141 results about "Laser propulsion" patented technology

An unmanned air vehicle is provided, which includes an airframe and a parallel hybrid-electric propulsion system mounted on the airframe. The parallel hybrid-electric propulsion system includes an internal combustion engine and an electric motor. A hybrid controller is configured to control both the internal combustion engine and the electric motor. A propeller is connected to a mechanical link. The mechanical link couples the internal combustion engine and the electric motor to the propeller to drive the propeller. An alternate unmanned air vehicle includes a second propeller driven by the electric motor. In this alternate unmanned air vehicle, the internal combustion engine is decoupled from the electric motor.

A hybrid propulsion aircraft is described having a distributed electric propulsion system. The distributed electric propulsion system includes a turbo shaft engine that drives one or more generators through a gearbox. The generator provides AC power to a plurality of ducted fans (each being driven by an electric motor). The ducted fans may be integrated with the hybrid propulsion aircraft's wings. The wings can be pivotally attached to the fuselage, thereby allowing for vertical take-off and landing. The design of the hybrid propulsion aircraft mitigates undesirable transient behavior traditionally encountered during a transition from vertical flight to horizontal flight. Moreover, the hybrid propulsion aircraft offers a fast, constant-altitude transition, without requiring a climb or dive to transition. It also offers increased efficiency in both hover and forward flight versus other VTOL aircraft and a higher forward max speed than traditional rotorcraft.

Microfluidic devices and methods for operations on micro through nano-meter scales. Methods of processing, handling and analysis of yocto-liter scale volumes. Methods and devices for single-molecule transports in milli-scale dimensions. Methods of laser propulsion of individual cells and droplets. Methods of packaging and manufacturing of micro and nanofluidic devices. Method of improving dispensing accuracy. Methods of uses and manufacturing of micro-optico-fluidic devices. Bottom up processing method. Ionic particle deflector device. Smart package device and methods for high-throughput synthesis and screening. Methods and devices for controlled refills of micro stamps. Methods and devices for insitu concentration and dilution of micro volumes of solids and liquids. Methods and devices for eliminating undesirable dry outs and evaporation of microscale volumes of fluids.

This invention is a pneumatic mass transportation system on the cutting edge of technology employing a combined cycle turbine power system with digital controls to effect acceleration, deceleration and train propulsion. The combustion turbines can be adapted to use alternative fuels including bio fuels as they are developed. The heat recover steam generator will recycle the hot exhaust gasses from the turbines to generate electricity to be used by the system. The multi-car train is propelled by differential air pressure forward and aft of the vehicle in the pneumatic tube. Air propulsion is achieved by large in-tube impellers driven by the turbines. A digital control system will operate the pitch of the impeller blades and the vacuum/pressure release valves in the tubes to produce full movement control of the trains.

An electromagnetic compatibility test method for electric propulsion system comprises the following steps: wave transparent rate of wave transparent subsidiary cabins of electric propulsion system is measured; steady state and transient state electric field radiation of electric propulsion system and steady state power line conducted emission are measured; spike of power line when electric propulsion system is in transient state working condition is measured; conduction of fictitious load and radiation emission characteristic and actual thrustor are compared and measured; influence of plume to communication is measured to obtain electromagnetic compatibility test data of electric propulsion system. The inventive method is not required to be carried out in an electromagnetic compatibility laboratory, and can be tested on out-field or working site of electric propulsion system, the test result has little error and can authentically reflect electromagnetic compatibility of the propulsion system, thus greatly lowering test cost and improving working efficiency.

