1. Mechanical Design for CubeSat Mission to Mars Study
The Mission Planning Lab conducts one-week long
CubeSat studies to assist a principal investigator,
or group of scientists, in designing a CubeSat
mission for their proposal. The most recent study
was a 6U (6U = 10 x 20 x 30 cm) CubeSat mission to
Phobos with one of the biggest challenges being the
volume constraints. Deployable solar arrays were
needed on the 2U by 3U faces, a deployable
antenna was needed on a 1U by 3U face, and a
propulsion system was needed with enough fuel to
travel to Mars and enter orbit around Phobos. The
science requirements, additional subsystems, and
mass also needed to be taken into account when
arranging the components within the CubeSat.
Mentor: Benjamin Cervantes, NASA Wallops Flight Facility, Mission Planning Lab, Code 589
Presented by: Lindsay Podsiadlik, University of Michigan, Mechanical Engineering
A CAD model was generated using Inventor and
went through several revisions throughout the week
as subsystems were updated and dimensions
changed. By using a propulsion system that only
required 1U of fuel and had a vertical dimension of
9.5 cm, all of the components were able to fit within
the 6U volume and all subsystem requirements
were met. The completed CubeSat design was then
presented to the principal investigator to be used in
their mission funding proposal.
Project Overview
Background Image: Phobos, courtesy of NASA Astronomy Picture of the Day http://apod.nasa.gov/apod/ap100317.html
Stowed solar arrays and antenna configuration.
Dimensions: 239.40 x 112.78 x 366.00 mm
366
mm
239 mm
+Z
+Y
+X
113 mm
Science &
Science Electronics
Battery
IRIS LNA
IRIS SSPA
EPS
IRISCHREC
Computer
Iodine Fuel Tank
Thruster
MIN-0
Thrusters
Deployment
Switch
XACT
Internal Layout
Power, Communications, Propulsion, Attitude
Control Systems, and Command & Data Handling
subsystems fit in available 6U volume with the
Science Instrument and Electronics.
Empty space needed for mounting, bracketry,
wires, cables, and more fuel. Baseplate and side
panels will possibly be used as thermal radiators.
Design Challenges
• Initial rough estimate for volume much greater than
allowed 6U
• Initial power estimates required up to eight 6U solar
panel arrays, taking up at least 2 cm in Y-direction
• CubeSat propulsion systems are all in early stages of
development and take up a large volume for the
thruster and fuel needed to get to Mars and enter
orbit about Phobos
• IRIS transceiver required component; large 0.5U
volume that generates a lot of heat
• Large antenna needed to communicate science and
spacecraft telemetry data back to Earth
• Component trades and arrangement to fit in 6U
• Four high-efficiency 6U solar panels provide enough
power and take up less height in Y-direction
• Smaller volume thruster and 1U of iodine fuel
• IRIS in optimal orientation and connected to
dedicated radiator away from other heat generating
components
• 30 x 30 cm deployable tri-fold antenna on –X face
Design Solutions
Deployed solar arrays and antenna configuration
