Products
R&D
- Integrated Fuel-Air HX for Turbine Engines
- Cryo HX w/Anisotropic Conductance
- Advanced Turbine Blade Cooling
- Small Rocket Motors
Services
Nosetips & Leading Edges for Hypersonic Vehicles
HYPER-X Leading Edge Test Models |
Micro Cooling Concepts' employees have worked on thermal protection systems for a variety of hypersonic systems, dating from the early-80's and continuing to the present day. While both passive and active systems have been used, from the late-80s to the present we have focused on active cooling solutions.
In 1988 our employees developed low-cost fabrication process for transpiration-cooled nosetips for ICBM reentry vehicles. This nosetip (at right) was designed to accommodate heat fluxes in excess of 10 kW/cm2. This work evolved into several leading edge development efforts.
Micro Cooling Concepts' employees have worked on four generations of leading edge designs, beginning in 1989 and continuing to the present day. In general the trend in leading edge design has been away from fairly sharp film cooled leading edges and towards extremely sharp convection cooled leading edges. In the fourth generation leading edge radii as small as 0.015" were considered.
- 1st Generation: Film-Cooled Scramjet Leading Edge for LMSC
- 2nd Generation: Film/Convection-Cooled Scramjet Leading Edge for NASP/
- 3rd Generation: Convection-Cooled Nosetip for Advanced Hypersonic Engines
- 4th Generation: Convection-Cooled Scramjet Leading Edge for USAF/WL HYTEK Program
- 4th Generation: Convection-Cooled Nosecap and Scramjet Leading Edge for NASA/Langley HYPER-X Program