The invention discloses a novel electric propulsion system. The system comprises an internal combustion engine, an electric generator, an electric distribution system, a propulsion motor and a propeller, wherein the electric generator is in cable connection with the propulsion motor through the electric distribution system; the propulsion motor is connected with the propeller through a clutch and a speed reducer; both the electric generator and the propulsion motor are synchronous motors; and the propeller is an adjustable pitch propeller. The novel electric propulsion system effectively solves the problems of high investment cost, electric loss, severe harmonic pollution, difficult maintenance and high failure risk due to the adoption of a variable frequency technique by the electric propulsion system in the prior art and also solves the problems of high voltage drop in a system power grid and big torque born by a starting transient mechanical shaft due to the high starting transient current in the electric propulsion system in the prior art. The novel electric propulsion system has little investment, convenient installation and maintenance, a low running cost, high system reliability, low failure risk in a use process and a remarkable economic benefit.

The invention discloses a radiation electromagnetic compatibility test method for an electric propulsion system and on-star radio frequency equipment. Firstly, an ion thruster is arranged in a wave transmitting secondary cabin; the wave transmitting secondary cabin is connected with a main vacuum tank; and electromagnetic radiation interference produced by a plume of the ion thruster is emitted out of the main vacuum tank through the wave transmitting secondary cabin. Each equipment and antenna are connected. When the electric propulsion system is started to normally work, both uplink level and downlink level of a responder are weak levels; conditions of uplink instruction reception and downlink remote metering error code are checked; if the instruction reception is correct, the code ratemeets the requirement and the responder is not interfered; remote metering parameters for a GPS (Global Positioning System) receiver are observed, and absolute positioning condition and relative positioning condition are determined; and if the remote metering is correct and the positioning is normal, the GPS receiver is not interfered.

A space vehicle (1), in particular a satellite or a probe, capable of executing high-thrust maneuvers or high specific impulse maneuvers. According to the invention, the space vehicle (1) includes at least one solid-propellant chemical thruster (10-14) and at least one electric thruster (20-24).

The invention discloses a ship electric propulsion system with hybrid power supply of a diesel generator set and a power battery. The system comprises a ship control system, a power system, a distribution board and an electric propulsion system, wherein a power management controller and a propulsion manipulation controller are arranged in the ship control system; the power system is connected with the electric propulsion system through the distribution board; the power system and the distribution board are connected with the power management controller respectively; and the electric propulsion system is connected with the propulsion manipulation controller. A shore power distribution box, a diesel generator set and a power battery pack are arranged in the power system; a frequency converter is arranged in the electric propulsion system and connected with a propulsion motor; the propulsion motor is connected with a propeller; a busbar is arranged in the distribution board and provided with a main switch and a load switch; the main switch is connected with the generator set; and the load switch is connected with the frequency converter. By adopting the hybrid power supply mode of diesel generator set and power battery, the safe sailing of the ship is ensured, and the continuation performance of the ship is improved.

The invention discloses an electric propulsion system for hybrid power boats and an implementation method thereof, wherein the electric propulsion system is suitable for inland river medium and small-sized river boats and comprises a power battery used as a system main power supply and a diesel generator set used as an auxiliary power supply. When a boat berths alongside and suspends shipping services, the power battery is charged by a shore power so as to store electric energy; when the boat sails normally, the electric propulsion system is powered by the power battery; when the stored electric energy of the power battery are completely consumed or the power battery goes wrong in the process of sailing, the auxiliary diesel generator set automatically starts and puts into operation so as to continue to supply power for the electric propulsion system to maintain the sailing of the boat; and in emergency, the power battery and the diesel generator set work together to supply power for the electric propulsion system so as to ensure the sailing safety of the boat. By using the system and the implementation method of the system disclosed by the invention, boats can realize zero discharge of waste gas/water, and remarkable effects of energy saving and expenditure cutting are generated; meanwhile, the hybrid power supply mode of the power battery and the diesel generator set ensures the sailing safety of a boat and improves the duration performance of the boat.

