Electric Propulsion applications for lunar Cargo missions

Paper number

IAC-06-D2.7.-A3.7.10

Author

Mr. Rafael Contreras Fernandez, Escuela Técnica Superior de Ingenieros Aeronáuticos, Spain

Coauthor

Mr. Karanjeet Singh, PlanetSpace Inc., Canada

Year

2006

Abstract

Different nations are currently developing a number of plans to put man back on the moon by 2020. The natural extension of returning humankind to the Moon is to create a permanent presence there. This implies that large amount of cargo must be transported on a regular basis to the Moon, so there is a need to develop new techniques to create an economical way of achieving this goal.

The success of the SMART-1 mission demonstrates Electric Propulsion as a valid propulsion method that can be employed to reduce the amount of propellant needed for the mission. This paper will study the use of Electric Propulsion in order to transport cargo to the moon, and the requirements that such systems will have to fulfil. The main advantage of using Electric Propulsion over traditional liquid/solid propellants is the reduction in the weight budget, due mainly to the reduction in the amount of propellant needed and the use of solar energy as the main power source. Electric Propulsion gives an Isp higher than liquid or solid propellant rocket engines, with a lower thrust, with a consequent increase in the duration of the mission. Hence, comparing these methods to traditional propulsion techniques, we could find Electric Propulsion to be much cheaper and feasible for a cargo mission, and also able to be employed for longer missions like those directed to Mars.

The paper will review in the first place the requirements of a cargo mission to the Moon, especially in terms of delta-v, proposing a typical mission that will be used as a reference. There are specific restraints on a cargo mission that are different from those of a manned mission, which will be addressed in the paper. The paper will be organised in a manner of a comparative study of different Electric Propulsion technologies, supported by numerous analysis for different variables that can affect the mission: trajectory, propellant weight, power consumption, specific impulse, fuel, thruster maintenance, time required to accomplish the mission, etc. These results will be compared to traditional liquid, solid and hybrid rocket engines, being able this way to recognize the edges and flaws of each technique, and concluding which propulsion system will be the best one for the reference mission.

Abstract document

IAC-06-D2.7.-A3.7.10.pdf

Manuscript document

IAC-06-D2.7.-A3.7.10.pdf (🔒 authorized access only).

To get the manuscript, please contact IAF Secretariat.