61
61
Nov 28, 2014
11/14
by
Alexander Bolonkin
texts
eye 61
favorite 0
comment 0
Author offers new Electric Hypersonic Aircraft
Topics: Electric Hypersonic Aircraft, aerocpace, hypersonic flight, hypersonic propulsion, hypersonic...
HT-4 body-wing configuration; caret wing research model; BBW and DBW hypersonic transport configurations.
Topic: HYPERSONIC AIRCRAFT -- CARET WINGS -- WI
HT-4 body-wing configuration; caret wing research model; BBW and DBW hypersonic transport configurations.
Topic: HYPERSONIC AIRCRAFT -- CARET WINGS -- WI
1,708
1.7K
Jul 11, 2010
07/10
by
NON
texts
eye 1,708
favorite 1
comment 0
No Abstract Available
Topics: HYPERSONIC AIRCRAFT, HYPERSONIC INLETS, TECHNOLOGIES, COMPUTER AIDED DESIGN, PROPULSION SYSTEM...
207
207
May 6, 2010
05/10
by
Matranga, G. J.; Weil, J
texts
eye 207
favorite 0
comment 0
Lifting reentry of hypersonic aircraft - x-15 aircraft
Topics: HYPERSONIC AIRCRAFT, LIFTING BODIES, LIFTING REENTRY VEHICLES, X-15 AIRCRAFT, LIFTING REENTRY
1,056
1.1K
Jul 11, 2010
07/10
by
NON
texts
eye 1,056
favorite 0
comment 0
The development of the ideas of F. A. Tsander and their realization in modern astronautics are traced in such areas as astrodynamics, the theory and design of motors and space vehicles, life support systems and astrobotanics. Considerable attention is given to analysis of the role and significance of the works of F. A. Tsander in the history of rocket and space science and technology.
Topics: AIRCRAFT ENGINES, ENGINE COOLANTS, HYPERSONIC AIRCRAFT, ENGINE DESIGN, MANUFACTURING, PERFORMANCE...
807
807
Jul 11, 2010
07/10
by
NON
texts
eye 807
favorite 0
comment 0
No Abstract Available
Topics: AEROTHERMODYNAMICS, ENGINE DESIGN, HYPERSONIC AIRCRAFT, AERODYNAMIC CHARACTERISTICS, AIRCRAFT...
461
461
May 6, 2010
05/10
by
Moul, M. T.; Paulson, J. W
texts
eye 461
favorite 0
comment 0
Dynamic lateral stability and control of high performance hypersonic aircraft
Topics: AIRCRAFT PERFORMANCE, SUPERSONIC AIRCRAFT, YAW, DYNAMIC STABILITY, HYPERSONIC AIRCRAFT, LATERAL...
750
750
Jul 11, 2010
07/10
by
Bahr, D. W.; Gleason, C. C
texts
eye 750
favorite 0
comment 0
Full annular versions of advanced combustor designs, sized to fit within the CF6-50 engine, were defined, manufactured, and tested at high pressure conditions. Configurations were screened, and significant reductions in CO, HC, and NOx emissions levels were achieved with two of these advanced combustor design concepts. Emissions and performance data at a typical AST cruise condition were also obtained along with combustor noise data as a part of an addendum to the basic program. The two...
Topics: DESCENT TRAJECTORIES, HYPERSONIC AIRCRAFT, RESEARCH AIRCRAFT, TRAJECTORY ANALYSIS, AERODYNAMIC HEAT...
The goal of this young investigator research plan is to establish a comprehensive research program that will advance the fundamental understanding of high-temperature oxidation mechanisms in novel reverse infiltrated multilayer ultra-high temperature ceramic (UHTC) coated carbon-carbon (C-C) composites that will provide oxidation for future hypersonic vehicles. C-C composites provide high strength and low density for their use in hypersonics, but they oxidize in air at temperatures 500 deg C,...
Topics: DTIC Archive, ARIZONA UNIV TUCSON, *CARBON CARBON COMPOSITES, *CERAMIC COATINGS, *HIGH TEMPERATURE,...
