of the NGL is driven by the requirement to provide a highly flexible launch system at minimized exploitation cost with a wide range of performance and mission capabilities available around 2025. The launch system concept investigations for the Next Generation Launcher (NGL) are part of the ESA Future Launchers Preparatory Programme (FLPP) which has the objective to prepare the technical and programmatic elements for making an informed decision on the best launch system to respond to the future institutional needs, while maintaining competitiveness on the commercial market. On some technologies rather than assessing the effectiveness and the advantages of aĪ look on the HV research programs developed so far is hereinafter described Most of these projects, however, were just prototypes orĭeveloped at the conceptual design stage and linked to flight testing focused mainly Germany, Italy, and Japan to simplify access to LEO and sustained high-speed flight Indeed, several high-speed aircraft concepts (i.e., lifting and winged vehicles) haveīeen conceived or developed in the USA, Russia (former USSR), Europe, France, Vehicle (HV) has driven continued researches in basic and applied technologies. In less than 2–3 hours, thus providing a lot of insights on the oncoming market ofĪs a result, over the decades the potential benefit of an operational hypersonic Many start-up industries areįocusing attention on hypersonic aircrafts able to fly, e.g., from New York to Sydney On the other hand, in the last few years, the attention to hypersonic travels forĬivilian application has also increased dramatically. Today this need is utmost stringent in the light of the NASA LEO to improve the levels of flexibility, affordability and safety of routine accessto. The increase in manned and unmanned space operations in low earth orbit (LEO)ĭemands an evolution in the vehicle for payloads transportation up to and from In the aviation field, great interest is growing in high-speed vehicle design. Besides these baseline requirements the extension of certain system architectures for demanding institutional missions (heavy LEO payload insertions) based on a Common Core Booster approach is being investigated as well. The required performance flexibility shall be achieved by using the same core configuration for the launch vehicle while providing the performance augmentation mainly by means of solid propellant strap-on boosters. This flexibility is expressed by the requirement to cover a performance range from 3.0 tons up to 8.0 tons in GTO with an intermediate step at 5.0 tons while being furthermore capable of performing missions into a variety of other orbits such as MEO, GEO, LEO and SSO. The conception of the NGL is driven by the requirement to provide a highly flexible launch system at minimized exploitation cost with a wide range of performance and mission capabilities to replace Ariane 5 around 2025.
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