Download or read book Height Velocity Test AH 1G Helicopter at Heavy Gross Weight Part 1 Low Elevation written by and published by . This book was released on 1974 with total page 51 pages. Available in PDF, EPUB and Kindle. Book excerpt: The United States Army Aviation Systems Test Activity conducted engineering flight tests to determine the operational height-velocity envelopes of the AH-1G helicopter at 9000 and 9500 pounds gross weight. This report constitutes the low elevation part of the evaluation conducted at Edwards Air Force Base, California, from 14 November 1973 through 5 February 1974. Operational height-velocity envelopes were defined from test data, are valid for 9000 and 9500 pounds at density altitudes up to 1000 feet, and represent combinations of airspeed and height above ground level where a straight-ahead landing may be accomplished following an engine failure. Autorotational landings at gross weights over 9250 pounds will probably result in rotor overspeed and the height above ground level at which the flare is executed becomes more critical as gross weight is increased to 9500 pounds. The operator's manual lacks clarity in describing pilot techniques to be used during the height-velocity maneuver and needs improvement in other areas. The height-velocity diagram developed during this evaluation, a discussion of the height-velocity diagram, a more thorough discussion of pilot techniques, the correct airspeed calibration chart, and the hog configuration descent performance chart should be incorporated in the operator's manual. A radio altimeter should be installed as standard equipment on the AH-1G helicopter.
Download or read book Height Velocity Test AH 1G Helicopter written by Gregory W. Condon and published by . This book was released on 1971 with total page 61 pages. Available in PDF, EPUB and Kindle. Book excerpt: The AH-1G height-velocity (H-V) flight test program was conducted at auxiliary test sites near Shafter and Bishop, California. The objective of this program was to develop an operational AH-1G H-V envelope for incorporation into the operator's manual. Near maximum performance H-V envelopes were determined for two gross weights at each of two density altitudes. Operational H-V envelopes were defined from the test data and are valid for all gross weights up to 8300 pounds at density altitudes of sea level and 5500 feet. Although the operational envelopes allow an adequate safety margin, the operational aviator requires additional training to accomplish the specified performance. This training should consist of autorotational entries at all airspeeds for low skid heights and airspeeds below 60 knots for high skid heights. Further AH-1G H-V testing should be conducted to: define the H-V envelopes at gross weights between 8300 and 9500 pounds; determine the autorotational characteristics following a sudden engine failure while accelerating through the recommended takeoff corridor; accurately determine the amount of altitude lost in accelerating to forward airspeed, as a function of pitch rates and pitch attitudes; and to provide data for analysis of skid height above the ground versus advance ratio and density ratio. The operational H-V envelopes and recommended pilot techniques presented in this report should be incorporated into the operator's manual at the earliest possible date. The related information presently in the operator's manual is inaccurate, incomplete and dangerously misleading.
Download or read book Zero zero Rotorcraft Certification Issues Volume 2 Plenary Session Presentations written by and published by . This book was released on 1988 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Investigation of the Helicopter Height velocity Diagram Showing Effects of Density Altitude and Gross Weight written by Robert J. Pegg and published by . This book was released on 1968 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Government Reports Announcements Index written by and published by . This book was released on 1977 with total page 1134 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.
Download or read book An Evaluation of the Height Velocity Diagram of a Lightweight Low Rotor Inertia Single Engine Helicopter written by William J. Hanley and published by . This book was released on 1965 with total page 59 pages. Available in PDF, EPUB and Kindle. Book excerpt: A series of flight tests was conducted at three selected altitudes (sea level, 5000 feet, 7000 feet) to determine the effects of altitude and weight on the height-velocity (H-V) diagram of a small, lightweight, low rotor inertia, medium disk loading, single rotor, single engine helicopter. Two gross weights of the helicopter were used. Quantitative and qualitative test data were collected to determine how the H-V diagram varies with density altitude and aircraft gross weight. An investigation was made into the effects on the diagram of a delayed collective pitch application response. Results disclosed a family of curves showing that increases in density altitude and/or gross weight enlarged the H-V diagram required for a safe power-off landing. Analysis of the results revealed that the key points (V sub cr, h sub min, and h sub max), which partially define the curves, could be determined by the solution of a set of linear equations. These results were identical to those reported in FAA technical Report ADS-1 except for the constants of the linear equations and the location of the critical height. The critical height indicated a slight increase as weight, altitude and collective pitch reduction time delay were increased. An average value for the critical height can be selected without upsetting the family of curves.
Download or read book Government Reports Annual Index written by and published by . This book was released on 1978 with total page 932 pages. Available in PDF, EPUB and Kindle. Book excerpt: Sections 1-2. Keyword Index.--Section 3. Personal author index.--Section 4. Corporate author index.-- Section 5. Contract/grant number index, NTIS order/report number index 1-E.--Section 6. NTIS order/report number index F-Z.
