Small Satellite Development

Small Satellites are establishing themselves as important tools for exploring our solar system. Developments in micro-electronics have enabled small and low-cost deep space probes to complement conventional space platforms in long-duration deep space missions. The paper presents a baseline design of an attitude control system for a spacecraft performing a Near Earth Object (NEO) fly-by mission. Following the autonomous escape and cruise phases, the NEO encounter phase is the most critical mission phase with the attitude control performed by a cluster of small Control Moment Gyros (CMG’s). The satellite needs to be rotated relatively fast to keep the NEO within its field of view for the imaging of the NEO. Simulations demonstrate the practicality and versatility on the use of CMGs for low-cost NEO deep space missions.

Indonesian satellite operations are mainly known for the operation of geostationary orbit (GSO) satellites for telecommunication missions. In the last decade, however, the activities of non-GSO satellites in Indonesia are significantly increasing. Therefore, the objectives of this research are to find out the cause of the growth and to predict the future operation of non-GSO satellites in Indonesia. For such purpose, review on the operation of non-GSO satellites in the past and now was done. Analysis on the characteristics of their missions, owners/operators, and technical characteristics of the satellites were done. Literature studies on the global trends and their defining strategic environments were also done to complete the insight. The study shows that increase in the use of non-GSO satellites is caused by the growth in remote sensing application, M2M application, and development of LAPAN's satellites. In the future, the growth of non-GSO remote sensing satellite is predicted to be caused by the same reason. The increase in the use of non-GSO telecommunication satellites, however, will be affected more by the new global trend. The increase in non-GSO remote sensing satellites does not affect significantly on the needs of frequency and ground stations. The increase in the non-GSO telecommunication satellites, however, needs significant additional frequency allocations and ground stations.

