• Launch window analysis and trajectory modeling
• Low Earth orbit
• Rendezvous and proximity operations
• Lunar/interplanetary transfers
• B-plane targeting
• Swing-by and capture maneuvers (e.g., LOI)
• Descent and landing
• Formation flying, stationkeeping, or libration point missions

Trajectory design and maneuver planning are modeled in STK using:

• High-precision numerical integrators with full force models
• The High Precision Orbit Propagator (HPOP) around any central body
• User-definable central bodies, force models, coordinate systems, and vectors
• Targeting profiles for control parameter calculations based on mission specifications and constraints
• Attitude simulation with atmospheric drag, solar radiation pressure, and gravity
• Multiple gravity field models to account for the full effects of two bodies simultaneously
• Scripted mission control sequences
• Optimizer tools for maneuvers and trajectories using formal statistical analysis techniques

Spacecraft Configuration
In addition to trajectory modeling, STK can be used to help design the actual configuration and bus of the spacecraft, including power, propulsion, and attitude control, and communications systems through:

• Studying the effects of solar array sizing, placement, orientation, and obscuration
• Conducting trade studies on engine placement, thrust design, and fuel budgets
• Applying customizable engine models to trajectory and maneuver designs
• Modeling receiver and transmitter antennas (power, frequency, codes, waveform, filtering, gain, channels, tracking loops, polarization, and modulations)
• Modeling satellite cross-links and relays for Earth and libration point orbits
• Identifying time windows and available ground antennas for uplink to satellite assets directly or via crosslink
• Modeling interference effects, such as terrain, weather, and body obscuration

Payload Design
STK can be used to model scanning, spinning, fixed, or targeted sensors to define payload instrumentation constraints such as camera fields of view or beam projections, allowing users to:

• Model payload sensor capability (fields of view, footprint)
• Define dynamic Earth, lunar, and Martian pole-to-pole sensor coverage from using 3-D terrain elevation data
• Model detailed inter-visibility constraints (e.g., lighting conditions)
• Schedule sensor activities

Determine launch opportunities
Users can evaluate available launch windows and conjunction analysis from any location using ephemeredes of all tracked space objects. STK allows analysis into:

• Covariance sphere visualization for enhanced space situational awareness
• Launch contingencies (free or early return)
• Surface launch opportunities from non-Earth bodies for orbital rendezvous