Abstract: The present invention relates to antibody-drug conjugates (ADCs) wherein a plurality of active agents are conjugated to an antibody through at least one branched linker. The branched linker may comprise a branching unit, and two active agents are coupled to the branching unit through a secondary linker and the branching unit is coupled to the antibody by a primary linker. The active agents may be the same or different. In certain such embodiments, two or more such branched linkers are conjugated to the antibody, e.g., 2-4 branched linkers, which may each be coupled to a different C-terminal cysteine of a heavy or light chain of the antibody. The branched linker may comprise one active agent coupled to the branching unit by a first branch and a second branch that comprises a polyethylene glycol moiety coupled to the branching unit. In certain such embodiments, two or more such branched linkers are conjugated to the antibody, e.g.

Abstract: A rotor assembly including a fixed fairing including an interface portion and a hub fairing including a depression. The depression is configured to receive at least a portion of the interface portion. The hub fairing is rotatable relative to the fixed fairing.

Abstract: A rotary wing aircraft includes a single main rotor hub configured to receive a rotor blade. The rotor blade includes a blade root, a blade tip, and a blade body. The blade body includes a leading edge and a trailing edge and defines a feathering axis. The leading edge and the trailing edge each include a first portion and a second portion that extend toward a first direction and a second portion, respectively. At a given radial location along the feathering axis, a local twist angle changes from a positive value to a negative value, a chord length decreases in value, a distance between the trailing edge and the feathering axis decreases in value, and the first portion of the leading edge extends toward the first direction. The rotor blade assembly also includes a trailing edge assembly having a trailing edge flap configured to be selectively deployed by an actuator.

Abstract: A rotor blade assembly includes a rotor blade having inboard and outboard regions, a blade body, and an internal spar, the blade body defining leading and trailing edges. A trailing edge assembly extends from and is connected to the trailing edge, and has a trailing edge flap and an actuator configured to deploy the trailing edge flap between first and second positions. In one of the first and second positions, an upper surface of the trailing edge flap conforms in profile to an upper surface of the rotor blade, and in the other, the trailing edge flap is inclined relative to the blade. During hovering flight, at least one trailing edge flap segment is deflected to enhance hover performance. During forward flight, at least one trailing edge flap segment is either not deflected for reduced effect on forward flight or is deflected for additional thrust.

Abstract: A rotary wing aircraft and a rotor assembly of a rotary wind aircraft is disclosed. The rotary wing aircraft includes at least one engine, and the rotor assembly is coupled to the at least one engine. The rotor assembly includes a first rotor hub, a second rotor hub, and a shaft fairing between the first rotor hub to the second rotor hub, the shaft fairing defined by a chord that varies between the first rotor hub and the second rotor hub.

Abstract: A rotor assembly includes a first rotor hub and a second rotor hub. The second rotor hub is coupled to the first rotor hub via a shaft fairing. The first rotor hub has a flat first surface coupled to the shaft fairing and a curved second surface opposite the flat first surface. The second rotor hub has a flat first surface on the lower side and a curved second surface opposite the flat first surface.

Abstract: A rotor blade for a rotary wing aircraft and a tip for the rotor blade. The rotor blade includes a blade root, a blade tip and a blade body that extends from the blade root to the blade tip. The blade tip includes: a continuously swept leading edge, a compound trailing edge, and a continuous anhedral.

Abstract: A rotary wing aircraft and a rotor assembly of a rotary wind aircraft is disclosed. The rotary wing aircraft includes at least one engine, and the rotor assembly is coupled to the at least one engine. The rotor assembly includes a first rotor hub, a second rotor hub, and a shaft fairing between the first rotor hub to the second rotor hub, the shaft fairing defined by a chord that varies between the first rotor hub and the second rotor hub.

Abstract: A rotor assembly includes a first rotor hub and a second rotor hub. The second rotor hub is coupled to the first rotor hub via a shaft fairing. The first rotor hub has a flat first surface coupled to the shaft fairing and a curved second surface opposite the flat first surface. The second rotor hub has a flat first surface on the lower side and a curved second surface opposite the flat first surface.

Abstract: A rotor blade for a rotary wing aircraft and a tip for the rotor blade. The rotor blade includes a blade root, a blade tip and a blade body that extends from the blade root to the blade tip. The blade tip includes: a continuously swept leading edge, a compound trailing edge, and a continuous anhedral.

Abstract: A boundary layer ingesting (BLI) blade having a span is provided and includes a root section connectable to a hub, a tip section disposable at a distance from the hub and having a pitch and a body extending in a spanwise dimension from the root section to the tip section. The root section has a local pitch from the root section to about a 70% span location, which is less than the pitch at the tip section, to thereby reduce local angles of attack in a boundary layer region defined in and around the root section.

Abstract: A boundary layer ingesting (BLI) blade having a span is provided and includes a root section connectable to a hub, a tip section disposable at a distance from the hub and having a pitch and a body extending in a spanwise dimension from the root section to the tip section. The root section has a local pitch from the root section to about a 70% span location, which is less than the pitch at the tip section, to thereby reduce local angles of attack in a boundary layer region defined in and around the root section.