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.

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 (product Improvement Test) of Production Oh-6a Helicopter Unarmed and Armed with the Xm-27e1 Weapon System Phase D
Engineering Flight Test (product Improvement Test) of Production Oh-6a Helicopter Unarmed and Armed with the Xm-27e1 Weapon System Phase D

Author: John I. Nagata

Publisher:

Published: 1968

Total Pages: 80

ISBN-13:

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An engineering flight test of the OH-6A helicopter equipped with the XM-27E1 armament subsystem was conducted at Edwards Air Force Base, California, by the US Army Aviation Test Activity. The objective of the test was to determine what effects the armament subsystem had on the performance and stability and control characteristics as compared with an aircraft without the armament subsystem. The testing consisted of 10.25 productive test hours and was conducted from 2 October 1967 through 24 October 1967. Performance degradation resulted from the drag imposed by the armament subsystem. The specific range at 2400 pounds gross weight decreased by 8 percent. The stability and control characteristics were essentially unchanged by the addition of the armament subsystem. During firing tests, there were no adverse control problems. However, during flight at 12 degrees left sideslip at 105 knots indicated airspeed (KIAS), the upper right windshield imploded. The sideslip angle should be limited to 8 degrees or less at 100 KIAS until the cause of the implosion can be determined. Noise level and vibration tests should be conducted during firing with the 'doors off' configuration. The performance data should be incorporated into the operator's manual. (Author).

Engineering Flight Test of Uh-1b/540 Rotor Helicopter Equipped with Xm-16/m-5, Xm-21/m-5 Or Xm-3/m-5 Armament Subsystem
Engineering Flight Test of Uh-1b/540 Rotor Helicopter Equipped with Xm-16/m-5, Xm-21/m-5 Or Xm-3/m-5 Armament Subsystem

Author: John I. Nagata

Publisher:

Published: 1966

Total Pages: 135

ISBN-13:

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This report presents the results of an engineering flight test of the UH-1B/540 rotor helicopter equipped with the XM-16, XM-21, or XM-3 armament subsystem in conjunction with the M-5 armament subsystem. The test was conducted by the U.S. Army Aviation Test Activity (USAAVNTA). Overall test objectives were to verify safety of flight, develope data for the operator's manual, and assure that aircraft modifications did not degrade the handling qualities or limit the operational characteristics of the subsystems. Specific objectives were to determine quantitatively the effect of the armament subsystems on stability, control and performance of the aircraft, to determine the rocket launcher jettison characteristics, and to define the usable limits of the flight envelope for safe jettison of the launchers. Testing was conducted at Edwards Air Force Base, California, and at sites in Fort Irwin and Bakersfield, California. A total of 152 flights for a productive flight time of 116.4 hours was flown on aircraft S/N 64-14105 between 13 November 1965 and 5 May 1966. This included 30 jettison flights and 35 firing flights.

Engineering Flight Test of the Ah-1g Helicopter Equipped with the Xm-28 Chin Turret with One 7.62mm Automatic Gun (m-134) and One 40mm Grenade Launcher (xm-129)-hybrid. Phase B
Engineering Flight Test of the Ah-1g Helicopter Equipped with the Xm-28 Chin Turret with One 7.62mm Automatic Gun (m-134) and One 40mm Grenade Launcher (xm-129)-hybrid. Phase B

Author: Peter V. Passinisi

Publisher:

Published: 1968

Total Pages: 51

ISBN-13:

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Part 5 of the AH-1G helicopter Phase B test was conducted at Yuma Proving Ground, Yuma, Arizona, from 6 through 9 February 1968 by the US Army Aviation Test Activity, Edwards Air Force Base, California. The test consisted of firing the XM-28 chin turret, with one 7.62 millimeter automatic gun (M-134) and one 40 millimeter grenade launcher (XM-129) to determine the weapons system's effect on the stability and control characteristics of the helicopter. No safety of flight restrictions resulted from firing this system within the flight envelope. Correction of four deficiencies is mandatory to provide acceptable mission effectiveness and safety. These deficiencies are the inadequate forward visibility from the pilot's cockpit due to the N-9A gunsight installation, the lack of a fire warning system, the lack of a standby generator for IFR flight, and link jam malfunctions of the minigun during symmetrical pull-out maneuvers. Fifteen shortcomings, for which correction is desirable, limit mission effectiveness. The reliability of the weapons system was questionable and service type testing should be conducted prior to system acceptance. Correction of the deficiencies is mandatory and should be tested prior to deployment. Shortcomings, for which correction is desirable, should be corrected on a high priority basis. (Author).

Engineering Flight Test of Uh-1b Helicopter Equipped with Xm-47 Antipersonnel Mine Dispensing Subsystem
Engineering Flight Test of Uh-1b Helicopter Equipped with Xm-47 Antipersonnel Mine Dispensing Subsystem

Author: Manfred Reif

Publisher:

Published: 1966

Total Pages: 116

ISBN-13:

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A limited engineering flight test was conducted to provide sufficient engineering data for a safety-of-flight release for the UH-1B helicopter equipped with the XM-47 antipersonnel mine dispensing subsystem. An additional objective was to provide sufficient performance and stability and control data to update the operator's manual data to be used for UH-1B helicopters equipped with the XM-47 subsystem. Testing consisted of 42 productive flight hours. When the XM-47 mine dispensing subsystem was installed on the UH-1B helicopter, antipersonnel mines could be safely dispersed within the recommended flight envelopes. In cases of emergency the dispensers could be safely jettisoned within the recommended envelopes. Jettisons during entry into autorotation and in close proximity to the ground should be avoided. The flying qualities of the UH-1B were essentially unaffected by the installation of the XM-47 mine dispensing subsystem.

Engineering Flight Test of Uh-1b Helicopter Equipped with Xm-16 Armament Subsystem and Engineering Flight Test of Uh-1b Helicopter Equipped with Xm-21 Armament Subsystem
Engineering Flight Test of Uh-1b Helicopter Equipped with Xm-16 Armament Subsystem and Engineering Flight Test of Uh-1b Helicopter Equipped with Xm-21 Armament Subsystem

Author: George M. Yamakawa

Publisher:

Published: 1966

Total Pages: 129

ISBN-13:

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Engineering flight tests of the UH-1B helicopter equipped with the XM-16 and XM-21 armament subsystems were conducted. The overall objective was to determine the effect of the installation of the subsystems on the UH-1B. Specific objectives were to determine the existence of any safety-of-flight conditions by evaluation of equantitative stability and control and vibration data and to determine any performance losses.

Engineering Flight Test of the Ah-1g Helicopter Equipped with the Xm-20 Armament Subsystem (automatic 20mm Cannon).
Engineering Flight Test of the Ah-1g Helicopter Equipped with the Xm-20 Armament Subsystem (automatic 20mm Cannon).

Author: Stephen G. Dorris

Publisher:

Published: 1968

Total Pages: 30

ISBN-13:

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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).

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).