Abstract: Biophotonic device for the point-of-care, real-time, non-invasive determination of parameters with diagnostic relevance, in particular an optical system for parameter characterization of an element of body fluid or tissue comprising an optical device which comprises: a light source for emitting light onto the element; and a spectrometer for recording the spectrum of light from the element, said light from the element being of transmittance, reflectance or Raman scattering of the emitted light by said element; the optical system further comprising a data processing module configured to: convert the recorded spectrum by a conversion matrix into a standardized spectrum, wherein said conversion matrix has been obtained by calibrating the optical system spectrum response against a spectrum reference; pre-process the converted spectrum; correlate, for parameter quantification, the converted pre-processed spectrum with pre-obtained spectral bands for each parameter; said spectrum being contained within uv-vis-nir wa

Abstract: The aircraft is capable of two distinct fuel-efficient flight regimes: one is a vertical flight regime supported by two large two-bladed rotors with low disc loading located on right and left longitudinal booms. The booms extend between outboard regions of a front wing and inboard regions of a rear wing that has a larger span an area than the front wing. The other flight regime is high speed up to high subsonic Mach number with the aircraft supported by wing lift with high wing loading, and with the rotors stopped and faired with minimal local drag contiguous to the booms. The longitudinal location of the aircrafts center of gravity, aerodynamic center and the center of the rotors are in close proximity. The front wing is preferably swept back, and the rear wing is preferably of W planform.

Abstract: The aircraft is capable of two distinct fuel-efficient flight regimes: one is a vertical flight regime supported by two large two-bladed rotors with low disc loading located on right and left longitudinal booms. The booms extend between outboard regions of a front wing and inboard regions of a rear wing that has a larger span an area. The other flight regime is high speed up to high subsonic Mach number with the aircraft supported by wing lift with high wing loading, and with the rotors stopped and faired with minimal local drag contiguous to the booms. The longitudinal location of the aircrafts center of gravity, aerodynamic center and the center of the rotors are in close proximity. The front wing is preferably swept back, and the rear wing is preferably of W planform.

Abstract: A wave reducing and eliminating ship hull including a generally triangular hull having a pointed narrow bow portion and a stern portion wider than the bow portion, the hull including generally rectilinear diverging sides extending substantially from the bow to the stern. The hull further includes a draft adjacent the bow deeper than the draft adjacent the stern, and the bow portion of the hull is generally free of depending structures.

Abstract: A transonic hull having a bow, a stern, a longitudinal length therebetween, side surfaces extending from the bow to outboard portions of the stern, a lower surface extending between the side surfaces, the transonic hull having a submerged volume with an approximately triangular shape in planview with apex adjacent the bow and a base adjacent the stern, and an approximately triangular shape in side view when in motion with a base adjacent the bow and an apex adjacent the stern.

Abstract: A transonic hull having a bow, a stern, a longitudinal length therebetween, side surfaces extending from the bow to outboard portions of the stern, a lower surface extending between the side surfaces, the transonic hull having a submerged volume with an approximately triangular shape in planview with apex adjacent the bow and a base adjacent the stern, and an approximately triangular shape in side view when in motion with a base adjacent the bow and an apex adjacent the stern.

Abstract: The invention refers to mono- and divalent (diabody) single chain Fv (scFv) antibody fragments, obtained by recombinant DNA techniques from the anti-carcinoembryonic antigen (CEA) monoclonal antibody (Mab) CB/ior-CEA.1. This antibody has high affinity for CEA and is employed in the diagnosis and follow-up of human colorectal tumors. As the original Mab, the monovalent fragment and the diabody exhibit high affinity for human CEA and recognize an epitope dependent of carbohydrate conservation. The monovalent scFv fragment and the diabody have affinity constants for CEA of (5.0±0.4)×109 L mol?1 and (2.8±0.3)×1010 L mol?1, respectively. These two fragments do not show cross reactivity with human normal cells and tissues, exception made of the normal colonic mucosa, where CEA is occasionally present.

Abstract: A transonic hull having a bow, a stern, a longitudinal length therebetween, side surfaces extending from the bow to outboard portions of the stern, a lower surface extending between the side surfaces, the transonic hull having a submerged volume with an approximately triangular shape in planview with apex adjacent the bow and a base adjacent the stern, and an approximately triangular shape in side view when in motion with a base adjacent the bow and an apex adjacent the stern.

Abstract: A transonic hydrofield TH has been established which defines the shape of a displacement transonic hull (TH). The hydrofield is characterized in not having curvatures such as shoulders, midbody, or rear quarter, with a deep draft forward and shallow draft aft. In consequence of TH's shape, surface wave-making sources typical of conventional displacement hulls are eliminated. The transonic hull TH corresponding to the hydrofield has substantially triangular waterplane in dynamic displacement conditions, maximum draft forward, and minimum draft aft, and planing lateral surfaces inclined at large angle are vertical to the waterplane.

Abstract: In this invention there is taught the use of air tubes or fluid-filled containers to define permanent hollow tubular space within a body of solidified fill material placed in a mining excavation. The fill uses a mixture of solids and liquids with the addition of a structurally binding substance such as cement in order to make the fill substance permanent and capable of providing structural integrity and strength in the fill notwithstanding the empty tubular space. The empty tubular space can be used in accessways for mining and hauling of ore, or ventilation; it can also be used to provide volume within which to place fine component of tailings of a concentrator, or to store contaminants, or to route fill material. The tubular empty space within the fill reduces the weight, time and cost of the fill operation, and eliminates the need to drive galleries in waste rock, or of constructing costly timbered galleries or steel tubes within the stope prior to backfilling with tails.

Abstract: An airfoil is specified with a double slotted leading edge flap having two members and adapted to be used together with a multi-slotted trailing edge flap. The leading edge flap uses two slots for landing and one or no slots for take off. The front leading edge flap member has specific shape parameters and curvatures. The rear leading edge member defines a slot substantially downstream of the cruise leading edge. Ahead of the trailing edge flap slot, there is provided a special slot across the wing's surface in special cooperation with a spoiler. The airfoil surface between the downstream slot of the leading edge flap and the special slot near the trailing edge flap is short and with negligible camber. Special consideration is given to wing torsion, fuel volume, number of slots, and effect of varying airfoil thickness on flap geometric and aerodynamic parameters.