Abstract: Stiffened skin panels comprise alternating truss core portions and solid laminate portions sandwiched between inner and outer facesheets, all formed from a fiber reinforced thermoplastic. The components of the panels are co-consolidated using induction heating. The panels are stiffened with spars fastened to the solid laminate portions.

Abstract: A movable surface of an aircraft has a front spar extending along a spanwise direction between opposing movable surface ends. The movable surface also includes a plurality of ribs defining a plurality of bays between adjacent pairs of the ribs. Each rib extends between the front spar and a trailing edge portion of the movable surface. The movable surface further includes an upper and a lower skin panels coupled to the ribs and the front spar. In addition, the bull surface includes a plurality of bead stiffeners coupled to an inner surface of at least one of the upper skin panel and the lower skin panel. The bead stiffeners within the bays are spaced apart from each other and are oriented non-parallel to the front spar and have a bead stiffener cap having opposing cap ends respectively locate proximate the front spar and the trailing edge portion.

Abstract: Examples are disclosed herein that relate to vehicles, composite parts, and three-dimensional (3D) textile preforms for composite parts. In one example, a 3D textile preform for a composite part comprises a flange portion and a stiffener portion extending upwardly from the flange portion. The stiffener portion comprises a first wall portion that extends from the flange portion and a second wall portion that extends from the flange portion at a location spaced from the first wall portion. A connecting portion connects the first wall portion and the second wall portion at a location spaced from the flange portion.

Abstract: A window clamp system and method are to secure a window pane to a window frame of a vehicle. The window clamp system includes a mounting bracket configured to be secured to the window frame, one or more ratchets coupled to the mounting bracket, and a spring clip configured to move in relation to the mounting bracket and the one or more ratchets. The spring clip is configured to engage a seal positioned around the window pane.

Abstract: A movable surface of an aircraft has a front spar extending along a spanwise direction between opposing movable surface ends. The movable surface also includes a plurality of ribs defining a plurality of bays between adjacent pairs of the ribs. Each rib extends between the front spar and a trailing edge portion of the movable surface. The movable surface further includes an upper and a lower skin panels coupled to the ribs and the front spar. In addition, the bull surface includes a plurality of bead stiffeners coupled to an inner surface of at least one of the upper skin panel and the lower skin panel. The bead stiffeners within the bays are spaced apart from each other and are oriented non-parallel to the front spar and have a bead stiffener cap having opposing cap ends respectively locate proximate the front spar and the trailing edge portion.

Abstract: Systems and processes that integrate thermoplastic and shape memory alloy materials to form an adaptive composite structure capable of changing its shape. For example, the adaptive composite structure may be designed to serve as a multifunctional adaptive wing flight control surface. Other applications for such adaptive composite structures include in variable area fan nozzles, winglets, fairings, elevators, rudders, or other aircraft components having an aerodynamic surface whose shape is preferably controllable. The material systems can be integrated by means of overbraiding (interwoven) with tows of both thermoplastic and shape memory alloy materials or separate layers of each material can be consolidated (e.g., using induction heating) to make a flight control surface that does not require separate actuation.

Abstract: A window clamp system and method are to secure a window pane to a window frame of a vehicle. The window clamp system includes a mounting bracket configured to be secured to the window frame, one or more ratchets coupled to the mounting bracket, and a spring clip configured to move in relation to the mounting bracket and the one or more ratchets. The spring clip is configured to engage a seal positioned around the window pane.

Abstract: A computer-implemented method of determining moisture content of a composite structure is provided. The method includes performing a thermal analysis calculation on the composite structure to determine a temporal surface temperature profile of the composite structure based on temporal environmental parameter profiles, wherein the surface temperature profile is determined independently of a moisture content of the composite structure. The method also includes performing a moisture content analysis calculation on the composite structure to determine a moisture content of the composite structure, wherein the moisture content analysis calculation is based on the determined temporal surface temperature profile and a thickness of the composite structure. The thermal analysis calculation is performed iteratively with a first time period and the moisture content analysis calculation is performed iteratively with a second time period that is longer than the first time period.

Abstract: Methods and systems for determining optical properties for light transmitted mediums are provided. One method includes acquiring one or more measured values indicative of a reflectance for a material, acquiring one or more measured values indicative of a transmittance for the material, and determining a set of calculated values for an index of refraction coefficient and an extinction coefficient from the one or more measured values indicative of reflectance and transmittance, respectively. The method includes identifying a calculated value from the set of calculated values for the index of refraction coefficient and a calculated value from the set of calculated values for the extinction coefficient that are within a threshold determined by the difference between the one or more measured values indicative of the reflectance or transmittance and a predicted reflectance or transmittance, respectively. The method includes determining a reflectance and transmittance for the material using the calculated values.

Abstract: Provided are assemblies having composite structures interlocked with shape memory alloy structures and methods of fabricating such assemblies. Interlocking may involve inserting an interlocking protrusion of a shape memory alloy structure into an interlocking opening of a composite structure and heating at least this protrusion of the shape memory alloy structure to activate the alloy and change the shape of the protrusion. This shape change engages the protrusion in the opening such that the protrusion cannot be removed from the opening. The shape memory alloy structure may be specifically trained prior to forming an assembly using a combination of thermal cycling and deformation to achieve specific pre-activation and post-activation shapes. The pre-activation shape allows inserting the interlocking protrusion into the opening, while the post-activation shape engages the interlocking protrusion within the opening. As such, activation of the shape memory alloy interlocks the two structures.

