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The NASA Space Launch Systems (SLS) outstanding capabilities for launching heavy, large diameter payloads will enable robust lunar architectures where the Near Rectilinear Halo Orbit (NRHO) is used as an aggregation node for lander and Orion elements. SLS capabilities and production status is discussed, as is the new large Exploration Upper Stage,...
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Context 1
... was done for a SLS lander for a NRHO campaign with assumptions as stated in Section VI, Table 6 and Table 3. This trade study compares five engine combinations for the AE and DE elements ( Table 5). The Block 1B cargo injects the Lander to TLI; the DE provides propulsion for a low dV 90 day outbound transfer to NRHO. ...Context 2
... was done for a SLS lander for a NRHO campaign with assumptions as stated in Section VI, Table 6 and Table 3. This trade study compares five engine combinations for the AE and DE elements ( Table 5). The Block 1B cargo injects the Lander to TLI; the DE provides propulsion for a low dV 90 day outbound transfer to NRHO. ...Similar publications
This paper presents an aircraft configuration trade space exploration for NASA’s SUbsonic Single Aft eNgine (SUSAN) Electrofan, which is a 180 passenger regional class transport aircraft that utilizes electrified aircraft propulsion and advanced propulsion airframe integration technologies to enable reduced fuel consumption and emissions. At its co...
Citations
This paper provides an overview of the project ‘RocketHandbrake’, which investigates the reusability of upper stages re-entering the earth’s atmosphere at high angles of attack as a means for aerodynamic braking, using Supersonic Braking Devices. For a maximum benefit, this concept takes so-called Ariane Next and Vega E -like launchers as reference configurations. However, the project does not aim to develop those launchers completely, but to clarify and focus on the required aerodynamic control surfaces, the entailed aerodynamics and resulting flow physics, flight dynamics, control laws, and structures, based on and for those example configurations. Furthermore, the results of phase one of the project are described and the decision process for choosing the Ariane Next as baseline configuration for the next project phases is detailed. This includes first aerodynamic, and mission analyses of reusable Ariane Next and Vega E upper stages featuring supersonic braking devices
Every 15 years, an Earth Mars alignment occurs that allows for a free return trajectory at Mars, which means no propulsive maneuver is required at Mars to effect an return to Earth. The vehicle swings by Mars and is thereafter on a path to intercept the Earth. This greatly reduces the energy requirements for the Earth-Mars in space stages, and allows for lighter stages and fewer launches than a stopover mission. With a trip time of 530 days, this 2033 crewed flyby mission could serve as a precursor to a later Mars surface mission. Only 4 elements are required; a long duration crew habitat, Earth return capsule, in-space stage and an Earth departure stage. Information on launch manifests, trajectories, transfer stages, operations, and challenges is presented for a crewed flight to Mars in the early 2030s.
