Download or read book Handling Qualities Evaluation of the OH 58A Helicopter Incorporating the Model 570B Three axis Stability and Control Augumentation System written by Raymond B. Smith and published by . This book was released on 1973 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt: A limited handling qualities evaluation of the OH-58A helicopter with a Bell Helicopter Model 570B three-axis stability and control augmentation system installed was conducted to determine its capability to perform instrument flight. Testing was performed by the US Army Aviation Systems Test Activity at Edwards Air Force Base, California. The testing consisted of 25 productive flight hours and was conducted from September through November 1972. The evaluation revealed significant improvements in the aircraft handling qualities with the addition of the augmentation system. The most significant enhancing characteristics provided by the equipment were: (1) increased damping of the lateral-directional oscillation (Dutch roll), (2) improvement of aircraft spiral stability from neutral to convergent, and (3) reduction in pilot effort required to maintain trim flight conditions. This evaluation was of limited scope, and primarily addressed handling qualities. It did not provide a basis to qualify the aircraft for instrument flight.

Download or read book Handling Qualities Evaluation OH 58A Helicopter Incorporating a Ministab 3 axis Stability Augmentation System written by Edward E. Bailes and published by . This book was released on 1975 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: A limited handling qualities evaluation of the OH-58A helicopter incorporating the SFENA 3-axis stability augmentation system called Ministab was performed by the United States Army Aviation Engineering Flight Activity at Edwards Air Force Base, California. The system identified as the SFENA Ministab stability augmentation system was manufactured by the Societe Francaise d'Equipements pour la Navigation Aerienne (SFENA) of France and made available for test by Kaiser Aerospace and Electronics Corporation of Palo Alto, California, who also installed and maintained the system during testing. The testing consisted of 11.2 productive flight hours and was conducted from 20 July through 24 August 1974. This evaluation was of limited scope and consisted of both quantitative data and qualitative pilot comments. The test results show significant improvements in the aircraft handling qualities with the addition of Ministab.

Download or read book Preliminary Airworthiness Evaluation OH 58C Helicopter Configured with a Mast Mounted Sight written by and published by . This book was released on 1980 with total page 77 pages. Available in PDF, EPUB and Kindle. Book excerpt: The United States Army Aviation Engineering Flight Activity conducted a preliminary airworthiness evaluation of the OH-58C helicopter with a mast mounted sight and Bell Helicopter, Textron Model 570B three-axis stability and control augmentation system. The evaluation was completed in two phases at the Bell Helicopter Engineering Flight Research Center, Arlington, Texas (elevation 630 ft). Phase 1 consisted of an evaluation of a dummy mast mounted sight installed on an instrumented helicopter. This phase was conducted between 15 and 30 October 1980 and 12 flights were flown for a total of 9.7 productive hours. Phase 2 consisted of a qualitative assessment of the handling qualities of the OH-58C configured with the operational Rockwell International sight. This phase was completed on 30 November 1980 in two flights for 1.5 productive test flight hours. The overall evaluation indicated that the OH-58C handling qualities with installed mast mounted sight and three-axis SCAS were satisfactory within the flight envelope tested. No problems were noted that will prevent future operational testing of the system. The addition of a three-axis SCAS significantly improved the OH-58C handling qualities, particularly in low speed flight, and is an enhancing characteristic.

Download or read book Preliminary Airworthiness Evaluation of the OH 58C with 3 Axis Stability Control Augmentation System and Improved Tail Rotor System written by M. L. Hanks and published by . This book was released on 1983 with total page 177 pages. Available in PDF, EPUB and Kindle. Book excerpt: This preliminary airworthiness evaluation was conducted on an OH-58C helicopter configured with a 3-axis digital stability control augmentation system (SCAS) and an improved tail rotor. Additional testing on the standard OH-58C equipped with the 3-axis SCAS was required in response to questions which surfaced during working sessions of the Joint Special Study Group investigating 0H-58 loss of tail rotor effectiveness. Testing was accomplished at Arlington, TX (elevation 630 feet), Leadville, CO (elev. 9927 feet) and Alamosa, CO (elev. 7535 feet). Test time totaled 44.2 productive flight test hours. With the improved tail rotor, adequate directional control margins were available for flight at all azimuths out to the wind limits (35 KTAS sideward and 30 KTAS rearward) of the aircraft at density altitudes up through 11,000 feet for a gross weight of 3,040 lb. The overall handling qualities of the OH-58C helicopter equipped with a 3-axis digital SCAS in either tail rotor configuration were significantly improved over the unaugmented aircraft configuration except as stated in the report. TWo handling quality deficiencies were noted.

