{
  "title": "Idealized spacecraft example from a measured AEPS operating point",
  "source": {
    "authors": "Jason D. Frieman et al.",
    "nasa_ntrs_document_id": "20210015735",
    "url": "https://ntrs.nasa.gov/citations/20210015735",
    "location": "2021 JANNAF presentation, slide 13, AEPS PPE test table, operating point 8"
  },
  "source_data_file": "aeps-ppe-test-data.csv",
  "source_row": {"point_id": 8, "discharge_power_W": 12000, "thrust_mN": 594, "specific_impulse_s": 2740, "total_efficiency_percent": 66.1, "reported_thrust_uncertainty_mN": 5, "reported_specific_impulse_uncertainty_percent": 0.9},
  "calculation": {
    "initial_mass_kg": 1000,
    "assumptions": ["constant thrust, specific impulse, discharge power and efficiency", "continuous operation", "no spacecraft power-system mass or trajectory dynamics"],
    "effective_exhaust_speed": "Isp * 9.80665 m/s",
    "propellant_flow": "measured thrust / effective exhaust speed",
    "ideal_delta_v": "effective exhaust speed * ln(initial mass / current mass)",
    "status": "Illustrative calculation from a laboratory operating point; not a flight result or mission prediction."
  },
  "limits": ["No solar-array or power-system mass", "No changing power with distance or orientation", "No engine lifetime or thermal limit", "No gravity, orbit geometry, thrust steering, coast periods or navigation", "Source measurement uncertainty is not propagated into a mission confidence interval"],
  "reproduction": "Run reproduce-aeps-mission-example.py with Python 3 standard library from any directory; it reads this directory's NASA-source table and writes CSV and SVG outputs."
}