Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Validation Of A Real Time Engineering Simulation Of The Uh 60a Helicopter PDF full book. Access full book title Validation Of A Real Time Engineering Simulation Of The Uh 60a Helicopter.
| Author | : Mark G. Ballin |
| Publisher | : |
| Total Pages | : 208 |
| Release | : 1987 |
| Genre | : |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 98 |
| Release | : 2001 |
| Genre | : |
| ISBN | : |
Helicopter slung-load operations are common in both military and civil contexts. Helicopters and loads are often qualified for these operations by means of flight tests, which can be expensive and time consuming. There is significant potential to reduce such costs both through revisions in flight-test methods and by using validated simulation models. To these ends, flight tests were conducted at Moffett Field to demonstrate the identification of key dynamic parameters during flight tests (aircraft stability margins and handling-qualities parameters, and load pendulum stability), and to accumulate a data base for simulation development and validation. The test aircraft was a UH-60A Black Hawk, and the primary test load was an instrumented 8- by 6- by 6-ft cargo container. Tests were focused on the lateral and longitudinal axes, which are the axes most affected by the load pendulum modes in the frequency range of interest for handling qualities; tests were conducted at airspeeds from hover to 80 knots. Using telemetered data, the dynamic parameters were evaluated in near real time after each test airspeed and before clearing the aircraft to the next test point. These computations were completed in under 1 min. A simulation model was implemented by integrating an advanced model of the UH-60A aerodynamics, dynamic equations for the two-body slung-load system, and load static aerodynamics obtained from wind-tunnel measurements. Comparisons with flight data for the helicopter alone and with a slung load showed good overall agreement for all parameters and test points; however, unmodeled secondary dynamic losses around 2 Hz were found in the helicopter model and they resulted in conservative stability margin estimates.
| Author | : David L. Key |
| Publisher | : |
| Total Pages | : 20 |
| Release | : 1982 |
| Genre | : |
| ISBN | : |
The paper describes a joint NASA/Army effort to perform a systematic ground-based piloted simulation validation assessment. The best available mathematical model for the subject helicopter (UH-60A Black Hawk) was programmed for real-time operation. Flight data were obtained to validate the math model, and to develop models for the pilot control strategy while performing mission-type tasks. The validated mathe model will be combined with motion and visual systems to perform ground based simulation during April of 1983. Comparisons of the control strategy obtained in flight with that obtained on the simulator will be used as the basis for assessing the fidelity of the results obtained in the simulator. (Author).
| Author | : Allen H. McCoy |
| Publisher | : |
| Total Pages | : 96 |
| Release | : 1997-12 |
| Genre | : Science |
| ISBN | : |
Historically, helicopter and load combinations have been qualified through flight testing, requiring considerable time and cost. With advancements in simulation and flight test techniques, there is potential to substantially reduce costs and increase the safety of helicopter sling load certification. Validated simulation tools make possible accurate prediction of operational flight characteristics before initial flight tests. Real time analysis of test data improves the safety and efficiency of the testing programs. To advance these concepts, the US Army and NASA, in cooperation with the Israeli Air Force and Technion, under a Memorandum of Agreement, seek to develop and validate a numerical model of the UH-60 with sling load and demonstrate a method of near real time flight test analysis. This thesis presents results from flight tests of a US Army Black Hawk helicopter with various external loads. Tests were conducted as the US first phase of this MOA task. The primary load was a container express box (CONEX), which contained a compact instrumentation package. The flights covered the airspeed range from hover to 70 knots. Primary maneuvers were pitch and roll frequency sweeps, steps, and doublets. Results of the test determined the effect of the suspended load on both the aircraft's handling qualities and it's control system's stability margins. Included were calculations of the stability characteristics of the load's pendular motion. Utilizing CIFER software, a method for near-real time system identification was also demonstrated during the flight test program.
| Author | : Peter H. Tyson |
| Publisher | : |
| Total Pages | : 303 |
| Release | : 1999-03-01 |
| Genre | : |
| ISBN | : 9781423545231 |
Helicopter/slung load systems are two body systems in which the slung load adds its rigid body dynamics, aerodynamics, and sling stretching dynamics to the helicopter. The slung load can degrade helicopter handling qualities and reduce the flight envelope of the helicopter. Confirmation of system stability parameters and envelope is desired, but flight test evaluation is time consuming and costly. A simulation model validated for handling quality assessments would significantly reduce resources expended in flight testing while increasing efficiency, productivity, and safety by aiding researchers, designers, and pilots to understand factors affecting helicopter-slung load handling qualities. This thesis describes a comprehensive dynamics and aerodynamics model for slung load simulation, obtained by integrating the NASA Ames Gen Hel UH-60A simulation with slung load equations of motion. Frequency domain analysis is used to compare simulation to flight test frequency responses and key system stability parameters. Results are given for no load, a 4K lb Block, and a 4K lb CONEX load. Handling quality parameters, stability margins, and load pendulum motion roots for cases without load aerodynamics and with static wind tunnel data were compared. Results illustrated state-of-the-art simulation modeling of helicopter/slung load dynamics and its accuracy in predicting key dynamic parameters of interest.
