Development of the Alaska Cubesat Auroral Plasma Spectrometer (ACAPS)

SCIENCE GOALS AND OBJECTIVES Observations illustrate that the fundamental processes that drive and modulate the auroral emissions are occurring on a wide range of spatial and temporal scales. Complete understanding of auroral dynamics cannot be achieved without simultaneous multi-point in situ observations of the particle dynamics at the spatial and temporal scales on which they occur. While satellite missions have provided excellent field and particle measurements, knowledge of the critical scale lengths remains ambiguous due to the limitations of single spacecraft observations. However, with the promise of constellations of small spacecraft and fast primary electron precipitation analyzers, such an array of satellites can separate and directly link the observed energized electron spectra to the associated spatial and temporal scales, thus providing critical insight into the processes driving and modulating the auroral emissions.

One of the premier instruments for aurora particle observations ever deployed, the Fast Auroral SnapshoT (FAST) ESAs provided 78 ms time resolution (up to 1.6 ms in burst mode with limited energy sampling). Our goal is to develop primary elements of a high time resolution auroral electron spectrometer (ACAPS) for CubeSats. ACAPS will provide high time resolution, non-distorting sensitivity control, and modest energy/angle resolution, for now. Accordingly, we cite four objectives, to be achieved within a 1U CubeSat resource envelope: 1. Design, build and perform beam testing and vibration testing on a prototype ESA mechanical model that meets specified performance and environmental requirements. 2. Demonstrate function of a non-distorting MCP sensitivity control for position sensitive counting instruments. 3. Design, build and perform beam testing and vibration testing on a prototype MCP detector and front end electronics for a 1D imaging system that meets specified requirements. 4. Integrate the ESA/Detector and perform end-to-end beam test to verify performance.

Achieving these objectives increases the ESA and Detector subsystems from TRL-2 to TRL-6 and enables observations necessary to answer our science questions. METHODOLOGY AND INSTRUMENT CONCEPT The goal is to implement ACAPS within resources for a 1U CubeSat instrument, with its entrance aperture viewing 360º x 10º from a stabilized 1U CubeSat unit (or 1U within a larger CubeSat). An important development aspect is a non-distorting count rate control feature in the Micro Channel Plate (MCP) stack that extends dynamic range by up to a factor of 100. This is accomplished by a Retarding Potential Analyzer (RPA) upstream of the last MCP stage. Resource minimization is a primary focus. We apply additive manufacturing (AM) techniques and the use of AM metals and plastics to minimize mass. The UAF GI and engineering departments have extensive machine shops with decades of experience in space flight instrument design and in both additive and subtractive manufacturing. Further, we use high resistance (lower max count rate) and custom shaped MCPs (minimize active area) to minimize HV current/power and mass/volume. This is enabled by our MCP/RPA sensitivity control approach.

IMPORTANCE AND RELEVANCE TO NASA This proposal addresses Key Science Question 2 from the most recent Heliophysics Decadal Survey: “Determine the dynamics and coupling of Earth’s magnetosphere, ionosphere, and atmosphere and their response to solar and terrestrial inputs” and follows the recommendation in the “Diversify” element of that document’s DRIVE initiative, in “targeting the development of very-small-satellite flight opportunities as a key growth area for both NASA and NSF”. This research also addresses Research Focus Area H3 from the most recent Heliophysics Roadmap, to “understand the coupling of the Earth's magnetosphere-ionosphere- atmosphere system, and its response to external and internal forcing”.

Support NASA's Heliophysics strategic science objectives to understand the Sun and its interactions with Earth and the solar system, including space weather. This will be achieved by developing/demonstrating instrumentation technology necessary to address the following science goals: Explore the physical processes in the space environment from the Sun to the Earth and throughout the solar system; Advance our understanding of the connections that link the Sun, the Earth, planetary space environments, and the outer reaches of our solar system; Develop the knowledge and capability to detect and predict extreme conditions in space to protect life and society and to safeguard human and robotic explorers beyond Earth.

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