81results about How to "Minimizing weight" patented technology

An inerting system (10) for an aircraft (12) includes one or more fuel tank circuits (15) associated with fuel tanks (16). An air source (17) supplies pressurized air. A heat exchanger (56) cools the pressurized air. An air separation module (46) is in fluid communication with the heat exchanger (56) and separates inerting gas from the pressurized air. A controller (40) controls flow of the inerting gas from the air separation module (46) to the fuel tanks (16).

A thermal management system for an aircraft is provided. The aircraft includes a primary air conditioning system which compresses and cools outside air to create inside air. The inside air pressurizes the internal volume of the aircraft and ventilates a first object in the internal volume. An exhaust exhausts a portion of the inside air to allow more outside air to be drawn into the aircraft. A cooler cools a coolant which in turn controls temperature of at least two objects in the internal volume.

An airbag configuration for braking the landing impact of flying payloads has a central airbag (17) and at least one torus ring (11, 12, 13) surrounding the central airbag. A payload (L) is attachable on the central airbag (17). A stabilizing device (19) is provided which extends from the lowermost portion of the at least one torus ring (11, 12, 13) to the central airbag (17). The central airbag provides primarily vertical braking of the landing impact while the torus ring provides primarily horizontal braking of the landing impact.

A turbocharger, having an axial compressor wheel and an axial turbine wheel mounted on a first shaft supported by a housing, and a radial compressor wheel and a radial turbine wheel mounted on a second shaft, the second shaft concentrically extending around the first shaft and being supported by the housing. The housing defines a first duct extending axially from the exducer of the axial compressor to the inducer of the radial compressor, and a second duct extending axially from the exducer of the radial turbine to the inducer of the axial turbine. A plurality of controllable compressor guide vanes extend through the first duct, and a plurality of controllable turbine stator vanes extend through the second duct. The housing is provided with variable diffuser vanes at the exducer of the radial compressor, and with variable turbine vanes at the inducer of the radial turbine. The variable turbine vanes and the turbine stator vanes are controlled to accurately control the rotation rate of the radial and axial turbines. The compressor guide vanes are controlled to minimize surge and maximize choke flow rate.

An inerting system (10) for an aircraft (12) includes one or more fuel tank circuits (15) associated with fuel tanks (16). An air source (17) supplies pressurized air. A heat exchanger (56) cools the pressurized air. An air separation module (46) is in fluid communication with the heat exchanger (56) and separates inerting gas from the pressurized air. A controller (40) controls flow of the inerting gas from the air separation module (46) to the fuel tanks (16).

A system and method relating to the measuring of torque in a rotating shaft is provided. An optical torque sensing system comprises a rotating shaft, wherein a sleeve of photo-elastic material overlays a portion of the shaft. A light emitting component delivers light into the photo-elastic material, wherein the light delivered by the light emitting component is directed through the photo-elastic material along an axis of the rotating shaft. A capturing component captures the light that exits the photo-elastic material. The exiting light comprises fringe pattern data, and a computing system computes torsion strain of the shaft based at least in part on the fringe pattern information.

There is provided an avionics system that provides several avionics functions within a single LRU. In one embodiment, the system comprises a software-configurable RF assembly, one or more processor assemblies that are configured to provide multiple TAWS / TCAS / Mode S / ADS-B / ATC functions, interfaces to allow connections to aircraft electronics and data loaders, and multipurpose antennas. In one embodiment, a common processor architecture allows generic avionics processors to be configured to operate a number of TAWS / TCAS / Mode S / ADS-B / ATC functions without the need for multiple LRUs, and software-defined RF functions allow RF circuitry that interfaces to the processors to handle current and future communication needs.

Actuation system for a door lock, where the door lock comprises a lock bolt driven by rotation of a lock pin that is functionally connected to the lock bolt. The actuation system comprises a cylindrical handle (5) with an outer diameter of between 6 and 9 cm. The system comprises a first pin receiver (8a) centred on the cylinder axis and a second pin receiver (8b) provided off centred between the cylinder axis and the cylindrical handle in order to be flexible with respect to post-mounting the actuating system on doors with already existing lock.

An optical coherent receiver in one embodiment has a heterodyne configuration, and in another embodiment has a homodyne configuration, in each configuration employs multiple feedback signaling and analog / digital processing to optimize response to a modulated optical input signal, the provision of both individual RF I and RF Q channel outputs.

