Abstract: A solar array integration system (AIS) and methods for mounting solar energy capture devices are provided. Such systems are useful for applications such as mounting photovoltaic (PV) modules to a suitable surface such as a rooftop. In one embodiment, the AIS includes a first row of tilted solar modules, a center spoiler coupled to the first row of tilted solar modules, the center spoiler is configured to deflect frontal airflow over the first row of tilted solar modules, and a second row of tilted solar modules, the second row of tilted solar modules being coupled to each other by an aerodynamic spar. The aerodynamic spar includes a deflector configured to deflect frontal airflow over the second row of tilted solar modules. The deflector may include a wedge-shaped profile. AIS can also include a third row of tilted solar modules, with an end spoiler coupled to the third row of tilted solar modules, and wherein the end spoiler is configured to deflect side airflow over the third row of tilted solar modules.

Abstract: A flexible ballistic resistant article for protecting a user from a high speed projectile, including an outer layer for stopping the forward motion of the projectile, and an inner layer disposed between the outer layer and the user. The inner layer reduces the backface signature of the outer layer thereby reducing the blunt trauma experienced by the user. The outer layer including a plurality of plies of high tensile strength fibers. The inner layer including a honeycomb core formed of undulated strips of resilient thermoplastic material, thermal compression bonded together to form cell walls defining a plurality of contiguous regularly shaped cells. The core having a first face formed by a first extremity of the cell walls, and a second face formed by a second extremity of the cell walls. The core further having means for maintaining the core in its expanded configuration so that it can be used to anisotropically flex to stabilize and spread the load experienced by the user.

Abstract: A shock absorbing pad system for a missile in a launch tube comprising a plurality of pads having inner and outer arcuate sheets separated by chevron shaped struts disposed in a circular array and having the inner arcuate sheets joined together by a circumferential tensile resistive fabric which is embedded in the inner arcuate sheets and extends therebetween so as to form a loop in the fabric when the pads are disposed in the launch tube and are in their free state, the loop straightening when the missile is loaded into the tube so that the circular array of pads act as a unit to resist shock and apply centering forces to the missile when it becomes eccentrically disposed in the launch tube.

Abstract: A seal for a large annular opening between a launch tube and a missile comprising a suspended hoop composed of a pair of cylindrical rings spaced apart by axially disposed chevron-shaped struts, the inner cylindrical ring having a frustoconically shaped lip extending from its lower margin and a foot cylindrical ring is disposed below the suspended hoop with a frustoconically or half-toroid shaped membrane having a fibrous cloth embedded therein extending between and into the inner cylindrical ring and the lip portion to provide a stabilizing seal.

Abstract: A unitized shock isolation and support system disposed in an annular space between two cylindrical surfaces utilizing a first compressible portion axially oriented chevron-shaped prebuckled struts to support a rigid or semirigid hoop larger in diameter than the inner cylinder and second compressible portion or a foam liner disposed on the inner diameter of the hoop, the foam liner being thicker than the annular space between the inner cylinder and the hoop to form a space efficient system mitigating shock and for laterally supporting the inner cylindrical surface within the outer cylindrical surface.

Abstract: A system for reducing the shock and vibration transmitted to a missile dug transportation, stowage or launch. Rings of segmented shock-absorbing pads are disposed along the launch tube in the annular space between the missile and the tube. These pad segments are unitized by a circumferential tensile fiber hoop connecting the pad segments, and portions of this unitizing hoop are used to form control loops between these pad segments. The loop characteristics may be selectively varied to control the effective modulus and circumferential length of each unitizing hoop thus varying the force/deflection characteristics of the pad ring.