Facing the Heat Barrier: a History of Hypersonics
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Ceramic Matrix Composites with Nano Technology–An Overview
International Review of Applied Engineering Research. ISSN 2248-9967 Volume 4, Number 2 (2014), pp. 99-102 © Research India Publications http://www.ripublication.com/iraer.htm Ceramic Matrix Composites with Nano Technology–An Overview Saubhagya Sharma, Samresh Kumar Shashi and Vikram Tomar Department of Material Science & Nano Technology, University of Petroleum & Energy Studies, Dehradun, Uttrakhand. Abstract Ceramic matrix composites (CMCs) are promising materials for use in high temperature structural applications. This class of materials offers high strength to density ratios. Also, their higher temperature capability over conventional super alloys may allow for components that require little or no cooling. This benefit can lead to simpler component designs and weight savings. These materials can also contribute in increasing the operating efficiency due to higher operating temperatures being achieved. Using carbon/carbon composites with the help of Nanotechnology is more beneficial in structural engineering and can decrease the production cost. They can withstand high stresses and temperatures than the traditional alumina, silicon carbide which fracture easily under mechanical loads Fundamental work in processing, characterization and analysis is important before the structural properties of this new class of Nano composites can be optimized. The fields of the Nano composite materials have received a lot of attention to scientists and engineers in recent years. The fabrication of such composites using Nano technology can make a revolution in the field of material science engineering and can make the composites able to be used in long lasting applications. 1. Introduction As we know that Composite materials are the type of materials that are formed by combining two or more materials of different physical and chemical properties. -
Aerothermodynamic Analysis of a Mars Sample Return Earth-Entry Vehicle" (2018)
Old Dominion University ODU Digital Commons Mechanical & Aerospace Engineering Theses & Dissertations Mechanical & Aerospace Engineering Summer 2018 Aerothermodynamic Analysis of a Mars Sample Return Earth- Entry Vehicle Daniel A. Boyd Old Dominion University, [email protected] Follow this and additional works at: https://digitalcommons.odu.edu/mae_etds Part of the Aerodynamics and Fluid Mechanics Commons, Space Vehicles Commons, and the Thermodynamics Commons Recommended Citation Boyd, Daniel A.. "Aerothermodynamic Analysis of a Mars Sample Return Earth-Entry Vehicle" (2018). Master of Science (MS), Thesis, Mechanical & Aerospace Engineering, Old Dominion University, DOI: 10.25777/xhmz-ax21 https://digitalcommons.odu.edu/mae_etds/43 This Thesis is brought to you for free and open access by the Mechanical & Aerospace Engineering at ODU Digital Commons. It has been accepted for inclusion in Mechanical & Aerospace Engineering Theses & Dissertations by an authorized administrator of ODU Digital Commons. For more information, please contact [email protected]. AEROTHERMODYNAMIC ANALYSIS OF A MARS SAMPLE RETURN EARTH-ENTRY VEHICLE by Daniel A. Boyd B.S. May 2008, Virginia Military Institute M.A. August 2015, Webster University A Thesis Submitted to the Faculty of Old Dominion University in Partial Fulfillment of the Requirements for the Degree of MASTER OF SCIENCE AEROSPACE ENGINEERING OLD DOMINION UNIVERSITY August 2018 Approved by: __________________________ Robert L. Ash (Director) __________________________ Oktay Baysal (Member) __________________________ Jamshid A. Samareh (Member) __________________________ Shizhi Qian (Member) ABSTRACT AEROTHERMODYNAMIC ANALYSIS OF A MARS SAMPLE RETURN EARTH-ENTRY VEHICLE Daniel A. Boyd Old Dominion University, 2018 Director: Dr. Robert L. Ash Because of the severe quarantine constraints that must be imposed on any returned extraterrestrial samples, the Mars sample return Earth-entry vehicle must remain intact through sample recovery. -
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 -
Book Tribute to George Low –“The Ultimate Engineer”
Book Tribute to George Low –“The Ultimate Engineer” The Ultimate Engineer: The Remarkable Life of NASA's Visionary Leader George M. Low by Richard Jurek Foreword by Gerald D. Griffin From the late 1950s to 1976 the U.S. manned spaceflight program advanced as it did largely due to the extraordinary efforts of Austrian immigrant George M. Low. Described as the "ultimate engineer" during his career at NASA, Low was a visionary architect and leader from the agency's inception in 1958 to his retirement in 1976. As chief of manned spaceflight at NASA, Low was instrumental in the Mercury, Gemini, and Apollo programs. Low's pioneering work paved the way for President Kennedy's decision to make a lunar landing NASA's primary goal in the 1960s. After the tragic 1967 Apollo I fire that took the lives of three astronauts and almost crippled the program, Low took charge of the redesign of the Apollo spacecraft, and helped lead the program from disaster and toward the moon. In 1968, Low made the bold decision to go for lunar orbit on Apollo 8 before the lunar module was ready for flight and after only one Earth orbit test flight of the Command and Service modules. Under Low there were five manned missions, including Apollo 11, the first manned lunar landing. Low's clandestine negotiations with the Soviet Union resulted in a historic joint mission in 1975 that was the precursor to the Shuttle-MIR and International Space Station programs. At the end of his NASA career, Low was one of the leading figures in the development of the Space Shuttle in the early1970s, and was instrumental in NASA's transition into a post-Apollo world. -
