Abstract: A wing lock and deployment apparatus for an air launched vehicle includes a driver acted on by a single linear actuation event. The disclosed wing lock and deployment apparatus is capable of unlocking deployable wings of an air launched vehicle, deploying deployable wings of the air launched vehicle from a stored position, and locking deployable wings of the air launched vehicle in a deployed position in sequential order with the one single linear actuation event.

Abstract: In an example, systems and methods for modeling apertures for additive manufacturing is disclosed. In an example, a computing device includes a processor configured to carry out operations. The operations include generating a computational model of a three-dimensional structure. The three-dimensional structure includes a first group of slats including a first plurality of slats substantially parallel to each other along a first axis and a second group of slats comprising a second plurality of slats substantially parallel to each other along a second axis, wherein the second group of slats intersects the first group of slats. The operations include outputting instructions for manufacturing a substrate in accordance with the generated computation model of the three-dimensional structure.

Abstract: A forming system includes a femtosecond laser and a control unit that includes one or more processors operatively connected to the femtosecond laser. The femtosecond laser is configured to emit laser pulses onto an inner surface of a face sheet of an acoustic inner barrel. The acoustic inner barrel includes an acoustic core comprising an array of hexagonal cells attached to an outer surface of the face sheet that is opposite the inner surface. The control unit is configured to control the femtosecond laser to laser drill a plurality of perforations in the face sheet via emitting laser pulses at pulse durations between about 100 femtoseconds and about 10,000 femtoseconds and at frequencies over 100,000 Hz.

Abstract: A forming system includes a femtosecond laser and a control unit that includes one or more processors operatively connected to the femtosecond laser. The femtosecond laser is configured to emit laser pulses onto an inner surface of a face sheet of an acoustic inner barrel. The acoustic inner barrel includes an acoustic core comprising an array of hexagonal cells attached to an outer surface of the face sheet that is opposite the inner surface. The control unit is configured to control the femtosecond laser to laser drill a plurality of perforations in the face sheet via emitting laser pulses at pulse durations between about 100 femtoseconds and about 10,000 femtoseconds and at frequencies over 100,000 Hz such that the perforations are formed without burning portions of the face sheet or the acoustic core surrounding the perforations.

Abstract: A system includes a chamber to receive a powdered material to be used to form an object. The system includes actuators coupled to the chamber. The actuators apply pressure waves to the powdered material in the chamber. The system also includes a controller to activate a plurality of the actuators in a sequence. Activation of the plurality of actuators in the sequence converges pressure waves on a particular volume of powdered material in the chamber to compress the particular volume and to transform at least a portion of the powdered material in the particular volume to solid material of the object.

Abstract: A forming system includes a femtosecond laser and a control unit that includes one or more processors operatively connected to the femtosecond laser. The femtosecond laser is configured to emit laser pulses onto an inner surface of a face sheet of an acoustic inner barrel. The acoustic inner barrel includes an acoustic core comprising an array of hexagonal cells attached to an outer surface of the face sheet that is opposite the inner surface. The control unit is configured to control the femtosecond laser to laser drill a plurality of perforations in the face sheet via emitting laser pulses at pulse durations between about 100 femtoseconds and about 10,000 femtoseconds and at frequencies over 100,000 Hz such that the perforations are formed without burning portions of the face sheet or the acoustic core surrounding the perforations.

Abstract: A heating apparatus for heating a reinforcing layer of a composite material structure is disclosed. The heating apparatus includes a housing having a base and a housing body defining a housing interior space. A radiant heating assembly is disposed within the housing and configured to transfer radiant heat to the reinforcing layer. Additionally, a convection heating assembly is formed within the housing including at least one convection assembly gas passage. The heating apparatus further includes a convection assembly gas outlet coupled to the convection assembly gas passage and a convection assembly gas flows from the convection assembly gas outlet. The convection assembly gas flows along to heat the convection assembly gas. The heating apparatus further includes a redirection gas passage coupled to a redirection nozzle formed at a convection heat application point. A redirection gas flows from the redirection nozzle to direct the convection assembly gas towards the reinforcing layer.

Abstract: A system includes a chamber to receive a powdered material to be used to form an object. The system includes actuators coupled to the chamber. The actuators apply pressure waves to the powdered material in the chamber. The system also includes a controller to activate a plurality of the actuators in a sequence. Activation of the plurality of actuators in the sequence converges pressure waves on a particular volume of powdered material in the chamber to compress the particular volume and to transform at least a portion of the powdered material in the particular volume to solid material of the object.

Abstract: A composite automation method and apparatus for the generation of short path course application of a composite lamina is realized by reconfiguring the functional mechanisms of the fiber placement head. Separating the fiber advance and retract functions, nesting the activation cylinders, and making use of push only activation results in a simplified, compact AFP delivery head. Uniform cutting is provided by a circular configuration fiber cutting blade, were at activation the blade both provides a progressive cutting force and rotates to providing a new cutting edge, and requires limited cutting edge guidance as all orientations cut equally well. The mechanism nested in functions and placed in close proximity to the compaction roller reduces the overall fiber course to the application point.

Abstract: A composite automation method and apparatus for the generation of short path course application of a composite lamina is realized by reconfiguring the functional mechanisms of the fiber placement head. Separating the fiber advance and retract functions, nesting the activation cylinders, and making use of push only activation results in a simplified, compact AFP delivery head. Uniform cutting is provided by a circular configuration fiber cutting blade, were at activation the blade both provides a progressive cutting force and rotates to providing a new cutting edge, and requires limited cutting edge guidance as all orientations cut equally well. The mechanism nested in functions and placed in close proximity to the compaction roller reduces the overall fiber course to the application point.

Abstract: A bonded metal fuselage for aerospace vehicles includes a monocoque structure having an outer metal skin, metal tear straps bonded to the outer skin and metal stringers bonded to the outer skin and to the tear straps. The outer chords of fuselage frames are fastened directly to tear straps and to the skin, obviating the need for clips to fasten the frames to the stringers.

Abstract: A bonded metal fuselage for aerospace vehicles includes a monocoque structure having an outer metal skin, metal tear straps bonded to the outer skin and metal stringers bonded to the outer skin and to the tear straps. The outer chords of fuselage frames are fastened directly to tear straps and to the skin, obviating the need for clips to fasten the frames to the stringers.