79 results about "Jet propulsion" patented technology

The invention relates to the technical field of underwater bionic robots, solves the technical problems that a traditional snake-shaped robot cannot automatically adapt to environment changes, the motion performance cannot be optimized, and multiple propelling modes of the traditional snake-shaped robot cannot be intelligently coordinated, and particularly relates to an underwater bionic snake-shaped robot and a hybrid self-adaptive control method thereof. Comprising a snakelike robot composed of a snakelike body assembly, a snakelike head assembly and a jet propulsion module. A reinforcement learning intelligent body is used for outputting control instructions for motor joints and control instructions for a jet propulsion module according to real-time environment perception and robot state feedback. The control of the motor joints may be adjusting parameters of the central pattern generator to generate a desired joint angle, or directly outputting a desired drive torque for each motor joint. The snakelike robot is suitable for tasks such as pipeline inspection and underwater detection, the manufacturing cost and the maintenance difficulty are reduced through modular design, and the intelligent level of the robot is improved through an advanced control method.

The application relates to the technical field of underwater bionic robots, solves the technical problems that a traditional snake-shaped robot cannot autonomously adapt to environmental changes, optimize motion performance and intelligently coordinate multiple propulsion modes, and particularly relates to an underwater bionic snake-shaped robot and a hybrid adaptive control method thereof, which comprises a snake-shaped robot composed of a snake body assembly, a snake head assembly and a jet propulsion module; control instructions for each electric joint and control instructions for the jet propulsion module are output by using a reinforcement learning intelligent agent according to real-time environmental perception and robot state feedback. The control of the electric joint can be adjusting the parameters of the central pattern generator to generate the expected joint angle, or directly outputting the expected driving torque of each electric joint. The snake-shaped robot provided by the application is suitable for pipeline inspection, underwater detection and other tasks, the modular design reduces the manufacturing cost and maintenance difficulty, and the advanced control method improves the intelligent level of the robot.

The invention discloses a bionic underwater robot based on electromagnetic drive flexible hinge jet propulsion and a motion control method of the bionic underwater robot, and belongs to the technical field of bionic actuators and robots. The multiple electromagnetic actuators arranged in a matrix mode are sequentially connected to form a hinge structure, every two vertically adjacent electromagnetic actuators are symmetrically arranged, the multiple electromagnetic actuators are all arranged on the rear side of the fairing and connected with the fairing through connecting pieces, and the multiple electromagnetic actuators are independently controlled; the comprehensive phase difference and the reversing time difference of the multiple electromagnetic actuators are controlled through the electromagnetic driving controller, differential propulsion is achieved, and flexible steering and efficient movement are achieved. The overall structure simulates the jellyfish appearance design, the appearance design conforming to the flowing resistance reduction characteristic is adopted, the resistance during movement in water can be effectively reduced, the electromagnetic driver is used for generating power, the annular flexible structure is extruded to enable a fluid medium to be rapidly sprayed out, and efficient underwater propelling of the micro-robot is achieved.

A jet propulsion boat includes: a boat body; a propulsion device that imparts propulsion force to the boat body to propel the boat body; an engine and an electric motor that drive the propulsion device; and a control device that determines which of an engine mode and an electric mode is to be used as an operation mode of driving the propulsion device in accordance with a condition, the engine mode configured to drive the propulsion device with the engine and the electric mode configured to drive the propulsion device with the electric motor while stopping the engine, and controls the engine and the electric motor to drive the propulsion device in the determined operation mode.

The utility model discloses a model machine for simulating the principle of a jet propulsion device, which relates to the field of jet propulsion device structures, and comprises a device main body, a servo motor is arranged in the device main body, an air filter matched with the servo motor is arranged in the device main body, the servo motor is connected with a single plunger type cylinder through a crank connecting rod mechanism, and the single plunger type cylinder is connected with the air filter. A displacement sensor is arranged at one end outside the single plunger type cylinder, a water tank is arranged outside the device body, and the water suction end of the single plunger type cylinder is connected with the output end of the water tank through a pipeline. According to the utility model, the servo motor operates, and the crank-link mechanism drives the single plunger cylinder to move. When a plunger rod of the single-plunger cylinder extends out, water in the water tank is sucked into the single-plunger cylinder through the water suction filter, the stop valve, the shock-proof throat and the water suction one-way valve in sequence, in the process, the rotating motion of the motor is successfully converted into the linear motion of the plunger cylinder, stable water suction is achieved, and meanwhile the water suction efficiency is improved by means of all the components. Water is effectively filtered, liquid flow is flexibly controlled, pipeline vibration is reduced, and liquid backflow is prevented.

