A Linear Formation Flying Astronomical Interferometer in Low Earth Orbit. (arXiv:1912.02350v1 [astro-ph.IM])
<a href="http://arxiv.org/find/astro-ph/1/au:+Hansen_J/0/1/0/all/0/1">Jonah T. Hansen</a>, <a href="http://arxiv.org/find/astro-ph/1/au:+Ireland_M/0/1/0/all/0/1">Michael J. Ireland</a>
Space interferometry is the inevitable endpoint of high angular resolution
astrophysics, and a key technology that can be leveraged to analyse exoplanet
formation and atmospheres with exceptional detail. However, the anticipated
cost of large missions such as Darwin and TPF-I, and inadequate technology
readiness levels have resulted in limited developments since the late 2000s.
Here, we present a feasibility study into a small scale formation flying
interferometric array in Low Earth Orbit, that will aim to prove the technical
concepts involved with space interferometry while still making unique
astrophysical measurements. We will detail the proposed system architecture and
metrology system, as well as present orbital simulations that show that the
array should be stable enough to perform interferometry with < 50m/s/year
delta-v and one thruster per spacecraft. We also conduct observability
simulations to identify which parts of the sky are visible for a given orbital
configuration. We conclude with optimism that this design is achievable, but a
more detailed control simulation factoring in a demonstrated metrology system
is the next step to demonstrate full mission feasibility.
Space interferometry is the inevitable endpoint of high angular resolution
astrophysics, and a key technology that can be leveraged to analyse exoplanet
formation and atmospheres with exceptional detail. However, the anticipated
cost of large missions such as Darwin and TPF-I, and inadequate technology
readiness levels have resulted in limited developments since the late 2000s.
Here, we present a feasibility study into a small scale formation flying
interferometric array in Low Earth Orbit, that will aim to prove the technical
concepts involved with space interferometry while still making unique
astrophysical measurements. We will detail the proposed system architecture and
metrology system, as well as present orbital simulations that show that the
array should be stable enough to perform interferometry with < 50m/s/year
delta-v and one thruster per spacecraft. We also conduct observability
simulations to identify which parts of the sky are visible for a given orbital
configuration. We conclude with optimism that this design is achievable, but a
more detailed control simulation factoring in a demonstrated metrology system
is the next step to demonstrate full mission feasibility.
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