Challenges and innovative technologies for a low cost lunar mission

Roeser, Hans─Peter; Auweter‐Kurtz, Monika; Wagner, Henri; Laufer, René; Podhajsky, Sandra; Wegmann, Thomas; Huber, Felix

doi:10.1016/j.actaastro.2005.07.048

Cited by 3 publications

(3 citation statements)

References 3 publications

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“…If the lunar mission demands a greater than 10 year lifetime of the constellation, then further analysis would provide the specifications for ion engine sizing, solar arrays, and batteries. From preliminary studies done by Roeser et al, the increase in mass was on the order of 100 kg [9].…”

Section: Discussionmentioning

confidence: 97%

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Lunar relay satellite capabilities via re-use of delivery vehicle modules

Miller

Dusold

Fraietta

et al. 2009

2009 IEEE Aerospace Conference

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Lunar communications can be problematic for mission success when trading multiple objectives such as reduced mass, landing trajectory, and the need for communication with other orbiting vehicles and ground stations. To this end, reusability of existing vehicle components─for purposes other than the original intent─is an enticing option. In the case of Constellation, the Ares upper stage instrument unit avionics IUA has promise for re-use as a lunar relay satellite. The guidance, navigation and control GNC avionics along with the electrical power system can be re-used to position the IUA into a suitable lunar orbit for use as a relay. The IUA can be inserted into a medium lunar orbit via re-use of the earth departure stage EDS for the lunar orbit insertion LOI burn. Additionally, the descent module from the Altair can be re-used as either a beacon on the lunar surface or as a relay node for surface operations. The ascent module can be reconfigured and reused as an orbiting relay satellite. The re-use of these modules would greatly improve the effective delivered mass. This specific instance of re-use improves the following mission objectives a) enhanced safety via improved situational awareness, b) increased public visibility of NASA's lunar mission, and c) higher volume of data for scientific discovery. We present an architecture for re-use of modules to populate a lunar communications satellite system. 12

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Section: Discussionmentioning

confidence: 97%

“…Roeser et al have investigated this issue and suggested using pulsed plasma thrusters [9]. They recommended an additional 75-85 kg for the total electrical propulsion system.…”

Section: Earth Departure Stage Lunar Orbit Insertionmentioning

confidence: 99%

Lunar relay satellite capabilities via re-use of delivery vehicle modules

Miller

Dusold

Fraietta

et al. 2009

2009 IEEE Aerospace Conference

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“…Beginning in a geo-transfer-orbit (GTO) the mission profile is designed to travel into a circular polar lunar orbit by using electrical propulsion systems which are also developed at the IRS space transportation workgroup [3], [4]. In reference to future human moon missions potential scientific objectives like stereoscopic imaging and digital mapping in high resolution enhanced with multispectral data represent an attractive contribution to lunar exploration.…”

Section: The Missionmentioning

confidence: 99%

Implementation of a Simulation Environment for Software and Hardware Simulation of Power Management for a Lunar Small Satellite Mission

2004

55th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronaut

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The University of Stuttgart plans an all electrical small satellite lunar mission. The usage of an electric propulsion system for the Earth-Moon transfer results in high and non-transient power demands while power input is dependent of the spacecraft orientation due to fixed mounted solar panels. A typical methodology designing a power supply system for a small satellite is to identify power management options and alternatives based on characteristic configurationally parameters. On one hand low battery capacities result in volume and mass savings but on the other hand in operation limitations like a specific sequence of successive operations and its duration. The engineering challenge of small satellite power supply system design is to optimize the trade-off between hardware limitations (volume and mass) and mission power requirements to fulfill the technical and scientific mission objectives. Therefore a power management software simulator is used to visualize effects on power management for different designs of power supply system and other satellite subsystems. By iterative hardware oriented optimization an adequate power supply system design was found.

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