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Saturday, April 18, 2020 | History

4 edition of Experimental and computational analysis of shuttle orbiter hypersonic trim anomaly found in the catalog.

Experimental and computational analysis of shuttle orbiter hypersonic trim anomaly

Experimental and computational analysis of shuttle orbiter hypersonic trim anomaly

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  • 17 Currently reading

Published by American Institute of Aeronautics and Astronautics, [National Aeronautics and Space Administration, National Technical Information Service, distributor in Washington, DC, Springfield, Va .
Written in English

    Subjects:
  • Space shuttle orbiters,
  • Wind tunnel tests,
  • Hypersonic wind tunnels,
  • Pitching moments,
  • Temperature effects,
  • Flow distribution,
  • Gas flow,
  • Ideal gas,
  • Navier-Stokes equation

  • Edition Notes

    StatementGregory J. Brauckmann; John W. Paulson, Jr.; K. James Weilmuenster.
    SeriesNASA-TM -- 112155., NASA technical memorandum -- 112155.
    ContributionsPaulson, John W., Weilmuenster, K. James., United States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL17837132M
    OCLC/WorldCa39777210

    Publications related to the WIND-US CFD Code. The following is a list of technical papers and journal articles containing information related to the development and application of the WIND-US CFD code or one of its direct predecessor codes (WIND, NASTD, PARC, NPARC). Overall, the HL would we kg without crew compared to the Space Shuttle Orbiter's empty weight of 84, kg. The space available inside for the crew and passengers, although less than the Shuttle, would be more than found in today's small corporate business jets.   The shuttle's processing director, Conrad Nagel, said Monday that NASA hoped to launch the shuttle Nov. 30, but that Dec. 1 was a more likely date because of a few remaining technical : Felicity Barringer.


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Experimental and computational analysis of shuttle orbiter hypersonic trim anomaly Download PDF EPUB FB2

Tween the present experimental results, computational predictions, the preflight aerodynamic data book released in7 and aero-dynamic coefficients derived from the flight of STS The re-suits of this study are expected to help define the optimum ap-proach for the design of the next-generation space transportati,m system.

A theoretical and computational study of the vibration excitation on the transition criteria of shock wave reflections Aerospace Science and Technology, Vol.

89 Optical Free-Flight Measurements using GPU-Accelerated Computer GraphicsCited by: Get this Experimental and computational analysis of shuttle orbiter hypersonic trim anomaly book a library. Experimental and computational analysis of shuttle orbiter hypersonic trim anomaly.

[Gregory J Brauckmann; John W Paulson; K James Weilmuenster; United States. National Aeronautics and Space Administration.]. Not Available adshelp[at] The ADS is operated by the Smithsonian Astrophysical Observatory under NASA Cooperative Agreement NNX16AC86ACited by: Experimental Hypersonic Aerodynamic Characteristics of the Space Shuttle Orbiter for a Range of Damage Scenarios [Gregory J.

Brauckman, William I. Scallion, Nasa Technical Reports Server (Ntrs)] on *FREE* shipping on qualifying offers. The NASA Technical Reports Server (NTRS) houses half a million publications that are a valuable means of Cited by: 7. Initial experimental testing conducted within two weeks of the accident simulated a broad spectrum of thermal protection system damage to the Orbiter windward surface and was used to refute.

Journal of Spacecraft and Rockets; Journal of Thermophysics and Heat Transfer; Experimental and computational analysis of Shuttle Orbiter hypersonic trim anomaly. Gregory J. Brauckmann, John W. Paulson Jr. and; Analysis of close-paced brush-fiber interfaces for spacecraft thermal management.

In this paper, we study the vibration excitation on the reflection of shock waves in hypersonic flows by using analytical and computational approaches.

First, a theoretical approach is established to solve the shock relations which are further applied to develop the shock polar analytical method for high-temperature by: 2. Experimental and computational analysis of shuttle orbiter hypersonic trim anomaly book studies, CUBRC also performed a large amount of CFD analysis to confirm and validate not only the tunnel freestream conditions, but also 3D flows over the orbiter acreage, wing leading edge, and control surfaces to assess data quality, shock interaction locations, and control surface separation regions.

and thus very little experimental data were available for the early Space Shuttle studies. Wind tunnel testing—an experimental technique used to obtain associated data—forces air past a scaled model and measures data of interest, such as local pressures, total forces, or heating rates. Accomplishing the testing necessary to cover the full.

This paper describes Shuttle Orbiter aerodynamic design conducted by Rockwell International under contract to NASA. Aerodynamic criteria key to establishing the external configuration are discussed together with evolution of the design including effects of wing-body blending on high angle of attack aerodynamics.

