell with the multiscale NNA–MCLACAR coating increases from ca. 5% up to ca. 32% when the incident angle increases from 0°to 60°. These remarkable improvements are of significance for practical deployment of commercial solar cells panels without a costly solar tracking system.

A Photovoltaic Model Based Method to Monitor Solar Array Degradation On-Board a Microsatellite

The lifespan of a microsatellite depends on the adequate power obtained from its solar array. Hence, it is important to monitor the degradation of the solar array in-orbit as uncertain activities of the Sun would change the space radiation environment. To monitor the degradation, a degradation model together with a space environmental model is typically used. In this paper, an alternate method to monitor the solar array degradation of a satellite using a photovoltaic model as a reference is proposed. The proposed method can be used on any satellite with its voltage, current, incidence angle, and temperature of the solar array known. From the results, the proposed method shows that the solar array of X-SAT has a higher rate of degradation from January 2012 to March 2012 due to extreme space weather event. Moreover, the degradation for the Y+ and Y– deployable solar panels over the first three years is 28.40% and 41.52%, respectively.

레이저 트래커를 이용한 태양전지판 전개시험장치의 중력축 정렬

In this paper, a gravity-axis alignment method is proposed for the deployment test whose equipment consists of a deployable solar panel, tape spring hinges, a deployment fixture, and a rotational structure with a zero-G device. If the deployment test equipment is not precisely aligned to the gravity axis, disturbances induced by its misalignment give critical impacts to the onground deployment test capability. In order to align the test equipment with the gravity axis, the exact gravity axis is identified prior to the alignment activity. We propose a method to align the laser tracker precisely to the gravity axis using an inclination sensor and achieve the alignment accuracy of laser tracker with 10SUP-4/SUP orders of magnitude in degree. If the exact gravity axis is acquired with the laser tracker, the deployment test equipment is aligned with the laser tracker. The proposed equipment has four compartments which are aligned and compensated with respect to the gravity axis; a deployment fixture, a rotation axis module, a horizontal shaft module, and the rotation axis of the solar panel. For each item, a new method for aligning with the gravity axis is proposed in this study. As a result, it is verified through test activities that the deployment test equipment is aligned with an accuracy with 10-3 orders of magnitude in degree.

SOLAR ENERGY PRODUCTION: SPECIfICS Of ITS TERRITORIAL STRUCTURE AND MODERN GEOGRAPHICAL TRENDS

The study deals with the socio-economic geographical analysis of the solar energy production — one of the most rapidly developing industries of the world energy complex. The aim of the study is to identify and explain main features of the territorial structure of solar energy production and assess its role and place in the world. The paper also investigates the factors that affect the development of solar energy production itself as well as the deployment of individual solar panels or solar power stations. The study carried out is based on the review of datasets and official documents which enable to draw a conclusion that the result of an intensive development of solar energy production is its dynamic spatial expansion visible in the emergence of new poles of growth which largely changes the territorial structure of the industry, transforming it from a monocentric to polycentric.