To use all functions of this page, please activate cookies in your browser.
With an accout for my.chemeurope.com you can always see everything at a glance – and you can configure your own website and individual newsletter.
- My watch list
- My saved searches
- My saved topics
- My newsletter
Solar power satellite
A solar power satellite, or SPS or Powersat, as originally proposed would be a satellite built in high Earth orbit that uses microwave power transmission to beam solar power to a very large antenna on Earth. Advantages of placing the solar collectors in space include the unobstructed view of the Sun, unaffected by the day/night cycle, weather, or seasons. It is a renewable energy source, zero emission, and generates no waste. However, the costs of construction are very high, and SPS will not be able to compete with conventional sources (at current energy prices) unless at least one of the following conditions is met:
In common with other types of renewable energy such a system could have advantages to the world in terms of energy security via reduction in levels of conflict, military spending, loss of life, and avoiding future conflict over dwindling energy sources.
Additional recommended knowledge
The SPS concept was first described in November 1968 . At first it was regarded as impractical due to the lack of a workable method of sending power collected down to the Earth's surface. This changed in 1973 when Peter Glaser was granted U.S. patent number 3,781,647  for his method of transmitting power over long distances (eg, from an SPS to the Earth's surface) using microwaves from a, perhaps square kilometer, antenna on the satellite to a much larger one on the ground, which came to be known as a rectenna.
Glaser then worked at Arthur D. Little, Inc., as a vice-president. NASA became interested and signed a contract with ADL to lead four other companies in a broader study in 1974. They found that, while the concept had several major problems -- chiefly the expense of putting the required materials in orbit and the lack of experience on projects of this scale in space, it showed enough promise to merit further investigation and research .
During the period from 1978 - 1981 the US Congress authorized DOE and NASA to jointly investigate. They organized the Satellite Power System Concept Development and Evaluation Program . The study remains the most extensive performed to date. Several reports were published addressing various issues, together investigating most of the possible problems with such an engineering project. They include:
After these studies were published, there was no follow up work and the concept dwindled. The DOE study conclusions were critical of the project's possibilities. Confusing press reports widely reported that the concept had been demonstrated to be infeasible .
More recently, the SPS concept has again become interesting, due to increased energy demand, increased costs, and emission implications, and starting in 1997 with the NASA "Fresh Look" however funding is still minimal.
In 2007, the US Department of Defense expressed interest in the concept.
At some cost point, the high initial costs of an SPS project will become favourable due to the low-cost delivery of power. By some estimates, this has already happened in some locations, as a result of the widely varying costs of electricity which sometimes approach (or even exceed) this point. In addition, continued advances in material science and space transport continue to whittle away at the startup cost of an SPS.
The SPS essentially consists of three parts:
In many ways, the SPS is a simpler conceptual design than most power generation systems previously proposed. The simple aspects include the physical structure required to hold the SPS together and to align it orthogonally to the Sun. This will be considerably lighter than any similar structure on Earth since it will be in a zero-g, vacuum environment and will not need to support itself against a gravity field and needs no protection from terrestrial wind or weather.
Solar energy conversion (solar photons to DC current)
Two basic methods of converting photons to electricity have been studied, Solar Dynamic (SD) and Photovoltaic (PV).
SD uses a heat engine to drive a piston or a turbine which connects to a generator or dynamo. Two heat cycles for Solar Dynamic are thought to be reasonable for this: the Brayton Cycle or the Stirling Cycle. Terrestrial Solar Dynamic systems typically use a large reflector to focus sunlight to a high concentration to achieve a high temperature so the heat engine can operate at high thermodynamic efficiencies; an SPS implementation is expected to be similar. 
PV uses semiconductor cells (e.g., Silicon or Gallium Arsenide) to directly convert sunlight photons into voltage via a quantum mechanical mechanism. These are commonly known as “Solar cells”, and will likely be rather different from the glass panel protected solar cell panels familiar to many and in current terrestrial use. They will, for reasons of weight, probably be built in membrane from, not suitable to terrestrial use which is subject to considerable gravitational loading.
Comparison of PV versus SD
The main problems with PV are that PV cells continue to be relatively expensive, and require a relatively large area to be acceptable. In addition, being semiconductors, the PV panels will require a reasonably large amount of energy to produce.
