Techniques for Aeroheating Thermal Protection and Temperature Effects on Hypersonic Vehicles
Award last edited on: 11/12/2002

Sponsored Program
Awarding Agency
Total Award Amount
Award Phase
Solicitation Topic Code
Principal Investigator
Eugene C Knox

Company Information

A & E Associates

Route 6 Box 6130
Tullahoma, TN 37388
   (615) 759-7001
Location: Single
Congr. District: 06
County: Coffee

Phase I

Contract Number: ----------
Start Date: ----    Completed: ----
Phase I year
Phase I Amount
Holloman AFB rocket sled requirements for computing the aeroheating and structural temperature effects thereof exceed the capabilities of available aeroheating methods in that accounting for shock impingement heating, real-gas, or non-air effects as needed for the sled application may be absent from these methods. In this SBIR Phase I effort an approach is proposed which will modify a flow code similar to the LANMIN code to include these effects. A companion conduction code, similar to the EXITS code, will be tailored to the thermal structural geometries of the Holloman rocket sled. The operation of this code will be compatible with the output of the flow code. The shock impingement effects will incorporate the results from NASA TN D-7139 and other available analytical/experimental work on this effect. The equilibrium real air Mollier tables will be made sufficiently large to include the extreme temperature associated with mach 10 operation in the Holloman atmospheric conditions. The Mollier tables for helium will be installed for computing the heating on the sled when passing through that gas. The resultant codes will allow the Holloman Test Group to compute the thermal protection (TPS) requirements at critical locations on the sled and the bond-line temperature between the TPS and that tests of candidate TPS materials can be performed to develop the TPS needed for the rocket sled - the ultimate objective of the program. The Phase II commercialization potential includes other hypersonic vehicle applications (like the NASP concept) within the aerospace industry; and industrial situations requiring TPS material for high temperature, high heat-rate environments, such as material casting and extrusion facilities (steel and aluminum).

Aeroheating Temperature Effects Flow Code Thermal Protection Pc-Based Computer Code Conduction Code

Phase II

Contract Number: ----------
Start Date: ----    Completed: ----
Phase II year
Phase II Amount
The Holloman rocket sled experiences severe thermal damage at speeds over Mach 5 and operations up to Mach 10 are needed. Hence, the need for increased thermal protection against the aeroheating and temperature effects on the sled components. First, the aerothermal environments must be defined, then thermal protection materials developed and tested to withstand these environments. The Phase I part of the program developed the analytical techniques for defining the aerothermal environments, including the changes introduced by "flying" through a second gas, such as helium, during the sled run. The Phase II effort will use these analytical techniques to define the aerothermal environments in areas on the sled that experience the severe thermal damage, compile a database of materials developed for high-temperature applications, screen these materials against the computed environments, and select those which can survive for validation tests on the sled. The validation process will include fabricating sled components using the selected materials and testing them on sled runs to the desired speeds. During these tests new temperature instrumentation will be tested and measurements made to validate the analytical environment predictions. Part of the Phase III commercialization effort will be to design a new sled with the validated materials or to develop new materials, if none are validated in the Phase II.

Aeroheating Temperature Effects Flow Code Thermal Protection Pc-Based Computer Code Conduction Code