Single event latch-up detection for nano-satellite external solar radiation mitigation system (original) (raw)
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Design and Implementation of an Effective Electrical Power System for Nano-Satellite
Design of electrical power system for Nano-satellites is presented. The role of this electrical power system is to provide electrical power for all the subsystems of KufaSat .This was achieved by the use of solar cells when the satellite is in direct sunlight and by two Lithium Polymer batteries when the Sun is eclipsed .The batteries are charged by the solar panels through three battery charge regulators which optimize the solar arrays’ voltages independently for maximum power transfer. Power is then transferred to subsystems through a number of power buses, 3.3V, 5V and unregulated.
Microcontroller-Based Intelligent Power Management System (Ipdms) for Satellite Application
2012
Efficient power distribution management is very crucial for satellites to navigate their orbits and achieve their mission objectives. The Satellite Electrical Power Subsystem (EPS) is responsible for power supply in satellites for housekeeping operations. This research project is aimed at the design of a microcontroller-based Intelligent Power Distribution Management System (IPDMS) for application in the efficient coordination of power savings and distribution to satellite system payloads. In the IPDMS design, 8-bits microcontroller was used to implement system intelligence. In addition, Java Programming Language was used to achieve a simulation model for virtual test for system reliability and efficiency. The IPDMS provided intelligence for real-time power storage. It managed power distribution through load shedding and power-cycling and actuated fault protection mechanism in the events of power emergencies very quickly and autonomously during eclipse and sunlight orbit periods. It...
Modeling and Simulation of Egyptsat-1 Satellite System Powered by Photovoltaic Module
2013
The paper presents a method of simulating photovoltaic module by tacking the manufacturer specified data sheet at standard test condition as inputs. A method for estimating the unknown parameters of the general single diode solar cell model using Newton's raphson method is described. The fourth parameters of the photovoltaic module are calculated with the aim of three remarkable points on the photovoltaic I-V characteristics and make. The developed model allows the predication of photovoltaic module behavior with respect changes on environmental and physical parameters. The main idea of this paper is to make a computer digital model instead of real model for photovoltaic module used in Egyptsat-1 satellite, and explain the relation of as a function of. [
2006
This paper discusses a development software tool for modelling and simulation of satellite electrical power subsystem (SEPSMS) in orbit operation analysis. The development of the components database to facilitate the modelling and simulation of the satellite EPS for remote sensing low earth orbit (LEO) application are introduced and some of them are deduced. In particular, the model of orbit estimation and solar array illumination are introduced, the specific output power of solar array based on GaAs solar cells single junction is presented also. The orbit perturbations and satellite separation from launch vehicle errors are included in the analysis of satellite EPS operation during the lifetime period of satellite. The model of off-nominal operation of the solar array is included in the EPS analysis during the lifetime period. Also the degradation parameters of the different EPS components are considered in the components models. The present work attempts to overcome certain inadequacies of contemporary simulation applications with respect to SEPSMS, by developing mathematical or empirical system modelling schemes for EPS components. These schemes are then integrated within a state-of-the-art simulation environment, so that they can be employed in practice [1]. For the purposes of the present work, it was decided to work with a state-of-the-art simulation program based on MatLab.7 Graphical User Interface (GUI). The EPS system parameters is presented in three figures screen grouped as; window of orbit and solar illumination, orbit shadowing period and local time of descending (LTD) , window of solar array output current, load profile and storage battery capacity all of them as a function of time. The third window shows the satellite bus voltage and static pattern of storage battery temperature. The result of the introduced tool is verified by another one for a similar satellite issued by an experienced agency in this field [2], the convergence was very high.
Przegląd Elektrotechniczny, 2012
Since the advent of the CubeSat nanosatellite standard it has been embraced by many universities as an affordable means of conducting space science, with the backbone of any such mission being the supply of electrical power to the spacecraft's payloads. This paper details the design of a photovoltaic-battery based power supply utilising peak power trackers for solar array regulation and battery charging. Uniquely, the peak power tracking is executed by an active search algorithm, Perturb & Observe, in both analogue and digital form as a measure of redundancy. Streszczenie. W artykule opisano projekt baterii fotowoltaicznych wykorzystujący uklad śledzenia maksymalnej mocy do sterowania procesem wytwarzania energii i ladowania baterii. Wykorzystano algorytm Perturb & Observe. (System fotowoltaicznego zasilania ukladow satelitarnych wykorzystujący uklad śledzenia mocy maksymalnej)
Improving the power bus stability of a nanosatellite
The power bus is responsible for transferring voltages and current to meet various subsystem power requirements. It is the single point for electrical power flow from the generation point to the subsystems. The power distribution bus is connected to four main device made up of the following: • The solar arrays responsible for primary power generation. • The secondary power which is obtained from batteries • Protection devices used for maintaining bus voltage and current within specifications • The loads which represents the entire subsystems. In working toward improving the stability of the bus, we studied and reviewed the current solar cell and battery technologies for implementation, to obtain the required power generated from the arrays and batteries at sun on and eclipse. The power conditioning system provides three voltages on the busses connected to satellite modules. It steps down the unregulated 7.2V to 5V and regulated 3.3V respectively. A simple external filter circuit, combined with dc/dc converters were developed to maintain and eliminate disturbance and restore the system to normal operation. Simulink was used as a simulation tool for to determine and analyze the stability conditions of the system upon implementation of the design.
