Rohr

An apparatus and method for welding a thermoplastic composite component is provided. The apparatus includes a tool (56) and a power source. The tool (56) includes a heating device (58) energized by the power source and a susceptor (60) spaced from the heating device (58). The susceptor (60) is configured for use in welding thermoplastic composite material and has a Curie temperature close to a susceptor temperature specified to be used during welding. The susceptor (60) is disposed on the tool (56) and includes a susceptor length extending longitudinally along the tool (56). The heating device (58) is configured to induce an electromagnetic field within a susceptor length first portion and second portion. The heating device (58) is configured to heat the first portion to the susceptor temperature and heat the second portion to a second temperature different than the susceptor temperature. The heating device (58) longitudinally overlaps the first portion.

A tool for operating a latch assembly includes a tool body (74), a tab, a first bumper, and a second bumper. The tool body (74) extends lengthwise between a first tool end (76) and a second tool end (78). The tool body (74) further extends between a first lateral end and a second lateral end. The tool body (74) forms a tool interface extending on a pivot axis. The pivot axis extends between the first lateral end and the second lateral end. The tab projects from the tool body (74) at the first tool end (76). The first bumper projects from the tool body (74) at a location between the first tool end (76) and the second tool end (78). The second bumper projects from the tool body (74) between the tab and the first bumper. The tab, the first bumper, and the second bumper project from a common side of the tool body (74).

A method (200) for forming a thermoplastic part includes sulfonating a thermoplastic film by exposing the thermoplastic film to a sulfonation fluid to form a sulfonated thermoplastic film and forming the thermoplastic part with a plurality of stacked thermoplastic film layers. The plurality of stacked thermoplastic film layers include at least one sulfonated thermoplastic film layer of the sulfonated thermoplastic film and a plurality of unsulfonated thermoplastic film layers. The at least one sulfonated thermoplastic film layer forms a first exterior thermoplastic film surface of the thermoplastic part.

A formation method is provided. During the method, a thermoplastic composite (TPC) skin and a lightning strike protection (LSP) layer are provided (502, 504). The TPC skin is arranged (506) with the LSP layer on a tool to provide a material stack, and the material stack is consolidated (508) to form a consolidated TPC structure. A thin film (TF) layer on the consolidated TPC structure using a plasma treatment process (510). The LSP layer may be configured as or otherwise include LSP material, and the TF layer may include a TF material configured as or otherwise including an amine functional group or an epoxy functional group.

A method for joining thermoplastic components comprises providing a first component (22) comprising a first fibre-reinforced thermoplastic composite and a second component (24) comprising a second fibre-reinforced thermoplastic composite. The first and second components (22, 24) are arranged to form a welding zone (46). A discrete welding configuration forming a plurality of discrete welds (54) is selected and the first component (22) is welded to the second component (24) within the welding zone (46) using the selected discrete welding configuration. The plurality of discrete welds (54) may serve as a damage arrestment feature by inhibiting crack formation and propagation in the joined first and second components (22, 24). Preferably, the joined first and second components (22, 24) form an aircraft structure (20).

In a method for joining thermoplastic components, a first component (22) comprising a first fibre-reinforced thermoplastic composite and a second component (24) comprising a second fibre-reinforced thermoplastic composite are provided with a shim assembly (66) arranged at the interface (48) between the first and the second components (22, 24). The shim assembly comprises a shim element (80) and an interface material (82). The first component (22) is welded to the second component (24) through the shim assembly (66) at the interface (48).

An electromechanical actuator is provided that includes a gear box, a ball screw arrangement (52), an electric motor (74), a one-way clutch, an actuator clutch (76), a rotary magnetic damper (78), and a translating cylinder (54). The ball screw arrangement (52) includes a screw shaft (66) and a ball nut. The screw shaft (66) includes a helical groove (72) and ball bearings (70) are disposed between the screw shaft (66) and the ball nut. The screw shaft (66) is coupled with the gear box. The electric motor (74) has a stator (74A), a rotor (74B), and a drive shaft (74C). The one-way clutch is coupled with the EM drive shaft (74C), and is configured to permit rotation of the EM drive shaft (74C) in only a first rotational direction. A first clutch member (76A) of the actuator clutch (76) is coupled with the EM drive shaft (74C) and a second clutch member (76B) is coupled with the gear box. The actuator clutch (76) is disposable in an engaged or in a disengaged configuration.

A nacelle compression rod is provided that includes a central member (78) and first and second rod extensions (80, 82). The central member (78) extends axially between first and second end surfaces (86A, 86B). The first rod extension (80), FRE, extends between an FRE spring end surface and an FRE tip surface. The second rod extension (SRE) extends between an SRE spring end surface and an SRE tip surface. The central member (78) includes a first end bore (92) extending axially into the central member (78) from the first end surface (86A), and a second end bore (94) extending axially into the central member (78) from the second end surface. The first rod extension (80) is partially disposed within the first end bore (92), and is linearly translatable. The second rod extension (82) is partially disposed within the second end bore (94), and is linearly translatable. The first end rod extension is biased axially outward and the second end rod extension is biased axially outward.

A thrust reverser includes an outer fixed structure, an inner fixed structure, a translating sleeve (54), and a blocker door assembly (62). The outer fixed structure (56) and the inner fixed structure (58) extend circumferentially about an axis forming a thrust reverser duct (64). The translating sleeve further forms the thrust reverser duct. The blocker door assembly includes a blocker door (66), a drag link (68), and a clevis fitting (70). The blocker door is pivotably mounted to the translating sleeve. The drag link is pivotably mounted to the blocker door. The clevis fitting includes an articulating fitting member (78), a fixed fitting member (80), and a fixed plate (82). The articulating fitting member is pivotably mounted to the drag link about a first tangentially-extending rotational axis. The articulating fitting member is pivotably mounted to the fixed fitting member about a second axially-extending rotational axis. The fixed fitting member and the fixed plate are mounted to the inner fixed structure.

A lock system (100; 200; 300; 400; 500) is provided including a blade (102; 302; 402), a blade stop (104; 404), a blade actuating member (106; 306; 406), a sensor (110), a controller (120) and an electric motor (108). The blade (102; 302; 402) is retracted past where the blade stop (104; 404) contacts an end of the blade actuating member (106; 306; 406) when the blade (102; 302; 402) is fractured and translated in the direction of a retracted unlocked position from an extended locked position. The sensor (110) can send a signal to the controller (120) based on the position of the blade (102; 302; 402). The controller (120 can determine when the signal from the sensor (110) indicates that the blade (102; 302; 402) has retracted past the point where the blade stop (104; 404) contacts the end of the blade actuating member (106; 306; 406).