Download or read book Combined Preliminary Airworthiness Evaluation and Airworthiness and Flight Characteristics Evaluation of the UH 1H with Preproduction Hub Spring and Composite Main Rotor Blades Installed written by Gary L. Skinner and published by . This book was released on 1988 with total page 53 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Army has incorporated a main rotor hub spring on the UH-1H helicopter designed to reduce large main rotor flapping angles which occur during some flight maneuvers. Composite main rotor blades (CMRB), also incorporated, are intended to increase performance and to improve reliability and survivability of the UH-1H. A preliminary airworthiness evaluation was conducted to determine suitability of the combined preproduction CMRB and hub spring configuration for compliance with the CMRB Critical Item Development Specification (CIDS). Due to high vibration characteristics and the occurrence of cyclic control feedback contributing to loss of aircraft control associated with CMRB, additional testing was conducted for comparison with standard metal main rotor blades (STD) and composite main rotor blades constructed with production tooling (PROD CMRB). Flight testing was evaluated under a variety of operating conditions from field elevations of 2302 ft to 9980 ft. Some improvement was noted in out-of-ground effect hover performance with PROD CMRB compared to CMRB, while level flight performance of the CMRB and PROD CMRB was not significantly different. Performance improved for the PROD CMRB compared to STD, but did not meet CIDS requirements. Handling qualities are similar for CMRB and PROD CMRB, and deteriorated when compared to STD with regard to maneuvering characteristics and main rotor speed control during autorotation. (edc).

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1989 with total page 960 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aeronautical Engineering written by and published by . This book was released on 1990 with total page 540 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).

Download or read book Technical Reports Awareness Circular TRAC written by and published by . This book was released on 1989-02 with total page 492 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Government reports annual index written by and published by . This book was released on 199? with total page 1668 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA SP written by and published by . This book was released on 1990 with total page 700 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aeronautical Engineering A Cumulative Index to a Continuing Bibliography supplement 248 written by and published by . This book was released on 1990 with total page 532 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Government Reports Announcements Index written by and published by . This book was released on 1989 with total page 1458 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Journal of Dynamic Systems Measurement and Control written by and published by . This book was released on 1999 with total page 352 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Preliminary Airworthiness Evaluation OV 1D Airplane with AN ALQ 147 XE 1 and XE 2 Systems Installed written by Robert N. Ward and published by . This book was released on 1978 with total page 111 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Airworthiness and Flight Characteristics Evaluation C 12A Aircraft written by Joseph C. Watts and published by . This book was released on 1976 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Airworthiness and Flight Characteristics Evaluation C 12A A Aircraft written by Joseph C. Watts and published by . This book was released on 1975 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Preliminary Airworthiness Evaluation of the Rutan Aircraft Factory RAF Inc LONG EZ Airplane written by V. L. Diekmann and published by . This book was released on 1983 with total page 162 pages. Available in PDF, EPUB and Kindle. Book excerpt: The U.S. Army Aviation Engineering Flight Activity conducted a Preliminary Airworthiness Evaluation of the Rutan Aircraft Factory, Inc. designed LONG-EZ airplane at Edwards AFB, Calif. During the test program 34 flights were conducted for a total of 32.0 hours, of which 24.5 were productive. The objectives of the evaluation were to assess the performance and handling qualities of the LONG-EZ so that the US Army Aviation Research and Development Command could issue an airworthiness release for concept feasibility evaluation of the aircraft. The test aircraft exhibited excellent potential for the light observation/reconnaissance mission and is satisfactory for the intended concept feasibility evaluation. The high availability and minimal maintenance down time due to ease of repair of composite structures during flight testing of the LONG-EZ were noteworthy. One deficiency and fifteen shortcomings were identified. The loss of directional control due to single point brake failure during take-off/landing and ground handling was identified as a deficiency and is a safety-of-flight hazard. The major shortcomings affecting mission versatility and pilot effectiveness were: decrease in engine power during low g maneuvers; limited directional control; excessive throttle freeplay; limited longitudinal trimmability; and inaccessability of the lateral trim system. The deficiency should be corrected if development continues. The shortcomings should be corrected prior to production.

