摘要:
An application system includes one or more flow control mechanisms controlling a flow path to a dispenser device, one or more position control mechanisms controlling a position of the dispenser device, and a memory device storing data associated with the flow control mechanisms, the position control mechanisms, one or more target areas, and computer-executable instructions. The computer-executable instructions may be executed to identify a target area, actuate the position control mechanisms to move the dispenser device toward the target area, actuate the flow control mechanisms to channel the sealant materials toward the dispenser device, dispense one or more first shots of the sealant materials onto the target area using the dispenser device for forming a dollop at the target area, and dispense one or more second shots of the sealant materials onto the target area using the dispenser device for forming a sealant layer that overlies the dollop.
摘要:
An aircraft includes a fuselage including a plurality of frame members disposed at predetermined intervals in a longitudinal direction of the fuselage and a plurality of stringers extending substantially linearly in the longitudinal direction. The fuselage defines an aircraft interior. A compartment is located in the interior of the fuselage. The compartment defines an interior area. A first one window assembly is mounted to an upper portion of the fuselage for introducing daylight into the interior area. The first window assembly is flanked by adjacent frame members of the plurality of frame members and adjacent stringers of the plurality of stringers. The first window assembly includes a window pane, an inner cover and a retainer. The inner cover introduces daylight from the window pane into the interior area. The retainer secures the window pane and the inner cover to the fuselage.
摘要:
A composition having a composite material having a polymer with about 1% to about 3% by weight thin-graphite materials dispersed therein; the thin-graphite materials having diameters less than or equal to 2 microns and a surface area greater than or equal to about 300 m2 per gram; and the composite material having a tensile modulus that is at least 25% greater than the unfilled polymer.
摘要:
The ice prevention system of the present invention utilizes, in combination, a de-ice subsystem and anti-ice subsystem in a new configuration on an aircraft with engines located behind its wings. Depending on the vertical location of the engines with respect to the wings, the anti-ice subsystem is configured on an upper or lower portion of a leading edge of the wings. If the engine is located above the wing, the anti-ice system is configured only on a section of the wing aligned with the engine and only on the upper portion of the leading edge. If the engine is located below the wing, the placement of anti-ice system is reversed. The de-ice subsystem is configured on the opposite portion of the leading edge adjacent to the anti-ice subsystem and on the remainder of the leading edge of the wing.
摘要:
A hydraulic system for an aircraft includes a brake operation device, a pressure supply, a reservoir, a shut-off valve, and a wheel brake. The shut-off valve is in fluid communication with and is disposed between the pressure supply and the brake valve. The shut-off valve can include a poppet, a first valve seat and a second valve seat. Movement of the poppet is controlled by operation of the brake operation device. The poppet is movable between a first position where the poppet acts against the first valve seat and a second position where the poppet acts against the second valve seat. In the first position, fluid flow is blocked between the pressure supply and the brake valve through the shut-off valve. In the second position, fluid flow is allowed between the pressure supply and the brake valve through the shut-off valve. The wheel brake is in fluid communication with and downstream from the shut-off valve.
摘要:
A fuel transfer system for an aircraft includes an upper tank, a lower tank, a fuel transfer line connecting the upper tank to the lower tank, an upper fuel transfer line outlet in the lower tank, a lower fuel transfer line outlet in the lower tank, an upper float valve associated with the upper fuel transfer line outlet, and a lower float valve associated with the lower fuel transfer line outlet. The upper fuel transfer line outlet, which is in the lower tank, is in fluid communication with the upper tank. The lower fuel transfer line outlet, which is located in the lower tank, is in fluid communication with the upper tank.
摘要:
A method of fabricating quantum confinements is provided. The method includes depositing, using a deposition apparatus, a material layer on a substrate, where the depositing includes irradiating the layer, before a cycle, during a cycle, and/or after a cycle of the deposition to alter nucleation of quantum confinements in the material layer to control a size and/or a shape of the quantum confinements. The quantum confinements can include quantum wells, nanowires, or quantum dots. The irradiation can be in-situ or ex-situ with respect to the deposition apparatus. The irradiation can include irradiation by photons, electrons, or ions. The deposition is can include atomic layer deposition, chemical vapor deposition, MOCVD, molecular beam epitaxy, evaporation, sputtering, or pulsed-laser deposition.
摘要:
A fuel transfer system for an aircraft includes an upper tank, a lower tank, a fuel transfer line connecting the upper tank to the lower tank, an upper fuel transfer line outlet in the lower tank, a lower fuel transfer line outlet in the lower tank, an upper float valve associated with the upper fuel transfer line outlet, and a lower float valve associated with the lower fuel transfer line outlet. The upper fuel transfer line outlet, which is in the lower tank, is in fluid communication with the upper tank. The lower fuel transfer line outlet, which is located in the lower tank, is in fluid communication with the upper tank.