The invention discloses a compressible fluid reducing vortex method and device, and belongs to the technical field of fluid machinery and jet propulsion. The problems that in the prior art, the energy loss is large, the efficiency is low, and the gas temperature is sharply increased in the compression process are solved. Efficient and controllable conversion among fluid pressure energy, internal energy and kinetic energy can be achieved, an air injection device based on the method can more fully convert heat energy into directional injection kinetic energy through the synergistic effect of acceleration and vortex elimination guide vanes, and the propelling efficiency is remarkably improved; and the stable recovery and conversion of kinetic energy are realized through vortex expansion, and an approximately isentropic mild pressurization process can be realized, so that the temperature rise is obviously inhibited, and the compression energy consumption and the cooling requirement are fundamentally reduced.

The utility model relates to a bionic lobster propeller based on a single-degree-of-freedom connecting rod, which comprises a lobster-head-shaped control cabin and a lobster-tail-shaped bionic jet propulsion unit, the lobster-head-shaped control cabin is used for integrating a power unit and providing installation support, and the rear part of the lobster-head-shaped control cabin is hinged with the lobster-tail-shaped bionic jet propulsion unit; and the shrimp-tail-shaped bionic jet propulsion unit is used for straightening energy storage and bending the reciprocating motion of jet to generate propulsion force. The bionic lobster propeller has the advantages that vortex ring jet flow is generated through bionic lobster tail movement, the hydrodynamic efficiency is remarkably improved, and the energy utilization rate is higher than that of a traditional propeller.

1. The name of the design product: double-body water-jet propulsion unmanned ship. 2. The use of the design product: unmanned ship for water operation. 3. The design points of the design product: in shape. 4. The picture or photo that best shows the design points: perspective view.

The application relates to a pulse jet propeller driven by a polyvinyl chloride electroactive gel material, belonging to the jet propulsion technical field; the propeller comprises a shell and a collapsible cabin arranged in the shell; one-way diaphragm pumps in communication with the collapsible cabin are arranged at the head / tail ends of the shell, water flows into the head end and is sprayed out of the tail end; clamping plate type driving modules are arranged on the two sides of the collapsible cabin; the collapsible cabin is compressed by applying a normal clamping force to the two side walls of the collapsible cabin, fluid in the cabin is extruded and sprayed out to complete a pulse jet propulsion action. The application realizes the water absorption and water spraying action of imitating a squid, and can complete flexible underwater movement and direction adjustment under low energy consumption.

The application relates to an oxygen-enriching device and an oxygen-enriching process thereof, and belongs to the technical field of jet propulsion devices. The oxygen-enriching device comprises an oxygen-enriching disc, one side of the oxygen-enriching disc is provided with an air inlet, and the other side is provided with a plurality of nitrogen-enriched separation outlets; a plurality of centrifugal separation flow channels are arranged in the oxygen-enriching disc, the plurality of centrifugal separation flow channels are sequentially and spacedly arranged along the circumference of the air inlet, one end of the centrifugal separation flow channel is communicated with the air inlet along the length direction of the centrifugal separation flow channel, and the other end penetrates through the oxygen-enriching disc in the direction away from the air inlet; the nitrogen-enriched separation outlet is arranged in one-to-one correspondence with the centrifugal separation flow channel, and the nitrogen-enriched separation outlet is communicated with the corresponding centrifugal separation flow channel; an air suction fan is arranged in the air inlet, and the air suction fan is coaxially connected with the oxygen-enriching disc; and a centrifugal driver is coaxially connected with the oxygen-enriching disc at the driving end. The oxygen-enriching device adopts a mechanical rotary separation mode, does not introduce other consumables, reduces the post-maintenance cost of the oxygen-enriching fan, and reduces the failure rate of the oxygen-enriching fan.

