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Optimal launch windows and mission planning for planetary destinations
Looking for the next launch? Every upcoming launch, with countdowns and streams, is on Mission Control: the launch schedule
Moon - Orbit mission via Direct transfer
Near-term lunar window. Suitable for cargo and crew rotation missions to Gateway.
Trans-lunar injection window. Direct transfer to lunar orbit with minimal delta-V.
Transfer to Sun-Earth L2 Lagrange point. Near-continuous availability with low delta-V requirements.
Standard lunar transfer window. Favorable geometry for south pole landing sites.
Low-energy lunar transfer via weak stability boundary. Lower delta-V at the cost of longer travel time.
Venus transfer window for flyby or orbit insertion. Can serve as gravity assist for outer planet missions.
Type I Hohmann transfer to Mars. Optimal window for minimum-energy trajectory during 2026 opposition.
Jupiter transfer via Venus or Earth gravity assist. Significantly reduces delta-V compared to direct Hohmann transfer.
Low-energy transfer to Ceres via Mars gravity assist. Ion propulsion recommended for efficient trajectory.
Saturn transfer requiring Jupiter gravity assist. VVEJGA trajectory minimizes propellant requirements.
Minimum energy elliptical transfer
Uses gravitational assists for lower delta-V
Planetary flyby to gain velocity
Shortest time, highest energy
Launch windows are calculated based on orbital mechanics and represent optimal transfer opportunities. Actual mission planning requires detailed trajectory analysis and spacecraft-specific parameters.
Optimal launch windows and mission planning for planetary destinations
Looking for the next launch? Every upcoming launch, with countdowns and streams, is on Mission Control: the launch schedule
Moon - Orbit mission via Direct transfer
Near-term lunar window. Suitable for cargo and crew rotation missions to Gateway.
Trans-lunar injection window. Direct transfer to lunar orbit with minimal delta-V.
Transfer to Sun-Earth L2 Lagrange point. Near-continuous availability with low delta-V requirements.
Standard lunar transfer window. Favorable geometry for south pole landing sites.
Low-energy lunar transfer via weak stability boundary. Lower delta-V at the cost of longer travel time.
Venus transfer window for flyby or orbit insertion. Can serve as gravity assist for outer planet missions.
Type I Hohmann transfer to Mars. Optimal window for minimum-energy trajectory during 2026 opposition.
Jupiter transfer via Venus or Earth gravity assist. Significantly reduces delta-V compared to direct Hohmann transfer.
Low-energy transfer to Ceres via Mars gravity assist. Ion propulsion recommended for efficient trajectory.
Saturn transfer requiring Jupiter gravity assist. VVEJGA trajectory minimizes propellant requirements.
Minimum energy elliptical transfer
Uses gravitational assists for lower delta-V
Planetary flyby to gain velocity
Shortest time, highest energy
Launch windows are calculated based on orbital mechanics and represent optimal transfer opportunities. Actual mission planning requires detailed trajectory analysis and spacecraft-specific parameters.