Value chain · CLM-0336
In plain terms
Different design studies over four decades have each simply assumed a different working lifetime for a solar power satellite, from about 15 years to 30 years; none has actually operated one long enough to know which is right.
The claim as recorded
Design-life assumptions for SPS concepts in the held corpus range from "15+ years" (2010) to "assumed 20 + years" (2019) to a 30-year system life set as a ground rule in the 1978 DOE/NASA reference design; none of these figures is based on a flown SPS.
Evidence behind this: T3 (SRC-085); T5 (SRC-041); T2 (SRC-026)
Scope and limits
A survey of stated ASSUMPTIONS, not a technical resolution of achievable design life. No source in the held corpus reports a measured or flown SPS design life.
What it assumes
Each figure is the design target/assumption stated by its own source; none of the three states, in the pages cited, the underlying basis (fatigue, radiation dose, propellant load) for its specific number.
Where it comes from
, PDF p.22 (printed p.10): "System life is 30 years with no salvage value or disposition costs." SRC-041, PDF p.8 (printed p.7): "...must also support a flexible and modular approach to achieving SPS long-life (15+ years)." SRC-026, PDF p.8 (journal p.177): "CASSIOPeiA's lack of mechanical wearing parts and sub-wavelength modularity allows the system to be designed for graceful degradation over its operational lifetime (assumed 20 + years) without planned maintenance".
Basis: assumed design/operational life in years, not measured
Related records
- Answers question
- QST-002 not published in this release
Cite this
energyaperture.com/c/clm-0336
CLM-0336, Energy Aperture, as of 1978; 2010; 2019.
Connected records
Other published records linked to this one. A list, not a judgement.
- Also from SRC-026
- CLM-0004The author of the 2019 CASSIOPeiA paper states the beam's strongest point is about 230 watts per square metre, and says that figure was...CLM-0006None of the five main studies mentions the international radio-frequency exposure limits, or any safety standard, or a restricted area...CLM-0013The paper that modern UK studies rely on for the beam figure calls anything below 1 kilowatt per square metre safe, with 230 watts per...CLM-0339A 2019 paper said solar power satellites are often assumed to need visits in orbit for repairs and refuelling, but that no system yet...CLM-0441A normal geostationary satellite needs a small, regular fuel-based nudge every year to stay in place. One 2019 design proposes cutting most...CLM-0504None of the main CASSIOPeiA-related documents in the register mentions any named safety or exposure standard, or describes any restricted...CLM-0660The 2019 CASSIOPeiA paper does not discuss electric propulsion for getting the satellite to its orbit. It only prices delivery using...CLM-1175The design would control its orientation without fuel. Small mirror panels near its front carry a coating whose reflection can be changed...More on the source page.
- Also from SRC-041
- CLM-0333In one 1978 design, structure and mechanisms made up about 18% of the satellite's dry mass; a 2010 paper gives about 20% as a general rule...CLM-0343A 2010 NASA paper argues that building a solar power satellite in space is not just a robot problem: the module design, the assembly steps...
- Also from SRC-085
- CLM-0013The paper that modern UK studies rely on for the beam figure calls anything below 1 kilowatt per square metre safe, with 230 watts per...CLM-0020The original 1978 design set the beam at 230 watts per square metre in the middle of the receiving site, about one twenty-third of that at...CLM-0023In the 1978 reference design, two limits set the size of the transmitter and the receiving site: how much heat the transmitter can shed...CLM-0039The 1978 report set the figure to protect radio and navigation systems from a disturbed ionosphere, called the number theoretical and...CLM-0045The apparent conflict between 12 and 23 was not an error. The underlying study gave a range, and the figure adopted sits near the top of it.CLM-0101The 1978 contract required the researchers to report fixes if ionospheric disturbance pushed the pilot-beam phase error past 2 to 3...CLM-0137In four major space solar power studies from 1978 to 2007, none put a number on how much of the beam's energy would be lost if the beam...CLM-0138The original 1978 government design for beaming power down from space adds up all the expected energy losses to get 63% overall efficiency...More on the source page.