This invention relates to the technical field of power devices and discloses a jet power device, including a cylindrical body with a cavity, a main shaft in the cavity, a compressor and a turbine connected to the main shaft to form a rotor; a diffuser, a guide vane and a burner rotatably connected to the main shaft to form a stator; a tail cone fitted with a tail nozzle to form a tail nozzle channel; air is compressed into high-pressure gas by the compressor, and the high-pressure gas enters the combustion chamber through the diffuser; fuel is atomized into fuel gas through an evaporator, and the atomized fuel gas mixes with the high-pressure gas in the combustion chamber to form an oil-gas mixture, which burns in the combustion chamber to form high-pressure fuel gas, which drives the turbine to rotate after passing through the guide vane, and the fuel gas passing through the turbine is ejected at high pressure from the tail nozzle channel to generate forward thrust. The turbine's work drives the compressor to rotate through the main shaft, and continues to compress air into the air inlet, forming a compression-expansion cycle, which maintains stable operation on its own.

The application relates to a thrust chamber of a jet propulsion device and an adaptive flame stabilizer thereof. The adaptive flame stabilizer comprises two side plates connected in rotation, an oil injection rod and a linkage mechanism. The oil injection rod is arranged between the two side plates, and a first nozzle is arranged on the oil injection rod. The linkage mechanism comprises an extension assembly and two linkage assemblies. One end of the extension assembly is communicated with the first nozzle, and the other end of the extension assembly is rotatably connected with the two linkage assemblies respectively. The ends of the two linkage assemblies away from the extension assembly are rotatably connected with the two side plates respectively. The adaptive flame stabilizer has a thrust state and a non-thrust state. In the thrust state, the oil injection rod sprays oil to the first nozzle, and the extension assembly is elongated to drive the two side plates to rotate to the side away from each other through the two linkage assemblies respectively. In the non-thrust state, the extension assembly is retracted to drive the two side plates to rotate to the side close to each other through the two linkage assemblies respectively.

The invention discloses a bladeless water jet propulsion device, and relates to the technical field of ship engineering or underwater propulsion, the bladeless water jet propulsion device comprises a support and a shell, the shell is provided with two fluid inlets and outlets, and the two fluid inlets and outlets are respectively a water inlet and a water jet; the shell is internally provided with a pressurizing chamber, the pressurizing chamber is communicated with the water inlet and the water injection nozzle, and the shell is rotationally connected with a crankshaft and a double-cavity partition plate which are coaxial with the pressurizing chamber; the two sides of the crankshaft are each fixedly provided with two peristaltic wheels, and the peristaltic wheels located in the portions, on the two sides of the double-cavity partition plate, of the pressurizing cavity are coaxially arranged on the crankshaft. The pressurizing chamber is in a cylindrical shape, and the peristaltic wheel is in a cylindrical shape. According to the novel blade type propeller, the inherent technical problem of a traditional blade type propeller is fundamentally solved, the safety, reliability and environmental adaptability of equipment are remarkably improved, and due to the fact that exposed rotating blades are abandoned, the propelling failure or overload risk caused by the fact that the blades are wound by sundries such as aquatic plants, fishing nets and floating objects is thoroughly eliminated.

The invention discloses a vector nozzle for a robot. Relates to the technical field of jet propulsion equipment. A hollow cavity is formed in a water storage cavity, and a linear nozzle is arranged at one end of the water storage cavity; the steering engine and the electromagnet are both arranged in the hollow cavity, an output shaft is arranged on the steering engine, and a magnetic rod is arranged on the electromagnet; the vector multi-nozzle disc is arranged at one end, provided with the linear nozzles, of the water storage cavity, and a plurality of inclined nozzles are arranged on the vector multi-nozzle disc; the gasket assembly comprises a large gasket and a small gasket, the large gasket is provided with a linear hole and a steering hole, the linear hole faces the linear nozzle, the steering hole corresponds to the inclined nozzle, the large gasket is driven by an output shaft on the steering engine, and the small gasket is driven by a magnetic rod of the electromagnet. According to the vector nozzle for the robot, the yawing moment needed by turning can be directly fused into the jet flow distribution process, the maneuvering performance is remarkably improved, and the weight and fault points of a mechanism are reduced.