Chapter 6.Qxd
CHAPTER 6: The NASA Family The melding of all of the NASA centers, contractors, universities, and often strong personalities associated with each of them into the productive and efficient organization necessary to complete NASA’s space missions became both more critical and more difficult as NASA turned its attention from Gemini to Apollo. The approach and style and, indeed, the personality of each NASA center differed sharply. The Manned Spacecraft Center was distinctive among all the rest. Fortune magazine suggested in 1967 that the scale of NASA’s operation required a whole new approach and style of management: “To master such massively complex and expensive problems, the agency has mobilized some 20,000 individual firms, more than 400,000 workers, and 200 colleges and universities in a combine of the most advanced resources of American civilization.” The author referred to some of the eight NASA centers and assorted field installations as “pockets of sovereignty” which exercised an enormous degree of independence and autonomy.1 An enduring part of the management problem throughout the Mercury and Gemini programs that became compounded under Apollo, because of its greater technical challenges, was the diversity and distinctiveness of each of the NASA centers. The diverse cultures and capabilities represented by each of the centers were at once the space program’s greatest resource and its Achilles’ heel. NASA was a hybrid organization. At its heart was Langley Memorial Aeronautical Laboratory established by Congress in 1917 near Hampton, Virginia, and formally dedicated in 1920. It became the Langley Research Center. Langley created the Ames Aeronautical Laboratory at Moffett Field, California, in 1939. -
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. -
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 -
The New Engineering Research Centers: Purposes, Goals, and Expectations
DOCUMENT RESUME ED 315 272 SE 051 142 TITLE The New Engineering Research Centers: Purposes, Goals, and Expectations. Symposium (District of Colombia, April 29-30, 1985). INSTITUTION National Academy of Sciences - National Research Council, Washington, DC. Commission on Engineering and Technical Systems. SPONS AGENCY National Science Foundation, Washington, D. REPORT NO ISBN-0-309-03598-8 PUB DATE 86 GRANT NSF-MEG-8505051 NOTE 213p.; Prepared by the Cross-Disciplinary Engineering Research Committee. AVAILABLE FROM National Academy Press, 1201 Constitution Ave. N.W., Washington, DC 20418 ($25.95). PUB TYPE Collected Works - Conference Proceedings (021) -- Viewpoints (120) EDRS PRICE MF01 Plus Postage. PC Not Available from EDRS. DESCRIPTORS *Engineering; *Engineering Education; *Engineering Technology; *Research Administration; Research and Development; *Research and Development Centers; Research Directors; Research Proposals; Scientific Research IDENTIFIERS *Engineering Research Centers ABSTRACT The aympoisum was held to describe the roots and future plans of the Engineering Research Center's (ERC's) concept and program. The first section of this symposium compilation describes the national goals that the ERCs represent. The second section presents the point of view of the National Science Foundation on the ERCs--the concept behind them, their goals, selection criteria, and mechanisms for support. The next section provides the plans and programs of the six existing centers:(1) Systems Research Center; (2) Center for Intelligent Manufacturin3 Systems;(3) Center for Robotic Systems in Microelectronics; (4) Center for Composites Manufacturing Science and Engineering; (5) Engineering Center for Telecommunications; and (6) Biotechnology Process Engineering Center. Two of the presentations were on exchange methods among the centers and the relationship between engineering.education and research. -
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. -
Tactical Missile Structures and Materials Technology
WILLIAM C. CAYWOOD, ROBERT M. RIVELLO, and LOUIS B. WECKESSER TACTICAL MISSILE STRUCTURES AND MATERIALS TECHNOLOGY Significant advances have occurred in missile structures and materials technology since the late 1940's. Some of the advances were the result of improvements in design concepts and material prop erties; others were from the development of new materials and fabrication techniques. Rapid strides in computer technology and methods of structural analysis have also played an important role. This article discusses the structural design requirements for the next generation of missiles and reviews the technological advances that will make it possible to meet those requirements. INTRODUCTION Antenna housing The Applied Physics Laboratory's experience in Cowl assembly tactical missile structural design began with the devel opment of the rocket-powered Terrier and the ramjet-powered Talos in the late 1940's. The air frames for those missiles were designed with conven tional aircraft materials, using slide rules, mechanical desk calculators, handbooks, and rule-of-thumb pro cedures. To ensure adequate safety margins, conser Innerbody fairing vative analytical procedures were pursued, followed Sheet magnesium Innerbody by extensive environmental testing. Simple aluminum forward cone Cast magnesium and steel structures operating at temperatures below Figure 1 - Magnesium components in Talos represented 300°F for Terrier and 600°F for Talos made up the 13 % of the weight of the primary load-carrying structure major portion of the missiles. Terrier was con and 10 % of the gross launch weight. structed primarily from machined castings. Talos, shown in Fig. 1 with its central air duct configura tion, used sheet metal construction.