{
  "title": "NSTAR DS1 flight points transcribed from JPL Publication 00-10 Table 12",
  "source_url": "https://pdssbn.astro.umd.edu/holdings/ds1-c-micas-3-rdr-visccd-borrelly-v1.0/document/doc_Apr04/int_reports/IPS_Integrated_Report.pdf",
  "source_sha256": "C160FE9CA4D81174B7D51FC6FDDC61D368C7AA3176D0B51F1D2891E8003BA77F",
  "locator": "PDF page 40 / printed page 33, Table 12",
  "plot": {
    "x": "PPU input power (kW)",
    "y": "navigation-derived in-flight thrust estimate (mN)",
    "marks": "14 points, preserving repeated throttle levels; no fitted curve or extrapolation",
    "uncertainty": "No bars plotted. Report \u00a72.6.2.4 estimates <0.5 mN uncertainty in navigation-derived thrust; this is not described as a 1-sigma or 95% interval and does not include calculated-thrust model error."
  },
  "boundary": "PPU input is not the same quantity as engine input; thrust is inferred from Doppler/radio tracking and a spacecraft-mass-versus-time model, not measured by an onboard load cell. Table 12 does not label each row by mission phase or operating mode.",
  "limitations": [
    "14 observations span 13 distinct throttle-level pairs; repeated levels are shown as separate points.",
    "No curve fit, interpolation, or extrapolation is supplied.",
    "At mission throttle level 83 (about 1.82 kW engine input), the report notes measured thrust up to 1.6 mN below the calculated value; figure error bars exclude calculated-thrust model uncertainty.",
    "This was flight use of solar electric propulsion after launch, not launch from Earth."
  ]
}