Abstract: In Lake Nabugabo, Uganda, a small satellite of the equatorial Lake Victoria, approximately 50% of the indigenous fish species disappeared from the open waters subsequent to establishment of the introduced predatory Nile perch (   Lates niloticus ). However, several of these species persisted in wetland refugia. Over the past decade, Nile perch in Lake Nabugabo have been intensively fished. Herein we report a resurgence of some indigenous species in open waters. In a multiyear study, we used annual transects in inshore and offshore waters of exposed ( no wetland ) and wetland habitats to document the pattern of resurgence. In 1995, haplochromine cichlids were largely confined to inshore areas, particularly wetland ecotones, and were rare in Nile perch stomachs, as were most other indigenous species. By 2000 haplochromine cichlids were abundant in inshore and offshore areas of both exposed and wetland transects. Several indigenous noncichlids also reappeared in the main lake, including three of the four original mormyrid species. Between 1995 and 1999, there was a dramatic increase in the proportion of haplochromines in the diet of Nile perch. When haplochromines were rare ( 1995 ), Nile perch switched from an invertebrate-dominated diet to piscivory at a large size ( 30 cm total length ). In 2000, however, Nile perch were strongly piscivorous by 5–10 cm total length. The pattern of faunal loss and recovery in Lake Nabugabo demonstrates the importance of refugia in providing the seeds of resurgence and provides a model with which to understand some changes in Lake Victoria.Resumen: En el Lago Nabugabo, Uganda, un pequeño satélite del lago ecuatorial Victoria, el 50% de las especies indígenas de peces, aproximadamente, desaparecieron de aguas abiertas después del establecimiento de la perca del Nilo (   Lates niloticus ); una especie depredadora introducida. Sin embargo, varias de estas especies persistieron en refugios de humedales. En el transcurso de la última década la perca del Nilo en el lago Nabugabo ha sido pescada intensivamente. En este documento presentamos información sobre el resurgimiento de algunas especies indígenas en aguas abiertas. En un estudio, a lo largo de varios años, usamos transectos anuales en aguas cercanas a la orilla y en aguas abiertas de hábitats expuestos (no humedales) y hábitats de humedal para documentar el patrón de resurgimiento. En 1995, los cíclidos haplocróminos fueron en su mayoría confinados a las áreas cercanas a las orillas, especialmente ecotonos de humedal, y fueron raros en los estómagos de perca del Nilo, así como lo eran la mayoría de las otras especies nativas. Para el año 2000 los cíclidos haplocróminos fueron abundantes tanto en las áreas cercanas a las orillas como en aguas abiertas de transectos expuestos y humedales. Muchas especies no-cíclidos también reaparecieron en el lago principal, incluyendo tres de las cuatro especies de mormíridos. Entre 1995 y 1999, hubo un dramático aumento en la proporción de haplocróminos en la dieta de la perca del Nilo. Cuando los haplocróminos fueron raros ( 1995 ), la perca del Nilo cambió de una dieta dominada por invertebrados a una dieta fuertemente piscívora a un tamaño grande ( 30 cm de longitud total ). Sin embargo, en el año 2000, la perca del Nilo fue fuertemente piscívora entre los 5 y 10 cm de longitud total. El patrón de pérdida de fauna y recuperación del lago Nabugabo demuestra la importancia de refugios para proveer las semillas del resurgimiento y provee un modelo para entender algunos cambios en el Lago Victoria.Resumen: En el Lago Nabugabo, Uganda, un pequeño satélite del lago ecuatorial Victoria, el 50% de las especies indígenas de peces, aproximadamente, desaparecieron de aguas abiertas después del establecimiento de la perca del Nilo (   Lates niloticus ); una especie depredadora introducida. Sin embargo, varias de estas especies persistieron en refugios de humedales. En el transcurso de la última década la perca del Nilo en el lago Nabugabo ha sido pescada intensivamente. En este documento presentamos información sobre el resurgimiento de algunas especies indígenas en aguas abiertas. En un estudio, a lo largo de varios años, usamos transectos anuales en aguas cercanas a la orilla y en aguas abiertas de hábitats expuestos (no humedales) y hábitats de humedal para documentar el patrón de resurgimiento. En 1995, los cíclidos haplocróminos fueron en su mayoría confinados a las áreas cercanas a las orillas, especialmente ecotonos de humedal, y fueron raros en los estómagos de perca del Nilo, así como lo eran la mayoría de las otras especies nativas. Para el año 2000 los cíclidos haplocróminos fueron abundantes tanto en las áreas cercanas a las orillas como en aguas abiertas de transectos expuestos y humedales. Muchas especies no-cíclidos también reaparecieron en el lago principal, incluyendo tres de las cuatro especies de mormíridos. Entre 1995 y 1999, hubo un dramático aumento en la proporción de haplocróminos en la dieta de la perca del Nilo. Cuando los haplocróminos fueron raros ( 1995 ), la perca del Nilo cambió de una dieta dominada por invertebrados a una dieta fuertemente piscívora a un tamaño grande ( 30 cm de longitud total ). Sin embargo, en el año 2000, la perca del Nilo fue fuertemente piscívora entre los 5 y 10 cm de longitud total. El patrón de pérdida de fauna y recuperación del lago Nabugabo demuestra la importancia de refugios para proveer las semillas del resurgimiento y provee un modelo para entender algunos cambios en el Lago Victoria.

This technical report update presents use case of CCSDS DVB-S2 for space telemetry. The DVB-S2 space telemetry blue book has been issue in 2013 by CCSDS. The following use cases are presented in the slides of this report :

- CNES DVB-S2 X-band use case for post-Pleiade

- CNES/ESA X-band telemetry for cubesats

- ESA/DGA ( with CNES support ) DVB-S2 coding for ARTEMIS – LOLA optical telemetry links

- Exemple of NASA’s future work on DVB-S2 Ka band space telemetry

- TDRS – ISS DVB-S2 Ka band coms

- NASA DVB-S2 modem test with HPA for telemetry

- DVB-S2 : Option for TDRS-Cubsat links using for instance VCM or ACM, HOM, Ka-band :

- DVB-S2 telemetry studied in China among other solutions

- Miniature DVB-S2 Ka-band telemetry transmitter Development activity for NASA-AMES center

- NASA LRCD DVB-S2 codes

- DVB-S2 LEO to GEO RF Cross Links

- Use of DVB-S2 telemetry by Aerospace corp

- Ka band for Cubesat with DVB-S2, exemple of DVB-S2 image telemetry for cubesat in Ka band

- NASA SBIR/STTR Technologies : DVB-S2 LEO-LEO Intersatellite links in Ka band

- DVB-S2 TM studied for cubesats for VHF links

- DVB-S2 Telemetry on DOVE-1 nanosatellite

- Constellation of more than 100 LEO nanosats with X-band DVB-S2 ACM telemetry : Flock

