Advancements in the Development of Low Enriched Uranium Nuclear Thermal Rockets

Venneri, Paolo; Kim, Yong Hee

doi:10.1016/j.egypro.2017.09.475

Cited by 5 publications

(2 citation statements)

References 7 publications

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“…In the end, they compared and showed how LEU-NTR is applied for different thrust levels. [12] Steiling (et.al, 1975) explored thrust augmentation of various afterburner ejectors. Using H/o2 sonic rocket as primary gas generator, static test were conducted.…”

Section: Literature Reviewmentioning

confidence: 99%

Thrust Augmentation and its Control Methods: Short Overview

Nikkisha¹,

Mishra²

2022

jame

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Augmentation plays a crucial role in many aircrafts and jet engines to elevate the thrust. Thrust is oe of the four fundamental forces of an aircraft. Augmentation methods are used in certain cases to increase the thrust to perform better landing and take-off. There is various augmentation methods in which afterburner is mostly used over other augmentation methods because of its advantages. In this paper an overview has been provided for thrust augmentation and its different control methods.

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Section: Literature Reviewmentioning

confidence: 99%

Thrust Augmentation and its Control Methods: Short Overview

Nikkisha¹,

Mishra²

2022

jame

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“…Advancement in entry, descent, and landing (EDL) are required to land heavy Table 2: Specification of SULEU & SCCTE. [6] payloads like human being & electric rovers in mars surface. Previous technology like mars science laboratory"s sky crane was not capable to land payloads greater than 2 metric tons.…”

Section: Mars Exploration and Radiation Protectionmentioning

confidence: 99%

Low Enriched Uranium based Nuclear Rocket Propulsion Technology: Mars Exploration Mission

Neupane

2019

IJRE

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Many space agencies like NASA, SPACE-X have promised to send humans into the red planet in future. So, considering their project of mars colonization, nuclear rocket propulsion would be the better option. Replacing chemical rockets by nuclear rockets may reduce the mission duration and also can reduce the mass of the propellant used. In chemical rockets, propellant releases energy through combustion but in case of nuclear rockets, propellant i.e. hydrogen is heated up in controlled fission reaction in nuclear reactor inside the rocket engine. Specific impulse of the nuclear rocket is greater than chemical rocket. This helps in providing gigantic thrust as a result mission duration is decreased. The challenging parameter of increasing specific impulse is solved by maximizing specific impulse which is done by increasing the exhaust core temperature. The fuel is selected in such a way so that the exhaust temperature would be obtained. The (U, Zr) Cgraphite fuel is selected because it has high uranium density and melting point is equivalent to exhaust core temperature which is sufficient enough to enhance the reactivity of the fissile material and thus to increase the rocket performance. A mathematical analysis shows that the percentage of mass of propellant used in mars mission will be lesser than the chemical rockets because the specific impulse is expected to be more in nuclear propulsion. The specific impulse obtained from the CFD Analysis of rocket nozzle is 979 sec with exit velocity of 9604m/s.

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Nuclear Electric Propulsion for Rapid Transportation Within the Solar System

Morrison¹

2021

Encyclopedia of Nuclear Energy

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Advancements in the Development of Low Enriched Uranium Nuclear Thermal Rockets

Cited by 5 publications

References 7 publications

Thrust Augmentation and its Control Methods: Short Overview

Thrust Augmentation and its Control Methods: Short Overview

Low Enriched Uranium based Nuclear Rocket Propulsion Technology: Mars Exploration Mission

Nuclear Electric Propulsion for Rapid Transportation Within the Solar System

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