IEEE - Aerospace and Electronic Systems - July 2022 - 23
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validation were found by simulation, as discussed in the
" Orbital Analysis " section.
ORBITAL ANALYSIS
The foundational application of consideration for this
work is laser pointing from the deep space environment,
and specifically within the Mars-Earth system. The relatively
long and varying range distances (approximately
0.4-2.7 AU), coupled with the extreme environmental
configurations and minimum mass constraints, creates a
formidable pointing challenge. Most commercial-off-theshelf
(COTS) solutions fall short of the requisite specifications,
which creates an opportunity to develop new technology
to address the mission needs. Beyond that, the
Mars-Earth system should be considered only as a starting
point, and any developed technologies should include
extensibility to Jovian distances in order to expand the
infusion potential for future mission scenarios.
Previous work has proposed planetary orbiter solutions
with a primary function of providing local communication
services, by considering higher altitudes (5000 km) to
maximize over-the-horizon visibility to both surface assets
and other orbiting spacecraft [11]. Such a strategy promises
an order ofmagnitude increase in transmitted data volumes
over lower altitude orbiters. Although significant progress
was made toward accomplishing that goal through the
Mars Telecommunication Orbiter effort [12], since then
the Agency has moved to a mission model in which spacecraft
need to maximize multifunctionality rather than focus
on a single purpose. In terms of an orbital mission profile,
this results in an altitude compromise down to hundreds of
kilometers to support acceptable imaging resolution with
the nadir-facing instruments on the spacecraft.
Using the Mars Reconnaissance Orbiter (MRO) as a
case study to conceptualize future payload requirements,
Figure 2.
Azimuth/elevation reference frame relative to the spacecraft.
(Note: Here and in Table 1, the term " elevation " refers to the
complement of the angle traditionally used in telescope reference
frames.)
Figure 1.
Illustration ofMRO scientific orbit.
Figure 3.
Illustration of Mars orbit. A scientific orbit requires a rapid slew
rate on the dark side of the planet, so that the communications
payload is in position to resume communication when the period
of occlusion ends.
JULY 2022
IEEE A&E SYSTEMS MAGAZINE
23
IEEE - Aerospace and Electronic Systems - July 2022
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