Download or read book AH 1S PROD Airworthiness and Flight Characteristics for Instrument Flight written by John S. Tulloch and published by . This book was released on 1980 with total page 47 pages. Available in PDF, EPUB and Kindle. Book excerpt: The United States Army Aviation Engineering Flight Activity conducted an Airworthiness and Instrument Flight Characteristics evaluation of a Production AH-1S (Prod) to determine potential for the AH-1S with Enhanced Cobra Armament System (ECAS) to meet instrument meteorological conditions qualification criteria. The test aircraft was configured with two tube launched, optically tracked, wireguided (TOW) missile launchers on each outboard wing stores station and a 7-tube lightweight launcher on each inboard wing stores station. The test consisted of 16.3 flight hours which were flown during 12 test flights. Four deficiencies and seven shortcomings associated with flying the AH-1S in instrument flight conditions, were identified. The deficiencies identified were: (1) Unsatisfactory cyclic control system mechanical characteristics; (2) large pitot-static system airspeed errors in climb and descent; (3) Easily excited lateral gust response; (4) Vertigo-inducing location of radio control panels. Five specification noncompliances were noted. The AH-1S (Prod) is not suitable for flight in instrument meteorological conditions, which infers tht the AH-1S (ECAS) will also not be suitable. (Author).

Download or read book Preliminary Airworthiness Evaluation of the AH 1S Modernized Cobra with the HELLFIRE TOW and Stinger Missiles Installed written by and published by . This book was released on 1984 with total page 193 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aircraft was operated at gross weights up to 10,400 lb, up to 11, 340 feet density altitude and at a lateral center of gravity (cg) range from one inch right to approximately three inches left. The asymmetric loadings were caused by the various combinations of armament configurations. The change in equivalent flat plate area compared to the clean aircraft for each configuration varied as a function of airspeed. At 130 knots true airspeed (KTAS), the increased flat plate area was 4.2 square feet for the Launcher configuration, 4. 8 square feet for the TOW configuration, 6.6 square feet for the Hellfire and Hellfire/TOW configurations, and 7.8 square feet for the Stinger/Hellfire/TOW configuration. The increase in flat plate area for the Stinger/Hellfire/TOW configuration reduced maximum level flight speed for normal rated power by approximatley 8 KTAS. With the exception of the two armament related shortcomings listed below, the handling qualities and the reactions to system failures of the AH-1S (MC) were not significantly changed by the asymmetric loading of the various armament configurations. Four shortcomings were noted and follow in decreasing order of importance: (1) the high left rolling response to a sudden engine failure at power settings above 75% torque; (2) the undesirable maneuvering stability characteristics above 1.4 g's; (3) insufficient left pedal margin available in right sideward flight above 10 knots in the Hellfire and Hellfire/TOW configurations; and (4) insufficient left pedal margin available for ball-centered forward flight below 30 KCAS in the armament configurations with left lateral cf offset. A CAUTION is recommended for inclusion in the operator's manual dealing with.

Download or read book Preliminary Airworthiness Evaluation AH 1G with the Airborne Target Acquisition Fire Control System and the Hellfire Modular Missile System Installed written by Patrick J. Moe and published by . This book was released on 1979 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Airworthiness and Flight Characteristics Test of a Sixth Year Production UH 60A written by Robert M. Buckanin and published by . This book was released on 1985 with total page 115 pages. Available in PDF, EPUB and Kindle. Book excerpt: Testing was conducted to obtain performance data for inclusion in the sixth year production UH-60A helicopter operator's manual. A total of 58 productive flight hours were flown at five different test sites between 3 and 20 October 1983 and 29 February and 18 September 1984. The out-of-ground effect hover gross weight capability was 16,526 pounds for 95 percent intermediate (30 minute limit) rated power available at 4700 feet pressure altitude and 35 C temperature. The increase in equivalent flat plate area of the sixth year production aircraft configuration over the first year configuration over the first year configuration was 5 square feet in level flight at a referred rotor speed (N sub R/sqare rot theta) of 258 revolutions per minute. Of this increase, 2.5 was attributed to the External Stores Support System fixed provision fairings, 1.5 sq ft to the external mounting brackets of the AN/ALQ-144(V) infrared countermeasures set and M130 chaff dispenser, and 1.0 sq ft to numerous other minor external changes. However, throughout the N sub R/square root theta range, the difference in power required between the first and sixth year production aircraft does not equate to a constant Fe. A limited investigated did not completely account for the power differences noted when flying at different dimensional conditions that produce the same nondimensional thrust coefficient.