Ceramic Matrix Composites with Nano Technology–An Overview
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
Green Composites in Architecture and Building Material Science
Modern Applied Science; Vol. 9, No. 1; 2015 ISSN 1913-1844 E-ISSN 1913-1852 Published by Canadian Center of Science and Education Green Composites in Architecture and Building Material Science Ruslan Lesovik1, Yury Degtev1, Mahmud Shakarna1 & Anastasiya Levchenko1 1 Belgorod Shukhov State Technological University, 308012, Belgorod, Russia Correspondence: Ruslan Lesovik, Belgorod Shukhov State Technological University, 308012, Belgorod, Russia. Received: September 5, 2014 Accepted: September 8, 2014 Online Published: November 23, 2014 doi:10.5539/mas.v9n1p45 URL: http://dx.doi.org/10.5539/mas.v9n1p45 Abstract Currently, the topic of improvement of man`s live ability is becoming increasingly important. The notion of luxury living in the city includes social comfort, environment comfort (urban, natural landscape component). A wide range of small architectural forms of different architectural design and purpose is developed. The basic material for the production of small architectural forms is concrete. On optimal combination of negative and positive qualities, concrete is the most cost- effective material. In order to avoid increasing the price of hardscape, at their creating, it`s actual to use local raw materials and industrial waste. On their basis the modern high quality building materials are developed. To reduce prime costs of construction materials the technogenic raw materials are used. The solution of this actual problem possibly on the basis of expansion of a source of raw materials of the stone materials suitable for production -
A Perspective on the Design and Development of the Spacex Dragon Spacecraft Heatshield
A Perspective on the Design and Development of the SpaceX Dragon Spacecraft Heatshield by Daniel J. Rasky, PhD Senior Scientist, NASA Ames Research Center Director, Space Portal, NASA Research Park Moffett Field, CA 94035 (650) 604-1098 / [email protected] February 28, 2012 2 How Did SpaceX Do This? Recovered Dragon Spacecraft! After a “picture perfect” first flight, December 8, 2010 ! 3 Beginning Here? SpaceX Thermal Protection Systems Laboratory, Hawthorne, CA! “Empty Floor Space” December, 2007! 4 Some Necessary Background: Re-entry Physics • Entry Physics Elements – Ballistic Coefficient – Blunt vs sharp nose tip – Entry angle/heating profile – Precision landing reqr. – Ablation effects – Entry G’loads » Blunt vs Lifting shapes – Lifting Shapes » Volumetric Constraints » Structure » Roll Control » Landing Precision – Vehicle flight and turn-around requirements Re-entry requires specialized design and expertise for the Thermal Protection Systems (TPS), and is critical for a successful space vehicle 5 Reusable vs. Ablative Materials 6 Historical Perspective on TPS: The Beginnings • Discipline of TPS began during World War II (1940’s) – German scientists discovered V2 rocket was detonating early due to re-entry heating – Plywood heatshields improvised on the vehicle to EDL solve the heating problem • X-15 Era (1950’s, 60’s) – Vehicle Inconel and Titanium metallic structure protected from hypersonic heating AVCOAT » Spray-on silicone based ablator for acreage » Asbestos/silicone moldable TPS for leading edges – Spray-on silicone ablator -
Xii Multifunctional Composites 11 Thermal Protection Systems
xii Multifunctional Composites 11 Thermal protection systems, Maurizio Natali, Luigi Torre, and Jos´e Maria Kenny 337 11.1 The hyperthermal environment . 337 11.2 Non-ablative TPS materials . 339 11.2.1 NA-TPS on the Space Shuttle . 339 11.2.2 SSO reusable surface insulation . 341 11.2.3 Conclusion remarks on non-ablative TPS materials . 342 11.3 High temperature composites as polymeric ablatives . 342 11.4 Testing facilities . 348 11.4.1 The oxy-acetylene torch testbed - OATT . 349 11.4.2 The simulated solid rocket motor - SSRM . 349 11.4.3 Plasma jet torches . 351 11.4.4 Recession rate sensing techniques for TPSs . 352 11.5 PAs as thermal insulating materials . 356 11.5.1 Rigid HSMs . 356 11.5.2 Flexible HSMs for TPSs . 356 11.5.3 Elastomeric HSMs for SRMs . 357 11.6 Phenolic impregnated carbon ablators . 359 11.7 Differences between FRPAs and LCAs . 