HYDRA

HYBRID ABLATIVE DEVELOPMENT FOR RE-ENTRY IN PLANETARY ATMOSPHERIC THERMAL PROTECTION

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 Obiettivo del progetto (Objective)

The aim of this proposal is the development of TPS for their use in space applications with extreme oxidative environments and high temperature resistance, such as hot parts of space vehicles for orbital entry (ARV), planetary probes and NEO exploration. Previous studies on ARV vehicle have shown that TPS hybrid systems based on ablators integrated with thermo-structural materials are good candidates. Europe has limited research and producers in ablative materials, almost abandoned since ARD missions in the 80´s. Recently the Moon robotics exploration program within ESA demands ablative solutions for thermal protection of planetary probes.

As expressed in the work program 2011, the space sector is contributing to the independence, security and prosperity of Europe. In this way, the European Commission has stated that a non-dependent access to the critical space technology is required at Europe level. The development and testing of ablative materials has not been intensively studied in European in the last 10 years, and few producers have been maintaining the capabilities for dual applications.

These technical approach is focused on a Hybrid TPS based on ablative/thermostructural assembly and their further testing rather than on the material development. The hybrid systems development will be addressed to the integration of ablative outer-shield and their joining with thermostructural frames based on ceramic composites and will provide an innovative technology solution consistent with European supplier’s capacities. In particular the joining of the different parts will be carried out by the use of advanced bonding technologies. The ablative parts will consist of two kinds of materials (resin based and cork based) while the CMCs will be based on carbon fibres reinforced SiC conventional composites. Relevant on-ground re-entry testing will be carried-out in a “plasma wind tunnel” facility and the results will be contrasted with the envisaged specifications.

Introduzione (Teaser)

Spacecraft require advanced thermal protection systems (TPSs) for atmospheric re-entry. EU-funded scientists are developing a concept with reduced weight and enhanced performance that will also relieve dependence on foreign space technologies.

Descrizione progetto (Article)

Ablative materials designed to slowly burn away in a controlled manner are a promising solution for atmospheric re-entry vehicles based on conventional capsule designs that are now being revisited. Europe has conducted minimal research into ablative materials since the 1980s but development is now seen as an important component of reducing dependence on other countries for critical space technology.

EU-funded scientists are developing innovative TPSs for superior performance compared to traditional carbon phenolic materials within the project 'Hybrid ablative development for re-entry in planetary atmospheric thermal protection' (http://www.hydra-space.eu/ (HYDRA)) .

The HYDRA concept combines an ablative outer shield with higher heat resistance together with low-mass, lightweight thermostructural frames from ceramic matrix composites (CMCs) to provide structural support. The hybrid design will improve thermal protection and corrosion resistance as well as enhance shock absorption and damage tolerance. Joining technologies will be key to project success.

Following comprehensive analysis of current and planned space missions, scientists chose Earth re-entry missions as a starting point and developed associated specifications for the hybrid TPS. A matrix of state-of-the-art ablative materials was constructed, including performance criteria as well as availability, with particular attention paid to International Traffic in Arms Regulations (ITAR) of the United States government.

The team chose two different materials for the protection shield, the first a rigid carbon graphite felt impregnated with a phenolic resin and the second a cork-based composite. Two CMCs have also been selected. Following a preliminary screening of seven adhesives, three were selected for detailed testing during the upcoming project phase.

In addition, researchers have developed theoretical models from which a complete coupled 3D model and simulation will be derived. HYDRA expects to deliver a novel TPS concept combining a low-density ablator with a high-performance CMC structural component. The hybrid system will enable an important reduction in mass and a simultaneous increase in temperature limits.

Researchers plan to meet the challenges of future space missions while relieving dependence on foreign-sourced space technologies for enhanced competitiveness of the EU space industry and the EU itself.