Difference between revisions of "Solar Power"
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The first small scale bases on the Moon with either use solar power or nuclear power (or both). | The first small scale bases on the Moon with either use solar power or nuclear power (or both). | ||
| − | + | There are basically two types of solar power, [[Solar Dynamic]] (SD) and [[Photovoltaic]] (PV). | |
| − | The problem with solar power is that PV conversion efficiency is only about 20% efficient, for rather high priced PV cells. Plus PV cells are rather heavy to ship from Earth and soft land on | + | SD uses a heat cycle to drive a piston or a turbine which connects to a generator or dynamo. Two popular cycles for Solar Dynamic are [[Brayton Cycle]] or [[Stirling Cycle]]. Solar Dynamic systems employ a large reflector to focus sunlight to a high concentration to achieve a high temperature for the heat cycle to operate at highest possible efficiency. |
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| + | PV uses semiconductors (e.g. Silicon or Gallium Arsenide) to directly convert sunlight photons into electric potential. Commonly know as “Solar cells” | ||
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| + | ==Comparison of PV versus SD== | ||
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| + | ===PV Problems=== | ||
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| + | The main problem with solar power is that PV conversion efficiency is only about 20% efficient, for rather high priced PV cells. Plus PV cells are rather heavy to ship from Earth and to soft land on Luna is very expensive. | ||
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| + | ===SD Problems=== | ||
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| + | SD has a much more severe pointing requirement than PV because it needs to maintain an accurate optical focus. | ||
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| + | If a PV array drifts off a few degrees, the power level drops a few percent. | ||
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| + | If a SD array drifts off a few degrees, the power level drops off to zero. | ||
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| + | ==Space Based Solar power== | ||
Until [[ISRU]] manufacturing is online, [[Solar Power Satellites]] (SPS) represent a more economic means of supplying large scale basebar power on the Moon in the early days. | Until [[ISRU]] manufacturing is online, [[Solar Power Satellites]] (SPS) represent a more economic means of supplying large scale basebar power on the Moon in the early days. | ||
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Let us assume a PV array is 10 times heavier per watt than a rectenna. | Let us assume a PV array is 10 times heavier per watt than a rectenna. | ||
| − | That means we can get 5*10 = 50 times as much power per kilogram for a rectenna than for a PV array. That means a rectenna will | + | That means we can get 5*10 = 50 times as much power per kilogram for a rectenna than for a PV array. That means a rectenna will be at least 50 times cheaper per watt of useful power than PV array. "At least" because the manufacturing cost of a rectenna will be much cheaper than for PV array. |
Soft landing hardware on to the Moon is very expensive, so weight is at a premium. | Soft landing hardware on to the Moon is very expensive, so weight is at a premium. | ||
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So one could put an SPS at lunar-L1 and beam microwaves from there to supply one or more rectennas on the Moon as a very efficient way to provide energy to a power hungry moon base. | So one could put an SPS at lunar-L1 and beam microwaves from there to supply one or more rectennas on the Moon as a very efficient way to provide energy to a power hungry moon base. | ||
| − | The sun angle across PV arrays on the lunar surface constantly changes, and is usually less than the 1,360 w/m^2. To | + | The sun angle across PV arrays on the lunar surface constantly changes, and is usually less than the 1,360 w/m^2. To maintain constant max power the PV array must have |
expensive and heavy steering equipment. Whereas a rectenna does not need to be steered, and always gets maximum power. | expensive and heavy steering equipment. Whereas a rectenna does not need to be steered, and always gets maximum power. | ||
Revision as of 09:48, 27 January 2007
The first small scale bases on the Moon with either use solar power or nuclear power (or both).
There are basically two types of solar power, Solar Dynamic (SD) and Photovoltaic (PV).
SD uses a heat cycle to drive a piston or a turbine which connects to a generator or dynamo. Two popular cycles for Solar Dynamic are Brayton Cycle or Stirling Cycle. Solar Dynamic systems employ a large reflector to focus sunlight to a high concentration to achieve a high temperature for the heat cycle to operate at highest possible efficiency.
PV uses semiconductors (e.g. Silicon or Gallium Arsenide) to directly convert sunlight photons into electric potential. Commonly know as “Solar cells”
Comparison of PV versus SD
PV Problems
The main problem with solar power is that PV conversion efficiency is only about 20% efficient, for rather high priced PV cells. Plus PV cells are rather heavy to ship from Earth and to soft land on Luna is very expensive.
SD Problems
SD has a much more severe pointing requirement than PV because it needs to maintain an accurate optical focus.
If a PV array drifts off a few degrees, the power level drops a few percent.
If a SD array drifts off a few degrees, the power level drops off to zero.
Space Based Solar power
Until ISRU manufacturing is online, Solar Power Satellites (SPS) represent a more economic means of supplying large scale basebar power on the Moon in the early days.
A SPS rectenna, on the other hand, is lightweight and has a conversion efficiency of over 90%.
Let us assume a PV array is 10 times heavier per watt than a rectenna.
That means we can get 5*10 = 50 times as much power per kilogram for a rectenna than for a PV array. That means a rectenna will be at least 50 times cheaper per watt of useful power than PV array. "At least" because the manufacturing cost of a rectenna will be much cheaper than for PV array.
Soft landing hardware on to the Moon is very expensive, so weight is at a premium.
The distance from L1 to Luna is about the same as the distance from Earth to a geostationary satellite.
So one could put an SPS at lunar-L1 and beam microwaves from there to supply one or more rectennas on the Moon as a very efficient way to provide energy to a power hungry moon base.
The sun angle across PV arrays on the lunar surface constantly changes, and is usually less than the 1,360 w/m^2. To maintain constant max power the PV array must have expensive and heavy steering equipment. Whereas a rectenna does not need to be steered, and always gets maximum power.
The ideal site for the lunar rectenna would be in Sinus Medii at the Lunar 0-Longitude point on the Lunar Equator, in the middle of the side which faces the Earth.
1) Because it is directly below the L-1 point, 2) it is the closest point on the lunar surface to the L-1 point, 3) Because at that point the lunar surface is at right angles to the incoming microwave beam.
All these factors permit the smallest rectenna at that location.
Without making any modifications at all to that very SPS, it could easily be maneuvered from L1 to GEO to feed a terrestrial ground based rectenna. The antenna design for L-1 to Luna will work equally well from GEO to Earth
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