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Book ChapterDOI

Radioisotope Power Systems for Space Applications

TL;DR: A Radioisotope Thermoelectric Generators (RTGs) were used in the past as electric power supplies for some navigational and meteorological missions, and most outer-planet missions as mentioned in this paper.
Abstract: At the beginning of the Space Age, both propulsion and power generation in the spacecraft has been the main issue for consideration. Considerable research has been carried out on technologies by several Space Agencies to reach outer planets and generate electric power for the systems and subsystems in the spacecraft (SC). Various types of power source such as solar photovoltaic, Radioisotope power systems (RPS) have been used by Space Agencies. New technology such as reactor based, electric solar sail and electrodynamic bare tethers might be used in the future for both propulsion and power generation. Mainly, both NASA and Russian Agency worked separately using nuclear technology to obtain more efficiency in their systems for deep space exploration. Radioisotope Power Systems (RPS), is a nuclear-powered system to generate electric power to feed communication and scientific systems on a spacecraft. Radioisotope Thermoelectric Generators (RTGs), a type of Radioisotope Power System, were used in the past as electric power supplies for some navigational and meteorological missions, and most outer-planet missions. Radioisotope power systems use the natural decay of radionuclides produced by a nuclear reactor. The expensive, man-made Plutonium-238 (238Pu) is the appropriate source of energy used in RPS fueling; its long half-life (~87 years) guarantees long time missions. The limited avability of Plutonium-238 is inadequate to support scheduled NASA mission beyond 2018. After the Cold War, throughout the Non-Proliferation of Nuclear Weapons Treaty, the production and processing of these resources have been severally reduced. There is a high-priority recommendation to reestablish production to solve the severe 238Pu demand problem (National Reseach Council, 2009). The isotope initially selected for terrestrial and space power applications was Cerium-144 because it is one of the most useful fission products available from nuclear reactor (Furlog, 1999; Lange, 2008). Its short half-life (about 290 days) made Cerium-144 compatible with a possible short-time mission. However, the high radiation associated with a powerful beta/gamma emission produces several problems with the payload interaction and safety in the case of reentry orbit. The development of RTGs was assigned to The Atomic Energy Commission in 1955. The first system developed for space situation was the System for Nuclear Auxiliary Power (SNAP). The Cerium-144 fueled SNAP-1 power system was never used in space. The first flight with a RTG was SNAP-3 in 1961 delivering 11.6 kW over a 280 days period, using as fueling Polonium-210 (Po-210) isotope. Po-210 is an alpha emitter with

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Journal ArticleDOI
TL;DR: In this paper, the possibility of developing concrete with TE properties to harvest stored heat in concrete structures have been systematically investigated by incorporating zinc oxides (ZnO) based nanoparticles in cement paste.

59 citations

Journal ArticleDOI
18 Jan 2021
TL;DR: Electrostatic, electrothermal and electromagnetic propulsion methods based on state of the art research and the current knowledge base are reviewed, placing emphasis on space propulsion systems that are electric and enable interplanetary missions.
Abstract: 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.

56 citations

Journal ArticleDOI
TL;DR: In this paper , the authors explore the endurance of typical mesoscopic n-i-p MAPbI 3 solar cells in LEO (low earth orbit) conditions and observe no measurable damage to the J-V performance for 10 MeV protons by in-situ measurements for the cells containing Spiro-OMeTAD as the hole transporting material.

9 citations

Journal ArticleDOI
01 Mar 2021
TL;DR: A novel methodology capable of defining the optimized structure under simultaneous thermomechanical constraints is proposed and 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.
Abstract: 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...

6 citations

28 Jul 2014
TL;DR: In this article, a radioisotope power system (RPS) design for a small low-power Venus lander is presented, which is based on high-temperature electronics technology that will enable the electronics and components of the lander to operate at Venus surface temperature.
Abstract: The Planetary Science Decadal Survey of 2013-2022 stated that the exploration of Venus is of significant interest. Studying the seismic activity of the planet is of particular importance because the findings can be compared to the seismic activity of Earth. Further, the geological and atmospheric properties of Venus will shed light into the past and future of Earth. This paper presents a radioisotope power system (RPS) design for a small low-power Venus lander. The feasibility of the new power system is then compared to that of primary batteries. A requirement for the power source system is to avoid moving parts in order to not interfere with the primary objective of the mission - to collect data about the seismic activity of Venus using a seismometer. The target mission duration of the lander is 117 days, a significant leap from Venera 13, the longest-lived lander on the surface of Venus, which survived for 2 hours. One major assumption for this mission design is that the power source system will not provide cooling to the other components of the lander. This assumption is based on high-temperature electronics technology that will enable the electronics and components of the lander to operate at Venus surface temperature. For the proposed RPS, a customized General Purpose Heat Source Radioisotope Thermoelectric Generator (GPHSRTG) is designed and analyzed. The GPHS-RTG is chosen primarily because it has no moving parts and it is capable of operating for long duration missions on the order of years. This power system is modeled as a spherical structure for a fundamental thermal analysis. The total mass and electrical output of the system are calculated to be 24 kilograms and 26 Watts, respectively. An alternative design for a battery-based power system uses Sodium Sulfur batteries. To deliver a similar electrical output for 117 days, the battery mass is calculated to be 234 kilograms. Reducing mission duration or power required will reduce the required battery mass. Finally, the advantages and disadvantages of both power systems with regard to science return, risk, and cost are briefly compared. The design of the radioisotope power system is considerably riskier because it is novel and would require additional years of further refinement, manufacturing, safety analysis, and testing that the primary batteries do not need. However, the lifetime of the radioisotope power system makes its science return more promising.

