scholarly journals Ceramic Matrix Composite (CMC) Thermal Protection Systems (TPS) and Hot Structures for Hypersonic Vehicles

2008 ◽  
Author(s):  
David Glass
Keyword(s):  
Matrix Composite ◽  
Thermal Protection ◽  
Ceramic Matrix Composite ◽  
Ceramic Matrix ◽  
Hypersonic Vehicles ◽  
Thermal Protection Systems ◽  
Protection Systems

scholarly journals Investigating the Thermo-Mechanical Behavior of a Ceramic Matrix Composite Wing Leading Edge by Sub-Modeling Based Numerical Analyses

Computation ◽  
2020 ◽  
Vol 8 (2) ◽  
pp. 22 ◽  
Author(s):  
Michele Ferraiuolo ◽  
Concetta Palumbo ◽  
Andrea Sellitto ◽  
Aniello Riccio
Keyword(s):  
Mechanical Behavior ◽  
Matrix Composite ◽  
Thermal Protection ◽  
Ceramic Matrix Composite ◽  
Leading Edge ◽  
Ceramic Matrix ◽  
Thermal Protection Systems ◽  
Protection Systems ◽  
Very High ◽  
Composite Wing

The thermo-structural design of the wing leading edge of hypersonic vehicles is a very challenging task as high gradients in thermal field, and hence high thermal stresses, are expected. Indeed, when employing passive hot structures based thermal protection systems, very high temperatures (e.g., 1400 °C) are expected on the external surface of the wing leading edge, while the internal structural components are required to not exceed a few hundred degrees Celsius (e.g., 400 °C) at the interface with the internal cold structure. Hence, ceramic matrix composites (CMC) are usually adopted for the manufacturing of the external surface of the wing leading edge since they are characterized by good mechanical properties at very high temperatures (up to 1900 °C) together with an excellent thermal shock resistance. Furthermore, the orthotropic behavior of these materials together with the possibility to tailor their lamination sequence to minimize the heat transferred to internal components, make them very attractive for hot structure based thermal protection systems applications. However, the numerical predictions of the thermo-mechanical behavior of such materials, taking into account the influence of each ply (whose thickness generally ranges between 0.2 and 0.3 mm), can be very expensive from a computational point of view. To overcome this limitation, usually, sub-models are adopted, able to focus on specific and critical areas of the structure where very detailed thermo-mechanical analyses can be performed without significantly affecting the computational efficiency of the global model. In the present work, sub-modeling numerical approaches have been adopted for the analysis of the thermo-mechanical behavior of a ceramic matrix composite wing leading edge of a hypersonic vehicle. The main aim is to investigate the feasibility, in terms of computational efficiency and accuracy of results, in using sub-models for dimensioning complex ceramic matrix components. Hence, a comprehensive study on the size of sub-models and on the choice of their boundaries has been carried out in order to assess the advantages and the limitations in approximating the thermo-mechanical behavior of the investigated global ceramic matrix composite component.

scholarly journals Infra-red and vibration tests of hybrid ablative/ceramic matrix technological breadboards for earth re-entry thermal protection systems

2017 ◽  
Vol 134 ◽  
pp. 85-97 ◽  
Author(s):  
Jorge Barcena ◽  
Iñaki Garmendia ◽  
Kostoula Triantou ◽  
Konstatina Mergia ◽  
Beatriz Perez ◽  
...  
Keyword(s):  
Thermal Protection ◽  
Ceramic Matrix ◽  
Thermal Protection Systems ◽  
Protection Systems ◽  
Infra Red ◽  
Vibration Tests

Optimized Design of Multilayer Thermal Insulations for Hypersonic Vehicles

2016 ◽  
Vol 697 ◽  
pp. 449-452 ◽  
Author(s):  
Guang Hai Wang ◽  
Feng Zhang ◽  
Xian Kai Sun ◽  
Hao Ran Sun ◽  
Yan Li Huo ◽  
...  
Keyword(s):  
Thermal Property ◽  
Thermal Protection ◽  
Thermal Response ◽  
Hypersonic Vehicles ◽  
Optimized Design ◽  
Thermal Protection Systems ◽  
Protection Systems ◽  
Calculation Results ◽  
Multilayer Insulation ◽  
Thermal Insulations

In this paper, high temperature multilayer thermal insulations were to investigate in thermal protection systems for hypersonic vehicles. The thermal response and thermal property of the multilayer insulations were simulated and analyzed by using Ansys software. The calculation results were analyzed and the effects of parameters such as layer thermal conductivity, layer thickness, layer density, and numbers of layer are clarified. Thermal property of multilayer insulations was optimized. The results are helpful to the optimum design of the multilayer insulation system.