| Author | : |
| Publisher | : |
| Total Pages | : 127 |
| Release | : 1982 |
| Genre | : |
| ISBN | : |
The United States Army Aviation Engineering Flight Activity (USAAEFA) conducted flight tests of the UH-60A helicopter for the Aeromechanics Laboratory (AL)of the US Army Aviation Research and Technology Laboratories to obtain data for validation of a simulator. A test program of sixty-nine flights totaling 97.4 tests hours was flown to provide AL with extensive handling qualities data. In addition to standard handling qualities tests, special system identification maneuvers were flown. Summary results of those tests are contained in this report.
| Author | : |
| Publisher | : |
| Total Pages | : 326 |
| Release | : 1993 |
| Genre | : |
| ISBN | : |
| Author | : National Aeronautics and Space Administration (NASA) |
| Publisher | : Createspace Independent Publishing Platform |
| Total Pages | : 26 |
| Release | : 2018-07-03 |
| Genre | : |
| ISBN | : 9781722242022 |
This paper describes a flight test demonstration of a system for identification of the stability and handling qualities parameters of a helicopter-slung load configuration simultaneously with flight testing, and the results obtained.Tests were conducted with a UH-60A Black Hawk at speeds from hover to 80 kts. The principal test load was an instrumented 8 x 6 x 6 ft cargo container. The identification used frequency domain analysis in the frequency range to 2 Hz, and focussed on the longitudinal and lateral control axes since these are the axes most affected by the load pendulum modes in the frequency range of interest for handling qualities. Results were computed for stability margins, handling qualities parameters and load pendulum stability. The computations took an average of 4 minutes before clearing the aircraft to the next test point. Important reductions in handling qualities were computed in some cases, depending, on control axis and load-slung combination. A database, including load dynamics measurements, was accumulated for subsequent simulation development and validation. Cicolani, Luigi S. and McCoy, Allen H. and Tischler, Mark B. and Tucker, George E. and Gatenio, Pinhas and Marmar, Dani Ames Research Center RTOP 581-30-22...
| Author | : Rui Wang |
| Publisher | : Springer Nature |
| Total Pages | : 1340 |
| Release | : 2019-12-03 |
| Genre | : Technology & Engineering |
| ISBN | : 9811504741 |
This book includes original, peer-reviewed research papers from the 11th International Conference on Modelling, Identification and Control (ICMIC2019), held in Tianjin, China on July 13-15, 2019. The topics covered include but are not limited to: System Identification, Linear/Nonlinear Control Systems, Data-driven Modelling and Control, Process Modelling and Process Control, Fault Diagnosis and Reliable Control, Intelligent Systems, and Machine Learning and Artificial Intelligence.The papers showcased here share the latest findings on methodologies, algorithms and applications in modelling, identification, and control, integrated with Artificial Intelligence (AI), making the book a valuable asset for researchers, engineers, and university students alike.
| Author | : Robert L. Barrie |
| Publisher | : |
| Total Pages | : 158 |
| Release | : 1999-12-01 |
| Genre | : |
| ISBN | : 9781423540335 |
Helicopter design at the Sikorsky Aircraft Corporation is aided by the use of the Sikorsky General Helicopter (GenHel(registered)) Flight Dynamics Simulation Model. Specifically, GenHel output is used by both handling qualities and maneuver loads engineers as a predictive design tool. Inherent in the use of an analytical model is the requirement for validation. This report seeks to validate the GenHel(registered) flight dynamics simulation models used in the design of the UH-60L Wide Chord Blade (WCB) modification. initially comparisons are made between the current analytical models and flight test data for selected trim flight conditions and dynamic maneuvers. Based on the correlation of the data, modifications are made to the analytical model where necessary. The modified analytical model will be validated through a final comparison with test flight data. The goal of this report is to validate the use of Sikorsky's GenHel(registered) flight simulation program as an analytic predictive tool in the design of the WCB modification and identify any areas where improvements could be applied. Validation of the WCB GenHel model serves two purposes. First it confirms the ability of GenHel to model the flight dynamic response of the UH-60L with the WCB modification. Second it confirms the predictive loads forwarded to the structural engineers during the design phase of the WCB.