Simulator Energy Produced by Photovoltaic Panels used in the Validation of Power Balance in Cubesats
2014
The CubeSats are small satellites with cubic shaped structures that are electrically energized only after inserted into orbit operation. Due to this condition it is necessary that the components of the electrical architecture cubesat are properly tested before of the operation in orbit, to highlight the level of reliability suitable for the application in question. In this context, this paper proposes a model to simulate the energy produced by photovoltaic panels in order to make the test charge and discharge batteries that are present in the power distribution system that supplies the electrical and electronic components installed on the cubesat. The validation of the simulation discussed in this work is done by testing the prototype which has been developed for this purpose. The positive results observed in the tests suggest that the simulation is able to reproduce the main conditions of energy production that is performed by the photovoltaic panel’s cubesat in the orbit of operat...
A Low Cost, Efficient Electrical Power System Design for CubeSat
10th International Conference on Recent Advances in Air and Space Technologies (RAST), 2023
This paper discusses the design of an Electrical Power System (EPS) for a 1U CubeSat. A low-cost, lightweight, and highly efficient EPS using commercial off-the-shelf (COTS) components is designed. The EPS comprises of three modules: Power generation, Power storage, and Power distribution. To determine the amount of power CubeSat would receive, various analyses are conducted on eclipse time and inclination. A polar orbit is chosen to minimize eclipse time without expending extra power to maintain the satellite in a retrograde orbit. Polycrystalline silicon solar panels are selected due to their decent efficiency, affordability, and availability. LG MJ1 batteries are chosen for their high specific energy, high maximum continuous discharge, stable end of discharge, among other factors. A detailed power budgeting and cost analysis of the proposed EPS is also conducted. The analysis shows that the chosen batteries can provide 3.60 W of power, sufficient to meet the required power of 3.55 W in the worst-case scenario for the satellite, with an expected total cost of $109.73.
Innovative Electric Power Supply System for Nano-Satellites
2013
This paper discusses modular electric power system (EPS) unit for different size of nano-satellites. Energy harvesting, battery charging and voltage regulation units for different architectures have been analyzed and developed on a single tile. Power generation for nano-satellites is usually distributed over a number of solar panels. Solar panels consist of different number of solar cells connected in various (series, parallel & mixed) configurations may be prone to different types of faults. Simple fault tolerance analysis of different configurations of various numbers of solar cells has been done. Boost power converter required for specific amount of power has been designed and implemented. Normally power conversion, storage and management is concentrated in a single point. This is a typical point of failure. We have developed a modular distributed EPS which consists of a number of small modular power converter, storage and distribution subsystems on single tile for different arch...
Journal of Astronomy and Space Sciences
A satellite power system should generate and supply sufficient electric power to perform the satellite mission successfully during the satellite mission period, and it should be developed to be strong to the failure caused by the severe space environment. A satellite power system must have a high reliability with respect to failure. Since it cannot be repaired after launching, different from a ground system, the failures that may happen in space as well as the effect of the failures on the system should be considered in advance. However, it is difficult to use all the hardware to test the performance of the satellite power system to be developed in order to consider the failure mechanism of the electrical power system. Therefore, it is necessary to develop an accurate model for the main components of a power system and, based on that, to develop an accurate model for the entire power system. Through the power system modeling, the overall effect of failure on the main components of the power system can be considered and the protective design can be devised against the failure. In this study, to analyze the failure mode of the power system and the effects of the failure on the power system, we carried out modeling of the main power system components including the solar array regulator, and constituted the entire power system based on the modeling. Additionally, we investigated the effects of representative failures in the solar array regulator on the power system using the power system model.