Download or read book Airworthiness and Flight Characteristics AH 1G Helicopter with Stabilized Night Sight SNS Phase I written by Gary L. Bender and published by . This book was released on 1969 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Phase 1 airworthiness and flight characteristics tests of the AH-1G helicopter with the mock-up stabilized night sight (SNS) installed indicated a feasibility for further development utilizing the actual SNS equipment. No significant changes in the handling qualities due to the SNS modification were noted during the tests. The static, proof load test results indicate that the structure is adequate to withstand the required loads. Testing was terminated early to obtain instrumented components (rotor blade, drag brace and pitch link) so the flight envelope and/or fatigue life of these components could be more accurately determined. These tests are scheduled to be completed during Phase 2 with the actual SNS installed.
Download or read book Airworthiness and Flight Characteristics AH 1G Helicopter with Stabilized Night Sight SNS written by Gary L. Bender and published by . This book was released on 1969 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Airworthiness and Flight Characteristics Test AH 1G Helicopter with Stabilized Night Sight SNS Phase II written by Gary L. Bender and published by . This book was released on 1970 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Phase II tests were conducted to evaluate the flight envelope of the AH-1G with the SNS installed for significant changes in the structural loads, handling qualities and performance due to this modification. The effects of weapons firing on the SNS system were also evaluated. The structural loads, handling qualities and performance of the AH-1G were not significantly changed by the SNS installation. The published AH-1G flight envelope is satisfactory for the SNS modified aircraft with one exception: due to the aircraft's reactions following sudden engine failure, the engine torque should be limited to less than 35 pounds per square inch, indicated, for all dives to airspeeds greater than 150 KCAS. Four deficiencies require correction before further testing in instrument flight conditions or in a combat environment.
Download or read book Engineering Flight Test AH 1G Helicopter Hueycobra Phase D Airworthiness and Flight Characteristics Part 2 Performance Addendum written by Rodger L. Finnestead and published by . This book was released on 1971 with total page 99 pages. Available in PDF, EPUB and Kindle. Book excerpt: This addendum to the performance report presents the results of turning performance, in-ground-effect (IGE) level acceleration and deceleration performance and dive recovery tests. These three tests were conducted to validate portions of the AH-1G operator's manual (TM 55-1520-221-10) and enhance the knowledte of interested government agencies as to the limitations and capabilities of the AH-1G helicopter. Three major limitations were encountered during testing that restricted the pilot from achieving maximum performance: level acceleration and deceleration performance IGE is limited by extreme pitch attitudes; level deceleration performance is limited by the pilot's ability to maintain rotor speed below the maximum limit (339 rpm); the cyclic control feedback limits aircraft turning and dive recovery performance at heavy gross weight and/or when high load factors are encountered. (Author).
Download or read book Engineering Flight Test AH 1G Helicopter Hueycobra Phase D Airworthiness and Flight Characteristics Part 2 Performance written by Rodger L. Finnestead and published by . This book was released on 1970 with total page 220 pages. Available in PDF, EPUB and Kindle. Book excerpt: Within the scope of this test, the AH-1G helicopter is suitable for the armed helicopter mission provided the insufficient directional control power and inadequate tail rotor drive system torque limitations are corrected. A directional control margin of 10 percent while hovering is the minimum acceptable for normal operation. Installation of the engine inlet screens and the engine particle separator decrease the performance capability of the AH-1G when maximum power available is the limiting parameter. The level-flight performance capabilities of the AH-1G vary with longitudinal cg location and improve as the cg moves aft. The degradation of hover performance capability when hovering in adverse crosswind is significant. The excellent climb performance, particularly from SL to 10,000 feet, enhances the capability of the AH-1G for the attack helicopter mission.
Download or read book Airworthiness and Flight Characteristics Test Limited AH 1G Helicopter with the Southeast Asia Multisensor Armament System Helicopter SMASH written by Gary L. Bender and published by . This book was released on 1970 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Engineering Flight Test AH 1G Helicopter HueyCobra Phase D Part 3 Vibration Characteristics written by Rodger L. Finnestead and published by . This book was released on 1970 with total page 127 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Phase D, Part 3 Airworthiness and Qualification Aircraft Vibration Tests of the AH-1G Helicopter were conducted. Six vibration parameters were evaluated to determine model specification compliance and mission suitability information for inclusion in technical manuals and other publications. The vibration levels of the AH-1G met all requirements of the detail model specification; however, a reduction in the vibration levels at airspeeds from maximum level-flight airspeed (VH) to limit airspeed (VL) is desirable for improved mission suitability. The detail model specification did not require any specific vibration levels at airspeeds other than VH. Future detail model specifications should contain vibration limits for all flight conditions and aircraft configurations.
Download or read book Engineering Flight Test of the Ah 1g Helicopter Equipped with the Xm 20 Armament Subsystem automatic 20mm Cannon written by Stephen G. Dorris and published by . This book was released on 1968 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: The engineering flight test of the AH-1G helicopter equipped with the XM-20 armament subsystem (automatic 20MM cannon) was conducted at Fort Hood, Texas from 31 January 1968 through 2 February 1968 by the US Army Aviation Test Activity, Edwards Air Force Base, California. Firing and nonfiring flight tests were conducted to determine the effects on the stability and control characteristics of the AH-1G helicopter caused by installation of the XM-20 armament subsystem. These tests were primarily qualitative in nature with limited qualitative data. The only stability and control characteristic which was affected either in the firing or nonfiring mode was the static longitudinal cyclic position gradients which were low at high speeds. The deficiencies detected during this test were the interference of the XM-20 gearbox with the XM-159 rocket pod and unreliability of the standard airspeed system due to the location of the static port in proximity to the XM-20 blast pressures. One firing rate of 600-800 spm is considered optimum. The XM-20 appears to offer greater stand-off capability, greater accuracy and more killing power than 2.75 inch rockets. It appears to be a reliable subsystem. The XM-20 configuration should be finalized, installed on a production AH-1G helicopter and certified for airworthiness throughout the AH-1G flight envelope as soon as possible to allow early introduction to Republic of Vietnam. (Author).
