(Student Paper) Analysis and Design of Corrugated-Core Sandwich Panels for Thermal Protection Systems of Space Vehicles

2006 ◽  
Author(s):  
Satish Bapanapalli ◽  
Oscar Martinez ◽  
Christian Gogu ◽  
Bhavani Sankar ◽  
Raphael Haftka ◽  
...  
Keyword(s):  
Thermal Protection ◽  
Sandwich Panels ◽  
Paper Analysis ◽  
Space Vehicles ◽  
Analysis And Design ◽  
Thermal Protection Systems ◽  
Student Paper ◽  
Protection Systems

Micromechanical Analysis of Composite Corrugated-Core Sandwich Panels for Integral Thermal Protection Systems

AIAA Journal ◽  
2007 ◽  
Vol 45 (9) ◽  
pp. 2323-2336 ◽  
Author(s):  
Oscar A. Martinez ◽  
Bhavani V. Sankar ◽  
Raphael T. Haftka ◽  
Satish K. Bapanapalli ◽  
Max L. Blosser
Keyword(s):  
Thermal Protection ◽  
Sandwich Panels ◽  
Micromechanical Analysis ◽  
Thermal Protection Systems ◽  
Protection Systems

Parametric study on factors influencing the stiffness of honeycomb sandwich panels using impulse excitation technique

2017 ◽  
Vol 21 (1) ◽  
pp. 115-134 ◽  
Author(s):  
M Phani Surya Kiran ◽  
I Balasundar ◽  
K Gopinath ◽  
T Raghu
Keyword(s):  
Thermal Protection ◽  
Sandwich Panels ◽  
Bending Stiffness ◽  
Bending Test ◽  
Design Stage ◽  
Design Parameters ◽  
Thermal Protection Systems ◽  
Honeycomb Sandwich ◽  
Protection Systems ◽  
Impulse Excitation

Metallic thermal protection systems are used to protect the airframe and pay load from aerodynamic and aerothermal heating in hypersonic cruise vehicles that are powered with advanced scramjet engines. Metallic thermal protection systems is a composite structure that contains honeycomb sandwich panels at the top and bottom and a variety of thermal insulating materials placed in between them. Several design factors influence the structural and thermal performance of the honeycomb sandwich panels. Panel bending stiffness is one important structural property that is generally estimated using a destructive 3-point or 4-point bending test. In this study, a numerical model based on the impulse excitation nondestructive evaluation technique has been developed to estimate the effect of various design parameters that affect the bending stiffness of the honeycomb sandwich panels. The results obtained are analyzed using standard statistical procedures. A major advantage of this method lies in evaluating the panel stiffness at the design stage without resorting to actual fabrication of the panels for destructive testing.

scholarly journals Editorial: Ultra High Temperature Ceramics for Aerospace Applications

2010 ◽  
Vol 3 (1) ◽  
pp. 9-9
Author(s):  
Raffaele Savino
Keyword(s):  
High Temperature ◽  
High Speed ◽  
Thermal Protection ◽  
Space Vehicles ◽  
Component Level ◽  
Ultra High Temperature Ceramics ◽  
Thermal Protection Systems ◽  
Protection Systems ◽  
The Subject ◽  
Ultra High Temperature

Improved interest in ultra-high-temperature ceramics (UHTCs) is being animating the scientific community. This emerging attention is driven by the demand of developing re-usable hot structures as thermal protection systems of aerospace vehicles, able to re-enter in planetary atmospheres at relatively high speed (order of 8-11 Km/s). In contrast to traditional blunt capsules or Shuttle-like vehicles, characterised by poor gliding capabilities and complex thermal protection systems, the future use of UHTCs opens new horizons for the development of spaceplanes with slender fuselage noses and sharp wing leading edges. Advanced aerodynamic configurations reduce the vehicles drag, enhance the vehicles performances, due to a larger manoeuvrability resulting in larger down range, cross range and abort windows, and reduce electromagnetic interferences and communications black-out. Analysis has shown that materials with temperature capability approaching 2000°C and above will be required for these space vehicles, but the state of the art Reinforced Carbon-Carbon (RCC) material, currently used on the Space Shuttle, have maximum use temperatures of approximately 1650°C. The articles collected in this issue provide state-of-art scientific advancements on the subject with particular attention to the potential technological applications. The papers specifically deal with research studies on monolithic ceramic materials, composed primarily of Zirconium and Hafnium Diborides with different additives. The activities are carried out at materials level, with furnace or arc-jet testing, or include developments of UHTC-based hot structures at sub-component level. In the latter case, ultra-high temperature ceramic prototype structures have been developed and tested with embedded structural health monitoring systems. I want to thank all the article contributors for their manuscripts. I hope they will be useful for future basic and applied researches on the subject.

Thermostructural Design of a Flying Winglet Experimental Structure for the EXPERT Re-entry Test

2009 ◽  
Vol 131 (7) ◽  
Author(s):  
M. Ferraiuolo ◽  
A. Riccio ◽  
M. Gigliotti ◽  
D. Tescione ◽  
R. Gardi ◽  
...  
Keyword(s):  
Thermal Stresses ◽  
Thermal Protection ◽  
Plastic Behavior ◽  
Space Vehicles ◽  
Test Bed ◽  
Temperature Dependent ◽  
Stress Criterion ◽  
Thermal Protection Systems ◽  
Protection Systems ◽  
Lift Off

Within the framework of the European Experimental Re-entry Test Bed (EXPERT) Program, aimed at improving the understanding of physical phenomena occurring during the return of space vehicles from space to earth, the design of a flying winged experimental payload has been performed in order to assess the thermomechanical behavior and resistance of ultrahigh temperature ceramics (UHTC) in real flight aerothermal environment. The EXPERT flying winglet article is intended to reproduce such conditions. Particular interest covers the design of the interfaces between the UHTC winglet and the EXPERT capsule thermal protection systems since thermal stresses arise during the re-entry phase. The fixation of the winglet to the capsule is achieved by means of dedicated bolts that must tolerate mechanical loads occurring at the first stages of the flight, that is, lift-off, ascent, and separation stages. The thermostructural design is performed by employing ANSYS/Workbench finite element commercial code; simulations take into account transient thermostructural loading conditions, the elastic-fragile behavior of the ceramic materials, and the temperature dependent elastic-plastic behavior of the capsule thermal protection systems. In the postprocessing phase, UHTC critical areas have been identified by following two different approaches. The first approach is deterministic and consists in applying a maximum stress criterion, the stress at a node is compared with the temperature dependent strength at that node. The second approach, which is commonly employed for elastic-fragile materials, is probabilistic and consists in applying a Weibull-like failure criterion. Thermal and structural analyses simulating the re-entry phase have demonstrated that the maximum stresses and temperatures evaluated do not exceed their corresponding limits. Then, a configuration respecting all the requirements of the design has been identified, and its thermal and mechanical performances are discussed in detail.

Optimized design of sandwich panels for integral thermal protection systems

2016 ◽  
Vol 55 (1) ◽  
pp. 13-23 ◽  
Author(s):  
Xuewei Fang ◽  
Jian Chen ◽  
Bingheng Lu ◽  
Yiqing Wang ◽  
Shanguang Guo ◽  
...  
Keyword(s):  
Thermal Protection ◽  
Sandwich Panels ◽  
Optimized Design ◽  
Thermal Protection Systems ◽  
Protection Systems
Sign in / Sign up

Export Citation Format

Share Document