Abstract: A radius filler includes a plurality of fibers encapsulated in resin and braided into a braided radius filler. The braided radius filler has a substantially triangular shape with concave radius filler side surfaces and a substantially planar radius filler base surface.

Abstract: A computer-implemented method of determining moisture content of a composite structure is provided. The method includes performing a thermal analysis calculation on the composite structure to determine a temporal surface temperature profile of the composite structure based on temporal environmental parameter profiles, wherein the surface temperature profile is determined independently of a moisture content of the composite structure. The method also includes performing a moisture content analysis calculation on the composite structure to determine a moisture content of the composite structure, wherein the moisture content analysis calculation is based on the determined temporal surface temperature profile and a thickness of the composite structure. The thermal analysis calculation is performed iteratively with a first time period and the moisture content analysis calculation is performed iteratively with a second time period that is longer than the first time period.

Abstract: Manufacturing a thermoplastic composite tubular structure embedded with a first load fitting comprising the steps of braiding a first plurality of inner layers of thermoplastic composite material around a soluble, expandable mandrel. A first load fitting is positioned on the first plurality of inner layers of thermoplastic composite material. A second plurality of outer layers of thermoplastic composite material is braided around the first load fitting and the mandrel so as to form an overbraided mandrel embedded with the first load fitting. The overbraided mandrel is installed into a matched tooling assembly and heated at a specified heating profile in order to consolidate the first plurality of inner layers of thermoplastic composite material and the second plurality of outer layers of thermoplastic composite material with the first load fitting so as to form a thermoplastic composite tubular structure embedded with the first load fitting.

Abstract: Systems and processes that integrate thermoplastic and shape memory alloy materials to form an adaptive composite structure capable of changing its shape. For example, the adaptive composite structure may be designed to serve as a multifunctional adaptive wing flight control surface. Other applications for such adaptive composite structures include in variable area fan nozzles, winglets, fairings, elevators, rudders, or other aircraft components having an aerodynamic surface whose shape is preferably controllable. The material systems can be integrated by means of overbraiding (interwoven) with tows of both thermoplastic and shape memory alloy materials or separate layers of each material can be consolidated (e.g., using induction heating) to make a flight control surface that does not require separate actuation.

Abstract: A system and method for harvesting energy from a vehicle, e.g., an aircraft, in operation. A plurality of piezoelectric members are coupled between structural members in the vehicle. A first portion of the plurality of piezoelectric members are non-resonant piezoelectric spacers coupled between structural members subject to a constant load during operation of the vehicle. A second portion of the plurality of piezoelectric members are resonant piezoelectric fillers coupled between structural members subject to a cyclical load during operation of the vehicle. Electrical conversion circuitry is coupled to each of the plurality of piezoelectric members for converting the output of each piezoelectric member to usable electrical energy. The electrical conversion circuitry is coupled to an energy storage device for storing the usable electrical energy and/or to an interface circuit for supplying energy for use in an electrical system in the vehicle.

Abstract: Methods and apparatuses are disclosed relating to multilayer 3D textile composite materials containing self-healing resins for use as protective structures on stationary objects, and moving objects including, without limitation, vehicles including spacecraft and aircraft.

Abstract: Systems and processes that integrate thermoplastic and shape memory alloy materials to form an adaptive composite structure capable of changing its shape. For example, the adaptive composite structure may be designed to serve as a multifunctional adaptive wing flight control surface. Other applications for such adaptive composite structures include in variable area fan nozzles, winglets, fairings, elevators, rudders, or other aircraft components having an aerodynamic surface whose shape is preferably controllable. The material systems can be integrated by means of overbraiding (interwoven) with tows of both thermoplastic and shape memory alloy materials or separate layers of each material can be consolidated (e.g., using induction heating) to make a flight control surface that does not require separate actuation.

Abstract: A heated roller shade system is provided. The heated roller shade system includes a roller located in a cavity defined between an inner wall of a vehicle and an outer wall of the vehicle. The roller shade system also includes a shade coupled to the roller. The roller is configured to selectively move the shade between a deployed position and an open position. The roller shade system also includes a heating mechanism coupled to at least one of the roller and the shade. The heating mechanism facilitates increasing a temperature of at least one of the roller and the shade.

Abstract: In one or more aspects of the present disclosure, a mandrel is disclosed. The mandrel having a shape memory alloy (SMA) shell having a longitudinal axis, an interior extending along the longitudinal axis and an exterior contour, the SMA shell being configured to interface with a structure to be cured, and at least one SMA actuation member disposed within the interior and connected to the SMA shell, where the at least one SMA actuation member is configured to exert pressure against the SMA shell effecting an interface pressure between the exterior contour of the SMA shell and the structure to be cured where the exterior contour has a predetermined actuated shape that corresponds to a predetermined cured shape of the structure to be cured.

Abstract: A radius filler includes a plurality of fibers encapsulated in resin and braided into a braided radius filler. The braided radius filler has a substantially triangular shape with concave radius filler side surfaces and a substantially planar radius filler base surface.