SD is a more mature technology, having been in widespread use in many contexts for centuries. But, SD has a much more severe pointing requirement than PV because most proposed designs require accurate and stable optical focus. If a PV array drifts off a few degrees, the power being produced will drop a few percent. But, if a SD array drifts off a few degrees, the power produced will drop off very quickly to zero, or near to it.
Currently, PV cells weigh between 0.5kg/kW and 10kg/kW depending on design. SD designs also vary but most seem to be heavier per kW produced than PV cells and thus this pushes up launch costs.
The lifetime of a PV based SPS is limited mainly by the ionizing radiation from the radiation belts and the Sun. Without some method of protection, this is likely to cause the cells to continuously degrade by about a percent or two per year. Deterioration is likely to be more rapid during periods of high exposure to energetic protons from solar particle events. If some practical protection can be designed, this also might be reducible.
Lifetimes for SD based SPS designs will be limited by structural and mechanical considerations, such as micrometeorite impact, metal fatigue of turbine blades, wear of sliding surfaces (although this might be avoidable by hydrostatic bearings or magnetic bearings), degradation or loss of lubricants and working fluids in vacuum, from loss of structural integrity leading to impaired optical focus amongst components, and from temperature extreme effects. As well, most mirror surfaces will degrade from both radiation and particle impact, but such mirrors can be designed simply (and so light and cheap), so replacement may be practical.
In either case, another advantage of the SPS design is that waste heat developed at collection points is re-radiated back into space, instead of warming the adjacent local biosphere as with conventional sources; thus thermal efficiency will not be in itself an important design parameter except insofar as it affects the power/weight ratio via operational efficiency and hence pushes up launch costs. (For example SD may require larger radiators when operating at a lower efficiency). Earth based power handling systems must always be carefully designed, for both economic and purely engineering reasons, with operational thermal efficiency in mind.
Clearly for a system (including manufacture, launch and deployment) to provide net power it must repay the energy needed to construct it. For current silicon PV panels the energy needs are relatively high, and typically several years of deployment in a terrestrial environment is needed to recover this energy. With SPS net energy received on the ground is higher (more or less necessarily so, for the system to be worth deploying), so this energy payback period would be somewhat reduced; however SD, being made of conventional materials, are more similar to conventional powerstations and are likely to be less energy intensive and would be expected to give quicker energy break even, depending on construction technology.
Wireless power transmission to the Earth
Wireless power transmission was early proposed to transfer energy from collection to the Earth's surface. The power could be transmitted as either microwave or laser radiation at a variety of frequencies depending on system design. Whatever choice is made, the transmitting radiation would have to be non-ionizing to avoid potential disturbances either ecologically or biologically if it is to reach the Earth's surface. This established an upper bound for the frequency used, as energy per photon, and so the ability to cause ionization, increases with frequency. Ionization of biological materials doesn't begin until ultraviolet or higher frequencies so most radio frequencies will be acceptable for this.
William C. Brown demonstrated in 1964 on CBS news with Walter Cronkite, a microwave-powered model helicopter that received all the power needed for flight from a microwave beam. Between 1969 and 1975 Bill Brown was technical director of a JPL Raytheon program that beamed 30 kW over a distance of 1 mile at 84% efficiency.
As well, to minimize the sizes of the antennas used, the wavelength should be small (and frequency correspondingly high) since antenna efficiency increases as antenna size increases. But, higher radio frequencies are typically more absorbed in the atmosphere than lower radio frequencies.
For these reasons, 2.45 GHz has been proposed as being a reasonable compromise. However, that frequency results in large antenna sizes at the GEO distance. A loitering stratospheric airship has been proposed to receive higher frequencies (or even laser beams), converting them to something like 2.45GHz for retransmission to the ground. The proposal has not been as carefully evaluated for engineering plausibility as other aspects of SPS design.
The sizing will be dominated by the distance from Earth to geostationary orbit (22,300 miles, 35,700 km), the chosen wavelength of the microwaves, and the laws of physics, specifically the Rayleigh Criterion or Diffraction limit, used in standard RF (Radio Frequency) antenna design.
