A rotor system includes a rotor duct; at least one rotor blade that includes an outboard end; a tip extension mechanism affixed at the outboard end of the at least one rotor blade, the tip extension mechanism including at least one shim, the at least one rotor blade with the tip extension mechanism affixed thereto including an extended rotor blade; and a blade tip affixed to an outboard end of the extended rotor blade, wherein the blade tip is affixed to the extended rotor blade via at least one removable fastener.

A duct for a ducted-rotor aircraft may include an internal structure and an aerodynamic exterior skin that is adhesively bonded to the internal structure. The skin may include a leading-edge portion disposed at an inlet of the duct and an inner portion disposed along an interior of the duct. The inner portion of the skin may be bonded to the internal structure with a first bondline of adhesive and the leading-edge portion of the skin may be bonded to the inner portion of the skin with a second bondline of adhesive. One or both of the first and second bondlines of adhesive may be of non-uniform thickness to take up tolerance stackups between the inner portion of the skin, the leading-edge portion of the skin, and the internal structure.

In one aspect, the present disclosure provides a system for reducing vibrations or stresses in a rotor blade system. The system may include at least three rotor blades configured to be rotated about a main rotor axis, where each of the three rotor blades may be adjusted by at least one electrically-adjustable control rod of a plurality of control rods. The plurality of control rods may include a first number of control rods forming a first group, and the plurality of control rods may include a second number of control rods forming a second group. A first circuit for may activate or deactivate the first group of control rods, and a second circuit may activate or deactivate the second group of control rods.

In one aspect, the present disclosure provides a system for reducing vibrations or stresses in a rotor blade system. The system may include at least three rotor blades configured to be rotated about a main rotor axis, where each of the three rotor blades may be adjusted by at least one electrically-adjustable control rod of a plurality of control rods. The plurality of control rods may include a first number of control rods forming a first group, and the plurality of control rods may include a second number of control rods forming a second group. A first circuit for may activate or deactivate the first group of control rods, and a second circuit may activate or deactivate the second group of control rods.

A method for improving performance in an aircraft having a winglet coupled to a wing, the winglet having a leading edge and a trailing edge continuously transitioning from a leading edge and trailing edge of the wing. The method includes coupling a wing tip to the winglet. The wing tip may include a curved leading edge from the winglet leading edge to a leading end point, a curved trailing edge from a winglet trailing edge to a trailing end point, and an end segment connecting the leading end point and the trailing end point. The end segment may be swept back from the trailing end point to the leading end point at an end segment angle.

A bond assembly includes a fixture having a first section movably coupled to a second section. The first section and the second section are disposed opposite one another. A bladder assembly is mounted to at least one of the first section and the second section. The bladder assembly is configured to apply controlled, localized pressure and heat to a component receivable between the first section and the second section.

A bond assembly includes a fixture having a first section movably coupled to a second section. The first section and the second section are disposed opposite one another. A bladder assembly is mounted to at least one of the first section and the second section. The bladder assembly is configured to apply controlled, localized pressure and heat to a component receivable between the first section and the second section.

A replacement tip section for a rotor blade, from which a legacy tip section was removed, includes a blade tip portion configured to be attached to an intermediate section of the rotor blade after removal of the legacy section. The intermediate section has a connection feature at an end of the intermediate section to which the blade tip portion is attachable. The replacement tip section includes a transition region configured to be attached to a forward end of the connection feature. The transition region is configured to form a leading edge of the rotor blade and extends from the blade tip portion to form an opening into which the intermediate section is attached. The transition region includes a first end having a first airfoil that conforms to the intermediate section airfoil at the connection feature, and a second end having a second airfoil that conforms to the blade tip portion.

A vehicle having an energy conversion system for converting wind energy into electrical energy includes a rotor with a rotor axis of rotation, which is oriented substantially parallel to the longitudinal axis of the vehicle or forms an acute angle with the longitudinal axis, wherein the energy conversion system is closer to the rear end than to the front end of the vehicle. Also described is a trailer comprising an energy conversion system for converting wind energy into electrical energy. In addition, an aircraft is described, including an energy conversion system for converting wind energy into electrical energy. Moreover, the energy conversion system is usable to improve the driving characteristics of vehicles. A headwind deflection system for vehicles also includes an energy conversion system for converting wind energy into electrical energy, comprising a rotor, a flow channel and a wind funnel. In addition, a kit of parts may include a vehicle and the headwind deflection system.

A bond fixture includes a support structure and a first assembly coupled to the support structure. The first assembly includes a frame defining a chamber and a first pressure pad and second pressure pad coupled to the frame opposite one another and positioned within the chamber. The second pressure pad is movable to control a pressure applied by the first pressure pad and the second pressure pad.