360 11.8 Nanostructured ablative materials . 360 11.8.1 Nanosilica as filler for traditional and nanostructured ablatives 363 Table of Contents xiii 11.8.2 Carbon nanofilaments based NRAMs . 366 11.9 Conclusions . 368 Bibliography . 369 Chapter 11 Thermal protection systems Maurizio Natali, Luigi Torre, and Jos´eMaria Kenny University of Perugia, Perugia, Italy Abstract Ablative materials play a vital role for the entire aerospace industry. Although some non-polymeric materials have been successfully used as ablatives, polymer ablatives (PA) represent the most versatile class of thermal protection system (TPS) materials. Compared with oxide, inorganic polymer, and metal based TPS materials, PAs have some intrinsic advantages, such as high heat shock resistance and low density. -
Highly Reliable 3-Dimensional Woven Thermal Protection System for Mars Sample Return
Highly Reliable 3-Dimensional Woven Thermal Protection System for Mars Sample Return Don Ellerby Presenting for Keith Peterson [email protected] (512) 650-0885 Co-Authors (alphabetical by last name), E. Christiansen, D. Ellerby, P. Gage, M. Gasch, D. Prabhu, J. Vander Kam , E. Venkatapathy, T. W hite This work is funded by NASA Ames IRAD PI: E. Venkatapathy ; Technical Lead: K. Peterson; 1 3D Woven for MSR - Overview • The MSR Challenge: – Reliability requirements for a Mars Sample Return (MSR) Earth Entry Vehicle (EEV) are expected to be more stringent than any mission flown to date. • This flows down to all EEV subsystems, including heat-shield TPS • Likely to be the key driver for design decisions in many subsystem trades. • The MSR formulation is holding an option to on-ramp a 3D-woven system. The goal of this effort is to: –Provide a recommended 3D woven TPS architecture for MSR using Risk Informed Decision Making (RIDM). • Risk Informed DeCision Making (RIDM): – MSR formulation will institute RIDM processes to select configurations it pursues in future design cycles. • RIDM is a deliberative process that uses a diverse set of performance measures, together with other considerations, to inform decision making. – RIDM acknowledges the inevitable gaps in technical information, and the need for incorporating the cumulative wisdom of experienced personnel to integrate technical and nontechnical factors in order to produce sound decisions. 2 Why 3D Woven on MSR? • All TPS systems under consideration have their own set of challenges: – Carbon-Carbon (Hot Structure): • Certification of thermal-structural performance during re-entry and at temperature under the high strain landing impact environment will be challenging. -
Hybrid Self-Reinforced Composite Materials Based on Ultra-High Molecular Weight Polyethylene
materials Article Hybrid Self-Reinforced Composite Materials Based on Ultra-High Molecular Weight Polyethylene Dmitry Zherebtsov 1,* , Dilyus Chukov 1 , Eugene Statnik 2 and Valerii Torokhov 1 1 Center of Composite Materials, National University of Science and Technology “MISiS”, 119049 Moscow, Russia; [email protected] (D.C.); [email protected] (V.T.) 2 Skolkovo Institute of Science and Technology, 143026 Moscow, Russia; [email protected] * Correspondence: [email protected] Received: 2 March 2020; Accepted: 3 April 2020; Published: 8 April 2020 Abstract: The properties of hybrid self-reinforced composite (SRC) materials based on ultra-high molecular weight polyethylene (UHMWPE) were studied. The hybrid materials consist of two parts: an isotropic UHMWPE layer and unidirectional SRC based on UHMWPE fibers. Hot compaction as an approach to obtaining composites allowed melting only the surface of each UHMWPE fiber. Thus, after cooling, the molten UHMWPE formed an SRC matrix and bound an isotropic UHMWPE layer and the SRC. The single-lap shear test, flexural test, and differential scanning calorimetry (DSC) analysis were carried out to determine the influence of hot compaction parameters on the properties of the SRC and the adhesion between the layers. The shear strength increased with increasing hot compaction temperature while the preserved fibers’ volume decreased, which was proved by the DSC analysis and a reduction in the flexural modulus of the SRC. The increase in hot compaction pressure resulted in a decrease in shear strength caused by lower remelting of the fibers’ surface. It was shown that the hot compaction approach allows combining UHMWPE products with different molecular, supramolecular, and structural features. -