Download or read book An Evaluation of the Effects of Altitude on the Height Velocity Diagram of a Single Engine Helicopter written by William J. Hanley and published by . This book was released on 1963 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of altitude on the height-velocity H-V) diagram for a light-weight, single-engine helicopter were investigated at four selected altitudes (sea level, 4000 ft., 7000 ft, and 10,000 ft.) and three gross weights (2415 lbs., 2650 lbs., and 2850 lbs.). Quantitative and qualitative information was collected to determine how the height-velocity diagram varies with density altitude and also to determine a means of calculating the height-velocity diagrams for various density altitudes from flight test data recorded at one density altitude. Flight test results disclosed a family of curves showing that increases in either density altitude or gross weight incrased either the airspeed or the height above ground required for safe operation. From these empirical curves, linear equations were derived which express the relationship of critical points of the height-velocity diagram of the test helicopter for various gross weights and operating altitudes.
Download or read book An Evaluation of the Height Velocity Diagram of a Heavyweight High Rotor Inertia Single Engine Helicopter written by William J. Hanley and published by . This book was released on 1966 with total page 59 pages. Available in PDF, EPUB and Kindle. Book excerpt: A series of flight tests was conducted at three selected altitudes (sea level, 5000 feet, 6500 feet) to determine the effects of altitude and weight on the height-velocity (H-V) diagram of a large, heavyweight, high rotor inertia, high disk loading, single rotor, single engine helicopter. Three gross weights of the helicopter were used. Quantitative and qualitative test data were collected to determine how the H-V diagram varies with density altitude and aircraft gross weight. An investigation was made into the effects on the diagram of a delayed collective pitch application response. Results disclosed a family of curves showing that increases in density altitude and/or gross weight enlarged the H-V diagram required for a safe power-off landing. Analysis of the results revealed that the key points (V sub cr, h sub min, and h sub max), which partially define the curves, could be determined by the solution of a set of linear equations.
Download or read book Engineering Flight Test of the Ah 1g Helicopter to Determine the Area of Inadequate Directional Control Power at 8100 Pounds Gross Weight written by John R. Melton and published by . This book was released on 1968 with total page 35 pages. Available in PDF, EPUB and Kindle. Book excerpt: The test was conducted at Grand Prairie Municipal Airport near Fort Worth, Texas, from 4 August 1967 to 12 August 1967 by the US Army Aviation Test Activity (USAAVNTA). Paced in-ground-effect (IGE) flight, hovering in winds, approaches to a spot, and arrestment of turn rates at various wind azimuths were investigated.
Download or read book Engineering Flight Test of the Ah 1g Helicopter hueycobra Phase B written by John R. Melton and published by . This book was released on 1968 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt: Part 1 of the AH-1G helicopter Phase B test was conducted at Ft Hood, Texas by the US Army Aviation Test Activity, Edwards AFB, California. The helicopter flying qualities were evaluated throughout the aircraft speed range for the Scout and Hog configurations at a mid-center-of-gravity location. Flying qualities were also evaluated during weapons firing and external stores jettison. The primary deficiencies detected during this test were stability and Control augmentation system (SCAS)-pylon coupling, inadequate in-ground-effect (IGE) directional control power, undue pilot attention required to avoid exceeding the torque limits of the helicopter transmission in dives and left rolls with fixed collective, and an inadequate, illogical fire control system. Other shortcomings were detected, such as airspeed system errors, degradation of flying qualities with SCAS off, static lateral cyclic control force imbalance, and marginal cockpit ventilation. Helicopter reactions to weapons firing and external stores jettison were satisfactory, and the contractor approved flight envelope for firing and jettison was acceptable.
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 Marines and Helicopters 1962 1973 written by William R. Fails and published by DIANE Publishing. This book was released on 1995-07 with total page 273 pages. Available in PDF, EPUB and Kindle. Book excerpt: Traces the development of helicopters in the Marine Corps from 1962 to 1973. Portrays accurately the difficulties faced and the obstacles conquered by the men who developed helicopters in the Marine Corps. Over 100 figures, maps, photos, and tables.
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1977 with total page 286 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Field Artillery Manual Cannon Gunnery written by Department of the Army and published by . This book was released on 2017-08-19 with total page 664 pages. Available in PDF, EPUB and Kindle. Book excerpt: Training Circular (TC) 3-09.81, "Field Artillery Manual Cannon Gunnery," sets forth the doctrine pertaining to the employment of artillery fires. It explains all aspects of the manual cannon gunnery problem and presents a practical application of the science of ballistics. It includes step-by-step instructions for manually solving the gunnery problem which can be applied within the framework of decisive action or unified land operations. It is applicable to any Army personnel at the battalion or battery responsible to delivered field artillery fires. The principal audience for ATP 3-09.42 is all members of the Profession of Arms. This includes field artillery Soldiers and combined arms chain of command field and company grade officers, middle-grade and senior noncommissioned officers (NCO), and battalion and squadron command groups and staffs. This manual also provides guidance for division and corps leaders and staffs in training for and employment of the BCT in decisive action. This publication may also be used by other Army organizations to assist in their planning for support of battalions. This manual builds on the collective knowledge and experience gained through recent operations, numerous exercises, and the deliberate process of informed reasoning. It is rooted in time-tested principles and fundamentals, while accommodating new technologies and diverse threats to national security.
