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4 edition of Development of the X-33 aerodynamic uncertainty model found in the catalog.

Development of the X-33 aerodynamic uncertainty model

Development of the X-33 aerodynamic uncertainty model

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Published by National Aeronautics and Space Administration, Dryden Flight Research Center, National Technical Information Service, distributor in Edwards, Calif, [Springfield, Va .
Written in English


Edition Notes

StatementBrent R. Cobleigh.
Series[NASA technical paper] -- NASA/TP-1998-206544., NASA technical paper -- 206544.
ContributionsNASA Dryden Flight Research Center.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL17591854M
OCLC/WorldCa42758571

VOLUME II TABLE OF CONTENTS A Type-S Pi tot Tube Calibration Study 1 by Robert F. Vollaro The Effect of Aerodynamic Interference Between a Type-S 24 Pi tot Tube and Sampling Nozzle on the Value of the Pi tot Tube Coefficient by Robert F. Vollaro The Effects of the Presence of a Probe Sheath on Type-S 30 Pi tot Tube Accuracy by Robert F. Vollaro An Evaluation of Single-Velocity. Frequency-Limited Adaptive Control of a Generic Transport Model in the Presence of Uncertainty in Control Effectiveness. Proceedings of the AIAA Science and Technology Forum and Exposition. Bershadsky, D., Dressel, L., & Johnson, E. ().

This software has been used for aerodynamic analyses on most of NASA's recent planetary and reusable launch vehicles: Mars landers jiSESl X^— X,^^ X, and the Shuttle Orbiter at high angles of attack)^ The geometry for the Orbiter was developed in GridTool,^^ based on a .   Uncertainty propagation in aerodynamic forces and heating analysis for hypersonic vehicles with uncertain-but-bounded geometric parameters Aerospace Science and Technology, Vol. 77 Numerical method of carbon-based material ablation effects on aero-heating for half-sphereCited by:

The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading—Part I: University Research and Methods Development J. Turbomach (October, ) The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading—Part II: Low and High-Speed Designs and Test VerificationCited by: 3. This paper proposes a new robust two-degree-of-freedom (DoF) design method for controlling the nonlinear longitudinal speed problem of hybrid electric vehicles (HEVs). First, the uncertain parameters of the HEV model are described by fuzzy α-cut representation, in which the interval uncertainty and the possibility can be simultaneously indicated by the fuzzy membership by: 6.


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Subcommittee hearing on H. R. 1203, to amend the act of October 30, 1941, as amended, to authorize Air Force officers designated by the Secretary of the Air Force to take action on reports of survey and vouchers pertaining to the loss, damage, spoilage, unserviceability, unsuitability, or destruction of government property

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Development of the X-33 aerodynamic uncertainty model Download PDF EPUB FB2

Get this from a library. Development of the X aerodynamic uncertainty model. [Brent R Cobleigh; NASA Dryden Flight Research Center.]. the X vehicle. The X program (Phase I and Phase II) had ambitious, fast-paced sched-ules with a total time from development to flight of years.

Development of VentureStar, the full-scale operational RLV, progressed in parallel with the X program [2]. Figure 1. The Lockheed-Martin X and early RLV compared to Shuttle. Experimental measurement of the aerodynamic heating via the global thermographic phosphor technique and development of a hypersonic boundary-layer transition correlation for X is described.

21st Century Collection of NASA and NACA Dryden Technical Reports: X-Plane, SR, Space Shuttle, Hypersonic Research, Fighter Planes (Two CD-ROM Set) [News, World Spaceflight] on *FREE* shipping on qualifying offers. 21st Century Collection of NASA and NACA Dryden Technical Reports: X-Plane, SR, Space Shuttle, Hypersonic ResearchPrice: $ This work deals with the aerodynamic database development of the Intermediate Experiment Vehicle.

The aerodynamic analysis, carried out for the whole flight scenario, relies on computational fluid dynamics, wind tunnel test, and engineering-based design data generated during the project phases, from rarefied flow conditions, to hypersonic continuum flow up to reach subsonic speeds by: Development of the X aerodynamic uncertainty model [microform] / Brent R.