Aerothermodynamic Design of the Mars Science Laboratory Heatshield
Aerothermodynamic Design of the Mars Science Laboratory Heatshield Karl T. Edquist∗ and Artem A. Dyakonovy NASA Langley Research Center, Hampton, Virginia, 23681 Michael J. Wrightz and Chun Y. Tangx NASA Ames Research Center, Moffett Field, California, 94035 Aerothermodynamic design environments are presented for the Mars Science Labora- tory entry capsule heatshield. The design conditions are based on Navier-Stokes flowfield simulations on shallow (maximum total heat load) and steep (maximum heat flux, shear stress, and pressure) entry trajectories from a 2009 launch. Boundary layer transition is expected prior to peak heat flux, a first for Mars entry, and the heatshield environments were defined for a fully-turbulent heat pulse. The effects of distributed surface roughness on turbulent heat flux and shear stress peaks are included using empirical correlations. Additional biases and uncertainties are based on computational model comparisons with experimental data and sensitivity studies. The peak design conditions are 197 W=cm2 for heat flux, 471 P a for shear stress, 0.371 Earth atm for pressure, and 5477 J=cm2 for total heat load. Time-varying conditions at fixed heatshield locations were generated for thermal protection system analysis and flight instrumentation development. Finally, the aerother- modynamic effects of delaying launch until 2011 are previewed. Nomenclature 1 2 2 A reference area, 4 πD (m ) CD drag coefficient, D=q1A D aeroshell diameter (m) 2 Dim multi-component diffusion coefficient (m =s) ci species mass fraction H total enthalpy -
Venus Entry Challenges and Solutions for Aerial Platform Deployment
Venus Entry Challenges and Solutions for Aerial Platform Deployment Ethiraj Venkatapathy, Don Ellerby, Paul Wercinski Entry Systems and Technology Division NASA Ames Research Center Peter Gage, Neerim Corp. Venus Aerial Platform Workshop #2, December 6, 2017 Pasadena, CA 1 Summary . Entry, Descent and Deployment (EDD) of aerial platforms at Venus with rigid aero-shell is no more challenging than at other destinations. • Limited only by the availability of efficient heat-shield/TPS technology. • NASA is investing in the maturation of “Heat-shield for Extreme Entry Environment Technology (HEEET)” to TRL 6 and is incentivizing its use for New Frontiers - 4 missions • Future Venus Aerial Platform missions can use HEEET in place of Carbon Phenolic, which is not currently available HEEET is more mass efficient and permits lower-deceleration entry profile . Lower ballistic coefficient concepts, ADEPT and HIAD, may offer additional opportunities • even lower-deceleration entry profiles • Release of multiple probes from open back of EV . Lowest ballistic coefficient lifting concepts (VAMP) may provide other science benefits but concept and technical maturity are low 12/06/17 2 NASA has Demonstrated Entry System Capability Missions have successfully survived entry environments ranging from the very mild (Mars Viking ~25 W/cm2 and 0.05 atm.) to the extreme (Galileo ~30,000W/cm2 and 7 atm.) P-V and Galileo used Carbon-Phenolic (CP) (but heritage CP TPS is no longer viable). HEEET is a mass efficient system that will be available for future Venus missions 6/11/16 3 Entry System: Protects the Scientific Payload and Deploys at the Right Location and Orientation Entry begins when atmospheric Typical Rigid Aeroshell: effects start to impact the system Function of Entry System: . -
APOLLO EXPERIENCE REPORT - THERMAL PROTECTION SUBSYSTEM by Jumes E
