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Utilization of H2O2 in Transpiration Cooling System for Active Heat Protection and Implementation of Thermal Decomposition for Catalyst Free H2O2/Kerosene Bipropellant Aerospike Rocket Engine

Project description

Efficient, compact, and durable propulsion system for sustainable satellite orbits

The surge in small satellite launches has led to an increase in orbital collisions, generating unprecedented space debris. To safeguard the longevity of our orbits, a compact, stable, and environmentally friendly propulsion system is imperative for small satellites. With the support of the Marie Skłodowska-Curie Actions programme, the HYPER-CAT project aims to develop an advanced propulsion system for small satellites. Using Hydrogen Peroxide (H2O2) and aerospike engines, the project tackles issues like catalyst degradation and extreme thermal loads. By leveraging the thermal decomposition process of H2O2, the team turns cooling challenges into an advantage. Liquid H2O2 absorbs heat convectively, creating gas layers to protect the structure, eliminating the need for catalysts.

Objective

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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HORIZON-TMA-MSCA-PF-EF - HORIZON TMA MSCA Postdoctoral Fellowships - European Fellowships

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(opens in new window) HORIZON-MSCA-2022-PF-01

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Coordinator

TECHNISCHE UNIVERSITAET DRESDEN
Net EU contribution

Net EU financial contribution. The sum of money that the participant receives, deducted by the EU contribution to its linked third party. It considers the distribution of the EU financial contribution between direct beneficiaries of the project and other types of participants, like third-party participants.

€ 189 687,36
Address
HELMHOLTZSTRASSE 10
01069 DRESDEN
Germany

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Region
Sachsen Dresden Dresden, Kreisfreie Stadt
Activity type
Higher or Secondary Education Establishments
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Total cost

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