- DVB-S2 Telemetry on 6U-Cubsats : Cranfield University

- Pre-project use case DVB-S2 X-band telemetry

- High Efficiency transmitter for nanosatellite - master thesis - use of DVB-S2 - TU Delft & ISIS

- DVB-S2 Telemetry use case on GEOS-R (NOAA - NASA)

- Antartic Broadband nanosat DVB-S2 (Australia Space Research Program)

- EUMETSAT DVB-S2 use case to send meteo images to end users

- Use of DVB-S2 in Asia to send meteo and earth observation images to end users

- GEO-KOMPSAT-2 (Geostationary - Korea Multi-Purpose Satellite-2) Program / Cheollian-2 / GK-2

- Outernet cubesat LEO DTE data casting

- Exemple of Space Agency space telemetry ground network compatible with CCSDS DVB-S2 (NASA NEN and SN)

- Two Exemples of commercial space telemetry ground network compatible with DVB-S2

- Presentation of DVB-S2 eXtension (DVB-S2x)

- Technical possibility of reactive TT&C Ka band LEO terminal using a DVB-S2 variant via Inmarsat 5

As shown by the slides, numerous projects have already adopted or earmarked DVB-S2 for their near earth space telemetry, for a wide variety of scenarii ( LEO DTE, LEO-GEO ISLs, LEO-LEO ISLs, … ). Significant current and future use of the DVB-S2 CCSDS standard (CCSDS 131.3-B-1) for telemetry is a fact. CCSDS DVB-S2 telemetry is used in X band, Ka band and optical band, and also in VHF, UHF,  L and S band. Several space agencies are significant DVB-S2 telemetry users, and other earth observation operators as well

Resistojets operating at low power (less than lOO W) and using liquid propellants have re-emerged as attractive propulsion options for orbit-raising small satellites deployed at Space Shuttle altitudes (approx. 2OO km). Compared to low power pulsed plasma thrusters (PPT), the resistojet produces two orders of magnitude more thrust (approximately 1.4 mN compared to 140 mN) which is required to overcome drag at solar maximum. The wet mass of both systems is approximately equal although the propellant volume for the PPT is significantly lower since it is stored in solid form. The major disadvantage of the resistojet propulsion system compared to the PPT, is in the complexity added from the propellant tanks. Shuttle integration concerns for the solid Teflon (trademark) propellant of the PPT are minimal or non-existent. Although non-toxic, the water or nitrous oxide propellant of the resistojet requires pressurized tanks and valves which increase safety requirements. To investigate the usefulness of the resistojet for small satellite applications, a series of performance tests have been completed at the AFRL Electric Propulsion Laboratory using the JPL inverted pendulum thrust stand. The tests were conducted for two types of resistojet thrusters developed at the University of Surrey which utilize a packed bed of SiC particles for the heat exchanger. Performance testing eas accomplished at power levels from 0-600 W for five propellants: water, nitrous oxide, water/ methanol, nitrogen, and helium. Two endurance tests were conducted to determine possible failure modes. Performance characterization and thermal models were developed for future design applications of these thrusters. Future USAF and Surrey Satellite Technology, Ltd. (SSTL) missions using these resistojets are also discussed.

In this article mathematical and computer models of sun sensor and magnetic sensor are considered that can be used for determination of small satellite attitude. In particular, the mathematical models of slit sun sensor and flux-gate magnetic sensor are given.

A conquista do espaço sideral esteve ligada pelas últimas décadas ao emprego de máquinas custosas e pesadas. A despeito do fato desta área não ter donos, todavia, o número de atores capazes de efetivamente se lançarem a uma empreitada dessa natureza era de apenas alguns poucos. A crescente dependência da humanidade em relação à tecnologia espacial fez com que cada vez mais se buscassem alternativas que permitissem facilitar a exploração do espaço em um contexto de congestionamento das órbitas mais baixas e orçamentos em declínio no pós Guerra Fria. Desta forma, projetos de satélites menores, até então negligenciados, voltaram a chamar a atenção de países e agências espaciais ao redor do globo. Com o advento do modelo cúbico de produção satelital tinha-se um catalisador perfeito para potencializar o uso desses artefatos em missões até então reservadas para seus irmãos de maiores proporções. O reaparecimento de pequenos satélites em novas bases técnicas trouxe questões interessantes à tona, pois permitiu que países marginalizados da arena espacial, ou com dificuldades para nela se afirmarem, pudessem desenvolver e lançar os seus próprios experimentos, provendo-lhes maior autonomia tecnológica. O Brasil se insere nesse quadro. Podem os cubesats ajudar países que, a exemplo do nosso, possuem programas espaciais sitiados por dificuldades financeiras e organizacionais? Quais as mudanças estruturais que esses objetos são capazes de suscitar no seio da indústria espacial que podem vir a ser benéficas para nações em desenvolvimento? Como se inserem no quadro maior de um programa espacial ambicioso que almeja um dia competir com aqueles já estabelecidos? Existe alguma política, no que tange ao Brasil, que visa tornar perene a sua construção? Estas são questões às quais este trabalho irá se dedicar no intuito de compreender se o que temos em mãos é uma tecnologia niveladora ou se os pequenos satélites, apesar do efeito positivo testemunhado, constituem apenas mais um elemento dentro de uma intricada trama de atores e tecnologias que necessitam de manejo adequado para surtirem efeito.