NASA TECHNICAL NOTE NASA TN D-7564 w= ro VI h d z c Q rn 4 z t APOLLO EXPERIENCE REPORT - THERMAL PROTECTION SUBSYSTEM by Jumes E. Puulosky und Leslie G, St. Leger Ly12d012 B. Johlzson Space Center Honst0~2, Texus 77058 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, 0. C. JANUARY 1974 ~--_. - .. 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. D-7564 4. Title and Subtitle 5. Report Date January 1974 APOLLOEXPERIENCEREPORT THERMAL PROTECTION SUBSYSTEM 6. Performing Organization Code I 7. Author(s) I 8. Performing Organization Report No. JSC S-383 James E. Pavlosky and Leslie G. St. Leger, JSC 10. Work Unit No. I 9. Performing Organization Name and Address 11. Contract or Grant No. Lyndon B. Johnson Space Center Houston, Texas 77058 13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address 14. Sponsoring Agency Code National Aeronautics and SDace Administration Washington, D. C. 20546 1 15. Supplementary Notes The JSC Director waived the use of the International System of Units (SI) for this Apollo Experienc Report because, in his judgment, the use of SI units would impair the usefulness of th'e report or result in excessive cost. 16. Abstract The Apollo command module was the first manned spacecraft to be designed to enter the atmos- phere of the earth at lunar-return velocity, and the design of the thermal protection subsystem for the resulting entry environment presented a major technological challenge. Brief descrip- tions of the Apollo command module thermal design requirements and thermal protection con- figuration, and some highlights of the ground and flight testing used for design verification of the system are presented. -
Applying the Ablative Heat Shield to the Apollo Spacecraft
View metadata, citation and similar papers at core.ac.uk brought to you by CORE provided by Embry-Riddle Aeronautical University The Space Congress® Proceedings 1967 (4th) Space Congress Proceedings Apr 3rd, 12:00 AM Applying the Ablative Heat Shield to the Apollo Spacecraft B. V. Coplan Materials Technology Directorate, Space Systems Division, Avco Corporation Wilmington, Massachusetts R. W. King Materials Technology Directorate, Space Systems Division, Avco Corporation Wilmington, Massachusetts Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Coplan, B. V. and King, R. W., "Applying the Ablative Heat Shield to the Apollo Spacecraft" (1967). The Space Congress® Proceedings. 4. https://commons.erau.edu/space-congress-proceedings/proceedings-1967-4th/session-15/4 This Event is brought to you for free and open access by the Conferences at Scholarly Commons. It has been accepted for inclusion in The Space Congress® Proceedings by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. APPLYING THE ABLATIVE HEAT SHIELD TO THE APOLLO SPACECRAFT B. V. Coplan R. W. King Materials Technology Directorate Space Systems Division Avco Corporation Wilmington, Massachusetts INTRODUCTION I. DESCRIPTION OF HEAT SHIELD The Apollo program to land men on the moon The ablative heat shield structure is com is administered by the National Aeronautics and posed of a fiberglass honeycomb, impregnated with Space Administration. Production of the space a phenolic resin and bonded with an epoxy-based craft command module has been assigned 'to the adhesive to the cleaned, stainless steel shell. North American Aviation Company. As a subcon The honeyc.omb structure is composed of a number of tractor to N.A.A., the Avco Corporation is pieces formed on molds to the proper curvatures . -
Reusable Stage Concepts Design Tool
DOI: 10.13009/EUCASS2019-421 8TH EUROPEAN CONFERENCE FOR AERONAUTICS AND AEROSPACE SCIENCES (EUCASS) DOI: ADD DOINUMBER HERE Reusable stage concepts design tool Lars Pepermans?, Barry Zandbergeny ?Delft University of Technology Kluyverweg 1, 2629 HS Delft [email protected] yDelft University of Technology Kluyverweg 1, 2629 HS Delft Abstract Reusable launch vehicles hold the promise of substantially reducing the cost of access to space. Many different approaches towards realising a reusable rocket exist or are being proposed. This work focuses on the use of an optimisation method for conceptual design of non-winged reusable upper stages, thereby allowing it to take into account landing on land, sea or mid-air retrieval as well as landing the full stage or the engine only. As the optimisation criterion, the ratio of the specific launch cost of the reusable to the expendable version is used. The tool also provides for a Monte Carlo analysis, which allows for investigating the ruggedness of the design solution(s) found. The article will describe the methods implemented in the Conceptual Reusability Design Tool (CRDT) together with the modifications made to ParSim v3, a simulation tool by Delft Aerospace Rocket Engi- neering. Furthermore, it will present the steps taken to verify and validate CRDT. Finally, several example cases are presented based on the Atlas V-Centaur launch vehicle. The cases demonstrate the tools capa- bility of finding optimum and the sensitivity of the found optimum. However, it also shows the optimum when the user disables some Entry Descent and Landing (EDL) options. 1. Introduction To make space more accessible, one can reduce the cost of an orbital launch. -
