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Future earth orbit transportation systems/technology implications
12
Citations
0
References
1976
Year
Space VehicleEngineeringTransportation Systems ModelingSea VehiclesDesign IntegrationSpace TransportationSystems EngineeringLogisticsTransport InfrastructureTransportation Systems AnalysisAircraft Design ProcessTransportation EngineeringTransportation SystemsOdinex AnalysisMechatronicsRocket EngineAerospace Propulsion SystemsPropulsionSustainable TransportAerospace EngineeringBusinessAerodynamicsAerospace PropulsionSpace Shuttle Technology
The study examines how advances beyond current Space Shuttle technology could enhance single‑stage‑to‑orbit vehicle performance. Using the ODINEX optimization program, the authors designed a wing‑body SSTO with LOX/LH engines, variable‑ratio nozzles, and explored assisted‑takeoff and air‑breathing propulsion rendezvous concepts. The analysis predicts a roughly 30 % increase in payload capacity by reducing weight and drag and improving propellants and engines.
Assuming Space Shuttle technology to be state-of-the-art, projected technological advances to improve the capabilities of single-stage-to-orbit (SSTO) derivatives are examined. An increase of about 30% in payload performance can be expected from upgrading the present Shuttle system through weight and drag reductions and improvements in the propellants and engines. The ODINEX (Optimal Design Integration Executive Computer Program) program has been used to explore design options. An advanced technology SSTO baseline system derived from ODINEX analysis has a conventional wing-body configuration using LOX/LH engines, three with two-position nozzles with expansion ratios of 40 and 200 and four with fixed nozzles with an expansion ratio of 40. Two assisted-takeoff approaches are under consideration in addition to a concept in which the orbital vehicle takes off empty using airbreathing propulsion and carries out a rendezvous with two large cryogenic tankers carrying propellant at an altitude of 6100 m. Further approaches under examination for propulsion, aerothermodynamic design, and design integration are described.