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Flight Stability And Control And Performance Results From The Linear Aerospike Sr 71 Experiment Lasre Nasa Tm 1998 206565 Oct 26 1998
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Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722240714 Total Pages :30 pages Book Rating :4.2/5 (47 download)
Book Synopsis Flight Stability and Control and Performance Results from the Linear Aerospike Sr-71 Experiment (Lasre) by : National Aeronautics and Space Administration (NASA)
Download or read book Flight Stability and Control and Performance Results from the Linear Aerospike Sr-71 Experiment (Lasre) written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-03 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Linear Aerospike SR-71 Experiment (LASRE) is presently being conducted to test a 20-percent-scale version of the Linear Aerospike rocket engine. This rocket engine has been chosen to power the X-33 Single Stage to Orbit Technology Demonstrator Vehicle. The rocket engine was integrated into a lifting body configuration and mounted to the upper surface of an SR-71 aircraft. This paper presents stability and control results and performance results from the envelope expansion flight tests of the LASRE configuration up to Mach 1.8 and compares the results with wind tunnel predictions. Longitudinal stability and elevator control effectiveness were well-predicted from wind tunnel tests. Zero-lift pitching moment was mispredicted transonically. Directional stability, dihedral stability, and rudder effectiveness were overpredicted. The SR-71 handling qualities were never significantly impacted as a result of the missed predictions. Performance results confirmed the large amount of wind-tunnel-predicted transonic drag for the LASRE configuration. This drag increase made the performance of the vehicle so poor that acceleration through transonic Mach numbers could not be achieved on a hot day without depleting the available fuel. Moes, Timothy R. and Cobleigh, Brent R. and Cox, Timothy H. and Conners, Timothy R. and Iliff, Kenneth W. and Powers, Bruce G. Armstrong Flight Research Center RTOP 244-33-02...
Book Synopsis Flight Testing the Linear Aerospike SR-71 Experiment (LASRE) by : Stephen Corda
Download or read book Flight Testing the Linear Aerospike SR-71 Experiment (LASRE) written by Stephen Corda and published by . This book was released on 1998 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: The design of the next generation of space access vehicles has led to a unique flight test that blends the space and flight research worlds. The new vehicle designs, such as the X-33 vehicle and Reusable Launch Vehicle (RLV) are powered by linear aerospike rocket engines. Conceived of in the 1960's, these aerospike engines have yet to be flown, and many questions remain regarding aerospike engine performance and efficiency in flight. To provide some of these data before flying on the X-33 vehicle and the RLV, a spacecraft rocket engine had been flight-tested atop the NASA SR-71 aircraft as the Linear Aerospike SR-71 Experiment (LASRE). A 20 percent-scale, semispan model of the X-33 vehicle, the aerospike engine, and all the required fuel and oxidizer tanks and propellant feed systems have been mounted atop the SR-71 airplane for this experiment. A major technical objective of the LASRE flight test is to obtain installed-engine performance flight data for comparison to wind-tunnel results and for the development of computational fluid dynamics-based design methodologies. The ultimate goal of firing the aerospike rocket engine in flight is still forthcoming. An extensive design and development phase of the experiment hardware has been completed, including approximately 40 ground tests. Five flights of the LASRE and firing the rocket engine using inert liquid nitrogen and helium in place of liquid oxygen and hydrogen have been successfully completed.
Book Synopsis Stability and Control Estimation Flight Test Results for the SR-71 Aircraft With Externally Mounted Experiments by : Timothy R. Moes
Download or read book Stability and Control Estimation Flight Test Results for the SR-71 Aircraft With Externally Mounted Experiments written by Timothy R. Moes and published by . This book was released on 2002 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt: A maximum-likelihood output-error parameter estimation technique is used to obtain stability and control derivatives for the NASA Dryden Flight Research Center SR-71A airplane and for configurations that include experiments externally mounted to the top of the fuselage. This research is being done as part of the envelope clearance for the new experiment configurations. Flight data are obtained at speeds ranging from Mach 0.4 to Mach 3.0, with an extensive amount of test points at approximately Mach 1.0. Pilot-input pitch and yaw-roll doublets are used to obtain the data. This report defines the parameter estimation technique used, presents stability and control derivative results, and compares the derivatives for the three configurations tested. The experimental configurations studied generally show acceptable stability, control, trim, and handling qualities throughout the Mach regimes tested.