Download or read book A Collection of Technical Papers written by and published by . This book was released on with total page 840 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Airworthiness and Flight Characteristics Test Production OH 58A Helicopter Unarmed and Armed with XM27E1 Armament Subsystem Stability and Control written by William A Graham (Jr) and published by . This book was released on 1970 with total page 162 pages. Available in PDF, EPUB and Kindle. Book excerpt: Stability and control tests were conducted on a production model OH- 58A helicopter to evaluate its flying qualities in the unarmed configuration and in an armed configuration with the XM27E1 weapon system. Limited testing was also performed to evaluate the helicopter slope landing capabilities and flying qualities with skis installed. Human factors and maintainability characteristics were noted throughout the evaluation. The testing consisted of 89 flights which totaled 85.3 hours of productive flight testing. Maintainability of the helicopter was excellent throughout the test program.

Download or read book A Pilot s Assessment of Helicopter Handling quality Factors Common to Both Agility and Instrument Flying Tasks written by and published by . This book was released on 1980 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Evaluation of the OH 58A Helicopter with an Allison 250 C20 Engine written by Emmett J. Laing and published by . This book was released on 1972 with total page 49 pages. Available in PDF, EPUB and Kindle. Book excerpt: The United States Army Aviation Systems Test Activity conducted a limited performance and handling qualities evaluation of the Bell Helicopter Company model OH-58A helicopter with an Allison 250-C20 engine installed. Twenty-five flights, 21.2 productive test hours, were required for the evaluation. Test results obtained with the Allison 250-C20 engine were compared with those previously obtained with the standard T63-A-700 engine. The primary performance improvement noted was an increase in out-of-ground-effect hover ceiling at a 3000-lb gross weight to 10,000 ft from 4600 ft. The long-range cruise airspeed was increased to 111 knots true airspeed from 104 knots true airspeed at a 5000-ft density altitude and a 3000-lb gross weight. The increased engine power did not significantly increase the service ceiling over the basic OH-58A at identical gross weights. One shortcoming, insufficient left directional control at 35 knots true airspeed in right sideward flight, was noted. Within the scope of the test, the performance of the OH-58A helicopter with the Allison 250-C20 engine was improved over the basic OH-58A helicopter. Handling qualities were essentially unchanged. (Author).

Download or read book Helicopter Test and Evaluation written by Alastair Cooke and published by John Wiley & Sons. This book was released on 2009-02-12 with total page 384 pages. Available in PDF, EPUB and Kindle. Book excerpt: Although a number of texts on helicopter aerodynamics have been written, few have explained how the various theories concerning rotorborne flight underpin practical flight test and evaluation. This book combines theoretical information on aerodynamics, stability, control and performance with details of evaluation methodologies and practical guidance on the conduct of helicopter flight tests. For each topic the relevant theory is explained briefly and followed by details of the practical aspects of testing a conventional helicopter. These include: * safety considerations * planning the tests * the most efficient way to conduct individual flights Where possible typical test results are presented and discussed. The book draws on the authors' extensive experience in flight test and flight test training and will appeal not only to professionals working in the area of rotorcraft test and evaluation, but also to helicopter pilots, rotorcraft designers and manufacturers and final year undergraduates of aeronautical engineering

Download or read book Roll Axis Hydrofluidic Stability Augmentation System Development written by Darroll Bengtson and published by . This book was released on 1975 with total page 137 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of this program was to develop, design, and flight test a roll-axis Hydrofluidic Stability Augmentation System (HYSAS) for the OH-58A helicopter. The system, when used with a yaw HYSAS, provides increased vehicle damping which improves the handling characteristics. Flight test evaluations were performed with satisfactory results.

