Select Spacecraft Page
On this page, you can explore the key features of the Moonlander simulation. First, users can select a spacecraft configuration from the available mission profiles. Then, the cockpit interface provides a live demonstration of the lander's descent, showing real-time telemetry, propulsion, and system status. All values are computed by the underlying physics engine and updated continuously.
Figure 0 — Spacecraft Selection Interface.Before entering the simulation cockpit, users can select a spacecraft configuration from the available mission profiles. Each spacecraft is defined by a JSON configuration that specifies mass properties, propulsion parameters, and initial mission conditions.
The selection interface presents all available spacecraft defined in the configuration file. The list on the left displays the available spacecraft names, while the panel on the right shows the detailed configuration parameters of the currently highlighted spacecraft. These parameters include mass distribution, thrust limits, specific impulse, initial position and velocity, and structural limits.
If the user does not explicitly select a spacecraft, the system automatically chooses the first spacecraft defined in the JSON configuration as the default. This ensures that the simulation backend always receives a valid spacecraft configuration, even if no selection is made in the UI.
Once a spacecraft is selected (or the default is applied), its configuration is transmitted to the simulation backend, where it initializes the physical model of the lander. This design separates configuration management from the simulation engine, allowing new spacecraft variants to be introduced simply by updating the configuration file without modifying simulation code.
Simulation demonstration
The following videos shows the primary cockpit interface of the Moonlander simulation during a representative descent run. All quantities are expressed in SI units and updated in real time based on the underlying C++ physics model.
Figure 1 — 1500m Descent Landing Demonstration. A complete descent from 1500 meters, showing the lander's response to the Adaptive Descent Controller and thrust adjustments in real time.
Interface Overview
NAV — Navigation
Displays the primary kinematic state of the lander, including simulation time, altitude above ground level, vertical velocity and horizontal velocity.
FUEL — Propellant State
Shows the remaining propellant mass and the current mass flow rate. Fuel consumption directly influences thrust availability and mission outcome.
LANDING VIEW — Descent Visualization
Provides a visual representation of the lander during descent. Below 1000 meters above ground level, the lander visibly approaches the surface. The autopilot can be activated by clicking on the autopilot button. Thrust can be controlled via a continuous slider (0–100%), and the simulation can be started, paused or stopped at any time.
ENGINE — Propulsion & Loads
Displays the current thrust output and the user-defined target thrust, both expressed in Newton. The resulting acceleration and g-load acting on the lander are computed internally and updated in real time.
STATUS — System State
Reports discrete system states such as OPERATIONAL , LANDED or DESTROYED, providing an explicit overview of the simulation state machine. It also reports in wheter the autopilot is activated or not plus the current information provided by autopilot such as the activated mode.