Of these vehicles the Space Shuttle Orbiter so far is the only operational vehicle. The other ones are conceptual studies or projects, which have reached different degrees of maturity.

RV-W’s are either launched vertically with the help of rockets or, in the case of TSTO systems, horizontally from a carrier vehicle, Cited by: 1. In this book basics of aerothermodynamics are treated, which are of importance for the aerodynamic and structure layout of hypersonic flight vehicles.

It appears to be Experimental and computational analysis of shuttle orbiter hypersonic trim anomaly book to identify from the beginning classes of hypersonic vehicles, because aerothermodynamic phenomena can have different importance for different vehicle classes.

Full text of "Computational Aerodynamics of Shuttle Orbiter Damage Scenarios in Support of the Columbia Accident Investigation" Paulson, J.

W., and Weilmuenster, K. J., "Experimental and Computational Analysis of Experimental and computational analysis of shuttle orbiter hypersonic trim anomaly book Orbiter Hypersonic Trim Anomaly," Journal of Spacecraft and Rockets, Vol.

32, No. 5, September-October Nickel-based superalloys are promising options for the thermal protection systems of hypersonic re-entry vehicles operating under moderate aerothermal heating conditions.

We present an experimental study on the interactions between PM EXPERIMENTAL AND COMPUTATIONAL INVESTIGATION OF AN ELECTRIC ARC AIR-SPIKE IN HYPERSONIC FLOW WITH DRAG MEASUREMENTS R.M.

Bracken*, L.N. Myrabo f, H.T. Nagamatsu*, E.D. Meloney§ Department of Mechanical Engineering, Aeronautical Engineering, and Mechanics Rensselaer Polytechnic Institute Troy, New York and M. This paper presents the static aerodynamics analysis of the MSL capsule in the hypersonic entry process for exploration mission to Mars.

Hypersonic static coefficients were derived from fully three-dimensional computational fluid dynamics solutions with a specified effective specific heat ratio on a typical trajectory by: 4.

The book has been prepared as a valuable contribution to the state-of-the-art on computational methods in hypersonic aerodynamics. All the chapters have been written by eminent scientists and researchers well known for their work in this field.

Enter your mobile number or email address below and we'll send you a link to download the free Kindle Cited by: Computational and Analytical Investigation of Aerodynamic Derivatives of Similitude Delta Wing Model at Hypersonic Speeds Figure 2 2-D geometry of the wedge From Figure 2, we obtain: With the changes in the equations of the analytical.

As part of the development of this TPS system, the X aeroheating environment is being defined through conceptual analysis, ground based testing, and computational fluid dynamics. This report provides an overview of the hypersonic aeroheating wind tunnel program conducted at the NASA Langley Research Center in support of the ground based.

This paper presents experimental results of TSTO (Two-Stage-To-Orbit) aerodynamic heating at hypersonic speed. TSTO is a promising space transportation system consisting of two stages, i.e., an orbiter and a booster, and is supposed to fly in a wide speed range from subsonic to hypersonic.

An Aerodynamic Analysis of Several Hypersonic Research Airplane Concepts from M = to Jim A. Penland,' James L. Dillon, t and Jimmy L. Pittmant NASA Langley Research Center, Hampton, Va. Several conceptual hypersonic research airplanes, designed within the constraints of a B launch aircraft,File Size: 2MB.

An overview of the wind tunnel program is given and aerodynamic characteristics of the final configuration are described. Aerodynamic parameters critical to definition of Orbiter entry control and performance are identified.

Trim capability and stability and control characteristics are discussed at critical regions in the entry trajectory. The Hypersonic Pitching Moment Anomaly of the Space Shuttle Orbiter Trim Situation and Possible Causes of the Pitching Moment Anomaly Pressure Coefficient Distribution at the Windward Side of the Orbiter The Forward Shift of the Center-of-Pressure Pages: In another example of an “unknown unknown,” Woods et al.

() noted that preflight predictions based on the aerodynamics in the Aerodynamic Design Data Book (ADDB) indicated that a deflection of the body flap would be required to trim the Space Shuttle Orbiter for the center of gravity and vehicle configuration of STS Hypersonic CFD Space Shuttle Simulations Space Operations Mission Directorate Computational fluid dynamics (CFD) simulations provide high-fidelity assessment of possible damage to the Space Shuttle, in support of the shuttle’s Damage Assessment Team.

