| Advanced Integrated TPS and Non Equilibrium Chemistry Instrumentation |
01 JUN 2007 |
51 pages |
| Authors:
Monika Auweter-Kurtz; Markus Fertig; Georg Herdrich; Michael Winter; STUTTGART UNIV (GERMANY F R)
|
 | Upon entering the atmosphere of celestial bodies, spacecraft encounter gases at velocities of more than 10 km/s, thereby being subjected to great heat loads. This makes it necessary to use high temperature thermal protection systems (TPS) to prevent the destruction of the space vehicle. The TPSs as well as the plasma environment during the entry have to be investigated by means of computational and ground facility simulations. The four plasma ... |
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| Fast Surface Temperature Measurement of Teflon Propellant in Pulsed Ablative Discharges Using HgCdTe Photovoltaic Cells (PREPRINT) |
2006 |
39 pages |
| Authors:
Erik L. Antonsen; Rodney L. Burton; Garrett A. Reed; Gregory G. Spanjers; ILLINOIS UNIV AT URBANA
|
| High speed Mercury Cadmium Telluride photovoltaic detectors sensitive to infrared emission are investigated as a means of measuring real-time surface temperature on a micro-second timeframe pulsed ablative discharge with Teflon(TradeMark) as the ablated material. Analysis is used to derive a governing equation for detector output voltage for materials with wavelength dependent emissivity. The detector output voltage is experimentally calibrated against thermocouples embedded in heated Teflon. Experimental calibration is performed with ... |
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| Ablation Study in a Capillary Sustained Discharge |
2006 |
11 pages |
| Authors:
Michael Keidar; Iain D. Boyd; Anthony Williams; Richard Beyer; MICHIGAN UNIV ANN ARBOR DEPT OF AEROSPACE ENGINEERING
|
| Electrothermal-chemical (ETC) ignition systems have been demonstrated in gun systems to provide desirable characteristics including reproducible shorter ignition delays. The optimum combination of capillary tube and fuse wire properties has not been identified yet. We present a combined theoretical and experimental study of the capillary discharge with an aim to develop a capillary plasma source with efficient energy conversion. The major emphasis in the present capillary discharge model is the ... |
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| High Temperature Coatings by Pulsed Electron Beam Ablation |
AUG 2005 |
44 pages |
| Authors:
Olivier Sudre; David B. Marshall; Sergio Lucato; ROCKWELL SCIENTIFIC CO THOUSAND OAKS CA
|
| The objective of this program was to investigate the deposition and properties of new high temperature coatings using pulsed-electron-beam ablation (PEBA) and to characterize the corrosion of those compounds in relevant environments. The PEBA technique has potential advantages for depositing compounds that are known to be difficult to deposit by conventional electron-beam evaporation. The use of ablation rather than melting and evaporation avoids changes in composition associated with differing evaporation ... |
|
| Solid Rocket Motor Insulation Testing |
13 JUL 2005 |
16 pages |
| Authors:
Rusty Blanski; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| GOAL: 50% lower erosion of insulation (44% weight reduction, 7.4% booster payload increase); OBJECTIVE: Development of ceramic forming polymer and/or structurally reinforced char layer. |
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| Plume Expansion and Ionization in a Micro Laser Plasma Thruster |
JUN 2005 |
14 pages |
| Authors:
Michael P. Reilly; George H. Miley; William A. Hargus Jr; ILLINOIS UNIV AT URBANA
|
| Ion density measurements have been performed on the plasma generated by an ablative diode laser thruster using a negatively biased flat plate probe. The biased probe data was coupled with measurement of the ablation crater through use of a scanning electron microscope (SEM). The SEM was used to analyze the post-pulse ablation spots to determine the volume of fuel ablated. The micro-laser plasma thruster (micro-LPT) discussed here ablates a target ... |
