Abstract: A laminated wing structure includes at least one layer of metal material and at least one layer of a shape memory polymer (SMP) material. The SMP is heated to a temperature in its glass transition band Tg to roll the wing around the air vehicle into a stored position. The metal layer(s) must be thin enough to remain below its yield point when rolled up. In preparation for launch, the SMP material is thermally activated allowing the strain energy stored in the layer of metal material to return the wing to its deployed position at launch. Once deployed, the SMP cools to its glassy state. The SMP material may be reinforced with fiber to form a polymer matrix composite (PMC). SMP may be used to provide shear strain relief for multiple metal layers. By offloading the motive force required to return the wing to its original deployed position from the SMP to the metal, the polymer does not acquire a permanent set and the wing may be deployed accurately.

Abstract: Methods and apparatus for non-axisymmetric radome according to various aspects of the present invention include a non-symmetric housing for a forward portion of a projectile. Multiple sensors may be positioned in an off-axis configuration within the non-symmetric housing reducing the possibility of one sensor interfering with the operation of another sensor. The non-symmetric housing may also be configured with a strengthening member suitably adapted to provide additional resistance to bending moments caused by external loading along a surface of the non-symmetric housing.

Abstract: A reconfigurable air vehicle wing may be selectively reconfigured to increase its chord. The wing has a leading edge portion and a trailing edge portion that are moved relative to one another to change the chord of the wing. The wing may be reconfigured from a compact configuration with a smaller chord, to and expanded configuration with a larger chord. The wing may include a foam material that forms part of the outer surface of the wing when the wing is in the expanded configuration. The foam may be a shape memory foam. Alternatively the leading edge section and the trailing edge section may be composed substantially fully of rigid materials. In either case the trailing edge section may be hingedly coupled to the leading edge section.

Abstract: A laminated wing structure includes at least one layer of metal material and at least one layer of a shape memory polymer (SMP) material. The SMP is heated to a temperature in its glass transition band Tg to roll the wing around the air vehicle into a stored position. The metal layer(s) must be thin enough to remain below its yield point when rolled up. In preparation for launch, the SMP material is thermally activated allowing the strain energy stored in the layer of metal material to return the wing to its deployed position at launch. Once deployed, the SMP cools to its glassy state. The SMP material may be reinforced with fiber to form a polymer matrix composite (PMC). SMP may be used to provide shear strain relief for multiple metal layers. By offloading the motive force required to return the wing to its original deployed position from the SMP to the metal, the polymer does not acquire a permanent set and the wing may be deployed accurately.

Abstract: A reconfigurable air vehicle wing may be selectively reconfigured to increase its chord. The wing has a leading edge portion and a trailing edge portion that are moved relative to one another to change the chord of the wing. The wing may be reconfigured from a compact configuration with a smaller chord, to and expanded configuration with a larger chord. The wing may include a foam material that forms part of the outer surface of the wing when the wing is in the expanded configuration. The foam may be a shape memory foam. Alternatively the leading edge section and the trailing edge section may be composed substantially fully of rigid materials. In either case the trailing edge section may be hingedly coupled to the leading edge section.

Abstract: Methods and apparatus for non-axisymmetric radome according to various aspects of the present invention include a non-symmetric housing for a forward portion of a projectile. Multiple sensors may be positioned in an off-axis configuration within the non-symmetric housing reducing the possibility of one sensor interfering with the operation of another sensor. The non-symmetric housing may also be configured with a strengthening member suitably adapted to provide additional resistance to bending moments caused by external loading along a surface of the non-symmetric housing.