Browse Topic: Chassis stiffness
It is a unique and challenging task to design a servo-flap main rotor control system that is operational at high density altitudes. At such elevated altitudes, both the main rotor blade and the servo-flap aerodynamics strongly affect helicopter operation. The changes in flap lift alter the aerodynamic pitching moment with respect to the main rotor blade, which results in an interesting blade feathering motion and its required control input. The servo-flap rotor design does not require any pitch link control spring rate. In addition, the blade torsional stiffness and tennis racket moment due to centrifugal force, are almost un-changed by the high altitude air density. The helicopter’s high altitude operation can be achieved through a unique combination of rotor design, servo-flap control, and installed engine power. The servo-flap rotor has a unique ability that allows flap adjustment every time the pilot alters the operating aircraft density altitude by 5,000 feet. This allows the aircraft to retain the same flight characteristics at any altitude that it had at sea level. This unique feature makes the servo-flap rotor one of the best candidates for high altitude flight operation. A new and improved design feature is proposed in this paper. The high altitude actuator control system provides a steady null offset that is simultaneously applied to all flaps. The new actuator signal is introduced in parallel with the basic servo-flap control system. The new hardware is designed to be used within the present control system. This design opens up the autorotation flap control range without impacting servo-flap flight control operation and safety.
Rotor Blades, especially active twist blades, have been investigated by DLR (German Aerospace Center) for many years and the feasibility of this technology was shown in several projects. (1-8) However, many relevant features must be taken into account within the design process. The most challenging aspect is the proper tuning of the structure to integrate the fragile actuators, because they have to sustain a variety of loads, while still providing the expected performance. Further different constraints on bending and torsional stiffness or axes positions of the rotor blade exist. At DLR a tool called SaMaRA (Structural Modelling and Rotor Analysis) was developed. It's a parametric finite element model to meet these partially conflicting requirements as part of a structural optimization framework. The proposed paper provides an overview of the adaption of structural properties and shows representative results for active twist blades.
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