Powerpoint template for scientific posters (Swarthmore College)

SPACE HAUC

Science Program Around Communications Engineering

with High Achieving Undergraduate Cadres

Lowell Center for Space Science and Technology (LoCSST)

Dat Le, Program Manager - [email protected]

NEXT STEPS

News Flash! Less than 2 weeks ago, the National Aeronautics

and Space Administration (NASA) selected SPACE HAUC for

Undergraduate Student Instrument Project (USIP) funding!

The preliminary conceptual design of the satellite shall continue into

Summer 2016 and beyond. As the design is reviewed and improved

upon, SPACE HAUC shall transition into the test and development

phase where the team shall begin validating the design and

constructing the physical satellite.

The Lowell Center for Space Science and

Technology (LoCSST) provides a home for

space science and technology research

activities on the UMass Lowell campus. Our

goal is to involve industry partners in

curriculum, research, projects and

proposals/business development while

training the next generation of space

scientists, technologists, teachers, business

leaders, and policy makers.

www.uml.edu/research/LoCSST

First conceptual rendering of the SPACE HAUC 3U CubeSat – solar panels are depicted in the

deployed position with a high-resolution camera taking images of the sun

MISSION

SPACE HAUC will demonstrate the practicality of high data rate X-

band communications using a phased array of patch antennas to

achieve dynamic beam steering on a CubeSat platform. This

allows for the satellite to maximize gain and by extension achieve

a very high data rate. SPACE HAUC plans to launch a 3U CubeSat

(10 cm x 10 cm x 30 cm, 4 kg).

BACKGROUND

SPACE HAUC is a multidisciplinary astronautical engineering

research and development project that aims to launch UMass

Lowell’s first satellite: a CubeSat.

A CubeSat is a miniaturized satellite used for conducting space

research. A 1U CubeSat is a 10 cm cube weighing no more than

1.33 kg. The use of CubeSats as an educational tool at the

University level has grown exponentially over the past few years

due to their small size, low cost, and short development time.

Many CubeSats settle for simple dipole antennas communicating

in the S-band. While easy to implement, these simplistic satellite

communications arrays limit the maximum data transfer to no

more than 2 – 5 Mbps. For future CubeSat applications

(formations of satellites, interplanetary missions), the

communications system must be more advanced.

In one example of a low-inclination (28°) orbit analysis, our team can analyze the amount of incident

radiation on surfaces of interest during the detumble stage when the spacecraft is spinning wildly. These

results will help inform our placement and sizing of required solar panels

DESIGN CHALLENGES and

SOLUTION / APPROACH

 Selection of low-outgassing materials

 Strict mass, power, and link budgets with margins

 Survive induced stress and shock/vibration due to launch vehicle

 Minimum power required by magnetorquers and on-board

computer during tumbling period

 Protection against harsh thermal radiation environment

 Ensure radiation tolerance to long-term dosage and single-event

upsets (SEU)

 Patch antenna and phase shifter integrated PCB

 Telemetry of mission data to be sent back to Earth via X-band

transmitter

 Distribution of power to all subsystems collectively requiring 15 W

 … and many more!

Our approach to overcoming these challenges begins with extensive

review of published literature and existing CubeSat documentation.

Then design solutions are generated by the team to be explored,

characterized, and applied to the challenges specific to SPACE HAUC.

Through an iterative process, the final design is chosen and testing

and validation begins. As our models are verified, the satellite shall

take form and in time be ready for launch.

References:

https://directory.eoportal.org/web/eoportal/satellite-missions/t/tecsar

http://www.radartutorial.eu/06.antennas/Phased%20Array%20Antenna.en.html

https://www.sparkfun.com/products/13034

http://www.thespacereview.com/article/1490/1

https://upload.wikimedia.org/wikipedia/commons/f/fd/Wannalancit_Mills_-_University_of_Massachusetts_Lowell_-_DSC00092.JPG

https://www.teachengineering.org/engrdesignprocess.php

50+ STUDENTS ACROSS SEVERAL SUBSYSTEM TEAMS

SPACE HAUC Organizational Chart; SPACE HAUC currently has 50+ students involved

in the ongoing design and development of the CubeSat

ACKNOWLEDGEMENTS

Thank you to NASA and the MASGC for funding our project.

Thank you to Professor John Palma (EE) and Professor Christopher Hansen (ME) for

their advisement and supervision in all matters related to Capstone projects.

Thank you to BAE Systems and Draper Laboratory for supporting our project from the

beginning by offering facilities and the guidance of your experienced staff.

Thank you Raytheon, the Raytheon UMass Lowell Research Institute (RURI), and to Mr.

Tom Sikina for your collective expertise and guidance regarding telemetry and

antennas.

And a big thank you to Professor Supriya Chakrabarti and Professor Tim Cook of the

Lowell Center for Space Science and Technology (LoCSST) for creating this project and

allowing for UMass Lowell students to become involved in space research and

development.

PROPOSED ANTENNA PARAMETERS

 Frequency Range: 8.0 to 8.4 GHz

 Polarization: Circular

 Number of elements: 16 (4 x 4)

 Array size: Square, within area of 8.1 cm x 8.1 cm

 Beam width: 27°(approximation)

 Range: 450 km, consistent with low-Earth orbit (LEO)

 Data Rate: Goal of 50 – 100 Mbps

Visualization of the antenna lobe containing maximum power created in MATLAB

by the beam steering team (left) and a schematic detailing the main direction of

the wavefront after phase shifting (right)

PHASED ARRAY ANTENNA

Beam steering will be achieved with a combination of patch

antennas and phase shifters. The phase shifters act as a means to

delay the delivery of voltage to each element, such that the

output radiation pattern of each antenna element constructively

and destructively interferes. As a result, the main lobe, which

contains the maximum power, is dynamically steered toward the

ground station below. When the CubeSat’s camera and

deployable solar panels are nominally pointed towards the sun,

the current plan is to mount the antennas on the opposite

satellite face.