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| Giant Momentum Coupling Coefficients from Nanoscale Laser-Initiated Exothermic Compounds |
APR 2005 |
6 pages |
| Authors:
Claude R. Phipps; James R. Luke; Wesley D. Helgeson; Darren Naud; Michael Hiskey; Lukas Urech; Thomas Lippert; Alexander Wokaun; PHOTONIC ASSOCIATES SANTA FE NM
|
| We report here on results obtained with laser-initiated micro-propellants, such as PVN, PVC, GAP, NC, and mixtures of these. All samples were doped with a laser absorbing component. In some cases, this was carbon nanopearls with 10nm mean diameter, while, in others, it was a carbon-based ink with m-size particles. We also report results of performance tests for absorbers tuned to the 935-nm laser wavelength. |
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| Polymer Nanocomposites Containing Polyhedral Oligomeric Silsesquioxanes (POSS) |
16 DEC 2004 |
1 pages |
| Authors:
Joseph M. Mabry; Timothy S. Haddad; Steven A. Svejda; AIR FORCE RESEARCH LAB EDWARDS AFB CA
|
| Polyhedral oligomeric silsesquioxanes (POSS) are being examined for use in many applications. These applications include space-survivable coatings, and ablative and fire-resistant materials. POSS compounds have a rigid, inorganic core and have been produced with a wide range of organic functionality. Due to their physical size, POSS incorporation in polymers generally serves to reduce chain mobility, often improving both thermal and mechanical properties. Herein, we describe the preparation and properties of ... |
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| Incorporation of Amorphous Metals into MEMS for High Performance and Reliability |
NOV 2003 |
41 pages |
| Authors:
John R. Porter; Jeffrey DeNatale; Natalie Gluck; Daniel Branagan; ROCKWELL SCIENTIFIC CO THOUSAND OAKS CA
|
| Amorphous or amorphous derived metals have properties that can be very different from their crystalline counterparts. Since mechanisms for crystalline slip are absent, they can have high hardness and strength and exhibit high elastic strain before failure. Increasing the elastic limit of a component metal has the potential to enable the redesign of MEMS components to achieve higher performance for a given size device. To exploit these properties, Rockwell Scientific ... |
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| Lightweight Ablating Insulation for Ramjet Combustion |
10 DEC 2002 |
24 pages |
| Authors:
Roy L. Carter; Robert M. Springfield; MISSISSIPPI POLYMER TECHNOLOGIES INC BAY SAINT LOUIS MS
|
| Parmax(trade name), a self reinforcing ultra-high performance polymer, was investigated as an ablative material in ramjet combustor applications, Phase I effort has demonstrated that Parmax(trade name) SRP materials offer a number of advantages over the existing ablative solution, These include 1) Superior erosion rate performance 2) Better insulative properties 3) Lower ablative material density 4) Superior mechanical properties and 5) Lower or comparable cost (in commercial stage) Phase I demonstrated ... |
|
| AFRL POSS Applications Research |
03 SEP 2002 |
24 pages |
| Authors:
Shawn Phillips; AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV
|
| The Air Force is heavily invested in POSS Applications Research and Development. Currently one application is being 'flight'tested' for a technology transition. New applications are being investigated (e.g. batteries, capacitors, radomes). The technology transfer to Hybrid Plastics is a success story with significant volume increase and price reduction. POSS Nanotechnology Offers Versatility. |
|
| Hypersonic Weapons Technology Shear Testing of Hypersonic Heatshield Materials at the NASA Hot Gas Test Facility |
APR 2002 |
12 pages |
| Authors:
Michael Rembert; Forrest Strobel; Gerald Russell; Warren Jaul; AEROTHERM CORP HUNTSVILLE AL
|
