3 edition of Proposed input for determining longitudinal aerodynamic parameters for the space shuttle found in the catalog.
Proposed input for determining longitudinal aerodynamic parameters for the space shuttle
by National Aeronautics and Space Administration, Langley Research Center in Hampton, Va
Written in English
|Statement||William T. Suit.|
|Series||NASA technical memorandum -- 85758.|
|Contributions||Langley Research Center.|
|The Physical Object|
This article focuses on the problem of parameter estimation of the uncoupled, linear, short-period aerodynamic derivatives of a Twin Squirrel helicopter in level flight and constant speed. A flight test campaign is described with respect to maneuver specification, flight test instrumentation, and experimental data collection used to estimate the aerodynamic derivatives. The. Aerodynamic Parameter Estimation from Flight Data Applying Extended and Unscented Kalman Filter Girish Chowdhary* and Ravindra Jategaonkar† DLR Institute for Flight Systems, Braunschweig, Germany. Aerodynamic parameter estimation is an integral part of .
American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA The Space Shuttle Columbia disaster was a fatal incident in the United States space program that occurred on February 1, , when the Space Shuttle Columbia (OV) disintegrated as it reentered the atmosphere, killing all seven crew disaster was the second fatal accident in the Space Shuttle program, after the breakup of Challenger soon after liftoff.
Longitudinal and lateral-directional maneuvers with gear down ft and ft , and kts Basic aerodynamic model: Discernible deviations in - longitudinal motion - lateral-directional motion variables 10 13 5 0 8 40 60 Neglecting Landing Gear Effects Time m/s 2 β x r θ α a deg/s deg deg deg Flight. Aerodynamics is the branch of hydrodynamics that deals with the laws of air motion and with the forces acting on the surfaces of streamlined bodies. Aerodynamics generally studies motion with velocities which are far short of the sound velocity ( m/s, km/h).
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Get this from a library. Proposed input for determining longitudinal aerodynamic parameters for the space shuttle. [William T Suit; Langley Research Center.]. SUMMARY A control input form to improve the identification of longitudinal aerodynamic parameters for the Space Shuttle, especially at low Mach numbers, has been proposed.
This input combines features of several inputs currently used with the Shuttle to improve the response in angle-of-attack without exceeding pitch rate limits. A control input form to improve the identification of longitudinal aerodynamic parameters for the Space Shuttle, especially at low Mach numbers, has been proposed.
This input combines features of several inputs currently used with the Shuttle to improve the response Author: W. Suit. Full text of "Aerodynamic design of the space shuttle orbiter" See other formats AERODYNAMIC DESIGN OF THE SPACE SHUTTLE ORBITER by W.E.
Bornemann Manager, Space Shuttle Aerodynamics Rockwell International Corporation Space Systems Group Lakewood Boulevard Downey, CA T.E.
Surber Supervisor, Orbiter Aerodyanmics and Rockwell International Corporation Space. National Aeronautics and Space Administration Washingtor, D.C. Sponsoring Agency Code - 5.
Supplementary Notes -~ 6. Abstract Wind-turdel tests have been conducted in the Langley V/STOL tunnel to determine the aerodynamic characteristics of a large transport aircraft designed to carry the space shuttle. The command language can be input to the VGM code by a UNIX style redirected file, or interactively while the code is executing.
An analysis of the longitudinal aerodynamics of the shuttle. and subsequent landing of Space Transportation System (STS)-1 (). Aeroscience encompasses the engineering specialties of aerodynamics and aerothermodynamics. For the shuttle, each specialty was primarily associated with analysis of flight through the Earth’s atmosphere.
Aerodynamics involves the study of local pressures generated over. The longitudinal aerodynamic parameters were determined from selected runs for the Columbia and Challenger Shuttle vehicles and these results will presented. This paper will supplement the existing flight-derived parameter data base by adding both longitudinal and lateral results using flight test data from the Space Shuttle Discovery.
These. Further, Peyada and Ghosh (11) proposed a new method christened the Neural-Gauss-Newton (NGN) method to estimate parameters. It can capture nonlinear aerodynamics and estimate aerodynamic. Several areas of Space Shuttle technology were addressed including aerothermal environment, thermal protection, measurement and analysis, Shuttle carrier aerodynamics, entry analysis of the STS Findings The real flight data of longitudinal and lateral-directional motion have been considered to estimate their respective aerodynamic parameters using the proposed methodology.
An illustration of an open book. Books. An illustration of two cells of a film strip. Video. An illustration of an audio speaker. Audio. An illustration of a " floppy disk. Software. An illustration of two photographs. Full text of "Aerodynamic design data book.
Volume 1M: Orbiter vehicle STS-1". A six-degree-of-freedom simulation analysis was conducted to examine the effects of longitudinal static aerodynamic stability and control uncertainties on the performance of the space shuttle.
The paper presents a method to identify aerodynamic parameters from flight-test data, determine the uncertainty in the identified parameters, and estimate the model-form uncertainties in the aerodynamic model.
This information is required for simulations designed to estimate the reliability of the system. Abstract. This chapter studies the effects of the body roll on vehicle handling dynamics.
Following the explanations of the roll mechanism, the possible effects of roll stiffness, transversal load transfer, camber change, roll steer, and suspension lateral compliance on the steady state handling characteristics of the vehicle are examined.
Steel structure. For the structure, steel cables are assumed to be formed into longerons (average thickness Δr L) and circular bands (average thickness Δr B). The value of Δr L required is.
Δr L = Rρ o /2T. where R is the cylinder radius, ρ o the atmospheric pressure and T the tension. For land density ρ L and depth x L, and bands of density ρ F, the total equivalent internal pressure. Several ways for obtaining aerodynamic parameters of an aircraft from flight data are presented with the emphasis on present problem areas.
The paper starts with a brief description of data analysis from steady measurements. Then, a concept of system identification applied to aircraft is introduced with a discussion of various steps in this.
Design example: Space Shuttle. The Space Shuttle thermal protection system was based on the use of surface materials with a high temperature capability, in combination with an underlying thermal insulation to reduce heat conduction to the interior of the vehicle.
The heat from the aerodynamic heating was thereby radiated back into space. predictive capability. Ordinary least-squares parameter estimation is used to identify model parameters. This method has been successfully applied in several applications using ight-test data.8,9 10 This modeling method currently must be applied to each aircraft to determine the appropriate model structure and parameter estimates.
Aerodynamic parameter estimation from flight data applying extended and unscented Kalman filter. Effect of longitudinal input on lateral rotor flapping angle. B.K. Walker, On-line implementation of nonlinear parameter estimation for the space shuttle main.
aerodynamic input parameters from rocketry and engineering literature. In some cases equa-tions are semi-empirical, that is they use relationships that have been ﬁtted to data from experiments using rockets of a standard shape.
In general, these equations are only applicable 1.Parameter Identification: Maximum Likelihood Conclusions Notes on the Validation Procedures Modelling Errors 5 Conclusions Parameter Identification Data Compatibility Flight Testing For Aerodynamic Parameter Identification Concluding Remarks 6 References Several concepts were analyzed for the FTB-X test bed.
The last configuration proposed at the end of the trade-off design activities, namely FTB-X_FW50, is shown in Fig. trade-off configuration analysis has been performed adopting a homogeneous set of independent parameters, evolving from the baseline configuration of FTB-1, which is the first flying test bed of the CIRA USV .