Design of command, data and telemetry handling system for a distributed computing architecture CubeSat

Asundi, Sharan; Fitz-Coy, Norman

doi:10.1109/aero.2013.6496901

Cited by 12 publications

(10 citation statements)

References 11 publications

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“…Current trajectories of CubeSat development suggest that the time will come when the majority of computationally intense tasks onboard a CubeSat will be those associated with autonomous decision making and science data handling [73]- [75]. However, at present, GNC tasks still consume a nontrivial portion of cyber resources.…”

Section: B Cyber Characteristics and Setupmentioning

confidence: 98%

Coupled Cyber–Physical System Modeling and Coregulation of a CubeSat

Bradley

Atkins

2015

IEEE Trans. Robot.

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We propose the application of state-space techniques to develop a novel coupled cyber-physical system (CPS) model and use feedback control to dynamically adjust CPS resource use and performance. We investigate the use of a gain scheduled discrete linear quadratic regulator controller and a forward-propagation Riccati-based controller to handle the discrete-time-varying system. We demonstrate the value of our approach by conducting a disturbance-rejection case study for a small satellite (CubeSat) application in which resources required for attitude control are adjusted in real-time to maximize availability for other computational tasks. We evaluate CPS performance through a set of metrics quantifying physical system error and control effort as well as cyber resource utilization and compare these with traditional fixedrate optimal control strategies. Results indicate that our proposed coupled CPS model and controller can provide physical system performance similar to fixed-rate optimal control strategies but with less control effort and much less computational utilization.

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Section: B Cyber Characteristics and Setupmentioning

confidence: 98%

Coupled Cyber–Physical System Modeling and Coregulation of a CubeSat

Bradley

Atkins

2015

IEEE Trans. Robot.

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“…CubeSats 13 are increasingly popular spacecraft platforms for mission-oriented experiments that can be accomplished via quick prototyping and launches [10-12]. 11 Hardware abstraction layer (HAL) is a layer of programming that allows a computer operating system to interact with a hardware device at a general or abstract level rather than at a detailed hardware level…”

Section: Sdr Applications In Cubesatsmentioning

confidence: 99%

“…POSIX defines the application programming interface (API) for software compatibility with variants of Unix and other operating systems [Wikipedia]. 13 CubeSats are a class of Small Satellites (SmallSats) weighing between 1 kg and 10 kgs that use standard size and form factor of 1 U (one unit) of 10 cm x 10 cm x 10 cm. A standard 3 U CubeSat (10 cm x 10 cm x 34 cm, 5 and 6 kg) has been demonstrated to support real mission, and larger CubeSats (6 U, 12 U, and 24 U) are developed.…”

Section: Sdr Applications In Cubesatsmentioning

confidence: 99%

“…The availability of modular, high-performance sequential and parallel processors that are resilient to radiation upsets allows the tailoring of hardware architectures to the application and to the CubeSat platform. This is especially suitable for missions that require the flexibility to support multiple TT&C and mission data from multiple satellites and ground stations [13][14][15].…”

Section: Sdr Applications In Cubesatsmentioning

confidence: 99%

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Communication Subsystems for Satellite Design

Nguyen¹,

Nguyen²

2021

Satellite Systems - Design, Modeling, Simulation and Analysis

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The objective of this chapter is to provide a comprehensive end-to-end overview of existing communication subsystems residing on both the satellite bus and payloads. These subsystems include command and mission data handling, telemetry and tracking, and the antenna payloads for both command, telemetry and mission data. The function of each subsystem and the relationships to the others will be described in detail. In addition, the recent application of software defined radio (SDR) to advanced satellite communication system design will be looked at with applications to satellite development, and the impacts on how SDR will affect future satellite missions are briefly discussed.

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“…The first step of the proposed approach consists of building diagrams and documents, which illustrate interrelationships and interdependencies of functional entities and support an effective mission design [31]. This step is necessary to understand system's architecture, providing answers to questions such as: which equipment provides what function; when the equipment fails what function is affected; how the system can be controlled before and after a failure; how backups and redundancies have to be managed to guarantee usability and accessibility in case of failure; etc.…”

Section: Step 1 Construct the Functional Block Diagramsmentioning

confidence: 99%

A Reliability Engineering Approach for Managing Risks in CubeSats

et al. 2018

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Besides large-scale space missions, the spread of CubeSats for a variety of applications is increasingly requiring the development of systematic approaches for risk management. Being these applications are based on components with low TRL (Technology Readiness Level) or with limited performance data, it is required to define approaches which ensure a systematic perspective. This paper aims to present a reliability engineering approach based on FMECA (Failure Mode, Effects, and Criticality Analysis) to manage CubeSat reliability data and prioritize criticalities early in the design phase. The approach firstly proposes an alpha-numeric coding system to support the identification and labeling of failure modes for typical CubeSats’ items. Subsequently, each FMECA coefficient (i.e., Severity, Occurrence, Detectability) has been linked to the CubeSat’s structural properties, reducing subjectivity by means of techno-centric proxy indicators. The approach has been validated in the design phases of a 6-Units university CubeSat for the observation of M-Dwarf stars and binary systems. The performed analysis supported the design process and allowed to identify the major criticalities of the CubeSat design, as demonstrated in the extended case study included in the paper. The formalized method could be applied to design procedures for nano-satellites, as well as being expanded for research and development in a variety of space missions.

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Design of command, data and telemetry handling system for a distributed computing architecture CubeSat

Cited by 12 publications

References 11 publications

Coupled Cyber–Physical System Modeling and Coregulation of a CubeSat

Coupled Cyber–Physical System Modeling and Coregulation of a CubeSat

Communication Subsystems for Satellite Design

A Reliability Engineering Approach for Managing Risks in CubeSats

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