A self-charging organic electroluminescent display is disclosed. A solar cell and an organic electroluminescent device are installed on a same substrate or different substrates. Using the photoelectric conversion property of the solar cell, the solar energy is converted into electrical energy and stored in a battery. Therefore, the electrical energy converted from the solar energy can be provided for the organic electroluminescent device to emit light, forming a self-charging organic electroluminescent display module.

A machine tool of small scale, light weight, and low cost, yet accomplishing a high degree of precision in machining. A spindle (2) is encased in a body frame (1) and disposed preferably in such a manner that the spindle (2) is movable along an axial center thereof or Z-axis direction by means of a Z-axis moving means (4). Either Y-axis table (5) or an X-axis table (6), at least being capable of moving along X-axis or Y-axis direction, or both is provided at one end of the spindle (2) on one side of the body frame (1) and arranged to be vertical with respect to the axial center of the spindle (2).

A thermal management system for an aircraft is provided. The aircraft includes a primary air conditioning system which compresses and cools outside air to create inside air. The inside air pressurizes the internal volume of the aircraft and ventilates a first object in the internal volume. An exhaust exhausts a portion of the inside air to allow more outside air to be drawn into the aircraft. A cooler cools a coolant which in turn controls temperature of at least two objects in the internal volume.

An interface jig for removably securing a portable auger to a vehicle includes a carriage guide assembly, a sliding carriage assembly and a receiver assembly. The carriage guide assembly includes a vertical support having an upper portion and a bottom portion. A hitch adapter is affixed to the bottom portion to secure the carriage guide assembly to a vehicle hitch receiver. The sliding carriage assembly includes a horizontal member having a first end opposite a second end. The first end Is affixed to a vertical member that slides along the vertical support between the upper portion and the lower portion of the carriage guide. The receiver assembly is attached to the second end of the sliding carriage assembly.

An insert comprising a lightweight structure configured for filling the gaps between axially spaced C-shaped lamination stacks and circumferentially spaced non-magnetic cradles on a permanent magnet rotor. The insert is secured to a rib by a dovetail tongue that fits within a dovetail groove provided along the length of each rib. The insert engages the adjacent cradles and has a circumferential surface that has the same radius of curvature as the top surface of the cradles.

A novel loop antenna containing a thin-walled ferrite box or other hollow; magnetic core structure of high permeability (considerably greater than 100), particularly useful for crossed loop antennas, and of optimal geometry and configuration for minimum volume, weight and space.

A small bend radius connector for a heater core is shown, wherein a first end of the connector has a rectangular cross section, a second end of the connector has a circular cross section, and wherein a size, a weight, and a cost of production of the connector are minimized.

An optical coherent receiver in one embodiment has a heterodyne configuration, and in another embodiment has a homodyne configuration, in each configuration employs multiple feedback signaling and analog / digital processing to optimize response to a modulated optical input signal, the provision of both individual RF I and RF Q channel outputs.

An acoustic assembly including a thin sound absorbing panel supported by foldable mounting brackets is adapted to be mounted upon the walls of an indoor listening enclosure. The space behind the panel functions as an acoustic diffusion chamber which augments the acoustic performance of the panel. A number of such assemblies are employed in a manner such that the panels are offset from the wall and downwardly angled.

A faucet assembly with an insulating core is disclosed. The insulating core has an inlet, an outlet and a socket portion communicating the inlet and the outlet, and is made of polyoxymethylene (POM). The faucet assembly has a controlling valve configured to be received in the socket portion for controlling the inlet and the outlet to communicate with or separate from each other and a metal body configured to contain the insulating core therein and having a knob for operating the controlling valve to communicate or separate the inlet and the outlet with or from each other, thereby allowing or disallowing water supply. The insulating core serves to insulate water flowing therethrough from the metal body thereof in terms of heat transmission and metal contamination.

A pedal-drive system for propelling multi-wheeled cycles includes two pedal level arms connected to a pair of two-bar linkages, which are drivingly attached to corresponding crank pins on each respective side of a common drive spindle, perpendicular to the cycle frame. The linkages rotate the said spindle per each pedal's downward stroke so that when one pedal arm is all the way down, the opposite pedal's crank pin is already beyond full up position, thus ensuring continuous rotation of the drive system. A sprocket on the spindle drives a chain, that drives a sprocket on a back wheel. For higher speeds, a typical bicycle multi-sprocket-cone and speed changing chain-derailleur may be incorporated. The pedal system may be used for small to large manually powered cycles, particularly scooters and bicycles, and may also include an auxiliary electric motor and battery for propulsion.

