Author: Brent R. Cobleigh
Publisher:
ISBN:
Category : Aeronautical instruments
Languages : en
Pages : 34
Get Book Here
Book Description
Blunt-forebody pressure data are used to study the behavior of the NASA Dryden Flight Research Center flush airdata sensing (FADS) pressure model and solution algorithm. The model relates surface pressure measurements to the airdata state. Spliced from the potential flow solution for uniform flow over a sphere and the modified Newtonian impact theory, the model was shown to apply to a wide range of blunt-forebody shapes and Mach numbers. Calibrations of a sphere, spherical cones, a Rankine half body, and the F-14, F/A-18, X-33, X-34, and X-38 configurations are shown. The three calibration parameters are well-behaved from Mach 0.25 to Mach 5.0, an angle-of-attack range extending to greater than 30 deg., and an angle-of-sideslip range extending to greater than 15 deg. Contrary to the sharp calibration changes found on traditional pitot-static systems at transonic speeds, the FADS calibrations are smooth, monotonic functions of Mach number and effective angles of attack and sideslip. Because the FADS calibration is sensitive to pressure port location, detailed measurements of the actual pressure port locations on the flight vehicle are required and the wind-tunnel calibration model should have pressure ports in similar locations. The procedure for calibrating a FADS system is outlined.
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781720527091
Category :
Languages : en
Pages : 32
Get Book Here
Book Description
Blunt-forebody pressure data are used to study the behavior of the NASA Dryden Flight Research Center flush airdata sensing (FADS) pressure model and solution algorithm. The model relates surface pressure measurements to the airdata state. Spliced from the potential flow solution for uniform flow over a sphere and the modified Newtonian impact theory, the model was shown to apply to a wide range of blunt-forebody shapes and Mach numbers. Calibrations of a sphere, spherical cones, a Rankine half body, and the F-14, F/A-18, X-33, X-34, and X-38 configurations are shown. The three calibration parameters are well-behaved from Mach 0.25 to Mach 5.0, an angle-of-attack range extending to greater than 30 deg, and an angle-of-sideslip range extending to greater than 15 deg. Contrary to the sharp calibration changes found on traditional pitot-static systems at transonic speeds, the FADS calibrations are smooth, monotonic functions of Mach number and effective angles of attack and sideslip. Because the FADS calibration is sensitive to pressure port location, detailed measurements of the actual pressure port locations on the flight vehicle are required and the wind-tunnel calibration model should have pressure ports in similar locations. The procedure for calibrating a FADS system is outlined.Cobleigh, Brent R. and Whitmore, Stephen A. and Haering, Edward A., Jr. and Borrer, Jerry and Roback, V. EricArmstrong Flight Research Center; Johnson Space Center; Langley Research CenterPROCEDURES; CALIBRATING; FOREBODIES; MATHEMATICAL MODELS; ALGORITHMS; POTENTIAL FLOW; PRESSURE MEASUREMENT; NEWTON THEORY; ANGLE OF ATTACK; DETECTION; F-14 AIRCRAFT; MACH NUMBER; POSITION (LOCATION); SENSITIVITY; SHAPES; SIDESLIP; SPHERES; TRANSONIC SPEED; UNIFORM FLOW; WIND TUNNEL CALIBRATION; X-33 REUSABLE LAUNCH VEHICLE; X-34 REUSABLE LAUNCH VEHICLE; X-38 CREW RETURN VEHICLE
Author: Ihab Samy
Publisher: Springer
ISBN: 3642240526
Category : Technology & Engineering
Languages : en
Pages : 185
Get Book Here
Book Description
This book considers two popular topics: fault detection and isolation (FDI) and flight data estimation using flush air data sensing (FADS) systems. Literature surveys, comparison tests, simulations and wind tunnel tests are performed. In both cases, a UAV platform is considered for demonstration purposes. In the first part of the book, FDI is considered for sensor faults where a neural network approach is implemented. FDI is applied both in academia and industry resulting in many publications over the past 50 years or so. However few publications consider neural networks in comparison to traditional techniques such as observer based, parameter estimations and parity space approaches. The second part of this book focuses on how to estimate flight data (angle of attack, airspeed) using a matrix of pressure sensors and a neural network model. In conclusion this book can serve as an introduction to FDI and FADS systems, a literature survey, and a case study for UAV applications.
Author: Min Zhao
Publisher: Springer Nature
ISBN: 9813365269
Category : Technology & Engineering
Languages : en
Pages : 257
Get Book Here
Book Description
This book provides an overview of advanced prediction and verification technologies for aerodynamics and aerothermodynamics and assesses a number of critical issues in advanced hypersonic vehicle design. Focusing on state-of-the-art theories and promising technologies for engineering applications, it also presents a range of representative practical test cases. Given its scope, the book offers a valuable asset for researchers who are interested in thermodynamics, aircraft design, wind tunnel testing, fluid dynamics and aerothermodynamics research methods, introducing them to inspiring new research topics.
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 648
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 74
Get Book Here
Book Description
Author: Masashi Mizukami
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 122
Get Book Here
Book Description
A flat plate and faired pod have been mounted on a NASA SR-71A aircraft for use as a supersonic flight experiment test bed. A test article can be placed on the flat plate; the pod can contain supporting systems. A series of test flights has been conducted to validate this test bed configuration. Flight speeds to a maximum of Mach 3.0 have been attained. Steady-state sideslip maneuvers to a maximum of 2° have been conducted, and the flow field in the test region has been surveyed. Two total-pressure rakes, each with two flow-angle probes, have been placed in the expected vicinity of an experiment. Static-pressure measurements have been made on the flat plate. At subsonic and low supersonic speeds with no sideslip, the flow in the surveyed region is quite uniform. During sideslip maneuvers, localized flow distortions impinge on the test region. Aircraft sideslip does not produce a uniform sidewash over the test region. At speeds faster than Mach 1.5, variable-pressure distortions were observed in the test region. Boundary-layer thickness on the flat plate at the rake was less than 2.1 in. For future experiments, a more focused and detailed flow-field survey than this one would be desirable.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 974
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 712
Get Book Here
Book Description
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1460
Get Book Here
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
