Abstract: A reconsolidated bamboo beam-column joint connected by a subassembly and a design method thereof are provided. Rectangular shear steel plates and vertical steel plates in embedded steel plates form an H-shaped section, and left and right ends of the vertical steel plates are embedded in mortises of a reconsolidated bamboo column and a reconsolidated bamboo beam respectively, thereby effectively improving bearing capacity of the joint. A half tenon is provided with an elliptical bolt hole in a penetrating manner and connected to the reconsolidated bamboo column by a bolt, and the half tenon is rotatable along a center of the elliptical bolt hole and movable along a long axis of the elliptical bolt hole, so that the energy is dissipated through friction between the reconsolidated bamboo half tenon and mortises, excellent energy consumption ability of the half tenon structure is exerted, and the anti-pulling resistance of the tenon is improved.

Abstract: Involved is an isolated antigen binding protein, being capable of binding CCR8 derived from a primate animal. Further involved are a pharmaceutical composition comprising the antigen binding protein, and an application of the antigen binding protein and/or the pharmaceutical composition in the prevention and/or treatment of a tumor or a cancer.

Abstract: A compression rod engagement apparatus is provided that includes an engagement feature, an engagement feature pin, and a mounting member. The engagement feature is attached to the engagement feature pin. The engagement feature pin is engaged with the mounting member in a home position and axial travel of the engagement feature pin along a lengthwise axis away from the home position in either axial direction is resisted by at least one spring force.

Abstract: A mechanical connection system is provided that includes a ceramic skin panel, at least one bushing, and at least one bolt. The ceramic skin panel includes a first surface, a second surface, and at least one aperture extending between the first surface and the second surface. The aperture has an axial centerline, a chamfered portion contiguous with the first surface, and an axial portion contiguous with the second surface. The chamfered portion includes a tapered surface disposed at a first angle such that a line extending along the tapered surface intersects the axial centerline at a plane of the second surface. The bushing has a housing and a collar. The housing is configured to mate with the chamfered portion of the aperture disposed within the ceramic skin panel. The collar is configured for engagement with the housing.

Abstract: An aircraft nacelle arrangement includes a compression rod disposed between a first nacelle half and a second nacelle half, wherein the first nacelle half and the second nacelle half are rotatable about a hinge between a closed position and an open position, a compression rod disposed between the first nacelle half and the second nacelle half, and a mounting bracket coupled to an exhaust nozzle flange of the aircraft engine, wherein the compression rod extends through the mounting bracket.

Abstract: An aircraft nacelle arrangement includes a compression rod disposed between a first nacelle half and a second nacelle half, wherein the first nacelle half and the second nacelle half are rotatable about a hinge between a closed position and an open position, a compression rod disposed between the first nacelle half and the second nacelle half, and a mounting bracket coupled to an exhaust nozzle flange of the aircraft engine, wherein the compression rod extends through the mounting bracket.

Abstract: A mechanical connection system is provided that includes a ceramic skin panel, at least one bushing, and at least one bolt. The ceramic skin panel includes a first surface, a second surface, and at least one aperture extending between the first surface and the second surface. The aperture has an axial centerline, a chamfered portion contiguous with the first surface, and an axial portion contiguous with the second surface. The chamfered portion includes a tapered surface disposed at a first angle such that a line extending along the tapered surface intersects the axial centerline at a plane of the second surface. The bushing has a housing and a collar. The housing is configured to mate with the chamfered portion of the aperture disposed within the ceramic skin panel. The collar is configured for engagement with the housing.

Abstract: A nacelle for an aircraft propulsion system includes a core cowl portion, a bifurcation portion and an extension portion. The core cowl portion extends about a centerline to the bifurcation portion. The bifurcation portion is connected to and extends radially between the core cowl portion and the extension portion. The extension portion projects out from the bifurcation portion and circumferentially extends over the core cowl portion. The extension portion includes an acoustic panel and a structural reinforcement. The acoustic panel includes a cellular core between a perforated face skin and a back skin, wherein the face skin is radially inboard of the back skin. The structural reinforcement is bonded to the back skin and structurally reinforces the acoustic panel.

