Abstract: A motion compensated integration system and process for scanning a field and producing images of one or more densely filled wavebands has a moveable platform, an optical sensor, and optical sensor line-of-sight measuring device, and a processor. The optical sensor is mounted to the moveable platform and is made up of a telescope that is in functional relationship with a focal plane array. The focal plane array comprises one or more sets of detectors capable of receiving one or more wavebands and producing focal plane array data of the wavebands, respectively. The optical sensor line-of-sight measuring device is capable of producing optical sensor line-of-sight movement data. The processor is capable of receiving the focal plane array data and the optical sensor line-of-sight movement data and producing output images representing the wavebands, respectively. The system and process may normalize the data to account for border regions of the stabilized arrays.

Abstract: An actuator for continuously aligning the primary mirror relative to the scraper the other resonator mirrors and the feedback mirror in a high power laser resonator, comprised of extended portions of the resonators primary mirror, feedback mirror and scraper mirror for a low power laser beam to travel parallel to but offset from the high power laser beam for aligning the mirrors. The low power laser beam is used to measure the position of the mirrors in the resonator. The low power beam is split into a beam which is incident on a quadrant cell for measuring the tip and tilt of the feedback mirror relative to the primary mirror and a beam which measures the translation of the feedback mirror relative to the primary mirror. A controller receives the data form the quadrant cells and sends signals to actuators on one mirror to move it relative to the other thus keeping the mirrors in constant alignment.

Abstract: A ferrous-alloy aircraft structural component such as a fastener is prepared by providing a ferrous-alloy component precursor that is not in its final heat-treated state, and coating with an aluminum-containing, curable organic coating material having a non-volatile portion that is predominantly organic and is curable at about the ferrous-alloy component's tempering temperature. The coated, ferrous-alloy is then tempered to concurrently impart predetermined metallurgical properties to the finished, ferrous-alloy material, and cure the organic, aluminum-containing coating.

Abstract: An improved and simplified system for densifying a cryogenic liquid for space vehicles is provided, which includes a heat exchanger having heat exchange tubes therein for receiving a flow of liquid from a storage tank, for example a liquid propellant in a vehicle storage tank. The heat exchanger is filled around the exchange tubes with a two-component bath, the volume of a primary component substantially exceeding the volume of a secondary component. The secondary component has a boiling temperature that is lower than the boiling temperature of the primary component, and both are lower than the boiling temperature of the cryogenic liquid. In one example, the liquid to be densified is oxygen, the primary component is liquid nitrogen, and a secondary component is liquid hydrogen. The secondary component is preferably injected into the heat exchanger in separate flows to prevent localized freezing of the first component.

Abstract: A woven preform for a ceramic composite has a plurality of layers and structural members. The plurality of layer are of woven yarns of fibrous material. The structural members extend between the layers. The layers and members define interlayer spaces. One or more of the layers may have a plurality of openings extending therethrough. Low density ceramic insulation made be deposited in the interlayer spaces via a slurry that enters the preform, or the preform after it has been made a part of a composite, through the openings. The carrier of the slurry exits the preform, leaving the randomly packed fibers in the interlayer spaces. The structural members may be walls that, along with the layers, define channels. The channels may be used to direct fluid through so as the composite functions as an insulator. The channels may be directed in the warp direction for achieving increased benefits.

Abstract: A ferrous-alloy aircraft structural component such as a fastener is prepared by providing a ferrous-alloy component precursor that is not in its final heat-treated state, and coating with an aluminum-containing, curable organic coating material having a non-volatile portion that is predominantly organic and is curable at about the ferrous-alloy component's tempering temperature. The coated, ferrous-alloy is then tempered to concurrently impart predetermined metallurgical properties to the finished, ferrous-alloy material, and cure the organic, aluminum-containing coating.

Abstract: A sealed-cavity microstructure and an associated method for manufacturing the microstructure. Specifically, the microstructure includes first and second wafers that are positioned relative to one another so as to form a cavity between the wafers. The microstructure further includes a seal between the first and second wafers and surrounding the cavity to create a pressure seal for the cavity. This seal allows the cavity of the microstructure to be maintained at a predetermined pressure different from that of the atmosphere outside the cavity. Importantly, the microstructure further includes a structural bond between the first and second wafers that structurally integrates the first and second wafers. The structural bond renders the microstructure more rugged such that the microstructure can withstand expansion, vibrational, and shock stresses experienced by the microstructure during subsequent manufacturing and use.

