32 results about "Thrust efficiency" patented technology

An external jet nozzle mixer (20) includes identically formed lobes (48), equal in number those of the internal mixer (42). External mixer (20) works with internal mixer (42), further to mix the engine internal bypass flow with the internal jet engine core flow, to level the disparate exhaust flow velocities, to reduce the peak velocities from the jet engine core and increase the lower bypass velocities of the engine internal bypass flow, and thereby to reduce noise. The internal lobe contours act as lifting flutes, causing mixing of the primary hot and cold flows before exiting the nozzle. The external lobe contours act as venturi chutes, accelerating the cooler ambient air secondary flow. The lobes thus act collectively as an injector to force the cooler ambient secondary flow into the previously mixed primary flow as it exits the nozzle. Also obtained is an increased thrust efficiency and a consequently decreased fuel consumption and engine emissions.

The invention relates to a reflecting type laser-electromagnetic field coupling thrustor which comprises a laser system, an electromagnetic accelerating electrode assembly and a static electric fieldassembly. The electromagnetic accelerating electrode assembly comprises an electromagnetic accelerating cathode, an electromagnetic accelerating anode and an electromagnetic accelerating electrode power source; the static electric field assembly comprises a static electric field accelerating electrode, a working medium and a static electric field accelerating power source, the static electric field accelerating power source provides power for the working medium and the static electric field accelerating electrode, and a potential difference is formed between the working medium and the static electric field accelerating electrode to form a static electric field; laser plasmas generated by ablation of the working medium by laser beams enter the static electric field, when the laser plasmas accelerated by the static electric field move to the position between the electromagnetic accelerating cathode and the electromagnetic accelerating anode, discharge arcs can be induced to be generated,the laser plasmas are heated by the discharge arcs and are further ionized, the laser plasmas are sprayed out in an accelerated manner under the joint effect of lorentz force and aerodynamic force, and thrust is accordingly generated. The reflecting type laser-electromagnetic field coupling thrustor has the beneficial effects that the thrust is adjustable, the thrust efficiency is high, and the thrust density is large.

The invention provides a wheel rim driven propeller thruster test device comprising a thrusting unit and a supporting unit. The supporting unit is mainly composed of a supporting mechanism and a stand. The thrusting unit is mainly composed of a control mechanism, a transmission mechanism and a thrusting mechanism. The whole thrusting unit is suspended on the stand by the supporting mechanism. The wheel rim driving mode of belt pulley transmission and arrangement of belt pulleys in a conduit is adopted so that transmission energy consumption and noise and propeller cavitation can be reduced and thrusting efficiency can be enhanced. Besides, thrust generated by the thrusting unit can be measured in real time by using the lever principle so as to be simpler and more convenient and more accurate than the conventional method by which thrust is reckoned by the open water performance.

A device for efficient self-contained timely sequential vehicular inertial thrust drive is presented comprising two in opposing motion direction internal frequency modulated mechanical oscillators using the simultaneous and combined effort of straight line and rotational inertial reluctance of flywheels. The oscillator's mass motions are obtained with a motor-generators imbedded into large backrest flywheels reciprocally exerting pulsed drive actions and dynamic braking action onto rotors. The motor generators are controlled by a manually tunable electronic controller allowing the fine tuning of the mass motions for finding the highest thrust efficiency. The oscillator's frequency modulation is obtained with an internal reaction less angular mutual reciprocal torque pulse exertion by the motor between the large backrest flywheels against the fast spinning rotor. The internal cycle is recycling unused backrest flywheel energy back into the power supply allowing for an efficient propulsion cycle without energy loss.

The invention discloses an energy-saving ship thruster, comprising a motor (1), a propeller (2) and a connecting rod (3), wherein the motor (1) and the propeller (2) are connected by a retarding mechanism (4); a beam ring (5) covers the propeller (2); a protective cover (6) is arranged at the opening of the beam ring (5); the motor (1) is a water generator. The speed of the energy-saving ship thruster is easy to control, the thrusting efficiency is high, and the propeller is difficult to damage.

The present invention relates to a marine vessel (1) with a hull (10) with a bottom (11), a bow, a stern (13), and a propulsion arrangement (2) including at least three propulsion units arranged at the stern of the marine vessel. The marine vessel (1) has a base line and a centerline. The at least three propulsion units include a centerline shaft propulsion unit (21) with a shaft line (22) and a propeller (23) and two turnable propulsion units (30) with respective propellers (31) and arranged at opposite sides of the centerline shaft propulsion unit. For improving thrust efficiency, while maintaining optimal steering capability, the propeller (23) of the centerline shaft propulsion unit (21) is arranged at a given distance aft of the stern (13) of the marine vessel (1).

The invention discloses a dish-shaped aircraft, relates to the technical field of aircraft, and provides an aircraft with increased functions of floating and diving on the water surface of the aircraft, high controllability, strong stealth capability and high thrust utilization. The auxiliary devices of the aircraft are packaged and integrated to form a saucer-shaped diving cabin with controllable airtightness. The saucer-shaped diving cabin is placed on the concave side of the saucer-shaped skirt wing to realize the floating and diving of the aircraft; The louver system is lower than three sets, and the louver system forms an annular array with the central axis of the dish-shaped skirt wing as the axis, thereby improving the controllability; the rectifier tube of the power system adopts the design of anti-radar detection and wind gathering.

