A propellant trade-off analysis model on Excel for green, storable propellant candidates that are potentially suitable for a lunar lander which must meet the REACH regulations

A propellant trade-off analysis model on Excel for green, storable propellant candidates that are potentially suitable for a lunar lander which must meet the REACH regulations:

Estimates the final mass of a lander for each propellant based on their respective specific impulse estimates used to scale the ratio of final mass to payload mass, assuming a 100kg payload.

Computes the required propellant mass for each candidate to meet a total delta v of 3750m/s using each of their respective final mass and specific impulse estimates.

Uses the oxidiser to fuel ratio and known densities of each propellant candidate to calculate the required tank volumes before assigning a material and maximum allowable stress, and calculating the required tank wall thickness, mass and total outer volume of each candidate's system.

Scores each propellant candidate from 1 to 5 for the following criteria: total wet mass, total volume, storability, toxicity, complexity, availability of high technology readiness level (TRL) hardware, and estimated associated cost of development.

Applies weightings to the scoring criteria to produce final scores for each propellant candidate before running a sensitivity analysis to assess the robustness of the weightings chosen.

The consistently highest scoring propellant is RP1 Kerosene fuel with High-Test Peroxide (HTP) oxidiser.