Abstract: An apparatus for launching projectiles from a host aircraft is disclosed. The apparatus comprises: a rotary launcher, a plurality of launch tube assemblies, a plurality of projectile retention means, and a plurality of ejection cartridges. The rotary launcher has a plurality of support fittings thereon, each for securing a tube assembly to the rotary launcher. Each projectile retention means securely retains each projectile within its respective launch tube. Each ejection cartridge is mounted to a respective launch tube assembly and interfaces with a projectile retention means to provide an ejection of that projectile retention means.

Abstract: A cryogenic liquid heat exchanger system has a subatmospheric pressure reservoir, a tube, and an initial fluid ejector. The sub-atmospheric pressure reservoir has a vacuum exhaust. The tube extends through the reservoir. The initial fluid ejector has a suction chamber inlet that is functionally connected to the reservoir vacuum exhaust. The system may have a plurality of fluid ejectors connected to one or more exhausts either in series or parallel. The initial fluid ejector may receive one or more pressurized fluid streams, and the streams may be steam. A process for generating sub-atmospheric pressures in a cryogenic fluid heat exchanger reservoir includes the step of discharging an initial fluid stream into an initial fluid ejector having a suction chamber functionally connected to an exhaust of the reservoir. A process for generating sub-atmospheric pressures in a cryogenic fluid heat exchanger reservoir includes the step of using a fluid ejector to reduce the pressure in the reservoir.

Abstract: Slush is made from a liquid using slush making systems or according to slush making processes. A jacketed vessel of the processes and the systems has an interior wall that defines an interior space. The interior space comprises a top and a bottom. The interior space has an average overall cross-sectional area taken through a vertical axis extending generally between the top and the bottom. The interior space also has a collection portion having an average collection portion cross-sectional area taken through the vertical axis that is less than the average overall cross-sectional area. The liquid is placed into the interior space and the interior walls are cooled. Slush forms on the interior walls and migrates to the collection portion. The collection portion is located at the interior space bottom when the slush density is higher than the liquid density and the collection portion is located at the interior space top when slush density is less than the liquid density.

Abstract: The objectives of the invention are met by an improved radar tracking system and a process of radar tracking. In the improved system and process, an estimate of a target range and a range uncertainity swath from a first radar system is inputted into a second radar system along with a duty factor. The second radar system determines a set of zero eclipse intervals and respective ranges of range pulse repetition frequencies that solves a first set of equations. A usable range pulse repetition frequency is chosen from the results. Next, an estimated target Doppler frequency region and a Doppler uncertainity swath is inputted into the second radar system. The second radar system is instructed to determine a set of clear Doppler frequency region intervals, and respective ranges of Doppler frequency pulse repetition frequencies by solving a second set of equations.

Abstract: A thermal expansion joint having a plurality of bendable tabs which flex to minimize the stress caused by thermal expansion. The tabs flex at their slot radii by the base of the tabs, allowing the tip of the tabs to move. Apertures in the tabs near the tip connect the tabs to a solid body or to tabs on another body. The tabs' flexing relieves stress in the body undergoing thermal expansion at the point it is connected to a body which has a different thermal expansion rate and/or experiences a different temperature. A plurality of tabs so connecting two bodies provides a stiff joint and reduces the thickness of the material otherwise needed to provide a connection what will not crack or otherwise break due to thermal strains at the connection between two bodies.

Abstract: The amplifier assembly includes a driver bellows and an output bellows. The driver bellows includes a first end and a second end. The first end is positionable adjacent a microactuator. The output bellows includes a first end and a second end. The first end of the output bellows is securely attached to the second end of the driver bellows. The second end of the output bellows is positionable adjacent a device to be actuated. The output bellows has a smaller volume than the driver bellows. Each bellows is filled with a working fluid. When the driver bellows is compressed by the microactuator the fluid displacement of the driver bellows is translated to the output bellows causing a displacement in the output bellows equal to the fluid displaced in the driver bellows. Thus, an amplified output stroke is provided of the desired magnitude.