For best efficiency, the satellite antenna should be circular and about 1 kilometers in diameter or larger; the ground antenna (rectenna) should be elliptical and around 14 kilometers by 10 kilometers. Smaller antennas would result in increased losses to diffraction/sidelobes. For the desired (23mW/cm²) microwave intensity  these antennas could transfer between 5 and 10 gigawatts of power. To be most cost effective, the system needs to operate at maximum capacity. And, to collect and convert that much power, the satellite would need between 50 and 100 square kilometers of collector area (if readily available ~14% efficient monocrystalline silicon solar cells were deployed). State of the art (currently, quite expensive, triple junction gallium arsenide) solar cells with a maximum efficiency of 40.7%  could reduce the necessary collector area by two thirds, but would not necessarily give overall lower costs. In either cases, the SPS's structure would be kilometers wide, making it larger than most man-made structures here on Earth. While almost certainly not beyond current engineering capabilities, building structures of this size in orbit has not yet been attempted.
LEO/MEO instead of GEO
A LEO system of space power stations has been proposed as a precursor to GEO space power beaming system(s). There would be advantages, (much shorter path length allowing smaller antenna sizes, lower cost to orbit) and disadvantages (constantly changing antenna geometries, increased debris collision difficulties, etc). It might be possible to deploy LEO systems sooner than GEO because the antenna development would take less time. Ultimately, because full engineering feasibility studies have not been conducted, it is not known whether this would be an improvement over a GEO installation.
Earth based infrastructure
The Earth-based receiver antenna (or rectenna) is a critical part of the original SPS concept. It would probably consist of many short dipole antennas, connected via diodes. Microwaves broadcast from the SPS will be received in the dipoles with about 85% efficiency. With a conventional microwave antenna, the reception efficiency is still better, but the cost and complexity is also considerably greater, almost certainly prohibitively so. Rectennas would be multiple kilometers across. Crops and farm animals may be raised underneath a rectenna, as the thin wires used for support and for the dipoles will only slightly reduce sunlight, so such a rectenna would not be as expensive in terms of land use as might be supposed.
Advantages of an SPS
The SPS concept is attractive because space has several major advantages over the Earth's surface for the collection of solar power. There is no air in space, so the collecting surfaces would receive much more intense sunlight, unaffected by weather. In geostationary orbit, an SPS would be illuminated over 99% of the time. The SPS would be in Earth's shadow on only a few days at the spring and fall equinoxes; and even then for a maximum of 75 minutes late at night when power demands are at their lowest. This allows the power generation system to avoid the expensive storage facilities (eg, lakes behind dams, oil storage tanks, etc) necessary in many Earth-based power generation systems. Additionally, an SPS will avoid entirely the polluting consequences of fossil fuel systems, the ecological problems resulting from many renewable or low impact power generation systems (eg, dams).
More long-term, the potential amount of power production is enormous. If power stations can be placed outside Earth orbit, the upper limit is vastly higher still. In the extreme, such arrangements are called Dyson spheres.
Without doubt, the most obvious problem for the SPS concept is the currently immense cost of space launches. Current rates on the Space Shuttle run between $3,000 and $5,000 per pound ($6,600/kg and $11,000/kg) to low Earth orbit, depending on whose numbers are used. Calculations show that launch costs of less than about $180-225 per pound ($400-500/kg) to LEO (Low Earth orbit) seem to be necessary.
However, economies of scale for expendable vehicles could give rather large reductions in launch cost for this kind of launched mass. Thousands of rocket launches could very well reduce the costs by ten to twenty times, using standard costing models. An alternative nuclear pulse based rocket model such as that developed in the Orion Project could further reduce launch costs. This puts the economics of an SPS design into the practicable range. Reusable vehicles could quite conceivably attack the launch problem as well, but are not a well developed technology.
Much of the material launched need not be delivered to its eventual orbit immediately, which raises the possibility that high efficiency (but slower) engines could move SPS material from LEO to GEO at acceptable cost. Examples include ion thrusters or nuclear propulsion. They might even be designed to be reusable.