873
873
Jul 12, 2010
07/10
by
MAUK, S. C
texts
eye 873
favorite 0
comment 0
THESE CITATIONS FROM THE INTERNATIONAL LITERATURE CONCERN VARIOUS ASPECTS OF ABLATION AND ABLATIVE MATERIALS. INCLUDED ARE ARTICLES COVERING AERODYNAMIC HEATING, HEAT SHIELDING, RADIATIVE HEAT TRANSFER, ATMOSPHERIC ENTRY, REENTRY EFFECTS, REENTRY SHIELDING AND REENTRY VEHICLES. ABLATION OF METEORITES IS ALSO COVERED. ARTICLES CONCERNING VARIOUS ABLATIVE MATERIALS ARE INCLUDED.
Topics: ANGLE OF ATTACK, LIFT, NACELLES, SUPERSONIC AIRCRAFT, SUPERSONIC DRAG, AERODYNAMIC CHARACTERISTICS,...
Topics: DTIC Archive, Meullen, N. F., BELL AEROSPACE CO BUFFALO NY, *HYPERSONIC AIRCRAFT, *RECONNAISSANCE...
301
301
Jun 21, 2010
06/10
by
Keltz, W. L.; Ringwall, C. G
texts
eye 301
favorite 0
comment 0
Fluidic roll control for Aerobee rocket vehicle
Topics: AERODYNAMIC HEATING, PROTECTIVE COATINGS, THERMAL INSULATION, COMPOSITE MATERIALS, CONTROL...
486
486
Jun 20, 2010
06/10
by
Spencer, B., Jr.; Stivers, L. S., Jr
texts
eye 486
favorite 0
comment 0
Optimum body length and volume design for minimal drag characteristics of hypersonic aircraft
Topics: AERODYNAMIC DRAG, AIRCRAFT DESIGN, HYPERSONIC AIRCRAFT, HYPERSONIC FLIGHT, HYPERSONIC SPEED,...
Through the well-known framework contracts, the EU is continuously supporting innovative technologies that might facilitate a step change required for air transport in the second half of this century and beyond. One of these goals is assessing high-speed flight transportation and its related technologies which are explored in LAPCAT and ATLLAS both being co-funded by the EC. Recently, they have been successfully extended towards a 2nd phase within the 7th Framework Programme. Whereas LAPCAT...
Topics: DTIC Archive, EUROPEAN SPACE RESEARCH AND TECHNOLOGY CENTRE NOORDWIJK (NETHERLANDS), *HYPERSONIC...
The effects of fuselage cross section and structural arrangement on the performance of actively cooled hypersonic cruise vehicles are investigated. An active cooling system which maintains the aircraft's entire surface area at temperatures below 394 K at Mach 6 is developed along with a hydrogen fuel tankage thermal protection system. Thermodynamic characteristics of the actively cooled thermal protection systems established are summarized. Design heat loads and coolant flowrate requirements...
Topics: NASA Technical Reports Server (NTRS), COOLING SYSTEMS, FUSELAGES, HYPERSONIC AIRCRAFT, PROPELLANT...
255
255
Jul 11, 2010
07/10
by
Taylor, L. W., Jr.; Mclaughlin, M. D
texts
eye 255
favorite 0
comment 0
A modified Newton-Raphson method has been used to determine the parameters in equations describing the vortex flow to obtain a best match with flight measurements of the flow behind the C-5A airplane. The flight measurements were made using a specially instrumented T-33 airplane which passed as closely as possible to the centers of the trailing vortices at several distances behind the C-5A airplane. The flight measurements were transformed to flow velocity relative to an inertial frame of...
Topics: AERODYNAMIC HEATING, COOLING SYSTEMS, HEAT SINKS, HYPERSONIC AIRCRAFT, AERODYNAMIC CONFIGURATIONS,...
171
171
Jul 25, 2010
07/10
by
PALLACKS, R
texts
eye 171
favorite 0
comment 0
DISCUSSED ARE NEW POSSIBILITIES OF OPERATING NET REFINEMENT METHODS THAT ARE OPEN, INCLUDING HOW DETERMINATION OF SUITABLE NUMBERING OF THE SET IS MADE.
Topics: AIRCRAFT CONSTRUCTION MATERIALS, AIRCRAFT STRUCTURES, ENGINE DESIGN, HYPERSONIC AIRCRAFT, ENGINE...
This basic research effort on pulsed air breathing/rocket laser propulsion, investigates the physics of laser energy deposition into stationary and hypersonic working fluids, inclusive of electrical breakdown, ignition of laser-supported detonation waves (LSD), and blast wave propagation over thruster impulse generating surfaces. The future application of AFOSR interest for this basic research endeavor is the laser launch of nano- and micro-satellites (i.e., 1-100 kg payloads) into Low Earth...
