Abstract: A rotor catch system includes a catch stem having a proximal end coupled to a rotor of a mud motor system and a distal end positioned within a sub housing of a drill string, a catch feature having a top portion and a spindle portion extending from the top portion and coupled to the distal end of the catch stem, a housing catch feature extending radially inward from an inner surface of the sub housing, and a catch bushing positioned between the top portion of the catch feature and the housing catch feature. The housing catch feature restrains axial movement of the catch bushing in the active catch state via contact between the catch bushing and the housing catch feature, and the catch bushing restrains axial movement of the catch feature in the active catch state via contact between the catch feature and the catch bushing.

Abstract: A rotor catch system includes a catch stem having a proximal end coupled to a rotor of a mud motor system and a distal end positioned within a sub housing of a drill string, a catch feature having a top portion and a spindle portion extending from the top portion and coupled to the distal end of the catch stem, a housing catch feature extending radially inward from an inner surface of the sub housing, and a catch bushing positioned between the top portion of the catch feature and the housing catch feature. The housing catch feature restrains axial movement of the catch bushing in the active catch state via contact between the catch bushing and the housing catch feature, and the catch bushing restrains axial movement of the catch feature in the active catch state via contact between the catch feature and the catch bushing.

Abstract: An assembly, configured in particular in the form of an aircraft assembly, comprises a plurality of individual components composed of a fibre-reinforced composite material. An edge section of at least one individual component is sealed by means of a sealing tape which contains reinforcing fibres and a curable plastics material.

Abstract: A method for repairing a sandwich composite structure comprising a pinned foam core. In the sub-region in which the pinned foam core is damaged, the at least one upper or lower cover layer is removed as far as the pinned foam. The pinned foam core is removed. A pinned replacement foam core is inserted, the pinned replacement foam core being impregnated with a resin. An upper or lower replacement cover layer is applied. The pinned replacement foam core and optionally the upper or lower replacement cover layer are cured.

Abstract: A fiber composite laying device for manufacturing a fiber composite scrim for forming a fiber composite component, includes a laying head, which is configured to supply a fiber composite band continuously in a supply region. A laying roller is configured to receive the fiber composite band from the supply region to unroll it towards a laying surface and to press it onto the laying surface in a laying region. A press is located between the supply region and the laying region and is configured to press the fiber composite band onto the laying roller in a pressing region. A cutter is configured to cut the fiber composite band to length between the supply region and the pressing region.

Abstract: A method for repairing a sandwich composite structure comprising a pinned foam core. In the sub-region in which the pinned foam core is damaged, the at least one upper or lower cover layer is removed as far as the pinned foam. The pinned foam core is removed. A pinned replacement foam core is inserted, the pinned replacement foam core being impregnated with a resin. An upper or lower replacement cover layer is applied. The pinned replacement foam core and optionally the upper or lower replacement cover layer are cured.

Abstract: A fiber composite laying device for manufacturing a fiber composite scrim for forming a fiber composite component, includes a laying head, which is configured to supply a fiber composite band continuously in a supply region. A laying roller is configured to receive the fiber composite band from the supply region to unroll it towards a laying surface and to press it onto the laying surface in a laying region. A press is located between the supply region and the laying region and is configured to press the fiber composite band onto the laying roller in a pressing region. A cutter is configured to cut the fiber composite band to length between the supply region and the pressing region.

Abstract: The present invention relates to a method of forming a curved prepreg strip or sheet, especially for use in fabricating a composite component. The method includes providing a strip or sheet of prepreg material having reinforcing fibers and drawing or conveying the prepreg material in a travel direction, wherein the material is drawn or conveyed in the travel direction at a speed which differs across a width of the strip or sheet transverse to the travel direction. Similarly, the invention relates to an apparatus for forming a curved prepreg strip or sheet, having: a mechanism for drawing or conveying a strip or sheet of prepreg material in a travel direction, wherein the mechanism is configured to draw or convey the strip or sheet of prepreg material in the travel direction at a speed which differs across a width of the strip or sheet transverse to the travel direction.

Abstract: A strain-hardening cementitious composite (SHCC) can include cement, fly ash (FA), dune sand (DS), and polyvinyl alcohol (PVA) fibers. The amount of DS in the SHCC can be at least 25% by weight. The cement can be Type I ordinary Portland cement, conforming to ASTM C150 specifications. The fly ash can be Class F fly ash (FA). The median particle size of the cement can be 14 ?m. The median particle size of the FA can be 10 ?m.

Abstract: An assembly, configured in particular in the form of an aircraft assembly, comprises a plurality of individual components composed of a fibre-reinforced composite material. An edge section of at least one individual component is sealed by means of a sealing tape which contains reinforcing fibres and a curable plastics material.

Abstract: The fire resistant cementitious composite is an engineered cementitious composite (EEC) having both flexural strength and fire resistant properties. The fire resistant cementitious composite includes a binder mixture formed from Portland cement and fly ash, sand, polyvinyl alcohol fibers, a polycarboxylic ether polymer and water. In the binder mixture, a weight ratio of the fly ash to the Portland cement is between approximately 1.0 and approximately 1.3. A weight ratio of the Portland cement to the sand is between approximately 0.85 and approximately 1.0. A weight ratio of the water to the binder mixture is between approximately 0.28 and approximately 0.33. The sand is preferably Arabian Gulf dune sand.

Abstract: The present invention relates to a method of forming a curved prepreg strip or sheet, especially for use in fabricating a composite component. The method includes providing a strip or sheet of prepreg material having reinforcing fibres and drawing or conveying the prepreg material in a travel direction, wherein the material is drawn or conveyed in the travel direction at a speed which differs across a width of the strip or sheet transverse to the travel direction. Similarly, the invention relates to an apparatus for forming a curved prepreg strip or sheet, having: a mechanism for drawing or conveying a strip or sheet of prepreg material in a travel direction, wherein the mechanism is configured to draw or convey the strip or sheet of prepreg material in the travel direction at a speed which differs across a width of the strip or sheet transverse to the travel direction.