96 results about "Auxiliary power unit" patented technology

A mobile fusion device (MFD) comprises three main sections: the MFD reactor (467), MFD support sub-systems (468), and the MFD support and fuel injection sub-systems (469), which are indicated by broken lines in Figure 1 The MFD reactor (467) is where the Deuterium and Tritium fuel is heated to high enough temperatures and densities and confinement times that fusion occurs, releasing neutrons that are absorbed in and heats up the 17Li-83Pb breeder blanket where more Tritium fuel is bred and where heat is transferred to Helium coolant. The MFD support sub-systems (468) houses auxiliary power units that generate electricity to power the electrical sub-systems of the MFD, and houses the MFD control computer, and where the Helium coolant is cryogenically cooled and purified, and where the 17Li-83Pb breeder blanket fluid is purified by separating and storing Deuterium fuel and Tritium fuel and Helium coolant, and where a Helium heat exchanger is located. The MFD support and fuel injection sub-systems (469) houses Deuterium and Tritium neutral beam injection plasma heating systems and a Deuterium and Tritium fuel gas puffer system and a Deuterium and Tritium fuel storage and pellet manufacturing system, and where the 17Li-83Pb breeder blanket fluid is purified by separating and storing Deuterium fuel and Tritium fuel and Helium coolant, and where a Helium heat exchanger is located, and where the Helium coolant is cryogenically cooled and purified, and houses auxiliary power units that generate electricity to power the electrical sub-systems of the MFD. The MFD is housed within a multi-layered pressurised outer containment pod MLP, which has a multi-layered pressurised rear access hatch MLH. The MFD is mounted on a sliding raft SR for ease of access.

The invention relates to the technical field of aero-engines, and discloses a combustion chamber with an adjustable air entraining structure, the combustion chamber comprises a cartridge receiver structure, the air entraining structure and an adjusting structure, the cartridge receiver structure comprises a first cartridge receiver and a second cartridge receiver, the first cartridge receiver and the second cartridge receiver are connected with each other and jointly define a mounting cavity, and the first cartridge receiver is provided with a first communication part and a second communication part; the air entraining structure is provided with a communicating cavity, the communicating cavity is provided with a first opening, a second opening and a third opening, the first opening communicates with the first communicating part, the second opening communicates with the second communicating part, and the third opening communicates with the engine; the adjusting structure comprises a first adjusting assembly and a second adjusting assembly, the first adjusting assembly covers the first communicating part and is arranged on the first casing, and the second adjusting assembly covers the second communicating part and is arranged on the first casing; ignition delay and flameout of the auxiliary power device in a small state are avoided, low-frequency excitation of the flame tube in a large state is avoided, and performance degradation of the combustion chamber in an intermediate value state is avoided.

An accessory power unit assembly includes a combustor assembly that includes a pulse detonation tube that defines a curved passage between an inlet that receives a compressed airflow and a discharge end. The detonation tube operates as a resonant cavity to sustain a standing pressure wave. Fuel injected into the pulse detonation tube is timed to coincide with movement of a standing wave toward a discharge end. The standing wave provides an increase in pressure of an output exhaust gas driving the turbine without a corresponding increase in load.

The utility model discloses a portable auxiliary power device fuel oil electromagnetic valve testing device which comprises a box body, a serial port relay is arranged in the box body, a first plug, a second plug and a power plug are arranged on the front side face of the box body, the power plug is connected with the serial port relay, and a flowmeter and a valve fixing tool are arranged on the upper surface of the box body. A protective transparent cover is further installed at the upper end of the box body through fixing screws, the first plug is connected with an electrical plug of a fuel oil electromagnetic valve fixed to the valve fixing tool through a wire bundle, a wire led out of the first plug is connected with a serial port relay, and the common end of the serial port relay is connected with a second plug. Compared with the prior art, the beneficial effects of the utility model are that the circuit control part, the pressure test part and the instrument interface part are integrated, the integration level is high, and the use is more portable and convenient; the testing device main body is made of polyurethane rigid plastic, and the protective transparent cover is arranged, so that the testing safety is effectively improved, and the testing device has a relatively high popularization value.