| During the past three years, a team consisting of the Naval Air Warfare Center (NAWC), the U,S, Army Aviation and Missile Command (AMCOM) and ITT Aerotherm has been developing thermal protection systems for advanced high- speed missile applications. To date, the development has consisted of evaluating 32 different thermal protection systems (TPS) in representative flight environments. The 32 materials were comprised of proven and unproven aerospace TPS materials ranging from ... |
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| OPTIMAL ARRAY GEOMETRIES FOR WADEBAND DOA ESTIMATION, |
FEB 2002 |
|
| Authors:
ULKII BAYSAL; Randolph L. Moses; OHIO STATE UNIV COLUMBUS DEPT OF ELECTRICAL ENGINEERING
|
 | (U) THIS PAPER ADDRESSES THE ROLE OF ARRAY GEOMETRY ON THE DIRECTION OF ARRIVAL ESTIMATING PERFORMANCE OF THE ARRAY WHERE THE IMPINGING SIGNAL IS WIDEBAND. THE PAPER CONCENTRATES ON ARRAYS THAT HAVE ISOTROPIC PERFORMANCE, WHOSE CRAMER RAO BOUND ON THE DIRECTION OF ARRIVAL OF A SINGLE SOURCE IS UNIFORM FOR ALL ANGLES. NECESSARY AND SUFFICIENT CONDITIONS ON THE LOCATION OF ARRAY ELEMENTS SO THAT THE ARRAY IS ISOTROPIC ARE DERIVED ... |
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| Overview of Characteristics and Experiments in IPM Plasmatrons |
APR 2000 |
|
| Authors:
A. N. Gordeev; INSTITUTE FOR PROBLEMS IN MECHANICS MOSCOW (USSR)
|
| Characteristics of IPG series plasmatrons as well as there application for reentry simulation and testing of thermal protection materials are discussed in the presented paper on the basis of 35-years experience of Plasma Laboratory of IPM RAS. Successful application of plasmatrons for simulation of reentry conditions and testing of thermal protection materials is based on using of plasmatron's advantages such as purity of plasma flow, its high stability, excellent reproducibility ... |
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| Diagnostic Tools for Plasma Wind Tunnels and Reentry Vehicles at the IRS |
APR 2000 |
|
| Authors:
Monika Auweter-Kurtz; Markus Feigl; Michael Winter; STUTTGART UNIV (GERMANY F R) INST FUERRAUMFAHRTSYSTEME
|
| Various plasma wind tunnels have been built for developing reusable space transportation systems and space probes entering the atmospheres of celestial bodies. All together they cover almost the whole reentry trajectory of a space craft 1.1. They generate continuous plasma flows of high specific enthalpy and velocity with thermal or magnetoplasmadynamic generators. Plasma wind tunnels are used for: development and qualification of radiation and ablative cooling materials and thermal protection ... |
|
| High-Gain Direct-Drive Target Design for Laser Fusion (Preprint) |
01-Jan-2000 |
6 pages |
| Authors:
S E Bodner; D G Colombant; A J Schmitt; M Klapisch; NAVAL RESEARCH LAB WASHINGTON DC PLASMA PHYSICS DIV
|
| A new laser fusion target concept is presented with a predicted energy gain of 125 using a 1.3 MJ KrF laser. This energy gain is sufficiently high for an economically attractive fusion reactor. X-rays from high- and low-Z materials are used in combination with a low-opacity ablator to spatially tune the isentrope, thereby providing both high fuel compression and a reduction of the ablative Rayleigh-Taylor instability. |
|
| High Velocity Interceptor Investigations |
SEP 1998 |
103 pages |
| Authors:
Hartmut H. Legner; Alan H. Gelb; David I. Rosen; George E. Caledonia; PHYSICAL SCIENCES INC ANDOVER MA
|
| High velocity interceptors operating at low altitudes in the range from ^20 to 30 km will experience a stressing aerothermal environment which can impact performance of the infrared sensor/designator system. This report addresses primarily two aspects of high velocity interceptors: a novel passively cooled window concept and the control of boundary layer transition to turbulence. A totally new concept for maintaining the IR transmitting window of an interceptor at low ... |
|
| Polyarylacetylene-Matrix Composites for Solid Rocket Motor Components |
01 SEP 95 |
11 pages |
| Authors:
H. A. Katzman; J. J. Mallon; W. T. Barry; AEROSPACE CORP EL SEGUNDO CA TECHNOLOGY OPERATIONS
|