The invention discloses a state self-detection and fault self-diagnosis method for a water jet propulsion main control unit, which comprises the following steps of: performing component characteristic analysis, fault mode analysis, optimal measuring point set selection and measuring point simulation value obtaining on a main control unit circuit to obtain a main control unit fault mode table, and finally forming a fault diagnosis process according to the main control unit fault mode table. Therefore, the reliability of the water-jet propulsion device is improved, a health management system of the water-jet propulsion device can be established, and fault diagnosis and fault monitoring are carried out on the water-jet propulsion device of the whole ship.

A jet propulsion boat includes a boat body; a main propulsion device including a jet device that jets a jet water stream from the boat body, and a direction change device that changes, in a lateral direction, an orientation of the jet water stream having been jetted; an auxiliary propulsion device provided on the boat body to impart a propulsion force in a lateral direction to the boat body; and a control device that controls the main propulsion device and the auxiliary propulsion device, and switches a control mode of the main propulsion device and the auxiliary propulsion device between a plurality of modes, in which the control mode includes a main control mode for driving the main propulsion device and stopping the auxiliary propulsion device to move the boat body, and a combined mode for driving both the main propulsion device and the auxiliary propulsion device to move the boat body.

The present invention provides a jet propulsion system, a jet-propelled boat, and a boat hull launching method that enable easy launching of the boat hull from a trailer. [Solution] This jet propulsion system 100 includes a jet propulsion mechanism 4 that generates thrust by ejecting a jet of water from the nozzle 44a, which is located at the stern 114 of the hull 110 and includes a nozzle 44 provided with a jet water nozzle 44a, a nozzle actuator 5a that rotates the nozzle 44 to change the direction of the jet water from the nozzle 44a, and a control unit 8 that performs oscillation control by repeatedly oscillating the nozzle 44 using the nozzle actuator 5a when lowering the hull 110 from the trailer T.

The present application relates to the field of jet propulsion technology, and provides a micro-mixing nozzle structure with staggered outlet velocity and a combustion chamber. The micro-mixing nozzle structure comprises a mounting seat and a first nozzle unit; the first nozzle unit comprises a plurality of side-by-side arranged premixing micro-pipes, among which a part is reference position premixing micro-pipes and the other part is staggered position premixing micro-pipes; along the axial direction of the premixing micro-pipe, the premixing micro-pipe has an inlet end, an outlet end and a gas passage; the inlet end is provided with an oxidant inlet, and the side wall of the premixing micro-pipe is provided with a fuel inlet communicating with the gas passage; the effective areas of the oxidant inlets corresponding to the staggered position premixing micro-pipes and the reference position premixing micro-pipes are different, so that the jet velocities of the outlet ends of the staggered position premixing micro-pipes and the reference position premixing micro-pipes are different. The present application arranges the different premixing micro-pipes in a staggered manner according to the jet velocity, realizes the staggered arrangement of the flame delay time of the different premixing micro-pipes, effectively suppresses the combustion oscillation, and can ensure the stability of the flame combustion.

The invention discloses a dynamic characteristic testing device and method for a water jet propulsion steering and backing mechanism, and the device comprises a steering and backing mechanism model which is fixedly hung below a piezoelectric three-component dynamic force testing platform. The steering and backing mechanism model and the piezoelectric type three-component dynamic force measuring table are both arranged in the circulating water tank test section, a rudder angle control motor is arranged above the circulating water tank test section, the driving end of the rudder angle control motor is connected with a rotating shaft which drives the steering and backing mechanism model to rotate, the rudder angle control motor is connected with a motor controller, and the motor controller is connected with the piezoelectric type three-component dynamic force measuring table. And a plurality of three-way acceleration sensors for collecting the vibration acceleration of the steering and backing mechanism model are arranged on the steering and backing mechanism model. Synchronous testing of three-direction dynamic force and three-direction vibration acceleration of the steering and backing mechanism in different rudder angle and backing bucket angle operation states can be achieved, and meanwhile the testing device is simple in structure, reasonable in design and convenient to mount and dismount.

