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Small Satellite Power Systems

Batteries
Batteries need to meet the power requirements that can not be covered by
solar panels. In very rare cases primary cells are the only power source
on-board, but more commonly rechargeable cells are employed. Batteries are
therefore generally employed in eclipse, or to meet short term power peaks. Rechargeable
batteries suffer from degradation with use, and so both the frequency and the
amount of charge taken out of the battery become factors in limiting lifetime.
Generally fewer cycles and less charge taken out in each cycle lead to a longer
battery life time. The choice of technology is therefore closely related to the
type of orbit. Low Earth Orbit may mean that a satellite clocks up over 14
charge/discharge cycles per day, or over 5000 per year. In higher orbits,
eclipses are rarer and so a greater depth-of-discharge can be tolerated for the
same lifetime. Some technologies are more suited to many charge/discharge
cycles, whereas others are better at handling large energy cycles. In addition
to the lifetime issues, battery technology choice is also based on the volume
and mass required for the energy storage, and in some case safety considerations
are important for instance if the spacecraft is carried on man-rated launchers
such as the Space Shuttle.
The primary battery technologies for Geostationary spacecraft are
Nickel-Cadmium and Nickel-Hydrogen. The latter is increasingly being placed in a
Common Pressure Vessel (CPV) in order to improve its energy density. Small satellites generally launch into Low
Earth Orbit and have employed Nickel Cadmium (NiCd) in most cases.
Nickel-Metal-Hydride batteries seemed promising technology for a while until
Lithium Ion (Li-Ion) batteries appeared which is superior in many respects.
Beyond that Lithium Polymer and even full Polymer batteries are promising
technology.
For small satellites, NiCd is still the basic choice as heritage and low cost
are desirable characteristics in many cases. Where mass is of the essence, or to
demonstrate new technology Li-Ion is being proposed into missions, and so far
has flown on three small satellites (STRV-1c/d
and PROBA)
| Technology |
Typical Energy
Density (Wh/kg) |
Comments |
| Nickel-Cadmium (NiCd) |
20-30 |
Extensive space heritage |
| Nickel-Hydrogen (NiH) |
35-55 |
|
| Lithium-Ion (Li-Ion) |
70-110 |
Few spacecraft have flown this |
Links
Sony
A good set of pages explaining the basic battery technologies (albeit for
terrestrial use)
Sanyo Battery
products
SAFT Battery
products, including space
Solar panels
Solar panels are generally used in missions where power must be generated
beyond the capabilities of primary battery cells. Solar panels produce
electrical power with Voltage determined by the cell technology and current by
the level of incident light. There are inherent efficiency losses, and with
typical solar flux of 1358W/m2, the solar cell efficiency determines
how much electrical power is generated by the total area of solar cells (not the
panels!). Both Voltage and Current change with temperature
and radiation dose, and as a result panels are less efficient at higher
temperatures, and degrade with time due to total radiation dose. A
technology with a long heritage is Silicon, but its advantages over
Gallium-Arsenide have gradually eroded over time. The current technology of
choice for most satellites is Gallium-Arsenide, and cells with efficiency
of up to 26% are available, with 30% efficiency cells on the drawing
board.
| Technology |
Typical efficiency
(%) |
Comments |
| Silicon (Si) |
12-17 |
Extensive space heritage |
| Gallium-Arsenide (GaAs) |
18-26 |
Extensive space heritage |
Silicon is seeing a comeback in thin-film solar panels, which have a low
efficiency near 10%, but have the advantage that they can be manufactured onto
thin flexible sheets. Cells sold for terrestrial applications are typically also
low efficiency Silicon, and have been successfully employed on very low cost
missions.

Micro-satellites
This list contains data on some select power systems of various small satellites.
Please refer to the key to the tables if
you are not using frames.
| Satellite |
Launch |
Orbit |
Battery |
Solar panel |
Comments |
| OSCAR-1 |
1961 |
|
|
None |
|
| UoSAT-1 |
1980 |
|
2 of 5 cell NiCd |
4 BM |
|
| UoSAT-2 |
1984 |
|
2 of 5 cell NiCd |
4 BM |
|
| UoSAT-3 |
1990 |
|
2 of 5 cell NiCd |
4 BM |
|
| UoSAT-4 |
1990 |
|
2 of 5 cell NiCd |
4 BM |
incl. experimental cells panel |
| ISES/REX |
1991 |
|
|
4 D |
|
| UoSAT-5 |
1991 |
|
2 of 5 cell NiCd |
4 BM, GaAs |
incl. experimental cells panel |
| S80/T |
1992 |
|
total 11 cell NiCd |
4 BM, GaAs |
|
| KitSat-1 |
1992 |
|
2 of 5 cell NiCd |
4 BM, GaAs |
|
| KitSat-2 |
1993 |
|
2 of 5 cell NiCd |
4 BM, GaAs |
|
| PoSAT-1 |
1993 |
|
2 of 5 cell NiCd |
4 BM, GaAs |
|
| HealthSat-2 |
1993 |
|
2 of 5 cell NiCd |
4 BM, GaAs |
plus experimental cells panel |
| Cerise |
1995 |
|
2 of 5 cell NiCd |
4 BM Si, 4D Si |
|
| FASat-Alfa |
1995 |
|
2 of 5 cell NiCd |
4 BM, GaAs |
|
| PROBA |
2002 |
|
Li-Ion and NiCd |
|
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Power systems - small satellites

Mini-satellites
| Satellite |
Launch |
Orbit |
Battery |
Solar panel |
Power |
Comments |
| Alexis |
1993 |
778km polar |
4 of 23 cells |
4 D, Si |
57W OA |
|
| STRV-1c/d |
2001 |
GTO |
Li-Ion and NiCd |
|
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Power systems - mini satellites

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