Boeing

An apparatus comprises a first wall including a first orifice, a first seal component, a second wall including a second orifice, a second seal component, and an interstitial space between the first wall and the second wall. In a sealed configuration, the first seal component extends across the first orifice and the second seal component extends across the second orifice. In a vented configuration, the first seal component and second seal component do not extend across the respective orifices, a passage is defined between the first orifice and the second orifice, and an interior of the passage is fluidically isolated from the interstitial space. A method comprises rupturing a part of a first seal component of an apparatus, forming a passage between a first orifice and a second orifice to fluidically isolate an interior of the passage from an interstitial space, and rupturing a second seal component.

There is provided a portable conduction welding apparatus for conduction welding of thermoplastic composite parts. The welding apparatus includes a support frame assembly, an air pressure assembly, a heating system, and controller(s) having power supply(ies). The air pressure assembly includes a linear pneumatic actuator assembly, a directional air valve assembly, and an air regulator assembly. The heating system includes a first heater assembly with first machined insulation plates, a first machined heater block, first heater element(s), and first thermocouple(s). The second heater assembly includes second machined insulation plates, a second machined heater block, a dovetail connector plate, an air cylinder isolator plate, second heater element(s), and second thermocouple(s). The welding apparatus welds together at a weldline, a first thermoplastic composite part aligned to the first heater assembly and a second thermoplastic composite part aligned to the second heater assembly, by applying force, and conducting heat during a thermal welding cycle.

A design system (214) comprises a computer system (212), a machine learning model system (225) and a design generator (130, 214). The design generator (130, 214) is configured to perform operations. The operations include identifying a reference image (134, 220, 300, 420, 500, 600, 700) of a design (201) of an interior (206) of an aircraft (204); identifying engineering data (137, 221, 380) for the design (201); receiving an element selection (222) of elements in the reference image (134, 220, 300, 420, 500, 600, 700) of the design (201) for modification; generating an enhanced image (135, 224, 314, 423) of the design (201) using the elements (223), the element selection (222), and the machine learning model system (225), wherein the elements in the enhanced image (135, 224, 314, 423) are enhanced elements (223); receiving an element modification (228) for modifying the enhanced elements (223); modifying the enhanced elements (223) using the element modification (228) that takes into account the engineering data (137, 221, 380) using the machine learning model system (225) to form a customized image (136, 229, 370, 425, 504, 604, 704) of the design (201) with modified elements (223) in place of enhanced elements (223); and displaying the customized image (136, 229, 370, 425, 504, 604, 704) on a display system (231). (Fig. 1)

A vehicle includes an internal cabin, a lavatory within the internal cabin, and a system within the lavatory. The system includes a waste flap. A motor is operatively coupled to the waste flap. The motor is configured to move the waste flap between an open position and a closed position. A sensor is configured to detect motion within a detection zone. An image emitter is configured to project one or more images into the detection zone. A control unit is configured to operate the motor to open the waste flap when the sensor detects the motion within the detection zone.

An apparatus comprises a tank and the tank comprises an inner wall configured to hold liquid, an outer wall surrounding the inner wall, and a gap separating the inner wall and the outer wall. The exemplary apparatus further comprises a flow component configured to, in a first mode, flow fluid into the gap and, in a second mode, flow the fluid out of the gap. A system includes the tank, the flow component, and a reservoir. In the first mode, the flow component is configured to flow the fluid from the reservoir into the gap. In the second mode, the flow component is configured to flow the fluid from the gap into the reservoir. A method comprises flowing the fluid into the gap of the tank and flowing the fluid out of the gap.

A structured inspection management system, method, and non-transitory computer-readable medium are disclosed for managing anomalies. The system organizes a plurality of inspection orders, each associated with an anomaly and defining inspection criteria for performing an inspection. The system presents inspection criteria for a selected inspection order and enforces restriction of allowable input to a predefined set of structured inspection responses associated with performance of the inspection. Based on at least one structured inspection response, the system automatically determines and stores an inspection status for the selected inspection order. When the inspection status indicates that the anomaly remains unresolved, the inspection order is maintained in an incomplete state for subsequent inspection or corrective action.

An air conditioning system (106) is configured to provide conditioned air (118) to an internal cabin (120) of an aircraft (100). The air conditioning system (106) includes a first fluid circuit (128) configured to receive bleed air (114), a second fluid circuit (150) configured to receive ambient air (154), and a turbo-compressor (138) including a turbine (182) within the first fluid circuit (128) and a compressor (184) within the second fluid circuit (150). The turbine (182) is coupled to the compressor (184) by a shaft.

An aircraft includes a plurality of sensors. The aircraft also includes a computer system. The computer system is configured to obtain an altitude of the aircraft based on first output of one or more sensors of the plurality of sensors. The computer system is configured to obtain aircraft speed of the aircraft based on second output of one or more sensors of the plurality of sensors. The computer system is configured to compute an estimated true airspeed for the aircraft based on a static temperature estimate, the altitude, and the aircraft speed. The computer system is also configured to provide the estimated true airspeed to one or more flight systems of the aircraft to enable control of the aircraft.

An adhesion promoter composition includes a species that may include BH_x and a solvent. Implementations of the adhesion promoter composition may include a method of providing a stable, surface-modified substrate. The adhesion promoter composition may include a surfactant such as an anionic surfactant, a cationic surfactant, or a nonionic surfactant, such as polyethylene glycol p-(1,1,3,3-tetramethylbutyl)-phenyl ether, a crown ether, a polysorbate, or a combination thereof. The adhesion promoter composition may include an activator such as ferric chloride, trimethyl borate, titanium tetrachloride, or a combination thereof. The species including BH_x or may include ammonia borane, dimethylamine borane, trimethylamine borane, triethylamine borane, dicyclohexylamine borane, ethylenediamine bis-borane, tert-butylamine borane, diphenylphosphine borane, pyridine borane, borohydrides, or a combination thereof.

Techniques for automatically implementing a mode of autonomy for an uncrewed vehicle and a remote controller include:- obtaining contextual input data regarding the uncrewed vehicle; predicting future statuses of operational parameters for the uncrewed vehicle, where the operational parameters are in a plurality of operational categories;- determining a future mode of autonomy for a function that allocates authority over the function between the uncrewed vehicle and the remote controller, where the determining is based on the future statuses of the operational parameters, and wherein the future mode of autonomy is for a time corresponding to the future statuses of the operational parameters- implementing the future mode of autonomy for the function, where the future mode of autonomy allocates a level of control for the function, and allocates a level of override authority for the function- executing, in accordance with the implementing, the function.