A head assembly for a rotary tool, comprising a body arranged for connection to a drive means, the drive means rotatable about a first axis of rotation; a rotatable element arranged for connection to a pad assembly, the rotatable element rotatable about a second axis of rotation disposed substantially parallel to the first axis of rotation; and, a locking assembly arranged to lock the rotatable element to the body to prevent rotation of the rotatable element relative to the body about the second axis of rotation.

A detachable synthetic rope connector with connector body, bale, main load pin sub assembly, and a restraining load sub assembly that permits the use of large diameter synthetic and other mooring components such as cable and chain on offshore work vessels without specialized deck equipment. The inventive connector allows for safe and redundant restraint of a mooring segment in order to provide transfer of the tension load while providing connection features that simplify separation and the reduction of safety risks to vessel working personnel and the environment, and the features allow for the connector to be separated easily while the portion holding the rope is restrained while the bale can be removed.

A multi-function combat laser is described that uses single or multiple laser sources (laser diodes) in a configuration such that when it is coupled with a dichroic substrate the laser sources outputs are coupled to produce a single desired output. The multi-function combat laser consolidates multiple laser functions for the dismounted soldier into a single package with shared power supplies, optics and laser sources.

An air cooling system for an unmanned aerial vehicle including a propeller (14) driven by an engine (12) has at least one cooling air duct (22) to direct cooling air to cool a vehicle component e.g. a cylinder head. The duct has at least one air inlet and at least one air outlet. Operation of the propeller causes a pressure differential between the air outlet (24,124) and the air inlet (23,123) which draws air through said cooling air duct (22). A cowling (16) can cover at least part of the engine, and can form a plenum and have the supply of cooling air through a front face aperture (164) or side walls (17) of the engine cowl (16).

Hollow fan blades for turbo fan gas turbine engines are formed of two separate detail halves. Each detail half has a plurality of cavities and ribs machined out to reduce weight. These detail halves are subsequently bonded and given an airfoil shape in the forming operation. In one embodiment, contiguous cavities are formed around freestanding ends of the ribs to reduce the number of cavities required. The freestanding end of each rib is flared such that it has a larger width than the rest of the rib. The cavity extends continuously around the free, flared end of the rib.

An improved pulper, mixer or defibering, rotor having a spar ring attached to a hub of the rotor with a series of curved vanes projecting from the spar ring. The curved vanes have a vane face and a trailing edge. The trailing edge may be unitary and integral with the vane, or may be segmented in combination with trailing edge portion provided on an underlying spar stub to which the vanes are attached. The hydrodynamic suction created by the trailing edge is enhanced by the addition of a dam at the vane tip end of the trailing edge zone. The vanes have a constant vane face angle relative to radians extending outward from the hub of the rotor. As a result of the constant vane face angle the pulp, or other materials, mixed by the vanes during rotation of the rotor are more consistently in contact with the vanes during rotation of the rotor. The vanes are also streamlined to reduce hydrodynamic drag especially at the vane tips where speed and therefore drag potential are at their highest levels. As a result, increased circulation and pumping effects with minimal power requirements are achieved. The vanes may be made of high wear resistant materials and are easily accessible for maintenance, repair or replacement.

The stimulated Brillouin scattering optical amplifier includes a first control optics assembly, a driver element, a second control optics assembly, a Brillouin active medium, and egressing optics. The first control optics assembly receives an incoming laser beam and adjusts that incoming laser beam in accordance with first desired wavelength, polarization and beam propagation parameters. A driver element produces a driver laser beam. A second control optics assembly receives the driver laser beam and adjusts that driver laser beam in accordance with second desired wavelength, polarization and beam propagation parameters. A Brillouin active medium receives an output from the first control optics assembly and an output from the second control optics assembly. The Brillouin active medium provides a non-linear optical interaction between the outputs such that the incoming laser beam is amplified producing an amplified Brillouin active medium output laser beam and a depleted driver laser beam. Egressing optics receives the amplified Brillouin active medium output laser beam and the depleted driver laser beam. The egressing optics controllably transmits the amplified Brillouin active medium output laser beam in accordance with third desired wavelength, polarization, and beam propagation parameters and prevents transmission of the depleted driver laser beam. The output of the egressing optics includes an amplified egressing optics output laser beam.