Interplanetary Transport System "Horizon"

This paper presents a comprehensive scientific and engineering analysis of the
concept of a reusable manned interplanetary transport system designated Horizon,
intended for regular expeditions to the Moon, Lagrange points, and Mars, with subsequent return and multiple reuse. The study encompasses a complete investigation
of the spacecraft architecture, including calculations of the nuclear-electric propulsion
system, optimization of continuous acceleration and deceleration trajectories, thermal
balance of the radiator system, crew radiation protection, as well as dynamic and
structural stability. A key innovation is the use of a deployable tether-based artificial
gravity system, which replaces massive centrifuges, offering significant mass savings and
reduced physiological stress on the crew. Flight time calculations were performed using a continuous low-thrust model, demonstrating the feasibility of reducing the transit
time to Mars to 116–164 days depending on the initial mass. An orbital refueling system is considered as a key element of sustainable interplanetary logistics. The Horizon
project could serve as the basis for the creation of a reusable interplanetary transport
infrastructure for the Solar System.