Topics: DTIC Archive, Myrabo , Leik N, RENSSELAER POLYTECHNIC INST TROY NY TROY United States, lasers, heat...
279
279
Jul 11, 2010
07/10
by
Schaefer, D. H
texts
eye 279
favorite 0
comment 0
Two dimensional digital computers and computer devices operate in parallel on rectangular arrays of digital radiant energy optical signal elements which are arranged in ordered rows and columns. Logic gate devices receive two input arrays and provide an output array having digital states dependent only on the digital states of the signal elements of the two input arrays at corresponding row and column positions. The logic devices include an array of photoconductors responsive to at least one of...
Topics: AIRFRAME MATERIALS, HYPERSONIC SPEED, NOZZLE DESIGN, SUPERSONIC COMBUSTION RAMJET ENGINES, EXHAUST...
393
393
Jul 5, 2010
07/10
by
Donaghey, C. E.; Ozkul, O. S
texts
eye 393
favorite 0
comment 0
No Abstract Available
Topics: AIRCRAFT FUELS, COST ANALYSIS, HYPERSONIC AIRCRAFT, LIQUID HYDROGEN, PRODUCTION ENGINEERING,...
546
546
May 28, 2011
05/11
by
McNeal, Curtis I., Jr.; Anderson, Willia
texts
eye 546
favorite 0
comment 0
NASA's current focus on technology roadmaps as a tool for guiding investment decisions leads naturally to a discussion of NASA's roadmap for peroxide propulsion system development. NASA's new Second Generation Space Transportation System roadmap calls for an integrated Reusable Upper-Stage (RUS) engine technology demonstration in the FY03/FY04 time period. Preceding this integrated demonstration are several years of component developments and subsystem technology demonstrations. NASA and the...
Topics: FLIGHT CHARACTERISTICS, WORKLOADS (PSYCHOPHYSIOLOGY), HYPERSONIC AIRCRAFT, OSCILLATIONS,...
166
166
Jul 11, 2010
07/10
by
TAKAHASHI, T.; KUWABARA, K
texts
eye 166
favorite 0
comment 0
IONIC CONDUCTION IN SINTERED OXIDES WITH HOLLANDITE TYPE STRUCTURE, WHICH HAVE TETRAGONAL LATTICE AND INVOLVE TUNNELS ALONG THE C AXIS, WAS INVESTIGATED. DEGREE OF SINTERING WAS DEFINED BY THE RATIO OF APPARENT DENSITY OF THEORETICAL X-RAY DENSITY. WHEN K2CO3, MGO AND TIO2 WERE FIRED AT 1200 C FOR 5 HR AFTER PREFIRING AT 950 C FOR 10 HR, THE DEGREE OF SINTERING REACHED 85 TO APPROXIMATELY 90%. FROM THE RESULTS OF THE POWER X-RAY DIFFRACTIONS, FLUORESCENCE X-RAY ANALYSES, AND LATTICE CONSTANTS,...
Topics: COOLING SYSTEMS, FAIL-SAFE SYSTEMS, HYPERSONIC AIRCRAFT, LIQUID HYDROGEN, SUPERSONIC AIRCRAFT,...
373
373
Jul 9, 2010
07/10
by
MARTSINKEVICH, L. M
texts
eye 373
favorite 0
comment 0
THE STATISTICAL CHARACTERISTICS OF THE SLOPES OF WAVES ARE CALCULATED ON THE BASIS OF CHARTS OF WAVE STEREOPHOTOGRAPHY. IT IS SHOWN THAT THE DISTRIBUTION OF THE PROJECTIONS OF SLOPE ONTO THE MAIN AXIS OF WAVE PROPAGATION AND ONTO THE AXIS PERPENDICULAR TO IT OBEY A NORMAL DISTRIBUTION LAW. THE DISTRIBUTION OF SLOPES CORRESPONDS TO THE THEORETICAL LAW OF DISTRIBUTION, DERIVED PREVIOUSLY.
Topics: AERODYNAMIC CONFIGURATIONS, AEROSPACE PLANES, AIRCRAFT DESIGN, BOOSTGLIDE VEHICLES, ECONOMIC...