| The fabrication process for an ablative material for solid rocket motor applications, carbon-fabric-reinforced polyarylacetylene (PAA) resin composite, is detailed. Data concerning the physical, mechanical, and ablative performance of this material are presented. PAA is a highly cross-linked aromatic polymer that contains only carbon and hydrogen. Its principal advantage is its high char yield (approx. 90 percent). For the resin synthesis, a controllable, low-temperature technique that produces a soluble, easy-to-process prepolymer ... |
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| Engineering Calculations Associated with the Ablative Thermal Protective Structures of Returnable Satellites |
17 NOV 94 |
24 pages |
| Authors:
Lianqun Xing; NATIONAL AIR INTELLIGENCE CENTER WRIGHT-PATTERSON AFB OH
|
| The paper describes one type of ablative thermal protective structure form associated with returnable satellites. It carries out discussions of ablation mechanisms and calculation methods associated with FL composite materials and silicone rubber. In conjunction with this, it carries out comparisons with flight tests and gives concluding opinions. (mm) ANNOTATION: Engineering Calculations Associated with the Ablative Thermal Protective Structures of Returnable Satellites--Translation. |
|
| The Laser Ablation of Gold Films at the Electrode Surface of a Quartz Crystal Microbalance |
MAY 93 |
16 pages |
| Authors:
James Perez; Brad R. Weiner; PUERTO RICO UNIV RIO PIEDRAS DEPT OF CHEMISTRY
|
| We report in this letter the amount of gold removed by ablation with a pulsed laser operating at 532 and 355 nm, by using a quartz crystal microbalance as a mass detector. The results indicate that for the 532 and 355 nm pulsed laser ablation of gold thin films, 10 (exp 13) - 10 (exp 15) atom per pulse are removed over the fluence range of 0.5-50. J/sq cm. The ... |
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| Ablative Thermal Protection Structure Design of Ballistic Reentry Spacecraft |
08 OCT 92 |
14 pages |
| Authors:
Chen Qinghua; FOREIGN AEROSPACE SCIENCE AND TECHNOLOGY CENTER WRIGHT- PATTERSON AFB OH
|
| The paper presents the ablative thermal protection structure design of a ballistic reentry spacecraft. The concepts, material selection, design approach, analytical computation and evaluation are described. Thermal protection structure, ablative material, ballistic reentry spacecraft and design. ANNOTATION: Ablative Thermal Protection Structure Design of Ballistic Reentry Spacecraft--Translation. |
|
| Performance of Reinforced Polymer Ablators Exposed to a Solid Rocket Motor Exhaust |
OCT 92 |
97 pages |
| Authors:
C. Boyer; T. Burgess; J. Bowen; K. Deloach; I. Talmy; NAVAL SURFACE WARFARE CENTER DAHLGREN DIV VA
|
| Summarized in this report is the effort by the Naval Surface Warfare Center Dahlgren Division NSWCDD) and FMC Corporation (a launcher manufacturer) to identify new high performance ablators suitable for use on Navy guided missile launchers (GML) and ships' structures. The goal is to reduce ablator erosion by 25 to 50 percent compared to that of the existing ablators such as MXBE350 (rubbermodified phenolic containing glass fiber reinforcement). This reduction ... |
|
| Proceedings of the Annual Advanced Polymer Components Symposium (2nd). Volume 3 |
JUL 92 |
178 pages |
| Authors:
John J. Rusek; PHILLIPS LAB EDWARDS AFB CA
|
| Advanced propulsion concepts rely on advanced propulsion materials. The Phillips Laboratory is aggressively pursuing advanced polymeric materials for use in Solid, Liquid, and Nuclear propulsion component applications. Traditional composite materials have high specific strengths, but suffer from high cost and labor intensive processing. The APC program is currently exploring thermotropic liquid crystal polymers; these materials have high specific strength and can be economically processed by traditional high volume routes such ... |
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| Ablative Heat Shield Studies for NASA Mars/Earth Return Entry Vehicles |
SEP 90 |
|
| Authors:
Michael K. Hamm; NAVAL POSTGRADUATE SCHOOL MONTEREY CA
