An FPGA-based radiation tolerant SmallSat Computer System

Julien, Connor; LaMeres, Brock J.; Weber, Raymond J.

doi:10.1109/aero.2017.7943634

Cited by 11 publications

(8 citation statements)

References 2 publications

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“…This means that the proposed control introduced in the terminal descent phase is essential and very effective and makes the landing very precise and reliable. For this terminal descent phase, the mass consumption varies within the range [1.20, 2.94] kg in the case of ∆t P = 1 s and [1.20, 3.08] kg in the case of ∆t P = 2 s. Thus, the total mass consumption considering the two phases (approaching phase and terminal descent) can be considered within the range [28,39] kg. Another test is performed considering 10 successive optimizations during the approaching phase (without hazard detection and thus without updating the final position of the approaching phase).…”

Section: Numerical Resultsmentioning

confidence: 99%

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PSO-Based Soft Lunar Landing with Hazard Avoidance: Analysis and Experimentation

et al. 2021

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The problem of real-time optimal guidance is extremely important for successful autonomous missions. In this paper, the last phases of autonomous lunar landing trajectories are addressed. The proposed guidance is based on the Particle Swarm Optimization, and the differential flatness approach, which is a subclass of the inverse dynamics technique. The trajectory is approximated by polynomials and the control policy is obtained in an analytical closed form solution, where boundary and dynamical constraints are a priori satisfied. Although this procedure leads to sub-optimal solutions, it results in beng fast and thus potentially suitable to be used for real-time purposes. Moreover, the presence of craters on the lunar terrain is considered; therefore, hazard detection and avoidance are also carried out. The proposed guidance is tested by Monte Carlo simulations to evaluate its performances and a robust procedure, made up of safe additional maneuvers, is introduced to counteract optimization failures and achieve soft landing. Finally, the whole procedure is tested through an experimental facility, consisting of a robotic manipulator, equipped with a camera, and a simulated lunar terrain. The results show the efficiency and reliability of the proposed guidance and its possible use for real-time sub-optimal trajectory generation within laboratory applications.

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Section: Numerical Resultsmentioning

confidence: 99%

“…This results in a more robust trajectory planning. All the work presented in this paper represents the first step for future real-time testing on hardware that has already been tested for flight, such as FPGA [28].…”

Section: Introductionmentioning

confidence: 99%

PSO-Based Soft Lunar Landing with Hazard Avoidance: Analysis and Experimentation

et al. 2021

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“…So far, there is no standard or common practices regarding system level data reporting, rather applicationspecific testing and reporting are done. In [3], for instance, a system level failure happens when the system generates an incorrect GPS output and non-critical or soft-error occurs when system crash or loss of positioning happens, whereas in [4], a system failure occurs when bugs are reported by a customized operational system or configuration bit upsets occur. This approach makes the component level information gathering more difficult and avoids the reusability of a system level test data.…”

Section: Motivationmentioning

confidence: 99%

Development and evaluation of a flexible instrumentation layer for system-level testing of radiation effects

Lopes

Pouget

Wrobel

et al. 2020

2020 IEEE Latin-American Test Symposium (LATS)

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In the context of the growing interest for systemlevel testing for radiation effects, this paper presents the development of different levels of software and firmware instrumentation with limited overhead that can be statically or dynamically added to the application under test in order to provide different levels of observability of radiation-induced single-event effects and total ionizing dose effects, as well as to improve the component-level diagnosis of failures observed at system-level. The instrumentation levels are described and applied to a digital control-loop application implemented on a Zynq7000 based commercial system-on-module. A first set of results obtained under high energy protons is presented and discussed.

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“…These are called temporal faults. These unwanted bit flips are often caused by effects such as ionizing radiation and extreme temperatures [52]. [59].…”

Section: Reliability Issues In Fpgasmentioning

confidence: 99%

“…configuration bitstream in runtime especially for safety-critical applications. SRAMbased FPGA CMEM are volatile, and the bits stored in them could be flipped due to undesired effects such as radiation and extreme temperatures[52]. To mitigate the effects of unwanted bit flips, each configuration frame in the bitstream of XilinxFPGAs is protected by a Frame Error Correcting Code (Frame ECC).…”

mentioning

confidence: 99%

R3TOS-Based Integrated Modular Space Avionics for On-Board Real-Time Data Processing

Adetomi

Enemali

Iturbe

et al. 2018

2018 NASA/ESA Conference on Adaptive Hardware and Systems (AHS)

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An FPGA-based radiation tolerant SmallSat Computer System

Cited by 11 publications

References 2 publications

PSO-Based Soft Lunar Landing with Hazard Avoidance: Analysis and Experimentation

PSO-Based Soft Lunar Landing with Hazard Avoidance: Analysis and Experimentation

Development and evaluation of a flexible instrumentation layer for system-level testing of radiation effects

R3TOS-Based Integrated Modular Space Avionics for On-Board Real-Time Data Processing

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