Aerospace and Electronic Systems - April 2019 - 41
Campagnola et al.
Table 2.
Dv 99 Budget, m/s
Maneuver
2nd LFB (Full Succ)
Dy1
7.98
7.98
7.98
7.98
Dy1 extra
6.00
6.00
6.00
6.00
TCM1þCU1
20.00
20.00
20.00
20.00
Dy2
2.15
2.15
2.15
2.15
TCM2þCU2
10.00
10.00
10.00
Dy3
1.85
1.85
1.85
Dy4
0.22
0.22
0.22
TCMþCU extra
10.00
10.00
10.00
Station Keeping
1.40
16.3
Extra sK
1.40
16.3
61.0
90.8
Total Dy
36.1
EML2 arrival
58.2
TCM1, which also yields to larger CU1 (see [11], [12] for
details). Another 10 m/s are allocated for three-flyby solutions, which we found with different launch geometries.
Finally, the science orbit for the current baseline requires
only 1.40 m/s/month station keeping costs, because it is
not very unstable. Other 1.40 m/s/month are included to
represent a more typical station keeping cost.
Success criteria for the mission is currently defined as
navigating through the first lunar flyby and reach Earth-
Sun-Moon region, with extra success including subsequent
lunar flybys and capture into libration orbit. Before completion of the onboard Dv, the spacecraft will be disposed
into an Earth-escape orbit for space debris compliance.
DESIGN APPROACH
The EQUULEUS trajectory is very challenging because of
the fixed initial conditions, low thrust, and Dv capabilities,
and chaotic dynamics. The trajectory is split into a science
phase, a forward transfer phase, and a backward transfer
phase. In the science phase, we produce a database of
thousands of quasi-periodic orbits around the Earth-Moon
L2 libration point, computed in high-fidelity model with
no deterministic maneuvers for at least 180 days, and
evaluate their stability properties and station-keeping costs
[13]. A new approach is being developed to enforce the
recently added science and eclipse constraints. Figures 4
and 5 show an example 1: four synodic resonant periodic
orbit that avoids eclipses for six months and fulfill both of
the science requirements for large portions of its period.
APRIL 2019
1 month@EML2
(extra succ.)
1y@EML2
In the transfer phase, we compute millions of potential
transfer orbits, using the three degrees of freedom of Dv1
to map the initial states into apogees, and from the halo
orbits back to the same apogee [12]. For both the science
and transfer phases, first guess solutions are generated
patching trajectory bits computed in different models; the
first guess solutions are then optimized by jTOP [4] in
a high-fidelity model that includes Earth, Sun, and Moon
ephemerides and low-order gravitational harmonics of the
Earth and the Moon.
OMOTENASHI
OMOTENASHI [6] is the world's smallest lunar lander,
and is developed by JAXA. The mission objective is the
technology demonstration of a lunar semihard landing by
a CubeSat. OMOTENASHI will also observe the radiation
Figure 4.
EQUULEUS science orbit in the Sun-Moon rotating frame.
IEEE A&E SYSTEMS MAGAZINE
41
Aerospace and Electronic Systems - April 2019
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