6 citations

References
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Book
01 Jan 1996
TL;DR: In this article, the authors present a survey of the state-of-the-art references in the field of space radiation and its applications in the space radiation environment and the ambient space environment.
Abstract: List of illustrations List of tables Preface Acknowledgement 1. Introduction 2. Fundamental length, time, and velocity 3. The ambient space environment 4. Neutral gas interactions 5. Plasma interactions 6. The space radiation environment 7. Particulate interactions 8. The state of the art References Index.

373 citations

Journal ArticleDOI
TL;DR: In this article, a simple electron-collection concept which is free of most of the physical uncertainties associated with plasma contactors in the rarefied, magnetized environment of an orbiting tether is discussed.
Abstract: The collection of electrons from the ionosphere is the major problem facing high-power electrodynamic tethers. This article discusses a simple electron-collection concept which is free of most of the physical uncertainties associated with plasma contactors in the rarefied, magnetized environment of an orbiting tether. The idea is to leave exposed a fraction of the tether length near its anodic end, such that, when a positive bias develops locally with respect to the ambient plasma, and for a tether radius small compared with both thermal gyroradius and Debye length, electrons are collected in an orbital-motion-limited regime. It is shown that large currents can be drawn in this way with only moderate voltage drops. The concept is illustrated through a discussion of performance characteristics for generators and thrusters.

294 citations


"Radioisotope Power Systems for Spac..." refers background in this paper

  • ...The large electromotive force produced by the tether moving in some plasma ambient near the planet generate induced current and then electric power (Sanmartin et al., 1993)....

    [...]

Book
01 Jan 2002
TL;DR: In this article, the authors present a system engineering overview of propulsion, propulsion, and power control in a command and data handling environment, with a focus on communication structure and communication structure.
Abstract: Introduction System Engineering Orbital Mechanics Propulsion Attitude Control Power System Thermal Control Command and Data Handling Communication Structure Appendices

156 citations


"Radioisotope Power Systems for Spac..." refers background in this paper

  • ...A second aeroshell improvement, known as Step 2 GPHS module, gives additional protection in the clads for hipervelocity reentry into the atmosphere (Benett, 2006; Brown, 2001; Griffin, 2004; Hastings, 2004)....

    [...]

  • ...The early RTGs developed a specific power slightly larger than 1 W/kg. SNAP-9A system reached 20 W/kg whereas later systems such as Galileo developed 5.4 W/kg (Brown, 2001; Griffin, 2004)....

    [...]

Journal ArticleDOI
TL;DR: In this paper, the authors provide a brief review of the factors influencing selection of radioisotopes and design of power systems, and discuss the current state of practice and future programmatic and technical challenges to continued use of radio-isotope power systems in space.

110 citations

Proceedings ArticleDOI
26 Jun 2006
TL;DR: The GPHS-RTG was designed such that it could produce 300 We at fueling with a mass of 55.9 kg, making it the most powerful RTG with the highest specific power ever flown as mentioned in this paper.
Abstract: The general-purpose heat source radioisotope thermoelectric generator (GPHS-RTG), which was most recently flown on the New Horizons mission to Pluto, was originally conceived in 1979 and executed in a crash program to replace another RTG for the planned International Solar Polar Mission (ISPM). ISPM would later morph into the Ulysses mission to explore the polar regions of the Sun. When the benefits of the GPHS-RTG technology became apparent, the Galileo program also adopted the GPHS-RTG as the power source for orbital exploration of Jupiter. The GPHS-RTG then became the power source of choice for the Cassini mission to Saturn. The GPHS-RTG was designed such that it could produce 300 We at fueling with a mass of 55.9 kg, making the GPHS-RTG the most powerful RTG with the highest specific power ever flown.

84 citations