Power beaming from geostationary orbit by microwaves has the difficulty that the required 'optical aperture' sizes are very large. For example, the 1978 NASA SPS study required a 1-km diameter transmitting antenna, and a 10 km diameter receiving rectenna, for a microwave beam at 2.45 GHz. These sizes can be somewhat decreased by using shorter wavelengths, although they have increased atmospheric absorption and even potential beam blockage by rain or water droplets. Because of the thinned array curse, it is not possible to make a narrower beam by combining the beams of several smaller satellites. The large size of the transmitting and receiving antennas means that the minimum practical power level for a SSPS will necessarily be high; small SPS systems will be possible, but uneconomic.
To give an idea of the scale of the problem, assuming an (arbitrary, as no space ready design has been adequately tested) solar panel mass of 20 kg per kilowatt (without considering the mass of the supporting structure, antenna, or any significant mass reduction of any focusing mirrors) a 4 GW power station would weigh about 80,000 metric tons, all of which would, in current circumstances, be launched from the Earth. Very lightweight designs could likely achieve 1 kg/kW,, meaning 4000 metric tons for the solar panels for the same 4 GW capacity station. This would be the equivalent of between 40 and 80 HLLV launches to send the material to low earth orbit, where it would likely be converted into subassembly solar arrays, which then could use high efficiency ion-engine style rockets to (slowly) reach GEO (Geostationary orbit). With an estimated serial launch cost for shuttle-based HLLVs of $500 million to $800 million, total launch costs would range between $20 billion (low cost HLLV, low weight panels) and $320 billion ('expensive' HLLV, heavier panels). Economies of scale on such a large launch program could be as high as 90% (if a learning factor of 30% could be achieved for each doubling of production) over the cost of a single launch today. On addition, there would be the cost of an assembly area in LEO (which could be spread over several power satellites), and probably one or more smaller one(s) in GEO. The costs of these supporting efforts would also contribute to total costs.
So how much money could an SPS be expected to make? For every one gigawatt rating, current SPS designs will generate 8.75 terawatt-hours of electricity per year, or 175 TW•h over a twenty year lifetime. With current market prices of $0.22 per kW•h (UK, January 2006) and an SPS's ability to send its energy to places of greatest demand (depending on rectenna siting issues), this would equate to $1.93 billion per year or $38.6 billion over its lifetime. The example 4 GW 'economy' SPS above could therefore generate in excess of $154 billion over its lifetime. Assuming facilities are available, it may turn out to be substantially cheaper to recast on-site steel in GEO, than to launch it from Earth. If true, then the initial launch cost could be spread over multiple SPS lifespans.
Gerard O'Neill, noting the problem of high launch costs in the early 1970s, proposed building the SPS's in orbit with materials from the Moon. Launch costs from the Moon are about 100 times lower than from Earth, due to the lower gravity. This 1970s proposal assumed the then-advertised future launch costing of NASA's space shuttle. This approach would require substantial up front capital investment to establish mass drivers on the Moon.
Nevertheless, on 30 April 1979, the Final Report ("Lunar Resources Utilization for Space Construction") by General Dynamics' Convair Division, under NASA contract NAS9-15560, concluded that use of lunar resources would be cheaper than terrestrial materials for a system of as few as thirty Solar Power Satellites of 10GW capacity each.
In 1980, when it became obvious NASA's launch cost estimates for the space shuttle were grossly optimistic, O'Neill et al published another route to manufacturing using lunar materials with much lower startup costs  This 1980s SPS concept relied less on human presence in space and more on partially self-replicating systems on the lunar surface under telepresence control of workers stationed on Earth. Again, this proposal suffers from the current lack of such automated systems, on Earth much less on the Moon.
Asteroid mining has also been seriously considered. A NASA design studyevaluated a 10,000 ton mining vehicle (to be assembled in orbit) that would return a 500,000 ton asteroid 'fragment' to geostationary orbit. Only about 3000 tons of the mining ship would be traditional aerospace-grade payload. The rest would be reaction mass for the mass-driver engine; which could be arranged to be the spent rocket stages used to launch the payload. Assuming, likely unrealistically, that 100% of the returned asteroid was useful, and that the asteroid miner itself couldn't be reused, that represents nearly a 95% reduction in launch costs. However, the true merits of such a method would depend on a thorough mineral survey of the candidate asteroids; thus far, we have only estimates of their composition. There has been no such survey. Once built, NASA's CEV should be capable of beginning such a survey, Congressional money and imagination permitting.
