• price
• payload
• optimization
• nanosatellite
• microsatellite
• microlauncher
• launch
• cost model
• analysis
• satellite
• small

Microlaunchers are small launch vehicles designed to transport up to 1000 kg of payload to Earth orbit. They are becoming increasingly relevant in the space industry due to their capacity to offer dedicated launches to small satellites. For a microlauncher to be commercially successful, it is critical to minimize the cost per kilogram of payload offered to satellite operators, which is influenced by the launch cost for the microlauncher as well as the total payload mass it is able to carry. Despite there being many projects in development, only a few microlaunchers are operative to this day, where Electron is the only modern microlauncher to offer reliable information on their commercial launches, making it necessary for theoretical studies to be developed to predict microlauncher performance.
The present thesis aims to develop a mass and cost model for a liquid propellant, ground-launched microlauncher, in the effort to understand the variables that affect the cost per kilogram of such a vehicle, where the characteristics and technologies of the Electron microlauncher will be used to validate each of the models results. Both models will be employed to compare various microlauncher configurations trying to determine those that provide the lowest costs per kilogram of payload.
The microlauncher mass model follows two different methodologies that perform complementary mass estimations. First, the optimization of a multistage microlauncher is explained, considering its propulsive characteristics and ∆v required to reach a given orbit. This optimization gives the split between propulsive and inert mass for each stage and most importantly, the payload ratio of this vehicle. The second methodology estimates the masses of the components of the most important subsystems of a microlauncher, providing a more in depth value of its inert mass. Both methodologies have been corroborated with the known mass of Electron.
A cost model has then been developed from the results of the mass model, considering the concept of the First Unit Cost, where the total cost of a microlauncher component is computed from its mass. With these values, the total cost per launch of a microlauncher is obtained, using Cost Estimation Relationships that have been adapted for microlauncher characteristics.
With both models, an estimation of the cost per kilogram of a liquid propellant microlauncher can be given. With this knowledge, multiple configurations of microlauncher vehicle and service are analyzed, including the number of stages, the engine feed system, the propellant selection, the yearly launch rate and the characteristics of the launch service.
Finally, several conclusions are reached on the main characteristics of a microlauncher and their influence on the payload ratio and launch cost to ultimately determine cost per kilogram of payload. A forecast on the future of the microlauncher market is also provided, considering the results and acquired knowledge from this thesis.