Abstract: The invention discloses a method for fabricating a deployable, inflatable aerodynamic control structure for aerospace vehicles which has a desired noncircular or noncylindrical cross-section. In a preferred embodiment, the control structure is configured as an inflatable airfoil and includes a flexible skin and a plurality of internally disposed airfoil-shaped bulkheads or integral rib members that are arranged, spaced apart, in cross-wise fashion along the axial length of the airfoil shaped control structure. The flexible skin is fabricated as a lay up, in ordered sequence, of plural layers of elastomeric rubber material and plural ply layers of resin-impregnated yarns or fabric. The result is a fiber-reinforced pressure membrane that is flexible and compactly foldable.

Abstract: A laser inspection tool system (100) includes a hand-held remote tool head (108) that provides an image of a target object (116) and a measurement surface (118). The remote tool head (108) includes light sources (208) and mirrors (210) that in conjunction generate two perpendicular lines of light that impinge the target object (116) and the measurement surface (118) and reflect to a form an image in a camera (218) in the remote tool head (108). The remote tool head (108) may be oriented at any angle relative to the measurement surface (118). A processor (102) remotely coupled to the remote tool head (108) captures the image and determines the offset between the light reflected by the target object (116) and the light reflected by the measurement surface (118), and the angle between the reflected lines of light.

Abstract: A rigid acoustic insulator panel for use as a sound insulator is disclosed. The panel is composed of a rigid matrix formed of randomly oriented, fused silica fibers having fiber diameters predominantly in the range between 0.5 and 2 .mu.m. The matrix has a three-dimensionally continuous network of open, intercommunicating voids, and a density of between about 2 and 6 lb/ft.sup.3. In one embodiment, the panel has greater flow resistance characteristics, progressing from a sound-absorbing side of the matrix to the opposite panel side. Also disclosed is a method of preparing the panel.

Abstract: The invention discloses a deployable, inflatable aerodynamic control structure for aerospace vehicles which has a desired noncircular or noncylindrical cross-section and fabrication methods therefor. In a preferred embodiment, the control structure is configured as an inflatable airfoil and includes a flexible skin and a plurality of internally disposed airfoil-shaped bulkheads or integral rib members that are arranged, spaced apart, in cross-wise fashion along the axial length of the airfoil shaped control structure. The flexible skin is fabricated as a lay up, in ordered sequence, of plural layers of elastomeric rubber material and plural ply layers of resin-impregnated yarns or fabric. The result is a fiber-reinforced pressure membrane that is flexible and compactly foldable.

Abstract: A wavefront sensor for use in a staring imaging system for generating focused and defocused images of an object scene that is being imaged by the imaging system from a single input optical beam impinged thereon. The wavefront sensor includes a beamsplitter for splitting an optical input beam into identical first and second half beam portions and for focusing the first and second half beam portions onto respective first and second focal planes. A phase plate is interposed between the beamsplitter and the second focal plane for inducing a known focus error in the second half beam portion. A photodetector is also provided and is effective to form a best focused image and a slightly out of focus image at the first and second focal planes, respectively. The focused and defocused images are combinable using phase diversity techniques to estimate wavefront aberrations present in the imaging system.

Abstract: An acoustic structure for use as a sound insulator in a jet engine is disclosed. The structure, which is carried in a sound-absorbing compartment of the engine, includes a framework and an acoustical insulation material disposed within the framework. The material is composed of a rigid matrix of randomly oriented, fused silica fibers having fiber diameters predominantly in the range 2-8 .mu.m, a three-dimensionally continuous network of open, intercommunicating voids, a flow resistivity between about 10-200K rayls/m, and a density of between about 2 and 8 lb/ft3. Also disclosed are a clad acoustical structure for sound attenuation in a jet engine, where operational temperatures exceed current jet engine designs, and a method of attenuating jet engine noise.

Abstract: An original signal, different portions of which are captured by two or more different receivers, is reconstructed from the outputs of the various receivers. In a first embodiment, signal reconstruction is achieved by first converting the analog receiver outputs into digital signals and then shifting the frequency of at least one of the digital signals such that a frequency difference is introduced between at least two of the digital signals. Thereafter, each digital signal is processed through a corresponding filter (38, 40) to derive filtered signals. These filtered signals are combined to derive a primary output signal which is a representation of the original signal. After the primary output signal is derived, it is passed on to an error determiner (44) where an error component is computed. This error component is used to adjust the parameters of the filters (38, 40) in such a manner as to reduce the error component.

Abstract: The present invention relates to a tape for seaming together RF shielding thermal blankets of the kind used for covering the metal components of high power RF transmit and receive communications systems which are susceptible to generating passive intermodulation products, such as the high power transmit antenna boom assemblies of communications spacecraft. The tape is constructed as a composite lay-up of materials which preferably include a plastic film top or outboard layer, a metallized plastic film or metal foil middle layer, and a transfer adhesive bottom layer for securing the middle layer to the outboard layer. The transfer adhesive functions both as a substrate attaching medium and as an electrical isolator for encapsulating the metal surfaces of the middle layer.

Abstract: A safe, vault or container 10 has a laminate wall that is resistant to the cutting effects of a high-temperature torch. The wall of the safe, vault or container 10 comprises a hardened steel outer panel 21 and a hardened steel inner panel 22. A refractory abrasive layer 23, as of Carborundum, is disposed adjacent the outer panel 21 to break any drill that might penetrate through the outer panel 21. A thermally conductive layer 24 is disposed adjacent the abrasive layer 23 to conduct heat rapidly away from any localized hot spots that might develop within the abrasive layer 23 when heat from a high-temperature torch is applied to a region of the outer panel 21. A thermally insulating layer 25 is disposed between the thermally conductive layer 24 and the inner panel 22 to inhibit heat transfer from the thermally conductive layer 24 to the inner panel 22. The thermally insulating layer 25 comprises a porous ceramic material consisting of vitreously fused ceramic fibers.

