Patent
Blades of helicopter rotor - are stabilised by stabilising rods connected to swash plate
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TLDR
In this paper, a model helicopter is stabilised by means of cyclical adjustable blades, which are actuated by a swash plate, and the inclination of the cardan ring corresponds to the cyclical actuation of the stabilising rods.Abstract:
The rotor of a helicopter, especially a model helicopter, is stabilised by means of cyclical adjustable blades (7) which are actuated by means of a swash plate (4). The rotor has three main blades (1) and a corresponding number of stabilising rods (6) which are attached to a swinging cardan ring (5) which is cyclically controlled by the swash plate (4). The inclination of the cardan ring, corresponding to the cyclical actuation of the stabilising rods (6), is transmitted with a phase difference of 90 deg. to the main rotor blades (1). USE - Helicopter rotors.read more
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Helicopter with horizontal control
TL;DR: A helicopter includes a system to effect motion in a horizontal dimension, thereby to direct the desired direction as discussed by the authors, which causes the body to be urged in a relatively horizontal direction from a relative position of rest.
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TL;DR: In this article, an actuator for engaging with a control assembly depending from the auxiliary rotor is presented. But the interaction occurs when the assembly engages with the actuator by a depending arm associated with the assembly.
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TL;DR: In this paper, the main rotor with blades is driven by a rotor shaft and causing a first lift force developed by the rotor when the helicopter is airborne, and these can be wheeled on a floor or ground surface.
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Patent
Airfoil boundary layer control means
TL;DR: A helicopter rotor blade, adjustably mounted for pitch change, has boundary layer control means including operating means including a first member fixed on the blade, and a second member movable on the rotor under the control of restraining means operative in response to conditions of flight independent of the angle of attack of the blade as mentioned in this paper.
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Self-feathering rotary wing
TL;DR: A controllable lifting rotary wing for an aircraft wherein each rotor blade is mounted in such a manner that it has freedom to oscillate in pitch about its feathering axis is described in this article.
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Helicopter rotor with blade trailing edge tabs responsive to control system loading
TL;DR: In this article, a helicopter rotor has blade trailing edge tabs which are actuated in response to control rod loading to reduce or cancel the blade pitching moments imposed upon the blade and hence the control rods by blade aerodynamic and inertial loads, or other loads encountered during rotor operation.