More recently the SPS concept has been suggested as a use for a space elevator. The elevator would make construction of an SPS considerably less expensive, possibly making them competitive with conventional sources. However it appears unlikely that even recent advances in materials science, namely carbon nanotubes, can reduce the price of construction of the elevator enough in the short term. That is, even if a space elevator is ever possible.
Lofstrom launch loop
An alternative to the carbon nanotube based Space Elevator could be a Lofstrom loop. This is a high capacity launch system capable of reaching a geosynchronous transfer orbit at low cost (Lofstrom estimates a large system could go as low as $3/kg to LEO for example.) Unlike the conventional space elevator it is believed that a launch loop could be built with today's materials.
The use of microwave transmission of power has been the most controversial issue in considering any SPS design, but any thought that anything which strays into the beam's path will be incinerated is an extreme misconception. Consider that quite similar microwave relay beams have long been in use by telecommunications companies world wide without such problems.
At the earth's surface, a suggested microwave beam would have a maximum intensity, at its center, of 23 mW/cm2 (less than l/4 the solar irradiation constant), and an intensity of less than 1 mW/cm2 outside of the rectenna fenceline (10 mW/cm2 is the current United States maximum microwave exposure standard). At present, per OSHA, , the workplace exposure limit (10 mW/sq. cm.) is expressed in voluntary language and has been ruled unenforceable for Federal OSHA enforcement.
The beam's most intense section (more or less, at its center) is far below dangerous levels even for an exposure which is prolonged indefinitely.  Furthermore, exposure to the center of the beam can easily be controlled on the ground (eg, via fencing), and typical aircraft flying through the beam provide passengers with a protective shell metal (ie, a Faraday Cage), which will intercept the microwaves. Other aircraft (balloons, ultra-light, etc) can avoid exposure by observing airflight control spaces, as is currently done for military and other controlled airspace. Over 95% of the beam energy will fall on the rectenna. The remaining microwave energy will be absorbed and dispersed well within standards currently imposed upon microwave emissions around the world.
The microwave beam intensity at ground level in the center of the beam would be designed and physically built into the system; simply, the transmitter would be too far away and too small to be able to increase the intensity to unsafe "death ray" levels, even in principle.
In addition, a design constraint is that the microwave beam must not be so intense as to injure wildlife, particularly birds. Experiments with deliberate microwave irradiation at reasonable levels have failed to show negative effects even over multiple generations. 
A commonly proposed approach to ensuring fail-safe beam targeting is to use a retrodirective phased array antenna/rectenna. A "pilot" microwave beam emitted from the center of the rectenna on the ground establishes a phase front at the transmitting antenna. There, circuits in each of the antenna's subarrays compare the pilot beam's phase front with an internal clock phase to control the phase of the outgoing signal. This forces the transmitted beam to be centered precisely on the rectenna and to have a high degree of phase uniformity; if the pilot beam is lost for any reason (if the transmitting antenna is turned away from the rectenna, for example) the phase control value fails and the microwave power beam is automatically defocused. Such a system would be physically incapable of focusing its power beam anywhere that did not have a pilot beam transmitter.
It is important for system efficiency that as much of the microwave radiation as possible be focused on the rectenna. Outside of the rectenna, microwave intensities would rapidly decrease, so nearby towns or other human activity should be completely unaffected.
The long-term effects of beaming power through the ionosphere in the form of microwaves has yet to be studied, but nothing has been suggested which might lead to any significant effect.
Defending solar power satellites
Solar power satellites would normally be at a high orbit that is difficult to reach, and hence attack.
However, it has been suggested that a large enough quantity of granular material placed in a retrograde orbit at the geostationary altitude could theoretically completely destroy these kinds of system and render that orbit useless for generations.
Whether this is a realistic attack scenario is arguable, and in any case at the present time there is only a small list of countries with the necessary launch capability to do this, such an attack would probably be considered an act of war, and conventional power generators are more easily attacked.