Abstract: A nacelle is provided for an aircraft propulsion system. This nacelle include a nacelle structure, a fanlet and an interface assembly. The fanlet is configured to translate axially along a centerline between an open position and a closed position. The interface assembly includes first and second interlocking components. One of the interlocking components is mounted to the nacelle structure, and the other one of the interlocking components is mounted to the fanlet. The first interlocking component includes a projection configured with a stop. The second interlocking component includes an aperture and a detent. The projection is adapted to extend axially into the aperture. The detent is adapted to engage the stop where the fanlet is in the closed position.

Abstract: A compression rod engagement apparatus is provided that includes an engagement feature, an engagement feature pin, and a mounting member. The engagement feature is attached to the engagement feature pin. The engagement feature pin is engaged with the mounting member in a home position and axial travel of the engagement feature pin along a lengthwise axis away from the home position in either axial direction is resisted by at least one spring force.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a fanlet and a track system configured to enable axial translation of the fanlet along a centerline between an open position and a closed position. The track system includes a first component, a second component and a lock. One of the first and the second components is configured as or otherwise includes a slider. The other one of the first and the second components is configured as or otherwise includes a track. The slider is mated with and configured to slide axially along the track. The lock is configured as or otherwise includes a bolt mounted with the first component. The lock is configured to move the bolt laterally into an aperture in the second component to prevent axial translation of the fanlet.

Abstract: A nacelle is provided for an aircraft propulsion system. This nacelle include a nacelle structure, a fanlet and an interface assembly. The fanlet is configured to translate axially along a centerline between an open position and a closed position. The interface assembly includes first and second interlocking components. One of the interlocking components is mounted to the nacelle structure, and the other one of the interlocking components is mounted to the fanlet. The first interlocking component includes a projection configured with a stop. The second interlocking component includes an aperture and a detent. The projection is adapted to extend axially into the aperture. The detent is adapted to engage the stop where the fanlet is in the closed position.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a fanlet and a track system configured to enable axial translation of the fanlet along a centerline between an open position and a closed position. The track system includes a first component, a second component and a lock. One of the first and the second components is configured as or otherwise includes a slider. The other one of the first and the second components is configured as or otherwise includes a track. The slider is mated with and configured to slide axially along the track. The lock is configured as or otherwise includes a bolt mounted with the first component. The lock is configured to move the bolt laterally into an aperture in the second component to prevent axial translation of the fanlet.

Abstract: A nacelle for an aircraft propulsion system includes a core cowl portion, a bifurcation portion and an extension portion. The core cowl portion extends about a centerline to the bifurcation portion. The bifurcation portion is connected to and extends radially between the core cowl portion and the extension portion. The extension portion projects out from the bifurcation portion and circumferentially extends over the core cowl portion. The extension portion includes an acoustic panel and a structural reinforcement. The acoustic panel includes a cellular core between a perforated face skin and a back skin, wherein the face skin is radially inboard of the back skin. The structural reinforcement is bonded to the back skin and structurally reinforces the acoustic panel.

Abstract: A ceramic turbine engine exhaust component, such as a ceramic matrix composite (“CMC”) exhaust center body may be positioned around a metallic attachment ring. The attachment ring may have a greater coefficient of thermal expansion than the CMC center body. A plurality of bolts radially-spaced around the circumference of the attachment ring may be inserted through apertures in the center body with a sliding fit, and may be coupled to the attachment ring. The bolts may slide within the apertures, allowing the attachment ring to thermally expand without applying extra loads on the exhaust center body due to the expansion.

Abstract: A ceramic turbine engine exhaust component, such as a ceramic matrix composite (“CMC”) exhaust center body may be positioned around a metallic attachment ring. The attachment ring may have a greater coefficient of thermal expansion than the CMC center body. A plurality of bolts radially-spaced around the circumference of the attachment ring may be inserted through apertures in the center body with a sliding fit, and may be coupled to the attachment ring. The bolts may slide within the apertures, allowing the attachment ring to thermally expand without applying extra loads on the exhaust center body due to the expansion.