IEEE - Aerospace and Electronic Systems - May 2021 - 30
Flight Demonstration of a Hybrid Battery/Supercapacitor Energy Storage System in an Earth Orbiting CubeSat
Figure 5.
Summary of environmental testing for JPL/CSUNSat1 project. A-1) JPL/CSUNSat1 payload inside JPL's TVAC chamber, including flight
cell test chassis (picture on right) for TVAC environmental testing. A-2) Functional block diagram of the CubeSat TVAC system. A-3) Representative TVAC discharge pulse test data under vacuum (pressure < 10-6 Torr) at -40 C. B-1) Block diagram on the integrated JPL/
CSUNSat1. B-2) Random vibration test profile on the integrated CSUNSat1. The overall root mean square acceleration (grms) in the x, y,
and z directions was determined to be 9.51, 9.49, and 9.53 grms, respectively. B-3) Integrated voltage measurements under TVAC.
cells, most likely attributable to variations in resistance
between the voltage measuring electronics and contact
with the cell terminals. Figure 5A-3 illustrates a representative pulse discharge test at -40 C of $7 A in hybrid
ESS mode through one of the integrated load resistors.
The voltage and current distributions provided good indications of functionality and performance of the entire payload assembly including optimization of payload
electronics to minimize cell leakage and electrical resistances. Individual cell masses were also measured both
Table 2.
Summary of Cell Mass Pre- and Post-TVAC
Cell Mass (gm)
30
Cell ID
Pre-Tvac
Post-Tvac
Li-ion
85.120
85.110
Supercap #1
73.350
73.350
Supercap #2
75.000
75.000
before and after the TVAC testing. As summarized in
Table 2, the cell mass differences of all the flight cells
were negligible after TVAC testing, indicating no electrolyte leakage from a cell can breach.
CSUNSAT1 INTEGRATION TESTING
After successful environment cell testing, the hybrid
ESS payload assembly was integrated into an aluminum
block casing designed specifically to interface to the
JPL/CSUNSat1 spacecraft, as shown in Figure 4C. The
hybrid ESS payload was successfully integrated into the
spacecraft, and was subsequently subjected to environmental testing.
The pyroshock, random vibration and TVAC testing
on the CubeSat with the ESS payload in place were then
carried out. The test data (see Figure 5B-2) was used to
calculate the overall root mean square acceleration (grms)
in the x, y, and z directions to be 9.51, 9.49, and 9.53
grms, respectively. In addition, no debris or particles were
detected upon inspection after the test up to launch random vibration levels.
IEEE A&E SYSTEMS MAGAZINE
MAY 2021
IEEE - Aerospace and Electronic Systems - May 2021
Table of Contents for the Digital Edition of IEEE - Aerospace and Electronic Systems - May 2021
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