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Problem Definition: In reusable systems, health monitoring of critical subsystems is mandatory during operation in order to account for all influences and to ensure a safe and reliable access to space independent from the previous uses.
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Problem Definition: The efficiency of reuse depends directly on the concept for RLV recovery, including the extend of recovery (e.g. engine section vs. full stage) and the recovery strategy (propelled, by parachute, mid-air retrieval, glide-back, etc.). Especially for retro propulsion as utilised in vertical landings, the interaction of nozzle and ambient flow needs to be investigated.
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Problem Definition: Due to the complexity of RLVs, one ESR will cover system design aspects. A fast interdisciplinary design process is key to successful analyses of future RLV. Fast structural design methods are needed which take into account the actual flight loads, allow for rapid variation in the design space and are flexible enough for complex cross-section shapes.
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Problem Definition: Future rocket engines aimed at RLV applications require high fatigue life and optimised engine cycles w.r.t. maximum durability and minimum maintenance costs. This requires novel approaches in engine design and verification.
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Problem Definition: The recent inclusion of hydrazine into the candidate list of SVHC in accordance with the REACH regulation has made the identification and the experimental investigation of green propellants critical for future launchers. Particularly in current upper stages, the primary propulsion is powered by storable toxic propellants or by cryogenic combinations.
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Problem Definition: ANCs can improve the design and performance of launch vehicles. The best ANC solution is closely related to the overall launcher design. However, a practical approach able to quickly and safely design optimized ANC basing on the overall launcher architectural and mission constraints has not yet been developed.
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Problem Definition: The capability to predict aerodynamic forces, moments and wall heat fluxes for various shapes & physical phenomena encountered during re-entry is of particular importance for RLV, but also for safe disposal of upper stages.
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Problem Definition: HREs have been investigated through lab-scale firing tests and numerical simulations, from 1D representations of the complete engine to detailed yet complex 3D and time resolved simulations of the internal combustion chamber geometry. These approaches do not allow the understanding of the complete engine behaviour and maturing the technology.
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Problem Definition: HREs could replace existing bi-liquid engines for new applications such as nano-launchers or orbital insertion of multiple payloads in various orbits as HREs offer much lower costs and large throttle ability. Drawbacks are related to the difficult to control oxidizer to fuel ratio during operation and to the residual inert mass.
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Problem Definition: Current low to medium specific impulse upper stage propulsion systems are all pressure fed because conventional turbopump systems do not offer advantages in performance and cost at low engine pressure levels. Electrical pump-feeding will allow to keep the overall performance of current propulsion systems using green propellants at moderate cost burden.
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Problem Definition: One ESR is dedicated to the overall system design of upper stages due to the complexity of upper stage design aspects including the development of green propulsion systems, electric pump-feeding and HRE’s as well as the adherence to safe disposal requirements and novel GNC solutions for injecting multiple payloads to different orbits.
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Problem Definition: Determining the exact place and time of re-entries is still challenging because different uncertainties need to be considered. In today’s launcher development, very conservative methods like combinatorial reliability are applied for reliability calculation. This frequently leads to masses and costs higher than necessary.
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Problem Definition: While single orbit injection is the routine, multiple platforms in orbit insertion is available but the secondary payloads have to accept the injection in the main satellite trajectory neighbourhood. Thus, multiple platform injections in dedicated and different trajectories with high level of accuracy need novel GNC designs.
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Expected Results: The optimal GNC and path planning strategy for future launchers design, depending on the propulsion architecture, ensuring a large reusability and flexibility with respect to the range of the orbital insertion conditions requests.
Problem Definition: Re-entry, descent and precision soft landing in atmosphere is very challenging. Europe has no flown experience for such launcher elements. The atmosphere presence demands nonlinear and robust control strategies to cope with the non-linearities and numerous uncertainties to be identified and implemented in the simulation software. Retargeting performance is envisaged as well.
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Expected Results: A tool to synthesize robust GNC for unmanned atmospheric re-entry vehicles under precision and soft landing constraints, depending on the specification of the vehicle itself and its dynamical conditions.
Problem Definition: A key challenge of reusable re-entry systems with multiple flight capabilities is the missionisation of the vehicle’s MA and GNC, which refers to both the recurrent activity to tailor the MA and GNC solution for the vehicle for one particular mission and also the capability of providing a single solution that is qualified for multiple landing sites.
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The project leading to this application has received funding from the European Union’s Horizon 2020 research and innovation programme under the Marie Skłodowska-Curie grant agreement No 860956.
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