Nuclear Electric Propulsion / Chemical Propulsion Hybrid Human Mars Exploration Campaign: First Mars Surface Mission

It was realized earlier that chemical propulsion systems utilize fuel very inefficiently, which greatly limits their lifespan. Electric propulsion is into existence to overcome this limitation of chemical propulsion. The magnetoplasmadynamic (MPD) thruster is presently the most powerful form of electromagnetic propulsion. It is the thruster’s ability to efficiently convert MW of electric power into thrust which gives this technology a potential to perform several orbital as well as deep space missions. MPD thruster offers distinct advantages over conventional types of propulsion for several mission applications with its high specific impulse and exhaust velocities. However, MPD thruster has limitations which limits its operational efficiency and lifetime. In this paper, the thruster limitations are reviewed with respect to three operational limits i.e., the onset phenomenon, cathode lifetime, and thruster overfed limits. The dependence and effects of the operational limits on each other is compared using different empirical models to derive a scaling factor that has been found for each geometrical arrangement; a limiting value exists beyond which the operation becomes highly unsteady and electrode erosion occurs. Along with reviewing and proposing methods to overcome power limitations for MPD thrusters, the relation between exit velocity and ratio of electrode’s radius is also verified using Maecker’s formula.

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An L1 Based Integration Node for Lunar and Mars Exploration with Solar Electric Propulsion for LEO to L1 and Mars Transfer

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit ◽

10.2514/6.2011-5715 ◽

2011 ◽

Author(s):

Benjamin Donahue ◽

Mike Farkas ◽

Mike Raftery ◽

Kevin Post

Keyword(s):

Electric Propulsion ◽

Mars Exploration ◽

Solar Electric Propulsion ◽

Integration Node

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Hall Thruster: An Electric Propulsion through Plasmas

Selected Topics in Plasma Physics ◽

10.5772/intechopen.91622 ◽

2020 ◽

Author(s):

Sukhmander Singh

Keyword(s):

Plasma Physics ◽

Electric Propulsion ◽

Life Time ◽

Terahertz Wave ◽

Space Science ◽

Hall Thruster ◽

Plasma Fusion ◽

Mathematical Relation ◽

Chemical Propulsion ◽

High Thrust

The chapter discussed the technological application of plasma physics in space science. The plasma technology is using laser-plasma fusion, inertial fusion, Terahertz wave generation and welding of metals. In this chapter, the application of plasma physics in the field of electric propulsion and types has been discussed. These devices have much higher exhaust velocities, longer life time, high thrust density than chemical propulsion devices and useful for space missions with regard to the spacecraft station keeping, rephrasing and orbit topping applications. The mathematical relation has been derived to obtain the performance parameters of the propulsion devices.

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A Conceptual Mars Exploration Vehicle Architecture with Chemical Propulsion, Near-Term Technology, and High Modularity to Enable Near-Term Human Missions to Mars

AIAA SPACE 2015 Conference and Exposition ◽

10.2514/6.2015-4611 ◽

2015 ◽

Cited By ~ 1

Author(s):

Mark G. Benton

Keyword(s):

Mars Exploration ◽

Vehicle Architecture ◽

Near Term ◽

Chemical Propulsion

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Micropropulsion Development at the ARC Seibersdorf Research

CANEUS2006: MNT for Aerospace Applications ◽

10.1115/caneus2006-11006 ◽

2006 ◽

Author(s):

Carsten Arthur Scharlemann ◽

Martin Tajmar

Keyword(s):

Hydrogen Peroxide ◽

Electric Propulsion ◽

Specific Impulse ◽

Electrical Power ◽

Preliminary Test ◽

Small Mass ◽

Space Missions ◽

Propulsion Systems ◽

Future Space ◽

Chemical Propulsion

The increasing application of micro-satellites (from 10 kg up to 100 kg) for a rising number of various missions demands the development of new miniaturized propulsion systems. Micro-satellites have special requirements for the propulsion system such as small mass, reduced volume, and very stringent electrical power constraints. Existing propulsion systems often can not satisfy these requirements. The Space Propulsion Department of the ARC Seibersdorf research dedicated itself to the development and test of various micropropulsion systems for present and future space missions. The portfolio of the systems under development includes electrical and chemical propulsion systems. The covered thrust and specific impulse of the developed propulsion systems ranges from 1μN to 1N and 500 s to 8000 s respectively. Based on the large experience obtained over several decades in the development of Field Emission Electric Propulsion systems (FEEP), several microstructured FEEPs have been developed. The design of these systems is presented as well as preliminary test results and a summarization of the experience obtained during the process of miniaturizing such systems. The development of miniaturized chemical propulsion systems includes a bipropellant and a monopropellant thruster. The bipropellant thruster constitutes the smallest existing 1N thruster utilizing hydrogen peroxide. The thruster system consists of two micopumps for the propellant feed and a microturbine to generate the power for operating the pumps. The monopropellant thruster is a derivative of the bipropellant thruster. It offers a lower specific impulse than the bipropellant system but due to its reduced system complexity it represents also a promising candidate for several future space missions. Both systems utilize rocket grade hydrogen peroxide (green propellant), which is decomposed with the help of an advanced monolithic catalyst. The present paper discusses the design methods and the physical limitations of such chemical propulsion systems with regard to their miniaturization and summarizes their performance evaluation.

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Investigation of Variation in the Performance of an Electro Thermal Thruster with Aerospike Nozzle

Advanced Engineering Forum ◽

10.4028/www.scientific.net/aef.16.91 ◽

2016 ◽

Vol 16 ◽

pp. 91-103

Author(s):

Pranav Menon

Keyword(s):

Electric Propulsion ◽

Specific Impulse ◽

Velocity Variation ◽

Propulsion Systems ◽

Exit Velocity ◽

Hot Plasma ◽

Exit Nozzle ◽

Ion Propulsion ◽

Aerospike Nozzle ◽

Chemical Propulsion

One of the most recently developed modes of propulsion is electric propulsion. The commonly used chemical propulsion systems have the advantage of a high Specific Impulse as compared to that of ion propulsion systems. However, owing to the efficacy of ion propulsion systems, it is considered the future of space exploration.Electro thermal thrusters produce thrust by using electrical fields to force hot plasma out of the nozzle with certain exit velocity. The plasma’s exit velocity and the system’s thrust capacity, as of now, are insufficient for space travel to be conducted within a reasonable time. I intend to study the possibility of improving the thruster’s performance by using an aerospike nozzle as an exit nozzle which meets the conditions required for the thruster to function appropriately. I shall be studying the plasma plume exit velocity variation with respect to the nozzles used. Also, a thermal analysis will be conducted in order to find the correct material for the nozzle.

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