Abstract: Multi-spectral planar photodiode pixels are provided in accordance with the present invention for simultaneously detecting multi-colors of infrared radiation. Each multispectral planar photodiode pixel includes a semiconductor substrate layer, a buffer layer of a first conductivity type material deposited on a semiconductor substrate layer, and a first color layer of the first conductivity type material deposited on the buffer layer. The multispectral planar photodiode pixel further includes a barrier layer of the first conductivity type material deposited on the first color layer, a second color layer of the first conductivity type material deposited on the barrier layer, and a cap layer of the first conductivity type material deposited on the second color layer. A first diode comprising a second conductivity type material is formed in the first color layer, and a second diode comprising a second conductivity type material is formed in the second layer.

Abstract: In one broad aspect the present invention comprises the steps of providing a titanium-based material preform and superplastically forming the preform to a final helmet shape. In another broad aspect, a first piece of fiber-reinforced titanium matrix composite material is hot isostatically pressed (HIP'ed) to form a side wall section. A second piece of fiber-reinforced titanium matrix composite material is hot pressed to form an upper dome section. The side wall section is then HIP/diffusion bonded to the upper dome section.

Abstract: Basic hydrogen peroxide used in chemical oxygen lasers can be produced using a lithium based lithium hydroxide with a lithium hydroxide makeup of the reacted basic hydrogen peroxide. Lithium hydroxide, water and hydrogen peroxide are mixed and 1) passed over a lithium hydroxide solid bed or 2) premixed with small particulate solid lithium hydroxide or lithium hydroxide monohydrate. The basic hydrogen peroxide produced is chilled and stored cold until mixed with chlorine to produce singlet delta oxygen for use in the chemical oxygen iodine laser. The spent basic hydrogen peroxide is rejuvenated by passing it over a solid lithium hydroxide or in-situ solid particulate lithium hydroxides. After dissolution, the rejuvenated basic hydrogen peroxide is then reacted with chlorine to produce more singlet delta oxygen.

Abstract: An alkaline peroxide cell for electrolytic regeneration of spent BHP from a chemical oxygen iodine laser, the cell having a for regenerating chlorine and a peroxide cell for regenerating BHP. The chlorine compartment having a potassium chloride electrolyte and producing chlorine gas for the chemical oxygen iodine laser. The peroxide cell having a spent BHP electrolyte and producing BHP for the chemical oxygen iodine laser. A cation exchange membrane between the chlorine compartment and the peroxide compartment allows potassium ions to be transported from the chlorine compartment to the peroxide compartment.

Abstract: A radar system and method for obtaining low sum and difference side lobe patterns from a phased array antenna comprising radiators distributed amongst four quadrants A, B, C, and D. The quadrants are arranged in a clockwise order of A, B, D, and C. Each quadrant is further divided into an inner portion and an outer portion. The monopulse sum pattern is determined by adding signals received by radiators in the A quadrant, B quadrant, C quadrant, and D quadrant. The elevation difference pattern is determined by subtracting a CD sum consisting of signals received by radiators in the C outer portion and the D outer portion from an AB sum consisting of signals received by radiators in the A outer portion and the B outer portion. The azimuth difference pattern is determined by subtracting a BD sum consisting of signals received by radiators in the B outer portion and the D outer portion from an AC sum consisting of signals received by radiators in the A outer portion and the C outer portion.

Abstract: Aqueous black liquor is gasified in a molten salt by spraying the black liquor into an enclosed zone above the surface of a turbulent molten salt pool. The black liquor is dried by means of hot gases rising from the surface of the pool and the resulting solid particles falling into the turbulent molten salt pool are dispersed and converted into a combustible gas and a reduced melt in which sulfide comprises at least about 95% of the total sulfur present. In a preferred embodiment the product gas is purified, burned and utilized in a gas turbine.

Abstract: A system for enabling an aircraft to accomplish extremely short takeoffs and landings, which includes an integrated flight control system; a takeoff system; a landing system and a high thrust-to-weight propulsion system. The integrated flight propulsion control system includes a multi-axis thrust vectoring system. The takeoff system is operably engageable with the multi-axis thrust vectoring system. The takeoff system includes means for rotating the aircraft nose upwardly below stall speed without substantial use of thrust vectoring from the multi-axis thrust vectoring system. The landing system is operably engageable with the multi-axis thrust vectoring system. It includes means for de-rotating the aircraft from a high angle of attack to a main gear touchdown angle of attack sufficiently low to avoid scraping the tail of the aircraft.