Cobleigh The face: Brent Harris / Brent Harris Controlling forebody asymmetries in flight [microform]: experience with boundary layer transition strip. The uncertainty models will be used to perform linear analysis of the X flight control system and Monte Carlo mission simulation studies.

Because the X aerodynamic uncertainty model was. Due to the need to contain the spread of coronavirus (COVID) the Library building and reading rooms are closed to visitors until further notice.

The health and safety of our community is of great importance to us and we look forward to staying connected with you online.

Development of the X Aerodynamic Uncertainty Developments in China’s Military Force _Projection and Expeditionary. Development of the X Aerodynamic Uncertainty Discrete Adjoint-Based Design for Unsteady Turbulent Flows On Dynamic Overset Unstructured Discrete Dynamical Classes For Galaxy Discs and the implication of a second generation of Tully-Fisher The key to any hypersonic vehicle development or tech-nology program is a credible preliminary system analysis to identify the technical requirements and guide technol-ogy development.

The X program provided an excel-lent training ground for system design, analysis and development of hypersonic technology. The complexityFile Size: KB. Throughout Aerodynamic and Aerothermodynamic Analysis of Space Mission Vehicles many examples are given, with detailed computations and results for the aerodynamics and aerothermodynamics of all such configurations.

Moreover, a final chapter on future launchers is provided and an Appendix on a possible manned mission to Mars closes the book.

The vector of aerodynamic force and moment coefficients, denoted as c, depends on vehicle state x V, input U and on a set of unknown aerodynamic parameters Θ = [θ D, θ S, θ L, θ l, θ m, θ n], through the aerodynamic model represented by the nonlinear real-valued function l (which translates the aerodynamic model defined in section 3).Cited by: 1.

Development of non-linear, low-speed aerodynamic model for the F/VISTA. Development of the C formation airdrop element geometry. William Blake. The Lockheed SR "Blackbird" is a long-range, high-altitude, Mach 3+ strategic reconnaissance aircraft developed and manufactured by the American aerospace company Lockheed was operated by both the United States Air Force (USAF) and NASA.

The SR was developed as a black project from the Lockheed A reconnaissance aircraft during the s by Lockheed's Skunk Works Designer: Clarence "Kelly" Johnson. Annotated Bibliography. Wayne Durham. Virginia Polytechnic Institute and State University, USA.

Search for more papers by this author Dynamic Concepts, Inc., USA. Search for more papers by this author.

Book Author(s): Wayne Durham. Virginia Polytechnic Institute and State University, USA. Search for more papers by this author.

Kenneth A. 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.

Papadopoulos," D. Prabhu,' M. Wright,* C. Davies, 5 R. McDaniel,' E. Venkatapathy,". 3 Reusable Booster System Technology Assessment. The statement of task for this study (see Appendix A) specifically calls for addressing the technical maturity of the key elements critical to the reusable booster system (RBS) implementation and the ability of current technology development plans to meet technical readiness chapter identifies these key elements, addresses their.

First, the hypersonic vehicle longitudinal dynamics model is made on the base of the fitting of aerodynamic parameters. As to the uncertainty of model parameters, a linear model of the uncertain part is established and the LQR controller parameters are thereupon designed with state transition and a first-order Taylor series expansion method.

() Local Fields of Extremals for Optimal Control Problems with State Constraints of Relative Degree 1. Journal of Dynamical and Control Systems() Global Optimisation in the power management of a Fuel Cell Hybrid Vehicle (FCHV).Cited by:. The Boeing X Dyna-Soar ("Dynamic Soarer") was a United States Air Force (USAF) program to develop a spaceplane that could be used for a variety of military missions, including aerial reconnaissance, bombing, space rescue, satellite maintenance, and as a space interceptor to sabotage enemy satellites.

The program ran from 24 October to 10 Decembercost US$ million Contract award: Octo – Decem The stated vision of the HSR Program is to ''establish the technology foundation by to support the U.S.

transport industry's decision for a production of an environmentally acceptable, economically viable, passenger, 5, nautical mile (n.m.), Mach aircraft.'' 1 This program vision is understood by the committee to mean that the HSR Program will deliver critical technologies.() A constructive interior penalty method for optimal control problems with state and input constraints.

American Control Conference (ACC), () Applicability of optimal control theory to adaptive supply chain planning and by: