To support the development of free-space-optical (FSO) communication technologies, an end-to-end physical layer model of a satellite communication service was developed. This service involves physical processes spanning multiple time scales: hours (relative platform dynamics), minutes (link selection, atmospheric attenuation), milliseconds (atmospheric turbulence, platform disturbances), and nanoseconds (photon and bit transportation). The modified multi-scale method (MMM) was used to combine the physics of these processes and to model an end-to-end global FSO communication service between an airborne platform and a satellite constellation. The method provides a better understanding of physical interdependencies, allows performance analysis on multiple time scales, and enables valuable insight into where to optimize such a service. The results show realistic performance metrics when compared to other smaller-scale models and demonstrations. The MMM can be used as a mission performance indicator of an end-to-end satellite communication service.

With Mars colonisation becoming a reality for the near future, it is of importance to analyse how crew and cargo can be transported between Earth and a colony on Mars. This article is a feasibility and design study of a launch vehicle whose mission is to shuttle crew and cargo from Low Mars Orbit to a colony on the Martian surface. A single-stage reusable rocket has been selected to fulfil this mission, code-named Charon. The mission profile of such a vehicle was created, leading to a Maximum Growth Allowance (MGA) Delta-V budget of 6.2 km/s. With the mission profile in mind, each subsystem underwent a preliminary design. With reliability and maintainability in mind, subsystems were designed for redundancy and modularity, and an abort system was included for an added level of safety. The iterative design process resulted in a vehicle with a MGA mass of 198.7 tons, capable of transporting 1200 kg of cargo and a crew of 6 people to a 500 km orbit and back. The preliminary design of the vehicle is deemed safe. Following a fault tree analysis, the Single Launch Loss of Mission, Vehicle and Crew (SL-LOM, SL-LOV, SL-LOC) probabilities are computed to be of 0.975%, 0.12%, and 0.079%. Finally, from the vehicle’s constraints on the base, the feasibility of the project has been reflected upon. It is deemed that such a concept is of high interest only when the base is already operational, due to the launch and maintenance infrastructure that it requires, as well as the power it requires from the Martian base.