Book Synopsis The SR-71 Test Bed Aircraft: A Facility for High-Speed Flight Research by : Stephen Corda
Download or read book The SR-71 Test Bed Aircraft: A Facility for High-Speed Flight Research written by Stephen Corda and published by . This book was released on 2000 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: The SR-71 test bed aircraft is shown to be a unique platform to flight-test large experiments to supersonic Mach numbers. The test bed hardware mounted on the SR-71 upper fuselage is described. This test bed hardware is composed of a fairing structure called the "canoe" and a large "reflection plane" flat plate for mounting experiments. Total experiment weights, including the canoe and reflection plane, as heavy as 14,500 lb can be mounted on the aircraft and flight-tested to speeds as fast as Mach 3.2 and altitudes as high as 80,000 ft. A brief description of the SR-71 aircraft is given, including details of the structural modifications to the fuselage, modifications to the J58 engines to provide increased thrust, and the addition of a research instrumentation system. Information is presented based on flight data that describes the SR-71 test bed aerodynamics, stability and control, structural and thermal loads, the canoe internal environment, and reflection plane flow quality. Guidelines for designing SR-71 test bed experiments are also provided.
Book Synopsis The Northeast Missouri Soil Health Guide by :
Download or read book The Northeast Missouri Soil Health Guide written by and published by . This book was released on 1999 with total page 59 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721002733 Total Pages :96 pages Book Rating :4.0/5 (27 download)
Book Synopsis Stability and Control Estimation Flight Test Results for the Sr-71 Aircraft with Externally Mounted Experiments by : National Aeronautics and Space Administration (NASA)
Download or read book Stability and Control Estimation Flight Test Results for the Sr-71 Aircraft with Externally Mounted Experiments written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-11 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt: A maximum-likelihood output-error parameter estimation technique is used to obtain stability and control derivatives for the NASA Dryden Flight Research Center SR-71A airplane and for configurations that include experiments externally mounted to the top of the fuselage. This research is being done as part of the envelope clearance for the new experiment configurations. Flight data are obtained at speeds ranging from Mach 0.4 to Mach 3.0, with an extensive amount of test points at approximately Mach 1.0. Pilot-input pitch and yaw-roll doublets are used to obtain the data. This report defines the parameter estimation technique used, presents stability and control derivative results, and compares the derivatives for the three configurations tested. The experimental configurations studied generally show acceptable stability, control, trim, and handling qualities throughout the Mach regimes tested. The reduction of directional stability for the experimental configurations is the most significant aerodynamic effect measured and identified as a design constraint for future experimental configurations. This report also shows the significant effects of aircraft flexibility on the stability and control derivatives.Moes, Timothy R. and Iliff, KennethArmstrong Flight Research CenterCONTROLLABILITY; SR-71 AIRCRAFT; MAXIMUM LIKELIHOOD ESTIMATES; DIRECTIONAL STABILITY; AIRCRAFT STABILITY; SUBSONIC SPEED; YAW; MACH NUMBER; ERROR ANALYSIS; AERODYNAMICS
Book Synopsis Your Guide for the American Community Survey by :
Download or read book Your Guide for the American Community Survey written by and published by . This book was released on 2002 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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Download or read book 1997 Census of Agriculture written by and published by . This book was released on 1999 with total page 320 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Income Tax Treatment of Cooperatives: Patronage refunds by : Donald A. Frederick
Download or read book Income Tax Treatment of Cooperatives: Patronage refunds written by Donald A. Frederick and published by . This book was released on 1993 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Ricky Ray Hemophilia Relief Fund Act of 1998 by : United States
Download or read book Ricky Ray Hemophilia Relief Fund Act of 1998 written by United States and published by . This book was released on 1998 with total page 8 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Quick Bibliography Series by : National Agricultural Library (U.S.). Reference Division
Download or read book Quick Bibliography Series written by National Agricultural Library (U.S.). Reference Division and published by . This book was released on 1978 with total page 818 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781725570887 Total Pages :30 pages Book Rating :4.5/5 (78 download)
Book Synopsis Closed-Loop System Identification Experience for Flight Control Law and Flying Qualities Evaluation of a High Performance Fighter Aircraft by : National Aeronautics and Space Administration (NASA)
Download or read book Closed-Loop System Identification Experience for Flight Control Law and Flying Qualities Evaluation of a High Performance Fighter Aircraft written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-16 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper highlights some of the results and issues associated with estimating models to evaluate control law design methods and design criteria for advanced high performance aircraft. Experimental fighter aircraft such as the NASA-High Alpha Research Vehicle (HARV) have the capability to maneuver at very high angles of attack where nonlinear aerodynamics often predominate. HARV is an experimental F/A-18, configured with thrust vectoring and conformal actuated nose strakes. Identifying closed-loop models for this type of aircraft can be made difficult by nonlinearities and high order characteristics of the system. In this paper, only lateral-directional axes are considered since the lateral-directional control law was specifically designed to produce classical airplane responses normally expected with low-order, rigid-body systems. Evaluation of the control design methodology was made using low-order equivalent systems determined from flight and simulation. This allowed comparison of the closed-loop rigid-body dynamics achieved in flight with that designed in simulation. In flight, the On Board Excitation System was used to apply optimal inputs to lateral stick and pedals at five angles at attack : 5, 20, 30, 45, and 60 degrees. Data analysis and closed-loop model identification were done using frequency domain maximum likelihood. The structure of identified models was a linear state-space model reflecting classical 4th-order airplane dynamics. Input time delays associated with the high-order controller and aircraft system were accounted for in data preprocessing. A comparison of flight estimated models with small perturbation linear design models highlighted nonlinearities in the system and indicated that the closed-loop rigid-body dynamics were sensitive to input amplitudes at 20 and 30 degrees angle of attack. Murphy, Patrick C. Langley Research Center NASA/TM-1998-207995, NAS 1.15:207995 ...