The invention discloses a thruster with a magnetically-coated cusped Laval nozzle. The thruster comprises an injection unit, a combustion chamber, the magnetically-coated cusped Laval nozzle and a hollow cathode, the magnetic coating cusped type Laval nozzle comprises a Laval nozzle body and a magnetic coating cusped type assembly. The Laval nozzle comprises a metal shrinkage pipe and a ceramic expansion pipe which are sequentially arranged in the axial direction. The periphery of the ceramic expansion tube is coaxially sleeved with the magnetic coating cusped assembly, and the magnetic coating cusped assembly comprises N stages of permanent magnets and N-1 spacer rings; the hollow cathode is arranged on the outer side of the tail end of the ceramic expansion tube. The magnetic-coated cusped Laval nozzle is adopted, a cusped field is introduced, rapid switching between a chemical direct-current propulsion mode and a magnetic jet propulsion mode can be achieved, and when the thruster needs rapid maneuvering orbital transfer, the chemical direct-current propulsion mode is adopted, and 10N-level thrust can be provided; when the thruster operates in a low orbit and needs to maintain the orbit height, a magnetic jet propulsion mode is adopted to generate thrust in a set direction, so that the orbit height of the satellite is kept unchanged.

A reverse bucket for a jet propulsion device includes a vertical ridge line that faces a discharge opening of a deflector to make a marine vessel move backward, a first inlet region and a second inlet region separated by the ridge line to receive water discharged from the discharge opening, first and second outlet regions to discharge the water received by the first and second inlet regions to the outside, and first and second guide regions to guide the water received by the first and second inlet regions to the first and second outlet regions. The first inlet region, the first guide region, and the first outlet region define a first recess portion including a first opening that faces the discharge opening. The second inlet region, the second guide region, and the second outlet region define a second recess portion including a second opening that faces the discharge opening.

The application provides a nuclear energy electric supercharged jet propulsion system and belongs to the field of aviation power. The nuclear power propulsion system of the traditional turbine engine type solves the problems that the working processes of a compressor and a turbine influence each other, the matching of the compressor and the turbine is relatively difficult, the performance of the propulsion system under variable working conditions is poor, and the arrangement of a heat exchanger in a closed cycle nuclear power system is relatively complex and the flow resistance of the heat exchanger is relatively large. The nuclear energy electric supercharged jet propulsion system comprises a regenerator, a cold end inlet connected with an outlet of a helium-xenon compressor, a cold end outlet connected with a cold end inlet of a heater, a hot end outlet of a first heat exchanger connected with a hot end inlet of a fuel heat exchanger, a second heat exchanger, a hot end inlet of the second heat exchanger connected with a circulating working medium outlet of a reactor system, a fuel tank, a discharge port of the fuel tank connected with the cold end inlet of the fuel heat exchanger through a fuel valve, and an engine shell, wherein air from the compressor outlet flows through the first heat exchanger and the second heat exchanger in sequence. The nuclear energy electric supercharged jet propulsion system is mainly used for the propulsion system of aviation equipment.

The invention discloses a Mars unmanned aerial vehicle system based on high-pressure micro air pump driving, which aims at solving the problems of low atmospheric density of Mars and insufficient lift force / poor Reynolds number effect of traditional rotors, and mainly comprises a pneumatic propulsion mechanism, an air injection mechanism, a gas compression mechanism and a flight control system, a closed-loop pneumatic propulsion structure with a high-pressure micro air pump, an air storage cylinder and a micro nozzle as the core completely replaces a traditional rotor wing or a fixed wing, stable and controllable thrust can be provided in a rarefied atmospheric environment, thrust vectorization adjustment is achieved, and the attitude and trajectory control precision of the unmanned aerial vehicle is improved; mars atmosphere (main CO2) is adopted as a unique working medium, the repeatable circulation of local material utilization, compression, storage, injection and gas resupply is realized, the flight time is prolonged, one-time gas source exhaustion is avoided, and the system reliability and the flight safety are improved through a safety lock and a pressure regulating valve.

The invention discloses a fuel supply control system and method for a jet propulsion device, belongs to the technical field of fuel supply control devices for air combustion-supporting jet propulsion devices, and can solve the background problems that a turbofan is used for exhausting air when an existing jet propulsion engine is used, and the turbofan is limited by the rotating speed of a driving motor in the mode; the problems that when the rotating speed reaches the limit, the air inflow cannot be increased, and when an existing fuel supply system suddenly increases the air inflow, fuel supply is insufficient, and then engine surge is caused are solved. The method comprises the steps that an air compressor is powered on, air is sucked and fed into a combustion section through an air inlet section, and fuel enters a fuel cavity through a fuel inlet; the ignition device is electrified to burn the fuel, and the fuel is sprayed out through the tail spraying section along with air flow; an electric telescopic rod is electrified to drive a barrier plate to rotate to increase the air inflow; and the fuel making pump is started to feed the fuel in the fuel cavity into the other fuel pipe to increase the supply of the fuel.