Space missions in the past were focused on traditional large costly satellites, but are now transitioning to smaller satellites. These satellites include nano-satellites, which is the object of this thesis, becoming one of the most exciting, diverse and fast paced satellites of today. In this study, CubeSats were investigated, focusing on double unit and triple unit CubeSats and deployment effects on CubeSat systems. The deployment effects on CubeSats depend on numerous uncertainties. However, with assumptions for some parameters, analyses can give approximate results. There are also some uncertainties for orbit perturbations such as atmospheric drag, earth gravity and solar radiation pressure which were briefly clarified. The objectives of this thesis are minimizing the risk of collision between CubeSats and deployer and gaining knowledge to optimize the lifetime of CubeSats. To accomplish these objectives specifications of these CubeSats were given and orbital elements were explained. Moreover, each scenario for the cases described reference CubeSats and simulation parameters are briefly explained. Afterwards, with the assumed parameters, some simulations performed. There are two main parts for simulations which are deployment effects to lifetime of CubeSats and collision risks for CubeSats deployment. To accomplish these simulations the two part divided for each part has 2 cases. These cases are altitude effects and ejection time for lifetime prediction part, direction difference and multiple ejection cases for obtaining collision risks part. Deployment altitude effects were explored with taking ballistic coefficient, atmospheric drag, and gravity effects into account. By using STK Lifetime Tool, lifetime for all CubeSats were calculated. Ejection time for CubeSats were changed to observe the effects on them. Solar activity effects are also considered and explained briefly. Deployment directions and multiple ejection cases were investigated with several simulations and some of them are shown. By the help of these simulations, the risk pie for CubeSats deployments were obtained. This thesis proposes knowledge for optimizing lifetime and proper deployment directions which are less risky against collision between CubeSats and deployer. The performed simulations also give some deployment system constraints.

Abstmct: This study presents a method to control the attitude of spacecraft using only magnetorquers without the gravity gradient boom. The main challenge is that the control torque can only be generated perpendicular to the geomagnetic field. If the dynamic model is expressed in the ...

This paper presents an approach to design a feasible and reliable Antenna deployment mechanism for CubeSat applications. Nano-Satellites have faced problems in designing their antenna deployment system due to space and protrusion constraints inside the Poly Pico-satellite Orbital Deployer (P-POD). In this design, the height of the sub-frame on which the antennae are mounted and the width of the antennae can be adjusted easily so as to meet the requirements of the P-POD or an X-POD. This mechanism allows use of either a single antenna of a combination of monopole and a dipole. The antennae are stowed on the sub-frame using Dyneema wire and are deployed using a through-hole resistor which is heated using a current limiting Integrated circuit. The paper discusses detailed results of mechanical, electrical and thermal interfaces of the antennae deployment mechanism with the satellite body and the structural analysis of the Antenna deployment mechanism in ANSYS 14.5 and the test results of the mechanism at different temperatures.

Space missions in the past were focused on traditional large costly satellites, but are transitioning to smaller satellites. Nowadays, humankind have the technology of landing a comet and try to make manned flight to Mars. These satellites include
nano-satellites, which is the object of this thesis, becoming one of the most exciting, diverse and fast paced satellites of today. 1U Cubesat is traditionally 10x10x10 cm cubic satellite that weights 1 kg. They are currently used in many countries and
educational institutions as technology demonstration and an easy access to space. The QB50 project is an initiative of the von Karman Institute to operate a network of 50 CubeSats to conduct in-situ, multi-point and long duration measurements in the lower thermosphere between 380 and 90 km. In this study, one of the participant of QB50 project, double unit CubeSat of Istanbul Technical University and Turkish Air Force Academy, namely BeEagleSat were investigated, focusing on orbital mission analysis. Starting with the known values and restriction of the project, simulations have been carried out in order to obtain the orbital analysis the satellite will would perform. Because of the atmospheric drag, the altitude of the satellites will gradually decrease. Additionally, perturbations in the orbit, comparatives with other models and simulations with different parameters were studied. By the help of assumptions for some parameters, analyses can give approximate results. There are also some uncertainties for orbit perturbations such as atmospheric drag, Earth gravity and solar radiation pressure which were briefly clarified. Before launch the primary work to do would be the analysis of the orbit the satellite would perform. In this way, the STK (Systems Tool Kit) software is used to perform this analysis. Deployment altitude effects were explored with taking ballistic coefficient, atmospheric drag, and gravity effects into account. By using STK Lifetime Tool, lifetime for all CubeSats were calculated. Solar activity effects are also considered and explained briefly. Definition of CubeSats, QB50 project and mission characteristic of BeEagleSat is the introduction part of this work. Afterwards, the architecture of BeEagleSat with the payloads and individual subsystems are briefly explained. Then, mission phases of the CubeSat which are mostly related with the ADCS subsystem are shown. In order to give a pre knowledge of surveyed analyses, orbital elements and orbital perturbations are shown with necessary calculations. Finally, simulations are done by predicting lifetime, calculating sunlight and coverage ability of BeEagleSat. This thesis proposes knowledge of the orbital limits and forecasted results of BeEagleSat and can be implemented to other CubeSats especially for another QB50 CubeSat.

SRMSAT – 2 is an advancing student small satellite mission, and a step forward in space exploration; pushing the ambits of small satellites to regimes beyond the Earth. Currently transitioning from the preliminary design review phase, the mission is directed towards the design of a small orbiter spacecraft to orbit and study the moon in a low lunar orbit (LLO). The SRMSAT – 2 is unlike conventional small satellites, which are usually operated in Earth orbits and have lower power constraints because communication from these orbits would not require a high amount of power and propulsion maneuvers are low or non-existent. There is also a strict size constraint on the subsystem set by launch vehicles because small satellites are almost always launched as piggyback. Apart from limitation by way of power, physical dimensions, mass, and budget, there is also a significant challenge imposed due to the distance involved, with the mission requiring communication from a distance up to 1.5 Million Km. ISRO Deep Space Network (IDSN) is necessary to support this mission, and the support is aspired. The subsystem consists of one High Gain Antenna for payload and housekeeping data transmission; and two Low Gain Antennas for omnidirectional coverage, used for command, ranging and emergency communications. The subsystem is S-Band based design with CCSDS compliance for easy interface with existing technologies and ground stations. The On-board transponder is configurable in-orbit and undergoes different changes in configuration throughout the mission as necessary; the changes include a change in data rate and change in transmitted power. This paper presents the constraints, architecture, requirements, and the preliminary design of the Telemetry, Tracking and Command Subsystem of the SRMSAT – 2. Nomenclature BER = Bit Error Rate í µí° ¶ í µí± 0 = Carrier-to-noise-density ratio Dr = Receive antenna diameter Dt = Transmit antenna diameter í µí±¬ í µí²ƒ í µí±µ í µí¿Ž = Energy per bit to noise power spectral density ratio EIRP = Equivalent Isotropically Radiated Power f = Frequency Gpt = Peak transmit antenna gain Gr = Receive antenna gain Grp = Peak receive antenna gain Gt = Net transmit antenna gain La = Polarization loss Laa = Atmospheric loss Lpr = Receive antenna pointing loss Lpt = Transmit antenna pointing loss Ls = Space loss Lt = Transmitter line loss P = Transmitter power R = Data rate RIP = Received Isotropic Power S = Propagation path length Ts = System noise temperature

The space sector has grown dramatically in recent years and is now seen as an important growth engine for the global economy. Tourism, mass and mega launches, moon, mars, asteroid missions, and deployment of the Webb observatory were highlightes in 2021. The year 2022 promises to be yet another fantastic sign of the private sector expanding its hold over modern space and enabling Space Industrialization to progress.
The year-on-year global payload deployments increased by 29%, fourteen civilians experienced space tourism, ushering in a new age of space exploration, and international launch attempts reached a record high of 145, mainly owing to SpaceX's Starlink and OneWeb missions. This is unprecedented, and there has never been a more exciting or better time to be part of the global space ecosystem. Influential commercial factors, evolving technologies, and human imagination are driving the new space sector to completely unexplored heights. Furthermore, the explosive growth of the space industry has resulted in large-scale entrepreneurship and exceptional start-up culture.

