&lt;p&gt;We propose to develop and test a proof of concept prototype for a standard CubeSat form factor platform, designed for missions to &lt;u&gt;deep space&lt;/u&gt; targets, as opposed to the conventional LEO CubeSat venue to date.&amp;nbsp; In testing, we will focus on the &amp;ldquo;tall poles&amp;rdquo; identified in the FY13 LunarCube IRAD study, for a variety of lunar targets. Tall poles include thermal issues, radiation effects, adequate power, communication links, limited mass and volume for subsystems, and propulsion from Earth to the target. Lunar applications, like the LWaDi &lt;u&gt;l&lt;/u&gt;unar &lt;u&gt;wa&lt;/u&gt;ter &lt;u&gt;di&lt;/u&gt;stribution CubeSat orbiter, typically have major thermal challenges as a &amp;ldquo;tall pole&amp;rdquo;, especially when the detectors need to be cooled or the packaging is very dense.&amp;nbsp; For this IRAD, we will &lt;em&gt;perform relevant thermal vacuum testing of the prototype platform using the detailed LWaDi mission thermal profile, to confirm that the design for LWaDi and similar missions will work and to drive the deep space CubeSat platform to a design level that is ready for external proposals&lt;/em&gt;.&amp;nbsp; Other constraints, including propulsion, power, attitude control, C&amp;amp;DH, and communications, will continue to be analyzed in parallel with thermal testing, and relevant, reusable COTS parts will be included in the prototype, per available funding.&amp;nbsp; It should be noted that the discipline engineering team assembled for the FY13 IRAD will be available to significantly advance the prototype model. The &lt;u&gt;end product&lt;/u&gt; will be a hardware CubeSat bus design (6U for deployment at the final target, 9U for deployment from GEO requiring a robust propulsion system to reach the target) that is understood from thermal, mechanical, and other perspectives, and ready for flight development.&amp;nbsp; As an additional payoff, we will also work to apply relevant test results to other mission profiles that we are developing, including impactors and surface instruments based on CubeSat standards, with various trajectories and life times.&lt;/p&gt;&lt;p&gt;In addition, we propose to deliver a detailed design and development plan, and to test a prototype of the optical subsystem, the component which represent the greatest &amp;lsquo;compactness&amp;rsquo; challenge of a compact yet capable version of a cubesat &amp;lsquo;work horse&amp;rsquo; instrument, an extremely compact (&amp;lt;2U) high spectral resolution (10nm), broadband IR spectrometer capable of measuring volatiles (water type and component, organics) and Fe- and Ti-bearing mineral distribution on a broad range of solar system bodies, including the Moon, where we propose to use it to determine water type (bound, adsorbed, ice) and component distribution from spectral features in the 1.3 to 3.7 um range for the LWaDi (Lunar Water Distribution) mission.&lt;/p&gt;