The focus of this investigation was on the understanding and prediction of the nonlinear geometric (large displacements) dynamic response of functionally graded panels subjected to the severe acoustic, thermal, and mechanical/aerodynamic excitations expected for hypersonic vehicles. The phenomenological analysis centered more specifically on the differences observed in the response of metallic panels and those functionally graded while a pre-existing reduced order modeling strategy was...
Topics: DTIC Archive, ARIZONA STATE UNIV TEMPE, *AIRCRAFT PANELS, *DYNAMIC RESPONSE, AERODYNAMIC FORCES,...
260
260
Jul 11, 2010
07/10
by
KLEIN, A
texts
eye 260
favorite 0
comment 0
THE TOTAL PRESSURE AND THE FLOW ANGLE AT VARIOUS DISTANCES FROM THE AXIS WERE STUDIED FOR FOUR ROTOR SPEEDS. DATA OBTAINED WITH A CYLINDRICAL PROBE WHICH ROTATED WITH THE ROTOR ARE COMPARED WITH VALUES INDICATED BY THE SAME PROBE KEPT IN A FIXED POSITION. NO SIGNIFICANT DIFFERENCES CONCERNING THE MEAN TOTAL PRESSURE, OR THE FLOW ANGLE AT GREAT DISTANCES FROM THE AXIS COULD BE OBSERVED FOR BOTH PROBE POSITIONS. THERE WERE, HOWEVER, DIFFERENCES IN THE FLOW ANGLE AMOUNTING TO AS MUCH AS TWO DEG IN...
Topics: FLOW DISTRIBUTION, FOREBODIES, HYPERSONIC AIRCRAFT, SURFACE GEOMETRY, ANGLE OF ATTACK, STATIC...
An investigation of approximate theoretical techniques for predicting aerodynamic characteristics and surface pressures for relatively slender vehicles at moderate hypersonic speeds was performed. Emphasis was placed on approaches that would be responsive to preliminary configuration design level of effort. Supersonic second order potential theory was examined in detail to meet this objective. Shock layer integral techniques were considered as an alternative means of predicting gross...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, HYPERSONIC AIRCRAFT, PERFORMANCE...
307
307
Jun 9, 2011
06/11
by
Mitcheltree, R. A.; DiFulvio, M.; Horvath, T. J.; Braun, R. D
texts
eye 307
favorite 0
comment 0
A combination of computational predictions and experimental measurements of the aerothermal heating expected on the two Mars Microprobes during their entry to Mars are presented. The maximum, non-ablating, heating rate at the vehicle's stagnation point (at alpha = 0 degrees) is predicted for an undershoot trajectory to be 194 Watts per square centimeters with associated stagnation point pressure of 0.064 atm. Maximum stagnation point pressure occurs later during the undershoot trajectory and is...
Topics: FLIGHT CONTROL, FLIGHT TESTS, RESEARCH VEHICLES, HYPERSONIC AIRCRAFT, PERFORMANCE PREDICTION,...
A theoretical study of the use of heat pipe structures for cooling the leading edges of hypersonic cruise aircraft was carried out over a Mach number range of 6 to 12. Preliminary design studies showed that a heat pipe cooling structure with a 33-in. chordwise length could maintain the maximum temperature of a 65 deg sweepback wing with a 0.5-in. leading edge radius below 1600 F during cruise at Mach 8. A few relatively minor changes in the steady-state design of the structure were found...
Topics: NASA Technical Reports Server (NTRS), COOLING SYSTEMS, HEAT PIPES, HYPERSONIC AIRCRAFT, LEADING...
This paper presents the status of the airbreathing hypersonic airplane and space-access vehicle design matrix, reflects on the synergies and issues, and indicates the thrust of the effort to resolve the design matrix and to focus/advance systems technology maturation. Priority is given to the design of the vision operational vehicles followed by flow-down requirements to flight demonstrator vehicles and their design for eventual consideration in the Future-X Program.
Topics: NASA Technical Reports Server (NTRS), AIR BREATHING ENGINES, HYPERSONICS, HYPERSONIC AIRCRAFT,...
The presentation will provide a brief overview of the project with specific focus on Dryden's role and capabilities exercised during X-43A.
Topics: NASA Technical Reports Server (NTRS), SUPERSONIC COMBUSTION RAMJET ENGINES, FLIGHT TESTS,...
The effort was in two areas: (1) development of advanced methods of flight path optimization, and (2) development of advanced methods of structural weight estimation.
