108results about How to "Reduce system weight" patented technology

A method of producing a nuclear medicine image of a subject comprising the steps of acquiring nuclear image data suitable to produce a nuclear tomographic image, the data being acquired by at least one gamma camera head (12, 14) rotating about the subject at an average first rate, acquiring x-ray imaging data suitable to produce an x-ray tomographic image for attenuation correction of the gamma camera image, the data being acquired by an array of detectors (20) irradiated by an x-ray source (18) rotating around the subject at an average second rate which is within a factor of 10 of the first rate, and reconstructing an attenuation corrected nuclear medicine image utilizing the nuclear imaging data and x-ray imaging data.

An oxygen concentrator system that includes or can be expanded to include more than one compressor is provided. The system utilizes a controller that is adapted to selectively activate or deactivate one or more of the compressors to optimize system performance and efficiency. Multiple compressors can be selected to operate at the same time, thereby enabling the system to operate at a higher peak pressure, increase the recovery of the PSA cycle, and expand the product rate. The additional compressors can also be removed when not in use so as to reduce weight of the system. In some implementations, the system housing reserves a certain amount of space for accommodating additional compressors and related components, which can be added to the system as after market parts. In other implementations, the additional compressor can be located external to the system.

A battery cooling system for a vehicle, to warm up or cool down a battery installed in the vehicle by selectively using a refrigerant and a coolant according to a mode of the vehicle may include a heat exchanger, connected with a refrigerant line of a heat pump system through first and second connection lines, connected with a cooling line of a cooling system for an electric device through a battery cooling line, and configured to selectively eat-exchange between the coolant and refrigerant introduced into the heat exchanger, two first valves disposed in the battery cooling line with the heat exchanger disposed therebetween, and selectively connecting the cooling line and the battery cooling line, a first branch line connected with the refrigerant line through a second valve, and a second branch line selectively connecting the refrigerant line and the second connection line through a third valve and a fourth valve.

An optical router switch array includes a plurality of switchable mirror elements having holographic liquid crystal arranged in stack cells. Each of the mirror elements is isolated electrically from the other switchable mirror elements by a plurality of substrates alternative arranged between the switchable mirror elements. Holographic gratings are formed on the holographic liquid crystal by exposure to holography at predetermined incident angles. A single switchable mirror element can also be provided in cases where an array is not required. The switchable mirror elements are polarization insensitive, stable within the operational spectral region, and stable versus temperature. The invention also includes methods for manufacturing a single switchable mirror element and the optical arrray.

The system includes a hydraulic surface actuator for operating a piston coupled to a structural member of an aircraft for moving the structural member. An electrical feedback sensor is coupled to the actuator piston rod. A summing circuit for receiving a command signal and the feedback signal is provided having an output which is coupled to a loop gain compensator for operating a servo motor. The shaft of the servo motor drives the shaft of a variable displacement pump having ports leading to the ports of the actuator. The variable displacement pump has a swash plate the angle of which is reduced by a hinge moment sensor and a de-stroking actuator when the load on the surface actuator exceeds a given percentage of maximum. A pump gain sensor measures the reduction in pump gain and produces an electrical output which is applied to the loop gain compensator to compensate for reduction in pump gain.

An ECS system includes a RAM air fan (RAF) system downstream of a respective heat exchanger in the relatively high temperature RAM exhaust. The RAF includes a RAF electric motor such that the RAF is driven at a speed independent of an ACM which reduces generated noise and increases overall operating efficiency. A fan rotor is completely supported by hydrodynamic foil journal and thrust bearings which permits effective operation of the RAF downstream of the respective heat exchangers in the relatively high temperature RAM exhaust. As the RAF is driven by the RAF electric motor the RAF is installed in the ECS system as a self-contained system such as Line Replaceable Units (LRUs).

The present invention relates to a body armor system designed to maximize protection, optimize mobility and reduce fatigue. More particularly, the system consists of a set of external, highly ergonomic hard armor plates in both ballistic and non-ballistic (riot) configurations, some of which utilize articulating, and/or interleaving segments, in combination with ballistic fabrics and or highly contoured pressed foam padding and harness systems that is flexible and lighter but still provides maximum protection. According to a preferred embodiment, an articulating plate assembly is formed by using plate segments that have at least two (2) step variation in the thickness of each plate along the adjoining seam line between each plate segment so as to facilitate an interleaving, articulating plate system that aids in defeating projectiles that may strike along the seam of adjoining plate segments.

The present invention provides a drive system for a mobile blower or a mobile sprayer. The drive system includes at least one flexible cable drive which connects a fan unit of the mobile blower or the mobile sprayer to a rotary power source to drive the fan. The present invention also provides mobile blowers and mobile sprayers including the drive system.

In a survey system involving either differential global positioning (DGPS) or robotic total station (RTS) systems, the mobile station includes the radio system in the surveyor pole and either connects the laser reflector system or the GPS to the top of the pole or provides a connector for releasably connecting the laser reflector system or GPS. Electric connections between the GPS or laser reflector system, and the radio system are made either by using the physical connector between the pole and the GPS or laser reflector system, or by providing separate electrical conductors and electrical connectors from the pole to the GPS or laser reflector. In the case of a RTS system the base station includes a GPS for locating the position of the base station. For added convenience, the pole may be formed in sections and the power supply may include an inductive coupling battery charger. Data communications may also take place using wireless technology such as Bluetooth.