The invention discloses a comprehensive optimization method of a simulation credibility evaluation model of an electric propulsion system. The comprehensive optimization method comprises the following steps: decomposing the electric propulsion system into multiple subsystems; decomposing the subsystems under various standards of a simulation system with an establishment process of system simulation as an evaluation standard until obtaining a minimum unit; carrying out topology modeling on the electric propulsion system; collecting branch voltages, a phase angle, active power and passive power of the electric propulsion system; adopting corresponding intelligent algorithms to optimize different attributes of the electric propulsion system to obtain a credibility evaluation optimization model; collecting data of an actual system under the same working condition, and using the credibility evaluation optimization model to test the actually collected data to obtain credibility; if the credibility is smaller than a credibility index n, carrying out topology modeling on the electric propulsion system again; and if the credibility is larger than the credibility index n, the credibility evaluation is terminated. The comprehensive optimization method disclosed by the invention is high in stability and is high in reliability.

The invention belongs to the power system risk evaluation technical field and provides a risk predictive evaluation method and device of a ship integrated electric propulsion system. The method includes the following steps that: the ship integrated electric propulsion system ship is divided into a plurality of subsystems, and all the sub systems are divided into a plurality of units; the failure rates and repair rates of all the units are calculated; the topological model of the ship integrated electric propulsion system is established; load flow calculation is performed on the ship integrated electric propulsion system under a normal working condition and a non normal working condition based on the topological model, so that risk evaluation results can be obtained; and the risk evaluation report of the ship integrated electric propulsion system is obtained according to the risk evaluation results. With the method and device of the invention adopted, the accurate risk evaluation results of the ship integrated electric propulsion system under different working conditions can be obtained, and therefore, a foundation can be laid for the improvement the performance of the ship electric propulsion system.

Provided are an all-satellite electromagnetic compatibility verification method and system based on an electric propulsion radiation emission simulator. The method includes firstly obtaining a radiation emission parameter of an electric propulsion system under a real ignition condition under vacuum conditions; constructing an electric propulsion electromagnetic radiation emission simulator which can generate the same electromagnetic radiation emission as the radiation emission parameters under the actual ignition conditions of the electric propulsion system; finally, in the all-satellite electromagnetic compatibility test, and the electric propulsion radiation emission simulator is used instead of the electric propulsion radiation emission under vacuum ignition conditions, to complete thetesting and evaluation of the satellite electromagnetic compatibility of the electric propulsion system. According to the all-satellite electromagnetic compatibility verification method and system, the range of radiated interference intensity of an electric thruster working normally to the satellite, and the test frequency band covers the frequency range of 1 GHz to 31 GHz; the magnitude of the electromagnetic radiation interference of the electric propulsion work is confirmed through the testing of three phases, and the electromagnetic radiation effect of the electric propulsion work processdoes not affect the normal operation of the all-satellite communication load in the L-band, C-band, Ku-band and Ka-band.

The invention discloses a novel ship electric propulsion system which adopts a power supply mode of taking a fuel cell as the main power supply and an energy storing battery pack as assistance. In the process from cold start to normal operation of a fuel cell system, or when the fuel cell system cannot output electric energy due to sudden failure, the electric propulsion system supplies emergency power by use of the energy storing battery; after the fuel cell system enters the normal operation state, the energy storing battery is in a floating charge state which can output electric energy anytime once the fuel cell system cannot supply power normally; in the case of sudden load reduction during the ship control or sudden effect of wind, wave or current, the electric propulsion system generates transient reverse power and produces regenerative electric energy; such regenerative electric energy is absorbed by the energy storing battery pack in the floating charge state so as to ensure the operation safety of the ship electric propulsion system; and by recycling the regenerative electric energy, the energy is saved. Through the invention, zero emission of the ship can be realized, and the ship electric propulsion system is a real green ship electric propulsion system.

Systems and methods are disclosed employing electric propulsion stationkeeping in a cyclical manner to better match the cyclical pattern of power generated by the solar array system. For a typical orbit design, e.g. a geostationary orbit, North-South stationkeeping can be intermittently suspended, tolerating some additional drift but yielding in a very significant reduction in the required solar power system. If necessary, stationkeeping can be supplemented with a chemical thrusters during off periods for the electric propulsion. Because of this, the overall electrical power margin for the solar array system design can be reduced without compromising the mission performance.