The invention discloses a multi-rotor unmanned aerial vehicle, a power control system and a power control method, and relates to the technical field of unmanned aerial vehicles, and the multi-rotor unmanned aerial vehicle comprises a vehicle body, vehicle arms, a main power device and an auxiliary power device. The at least two vehicle arms are arranged on the vehicle body, and the at least two main power devices are arranged on the vehicle arms. The at least two auxiliary power devices are arranged on the vehicle arm, and the auxiliary power devices and the main power device are distributed in the extending direction of the vehicle arm at intervals. When the main power device is normal, the auxiliary power device is in a non-working state; when the main power device breaks down, the auxiliary power device provides power guarantee for the unmanned aerial vehicle. According to the scheme, the at least two auxiliary power devices are arranged on the vehicle arms, a main power and auxiliary power cooperative system is formed, power loss can be rapidly compensated when the main power devices fail, the fault-tolerant capability and flight stability of the unmanned aerial vehicle are improved, and the unmanned aerial vehicle is more stable. And the safety and reliability of the unmanned aerial vehicle in a complex environment and a task key scene can be improved.

The application discloses a compressor variable frequency driver with a wide input voltage range, which comprises an AC power input unit, an EMI filter unit, a rectifier unit, a Boost PFC control unit, a bus electrolytic capacitor, an input voltage detection unit, an MCU control unit, an auxiliary power unit, a three-phase inverter bridge and a compressor; the output end of the AC power input unit is connected with the input end of the EMI filter unit, and the output end of the EMI filter unit is connected with the input end of the rectifier unit; one way of the output end of the rectifier unit is connected with the input end of the Boost PFC control unit. The application has high reliability, the control algorithm realizes self-adaptation according to real-time compensation of the bus voltage, and avoids compressor control mismatch caused by bus voltage fluctuation; meanwhile, through the input voltage detection and judgment unit and the multi-stage protection mechanism, overvoltage and overcurrent faults are effectively inhibited, and the service life of power devices and electrolytic capacitors is prolonged.

To provide a technique for inspecting operations of components assembled into an electrically assisted bicycle with space savings and a simple facility.SOLUTION: An inspection system 1 comprises a DC power supply 2, a strain sensor 6, a signal transceiver 7, and a determinative PC 8. Since, in the inspection system 1, the signal transceiver 7 performs outputting a control signal to the strain sensor and receiving a reaction value of the strain sensor corresponding thereto from a primary substrate, which are performed by a control circuit inside an auxiliary power unit in an electrically assisted bicycle, the control circuit inside the auxiliary power unit (auxiliary power unit equivalent to the actual machine) becomes unnecessary, and thus an exclusive battery equivalent to the actual machine which supplies power to the auxiliary power unit becomes unnecessary. The signal transceiver 7 generates a control signal to transmit it to suitable parts, and allows the strain sensor 6 to respond, whereby operations of the primary substrate B1 and a secondary substrate B2 can be inspected in a state that the maximum consumption current of the strain sensor in the auxiliary power unit is simulatively reproduced, and a surrounding state is simulatively reproduced.SELECTED DRAWING: Figure 1

The application discloses a kind of motor electromagnetic vibration characteristic testing devices of stator and rotor separation.The device includes bottom plate and stator, rotor, bearing seat, sensor system, coupling and auxiliary power device on it, and the stator shell of stator is connected with bottom plate only by the stator support at both ends of stator;Rotor both ends have detachable mass for adjusting unbalance;Rotor is fixed on bearing seat by bearing, bearing seat is fixed on bottom plate, and there are gasket and guide key between bearing seat and bottom plate;Rotor displacement sensor of sensor system is used to detect the position of rotor, Hall sensor and PCB magnetic sensor are used to detect the space-time characteristics of stator core surface magnetic field, and stator vibration sensor is used to measure the vibration of stator;Auxiliary power device provides original power or applies load for rotor.The application can be used to obtain electromagnetic exciting force between motor stator and rotor air gap, and various eccentric states of motor rotor can be simulated comprehensively.

The invention discloses an auxiliary power device modeling method based on fuzzy set intelligent optimization. The method comprises the following steps: firstly, establishing models of all parts of the APU according to an aerodynamic thermodynamic law, and constructing a common working equation set; then, the particle swarm optimization process is divided into four typical states of exploration, depth, convergence and local optimum, and the current state is identified in real time by using a fuzzy estimator. And on the basis, optimizing hyper-parameters such as inertia weight, cognitive coefficient and social coefficient are adaptively adjusted according to the recognition state. And finally, taking a residual weighted least square function with a quadratic penalty term as a fitness index, and driving a particle swarm to solve an equation set. According to the method, through the state recognition and parameter self-adaption mechanism, the defects that a traditional Newton method is high in dependency on an initial value and a basic particle swarm algorithm is prone to falling into local optimum and slow in convergence are effectively overcome, and efficient and steady solution of the APU model is achieved.

