3 edition of Development of the X-33 aerodynamic uncertainty model found in the catalog.
Development of the X-33 aerodynamic uncertainty model
1998 by National Aeronautics and Space Administration, Dryden Flight Research Center, National Technical Information Service, distributor in Edwards, Calif, [Springfield, Va .
Written in English
|Statement||Brent R. Cobleigh.|
|Series||[NASA technical paper] -- NASA/TP-1998-206544., NASA technical paper -- 206544.|
|Contributions||NASA Dryden Flight Research Center.|
|The Physical Object|
With the capability of high speed flying, a more reliable and cost efficient way to access space is provided by hypersonic flight vehicles. Controller design, as key technology to make hypersonic flight feasible and efficient, has numerous challenges stemming from large flight envelope with extreme range of operation conditions, strong interactions between elastic airframe, the propulsion Cited by: When the Enter key is pressed the numerical value of the right-hand side is assigned to the variable, and MATLAB displays the variable and its assigned value in the next two lines. The following shows how the assignment operator works. >> x=15 x = 15 >> x=3*x x = . At the TIB Technik/Naturwissenschaften (Science/Technology) and TIB Conti-Campus sites, lending and returning items (Monday to Friday from to ) and registration (Monday to Friday from to ) is possible.
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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, Development of the X-33 aerodynamic uncertainty model book sched-ules with a total time from development to flight Development of the X-33 aerodynamic uncertainty model book years.
Development of VentureStar, the full-scale operational RLV, progressed in parallel with the X program . 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 Development of the X-33 aerodynamic uncertainty model book 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 Development of the X-33 aerodynamic uncertainty model book.
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 Development of the X-33 aerodynamic uncertainty model book 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: - Bandu N. Pamadi and Gregory J.
Brauckmann, Aerodynamic Characteristics and Development of the Aerodynamic Database of the X Reusable Launch Vehicle, International Symposium on Atmospheric Reentry Vehicles and Systems, Arcachon, France, MarchThe Penn State Department of Aerospace Engineering, established in and the only aerospace engineering department in Pennsylvania, is consistently recognized as one of the top aerospace engineering departments in the nation, and is also an international leader in aerospace education, research, and engagement.
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.
This paper reviews the state of phosphor thermometry, focusing on developments in the past 15 years. The fundamental principles and theory are presented, and the various spectral and temporal modes, including the lifetime decay, rise time and intensity ratio, are discussed.
The entire phosphor measurement system, including relative advantages to conventional methods, choice of phosphors Cited by: A result of topology is that if the base space P is contractible, a cross section exists.
Clearly, for an aircraft, the flight envelope P is a contractible space, so that a cross section is guaranteed to exist. TOWARDS THE X The X is a reduced-scale, unmanned, suborbital demonstration vehicle for the new space shuttle, the "Venture Cited by: 5.
高超声速空气动力学是空气动力学研究的前沿,它随着现代高超声速飞行器的发展需求而发展.未来高超声速空气动力学的发展趋势可大致概括为重视物理建模、预测的精细化;重视实用的高性能计算、海量信息的提取和理解;重视飞行器与流动的非定常、非线性的耦合运动及控制研究;重视多目标/多学科. First, a signal model of MSI was introduced to compactly represent the signal distribution in the spectral dimension and enable accelerations of MSI scans.
The model-based reconstruction was demonstrated to provide 3-fold acceleration beyond conventional acceleration techniques including parallel imaging and partial Fourier reconstruction.
As part of the industry/government partnership, personnel and facilities at the Langley Research Center (NASA) were assigned the task of providing information regarding the aerodynamic forces and moments, the surface heating, and the criteria for boundary-layer transition to Lockheed Martin in support of X development and design.
Uncertainty in penetration determinations were _>_+ 10 per- cent at a given diameter. Particle density measurement 6. Opacity measurement for saturated gas stream Model development should be furthered with respect to: 1. (about 35 x 33 10 cfm or m /s as compared with the present pilot plant capacity 3 x cfm or m3/s).
Development of the X Aerodynamic Uncertainty Model Brent R. Cobleigh Dryden Flight Research Center Edwards, California. April The NASA STI Program Office in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space science.
Read "NASA Lessons Learned in Engineering: Marshall Engineers Recount Problems and Solutions on Saturn V Rocket, Apollo, Space Shuttle, SSME, Hubble Space Telescope, X, Other Vehicles and Systems" by Progressive Management available from Rakuten Kobo.
This report is Brand: Progressive Management. Bruce Jackson and Christopher I. Cruz, Preliminary Subsonic Aerodynamic Model for Simulation Studies of the HL Lifting Body, NASA TM, Augustpp. Richard S. Pappa, Axel Schenk and Christopher Noll, Eigensystem Realization Algorithm Modal Identification Experiences With Mini-Mast, NASA TM, Februarypp.
Keshmiri S, Colgren R () Development of an aerodynamic database for pdf generic hypersonic air vehicle. In: Proceedings of AIAA guidance, navigation, and control conference and exhibit, AIAA, San Francisco, CA, USA, pp – Google ScholarAuthor: Congchao Yao, Xinmin Wang, Yao Huang, Yuyan Cao.The Rockwell X used the Space Shuttle Main Engine (SSME), which meant the propellant would have to be carried in the fuselage of the vehicle.
Since this was a cooperative government industry project, NASA engineers could participate in the design phase of .To this end, extensive ebook investigations ebook been conducted by Culler and McNamara  , Miller and McNamara , and Miller et al.
 to assess the interaction between coupled structural, thermal, and fluid element methods have been formulated by Daneshjo and Ramezani  and Carrera et al.  to study the linear dynamics of laminate plates exhibiting rich coupling Cited by: 4.