Total Dose Test Results for CubeSat Electronics

Avery, Keith; Finchel, Jeffery; Mee, Jesse; Kemp, W.T.; Netzer, Richard; Elkins, Donald; Zufelt, Brian; Alexander, David

doi:10.1109/redw.2010.6062504

Cited by 10 publications

(12 citation statements)

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“…To make a fatal failure due to radiation in the expected operational lifetime of two years less likely, several parts of the EPS were implemented in a redundant configuration (the regulators that power consumers were duplicated in a hot-redundant configuration and three MPPT integrated circuits were used). The EPS is controlled using an Atmega 1280 microcontroller, which has been previously tested for radiation dose damage [26] and found to be operable after doses of 18.3 kRad, making it suitable considering the expected mission lifetime. External Ferroelectric Random Access Memory (FRAM) is used to provide reliable operation via the provision of a non-volatile memory for data and firmware storage.…”

Section: Electrical Power Generation and Distribution Subsystemmentioning

confidence: 99%

ESTCube-1 nanosatellite for electric solar wind sail in-orbit technology demonstration

Lätt¹,

Slavinskis

Ilbis

et al. 2014

Proc. Estonian Acad. Sci.

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This paper presents the mission analysis, requirements, system design, system level test results, as well as mass and power budgets of a 1-unit CubeSat ESTCube-1 built to perform the first in-orbit demonstration of electric solar wind sail (E-sail) technology. The E-sail is a propellantless propulsion system concept that uses thin charged electrostatic tethers for turning the momentum flux of a natural plasma stream, such as the solar wind, into spacecraft propulsion. ESTCube-1 will deploy and charge a 10 m long tether and measure changes in the satellite spin rate. These changes result from the Coulomb drag interaction with the ionospheric plasma that is moving with respect to the satellite due to the orbital motion of the satellite. The following subsystems have been developed to perform and to support the E-sail experiment: a tether deployment subsystem based on a piezoelectric motor; an attitude determination and control subsystem to provide the centrifugal force for tether deployment, which uses electromagnetic coils to spin up the satellite to one revolution per second with controlled spin axis alignment; an imaging subsystem to verify tether deployment, which is based on a 640 × 480 pixel resolution digital image sensor; an electron gun to keep the tether at a high positive potential; a high voltage source to charge the tether; a command and data handling subsystem; and an electrical power subsystem with high levels of redundancy and fault tolerance to mitigate the risk of mission failure.

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Section: Electrical Power Generation and Distribution Subsystemmentioning

confidence: 99%

ESTCube-1 nanosatellite for electric solar wind sail in-orbit technology demonstration

Lätt¹,

Slavinskis

Ilbis

et al. 2014

Proc. Estonian Acad. Sci.

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“…There have been previous studies of such effects in the context of small satellites and CubeSats [23,24] that have shown that COTS components start showing effects of radiation damage at 5 kRad and start to threat the mission at about 10 kRad. The results of these studies had to be taken into account when designing the EPS for ESTCube-1.…”

Section: Requirements For the Subsystemmentioning

confidence: 99%

“…To avoid single points of failure of power buses, all critical decoupling capacitors were connected in pairs in series. Still, the expected total ionizing radiation dose during the required satellite lifetime for the EPS components allows the use of COTS components [23], but redundant systems were used where possible.…”

Section: General Designmentioning

confidence: 99%

“…The processing is done on an ATMega1280 AVR microprocessor from Atmel. The processor has been tested for space conditions previously [23] and was considered to be suitable for the requirements of this mission (total ionizing dose received would be less than 6 kRad [22]). To harden the system against radiation effects and to provide long-term storage possibility both for firmwares and for telemetry, the processor has been augmented with parallel (256 kbit FM18W08 from Ramtron) and SPI (two 2 Mbit FM25V20 chips from Ramtron) ferroelectric random access memories.…”

Section: Telemetry and Controlmentioning

confidence: 99%

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Design and pre-flight testing of the electrical power system for the ESTCube-1 nanosatellite

Pajusalu¹,

Ilbis²,

Ilves³

et al. 2014

Proc. Estonian Acad. Sci.

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This work describes the final design and implementation of the electrical power system for ESTCube-1, a 1-unit CubeSat tasked with testing the electrostatic tether concept and associated technologies for the electric solar wind sail in polar low Earth orbit. The mission required an efficient and reliable power system to be designed that could efficiently handle highly variable power requirements and protect the satellite from damage caused by malfunctions in its individual subsystems, while using only commercial-off-the-shelf components. The system was developed from scratch and includes a novel redundant standalone nearly 90% efficient maximum power point tracking system, based on a commercially available integrated circuit, a lithiumion battery based fault-tolerant power storage solution, a highly controllable and monitorable power distribution system, capable of sustaining loads of up to 10 W, and an AVR microcontroller based control solution, heavily utilizing non-volatile ferroelectric random access memories. The electrical power system was finalized in January 2013 and was launched into orbit on 7th of May, 2013. In this paper, we describe the requirements for the subsystem, the design of the subsystem, pre-flight testing, and flight qualification.

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“…Potential RadiationSensitive EEE Parts may be found in the Table II while comparison of the Radiation-Sensitive EEE Parts between all COTS and space grade GPSR is illustrated in the Table III. Many literatures indicates that total ionizing dosage that LEO satellites expose to may ranged from several to tens of krads [1,2]. For the orbit of FORMOSAT-2, a 4mm thickness GPSR compartment will receive around 6krads for the total of 5 years ionizing.…”

Section: B Space Grade Version Gpsrmentioning

confidence: 99%

TID testing and SEE mitigation approach of a long mission life GPS receiver using COTS parts

Cheng

Lin

Chen

2012

2012 6th ESA Workshop on Satellite Navigation Technologies (Navitec 2012) &Amp; European Workshop on GNSS Signals and Signal Pr

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Compared to conventional hardware GPS receivers (GPSR), software GPS receivers are more suitable for research and development. Software GPS receivers can be dynamically programmed in software to reconfigure the characteristics of GPS receiver and new algorithms can easily be integrated without changing the design of the hardware. However, the most important issue for this approach is the computational load. It can be solved by using the high performance state-of-art digital signal processor. The harshness of space environment, such as Total Ionizing Dosage (TID), Single Event Effect (SEE), always cast certain thread to GPS receiver intended for space applications. Common resolution to cope with this thread is the robustness of space grade EEE parts toward those effects along with the protection of circuit design. Nevertheless, the most of the state-of-art EEE parts are not space qualified. In this study, certain Commercial Off The Shelf (COTS) parts such as COTS level RF Front-End (RFFE) and Digital SignalProcessor (DSP) along with single event effect (SEE) mitigation circuit design, are considered in the proposed GPSR design for their advantages, such as availability, performance, size, weight and lead time, over regular space qualified ones.

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Total Dose Test Results for CubeSat Electronics

Cited by 10 publications

References 0 publications

ESTCube-1 nanosatellite for electric solar wind sail in-orbit technology demonstration

ESTCube-1 nanosatellite for electric solar wind sail in-orbit technology demonstration

Design and pre-flight testing of the electrical power system for the ESTCube-1 nanosatellite

TID testing and SEE mitigation approach of a long mission life GPS receiver using COTS parts

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