The invention discloses a satellite-borne GNSS-R multi-beam phased array antenna beam control unit. The satellite-borne GNSS-R multi-beam phased array antenna wave beam control unit comprises a first beam controller and a second beam controller, wherein the first beam controller and the second beam controller are used for conducting calculation and beam control on beam control codes of a multi-beam phased array antenna to the sky and beam control codes of a multi-beam phased array antenna to the ground respectively. Each of the first beam controller and the second beam controller comprises an FPGA phase matching module, a DSP information processing module and a phase matching interface circuit module. Each FPGA phase matching module receives a beam control instruction from a superior instruction unit through the time sequence design of an FPGA; each DSP information processing module is connected with the corresponding FPGA phase matching module, calculates the beam control codes according to the corresponding beam control instruction, conducts various kinds of compensation and splicing operation on the beam control codes and calculation of a check code at the same time, returns a processing result to the corresponding FPGA phase matching module, and conducts movement direction distribution on the beam control codes which are obtained through calculation; each phase matching interface circuit module is connected with the corresponding FPGA phase matching module and a plurality of exciters, and transmits the beam control codes which are processed through movement direction distribution to the corresponding exciters, so that a corresponding phased array antenna unit is controlled.

A cooling air supply system for an aircraft is configured to supply cooling air from the surroundings of the aircraft to at least two devices requiring cooling air (38, 44, 56) within the aircraft. The cooling air supply system includes an air inlet, an air channel communicating with the air inlet, and an air distribution device for the distribution of air from the air channel to the at least two devices requiring cooling air. The air inlet is sized to provide sufficient air flow to accommodate a maximum cooling air requirement of the at least two devices requiring cooling air.

An exemplary optical isolator, such as a magnetic-semiconductor composite optical isolator, and method for making the same, is provided that includes a semiconductor waveguide and a magnetic-semiconductor composite layer. The semiconductor waveguide includes a guide layer, a first clad layer and a second clad layer. The guide layer includes one or more layers with a first end, a second end, a top, and a bottom, the guide layer allows a light wave incident the first end of the guide layer to propagate in a positive propagation direction, and allows a light wave incident the second end of the guide layer to propagate in a negative propagation direction. The first clad layer and the second clad layer are provided, respectively, relative to the bottom and the top of the guide layer, and the second clad layer has a thickness to allow an optical field penetration through the second clad layer. The magnetic-semiconductor composite layer is provided in the presence of a magnetic field oriented in a desired direction and is positioned relative the second clad layer and at a thickness and index of refraction to receive the optical field penetration through the second clad layer and to attenuate a light wave that propagates in the negative propagation direction more than the attenuation of a light wave that propagates in the positive propagation direction. The magnetic-semiconductor composite optical isolator may be integrated with a semiconductor laser, such as on the same semiconductor substrate.

An emergency lighting arrangement preferably includes plural emergency light units connected to an on-board power supply network of an aircraft, and plural emergency current sources that each include at least one capacitor. Each emergency light unit includes an emergency light emitting element and a control unit that automatically connects the capacitor of the emergency current source to the emergency light emitting element upon the failure of the on-board power supply network. Preferably, the emergency current source including the capacitor is integrated into the emergency light unit. The emergency light unit may further include normal operation light emitting elements selectively connected by the control unit to the on-board power supply network. The control unit switches between normal operation of the normal light emitting elements and charging of the capacitor, and emergency operation in which the capacitor discharges through the emergency light emitting element.

A device, system, and method for monitoring tire pressure of a vehicle, involving a sensor having a structure for carrying a primary current to generate a primary electromagnetic field; and a pressure target module having a structure for inducing a secondary current to generate a secondary electromagnetic field when disposed in a vicinity of the sensor during a revolutionary incident.

The invention relates to a charging circuit for an energy storage device (1), having a multiplicity of energy supply branches (Z) each with a multiplicity of energy storage modules (3) for generating an AC voltage at a multiplicity of output connections (1a, 1b, 1c) of the energy storage device (1). The charging circuit has a first half-bridge circuit (9) having a multiplicity of first supply connections (8a, 8b, 8c) each coupled to one of the output connections (1a, 1b, 1c) of the energy storage device (1), a first supply node (37a; 37b; 47a; 47b) coupled to the first half-bridge circuit (9), a second supply node (37a; 37b; 47a; 47b) coupled to a reference potential rail (4) of the energy storage device (1), a converter inductor (10) connected between the first supply node (37a; 37b; 47a; 47b) and the first half-bridge circuit (9), a diode half-bridge (32) coupled between the first supply node (37a; 37b; 47a) and the second supply node (37a; 37b; 47b), and a supply circuit (35; 44, 45) designed to at least occasionally provide a charging DC voltage (U_L) between the first supply node (37a; 37b; 47a; 47b) and the second supply node (37a; 37b; 47a; 47b). In this case, the first half-bridge circuit (9) has a multiplicity of semiconductor switches (9c) each coupled between the first supply node (37a; 37b; 47a; 47b) and one of the multiplicity of first supply connections (8a, 8b, 8c).

A wireless passenger service system for an aircraft having a power system and a cabin management system that includes a wireless receiver and a wireless passenger control unit. The wireless receiver is able to receive a wireless signal and is operationally connected to the power and cabin management systems of the aircraft. The wireless passenger control unit is able to send a wireless signal. In response to receiving a wireless signal from the wireless passenger control unit, the wireless receiver is configured to activate at least one passenger service function of the cabin management system of the aircraft.