The invention discloses an aeroengine. The aeroengine comprises a gas compressor, a combustion chamber, a turbine, a nozzle pipe, an auxiliary combustion chamber and an auxiliary nozzle pipe, wherein the gas compressor communicates with the turbine through the combustion chamber; a working medium outlet of the turbine communicates with the nozzle pipe; a working medium leading-out opening is formed in a fluid channel between the gas compressor and the turbine; and the working medium leading-out opening communicates with the auxiliary nozzle pipe through the auxiliary combustion chamber. The aeroengine disclosed by the invention is simple in structure and high in thrust efficiency.

The invention provides a ship thruster. By the aid of a sliding groove disk, two rotatable oblique rotating mechanisms and one group of bevel gear groups connected with a motor, reciprocating blades obliquely rotate at a specific position to provide thrust for a ship. The ship thruster is high in thrusting efficiency, simple to manufacture, low in noise and free from pollution, and the ship, a warship and a submarine can be driven by an internal combustion engine, nuclear power, storage batteries or manpower.

The invention discloses an engine. The engine comprises a pneumatic turbine, a gas compressor, a combustion chamber A, a turbine, a combustion chamber B and a spraying pipe; the pneumatic turbine and the gas compressor are arranged in a transmission manner; the gas compressor is communicated with the turbine by the combustion chamber A; and the turbine is communicated with the spraying pipe by the combustion chamber B. The engine has the advantages of simple structure and high thrust efficiency.

The invention discloses a watercraft or aircraft provided with improved thrusters. The watercraft or aircraft is characterized by comprising a craft body, at least one thrusting device, a control device, an operation device and a power supply device, wherein the at least one thrusting device is mounted on the craft body and used for providing power; the control device is mounted inside the craft body and used for receiving operation signals sent out by the operation device so as to control the at least one thrusting device to work; the power supply device is mounted inside the craft body and used for providing electric energy for the at least one thrusting device and the control device. The watercraft or aircraft has the beneficial effects as follows: the watercraft or aircraft adopts the through flow guiding body design, the power loss of a water suction port of the pump-jet thrusters can be effectively reduced, and the thrusting efficiency can be improved; the jet velocity is greatly increased by the aid of the combination of multiple stages of annular pump-jet thrusters, jet pressure heads are increased, and the combination is a high-speed thruster combination; the watercraft or aircraft can realize intelligent sensing and is flexible to operate and simple in structure.

The invention discloses an air cushion ship model which comprises a ship model body, a plurality of air cushion fans, air inlet channels, a pneumatic thruster and a hydraulic thruster. An air cushion layer is arranged on the front portion of the bottom face of the ship model body, the air cushion fans are arranged on the tail portion of the ship model body, the air inlet channels correspond to the air cushion fans respectively, one end of each air inlet channel is connected with the air cushion layer, the other end of each air inlet channel is connected with the corresponding air cushion fan, the pneumatic thruster is arranged on the top face of the ship model body, and the hydraulic thruster is arranged in the ship model body. A hydraulic thrusting mode and a pneumatic thrusting mode are combined, thrusting efficiency is high, and winding can be prevented.

The invention discloses an engine which comprises a pneumatic turbine impeller A, a pneumatic turbine impeller B, a compressor impeller A, a compressor impeller B, a combustion chamber and a spraying pipe. The pneumatic turbine impeller A and the pneumatic turbine impeller B are arranged in a counter rotating mode. The pneumatic turbine impeller A and the compressor impeller A are arranged in a transmission mode. The pneumatic turbine impeller B and the compressor impeller B are arranged in a transmission mode. The compressor impeller A and the compressor impeller B communicate with each other in a series connection mode. A compressed gas outlet of the compressor impeller B communicates with the spraying pipe through the combustion chamber. The engine has the advantages of being simple in structure and high in thrust efficiency.

The invention discloses a tilt fly-around retention control effect evaluation method based on an eccentricity rate tilt angle vector. According to the method, for a four-pulse configuration retention control process of a formation control model built based on a Gaussian perturbation equation, quick evaluation is carried out on a configuration parameter capture control effect according to the absolute trajectory determination data of a ground measurement and control system; and normal and tangential trajectory control engine thrust efficiency of four pulses is calibrated respectively. With the method adopted, trajectory control precision is improved. The method is high in reliability, high in operability, is easy to popularize and use, and has important guiding significance for task implementation.

A fuselage assembly for an unmanned aerial vehicle (UAV) is provided that includes a top fuselage assembly, a bottom fuselage assembly, and a planar support frame disposed therebetween. The top fuselage assembly and the bottom fuselage assembly may form one or more rotor ducts disposed about the one or more UAV propulsion motor seats, respectively, where the rotor ducts are configured to protect rotating rotors disposed therein from physical damage caused by impacts that are dangerous to fly from the environment. The fuselage assembly may also include a heat sink thermally coupled to the electronics of the UAV and disposed within the fuselage assembly such that rotating blades in the rotor duct draw air from outside the inlet aperture of the top fuselage assembly, through the airflow channel of the dissipative surface in which the heat sink is disposed, and into the rotor duct via the airflow outlet.