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Financement de l’UE (189 687 €) : Utilisation de H2O2 dans le système de refroidissement par transpiration pour la protection active contre la chaleur et mise en œuvre de la décomposition thermique … Hor14/07/2023 Programme de recherche et d'innovation de l'UE « Horizon »
Vue d’ensemble
Texte
Utilisation de H2O2 dans le système de refroidissement par transpiration pour la protection active contre la chaleur et mise en œuvre de la décomposition thermique pour un moteur de fusée Aerospike à bipropergol H2O2/kérosène sans catalyseur
The rapid increase in the number of small satellites in recent years has dramatically boosted the probability of orbital collisions that inevitably create space debris. To preserve the orbit's sustainability, a storable/stable, environmentally-friendly, highly efficient, and compact propulsion system is required to be mounted on the satellites. Hydrogen Peroxide (H2O2) and aerospike engines are promising candidates if the major flaws are solved: catalyst performance degradation due to stabilizer poisoning and extreme thermal loads at the spike structure. In this proposal, I want to test the novel concept of utilizing the thermal decomposition process of H2O2 by turning the aerospike engine's cooling challenges into an advantage. Liquid H2O2 adsorbs heat from the structure convectively, then vaporizes/decomposes to create gas layers to protect the structure from the direct contact of the combustion gas. The thermal decomposition of H2O2 eliminates the use of catalysts. Overall, the concept offers a unique approach to an efficient, compact, and durable propulsion system for small satellites. In the project, liquid H2O2 will be injected into the H2O2/Kerosene staged-combustion vitiated-air heater through the additive manufactured porous metallic wall (Fraunhofer IWS). Testing in various conditions, heat flux/temperature/pressure will be measured directly. Key variables (Da and H*) can't be directly measured. Hence, the mathematical model will be formulated to derive these variables under given conditions. The model will be validated by comparing the mono/bipropellant flame front locations between the simulations/experiments. Then, I will generate a low-order modeling tool that can predict the cooling performance and combustion efficiency based on the data and the model. The tool will be implemented to apply the new concept to existing TUD etholox rockets. The spike module will be fabricated, integrated and tested for concept verification.
| TECHNISCHE UNIVERSITAET DRESDEN | 189 687 € |
https://cordis.europa.eu/project/id/101110555
Cette annonce se réfère à une date antérieure et ne reflète pas nécessairement l’état actuel. L’état actuel est présenté à la page suivante : Technische Universität Dresden KöR, Dresden, Allemagne.
