TY  - GEN
AB  - CubeSats are small cost-effective satellites that provide a platform for students and
researchers to perform various experiments and conduct data acquisition in space. Many CubeSats
have mission plans that require them to reach a target altitude quickly, which is commonly
accomplished by incorporating one-time deployment mechanisms to increase drag. This project
investigates a mechanism designed to dynamically adjust the drag. This was done by researching
concepts for drag rate systems such as developable mechanisms, deployable solar arrays, and
origami-based drag sails. Based on the combination of performance criteria of least moving parts,
greatest possible area to increase drag, and highest potential of reliable deployment the design
chosen was an origami-based drag sail with tape spring booms. The anticipated reduction in deorbiting
time for the proposed design is 20%, with the drag sail fitting into a lU CubeSat, and a
possible deployed area of 0.414 m^. The concept chosen shows promise for increasing the drag to
de-orbit quickly and the reducing drag to maximize time at a desired altitude.
AD  - University of Southern Indiana
AU  - Marx, Joseph
DA  - 2019-11-19
DO  - 10.58090/usi.1559879
DO  - doi
ID  - 1559879
L1  - https://library.usi.edu/record/1559879/files/SP564.pdf
L2  - https://library.usi.edu/record/1559879/files/SP564.pdf
L4  - https://library.usi.edu/record/1559879/files/SP564.pdf
LA  - eng
LK  - https://library.usi.edu/record/1559879/files/SP564.pdf
N2  - CubeSats are small cost-effective satellites that provide a platform for students and
researchers to perform various experiments and conduct data acquisition in space. Many CubeSats
have mission plans that require them to reach a target altitude quickly, which is commonly
accomplished by incorporating one-time deployment mechanisms to increase drag. This project
investigates a mechanism designed to dynamically adjust the drag. This was done by researching
concepts for drag rate systems such as developable mechanisms, deployable solar arrays, and
origami-based drag sails. Based on the combination of performance criteria of least moving parts,
greatest possible area to increase drag, and highest potential of reliable deployment the design
chosen was an origami-based drag sail with tape spring booms. The anticipated reduction in deorbiting
time for the proposed design is 20%, with the drag sail fitting into a lU CubeSat, and a
possible deployed area of 0.414 m^. The concept chosen shows promise for increasing the drag to
de-orbit quickly and the reducing drag to maximize time at a desired altitude.
PY  - 2019-11-19
T1  - CubeSat deployable origami-inspired drag sail for drag control
TI  - CubeSat deployable origami-inspired drag sail for drag control
UR  - https://library.usi.edu/record/1559879/files/SP564.pdf
Y1  - 2019-11-19
ER  -