22 results found Selected 0 items No itemsClear selection Select / deselect all results (all pages, 22 total) Bio-Inspired Morphing Wing UAV for deployment from HAPS and Orbit The project demonstrates a proof-of-concept of a next generation bio-inspired morphing wing inspired by academic research of the Peregrine Falcon morphology. Asymmetric span morphing has previously been demonstrated for UAV roll control via in-plane partial span change. This design has full bird-like span change and a unique out-of-plane modality. This offers novel drag reduction characteristics when made to form an airflow channel in conjunction with a fixed surface such as the fuselage, in “cupped wing” flight. United Kingdom Discovery ETD 2020-06-a Stellar Advanced Concepts Ltd 2021 - 2022 Bio-Inspired Morphing Wing UAV for deployment from HAPS and Orbit Modelling capsule stability accounting for shape change The design of a re-entry vehicle and the analysis of its performance are extremely challenging tasks. The difficulties increase when the understanding of its transient behaviour is sought and grow even further if this transient is affected by uncontrolled phenomena such as the shape change caused by the ablation of the thermal protection material used as heat shield. Belgium TDE T718-402MP VON KARMAN INSTITUTE 2017 - 2021 Modelling capsule stability accounting for shape change Inflatable Systems for Aerocapture and Aerobraking This work has primarily focused on establishing scenarios where inflatable devices could be the most useful. Given that these missions rely on aerodynamic drag that results in (potentially significant) heating, the authors have sought to find solutions to minimize heat fluxes acting on the device surface, and especially keeping it within the limits of flexible/foldable TPS materials for the aerocapture scenario. Portugal Discovery 19-D-S-OPS-02 Spin.Works 2020 - 2021 Inflatable Systems for Aerocapture and Aerobraking Feasibility and Preliminary Design of a Moon Drone Vehicle This activity will provide for a preliminary design of a small drone vehicle that is able to autonomously depart from the surface of a rover, hover, and return to its base on top of the rover. Equipped with cameras (vision, multi spectral) and other instruments, the drone will be used to quickly explore the surroundings of the rover providing at larger distances observation and data and supplementing the observation data provided by some instruments of the rover. Italy TDE T318-602MP THALES ALENIA SPACE ITALIA SPA 2020 - 2021 Feasibility and Preliminary Design of a Moon Drone Vehicle Hypersonic simulation tool based on Lattice Boltzmann solver Over the last few years schemes based on minimal kinetic models for the Boltzmann equation are becoming increasingly popular as a reliable alternative over conventional Computational Fluid Dynamics (CFD) techniques. Due to the flexibility afforded by its close connection to the kinetic theory recent research has led to major improvements, including consistent models for aerothermodynamics and highly compressible flow in low gravity operating conditions. Belgium TDE T718-505MP CENAERO. CENTRE DE RECHERCHE EN AERONAUTIQUE ASBL 2018 - 2021 Hypersonic simulation tool based on Lattice Boltzmann solver Challenges related to the design of a reservoir for the transport of H2 This activity proposes to implement a reference model for computer simulation of storage of H2 which takes into account the role of molecular excited states. Different materials will be studied as possible candidates (intermetallic compounds, hydrides, organic liquids, nanotubes) in accordance with the existing practice in industrial applications or proposing alternative materials. Italy TDE T718-502MP UNIVERSITY OF BARI 2017 - 2021 Challenges related to the design of a reservoir for the transport of H2 Experimental characterisation of transient flow phenomena in cryogenic Fluids The activity focuses in particular when considering multiple re-ignition of upperstages. This entails waterhammer effects or pre-combustion phenomena where propellants undergo drastic changes due to sudden exposure to near-vacuum conditions. To allow proper modelling, detailed experiments need to be created for typical multi-phase, multi-component flow. Following activities are foreseen: Evaluation of the liquid front behaviour during waterhammer prior, during and after impact for different operational conditions. Belgium GSTP G614-004MP SAFRAN Aero Boosters 2016 - 2021 Experimental characterisation of transient flow phenomena in cryogenic Fluids Modelling of hot plume with particles for improved launcher applications The technical work will be organised in 2 phases. In Phase 1 a new model for hot plume with particles will be developed to include the necessary physics such that the combustion process can be computed, the evolution of the alumina can be calculated in the engine and the subsequent impact of the alumina in terms of heat radiation to the upper stages can be quantified. Finally, in Phase 2 the new model will be used in combination with any CFD code provided by the bidder and validated with experimental data provided by ESA. Switzerland GSTP G614-011MP CFS ENGINEERING SA 2015 - 2020 Modelling of hot plume with particles for improved launcher applications Preliminary Activities for a Mars Balloon Probe . Germany GSTP G637-001TFg Mars Society Deutschland e.V. 2017 - 2020 Preliminary Activities for a Mars Balloon Probe Aerodynamic of Hypervelocity Bodies ESA has long experience with LEO entry missions like Hermes, ARD, MSRO, and more recently EXPERT and IXV among others. Based on an experience of more than 4 decades of aerodynamic assessment, which have supported most of European space related projects, it is the opportunity to extend the prediction capability to the upper range of the hypersonic, the hypervelocity, to adapt the European Industry to the need of future missions and events. Belgium GSTP G614-009MP VON KARMAN INSTITUTE 2015 - 2019 Aerodynamic of Hypervelocity Bodies Pagination « First First page ‹‹ Previous page 1 2 3 ›› Next page Last » Last page Filter by Programme TDE (10) GSTP (7) Preparation (3) Discovery (2) Filter by Start Year 2021 (6) 2017 (4) 2015 (3) 2022 (3) 2019 (2) 2020 (2) 2016 (1) 2018 (1) Filter by End Year 2023 (8) 2021 (6) 2019 (2) 2020 (2) 2022 (2) 2018 (1) 2024 (1) Filter by Keywords 1-Launchers (3) aerocapture (3) aerobreaking (2) athmospheric drag (2) Mars (2) Orbital capture (2) Orbit insertion (2) Re-entry (2) 1-Avionics and Processing (1) 7-Sensing & Positioning (1) 18-Aerothermodynamics (1) 33-Space and Energy (1) 37-Exploration Technology (1) ADR (1) aerobraking (1) bio-inspired (1) Biomimetics (1) Biomimicry (1) decelerator device (1) HAPS (1) inflatable (1) interplanetary transfer (1) IOS (1) OOS (1) refuelling (1) Servicing (1) UAV (1) Filter by Contractor DLR - German Aerospace Center (2) THALES ALENIA SPACE ITALIA SPA (2) VON KARMAN INSTITUTE (2) VORTICITY LTD (2) ArianeGroup (1) ArianeGroup GMBH (1) ASTOS SOLUTIONS GMBH (1) Astroscale (1) CENAERO. 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