Nuclear systems for Mars exploration

Balint, Tibor S.

doi:10.1109/aero.2004.1368102

Cited by 8 publications

(3 citation statements)

References 25 publications

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“…Note that the cruise phase could last between 6 months to a year depending on the launch opportunity (Balint, 2004a). Note that the cruise phase could last between 6 months to a year depending on the launch opportunity (Balint, 2004a).…”

Section: Launch and Cruise Phasesmentioning

confidence: 99%

Thermal Analysis of a Small-RPS Concept for the Mars NetLander Network Mission

Balint¹,

Emis²

2005

AIP Conference Proceedings

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The NetLander Network mission concept was designed with up to 10 small landers to perform environmental monitoring on the surface of Mars over a long duty cycle. Each lander would utilize a small Radioisotope Power System (RPS) to generate about 20 to 25 We of electric power. Each small-RPS would use a single General Purpose Heat Source (GPHS) module to generate about 250 Wt of thermal power (BOL), which must be dissipated throughout all phases of the mission. This paper describes a custom concept for a small-RPS, specifically suited for the NetLander, and discusses an analysis of the thermal environment for five phases of the mission. On Earth and on Mars the small-RPS would operate in planetary atmospheres and the waste heat would be removed through a passive radiator. During the cruise phase, including the launch, a fluid loop would provide active cooling to the radiator of the small-RPS and would reject the excess heat through an external radiator. For the entry, descent and landing (EDL) phase the lander would accumulate the excess heat, while building up thermal inertia inside. This analysis provides an initial step towards developing an end-to-end systems approach to better understand the operation of a small-RPS, and to account for the relevant operating phases and environments encountered during a mission.

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Section: Launch and Cruise Phasesmentioning

confidence: 99%

Thermal Analysis of a Small-RPS Concept for the Mars NetLander Network Mission

Balint¹,

Emis²

2005

AIP Conference Proceedings

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“…This all can be possibly done by space exploration. NASA has done some phenomenal work on nuclear power systems [1]. Space exploration is done by satellites that need electrical power to do their required work [2].…”

Section: Introductionmentioning

confidence: 99%

Comparison of DC-DC converters for solar power conversion system

Mishra

Senapati

Salkuti

2022

IJEECS

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This paper covers the comparison between four different DC-DC converters for solar power conversion. The four converters are buck converter, buck-boost converter, boost converter, and noninverting buck-boost converter. An MPPT algorithm is designed to calculate battery voltage, current of PV array, the voltage of PV array, power of PV array, output power. It is observed that the non-inverting buck-boost converter is the finest converter for solar power conversion. The final circuit design has the results of 12.2V battery voltage, 0.31A current of PV array, 34V voltage of PV array, 23mW power of PV panel, and 21.8mW of output power. The efficiency of this system is nearly 95%. All four circuits are simulated in MATLAB/Simulink R2020b.

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“…A brief overview of potential power system options for manned moon and mars mission comprises of power technologies including power sources (both external and internal), and power storage devices. A more comprehensive summary of these power systems can be found in Balint and Jordan (2005) and Balint (2004a, b). Additional details on radioisotope power systems are provided in Abelson et al (2004a, b, 2005) and Surampudi et al (2001) while energy storage technologies are discussed in Mondt et al (2004), and solar power generation in Cutts and Prusha (2003).…”

Section: Introductionmentioning

confidence: 99%

Development of payload housing for temperature and pressure control of bio fuel cells for space applications

Jayaram

2009

Journal of Engineering, Design and Technology

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PurposeAlternative energy sources and power generation techniques for long‐term space missions are gaining importance in recent years for future bases and colonies on the Moon or Mars. Current technologies used for manned or unmanned missions to the Moon or Mars use either solar panels (bulky, expensive/kilogram to space, and inefficient) or nuclear energy (extremely dangerous and unpopular). Enzyme based bio fuel cells can be used as alternative energy sources, but its survival depends on maintaining appropriate temperature and pressure in space. The purpose of this paper is to detail the concept design and development of a payload tank to house bio fuel cells for operations in space environment.Design/methodology/approachDetails about the development of the design methodology for such housing are discussed. A full‐scale payload tank is designed to house a small biological fuel cell using space grade materials. Requirements analysis, design, validation, and manufacturing process are covered.FindingsThe outcome is a dimensionally optimized housing structure for housing biological fuel cells and maintaining the temperature and pressure for survival of the fuel cell.Originality/valueThe designed payload housing satisfies all the constraints and requirements. Furthermore, its advantages include scalability and modularity by virtue of using optimized design approach. The final product provides a planned procedure for designing larger housing for other missions.

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Nuclear systems for Mars exploration

Cited by 8 publications

References 25 publications

Thermal Analysis of a Small-RPS Concept for the Mars NetLander Network Mission

Thermal Analysis of a Small-RPS Concept for the Mars NetLander Network Mission

Comparison of DC-DC converters for solar power conversion system

Development of payload housing for temperature and pressure control of bio fuel cells for space applications

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