INTRODUCTION TO C3HARME PROJECT

2021 ◽  
Author(s):  
LUCA ZOLI ◽  
DILETTA SCITI
Keyword(s):  
High Temperature ◽  
High Speed ◽  
Thermal Protection ◽  
Weight Ratio ◽  
Ceramic Matrix Composites ◽  
Ceramic Matrix ◽  
Matrix Composites ◽  
Thermal Protection Systems ◽  
Protection Systems ◽  
Ultra High Temperature

High-speed aviation brings many challenges, one being the materials used ensure the aircraft and rockets travelling at hypersonic speed arrive at their destination safely. Control surfaces and thermal protection systems for vehicles flying at Mach 5 or above must withstand extremely hot temperatures and intense mechanical vibrations at launch, during cruising and re-entry into the Earth’s atmosphere. UHTCMCs (Ultra-High Temperature Ceramic Matrix Composites) belong to a new subclass of ceramic matrix composites (CMCs) with superior properties in terms of structural and chemical stability at elevated temperature and erosion/ablation resistance keeping excellent strength-to-weight ratio, thermal shock resistance and adequate damage tolerance. They are the latest potential candidates for thermal protection systems (TPSs), able to outperform bulk ultra-high temperature ceramics (UHTCs). C3HARME is a 4-years EU funded program involving 12 European partners from 6 countries focused on the design, fabrication and testing of UHTCMCs for nearzero erosion nozzles and near-zero ablation TPS tiles. C3harme will look at different technologies coming from the science of bulk ceramics and CMCs and combine them to find out new approaches for their manufacturing. Novel theoretical models and testing methodologies are necessary to characterize properly these materials. This talk will summarize some of the findings and advances of the program, with special emphasis on the innovative approaches that we have implemented.

scholarly journals Hot Structure Flight Data of a Faceted Atmospheric Reentry Thermal Protection System

2019 ◽  
Vol 2019 ◽  
pp. 1-16 ◽  
Author(s):  
Hannah Boehrk ◽  
Hendrik Weihs ◽  
Henning Elsäßer
Keyword(s):  
Matrix Composite ◽  
Heat Balance ◽  
Thermal Protection ◽  
Ceramic Matrix Composite ◽  
Ceramic Matrix ◽  
Thermal Protection System ◽  
Protection System ◽  
Maximum Temperature ◽  
Nose Radius ◽  
Maximum Heat

The second sharp-edged flight experiment is a faceted suborbital reentry body that enables low-cost in-flight reentry research. Its faceted thermal protection system consisting of only flat radiation-cooled thermal protection panels is cost-efficient since it saves dies, manpower, and storage. The ceramic sharp leading edge has a 1 mm nose radius in order to achieve good aerodynamic behaviour of the vehicle. The maximum temperature measured during flight was 867°C just before transmission ended and was predicted with an accuracy of the order of 10%. The acreage thermal protection system is set up by 3 mm fiber-reinforced ceramic panels isolated by a 27 mm alumina felt from the substructure. The panel gaps are sealed by a ceramic seal. Part of the thermal protection system is an additional transpiration-cooling experiment in which nitrogen is exhausted through a permeable ceramic matrix composite to form a coolant film on the panel. The efficiencies at the maximum heat flux are 58% on the porous sample and 42% and 30% downstream of the sample in the wake. The transient load at each panel location is derived from the trajectory by oblique shock equations and subsequent use of a heat balance for both cooled and uncooled structures. The comparison to the heat balance HEATS reveals heat sinks in the attachment system while the concurrence with the measurement is good with only 8% deviation for the acreage thermal protection system. Aerodynamic control surfaces, i.e., canards, have been designed and made from a hybrid titanium and ceramic matrix composite structure.

Performance of cork and ceramic matrix composite joints for re-entry thermal protection structures

2017 ◽  
Vol 108 ◽  
pp. 270-278 ◽  
Author(s):  
K. Triantou ◽  
B. Perez ◽  
A. Marinou ◽  
S. Florez ◽  
K. Mergia ◽  
...  
Keyword(s):  
Matrix Composite ◽  
Thermal Protection ◽  
Ceramic Matrix Composite ◽  
Ceramic Matrix ◽  
Composite Joints ◽  
Protection Structures
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