Vibeship-spawner-skills mission-planning

id: mission-planning name: Mission Planning category: space version: 1.0.0 description: > Use when designing space missions, computing launch windows, optimizing trajectories, analyzing payload constraints, or planning mission phases and contingencies.

triggers:

• "mission design"
• "launch window"
• "trajectory optimization"
• "mission timeline"
• "mass budget"
• "propellant budget"
• "mission phases"
• "porkchop plot"
• "C3"
• "gravity assist"
• "low thrust"
• "mission architecture"
• "LEO"
• "GEO"
• "interplanetary"

provides:

• name: launch_window_analysis description: Compute launch windows for LEO, GEO, sun-sync, and interplanetary missions
• name: trajectory_optimization description: Optimize trajectories including porkchop plots and gravity assists
• name: mission_timeline description: Define mission phases from launch through disposal
• name: mass_budget description: Spacecraft mass allocation and propellant sizing

knowledge_base: mission_types: by_destination: LEO: "< 2000 km altitude" MEO: "2000 - 35786 km" GEO: "35786 km (geostationary)" Lunar: "Moon orbit or surface" Interplanetary: "Beyond Earth-Moon system" Deep_Space: "Outer planets and beyond" by_orbit_type: - Circular - "Elliptical (Molniya, GTO)" - "Sun-synchronous" - "Frozen orbit" - "Halo/Libration point" by_purpose: - Earth Observation - Communications - Navigation - Science/Exploration - Human Spaceflight

launch_sites: kennedy: name: "Kennedy Space Center" latitude: 28.524 longitude: -80.651 azimuth_range: "35-120 deg" vandenberg: name: "Vandenberg SFB" latitude: 34.632 longitude: -120.611 azimuth_range: "147-201 deg (polar/SSO)" baikonur: name: "Baikonur Cosmodrome" latitude: 45.965 longitude: 63.305 azimuth_range: "35-99 deg" kourou: name: "Guiana Space Centre" latitude: 5.232 longitude: -52.769 azimuth_range: "-10 to 93 deg" note: "Minimum achievable inclination = launch site latitude"

launch_windows: leo_rendezvous: description: "Launch when site rotates under target orbital plane" frequency: "2 opportunities per day (ascending/descending)" duration: "~10 minutes typical" geo: description: "Target longitude alignment" frequency: "1 window per day" duration: "~90 minutes with GTO insertion" sun_sync: description: "Based on Local Time of Ascending Node (LTAN)" common_ltans: - "6:00 (dawn-dusk, low sun glint)" - "10:30 (morning, good illumination)" - "13:30 (afternoon, Landsat heritage)" inclination: "~98 deg for 700 km altitude" interplanetary: description: "Synodic period alignment for minimum energy transfer" earth_mars: "~26 months between opportunities" earth_venus: "~19 months between opportunities" window_duration: "~30 days around optimal"

trajectory_optimization: porkchop_plot: description: "C3 contours vs departure/arrival dates" use: "Find minimum energy launch windows" parameters: "Departure date, arrival date, launch C3" gravity_assist: description: "Use planetary flyby to change velocity" benefit: "Free delta-v from planet's orbital motion" examples: - "VVEJGA (Venus-Venus-Earth-Jupiter)" - "Voyager grand tour" low_thrust: description: "Electric propulsion spiral transfers" characteristics: - "High Isp (1000-3000s)" - "Low thrust (mN to N)" - "Long transfer times" - "Continuous thrust arcs"

mission_phases: typical_leo: - name: Launch duration: "~10 minutes" events: "Liftoff, Max-Q, stage separations, fairing jettison" - name: Orbit Insertion duration: "~1 hour" events: "Upper stage burn, separation, solar array deploy" - name: Commissioning duration: "~30 days" events: "Checkout, calibration, pointing verification" - name: Operations duration: "Mission life - 30 days" events: "Primary mission activities" - name: Disposal duration: "~30 days" events: "De-orbit burn, passivation, final contact" interplanetary: - Launch and Earth departure - Cruise with trajectory corrections (TCMs) - Approach and orbit insertion - Science operations - Extended mission (if funded)

mass_budget: categories: - Structure (primary, secondary, mechanisms) - Power (solar arrays, batteries, electronics) - ADCS (wheels, thrusters, sensors) - Propulsion (engine, tanks, propellant) - Thermal (MLI, heaters, radiators) - Communications (transponder, antennas) - C&DH (computer, data recorder) - Payload (mission-specific) margins: early_phase: "30%+ contingency" preliminary: "20% contingency" critical_design: "10% contingency" flight: "0% (actual mass)" rocket_equation: "delta_v = Isp * g0 * ln(m_wet / m_dry)"

propulsion_sizing: isp_by_type: cold_gas: 70 monopropellant: 220 bipropellant: 320 ion: 3000 hall: 1500 tank_mass_fraction: cold_gas: 0.5 monopropellant: 0.15 bipropellant: 0.10 electric: 0.05

patterns:

• name: mission_concept_development steps:

  • "Define science/mission objectives"
  • "Derive requirements (orbit, pointing, data rate)"
  • "Select mission architecture"
  • "Trade study on orbit types"
  • "Preliminary mass and power budget"
  • "Identify launch vehicle options"

• name: trajectory_design steps:

  • "Generate launch window candidates"
  • "Create porkchop plots for options"
  • "Select baseline trajectory"
  • "Design backup trajectories"
  • "Calculate delta-v budget with margins"
  • "Verify launch vehicle capability"

• name: operations_planning steps:

  • "Define mission phases and transitions"
  • "Identify critical operations"
  • "Plan contingency procedures"
  • "Schedule ground contacts"
  • "Allocate data volume per pass"
  • "Document flight rules"

anti_patterns:

• name: single_launch_window problem: "Mission fails if window missed" solution: "Always identify backup windows"
• name: optimistic_mass_budget problem: "No margin for growth" solution: "20%+ contingency in early phases"
• name: ignoring_station_keeping problem: "Orbit degrades over time" solution: "Budget delta-v for orbit maintenance"
• name: single_string_critical_path problem: "Any failure ends mission" solution: "Redundancy for critical functions"
• name: no_disposal_plan problem: "Space debris liability" solution: "Plan end-of-life from start (25-year rule)"

checklist: requirements: - "Science/mission objectives documented" - "Success criteria defined" - "Constraints identified (cost, schedule, mass)" - "Stakeholder requirements captured" trajectory: - "Launch windows identified" - "Primary trajectory designed" - "Backup trajectories available" - "Delta-v budget with margins" mass_budget: - "All subsystems accounted" - "Margins applied (20%+ for early phase)" - "Propellant sized for delta-v budget" - "Launch vehicle capability verified" timeline: - "All phases defined" - "Key events scheduled" - "Critical operations identified" - "Contingency time included" risk: - "Failure modes identified" - "Redundancy plan in place" - "Contingency procedures documented" - "Abort options defined"