Topics: NASA Technical Reports Server (NTRS), TRAJECTORY ANALYSIS, HYPERSONIC AIRCRAFT, ESTIMATING,...
The research during the third reporting period focused on fixed order robust control design for hypersonic vehicles. A new technique was developed to synthesize fixed order H(sub infinity) controllers. A controller canonical form is imposed on the compensator structure and a homotopy algorithm is employed to perform the controller design. Various reduced order controllers are designed for a simplified version of the hypersonic vehicle model used in our previous studies to demonstrate the...
Topics: NASA Technical Reports Server (NTRS), AIRCRAFT CONTROL, CONTROLLERS, HOMOTOPY THEORY, HYPERSONIC...
Topics: DTIC Archive, JOINT PUBLICATIONS RESEARCH SERVICE ARLINGTON VA, *FOREIGN TECHNOLOGY, EUROPE, SPACE...
397
397
Jul 12, 2010
07/10
by
NON
texts
eye 397
favorite 0
comment 0
No Abstract Available
Topics: AERODYNAMIC CONFIGURATIONS, STRUCTURAL DESIGN, AIRCRAFT DESIGN, CONFERENCES, HYPERSONIC AIRCRAFT,...
NASA Ames has a long tradition in leadership with the use of ballistic ranges and shock tubes for the purpose of studying the physics and phenomena associated with hypervelocity flight. Cutting-edge areas of research run the gamut from aerodynamics, to impact physics, to flow-field structure and chemistry. This legacy of testing began in the NACA era of the 1940's with the Supersonic Free Flight Tunnel, and evolved dramatically up through the late 1950s with the pioneering work in the Ames...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMICS, BALLISTIC RANGES, FLOW DISTRIBUTION, HYPERSONIC...
As part of NASA's continuing research into hypersonics and 85 square foot hypersonic wing test section of a proposed hypersonic research airplane was laboratory tested. The project reported on in this paper has carried the hypersonic wing test structure project one step further by testing a single beaded panel to failure. The primary interest was focused upon the buckling characteristics of the panel under pure compression with boundary conditions similar to those found in a wing mounted...
Topics: NASA Technical Reports Server (NTRS), BUCKLING, HYPERSONIC AIRCRAFT, SKIN (STRUCTURAL MEMBER),...
The weights of major structural components of hypersonic, liquid hydrogen fueled aircraft are estimated and discussed. The major components are the body structure, body thermal protection system tankage and wing structure. The method of estimating body structure weight is presented in detail while the weights of the other components are estimated by methods given in referenced papers. Two nominal vehicle concepts are considered. The advanced concept employs a wing-body configuration and hot...
Topics: NASA Technical Reports Server (NTRS), AIRCRAFT STRUCTURES, HYPERSONIC AIRCRAFT, STRUCTURAL...
Assessing prediction confidence and enabling its use as a decision-making metric for autonomous model fidelity selection is essential to the USAF's vision of a Digital Twin as a viable approach for condition-based fleet management by tail number. Significant strides have been made in modeling complex interactions of the multi-physics, fluid-thermal-structural coupling applicable to hypersonic flow conditions. However, validation of these models remains a challenge due to limited experimental...
Topics: DTIC Archive, AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH AEROSPACE SYSTEMS DIR,...
The probable descent operating conditions for a hypersonic air-breathing research airplane were examined. Descents selected were cruise angle of attack, high dynamic pressure, high lift coefficient, turns, and descents with drag brakes. The descents were parametrically exercised and compared from the standpoint of cold-wall (367 K) aircraft heat load. The descent parameters compared were total heat load, peak heating rate, time to landing, time to end of heat pulse, and range. Trends in total...
Topics: NASA Technical Reports Server (NTRS), DESCENT TRAJECTORIES, HYPERSONIC AIRCRAFT, RESEARCH AIRCRAFT,...
In Germany the Ministry of Research and Technology (BMFT) initiated in 1986 study work at industry focused on Determining of the principal features and results as Starting Points for German Industry in the Development of Future Hypersonic Transport-Aircraft with a view to Possible Hypersonic Aircraft Projects. Then, after the start of the newly initiated German Hypersonics Technology Programme in 1987 the Two-Stage-To-Orbit (TSTO) transportation system became the reference concept of the German...
Topics: DTIC Archive, AEROSPACE CONSULTING TAUFKIRCHEN (GERMANY), *AIRFRAMES, *ENGINEERING, *ENGINES,...