|
| A material that behaves likes a glassy ablator on the surface, has a low thermal conductivity, is structurally tough, lightweight, and is in some sense reusable, would be desirable for the protective heat shield used on Earth entry vehicles. A material for this purpose has been developed that uses silicon dioxide (fused quartz) in a fibrous packed matrix, forming blocks which can behave as a glassy ablator on the surface ... |
|
| Proceedings of Technology Showcase held at Tom Bevil Center, Huntsville, AL on 7 and 9 August 1990. |
09 AUG 1990 |
|
| Authors:
ARMY MISSILE COMMAND REDSTONE ARSENAL AL RESEARCH AND ENGINEERING DIRECTORAT E (PROVISIONAL)
|
| Six Directorates from the U.S. Army Missile Command Research Development and Engineering Center showcased research currently being carried out by the Command. Future needs and objectives are also addressed. |
|
| Proceedings of Technology Showcase Held in Huntsville, Alabama on 7-9 August 1990 |
09 AUG 90 |
581 pages |
| Authors:
ARMY MISSILE RESEARCH DEVELOPMENT AND ENGINEERING CENTER REDSTONE ARSENAL AL
|
| Six Directorates from the U.S. Army Missile Command Research Development and Engineering Center showcased research currently being carried out by the Command. Future needs and objectives are also addressed. |
|
| Modifications to the Aerotherm Charring Material Thermal Response and Ablation Program (CMA) for Carbon Ablation Analysis |
MAR 89 |
91 pages |
| Authors:
C. C. Chan; JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB
|
| Modifications to the Aerotherm Charring Material Thermal Response and Ablation Program (CMA) have been made to resolve deficiencies that were identified during the Aerospace Nuclear Safety Program's Galileo-VEEGA ablation studies. The primary modifications deal with integrating the Hunter carbon oxidation subroutine with the mainstream ablation calculations in CMA. The modified program uses a surface temperature criterion to determine when to switch between the Hunter oxidation subroutine and the sublimation routines ... |
|
| Fire Retardant Coatings for Military Equipment - A Review |
FEB 88 |
|
| Authors:
L. V. Wake; MATERIALS RESEARCH LABS ASCOT VALE (AUSTRALIA)
|
| A continued increase in the use of fire retardant coatings by the Australian Defence Forces (ADF) is expected in view of the higher levels of composite and other lightweight materials being employed in modern military equipment. However, the increased smoke production reportedly associated with some fire retardant coatings has led to differences of opinion on the relative benefits associated with their use. This aspect combined with the growing awareness on ... |
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| The Rayleigh-Taylor Instability in Ablatively Accelerated Targets with 1, 1/2 and 1/4 Micrometers Laser Light |
22 SEP 87 |
|
| Authors:
Mark H. Emery; Jill P. Dahlburg; John H. Gardner; NAVAL RESEARCH LAB WASHINGTON DC
|
| The results of a series of detailed numerical simulations are presented for the Rayleigh-Taylor instability in laser ablatively accelerated targets for a fairly wide range of initial conditions. It is shown that the Rayleigh-Taylor growth rate in an ablative environment is a strong function of the laser wavelength. For perturbation wavelengths about 3 times the inflight target thickness, the ratios of the numerical growth rates to the classical growth rates ... |
|
| Neutral Beam Interactions with Materials |
18 JUN 85 |
|
| Authors:
R. M. Gilgenbach; J. J. Duderstadt; MICHIGAN UNIV ANN ARBOR COLL OF ENGINEERING
|
| This annual report describes experimental and theoretical research which concerns the interaction of neutral or ion beams with surface ablation plasmas. This problem is of interest in the case of particle penetration to outgassing or ablating objects in a high vacuum environment. We have constructed a neutral beam-ablation plasma experiment which employs a Q-switched ruby laser to independently generate a dense ablation plasma. Keywords include: Neutral- beams, radiation signatures, and ... |
