Radioisotope Power Systems for Space Applications

Sánchez-Torres, Antonio

doi:10.5772/20928

Cited by 10 publications

(11 citation statements)

References 8 publications

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“…Table 1 provides a summary of the power density (W g À1 ), half-life, and emission modes of these candidates. 16 As illustrated in Table 1, 244 Cm boasts the highest thermal power output among the isotope candidates but suffers from a short half-life, with its specific heat power (W g À1 ) halved every 18 years. In contrast, 90 Sr, which has a slightly longer half-life of 28 years, requires thicker shielding to protect the outer system from b-rays, thereby increasing the RTG's total weight and cost.…”

Section: The Radioisotope Heat Source (Rhs)mentioning

confidence: 99%

“…238 Pu achieves a balance by offering both a long half-life and high specific heat power from its alpha decay and is traditionally used in RTGs in the form of pure plutonium oxide (PuO 2 ). 16 However, driven by concerns regarding scarcity and cost of 238 Pu, the European space program has opted to use 241 Am, despite its lower thermal power output compared to other isotopes. This shift from 238 Pu to 241 Am is part of the European Space Agency (ESA) program since 2009 to develop new types of TEGs compatible with the power output of 241 Am.…”

Section: The Radioisotope Heat Source (Rhs)mentioning

confidence: 99%

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Thermoelectric materials for space explorations

Palaporn,

Tanusilp,

Sun

et al. 2024

Mater. Adv.

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Section: The Radioisotope Heat Source (Rhs)mentioning

confidence: 99%

Section: The Radioisotope Heat Source (Rhs)mentioning

confidence: 99%

Thermoelectric materials for space explorations

Palaporn,

Tanusilp,

Sun

et al. 2024

Mater. Adv.

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“…These propulsion systems mainly apply to much larger systems in comparison to small satellites or microthrusters, however, there exists some concepts that apply to small satellites. Most commonly, radioisotope thermoelectric generators are used (RTG) [131]. These systems have generally used plutonium but plutonium is scarce and identifying alternative radioisotopes is important for future small satellite probe missions [132].…”

Section: Nuclearmentioning

confidence: 99%

Electric Propulsion Methods for Small Satellites: A Review

2021

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Over 2500 active satellites are in orbit as of October 2020, with an increase of ~1000 smallsats in the past two years. Since 2012, over 1700 smallsats have been launched into orbit. It is projected that by 2025, there will be 1000 smallsats launched per year. Currently, these satellites do not have sufficient delta v capabilities for missions beyond Earth orbit. They are confined to their pre-selected orbit and in most cases, they cannot avoid collisions. Propulsion systems on smallsats provide orbital manoeuvring, station keeping, collision avoidance and safer de-orbit strategies. In return, this enables longer duration, higher functionality missions beyond Earth orbit. This article has reviewed electrostatic, electrothermal and electromagnetic propulsion methods based on state of the art research and the current knowledge base. Performance metrics by which these space propulsion systems can be evaluated are presented. The article outlines some of the existing limitations and shortcomings of current electric propulsion thruster systems and technologies. Moreover, the discussion contributes to the discourse by identifying potential research avenues to improve and advance electric propulsion systems for smallsats. The article has placed emphasis on space propulsion systems that are electric and enable interplanetary missions, while alternative approaches to propulsion have also received attention in the text, including light sails and nuclear electric propulsion amongst others.

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“…The weight of a model of the Power System for this type of radiator is about M ¼ 56 kg, as reported in Sanchez-Torres. 29 Commonly, the maximum acceleration during launch phase of spacecraft are 20 times the gravity acceleration, g, on Earth. Overall, the forces applied to the quarter of the cross section (Figure 14(b) is the product of the Power System weight and the total acceleration in both directions split by four per unit of length, as reported by equation ( 14)…”

Section: Thermomechanical Topology Optimization: Validation On a Real Componentmentioning

confidence: 99%

A new methodology for thermostructural topology optimization: Analytical definition and validation

Caivano

Tridello

Codegone

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part L:

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In the last few years, the rapid diffusion of components produced through additive manufacturing processes has boosted the research on design methodologies based on topology optimization algorithms. Structural topology optimization is largely employed since it permits to minimize the component weight and maximize its stiffness and, accordingly, optimize its resistance under structural loads. On the other hand, thermal topology optimization has been less investigated, even if in many applications, such as turbine blades, engines, heat exchangers, thermal loads have a crucial impact. Currently, structural and thermal optimizations are mainly considered separately, despite the fact that they are both present and coupled in components in service condition. In the present paper, a novel methodology capable of defining the optimized structure under simultaneous thermomechanical constraints is proposed. The mathematical formulation behind the optimization algorithm is reported. The proposed methodology is finally validated on literature benchmarks and on a real component, confirming that it permits to define the topology, which presents the maximized thermal and mechanical performance.

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Radioisotope Power Systems for Space Applications

Cited by 10 publications

References 8 publications

Thermoelectric materials for space explorations

Thermoelectric materials for space explorations

Electric Propulsion Methods for Small Satellites: A Review

A new methodology for thermostructural topology optimization: Analytical definition and validation

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