The hypersonic stability, control, and performance characteristics of two configurations have been determined. Each configuration had a 50 deg swept delta wing, a vertical tail, and a body flap. One model represented a control configured vehicle with a reduced level of longitudinal static stability; the other model was designed for a conventional level of stability. Data were obtained over an angle of attack range of 0 deg to 50 deg and included effects of component buildup. In addition, the...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, CONTROL STABILITY, HYPERSONIC...
An investigation to provide the analyses, data, and hardware required to experimentally validate the beaded panel concept and demonstrate its usefulness as a basis for design of a Hypersonic Research Airplane (HRA) wing is reported. Combinations of the beaded panel structure, heat shields, channel caps and corrugated webs for ribs and spars were analyzed for the wing of a specified HRA to operate at Mach 8 with a lifespan of 150 flights. Detailed analyses were conducted in accordance with...
Topics: NASA Technical Reports Server (NTRS), HYPERSONIC AIRCRAFT, WING PANELS, AERONAUTICAL ENGINEERING,...
A conceptual design of a multi-stage aerospace craft is presented. Two perspective views of the vehicle are developed to show the two component configuration with delta wing, four vertical tail surfaces, tricycle landing gear, and two rocket exhaust nozzles at the rear of the fuselage. Engines for propulsion in the atmosphere are mounted on the fuselage in front of the wing root attachment.
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CONFIGURATIONS, AEROSPACE PLANES, AIRCRAFT...
229
229
Jun 27, 2010
06/10
by
Downs, W. R
texts
eye 229
favorite 0
comment 0
Chemical processes for producing oxygen and water on moon from lunar rocks and soils
Topics: GAS INJECTION, TURBULENT BOUNDARY LAYER, HYDROGEN, INJECTORS, JET MIXING FLOW, SUPERSONIC...
The Air Force requires new technical capabilities to control the flight characteristics of planned hypersonic aircraft. The plasma actuator concept offers the possibility to quickly maneuver a hypersonic vehicle merely by switching on or off the generation of a lightly ionized air plasma along panels embedded in the aircraft's skin. The goal of this basic research effort is to harness the state-of-the-an in multidimensional plasma modeling capabilities to better understand the basic physics of...
Topics: DTIC Archive, MIAMI UNIV CORAL GABLES FL, *FLIGHT CONTROL SYSTEMS, *HYPERSONIC AIRCRAFT, MILITARY...
Travel markets which would be served by high speed commercial transport aircraft and the ability of the airlines to schedule and route the aircraft in a way that would achieve good daily utilization and productivity are examined. The following areas are considered: (1) identification of the major long-haul city pairs that would most likely demand nonstop service; (2) selection of flight tracks observing alternative sonic boom restrictions; (3) estimation of flight times for all city pairs for...
Topics: NASA Technical Reports Server (NTRS), AIR TRAFFIC CONTROL, AIRLINE OPERATIONS, HYPERSONIC AIRCRAFT,...
Aerodynamic characteristics of a model designed to represent an all body, hypersonic cruise aircraft are presented for Mach numbers from 0.65 to 10.6. The configuration had a delta planform with an elliptic cone forebody and an afterbody of elliptic cross section. Detailed effects of varying angle of attack (-2 to +15 deg), angle of sideslip (-2 to +8 deg), Mach number, and configuration buildup were considered. In addition, the effectiveness of horizontal tail, vertical tail, and canard...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, HYPERSONIC AIRCRAFT, WIND TUNNEL...
An ablative material composed of silica-filled elastomeric silicone was tested to evaluate its thermal and structural performance as an external insulator, or heat shield, for a hypersonic research aircraft. The material was also tested to determine whether it would form a durable char layer when initially heated and thereafter function primarily as an insulator with little further pyrolysis or char removal. Aerothermal tests were representative of nominal Mach 6 cruise conditions of the...
Topics: NASA Technical Reports Server (NTRS), ABLATIVE MATERIALS, HEAT SHIELDING, HYPERSONIC AIRCRAFT,...
This presentation will overview European Thermal Protection Systems (TPS) and Hot Structures activities in Europe. The Europeans have a lot of very good work going on in the area. The presentation will discuss their emphasis on focused technology development for their flight vehicles.
Topics: NASA Technical Reports Server (NTRS), THERMAL PROTECTION, HYPERSONIC AIRCRAFT, HYPERSONIC HEAT...
