Advanced Integrated TPS and Non Equilibrium Chemistry Instrumentation
Abstract
Upon entering the atmosphere of celestial bodies, spacecraft encounter gases at velocities of more than 10 km/s, thereby being subjected to great heat loads. This makes it necessary to use high temperature thermal protection systems (TPS) to prevent the destruction of the space vehicle. The TPSs as well as the plasma environment during the entry have to be investigated by means of computational and ground facility simulations. The four plasma wind tunnels PWK 1-4 which are in operation at IRS reproduce thermal, aerodynamic and chemical load on the surface of a space vehicle entering a celestial body s atmosphere. Various plasma generators have been developed: Magnetoplasmadynamic plasma generators are used to produce high enthalpy plasma flows. Thermal plasma generators produce moderate enthalpies at higher stagnation pressures to simulate the follow-on flight path. In addition, inductively heated plasma generators for basic material investigations (catalytic efficiency / plasma wall reaction processes) and the simulation of entry scenarios for celestial bodies such as Mars or Venus have been developed [1]. Numerous material test diagnostic tools e.g. mechanical probes for heat flux and Pitot pressure measurements and TPS material tests have been developed and qualified. Parallel to these methods, further intrusive probes like electrostatic probes and non-intrusive diagnostics were applied for detailed investigation of high enthalpy plasma flows and material behavior during the tests [2, 3]. These tools provide an excellent opportunity to develop and qualify radiation-cooled materials for reuseable spacecraft and ablative material systems to be used for capsules and interplanetary probes.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 2007
- Accession Number
- ADA476534
Entities
People
- Georg Herdrich
- Markus Fertig
- Michael Winter
- Monika Auweter-kurtz
Organizations
- University of Stuttgart