A system and process for bonding involves a pocket made into one article is used to secure that article to another using a flowable, curable material (e.g., resin) which during saturation enters through a passageway and at least partially fills the void. When the article is cured, the article is bonded to another article to which resin has also been applied since the void (now containing cured material) is larger than the passageway.

A system and process for bonding involves a pocket made into one article is used to secure that article to another using a flowable, curable material (e.g., resin) which during saturation enters through a passageway and at least partially fills the void. When the article is cured, the article is bonded to another article to which resin has also been applied since the void (now containing cured material) is larger than the passageway.

A polymer composite composition for use in high temperature applications such as furnaces, heat shields and aeronautical jet and rocket motors. In a particular application, the disclosed composition is applied to the manufacture of rocket motor cases, or parts thereof, to provide rigid thermal protection (RTP). The polymer composite composition comprises cyanate ester resin, fine lengths of carbon fibre and refractory filler material.

The disclosure relates to a component device, in particular for a primary supporting component of an aircraft, which comprises a first component element, a second component element, a bonding providing a connection between the first component element and the second component element, a marker substance device configured to dispense a volatile marker gas to the environment when in contact with the surrounding air and being hermetically sealed from the surrounding air by the first component element, the second component element, and/or the bonding if the bonding is not damaged, and a detector device configured to detect the marker gas dispensed by the marker substance device.

The disclosure relates to a component device, in particular for a primary supporting component of an aircraft, which comprises a first component element, a second component element, a bonding providing a connection between the first component element and the second component element, a marker substance device configured to dispense a volatile marker gas to the environment when in contact with the surrounding air and being hermetically sealed from the surrounding air by the first component element, the second component element, and/or the bonding if the bonding is not damaged, and a detector device configured to detect the marker gas dispensed by the marker substance device.

Composite laminate structures are produced using partially cured parts. Partial curing of the parts is achieved by applying a catalyst to regions of the parts that are to be fully cured. These regions cure at a lower-than-normal temperature while remaining regions of the part remain uncured, allowing them to be co-bonded or co-cured to other structures.

Composite laminate structures are produced using partially cured parts. Partial curing of the parts is achieved by applying a catalyst to regions of the parts that are to be fully cured. These regions cure at a lower-than-normal temperature while remaining regions of the part remain uncured, allowing them to be co-bonded or co-cured to other structures.

In a 3D printing method, a coalescent dispersion for forming a 3D object is selected. The dispersion includes an aqueous vehicle and an infrared or near-infrared binding agent dissolved or dispersed therein. The binding agent is a phthalocyanine having a polar group attached to each side chain or a naphthalocyanine having a polar group attached to each side chain. A sinterable material is deposited and heated to a temperature ranging from about 50 C to about 350 C. The dispersion is selectively applied on at least a portion of the sinterable material. The sinterable material and the dispersion applied thereon are exposed to infrared or near-infrared radiation. The binding agent absorbs the radiation and converts it to thermal energy. At least the portion of the sinterable material in contact with the binding agent is at least cured to form a first layer of the 3D object.

The present disclosure describes a three-dimensional object. The three-dimensional object includes a light polymerized body, at least one internal chamber residing within the light polymerized body, the at least one internal chamber having at least one frangible wall, and a curable component contained within the at least one internal chamber. The three-dimensional object may further include at least one channel extending inwardly from an outer surface of the light polymerized body toward the internal chamber and at least a portion of the at least one channel being adjacent to the at least one frangible wall of the at least one internal chamber. Methods of bonding an insertable object to a three-dimensional object and kits are also described.

The present disclosure describes a three-dimensional object. The three-dimensional object includes a light polymerized body, at least one internal chamber residing within the light polymerized body, the at least one internal chamber having at least one frangible wall, and a curable component contained within the at least one internal chamber. The three-dimensional object may further include at least one channel extending inwardly from an outer surface of the light polymerized body toward the internal chamber and at least a portion of the at least one channel being adjacent to the at least one frangible wall of the at least one internal chamber. Methods of bonding an insertable object to a three-dimensional object and kits are also described.