The second Young Engineers’ Satellite (YES2) is a project of the ESA Education Department. Its mission is to demonstrate the re-entry of a light-weight capsule by the use of a tether rather than a conventional retro-rocket. The satellite is built by mostly European students under management of Delta-Utec SRC from the Netherlands. The hardware is launched together with the ESA Foton-M3 mission, on a Soyuz launch vehicle carrying a Foton satellite onto which YES2 is attached, mid-September 2007 from Baikonur Kosmodrome.

The mission hardware consists of three main elements. First, FLOYD - the Foton Located YES2 Deployer, which is the tether deployer that will remain attached to Foton during the whole mission. Second, the subsatellite attached to the other end of the tether: MASS - the Mechanical and data Acquisition Support System. Third, Fotino – a re-entry capsule, to be released from MASS after tether deployment. The total hardware mass is 36 kg, of which 14 kg will be deployed on the end of the 5.5 kg, 30 km long, 0.5mm thick tether: the 6 kg Fotino together with MASS will be lowered into a new orbit through momentum transfer utilising the gravity gradient and the Coriolis effects. In this new orbit Fotino's speed is drastically reduced, so that when Fotino is released from MASS, it will not make another orbit, but collide with the atmosphere, slow down due to the heavily increased air drag, re-enter and land. The tether is cut on the FLOYD end 10 seconds after the release of Fotino, causing also tether and MASS to hit the atmosphere but burn completely. During the deployment the tether will be among the brightest object on the sky in areas close to twilight and when it is fully deployed it will be the longest man-made object in space ever. The Foton satellite will orbit the Earth in a near circular orbit at 280 km altitude. The YES2 mission is performed during day 11 of the Foton-M3 mission, with the planned landing zone in the area of Kazakhstan.

The paper describes briefly the mission, organizational and educational aspects, and goes deeper into the design and innovative technology development.

Small Satellite electronic components are generally unavailable for physical upgrade or repair after launch. Run-time Reconfigurable (RTR) computing technology of SRAM-based Field Programmable Gate Arrays (FPGAs) allows to overcome this problem - application of RTR can facilitate new hardware circuits to be uploaded via a radio link without an interruption of service in the FPGAs. In this project these advances

Current commercial Earth Observation satellites have very restricted image processing capabilities on-board. They mostly operate according to a ‘store-and forward’ mechanism, where the images are stored on-board after being acquired from the sensors and are downlinked when contact with a ground station occurs. However, in order for disaster monitoring satellite missions to be effective, there is a need for automated and intelligent image processing onboard. In fact, the need for increasing the automation on-board is predicted as one of the main trends for future satellite missions. The main factors that hold back this concept are the limited power and computing resources on-board the spacecraft. This paper reviews existing image processing payloads of earth observing small satellites. An autonomous change detection system is proposed to demonstrate the feasibility of implementing an intelligent system on-board a small satellite. Performance results for the proposed intelligent imaging system are estimated, scaled and compared to existing hardware that are being used in the SSTL DMC satellite platform.

SRMSAT - 2 is a student-built micro satellite being designed for a lunar mission. Small satellites provide an economic platform to perform small scale scientific experiments and demonstrations of space technologies. The generation, storage and distribution of power along with the protection of components in small satellites is a unique challenge to power engineers because of mass and size constraints. Every subsystem and payload equipment needs to operate under specific voltage conditions when they are required to be operated. The power system also needs to support the satellite functions during eclipse where no power is generated by the solar panels. In addition to this, all equipment needs to be protected from over current, voltage fluctuations and radiation. It is the job of the Electrical Power System to take care of these tasks. The key components of SRMSAT – 2 power system include Ultra triple junction (UTJ) GaAs solar cells controlled by maximum power point trackers and secondary Li-ion battery pack.

There are an increasing number of planned earth and planetary observation missions incorporating thermal infrared imaging instruments. The integration of uncooled microbolometer technology into these instruments provides size, mass, and power consumption advantages that are ...