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Aviation History
1959
1959 - 1418.PDF
FLIGHT, 15 May 1959 691 Helicopters of the World . . . Cessna Aircraft Corporation Wichita, Kansas. CH-1C This clean-lined helicopter is an improved version of the YH-41, as sup- plied to the U.S. Army. A specialized version, adapted specifically as an instru- ment trainer, is now being demonstrated to the U.S. Armed Forces. The makers feel that the -1C represents a real technical advance, by virtue of its inherent stability. They report:— "In the light helicopter field the stability ofthe CH-1C is unsurpassed. It is completely stable in roll, pitch, and yaw allowing indefinitehands-off flight . . . The pilot is not aware of the control inputs from the gyro stabilizingmechanism due to the fact that a mixing linkage is used which prevents feed back from the sys-tem to the cyclic stick. No aerodynamics penalty is paid for stabilization because it is completelyenclosed within the airframe . . . Control response has not been sacrificed. Doubly effec-tive in cross-wind hovering and manoeuvring is the large tail rotor which provides powerfuldirectional control." The following claims are also advanced:"The versatile functional design of the CH-1C lends itself to a degree of operationalefficiency heretofore unattainable in any single helicopter. The forward-mounted engine in-stallation affords maximum accessibility and ease of maintenance. This configuration per-mits a direct drive from the engine to the simple, long-life transmission consisting of arugged ring gear and pinion and a take-off gear to power the tail rotor. The transmission andengine location permit a cabin design with unlimited visibility in every direction . . ." The engine is a Continental FSO-526A of 270 h.p. and the total cabin volume 201 cu ft. • Rotor diam., 35ft; max. length, 42ft 6in;empty weight with standard equipment, 2,065 lb; gross weight, 3,100 lb; max. speed atsi., 122 m.p.h.; cruising speed, 92-120 m.p.h.; hovering ceiling at gross weight at 95 deg F inground effect, 6,500ft; normal range, 226 n.m. Doak Aircraft Co. Inc. 22309 Western Avenue, Torrance, Calif. Model 16 No great amount of informa- tion on this interesting VTOL aircraft has been released, but when the photograph on this page was issued last November it was stated:— "Using the National Aeronautics and SpaceAdministration's High Speed Flight Station at Above, Brantly B-2. Below, Cessna CH- 1C 1 Edwards, the Doak 16 first will make transitionflights. With ducted propellers on wing-tips aimed straight up, the novel aircraft first willrise vertically, then slowly rotate ducts forward in transition to horizontal flight, then rotateducts back and land vertically. It is powered by an 825 h.p. Lycoming T53 shaft turbineengine. Once in air, Doak 16 will operate as conventional airplane with much higher speedand longer range than helicopters. Where air- ports are available it will also take off and landhorizontally as conventional aircraft. This requires less power for take-off and thereforepermits carrying extra fuel loads for even greater range. After transition flights the Doak16 will move into normal airplane category, where higher speeds will be studied." Length, 32ft; gross weight, 2,700 lb. Doman Helicopters Inc. Danbury, Conn. LZ-5 This is an eight-seater helicopter with an unconventional rotor system, de- scribed in our former review (Flight, March 21, 1958). The welded steel tube fuselage is covered with magnesium alloy sheet, and the Lycoming SO-580-A1B engine is installed in the nose. Most of the skinning of the aircraft is non-struc- tural and may be easily removed to con- vert to the stripped configuration for greater payload, repair or refinishing. The ability to utilize the stripped configuration is valuable for cargo operation since it increases the payload by approximately Shown below in hovering flight is the Doak Model 16
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