|
| Numerical Models for Plasma-Solid Interactions in Electrothermal Mass Accelerators |
JUN 85 |
50 pages |
| Authors:
N. K. Winsor; D. A. Tidman; S. A. Goldstein; GT-DEVICES INC ALEXANDRIA VA
|
| This report describes the physics contents of codes and the results applying them to simulations of electrothermal mass accelerators. The overall objective was to investigate the dynamics of these accelerators including 2D effects. This has involved the development of computer models for the interactions of multi-species plasma with solid surfaces in single and multiple module plasma mass accelerators. The models are being used to make choices between materials and discharge ... |
|
| Modeling the Exhaust of the Pulsed Plasma Thruster |
FEB 85 |
|
| Authors:
D. W. Yannitell; LOUISIANA STATE UNIV BATON ROUGE DEPT OF MECHANICAL ENGINEERING
|
| The work presented in this report is an investigation of the plasma flow on a Teflon Pulsed Plasma Thruster (PPT), and the resulting plume. The long range goal is a theoretical model of the flow, both between and beyond the thruster electrodes, that could aid in the improvement of performance, and also predict the contamination potential of the device. The overall model required consists of an internal portion interfaced with ... |
|
| Laser Hardened Missile Casing Structure. |
14 FEB 1984 |
|
| Authors:
E. J. Rolinski; D. M. Patterson; DEPARTMENT OF THE AIR FORCE WASHINGTON DC
|
| A laser hardened casing structure for a missile or the like is described which comprises, in a preferred embodiment, a pair of thermally protective layers with a laser hardened barrier layer sandwiched there between and comprising a heavy metal bearing resin impregnated carbon fabric, all of said layers being adhesively joined and secured to the outer surface of the casing structure to be protected. |
|
| Development of a High Temperature Single Impact Rain Erosion Test Capability |
1984 |
|
| Authors:
K. N. Letson; S. P. Risner; ARMY MISSILE LAB REDSTONE ARSENAL AL
|
| A single impact rain erosion test capability has been developed to obtain data on fiber loaded Teflon (e.g. Duroid) ablative radome materials at temperatures up to their ablating temperature (approx. 1250 F). This effort was undertaken as a result of the prior inability to (1) obtain experimental data for single water droplet impacts on these materials at temperatures significantly above 400 F at velocities near Mach 5, and (2) identify ... |
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| Nonlinear Modeling and Initial Condition Estimation for Identifying the Aerothermodynamic Environment of the Space Shuttle Orbiter |
DEC 1983 |
|
| Authors:
C. D. Lutes; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
|
| This report describes improvements made to the data analysis tool HEATEST, used for identification of the reentry aerothermodynamic environment of the Space Shuttle Orbiter. The heating model was changed from a linear perturbation form to that of a piecewise linear interpolation form to account for nonlinear heating rates. Also, a fixed-point initial condition smoother was incorporated to gain better estimates of unknown initial temperatures. Verification of these modifications was accomplished ... |
|
| An Investigation of the Thermodegradation of Ablative Organic Silicon Resin |
10 NOV 1983 |
|
| Authors:
W. J. Sun; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH
|
| TGA, DTA and IR spectroscopy was used to characterize organosilicone ablative materials. Weight loss data and IR curves indicating the extent of thermal degradation are reported. (LS-PL). ANNOTATION: An Investigation of the Thermodegradation of Ablative Organic Silicon Resin--Translation. |
|
| Journal of Engineering Thermophysics (Selected Articles) |
20 MAY 1983 |
|
| Authors:
Chi-Ya Ts'ui; Hsin-Hai Chou; Sung-Ling Liu; Fei-Ta Fan; Fang-Yuan Chu; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH
|
|
| Diethynylbenzene-Ethynylpyrene Copolymers. |
18 JAN 1983 |
|
| Authors:
Norman Bilow; DEPARTMENT OF THE AIR FORCE WASHINGTON DC