A Study of the Mechanical Properties of Composite Materials with a Dammar-Based Hybrid Matrix and Two Types of Flax Fabric Reinforcement
polymers Article A Study of the Mechanical Properties of Composite Materials with a Dammar-Based Hybrid Matrix and Two Types of Flax Fabric Reinforcement Dumitru Bolcu † and Marius Marinel St˘anescu*,† Department of Mechanics, University of Craiova, 165 Calea Bucure¸sti,200620 Craiova, Romania; [email protected] * Correspondence: [email protected]; Tel.: +40-740-355-079 † These authors contributed equally to this work. Received: 7 July 2020; Accepted: 22 July 2020; Published: 24 July 2020 Abstract: The need to protect the environment has generated, in the past decade, a competition at the producers’ level to use, as much as possible, natural materials, which are biodegradable and compostable. This trend and the composite materials have undergone a spectacular development of the natural components. Starting from these tendencies we have made and studied from the point of view of mechanical and chemical properties composite materials with three types of hybrid matrix based on the Dammar natural hybrid resin and two types of reinforcers made of flax fabric. We have researched the mechanical properties of these composite materials based on their tensile strength and vibration behavior, respectively. We have determined the characteristic curves, elasticity modulus, tensile strength, elongation at break, specific frequency and damping factor. Using SEM (Scanning Electron Microscopy) analysis we have obtained images of the breaking area for each sample that underwent a tensile test and, by applying FTIR (Fourier Transform Infrared Spectroscopy) and EDS (Energy Dispersive Spectroscopy) analyzes, we have determined the spectrum bands and the chemical composition diagram of the samples taken from the hybrid resins used as a matrix for the composite materials under study. -
Investigating the Mechanical Properties of Polyester- Natural Fiber Composite
International Research Journal of Engineering and Technology (IRJET) e-ISSN: 2395-0056 Volume: 04 Issue: 07 | July -2017 www.irjet.net p-ISSN: 2395-0072 INVESTIGATING THE MECHANICAL PROPERTIES OF POLYESTER- NATURAL FIBER COMPOSITE OMKAR NATH1, MOHD ZIAULHAQ2 1M.Tech Scholar,Mech. Engg. Deptt.,Azad Institute of Engineering & Technology,Uttar Pradesh,India 2Asst. Prof. Mechanical Engg. Deptt.,Azad Institute of Engineering & Technology, Uttar Pradesh,India ------------------------------------------------------------------------***----------------------------------------------------------------------- Abstract : Reinforced polymer composites have played an Here chemically treated and untreated fibres were mixed ascendant role in a variety of applications for their high separately with polyester matrix and by using hand lay –up meticulous strength and modulus. The fiber may be synthetic technique these reinforced composite material is moulded or natural used to serves as reinforcement in reinforced into dumbbell shape. Five specimens were prepared in composites. Glass and other synthetic fiber reinforced different arrangement of natural fibres and glass fiber in composites consists high meticulous strength but their fields of order to get more accurate results. applications are restrained because of their high cost of production. Natural fibres are not only strong & light weight In the present era of environmental consciousness, but mostly cheap and abundantly available material especially more and more material are emerging worldwide, Efficient in central uttar Pradesh region and north middle east region. utilization of plant species and utilizing the smaller particles Now a days most of the automotive parts are made with and fibers obtained from various lignocellulosic materials different materials which cannot be recycled. Recently including agro wastes to develop eco-friendly materials is European Union (E.U) and Asian countries have released thus certainly a rational and sustainable approach.