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721024360 Total Pages :38 pages Book Rating :4.0/5 (243 download)
Book Synopsis The Sr-71 Test Bed Aircraft by : National Aeronautics and Space Administration (NASA)
Download or read book The Sr-71 Test Bed Aircraft written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-11 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: The SR-71 test bed aircraft is shown to be a unique platform to flight-test large experiments to supersonic Mach numbers. The test bed hardware mounted on the SR-71 upper fuselage is described. This test bed hardware is composed of a fairing structure called the "canoe" and a large "reflection plane" flat plate for mounting experiments. Total experiment weights, including the canoe and reflection plane, as heavy as 14,500 lb can be mounted on the aircraft and flight-tested to speeds as fast as Mach 3.2 and altitudes as high as 80,000 ft. A brief description of the SR-71 aircraft is given, including details of the structural modifications to the fuselage, modifications to the J58 engines to provide increased thrust, and the addition of a research instrumentation system. Information is presented based on flight data that describes the SR-71 test bed aerodynamics, stability and control, structural and thermal loads, the canoe internal environment, and reflection plane flow quality. Guidelines for designing SR-71 test bed experiments are also provided.Corda, Stephen and Moes, Timothy R. and Mizukami, Masashi and Hass, Neal E. and Jones, Daniel and Monaghan, Richard C. and Ray, Ronald J. and Jarvis, Michele L. and Palumbo, NathanArmstrong Flight Research CenterSR-71 AIRCRAFT; FLIGHT TESTS; AERODYNAMIC STABILITY; TEST STANDS; FUSELAGES; STRUCTURAL DESIGN; SUPERSONIC SPEED; LOADS (FORCES); FAIRINGS; MACH NUMBER
Book Synopsis The Mulberry Empire by : Philip Hensher
Download or read book The Mulberry Empire written by Philip Hensher and published by HarperCollins UK. This book was released on 2016-08-25 with total page 548 pages. Available in PDF, EPUB and Kindle. Book excerpt: The bestselling novel from the Man Booker Prize shortlisted author of The Northern Clemency and King of the Badgers.
Book Synopsis Flight Test Results from the NF-15B Intelligent Flight Control System (IFCS) Project with Adaptation to a Simulated Stabilator Failure by : National Aeronaut Administration (Nasa)
Download or read book Flight Test Results from the NF-15B Intelligent Flight Control System (IFCS) Project with Adaptation to a Simulated Stabilator Failure written by National Aeronaut Administration (Nasa) and published by . This book was released on 2020-08-05 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Adaptive flight control systems have the potential to be more resilient to extreme changes in airplane behavior. Extreme changes could be a result of a system failure or of damage to the airplane. A direct adaptive neural-network-based flight control system was developed for the National Aeronautics and Space Administration NF-15B Intelligent Flight Control System airplane and subjected to an inflight simulation of a failed (frozen) (unmovable) stabilator. Formation flight handling qualities evaluations were performed with and without neural network adaptation. The results of these flight tests are presented. Comparison with simulation predictions and analysis of the performance of the adaptation system are discussed. The performance of the adaptation system is assessed in terms of its ability to decouple the roll and pitch response and reestablish good onboard model tracking. Flight evaluation with the simulated stabilator failure and adaptation engaged showed that there was generally improvement in the pitch response; however, a tendency for roll pilot-induced oscillation was experienced. A detailed discussion of the cause of the mixed results is presented. Bosworth, John T. and Williams-Hayes, Peggy S. Armstrong Flight Research Center NASA/TM-2007-214629, H-2751, AIAA-2007-2818 ADAPTIVE CONTROL; FLIGHT CONTROL; NEURAL NETS; FORMATION FLYING; AIRCRAFT STABILITY; STABILITY TESTS; ADAPTATION; ROLL; SYSTEM FAILURES; FLIGHT SIMULATION; STABILIZERS; FLIGHT TEST VEHICLES
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721093229 Total Pages :120 pages Book Rating :4.0/5 (932 download)
Book Synopsis Flow-Field Survey in the Test Region of the Sr-71 Aircraft Test Bed Configuration by : National Aeronautics and Space Administration (NASA)
Download or read book Flow-Field Survey in the Test Region of the Sr-71 Aircraft Test Bed Configuration written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-13 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 deg 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. Mizukami, Masashi and Jones, Daniel and Weinstock, Vladimir D. Armstrong Flight Research Center RTOP 523-90-24
