Rohr Patente

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).

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).

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).

A tertiary lock system (20) for an aircraft thrust reverser, comprising: a lock member (22) actuatable between a locked position, in which a loadpath of the lock member (22) engages a movable component (10) to prevent deployment of the thrust reverser, and an unlocked position, in which the lock member (22) permits deployment of the movable component (10) of the thrust reverser; wherein the lock member comprises an element (30) arranged such that at least a portion of the element extends into or through the loadpath of the lock member; and a locking verification system (50) including a sensor module (52) arranged for interrogating the element when the lock member is in the locked position; wherein the locking verification system is configured to: confirm that the tertiary lock system has been commanded to actuate the lock member into the locked position; instruct the sensor module to interrogate the element; and verify that the lock member is in the locked position and the loadpath is uncompromised in response to determining that the element is intact.

A lock system (100) for an aircraft thrust reverser (1) is provided and comprises: a lock shaft (150) moveable along a longitudinal axis (102) in a first direction (104) towards an unlocked position and in a second direction (106) towards a locked position; a solenoid (300) having a body (310) and an armature (320); and a ratchet assembly (200). The ratchet assembly (200) comprises a holding pawl (220) comprising a holding pawl pivot point (223) about which the holding pawl (220) is pivotable, and which is fixed relative to the body (310). The ratchet assembly (200) comprises a driving pawl (230) comprising a driving pawl pivot point (233) about which the driving pawl (230) is pivotable, and which is fixed relative to the armature (320). The ratchet assembly also comprises axially spaced ratchet protrusions (242) fixed relative to the lock shaft (150). The armature (320) is configured to move through a solenoid stroke distance towards the body (310) in the first direction (104) on activation of the solenoid (300), and to move back through the solenoid stroke distance away from the body (310) on deactivation of the solenoid (300). The driving pawl (230) is configured to engage with a ratchet protrusion (242) so as to drive movement of the lock shaft (150) in the first direction (104) on movement of the armature (320) in the first direction (104) and to release from engagement with the ratchet protrusion (242) so as to move relative to the lock shaft (150) on movement of the armature (320) in the second direction (106). The holding pawl (220) is configured to allow the lock shaft (150) to move relative to the body (310) when the driving pawl (230) is driving movement of the lock shaft (150), and to engage with a ratchet protrusion (242) so as to limit axial movement of the lock shaft (150) relative to the body (310) while the driving pawl (230) is moving in the second direction (106).

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A door assembly (26) for an aircraft (20) includes a door (28), a door handle (34), a door hinge (32), a support assembly (50), and a lifting assembly (58). The door handle (34) is rotatable between an unlatched position and a latched position. The support assembly (50) rotatably mounts the door hinge (32) to the door (28). The lifting assembly (58) includes a latch cam (120), a lift track (123), and a latch idler (122). The latch cam (120) is mounted to the door handle (34), rotatable with the door handle (34) about the door handle rotational axis (124), and forms an eccentric roller path (126) extending about the door handle rotational axis (124). The latch idler (122) includes a first roller (146) and a second roller (148). The first roller (146) is disposed on a lift track (123) of the support assembly (50) and configured to roll along the lift track (123). The second roller (148) is disposed within the eccentric roller path (126). The latch idler (122) is configured to lift the door (28) as the door handle (34) rotates from the latched position to the unlatched position.

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An interlock assembly (52) for an aircraft door (28) includes a shaft (54), an interlock first portion (56), and an auto-disarm second portion (58). The shaft (54) is rotatable about a second rotational axis (60) between an armed position and a disarmed position. The shaft (54) includes an interlock cam (64) and an auto-disarm cam (66). In a first interlock position, the interlock first portion (56) permits rotation of the shaft (54) between the armed position and the disarmed position. In a second interlock position, the interlock first portion (56) prevents rotation of the shaft (54) from the disarmed position to the armed position. In a first auto-disarm position, the auto-disarm second portion (58) permits rotation of the shaft (54) between the armed position and the disarmed position. In a second auto-disarm position, the auto-disarm second portion (58) prevents rotation of the shaft (54) from the disarmed position to the armed position.

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A welding assembly (530) is disclosed. The welding assembly (530) includes a plurality of separately controllable actuators (570) (e.g., pneumatic, having an axially movable ram) to press a corresponding portion of a first workpiece (e.g., a discrete flange (512) of a first stiffener (510)) against a second workpiece (e.g., an outer skin (502)) for welding operations (e.g., via induction welding).

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A method for forming a composite propulsion system case includes providing a liner, bonding a thermoplastic film layer to the liner using an adhesive, and, subsequent to bonding the thermoplastic film layer to the liner, depositing a thermoplastic composite material onto the thermoplastic film layer to form an outer shell of the composite propulsion system case. The outer shell extends circumferentially about an axial centerline of the composite propulsion system case. The outer shell forms an outer radial surface of the composite propulsion system case.

An assembly for an aircraft propulsion system (10) includes an upstream cowl (66) and a downstream cowl (68). The upstream cowl (66) extends axially from a first upstream end (70) to a first downstream end (72). The upstream cowl (66) includes an inner barrel panel (74), an outer barrel panel (76), and a bulkhead (82). The bulkhead (82) extends radially between and connects the inner barrel panel (74) and the outer barrel panel (76) at the first downstream end (72). The downstream cowl (68) extends axially from a second upstream end (84) to a second downstream end (86). The downstream cowl (68) includes a cowl panel (92) and a seal assembly (94). The seal assembly (94) includes a seal frame (98) and a seal member (100). The seal frame (98) is mounted to the bulkhead (82). The seal member (100) is mounted to the cowl panel (92). The seal member (100) includes a first radial portion (126) projecting away from the cowl panel (92). The first radial portion (126) is located at the second upstream end (84).

A latch (48) includes a handle (64), a hook (66), a first link (68), and a second link (70). The hook (66) is rotatably mounted to the handle (64) at a first rotational axis (116). The hook (66) includes a hook body (108). The hook body (108) includes a first lateral portion (110) and a second lateral portion (112). The first lateral portion (110) is laterally spaced from the second lateral portion (112). The first link (68) is laterally between the first lateral portion (110) and the second lateral portion (112). The first link (68) is rotatably mounted to the first lateral portion (110) and the second lateral portion (112) at the first rotational axis (116). The second link (70) is laterally between the first lateral portion (110) and the second lateral portion (112). The second link (70) is rotatably mounted to the first link (68) at a second rotational axis (172). The second link (70) is configured for translation relative to the first lateral portion (110) and the second lateral portion (112).

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An end effector (102, 202, 302) for the through thickness reinforcement of a fibrous preform (110) includes a needle cleaning material (220, 320) configured to contact a needle (108, 208, 308) to clean resin from the needle during or between through thickness reinforcement operations. The needle cleaning material may extend from a presser foot toward the needle. The needle cleaning material may slidingly engage the needle in response to movement of one of the needle or the presser foot moving (e.g., translating and/or rotating) with respect to the other of the needle or the presser foot.

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