|
| The invention describes a high char yielding matrix resin for use in fabricating carbon-carbon composites comprised of a polymerizable mixture of a diethynylbenzene monomer and an ethynylpyrene monomer. |
|
| An Assessment of Ablative Organotin Antifouling (AF) Coatings |
1983 |
6 pages |
| Authors:
Theodore Dowd; DEPARTMENT OF THE NAVY WASHINGTON DC
|
| The widely used cuprous oxide antifouling paints are no longer able to meet the increasing demands of the Marine industry. Now that fuel and drydocking costs have soared, the Marine industry is looking for antifouling paints that will permit extended drydocking intervals and to perform foul-free between dockings to keep fuel costs to a minimum and in addition, to eliminate the costly underwater mechanical brushing. The new ablative antifouling coatings ... |
|
| 120MM Gun Heat Input Measurements |
JUL 1982 |
|
| Authors:
Timothy L. Brosseau; Irvin C. Stobie; J. Richard Ward; Robert W. Geene; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| Imbedded thermocouples just beyond the engraving region have been used to measure total heat input in guns. The method has been applied to the XM256 cannon to estimate erosion. Rounds were fired with JA2, M30, M6, and M1 propellants with various charge to mass ratios. Efforts were made to measure total heat input without the combustible case. Total heat input was reduced from 387 J/mm to 247 J/mm in a ... |
|
| Diethynylbenzene-Ethylnylpyrene Copolymers. |
13 APR 1982 |
|
| Authors:
Norman Bilow; DEPARTMENT OF THE AIR FORCE WASHINGTON DC
|
| This invention relates to aromaticacetylene compounds and their utilization as ablative materials for re-entry vehicles. In a more particular aspect, this invention relates to the synthesis of diethynylbenzene-ethynylpyrene copolymers and their use as high char yielding matrix resins for carbon-carbon composites. The increased use and interest in the operation of re-entry vehicles has generated a considerable research effort in an attempt to develop structural materials that exhibit high strength and ... |
|
| MK 66 Rocket Signature Reduction |
APR 1982 |
20 pages |
| Authors:
James D. Habersat; ASSOCIATION OF SCIENTISTS AND ENGINEERSOF THE NAVAL SEA SYSTEMS COMMAND WASHINGTON DC
|
| A limited signature reduction study for the 2.75-inch rocket was conducted. The objective of the study was to reduce the visible signature of the rocket motor. The rocket motor used for demonstration tests was the MK 66, which burns for approximately one second. It contains a double-base, non-aluminized propellant. The visible signature is primarily smokeless, consisting mainly of a bright orange flame resulting from afterburning of the fuel-rich exhaust. The ... |
|
| Ablative Acceleration of Planar Targets to High Velocities |
30 MAR 1982 |
|
| Authors:
J. Grun; S. P. Obenschain; B. H. Ripin; R. R. Whitlock; E. A. McLean; NAVAL RESEARCH LAB WASHINGTON DC
|
| Laser irradiated targets are ablatively accelerated to velocities near those required for fusion pellet implosions while remaining relatively cool and uniform. The target velocities and velocity profiles are measured using a double-foil method, which is described in detail. Also, the ablation plasma flow from the target surface is spatially resolved, and the scalings with absorbed irradiance of the ablation pressure, ablation velocity, and mass ablation rate are determined. Results are ... |
|
| Manufacturing Methods and Technology Project for Production of Low Cost Missile Vanes |
FEB 1982 |
66 pages |
| Authors:
R. J. Schwalbe; W. F. Prater; F. H. Koo; J. C. Winkler; MARTIN MARIETTA AEROSPACE ORLANDO FL
|
| Martin Marietta's experience with ablative air vanes dates to the 1950s with the development of the Pershing I missile. In 1969, Martin Marietta Orlando Aerospace demonstrated net molding and primary bonding on the Sprint air vanes, and also the potential cost savings during manufacturing. However, the high pressures required for molding caused excessive deflections of the metallic substructure. Pershing II (PII), started in the 1970s, used proven air vane technologies ... |
