Abstract: In accordance with some embodiments of the present disclosure, a drilling system comprises a rotating control device (RCD). A plurality of sensors included in or in proximity to the RCD are configured to detect drilling conditions associated with the RCD during a drilling operation. A control system is configured to determine an adjustment to a drilling parameter based on the drilling conditions.

Abstract: An aircraft panel assembly comprising a first panel constructed from a first sheet material having a first thermal expansion coefficient, the first panel comprising a first face, a second panel constructed from a second sheet material having a second thermal expansion coefficient different from the first thermal expansion coefficient, the second panel comprising a second face facing the first face, the first and second panels being joined at a first discrete fastening point and a second discrete fastening point, the fastening points being connected by a first notional panel join line describing the shortest distance between the fasteners along the first face, and a second notional panel join line describing the shortest distance between the fasteners along the second face, in which the first panel comprises a stress relief feature between the fastening points such that the first notional panel join line diverges from, and converges with, the second notional panel join line.

Abstract: An aircraft wing cover (10) comprising an integrally stiffened sandwich panel including first and second skins (11, 12) sandwiching a core layer (13), wherein at least one of the skins has a plurality of spanwise extending integral regions of increased thickness (18) accommodated by corresponding regions (19) of decreased thickness in the core. Also, a method of fabricating an aircraft wing cover, and a method of designing an aircraft wing.

Abstract: An aircraft wing cover (10) comprising an integrally stiffened sandwich panel including first and second skins (11, 12) sandwiching a core layer (13), wherein at least one of the skins has a plurality of spanwise extending integral regions of increased thickness (18) accommodated by corresponding regions (19) of decreased thickness in the core. Also, a method of fabricating an aircraft wing cover, and a method of designing an aircraft wing.

Abstract: An aircraft panel assembly comprising a first panel constructed from a first sheet material having a first thermal expansion coefficient, the first panel comprising a first face, a second panel constructed from second sheet material having a second thermal expansion coefficient different to the first thermal expansion coefficient, the second panel comprising a second face facing the first face, the first and second panels being joined at a first discrete fastening point and a second discrete fastening point, the fastening points being connected by a first notional panel join line describing the shortest distance between the fasteners along the first face, and a second notional panel join line describing the shortest distance between the fasteners along the second face, in which the first panel comprises a stress relief feature between the fastening points such that the first notional panel join line diverges from, and converges with, the second notional panel join line.

Abstract: The flowability of fine particle size, rutile titanium dioxide is improved by uniformly mixing 0.05-2% by weight of naphthenic acid with the titanium dioxide.