SPS's economic feasibility
Current energy price landscape
In order to be competitive on a purely economic level, an SPS must cost no more than existing supplies.[dubious (Such costs must include the costs of cleaning waste from construction, operation and dismantling of the generating systems--including lifestyle and health costs.. Currently(2007) most Earth-based power generation does not include these costs. The cost figures below are undated, but are obsolete as of 2007. This greatly reduces the prices paid for power currently reducing the apparent benefits of SPS'.) This may be difficult, especially if it is deployed for North America, where energy costs have been relatively low. It must cost less to deploy, or operate for a very long period of time, or offer other advantages. Many proponents ][who?] have suggested that the lifetime is effectively infinite, but normal maintenance and replacement of less durable components makes this unlikely. Satellites do not, in our now-extensive experience, last forever. (But with regular maintenance there is no reason that a high orbit satellite has to 'die.' Currently (2007) the majority of such satellites--weather and communications, fail due to correctable maintenance issues which we do not correct because we have no repair people on site. Common failures are: running out of station keeping fuel or dead batteries-no longer holding a charge. Neither of these failure modes is much of a problem if service is available. With available refueling and battery replacement, the life of a satellite can be greatly increased. Structural components, which make up the largest percentage of mass, seldom fail. Nearly all of the other components can be modularized for easy replacement/upgrade.)
Current prices for electricity on the public grid fluctuate depending on time of day, but typical household delivery costs about 5 cents per kilowatt hour in North America. If the lifetime of an SPS is 20 years and it delivers 5 gigawatts to the grid, the commercial value of that power is 5,000,000,000 ÷ 1000 = 5,000,000 kilowatts[clarify], which multiplied by $.05 per kW•h gives $250,000 revenue per hour. $250,000 × 24 hours × 365 days × 20 years = $43,800,000,000. By contrast, in the United Kingdom (October 2005) electricity can cost 9–22 cents per kilowatt hour. This would translate to a lifetime output of $77–$193 billion for power delivered to the UK.
Comparison with fossil fuels
There are several problems with existing energy delivery systems. They are subject to (among other problems)
Following the Kyoto Treaty, 141 countries introduced the first system of mandatory emissions control via carbon credits. The ultimate direction of such policies is to increase efficiency of fossil fuel use, perhaps to the point of elimination in some countries or even globally. But, the energy requirements of third world or developing countries (e.g. China and India) are increasing steadily. Because of the net increase in demand, energy prices will continue to increase, though how fast and how high are less easily predicted.
Comparison with nuclear power (fission)
On balance, SPS avoids nearly all of the problems with current nuclear power schemes, and does not have larger problems in any respect, although public perception of microwave power transfer (ie, in the beams produced by an SPS and received on Earth) dangers could become an issue.
Comparison with nuclear fusion
Nuclear fusion is a process used in thermonuclear bombs (e.g., the H-bomb). Projected nuclear fusion power plants would not be explosive, and will likely be inherently failsafe. However, sustained nuclear fusion generators have only just been demonstrated experimentally, despite well funded research over a period of several decades (since approximately 1952). There is still no credible estimate of how long it will be before a nuclear fusion reactor could become commercially possible; fusion research continues to receive substantial funding by many nations. For example, the ITER facility currently under construction will cost €10 billion. There has been much criticism of the value of continued funding of fusion research. Proponents have successfully argued in favor of ITER funding.
By contrast, SPS does not require any fundamental engineering breakthroughs, has already been extensively reviewed from an engineering feasibility perspective over some decades, and needs only incremental improvements of existing technology to be deployed. Despite these advantages, SPS has received minimal research funding to date.
Comparison with terrestrial solar power
In the case of the United Kingdom, the country as a whole is further north than even most inhabited parts of Canada, and hence receives little insolation over much of the year, so conventional solar power is not competitive at 2006 per-kilowatt-hour delivered costs. However, per-kilowatt-hour photovoltaic costs have been in exponential decline for decades, with a 20-fold decrease from 1975 to 2001, so this situation may change.
Let us consider a ground-based solar power system versus an SPS generating an equivalent amount of power.
Both SPS and ground-based solar power could be used to produce chemical fuels for transportation and storage, as in the proposed hydrogen economy. Or they could both be used to run an energy storage scheme (such as pumping water uphill at a hydropower generation station).