The invention discloses a satellite formation flight ground test platform control software design method, which can receive actual pose data transmitted by a pose monitoring system through a serial port, remove errors and noise through a TD filtering function, and then obtain an expected target pose through pose planning. After an upper computer transmits data of an actual target pose and an expected target pose to a lower computer through WiFi, the lower computer generates a calculation control quantity through a certain control strategy by calculating pose deviation and then distributes the calculation control quantity to each cold jet propeller according to a thrust distribution equation, a PWM modulation module outputs a modulated digital signal according to a distribution strategy, and the modulated digital signal is transmitted to the lower computer. The working duty ratio and the thrust of the propellers are controlled, accurate control over satellite formation flight is achieved, meanwhile, software provides a concise and clear visual operation interface for a ground test platform, and coordinate value changes of all air-floating satellites are displayed through images, so that the operation difficulty of a satellite formation flight ground test is reduced, and the working efficiency of the satellite formation flight ground test is improved. And the data visualization degree is improved.

Integrated wing / jet propulsion design, characterized in that one or more fixed ducted propellers / blowers are mounted as propulsion on the upper surface, in the rear part of the wing profile, but clearly in front of the wing trailing edge and in front of a wing flap.

The present invention provides a jet propulsion system and a jet-propelled boat that enable the operator on board to immediately correct any unintended movement of the hull caused by radio control. [Solution] This jet propulsion system 100 comprises a jet propulsion mechanism 4, a jet water flow modification operation unit 6a that controls the movement of the hull 110 by changing at least one of the magnitude of the thrust force of the jet water flow, the left-right direction of the jet water flow, and the front-rear direction of the jet water flow, a wireless control device 2 that instructs the movement of the hull 110, and a control unit 8 that, when in wireless control mode, cancels wireless control mode and forcibly switches to manual control mode in which the hull 110 is moved by operation of the jet water flow modification operation unit 6a by the operator U1 based on the operation of the jet water flow modification operation unit 6a by the operator U1.

The invention relates, inter alia, to a bow module (30) for a modular watercraft (20). The watercraft (20) includes interconnectable modules including a stern module (22) and a bow module (30), which can be releasably connected by means of a first connection mechanism (26). The stern module (22) is connectable to a jet-propulsion module (24). The bow module (30) has a connection element (40) and a float (50). The connection element (40) is connectable to the stern module (22) by means of the first connection mechanism (26) and a dimensionally stable float receptacle (42) for receiving the float (50). The float (50) is inflatable by means of compressed air and is dimensionally stabilizable and, in an inflated state, is clampable or clamped into a recess (48) of the float receptacle (42).

A jet propulsion boat includes: a boat body; a jet water stream generation device that jets a jet water stream from the boat body to impart a propulsion force in a front-rear direction to the boat body; a steering device including a steering operator operated by a driver, and changes an orientation in a lateral direction of a propulsion force of the jet water stream generation device in response to an operation on the steering operator; an auxiliary propulsion device provided on the boat body to impart a propulsion force in a lateral direction to the boat body; and a control device that controls the auxiliary propulsion device based on an operation of the steering device.

The utility model relates to a wearable jet-propelled personal aircraft which comprises an aircraft framework, and jet propellers used for providing thrust in the vertical direction and rotor aircrafts used for providing thrust in the horizontal direction are arranged on the two sides of the aircraft framework. A fuel tank used for providing fuel for the jet propeller is arranged in the aircraft framework, and a backrest assembly used for fixing the upper body area of the human body is arranged on one side of the aircraft framework. According to the utility model, thrust is generated by arranging the jet thruster. Vertical or inclined takeoff can be achieved, and the inclination angle during flight is adjusted through the rotor craft in the takeoff process. When the thrust forces of the jet propellers on the left side and the right side are different, the whole aircraft can move leftwards or rightwards.