One Variant of Manned Mission to Mars with a Nuclear Electric Propulsion

2011 ◽  
Vol 1 (2) ◽  
pp. 1-17 ◽  
Author(s):  
M. S. Konstantinov ◽  
H. W. Loeb ◽  
V. G. Petukhov ◽  
G. A. Popov
Keyword(s):  
Electric Propulsion ◽  
Space Mission ◽  
Optimization Criterion ◽  
Low Earth Orbit ◽  
Problem Definition ◽  
Specific Mass ◽  
Propulsion Systems ◽  
Propulsion Efficiency ◽  
Mass Minimization ◽  
Low Mass

In this paper, one possible way for implementing a manned mission to Mars is examined. Typical peculiarities of the mission are as follows: the nuclear electric propulsion; relatively low mass of the spacecraft at a low Earth orbit (200 tons) and the crew time in flight is high (900-1000 days). Space mission analysis of the chosen variant is performed. As an optimization criterion, the authors chose the fuel mass required for the flight. Under examined problem definition such mass minimization is equivalent to maximal final mass of the spacecraft and maximal permissible total mass of power and electric propulsion systems. The authors show that to implement the examined manned mission, it is necessary to create the nuclear electric power and electric propulsion systems with a specific mass lower than 12.5 kg/kW under propulsion efficiency of 0.8, specific mass of the system for propellant storage of 0.05 and manned spacecraft complex mass of 52.1 tons. Under propulsion efficiency of 0.7, specific mass of power-propulsion should be lower than 10.9 kg/kW.

scholarly journals Introduction to Plasma Based Propulsion System: Hall Thrusters

2021 ◽  
Author(s):  
Sukhmander Singh ◽  
Sanjeev Kumar ◽  
Shravan Kumar Meena ◽  
Sujit Kumar Saini
Keyword(s):  
Electric Propulsion ◽  
Low Earth Orbit ◽  
Current Status ◽  
Earth Orbit ◽  
Hall Thrusters ◽  
Small Satellite ◽  
Propulsion Systems ◽  
Small Satellites ◽  
Long Time ◽  
The Cost

Technically, there are two types of propulsion systems namely chemical and electric depending on the sources of the fuel. Electrostatic thrusters are used for launching small satellites in low earth orbit which are capable to provide thrust for long time intervals. These thrusters consume less fuel compared to chemical propulsion systems. Therefore for the cost reduction interests, space scientists are interested to develop thrusters based on electric propulsion technology. This chapter is intended to serve as a general overview of the technology of electric propulsion (EP) and its applications. Plasma based electric propulsion technology used for space missions with regard to the spacecraft station keeping, rephrasing and orbit topping applications. Typical thrusters have a lifespan of 10,000 h and produce thrust of 0.1–1 N. These devices have E→×B→ configurations which is used to confine electrons, increasing the electron residence time and allowing more ionization in the channel. Almost 2500 satellites have been launched into orbit till 2020. For example, the ESA SMART-1 mission (Small Mission for Advanced Research in Technology) used a Hall thruster to escape Earth orbit and reach the moon with a small satellite that weighed 367 kg. These satellites carrying small Hall thrusters for orbital corrections in space as thrust is needed to compensate for various ambient forces including atmospheric drag and radiation pressure. The chapter outlines the electric propulsion thruster systems and technologies and their shortcomings. Moreover, the current status of potential research to improve the electric propulsion systems for small satellite has been discussed.

scholarly journals A Review of Low-Power Electric Propulsion Research at the Space Propulsion Centre Singapore

Aerospace ◽  
2020 ◽  
Vol 7 (6) ◽  
pp. 67 ◽  
Author(s):  
George-Cristian Potrivitu ◽  
Yufei Sun ◽  
Muhammad Wisnuh Aggriawan bin Rohaizat ◽  
Oleksii Cherkun ◽  
Luxiang Xu ◽  
...  
Keyword(s):  
Low Power ◽  
Electric Propulsion ◽  
Form Factors ◽  
Low Earth Orbit ◽  
Earth Orbit ◽  
Small Satellite ◽  
Space Propulsion ◽  
Propulsion Systems ◽  
Small Satellites ◽  
Plasma Thruster

