Review of Nuclear Thermal Propulsion Systems

Gabrielli, Roland; Herdrich, Georg

doi:10.1016/j.paerosci.2015.09.001

Cited by 43 publications

(6 citation statements)

References 36 publications

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“…The specific impulse of a thermal rocket is maximized by using propellant of minimum molecular weight, hydrogen. If the propellant temperature could reach at 3000 K, the specific impulse in vacuum becomes 900 seconds [17,18]. Nevertheless, Kare's estimation of the properspecific impulse is around 600 seconds.…”

Section: A New Design Of Laser Propulsionmentioning

confidence: 99%

Beamed Launch Propulsion

Mori¹

2019

Propulsion Systems

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An advanced concept of launch system from ground to orbit, called laser launch system, has been discussed. As a 100-kW-class fiber laser has been developed today, the laser propulsion is now a realistic option for launching microsatellites frequently at very low cost. In this chapter, we shall discuss several unresolved technical problems such as propulsion design and laser beam transmission through atmosphere. It is proved theoretically that high specific impulse higher than 900 seconds is possible in a new conceptual design. On the other hand, the laser beam may be suffered by the atmospheric turbulence when the launch vehicle reaches at altitude higher than 10 km.

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Section: A New Design Of Laser Propulsionmentioning

confidence: 99%

Beamed Launch Propulsion

Mori¹

2019

Propulsion Systems

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“…In nuclear thermal propulsion (NTP), the energy released from nuclear fission of radioactive isotopes is used to heat cryogenic propellants, thereupon resulting in high specific impulses [249]. Extensive tests since the 1970s [250] have consequently identified a clear path for actualizing high TRL of 5-6 for NTP [150].…”

Section: Solar and Nuclear Thermal Propulsionmentioning

confidence: 99%

Chasing nomadic worlds: A new class of deep space missions

Lingam¹,

Hein²,

Eubanks³

2023

Acta Astronautica

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“…Any technique for using water as a propellant must implement a power source sufficient to either heat water to useful propulsive temperatures or electrolyze water into its fuel and oxidizer components [6][7][8]. In our approach, we explore using solar concentrators, focusing power onto a chamber of a highly refractive material such as Tantalum Hafnium Carbide [5] to superheat working fluid temperatures to 4000 K.…”

Section: Introductionmentioning

confidence: 99%

A Solar Thermal Steam Propulsion System Using Disassociated Steam for Interplanetary Exploration

Vance,

Espinoza,

Martinez Dominguez

et al. 2024

Aerospace

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Sustainable space exploration will require using off-world resources for propellant generation. Using off-world-generated propellants significantly increases future missions’ range and payload capacity. Near Earth Objects (NEOs) contain a range of available resources, most notably water-ice and hydrated minerals. However, water-bearing regolith needs to be excavated and the water extracted. Water is a compelling choice for fuel as it is readily available in interplanetary space and easily stored. In this paper, we propose using solar concentrators, which can efficiently convert incident sunlight into heat without the need for moving parts. When water is heated up to 4000 K, a value consistent with high-performance refractive materials, it experiences significant disassociation into H2, O2, OH, H, and O components, providing a path for adding considerable additional chemical energy per degree of temperature increase, and producing theoretical specific impulse (Isp) values in the range of 643 s to 659 s.

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Review of Nuclear Thermal Propulsion Systems

Cited by 43 publications

References 36 publications

Beamed Launch Propulsion

Beamed Launch Propulsion

Chasing nomadic worlds: A new class of deep space missions

A Solar Thermal Steam Propulsion System Using Disassociated Steam for Interplanetary Exploration

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