HYPER-CAT
Financiado
Utilization of H2O2 in Transpiration Cooling System for Active Heat Protection a...
Utilization of H2O2 in Transpiration Cooling System for Active Heat Protection and Implementation of Thermal Decomposition for Catalyst Free H2O2/Kerosene Bipropellant Aerospike Rocket Engin
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, en...
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.
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Duración del proyecto: 34 meses
Fecha Inicio: 2023-07-10
Fecha Fin: 2026-05-12
Fecha Fin: 2026-05-12
Línea de financiación: concedida
El organismo HORIZON EUROPE notifico la concesión del proyecto el día 2023-07-10
Línea de financiación objetivo
El proyecto se financió a través de la siguiente ayuda:
HORIZON-MSCA-2022-PF-01-01:
MSCA Postdoctoral Fellowships 2022
Cerrada
hace 2 años
Presupuesto
El presupuesto total del proyecto asciende a
190K€
Líder del proyecto
TECHNISCHE UNIVERSITAET DRESDEN
No se ha especificado una descripción o un objeto social para esta compañía.
Perfil tecnológico
TRL
4-5
Perfil tecnológico
TRL
4-5