Abstract: A method for sewing a plurality of gore-shaped metalized mesh fabric panels to each other to form a parabolic dish-shaped reflector surface for subsequent attachment to the radially extendable rib members of a deployable parabolic reflector. The method includes using a template having "cut" and "sew" lines indicated thereon for cutting out a desired number of gore-shaped panels from a bolt of metalized mesh fabric and sewing the panels together along adjacent side edges thereof to form the dish-shaped reflector surface. The dish-shaped reflector surface is then attached to the reflector by sewing the mesh fabric panels to stitch holes provided in each rib member. The reflector surface is accurized by using a wedge-shaped tool which is placed on a slack reflector panel adjacent a gore seam.

Abstract: To develop a design form for a Cassegrain-type telescope with spherical primary and secondary mirrors, which is well-corrected for chromatic aberration as well as for geometrical aberrations including spherical aberration, coma and astigmatism, the designer begins with a "starting design form" for a conventional Cassegrain-type telescope with spherical primary and secondary mirrors, and then modifies the "starting design form" by:(a) positioning lens elements of a corrector lens group along an optic axis inside the front focal plane of the spherical primary mirror, where the lens elements of the corrector lens group are made of optical materials that enable a desired degree of correction for chromatic aberration to be achieved;(b) providing a reflective coating on a central portion of the back surface of the rear-most lens element of the corrector lens group, which replaces the secondary mirror of the "starting design form" and becomes the secondary mirror of the telescope;(c) locating the entrance pupil of t

Abstract: Wavefront correction apparatus for correcting a stepped wavefront output produced by certain angles of scan and by certain positions of scan in scanning microlens arrays includes anamorphic transfer optics with diffractive corrections. The transfer optics form the outputs of all of the unit cell trains of the microlens arrays into a unique, separate, linear image at each position of scan of the scanning array. A stepped wavefront corrector is positioned in the path of each linear image, and selected thicknesses of the material in the stepped wavefront corrector are effective to vary the times of optical passage through the stepped wavefront corrector in amounts to restore the wavefront to a continuous, unstepped form at the outlet of the plate.

Abstract: Design forms are disclosed for wide-field infrared imaging systems characterized by a large ratio of entrance aperture to focal length, where the limiting aperture stop is located in the converging image space.

Abstract: In a lens assembly for a telescope objective that comprises liquid lens elements contained between adjacent glass lens elements, each glass lens element is adhesively bonded to an interior surface of a corresponding cylindrical mounting ring by a sealant that is impervious to the liquid lens elements. The sealant is a proprietary fluorosilicone compound marketed as "DOW CORNING X5-8738". The cylindrical mounting rings (with the corresponding glass lens elements bonded thereto) are coaxially aligned so that planar end surfaces of adjacent mounting rings adjoin each other. Compressible O-rings made of Viton.RTM. are received in annular grooves formed on one end surface of each pair of adjoining end surfaces of adjacent mounting rings. Adjacent mounting rings are secured to each other to provide three-point mounting contact between adjacent mounting rings so as to obtain precise axial alignment of the glass lens elements.

Abstract: A metallized mesh fabric construction for use as the individual reflector panels of a radio frequency (RF) deployable parabolic reflector of the type which includes a plurality of panel supporting rib members which, upon deployment, unfurl in a spiral manner from a central hub to form the parabolic reflector surface. The mesh fabric includes silver coated nylon strands and stretch resistant plastic or synthetic strands interwoven in a "Marquisette" or "Leno" style weave. The stretch resistant strands of the mesh fabric are oriented along the chordal direction (i.e., transverse to the radial direction of the unfurlable ribs) in order to withstand the tension placed on the mesh fabric during deployment of the reflector and hence maintain the shape and accuracy of the reflector surface and resist creep. The weave has openings sized sufficiently large to minimize the effects of wind load yet sufficiently small to provide good reflective performance of radio frequencies up to and including X-Band frequencies.

Abstract: A large aperture microlens array assembly has at least two arrays of microlenses with individual unit cell trains optically interconnecting individual microlenses in one array with related individual microlenses in another array. In each unit cell train the light entering an entrance pupil of a microlens in one array is transmitted through the exit surface of a related microlens of the other array to provide a collimated output through the exit. One array may be moved with respect to the other array for scanning a field of regard.

Abstract: Design forms are disclosed for 5.times. and 10.times. laser beam expanders whose lens elements consist of glass and liquid optical materials, which provide diffraction-limited performance without refocussing over a wavelength range from 0.4 micron to 0.8 micron.

Abstract: A matrix of infrared generating cells is disclosed. Each cell includes a resistive element formed over and traversing a cavity formed on the surface of the supporting semiconductor substrate.

Abstract: The present invention is directed to a vessel that is form stabilized. The stability is achieved by the particular shape or orientation of the struts or both. In one embodiment the dihedral struts have a cambered cross-section area. In another embodiment the cross-section area of the struts are symetrical and the struts are mounted in a toe out position.

Abstract: The present invention is directed to maneuvering control systems for small waterplane-area twin hull design watercraft. The maneuvering control system of the present invention includes horizontal or dihedral foils mounted on the lower hulls of the watercraft. The foils may take the form of a one-piece rotatable foil or a foil that includes a plurality of movable sections.