Value chain · CLM-1478
In plain terms
Almost everything that can go wrong with this design makes the beam fall apart and become harmless, which is the right way to fail. Two things do not. If someone fakes the ground signal, the satellite aims at the fake. And if the internal reference cabling drifts, the beam weakens and wanders rather than switching off.
The claim as recorded
Enumerating the failure modes of the disclosed retrodirective architecture: loss of the pilot, loss of the reference frequency, and loss of the timing tick in a sampled implementation all destroy coherence and defocus the beam, which is fail-safe. A failed phase detector doubles the effective spacing for its cell, raising that cell's residual about fourfold, which is local and graded. A failed element costs one part in N. Two failure modes do not defocus to safety. A FORGED PILOT causes the array to form a beam toward the forgery, using the beam's own designed steering path, and is the only failure that points power somewhere rather than nowhere; no pilot authentication is disclosed for this architecture in any source searched. The 1978 US reference design did specify a coded pilot, which NASA's 1981 system definition says guards against attempts to dephase the beam or redirect its power. NASA's 1981 technical summary of the power transmission work gives the preliminary design of the pilot code developed for that system by then, a direct-sequence pseudonoise spreading code on the pilot carrier, and the review panel report bound into it judged that not enough attention had been paid to security and antijamming and asked for state-of-the-art cryptography. None of these reports describes a check by which the satellite could tell a forged pilot from a real one, and none shows that the code would stop deliberate interference. DRIFT IN THE REFERENCE DISTRIBUTION produces aperture phase error at full weight, causing gain loss and mispointing rather than defocus, and the pilot cannot correct it.
Evidence behind this: T0-analysis. Enumerates the failure modes of the disclosed architecture and their consequences, each traced to a record or a derivation.
Scope and limits
Derived from disclosed architecture, not from any tested system. No source obtained describes testing any of these failure modes on CASSIOPeiA hardware, and the fail-safe evidence is from a different, planar, 1978 design. THE SOURCES THIS RECORD DRAWS ON GIVE NO TIME CONSTANT FOR ANY OF THESE TRANSITIONS: DOE/ER-0023, the GB2563574 patent and CALC-101 give none (CALC-101's millisecond values are timing tolerances, not transition times). For the retrodirective concept of the US reference design, NASA's 1981 system definition states that fail-safe dephasing takes milliseconds, with no derivation on the page (CLM-1020). That is an order of magnitude for a different design, and it covers only the fail-safe defocus, not a forged pilot or reference drift. RP-1076's code is a spreading code; its pages give it to separate the pilot from the power signal, to let several satellites share the pilot band and, without showing how, to give link security and protection against jamming (PDF p.44); this record does not assess whether such a code could be copied or forged. Confidence is MED because the enumeration is a construction from the architecture rather than a reading of a source, and an enumeration can be incomplete in a way a quotation cannot.
What it assumes
That loss of a reference causes elements to decorrelate rather than to hold their last applied phase. This is not stated in any source obtained and the alternative matters: held phases would keep groups mutually coherent and make the collapse shallower, per CLM-0911's collapse-depth relation.
Where it comes from
This is the project's own working, shown in full:
Pilot loss, SRC-085 p30 directly. Interpolation and detector spacing, CLM-0896 for what the patent discloses and CLM-0912 for the scaling: the residual goes as the SQUARE of detector spacing, so doubling it raises rms about fourfold - but that is the small-spacing asymptote and it holds only below about D/Lc = 0.3, overstating the residual by a factor of 33 at D/Lc = 4, so it must not be used to size a spacing. Element failure rate tolerance, SRC-085 p27, Figure 15: "FAILURE RATE OF DC-RF POWER CONVERTER TUBES = 2% (A MAXIMUM OF 2% HAVE FAILED AT ANY ONE TIME)". Reference drift, CLM-0902. Absence of authentication for this architecture, CLM-0899 and the 2026-09-13 search. Coded pilot in the US reference design: SRC-085 printed p.45 (PDF p.57) lists pilot-beam coding, for security and so that each satellite can tell which pilot is its own; SRC-554 PDF p.46 (printed 36) says the baseline codes each pilot signal to guard against attempts to dephase the beam or redirect its power, and PDF p.48 (printed 38) lists secure operation through the coded pilot among its retrodirective conclusions. SRC-107 (NASA RP-1076, 1981) PDF p.44 (printed 15), in paraphrase: the uplink pilot carries code modulation for link security and protection against jamming; PDF p.98 (printed 69), in paraphrase: the coded pilot signal that has been developed uses a split-phase, direct-sequence pseudonoise code, modulo-2 added to optional command data, that biphase-modulates the 2450 MHz pilot carrier; PDF p.108 (printed 79), after the preliminary pilot signal specifications: a 12-stage maximal-length shift-register sequence of period 4095 is recommended as the spread-spectrum code; PDF p.267 (printed 238), in the appendix review panel report of the January 1980 microwave workshop: "not enough attention has been paid to the problem of security and antijamming", with state-of-the-art cryptography and National Security Agency standards to be built in from the outset and spread spectrum to be added for antijamming and antispoofing. CLM-0899 records the coding from RP-1076 printed p.63, and CLM-1039 the safeguards listed by the 1980 military assessment. A text search of SRC-085 and SRC-554 for coding and security terms found no description of how the coding works; a search of all 281 page texts of SRC-107 found the signal design above and no check that rejects a forged pilot. Dephasing time, CLM-1020.