Using the powerful and reliable comput. This Note records the results of a review and analysis of the status of the computational fluid dynamic (CFD) modeling techniques related to the National Aerospace Plane (NASP) operation. The research sought to evaluate independently the degree of uncertainty and the technical risk involved in predicting the NASP performance using numerical.

space shuttle orbiter is a good example of warm structure. The entire vehicle is protected with a thermal protection system (TPS) to shield the aluminum substructure from overheating beyond the warm temperature limit (ref. An example of a recent hot structure is the new hypersonic flight research vehicle called Hyper-X.

ASYMPTOTIC ANALYSIS OF HYPERSONIC VEHICLE DYNAMICS ALONG ENTRY TRAJECTORY by William D. Janicki Lt, United States Air Force B.S., Astronautical Engineering U.S.

Air Force Academy, Submitted to the Department of Aeronautics and Astronautics in Partial Fulfillment of the Requirements for the Degree of Master of Science.

Written by best-selling author, John D. Anderson, Jr., this book covers the subject of sustained hypersonic flight, the technology behind the Space Shuttle and other high speed flight vehicles.

Anderson's book offers timely and up-to-date information on hypersonic flow-an area that has grown explosively in the last decade. installed on the Space Shuttle, was flown on STS in March A second flight experiment with a inch tall protuberance was recently flown on STS (August, September ).

• Numerous computational fluid dynamics (CFD) simulations were used to optimize the height and shape of the BLT protuberance. Numerical Simulation of Hypersonic Aerodynamics and the Computational Needs for the Design of an Aerospace Plane Author: Shiao-kung Liu Subject: Records the results of a review and analysis of the status of the computational fluid dynamic (CFD) modeling techniques related to the National Aerospace Plane (NASP) operation.

This Note records the results of a review and analysis of the status of the computational fluid dynamic (CFD) modeling techniques related to the National Aerospace Plane (NASP) operation. It was undertaken as a task in the study, The National Aerospace Plane (NASP): Development Issues for Follow-on Systems, performed within the Technology.

This official NASA history document - converted for accurate flowing-text e-book format reproduction - is a fascinating account by the former chief scientist of the Dryden Flight Research Center of the major space and aeronautical developments of the last 40 years, including the Space Shuttle, X, X, the lifting body program, the National Aerospace Plane (NASP), and other hypersonic Brand: Progressive Management.

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A space shuttle orbiter is subjected to thrusts from five of the engines of its reaction control system. Four of the thrusts are shown in the figure; the fifth is an N upward thrust at the right rear, symmetric to the N thrust shown on the left rear%(13).

These problems include a Space Shuttle frame component, an insulated cylinder, a metallic panel for a thermal protection system, and a model of the Space Shuttle Results generally indicate a Orbiter wing.

preference for implicit over explicit algorithms for solution of transient structural heat transfer problems when the governing equations are. Aerodynamic characteristic analysis of hypersonic cruise aircraft is more difficult than that of conventional aircraft, for the complex flow field simulation and inadequate amount of results under limited flight conditions.

In this paper, numerical schemes applicable for hypersonic flow field are adopted to acquire a set of aerodynamic characteristics of a typical hypersonic cruise aircraft Cited by: 2. Available coefficients of longitudinal motion are presented for a variety of shapes of operational and studied vehicles, and aerothermodynamic issues of stabilization, trim, and control devices are treated.

A full chapter is devoted to describing equations for aerodynamic forces, moments, center of pressure, trim, and stability. Tanabe, A, Matsuo, A, Kojima, T & Taguchi, HNumerical evaluation of aerodynamic interference between wing and fuselage for hypersonic experimental aircraft.

in 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition.,48th AIAA Aerospace Sciences Meeting Including the New Horizons Author: Akira Tanabe, Akiko Matsuo, Takayuki Kojima, Hideyuki Taguchi.

Therefore, SEADS was developed under the orbiter experiments program to take the measurements required for precise pdf of air data across the orbiter's atmospheric flight-speed range (i.e., hypersonic, supersonic, transonic and subconic Mach numbers) or from lift-off tofeet during ascent and fromfeet to touchdown.Full text of "CFD Simulations in Support of Shuttle Orbiter Contingency Abort Aerodynamic Database Enhancement" See other formats AIAA CFD SIMULATIONS IN SUPPORT OF SHUTTLE ORBITER CONTINGENCY ABORT AERODYNAMIC DATABASE ENHANCEMENT P.

E. Papadopoulos," D. K. Prabhu,' M. J. Wright,* C. B. Davies, 5 R. D. .Atmospheric entry is the movement of ebook object from outer space into and through the gases of an ebook of a planet, dwarf planet, or natural are two main types of atmospheric entry: uncontrolled entry, such as the entry of astronomical objects, space debris, or bolides; and controlled entry (or reentry) of a spacecraft capable of being navigated or .