|
| Ablative-Resistant Dielectric Ceramic Articles. |
08 DEC 1981 |
|
| Authors:
Roy W. Rice; William J. McDonough; Stephen W. Freiman; John J. Mecholsky Jr; DEPARTMENT OF THE NAVY WASHINGTON DC
|
| A tough, ablative-resistant, dielectric ceramic material is constructed using powder metallurgy techniques. The composite comprises a boron nitride particulate phase immersed in an Al2O3 matrix. The boron nitride particles are preferably 3-5 microns in size, and create the capability of sustaining thermal strains without generating the thermal stresses that lead to material failure. The composite displays superior mechanical strength characteristics. (Author) |
|
| Wind Tunnel Tests of the Space Shuttle Foam Insulation with Simulated Debonded Regions. Addendum |
SEP 1981 |
|
| Authors:
L. A. Ticatch; K. W. Nutt; CALSPAN FIELD SERVICES INC ARNOLD AFS TN AEDC DIV
|
| Wind tunnel tests of the Space Shuttle External Tank foam insulation, with simulated lightning protectors, were conducted in the von Karman Gas Dynamics Facility Tunnel C. The tests were conducted to examine three lightning conductive coating materials for debris production potential in simulated convective heating environments. The material samples were tested using the wedge technique. The tests were run at a free-stream Mach number 10 and a free stream total ... |
|
| Bonded Bulk Graphite and Process for Bonding. |
21 AUG 1981 |
|
| Authors:
Dennis M. Riggs; Edward L. Harvey; DEPARTMENT OF THE ARMY WASHINGTON DC
|
| Bulk pieces of graphite bonded with a graphitizable binder comprising a liquid crystalline component of pitch, which softens at about 240 C and becomes very fluid at about 300 C to about 500 C. The bonded graphite pieces appear as a monolithic material even under 1000x magnification. The bonding is effected under vacuum or in an inert atmosphere at temperatures of from about 700 C to about 3000 C, usually ... |
|
| Hypervelocity Track Tests of the Ablative Characteristics of Heatshield Materials for the NASA Galileo Probe |
AUG 1981 |
22 pages |
| Authors:
A. M. Adams; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN
|
| Tests were conducted in a hypervelocity track facility to establish the ablative characteristics of the heatshield material for the NASA Galileo Probe. Data were obtained from eight shots at launch velocities of 17,500 fps and 18,000 fps. All shots were conducted using argon gas in the range tank. The test required the nosetip to be recovered intact. Measurements were made of the model velocity and in-flight surface temperature. A description ... |
|
| Wind Tunnel Tests of the NASA Shuttle External Tank SLA/SOFI Panels at Mach Numbers from 0.60 to 1.50 |
JUN 1981 |
|
| Authors:
R. G. Meyer; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN
|
| A test was conducted to determine whether exposure of the Super Light Ablator/Spray-on-Foam Insulation (SLA/SOFI) to the STS-1 launch trajectory dynamic pressures would produce additional cracks or cause separations from the cryogenic tank. Low-speed movies and stereo-photography were used to record the effects of the tunnel flow at free-stream Mach numbers from 0.60 to 1.50. Four configurations were tested in the Propulsion Wind Tunnel (16T) during the period from March ... |
|
| Wind Tunnel Tests of the Space Shuttle Foam Insulation with Simulated Debonded Regions |
APR 1981 |
|
| Authors:
D. W. Stallings; A. S. Hartman; CALSPAN FIELD SERVICES INC ARNOLD AFS TN AEDC DIV
|
| The tests were conducted to investigate the survivability of the external tank protection system with a hole in the insulation caused by area debonding and insulation tear-out. The material samples were tested using the wedge technique. The tests were run at a free-stream Mach No. 10 and a free stream total temperature of 1900 R. The wedge angle was varied to provide test conditions which were representatives of those expected ... |
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