Download or read book Engineering Flight Test AH 1G Helicopter Hueycobra Phase D Part 1 Handling Qualities written by Rodger L. Finnestead and published by . This book was released on 1970 with total page 427 pages. Available in PDF, EPUB and Kindle. Book excerpt: The AH-1G helicopter manufactured by Bell Helicopter Company (BHC) was designed specifically to meet the US Army requirements for an armed helicopter. Tandem seating is provided for a two-man crew. The main rotor system is a two-bladed, semi-rigid, 'door hinge' type with the stabilizer bar removed. The engine is derated to 1100 shp due to the maximum torque limit of the main transmission. Distinctive features of the AH-1G are: the narrow fuselage (36 inches), the stub midwing with four external store stations, the integral chin turret. The flight control system is of the mechanical, hydraulically boosted, irreversible type with conventional helicopter controls in the aft cockpit (pilot station). The controls in the forward cockpit (copilot/gunner station) consist of conventional antitorque pedals and sidearm collective and cyclic controls. An electrically operated force trim system is connected to the cyclic and directional controls to induce artificial feel and to provide positive control centering.
Download or read book Engineering Flight Test AH 1G Helicopter Hueycobra written by Rodger L. Finnestead and published by . This book was released on 1969 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Airworthiness and Flight Characteristics Evaluation YAH 1S Improved Cobra Agility and Maneuverability Helicopter written by Gary L. Skinner and published by . This book was released on 1975 with total page 102 pages. Available in PDF, EPUB and Kindle. Book excerpt: Limited flight tests of a prototype aircraft were conducted at 3 test facilities at various altitudes. Testing concentrated on hover and level flight performance, controllability, and low-speed flight characteristics at heavy gross weight, high density altitude test conditions. The YAH-1S represents a significant improvement over the AH-1G/Q helicopter by virtue of its increased useful load-carrying capability, directional controllability and control margin, and hover performance capability. The control system characteristics of the YAH-1S failed to meet several requirements of applicable paragraphs of military specification MIL-H-8501A and the approved BHC deviations to MIL-H-8501A against which they were tested, but were still considered satisfactory. One shortcoming was noted.
Download or read book Engineering Flight Test AH 1G Helicopter Hueycobra Phase B written by Rodger L. Finnestead and published by . This book was released on 1969 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt: The AH-1G helicopter Phase B, Part 6 test program was conducted at Shafter, California, and Edwards Air Force Base, California. The program was conducted to determine level flight performance, autorotational performance, engine characteristics, armed helicopter mission capability and to evaluate the in-ground-effect (IGE) handling qualities with the canopy doors removed.
Download or read book Engineering Flight Test AH 1G Helicopter Hueycobra written by Rodger L. Finnestead and published by . This book was released on 1971 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Engineering Flight Test AH 1G HueyCobra Helicopter Autorotational Entry Characteristics written by Brock M. Nicholson and published by . This book was released on 1971 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Performance and Handling Qualities Evaluation AH 1G Helicopter with Low Reflective Infrared optical Paint written by Albert L. Winn and published by . This book was released on 1975 with total page 53 pages. Available in PDF, EPUB and Kindle. Book excerpt: The performance and handling qualities of an AH-1G helicopter were evaluated in the basic paint configuration, with the fuselage and main and tail rotors painted with a low reflective infrared (IR)/optical paint (FSN 8010-083-6588), and in a modified IR/optical paint configuration in which the tail rotor blades and the main rotor leading edge were stripped of the IR/optical paint. Flight tests were conducted by the United States Army Aviation Engineering Flight Activity at Edwards Air Force Base, California, between 27 November 1974 and 10 April 1975. Twenty-five flights were flown for a total of 24.7 productive flight hours. Performance testing was limited to hover, level flight, and autorotational descent. Handling qualities were qualitatively evaluated throughout the conduct of the test program. Additionally, maneuvering stability was quantitatively evaluated in the IR/optical paint configuration and compared with results from previous reports.
Download or read book Airworthiness and Flight Characteristics Evaluation AH 1Q Helicopter written by Leslie J. Hepler and published by . This book was released on 1973 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book AH 1G Lateral Flight Performance Test written by Leslie J. Hepler and published by . This book was released on 1972 with total page 21 pages. Available in PDF, EPUB and Kindle. Book excerpt: The lateral flight performance of the tractor-tail-rotor-configured AH-1G helicopter was evaluated at gross weights of 8500 and 9500 pounds. The AH-1G is capable of 0.53g and 0.38g accelerations in right and left lateral flight, respectively, at 8500 pounds. At a 9500-pound gross weight, acceleration was 0.23g to the right and 0.20g to the left. Aircraft handling qualitites and time required to attain maximum lateral velocity are dependent upon rate and type of control application. A step-type lateral control input permitted rapid attainment of accelerating attitude but produced yaw oscillations which resulted in loss of directional control and caused high pilot workload in stabilizing power and aircraft attitude. Ramp inputs delayed establishment of the accelerating attitude. A modified pulse input induced negligible roll and yaw oscillation and produced rapid establishment of the desired roll attitude. Direction-of-flight reversals induced large power transients that frequently exceeded the transmission torque limits. Precise heading and pitch attitude could not be maintained during the reversals. Airspeed in lateral flight could not be determined without special airspeed measuring devices. The sideward airspeed limit was exceeded frequently in left lateral flight with no warning or cue to the pilot that the limit had been reached.
