Engineering Test (airworthiness and Performance Tests) of Uh-1c Helicopter with Cluster, Canister, Riot Control Cs, 130 Lb, E-159
Engineering Test (airworthiness and Performance Tests) of Uh-1c Helicopter with Cluster, Canister, Riot Control Cs, 130 Lb, E-159

Author: George Yamakawa

Publisher:

Published: 1967

Total Pages: 35

ISBN-13:

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Flight tests were conducted at Edwards Air Force Base by USAAVNTA personnel to develop a jettison and firing envelope for the E-159 system suspended from a M-75 grenade launcher/M-60C machine gun equipped UH-1C helicopter. This report includes the recommended safe jettison and firing envelopes. Effects on UH-1C performance, stability and control characteristics are included in this report. No flight control correction was required during or after the firing and/or jettison of the E-159. Single E-159 canister loading was not recommended, nor was jettison of the empty strongback. The previously reported self-excited, undamped pylon motion vibration characteristics were observed during these tests. These vibration characteristics were considered to be unsatisfactory and require correction. (Author).

Engineering Flight Test of the Uh-1c Helicopter Equipped with the M-5 Grenade Launcher and the Xm-158 Or Xm-159 Airborne Rocket Launcher Pods Suspended from the Xm-156 Multiarmament Mount
Engineering Flight Test of the Uh-1c Helicopter Equipped with the M-5 Grenade Launcher and the Xm-158 Or Xm-159 Airborne Rocket Launcher Pods Suspended from the Xm-156 Multiarmament Mount

Author: Jerry W. Petrie

Publisher:

Published: 1967

Total Pages: 95

ISBN-13:

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Presented are the results of engineering flight test of the UH-1C (UH-1B/540 rotor) helicopter equipped with the M-5 grenade launcher and the XM-158 or XM-159 airborne rocket launcher pods suspended from the X-156 multiarmament helicopter mount. Tests included 32 jettison flights for the XM-158 pods, 20 jettison flights for the XM-159 pods and 16 firings of the XM-159 pods. The objective was to determine quantitative effect of the XM-159 pods installed from the XM-156 mount on the stability, control and performance of the helicopter; to determine the XM-158 and XM-159 jettison characteristics and define the flight envelope for safe jettison of the pods; and to determine the flight envelope for firing the XM-159 pods. There were no significant adverse changes in the stability and control characteristics of the UH-1B/540 due to the installation of the XM-159. Previously reported longitudinal dynamic instability in climbs was also present throughout the tests. Self-excited undamped lateral 2/3-per-rev vibration was prevalent during the tests. Insufficient rocket-to-aircraft clearance for firing the XM-159 on the XM-156 mount was present without the addition of 4-inch cast aluminum spacers between the XM-156 mount and the universal pylon. The XM-159 was adjusted to maximum elevation to provide sufficient clearance for firing with the spacers installed. No major stability and control problems were encountered during the firing tests of the XM-159 or during the jettison tests of both the XM-158 and XM-159. Recommended flight envelopes were developed for jettison of both systems. (Author).

Engineering Flight Test of the Uh-1c Helicopter Equipped with the Xm-30 Weapon System
Engineering Flight Test of the Uh-1c Helicopter Equipped with the Xm-30 Weapon System

Author: Kenneth R. Ferrell

Publisher:

Published: 1967

Total Pages: 96

ISBN-13:

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The Army Preliminary Evaluation of the UH-1C/XM-30 weapon system was conducted by the U.S. Army Aviation Test Activity at Edwards Air Force Base and Fort Irwin, California. The degradation in level flight performance attributed to the weapon installation was defined and no objectionable flying qualities were encountered during firing or non-firing tests. The armed mission capability of the helicopter was degraded by high levels of stress, vibration, blast, and noise during firing and restrictive limitations were imposed by gun malfunctions and system gross weight. The reliability of the weapon system was poor and should be improved prior to further Army testing.