The invention discloses a laser propulsion aircraft with vector nozzle, comprising an effective load and control instrument bay (1), a propellant storage box (2), a plane reflecting mirror (3), a concave paraboloid reflecting mirror (4), a convex paraboloid reflecting mirror (5), a high transmittance plate glass (6) and a laser propulsion engine (7). The effective load and control instrument bay is set on the head of the aircraft; said propellant storage box is set in the middle part of the aircraft and is adjacent to the effective load and control instrument bay. The concave paraboloid reflecting mirror and the convex paraboloid reflecting mirror are set on the aircraft belly on the back position, wherein the two mirrors have the same axle line and focus. The high transmittance plate glass is set below the convex paraboloid reflecting mirror and is round plate glass, and diameter thereof is slightly bigger than that of the concave paraboloid reflecting mirror, and is embedded in the shell of the aircraft belly. The plane reflecting mirror is set on the top of the concave paraboloid reflecting mirror. The invention provides a laser propulsion aircraft, which has uncorrelated propulsion direction and laser beam direction, pollution free engine and lower requirement on performance of laser incoming window of the thrust chamber, for aerospace launch and proximity space flight.

A space propulsion system includes an electrostatic thruster with a first electrical load; a resistojet; a propellant fluid feed circuit; and an electrical power supply circuit including a first power supply line and a first switch for selecting between connecting the first power supply line to the resistojet and connecting the first power supply line to the first electrical load of the electrostatic thruster. The propulsion system thus enables a space propulsion method to be applied that includes a switching step for selecting a first propulsion mode in which the resistojet is activated, or a second propulsion mode in which the electrostatic thruster is activated.

The invention discloses a marine extended-range fuel cell hybrid electric propulsion system and a control strategy thereof. The marine extended-range fuel cell hybrid electric propulsion system is suitable for small-and-medium-sized ships in inland rivers and lakes, and is the hybrid electric propulsion system that uses a lithium battery as a main power source of the electric propulsion system andallows the lithium battery and a fuel cell engine to be grid-connected to be used as a range extender through a diode and a controllable switch. On the one hand, in the navigation process of a ship,when the nuclear charge state of the lithium battery is low, the fuel cell engine is started to charge the lithium battery, and the cruising ability of an electric propulsion ship is improved; and onthe other hand, the fuel cell engine and the lithium battery are grid-connected when the power output is large, the advantages of the lithium battery are fully exerted, the application defects of a fuel cell are overcome, multiple working modes are applied to be switched to each other, the sailing working conditions of the ship are met, and the effects of energy conservation and emission reductionare achieved.

The invention discloses a vector magnetic nozzle used for electric propulsion. The vector magnetic nozzle is composed of a permanent magnet arranged in front of a plasma flame-spraying nozzle and a plurality of non-concentric coils which are arranged at the back of the nozzle and form a dipole field. The permanent magnet and the non-concentric coils form a double-magnetic mirror tube so that plasmas can be in reciprocating motion in the double-magnetic mirror tube. The plasmas are heated in effect of ion cyclotron wave resonance under current modulation of the non-concentric coils. Proportion of current on the plurality of non-concentric coils when the plasmas are released from the magnetic nozzle is adjusted so that the vector direction of an external magnetic field of the plasma flame-spraying nozzle of a propeller deviates from the central axis of the propeller so as to guide the flow direction of external plasmas and further to change the thrust vector direction of the propeller. The vector magnetic nozzle can greatly reduce the quantity of the propellers of an attitude control system through vector propulsion, simultaneously greatly improves reliability of the attitude control system, enables vertical speed of the plasmas to be converted to parallel speed, improves parallel flow rate of external flow plasmas, and achieves the purpose of increasing thrust.