Simplified Mars Rocket Trajectory Calculator
This tool estimates the feasibility of a Trans-Mars Injection (TMI) burn and Hohmann transfer time, with a simplified visual representation. It does not calculate a true optimal trajectory. See notes at the bottom for simplifications.
Calculation Results:
Enter values above and click "Calculate & Visualize" to see results and animation.
Key Simplifications & Notes:
- Optimal Trajectory: This is a simplified model, not a true multi-variable optimization. It calculates requirements for a specific type of transfer (Hohmann-like departure).
- Planetary Alignment: Assumes average orbital distances for Hohmann time; does not consider actual planetary positions or launch windows. Visualization shows a conceptual alignment.
- Gravity: Considers Earth's gravity for orbit/escape and Sun's gravity for interplanetary Hohmann transfer time. Does not model n-body effects.
- Burns: Assumes instantaneous (impulsive) burns. Does not account for gravity losses during finite burn times or atmospheric drag during ascent.
- Phases Not Included: Does not calculate delta-V for mid-course corrections, Mars Orbit Insertion (MOI), landing, or Earth re-entry. The TMI burn is only for leaving Earth's sphere of influence towards Mars.
- Hyperbolic Excess Velocity (v-infinity): A fixed target of 2.9 km/s is used for the Trans-Mars Injection. This is a typical value for efficient transfers.
- Visualization: The animation is a simplified 2D representation and not to scale for actual interplanetary distances, but illustrates the concepts. Earth's parking orbit is exaggerated for visibility.