Related records
- Answers question
- QST-013 not published in this release
- Supersedes
- CLM-0906 not published in this release
Cite this
energyaperture.com/c/clm-1478
CLM-1478, Energy Aperture, as of 2026-10.
Connected records
Other published records linked to this one. A list, not a judgement.
- 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.
- Also from SRC-088
- CLM-0896The patent describes measuring the incoming steering signal at scattered sensors, not at every antenna, and working out the values in...CLM-0897The satellite aims its beam by listening for a low-power signal sent up from the receiving station, measuring the shape of that arriving...CLM-0899The patent never says the steering signal is protected in any way. There is a difference between scrambling that signal so nobody can read...CLM-0900The satellite can point its beam far further than there is Earth to point at, so moving power from one receiving station to another is not...CLM-0903The shared clock tells every sensor to take its reading at the same moment. How precise that clock must be depends on how fast the thing...CLM-0905Sharing a clock is not the same as being told what to do. The clock and the carrier tell the antennas nothing about where to send the power...CLM-0913When the satellite corrects its own bending by listening to the ground signal, what is left over is not how far the antennas moved. It is...CLM-0942Three documents held here give three different sizes for the same satellite's transmitting antenna. The patent says 1 to 1.5 km across and...More on the source page.
- Also from SRC-107
- CLM-0033 (low confidence)Apart from a 1981 NASA review that found no evidence for the number and suggested a higher one, nobody was found to have revisited it, and...CLM-0060In 1981 a NASA review panel said the 230 watts per square metre figure rested on an obsolete theory with no experimental support, and made...CLM-0061The experiments were done. They found heating two or three times stronger than normal, not the tenfold effect predicted, no irregularities...CLM-0062By 1981 the theory was being revised to a steeper frequency dependence, which would raise the permitted power density.CLM-0063NASA suggested in 1981 that 550 to 600 watts per square metre might be reasonable, roughly two and a half times the figure still in use...CLM-0101The 1978 contract required the researchers to report fixes if ionospheric disturbance pushed the pilot-beam phase error past 2 to 3...CLM-0160A 1978-81 NASA design study calculated that simply pointing the satellite's structure accurately enough, without any electronic correction...CLM-0420NASA's 1981 report says the experiments found nothing supporting the 23 milliwatt limit, that the measured heating was two or three times...More on the source page.
- Also from SRC-554
- CLM-0911If the steering signal from the ground stops, the 1978 design's beam does not carry on pointing somewhere. It falls apart, and the power on...CLM-1017By 1981 the programme itself said the ionospheric limit it had designed to was probably too cautious, and worked out what relaxing it to...CLM-1018Three years of study left the efficiency chain exactly where 1978 put it, and Boeing's own version says out loud the solar constant the...CLM-1019The programme gave three reasons for choosing the klystron; the company that designed the satellite said the choice was more or less...CLM-1020By 1981 the programme was confident the beam could be pointed and formed, and named the network that carries the timing reference across...CLM-1022A loss you can make up by adding solar panels costs about 56 million dollars per percentage point; a loss at the ionospheric ceiling costs...CLM-1087When the programme wrote down why it used 2.45 GHz, its reasons were consistent: each time it named the industrial band and how the beam...CLM-1091The people running the programme said 2.45 GHz was sensible and also said, in the same breath, that nobody international had agreed to it...