Airworthiness and Flight Characteristics Test, OV-1C Takeoff Performance
Airworthiness and Flight Characteristics Test, OV-1C Takeoff Performance

Author: Raymond B. Smith

Publisher:

Published: 1979

Total Pages: 33

ISBN-13:

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The United States Army Aviation Engineering Flight Activity conducted takeoff performance tests on an OV-1C aircraft, serial number 67-18918, from 11 April through 19 July 1978. The aircraft was tested at Edwards Air Force Base (field elevation 2273 feet) and South Lake Tahoe, California (field elevation 6262 feet). Twelve flights totaling 6.9 productive flight hours were conducted. Takeoff performance tests were conducted on the OV-1C to substantiate the performance data currently incorporated in the operator's manual. Tests were conducted using two normal takeoff techniques and a minimum run takeoff technique at each of three gross weights. All takeoffs were made from hard, dry, paved level runways. Test results show that the estimated data for normal takeoff is satisfactory but the data for the minimum run technique in the operator's manual is optimistic. (Author).

Airworthiness and Flight Characteristics Test of a Sixth Year Production UH-60A.
Airworthiness and Flight Characteristics Test of a Sixth Year Production UH-60A.

Author: Robert M. Buckanin

Publisher:

Published: 1985

Total Pages: 115

ISBN-13:

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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.

Engineering Flight Test of the Uh-1b Helicopter Equipped with the Model 540 Rotor System. Phase D
Engineering Flight Test of the Uh-1b Helicopter Equipped with the Model 540 Rotor System. Phase D

Author: Laurel G. Schroers

Publisher:

Published: 1966

Total Pages: 299

ISBN-13:

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The objectives of the test were to determine the airworthiness and to define the performance characteristics and flying qualities of the helicopter. Test Results, where appropriate, were compared with previous test results of the standard UH-1B. Tests were conducted at Edwards Air Force Base, California, and at remote test sites in California and Colorado from 19 May 1965 through 30 April 1966. Total aircraft flight time was 336.30 hours. Quantitative helicopter performance was defined for hovering, takeoff, climb, level flight, and autorotation. Stability and control characteristics were investigated for varied conditions of altitude, airspeed, center-of-gravity location, and gross weight.

Airworthiness and Flight Characteristics Test (A & FC) of the CH-47D Helicopter
Airworthiness and Flight Characteristics Test (A & FC) of the CH-47D Helicopter

Author:

Publisher:

Published: 1984

Total Pages: 244

ISBN-13:

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An Airworthiness and Flight Characteristics Test of the Boeing Vertol CH-47D helicopter (USA S/N 81-23383) was conducted by the U.S. Army Aviation Engineering Flight Activity. The test was conducted at St. Paul, Minnesota (elevation 704 feet). Edwards Air Force Base (elevation 2302 feet), Bishop (elevation 4120 feet), and Coyote Flats (elevation 9980 feet), California. A total of 148.8 hours (105.4 productive hours) were flown between 25 January and 13 December 1983. Hover, level flight, and autorotational descent performance tests were conducted. Handling qualities tests included static and dynamic stability, maneuvering stability, takeoff and landing characteristics, power management, simulated systems failures, simulated Instrument Meteorological Conditions flight evaluation, and vibration evaluation. Cockpit and subsystem evaluations were also made. The CH-47D exceeded those performance requirements of the Prime Item Development Specification which were evaluated during this test. The Advanced Flight Control System heading select capability and the pressure refueling capability were found to be enhancing characteristics of the aircraft. Three significant shortcomings were found: the poor engine governing system which allows large rotor speed excursions with changes in power setting or airspeed, the high level of cockpit vibrations at and above cruise airspeeds, and an easily excited three-axis airframe oscillation during high power conditions at light gross weight.

Preliminary Airworthiness Evaluation of the UH-60A Configured with the External Stores Support System (ESSS).
Preliminary Airworthiness Evaluation of the UH-60A Configured with the External Stores Support System (ESSS).

Author: Arthur R. Marshall

Publisher:

Published: 1983

Total Pages: 88

ISBN-13:

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The Preliminary Airworthiness Evaluation of the UH-60A helicopter configured with the External Stores Support System was conducted. A total of 26 test flights were conducted. Limited level flight performance tests were conducted to determine the change in drag of the UH-60A helicopter caused by three External Stores Support System configurations with various stores installed. An unexplained increase in power required was found between the Preliminary Airworthiness Evaluation test aircraft and the aircraft used during a previous Airworthiness and Flight Characteristics evaluation.