Accession Number:

ADA278632

Title:

An Adaptive, Unstructured, Finite-Element, Multi-Material, Thermal Analysis

Descriptive Note:

Technical rept. Jan 1991-Jan 1992

Corporate Author:

AEROSPACE CORP EL SEGUNDO CA

Personal Author(s):

• Chang, I-Shih

Report Date:

1993-11-01

Pagination or Media Count:

35.0

Abstract:

An efficient method has been developed for obtaining a high- resolution temperature distribution of the transient heat conduction inside an arbitrary domain containing any number of anisotropic materials. The method combines an adaptive, unstructured, mesh generation technique and a finite- element analysis program for a multi-material thermal analysis. The technique allows easy generation of fine elements in a high-temperature gradient area and coarse elements in a low-temperature gradient area to enhance the quality of analysis results with minimum effort and cost. Continuity of finite-element mesh across the boundaries of multiple materials is precisely preserved. The thermal conduction inside an infinite cylinder and inside a two-layer slab is analyzed, and the results are compared to the exact solution to validate the solution procedure. Application of the method to investigate heat penetration in the Titan 4 Solid Rocket Motor Upgrade nozzle flexseal of a multi-material structure is demonstrated. Extension of the method to calculate thermal response of a Star-37S nozzleexit cone insulation and supporting structure with complicated, multiple charring materials is discussed.

Descriptors:

• *FINITE ELEMENT ANALYSIS
• *THERMAL ANALYSIS
• *CONDUCTION(HEAT TRANSFER)
• TRANSIENTS
• LOW TEMPERATURE
• TWO DIMENSIONAL
• BOUNDARY LAYER
• MESH
• RESPONSE
• THERMAL FATIGUE
• ROCKET ENGINES
• COMPUTER AIDED DIAGNOSIS
• TITANIUM
• NOZZLES
• TEMPERATURE GRADIENTS
• PENETRATION
• HIGH RESOLUTION
• MATERIALS
• HIGH TEMPERATURE
• INSULATION

Subject Categories:

• Computer Programming and Software
• Thermodynamics
• Solid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE