JPL Technical Report Server

Mars Relay Spacecraft: A Low-Cost Approach

Show simple item record

dc.contributor.author SvitekT, . en_US
dc.contributor.author King, J.
dc.contributor.author Fulton, R.
dc.contributor.author McOmber, R.
dc.contributor.author Hastrup, R.
dc.contributor.author Miller, A.
dc.date.accessioned 2004-10-02T17:44:57Z
dc.date.available 2004-10-02T17:44:57Z
dc.date.issued 1995-09
dc.identifier.citation AIAA/Utah State University Conference on Small Satellites, Logan, Utah, September 1995 en_US
dc.identifier.clearanceno 95-0692
dc.identifier.uri http://hdl.handle.net/2014/29877
dc.description.abstract The next phase of Mars exploration will utilize numerous globally distributed small low-cost devices including landers penetrators microrovers and balloons. Direct-to-Earth communications links if required for these landers will drive the lander design for two reasons: a) mass and complexity needed for a steerable high-gain antenna and b) power requirements for a high-power amplifier (i.e. solar panel and battery mass). Total mass of the direct link hardware for several recent small-lander designs exceeded the mass of the scientific payload. Alternatively if communications are via a Mars-orbiting relay spacecraft resource requirements for the local UHF communication link are comparatively trivial: a simple whip antenna and less than 1 watt power. Clearly using a Mars relay spacecraft (MRS) is the preferred option if the MRS mission can be accomplished in an affordable and robust way. Our paper describes a point design for such a mission launched in the s001 or 2003 opportunity. en_US
dc.format.extent 24739 bytes
dc.format.mimetype application/pdf
dc.language.iso en_US
dc.subject.other Mars Relay Spacecraft en_US
dc.title Mars Relay Spacecraft: A Low-Cost Approach en_US


Files in this item

This item appears in the following Collection(s)

Show simple item record

Search


Browse

My Account