Abstract: A reinforced elastomer panel (100) has a first rigid member (104) with an edge (116) attached to a first end of an elastomer panel (114). The first rigid member (104) has a removable plate (106) that provides access to a cavity (108). Attached to the first rigid member (104) is a reinforcing member (102) that extends through the elastomer panel (114). A second rigid member (118) has an edge attached to a second end of the elastomer panel (114).

Abstract: A conformable weapons platform (52) has a cavity (60) in a skin of an aircraft. A weapon launching system (62) is contained in the cavity (60). A pair of elastomer doors (56, 58) are attached to a perimeter of the cavity.

Abstract: An apparatus (30) for eliminating gaps (20) in a door of an airplane has an elastaueric bladder (32) bonding along an edge (24) of a door gap (20). The elastomeric bladder (32) includes a port providing for access to an interior cavity (34). A pneumatic actuator is coupled to the port.

Abstract: An aircraft (50) with a variable cargo bay (52) includes a frame (60). A pair of fairing assemblies (54, 56) is coupled to the frame (60). Each of the pair of fairing assemblies (54, 56) has a ramp (100) connected to the frame (60) by a front sliding pivoting mechanism (106). A door assembly (58) is between the pair of fairing assemblies (54, 56) and is coupled to the frame (60).

Abstract: An environmental cover (50) for a reinforced elastomer panel (70) has a knit fabric (82) covered with an electrically conductive material. An environmental calendared sheet (84) is attached to a first surface of the knit fabric (82) and an elastomer calendared sheet (80) is applied to a second surface of the knit fabric (82).

Abstract: A tail (14) for an aircraft (10) has a center member (20) pivotally attached to the aircraft (10). A leading edge flap (22) extends along a length of the center member (20). An elastomeric skin (30) is connected between an exterior surface (26) of the center member (20) and an adjacent exterior surface (28) of the leading edge flap (22).

Abstract: A fairing (100) for an expandable bay of an has a ramp (108). A front linkage bar (102) has a first end pivotally connected to a finger (106) of the ramp (108) and a second end pivotally connected to the aircraft. A mating panel (112) is next to an interior edge (132) of the ramp (108) and pivotally connected to the ramp (108). An exterior elastomer panel (124) is connected between an exterior edge (126) of the ramp (108) and the aircraft.

Abstract: A hinge line system (52) for an aircraft has a structural block (22) attached to a first edge of a hinge line. The structural block (22) has a flange (28) attached to a first end of an elastic sheet (32). A second structural block (24) is attached to a second edge of the hinge line. The second structural block (24) has a second flange (30) attached to a second end of the elastic sheet (32).

Abstract: A titanium matrix composite laminate (42) includes alternating layers of a titanium matrix foil (12) and a fiber mat (14). The titanium matrix foil (12) is formed from a super alpha titanium alloy having a beta phase stabilizer equivalency of at least thirteen. The beta phase stabilizer is selected from the elements molybdenum, vanadium, niobium, tantalum, halfnium, tungsten or some combination thereof. The fiber mat (14) is formed of silicon carbide (SiC) and has a carbon coating. Once a layup (16) of the alternating layers is formed, it is placed in a mold (22). Heat and pressure are then applied in a step called consolidation (40). The result is a titanium matrix composite laminate (42).

Abstract: An active reinforced elastomer system (50) has a rigid attachment block (56). A stiffening member (58) slides through an opening in the rigid attachment block (56). A shape memory alloy structure (62) is attached to the rigid attachment block (56). An elastomer panel (52) is attached to the rigid attachment block (56) and covers the stiffening member (58).

Abstract: An expandable fuel cell (72) for an aircraft (70) has a flexible structure (126) having a perimeter (124) attached to an airframe of the aircraft (70). The flexible structure (126) has an empty position, in which the flexible structure (126) approximately conforms to a moldline (76) of the aircraft (70), and a full position, in which the flexible structure (126) forms a smooth curvilinear protrusion from the moldline (76) of the aircraft (70). A fuel bladder (152) is positioned between the flexible structure (126) and the airframe.

Abstract: A retractable sensor system (12) for an aircraft has a sensor (16) coupled to an actuation mechanism (18). The sensor (16) moves from a retracted position to an expanded position. A reinforced elastomer section (14) in an exterior surface (48) of the aircraft covers the sensor (16) and the actuation mechanism (18). The reinforced elastomer section (14) has an interior surface and an exterior surface and the sensor (16) has a portion adjacent to the interior surface. The reinforced elastomer section (14) has a flush position and an expanded position.

Abstract: A blade seal (20) for an aircraft has a mounting structure (22). A composite blade (26) is attached to the mounting structure (22). The composite blade (26) has a plurality of holes (28). An elastomer substance (30) is used to fill the plurality of holes (28).

Abstract: A sensor system for a reinforced elastomer panel (100) has an optical source (104) emitting an optical signal. An optical strain sensor (102) is embedded in an elastomer sheet (40) of the reinforced elastomer panel (100) and receives the optical signal. A strain processing system (108) is optical coupled to the optically strain sensor (102).

Abstract: A color selective, anti-reflective optical coating has a substrate (42), a first layer (44) and a second layer (46). The first layer (44) has an index of refraction that is 25% to 39% greater than an index of refraction of the substrate (42). The first layer (44) has a width of between 12.31 nanometers and 13.41 nanometers. The second layer (46) has an index of refraction that is between 1% and 17.5% less than the index of refraction of the substrate (42). The second layer (46) has a width between 118.32 nanometers and 130.78 nanometers. When the color selective, anti-reflective optical coating is applied to a head lamp lens (40), it significantly increases the output of the head lamp (20) and has a distinctive tint.

Abstract: A rotating heat exchanger (10) has a first air turbine (16) connected to a first end of an axle (20). The second end of the axle (20) is connected to a second air turbine (18). A heat pipe (30, 40, 42, 44) extends from the first air turbine (16) to the second air turbine (18).

Abstract: Two-layer, thin film coating designs on glass substrates are described which reduce coated surface reflectance while inhibiting the visibility of fingerprints.

Abstract: A fiber optic switch and attenuator (10) has a sealed capsule (12). The sealed capsule (12) contains a first fluid (14), having a first index of refraction and having a first density. The sealed capsule (12) contains a second fluid (16), having a second index of refraction, the second index of refraction being greater than the first index of refraction. The second fluid (16) has a second density that is not equal to the first density. A bobbin (18) is contained in the sealed capsule (12). A fiber optic core (20) is wrapped around the bobbin (18). The fiber optic core (20) has a core index of refraction. The core index of refraction is less than the second index of refraction and greater than the first index of refraction. The fiber optic core (20) has a first end (22) and a second end (24) outside the sealed capsule (12).

Abstract: This invention discloses an improved cutting tool such as a counterbore cutter or piloted reamer that is comprised of a free-spinning pilot connected to the cutting tool. The free-spinning pilot allows the cutting tool to rotate within it while it makes firm contact with a pre-drilled hole in material to be cut improving the location of the cutter relative to the hole.

Abstract: A system (50) for determining strain includes: a stimulating light source (54, 56); a device (64) for placing stress on an object (58); a number of local strain gauges (66) attached to the object (58); and an image capturing device (62, 64). A controller (52) is coupled to the stimulating light source (54, 56) and has a signal that turns on the stimulating light source (54, 56). The controller (52) receives a strain signal from each of the local strain gauges (66) located on the object (58). The controller (66) has an image signal that determines when the image capturing device (62, 64) captures an image.