A device to verify main rotor swashplate positioning includes an inner surface of a first section and a gradient surface of a second section. The gradient surface of the second section may have a plurality of graduation indications. In one implementation, the inner surface of the first section at least partially defines a travel arc that is parallel to and concentric with the inner surface. In such an implementation, the device may be configured to move along the travel arc as it rotates about a collective sleeve to contact a swashplate lug.

An inertia weight assembly positionable within a receiving portion of a rotor blade for use on a rotorcraft. The inertia weight assembly includes a weighted core and a casing having a closed outboard end and forming a cavity. The weighted core is disposed in the cavity such that the casing at least partially encloses the weighted core. The weighted core is formed from a first material and the casing is formed from a second material that is dissimilar to the first material. The casing provides an interface between the weighted core and the receiving portion of the rotor blade. The second material is more bondable to the receiving portion of the rotor blade than the first material.

The present invention discloses a multi-rotor aircraft with a multi-axis misalignment layout, which comprises a frame, a plurality of upper power sources, a plurality of lower power sources, a plurality of upper propellers, and a plurality of lower propellers. The plurality of upper propellers are provided at intervals and are connected to the upper part of the frame through the plurality of upper power sources. The plurality of lower propellers are provided at intervals and are connected to the lower part of the frame through the plurality of lower power sources. In the vertical projection direction of the frame, the plurality of upper propellers and the plurality of lower propellers are staggered. The upper propellers and the lower propellers are staggered so that the pitch between the upper propellers and the lower propellers is large.

A balance weight assembly for a rotor blade of a rotorcraft. The balance weight assembly includes a balance weight pocket formed by a balance weight tray and a cover. The balance weight tray has an upper surface including a lip region extending outwardly from a projected region with an outboard boss. A balance weight receiving cavity is recessed from the upper surface and contains a plurality of balance weights. The projected region is disposed within an opening in a hollow blade spar such that the outboard boss of the balance weight tray has a contact relationship with an outboard surface of the opening. The cover is coupled to the balance weight tray such that the lip region of the balance weight tray and at least a portion of the cover have a clamping relationship with the blade spar, thereby coupling the balance weight pocket to the blade spar.

In an implementation, a rotor blade (alternatively referred to herein as blade) for a helicopter or other aircraft may include an outer layer. The outer layer may define a cavity. The outer layer may at least partially correspond to an airfoil, e.g., a wing. One or more inserts may be included within the cavity and be encompassed thereby. The first insert may have a density of at least 0.6 pounds per cubic inch.

In an implementation, a rotor blade for a helicopter may include an outer layer. The outer layer may have a leading edge region and a trailing edge region and may define a cavity. The leading edge region may include a first shape at least partially corresponding with an airfoil, e.g., a wing. An insert may be included within the cavity and be encompassed thereby. The insert may include a shape that substantially corresponds with the first shape, e.g., the insert may substantially correspond with a leading edge of an airfoil. The insert may have a plurality of weight shot each of which may be surrounded by a binding agent.

In an embodiment, an apparatus includes: a gearbox including: a housing having an opening; an input pinion disposed in the housing; a moving feature mechanically coupled to the input pinion, the moving feature and the input pinion being operable to convert between power and torque; and first sensors disposed on the moving feature, the first sensors having batteries, where the moving feature is operable to rotate about a common axis, each of the first sensors being exposed by the opening as the moving feature rotates about the common axis.

A rotor blade is provided that includes an airfoil extending spanwise from a base to a tip. The airfoil extends longitudinally (e.g., chordwise) from a leading edge to a trailing edge. The airfoil extends laterally between a first side and a second side. The airfoil includes a body and a weight. The body includes a plurality of body layers. Each of the body layers includes fiber reinforcement within a body thermoplastic matrix. The weight includes a weight layer embedded within the body. The weight layer includes metal powder within a weight thermoplastic matrix.

A multi-blade rotor of a rotary wing aircraft, the multi-blade rotor comprising at least one rotor blade that defines a pitch axis and that is provided with an associated pitch-control lever that is operatively coupled to a pitch link rod, the pitch link rod defining a longitudinal axis, wherein the associated pitch-control lever comprises an accommodation that is located on the longitudinal axis of the pitch link rod at a predetermined distance from the pitch axis of the at least one rotor blade, the pitch link rod being operatively coupled to the associated pitch-control lever at the accommodation of the associated pitch-control lever, wherein the predetermined distance is adjustable in order to enable adjustment of track and balance of the multi-blade rotor.

The present invention includes a span-balance pocket in a surface of a rotor blade, the span-balance pocket including an inboard surface and an outboard surface; and one or more weights disposed in the span-balance pocket to span-balance the rotor blade; and at least one of one or more retention devices to retain the one or more weights against the outboard surface of the span-balance pocket or the span-balance pocket is machined or molded into a tip block of the rotor blade.