Many advances in solar cell efficiency (eg, improved construction techniques) that make an SPS more economically feasible might make a ground-based system more economic as well. Also, many SPS designs assume the framework will be built with automated machinery supplied with raw materials, typically aluminium. Such a system could be (more or less easily) adapted for operation on Earth, no launching required. However, Earth-based construction already has access to inexpensive human labor that would not be available in space, so such construction techniques would have to be extremely competitive to be significant on Earth.
Solar Panel Mass Production
Currently the costs of solar panels are too high to use them to produce bulk domestic electricity in most situations. However, mass production of the solar panels necessary to build a SPS system would be likely to reduce those costs sufficiently to change this -- perhaps substantially -- especially as fossil fuel costs have been increasing rapidly. But, any panel design suited to SPS use is likely to be quite different than earth suitable panels, so not all such improvements will have this effect. This may benefit earth based array designs as costs may be lower (see the cost analysis above), but will not be able to take advantage of maximum economies of scale, and so piggyback on production of Earth based panels.
It should be noted, however, that there are also frequent developments in the production of solar panels. Thin film solar panels and so-called "nanosolar" might increase collection efficiency, reduce production costs as well as weight, and therefore reduce the total cost of an SPS installation. In addition, private space corporations could become interested in transporting goods (such as satellites, supplies and parts of commercial space hotels) to LEO (Low Earth orbit), since they already are developing spacecraft to transport space tourists. If they can reduce costs, this will also increase the economic feasibility of an SPS.
Comparison with Other Renewables (wind, tidal, hydro, geothermal)
Other renewable energy sources (e.g., wind energy, tidal energy, hydro-electric, geothermal, ethanol), have the capacity to supply only a tiny fraction of the global energy requirement, now or in the foreseeable future. For most, the limitation is geography as there simply are very few sites in the world where generating systems can be built, and for hydro-electric projects in particular, there are few sites still open. For 2005, in the US, hydro-electric power accounted for 6.5% of electricity generation, and other renewables 2.3%. The U.S. Govt. Energy Information Administration projects that in 2030 hydro-power will decline to 3.4% and other renewables will increase to 2.9%.
Ocean-based windpower is one possibility (there being large areas for potential installations), but it is strongly affected by two factors; the difficulty of long distance power transmission as many regions of high demand are not near the sea, and be the very large difficulty of coping with corrosion, contamination, and survivability problems faced by all seaborne installations.
Ethanol power production depends on farming in the case of corn or sugar cane origin ethanol, currently the two leading sources. There is insufficient farming capacity for both significant energy production and food production. Corn prices have risen substantially in 2006 and 2007, partly as a result of nascent ethanol production demand. Ethanol from cellulose (eg, agricultural waste or purpose collected non-cultivated plants, eg, switchgrass)) is not practicable as of 2007, though pilot plants are indevelopment. Processing improvements (eg, a breakthrough in enzyme processing) may change this relative disadvantage.
For the past several years there has been no line item for SPS in either the NASA nor DOE budgets, a minimal level of research has been sustained through small NASA discretionary budget accounts.
NASA's "Fresh Look" study in 2000
NASDA (Japan's national space agency) has been researching in this area steadily for the last few years. In 2001 plans were announced to perform additional research and prototyping by launching an experimental satellite of capacity between 10 kilowatts and 1 megawatt of power.
The National Space Society (a non-profit NGO) maintains a web page where the latest SPS related references are posted and kept current .
In May 2007 a workshop was held at MIT in the U.S.A. to review the current state of the market and technology
In 2007 the U.S. Department of Defense expressed interest in studying the concept.
On 10/10/2007 The National Security Space Office of the US Department of Defense, published an assessment report . The report was released at a press conference which simultaneously announced the formation of the Space Solar Alliance for Future Energy which intends to pursue the recommendations of the NSSO-Led Study.
Space stations transmitting solar power have appeared in science-fiction works like Isaac Asimov's Reason (1941), that centers around the troubles caused by the robots operating the station.
|This article is licensed under the GNU Free Documentation License. It uses material from the Wikipedia article "Solar_power_satellite". A list of authors is available in Wikipedia.|