Download or read book Evaluations of Helicopter Instrument flight Handling Qualities written by S. R. M. Sinclair and published by . This book was released on 1982 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Flight Test Identification and Simulation of a UH 60A Helicopter and Slung Load written by and published by . This book was released on 2001 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book Loss of Tail Rotor Effectiveness Evaluation of the OH 58C Helicopter with Directional SAS Stability Augmentation System written by and published by . This book was released on 1988 with total page 292 pages. Available in PDF, EPUB and Kindle. Book excerpt: The U.S. Army Aviation Engineering Flight Activity conducted a loss of tail rotor effectiveness (LTE) evaluation of the JOH-58C. The JOH-58C configuration includes a directional stability augmentation system (SAS) manufactured by the SFENA Corporation, the larger-diameter tail rotor, and the improved engine fuel control. Handling qualities were evaluated at Edwards AFB, California (elevation 2302 feet). Twenty-eight flights were conducted for a total of 26.7 productive flight test hours. Primary emphasis of the evaluation was to evaluate the handling qualities of the JOH-58C in comparison to the standard OH-58C. The limited authority SAS (7% of full control travel) will not significantly reduce the conditions conducive to LTE. The overall handling qualities of the JOH-58were moderately improved compared to the standard OH-58C. The concept of a SAS which damps uncommanded yaw rates demonstrated potential for reducing conditions conducive to LTE. However, the limited authority SAS saturated at small yaw rates (deg/sec) and did not significantly reduce the characteristic high yaw rates and moderate yaw attitude excursions observed in the JOH-58C. The JOH-58C exhibited moderate pitch, roll, and yaw excursions at 15 to 25 KTAS in azimuths from 240 degrees clockwise to 280 degrees. This characteristic was a shortcoming, upgraded from a deficiency for the standard OH-58C. Five additional shortcomings, of which four were previously identified in the standard OH-58C, were noted.

Download or read book An Experimental Evaluation of the Sternberg Task as a Workload Metric for Helicopter Flight Handling Qualities FHQ Research written by and published by . This book was released on 1984 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Helicopter Handling Qualities written by and published by . This book was released on 1982 with total page 262 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Design of a Helicopter Stability and Control Augmentation System Using Optimal Control Theory written by Alvin Rudolph Lang and published by . This book was released on 1971 with total page 103 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report presents the design of a helicopter stability and control augmentation system using optimal control techniques. The helicopter used as an example was the Sikorsky H-53, but the design procedure is applicable to other helicopters as well. Only the longitudinal dynamics are considered. A technique is described for the design of multivariable feedback controllers based upon results in optimal control theory. For a specified performance index the feedback controller is obtained by solving the matrix Riccati equation. A model is used in the forward controller such that the response of the model to pilot inputs approximates the desired helicopter response. A fixed gain controller is obtained which may be used over the entire helicopter flight envelope. The results show that optimal control theory can be used to design a helicopter stability and control augmentation system. Responses obtained may be classified as those which are desirable and yield good handling qualities. (Author).

Download or read book Airworthiness and Flight Characteristics Evaluation OH 58C Interim Scout Helicopter written by and published by . This book was released on 1979 with total page 205 pages. Available in PDF, EPUB and Kindle. Book excerpt: The United States Army Aviation Engineering Activity conducted an airworthiness and flight characteristics evaluation of the OH-58C Interim Scout helicopter. Performance, handling qualities, and vibration characteristics were evaluated to provide engineering test data for use in the OH-58C Operator's Manual and to detect any aircraft deficiencies or shortcomings. The OH-58C was tested at Edwards Air Force Base, California (elevation 2302 feet), and alternate test site elevations of 4120, and 9980 feet. A total of 97 flights were conducted for a total of 123.5 flight hours. Due to the more powerful T63- A-720 engine installed in the helicopter, the hover and takeoff capability at heavy gross weights and high altitudes and the forward flight climb performance of the OH-58C is significantly improved over the OH-58A. Performance in terms of power required and fuel flow is slightly degraded when compared to the OH-58A at similar gross weights and altitudes and in general did not meet the estimates of the detail specification for the OH-58C. The handling qualities and vibrations of the OH-58C are similar to the OH-58A when operating at similar gross weights and altitudes. Three handling qualities deficiencies relative to the low speed flight characteristics were identified.