The age of space electric propulsion arrived and found the space exploration endeavors at a paradigm shift in the context of new space. Mega-constellations of small satellites on low-Earth orbit (LEO) are proposed by many emerging commercial actors. Naturally, the boom in the small satellite market drives the necessity of propulsion systems that are both power and fuel efficient and accommodate small form-factors. Most of the existing electric propulsion technologies have reached the maturity level and can be the prime choices to enable mission versatility for small satellite platforms in Earth orbit and beyond. At the Plasma Sources and Applications Centre/Space Propulsion Centre (PSAC/SPC) Singapore, a continuous effort was dedicated to the development of low-power electric propulsion systems that can meet the small satellites market requirements. This review presents the recent progress in the field of electric propulsion at PSAC/SPC Singapore, from Hall thrusters and thermionic cathodes research to more ambitious devices such as the rotamak-like plasma thruster. On top of that, a review of the existing vacuum facilities and plasma diagnostics used for electric propulsion testing and characterization is included in the present research.

scholarly journals A Comprehensive Review of Atmosphere-Breathing Electric Propulsion Systems

2020 ◽  
Vol 2020 ◽  
pp. 1-21
Author(s):  
Peng Zheng ◽  
Jianjun Wu ◽  
Yu Zhang ◽  
Biqi Wu
Keyword(s):  
Electric Propulsion ◽  
Low Earth Orbit ◽  
Propulsion System ◽  
Earth Orbit ◽  
Space Propulsion ◽  
Propulsion Systems ◽  
Comprehensive Review ◽  
The Past ◽  
Atmospheric Molecules ◽  
The Future

To develop the satellites for a low-Earth-orbit environment, atmosphere-breathing electric propulsion (ABEP) systems have become more attractive to researchers in the past decade. The system can use atmospheric molecules as the propellant to provide thrust compensation, which can extend the lifetime of spacecraft (S/C). This comprehensive review reviews the efforts of previous researchers to develop concepts for ABEP systems. Different kinds of space propulsion system are analysed to determine the suitable propulsion for atmosphere-breathing S/C. Further discussion about ABEP systems shows the characteristic of different thrusters. The main performance of the ABEP system of previous studies is summarized, which provides further research avenues in the future. Results show great potential for thrust compensation from atmospheric molecules. However, the current studies show various limitations and are difficult to apply to space. The development of ABEP needs to solve some problems, such as the intake efficiency, ionization power, and electrode corrosion.

scholarly journals An advance in transfer line chilldown heat transfer of cryogenic propellants in microgravity using microfilm coating for enabling deep space exploration

2021 ◽  
Vol 7 (1) ◽  
Author(s):  
J. N. Chung ◽  
Jun Dong ◽  
Hao Wang ◽  
S. R. Darr ◽  
J. W. Hartwig
Keyword(s):  
Space Exploration ◽  
Fluid Management ◽  
Microgravity Condition ◽  
Space Mission ◽  
Low Earth Orbit ◽  
Earth Orbit ◽  
Deep Space ◽  
Deep Space Exploration ◽  
Quenching Efficiency ◽  
Proper Perspective

AbstractThe extension of human space exploration from a low earth orbit to a high earth orbit, then to Moon, Mars, and possibly asteroids is NASA’s biggest challenge for the new millennium. Integral to this mission is the effective, sufficient, and reliable supply of cryogenic propellant fluids. Therefore, highly energy-efficient thermal-fluid management breakthrough concepts to conserve and minimize the cryogen consumption have become the focus of research and development, especially for the deep space mission to mars. Here we introduce such a concept and demonstrate its feasibility in parabolic flights under a simulated space microgravity condition. We show that by coating the inner surface of a cryogenic propellant transfer pipe with low-thermal conductivity microfilms, the quenching efficiency can be increased up to 176% over that of the traditional bare-surface pipe for the thermal management process of chilling down the transfer pipe. To put this into proper perspective, the much higher efficiency translates into a 65% savings in propellant consumption.

Electromagnetic emission experiences using electric propulsion systems

1989 ◽  
Vol 5 (5) ◽  
pp. 534-547 ◽  
Author(s):  
James S. Sovey ◽  
Lynnette M. Carney ◽  
Steven C. Knowles
Keyword(s):  
Electric Propulsion ◽  
Electromagnetic Emission ◽  
Propulsion Systems
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