The invention relates to an improved external power supply module for an aircraft, the power supply module (APSM) comprising at least an electrical connection to a first AC power distribution network (GPU1), an electrical connection to a second AC power distribution network (GPU2), a synchronization and connection module, and a power converter (C1), the power supply module (APSM) being external to the aircraft (AC). The power converter (C1) is configured to deliver a DC supply voltage (HVDC1) to said aircraft (AC), the DC supply voltage (HVDC1) being obtained from the first and second AC power distribution networks (GPU1, GPU2) by the synchronization and connection module. Advantageously, it is thus possible to supply electrical energy to a plane parked in an airport area without complex logistics and without using the auxiliary power unit of the plane.

The invention relates to an aircraft power supply module (APSM) for powering an aircraft (AC), comprising at least one first input (I1) configured to make an electrical connection to a first AC power distribution network (GPU1) and a power converter (C1). The APSM is external to the aircraft (AC), and the power converter (C1) is configured to deliver a direct current supply voltage (HVDCN1) to the aircraft (AC) from at least the first AC power distribution network (GPU1) via an output (O1) configured for a connection to the aircraft (AC). Advantageously, this makes it possible to power an aircraft parked on an airport apron without requiring complex logistics and without having to use its auxiliary power unit. Fig. 1

A fuel transfer device and an auxiliary power unit fuel system equipped with the fuel transfer device are disclosed. The fuel transfer device is connected between a main fuel line and an auxiliary fuel line, and includes: a housing, which is formed as a sealed housing, having a peripheral wall portion, a first base plate near the upstream side of the fuel flow path, and a second base plate near the downstream side of the fuel flow path; a main fuel line, which is disposed between the peripheral wall portion of the housing and the main fuel line; an auxiliary fuel line, which is disposed between the peripheral wall portion of the housing and the auxiliary fuel line; a one-way valve, which is disposed in the auxiliary fuel line, allowing fuel in the auxiliary fuel line to flow to the housing; and a fuel replenishment mechanism, which is disposed in the main fuel line, and replenishes the main fuel line with fuel supplied from the auxiliary fuel line to the housing via the one-way valve when the pressure in the main fuel line drops due to the opening of the auxiliary fuel line. This improves fuel pressure fluctuations in the main fuel line during the starting process of the auxiliary power unit, thereby increasing starting reliability.

The invention discloses a frequency conversion linkage control system of energy-saving semiconductor waste gas washing equipment, which comprises a waste gas treatment unit, an auxiliary power unit, a frequency conversion driving module, a sensor network and an intelligent control unit, and is characterized in that the waste gas treatment unit comprises a plasma reaction cavity and a washing tower, and a plasma torch is arranged in the plasma reaction cavity; the auxiliary power unit comprises a fan and a circulating water pump; the variable-frequency driving module is electrically connected with the fan and the circulating water pump; the sensor network comprises a component sensor, a flow sensor and a pressure sensor; a fuzzy PID control algorithm is arranged in the intelligent control unit, and the intelligent control unit is electrically connected with the sensor network, the variable frequency driving module and the waste gas treatment unit. The system has the beneficial effects that through multi-parameter real-time monitoring and multi-unit cooperative control, dynamic and accurate matching of the waste gas treatment capacity is achieved, and system energy consumption and washing liquid consumption are remarkably reduced. The system has self-learning and predictive adjusting capabilities and adapts to complex and changeable semiconductor waste gas working conditions.

The application discloses a super-compact wide-speed-range combined compressor structure and belongs to the field of auxiliary power devices.The structure comprises an axial flow rotor, variable-camber inlet adjustable guide vanes, a high-speed forward-swept centrifugal impeller, an integrated non-uniform consistency diffuser, a gear transmission device, a built-in starting and power generation integrated motor and an inner connecting ring; the key of the application lies in that the super-compact wide-speed-range combined compressor structure comprises the axial flow rotor, the variable-camber inlet adjustable guide vanes, the high-speed forward-swept centrifugal impeller, the integrated non-uniform consistency diffuser, the gear transmission device, the built-in starting and power generation integrated motor and the inner connecting ring.The combined compressor structure is compact, the component efficiency is high, and the stable working range is wide, so that the fuel consumption of the auxiliary power device is reduced, and the economy of the auxiliary power device is improved.

A power supply system (100) for an aircraft, comprising: a plurality of main generators located in a left channel and a right channel; an auxiliary power unit (APU) starter generator (ASG) located in the right channel and configured to supply power when the main generators fail; a plurality of transformer rectifier units (TRUs) located in the left channel, the right channel and an emergency channel; a plurality of autotransformer units (ATUs) located in the left channel, the right channel and the emergency channel; and a ram air turbine (RAT) located in the emergency channel. The present invention further relates to a method for using a power supply system to supply power an aircraft.

The application provides a combined power system based on a methanol fuel cell auxiliary power device and a turbofan main engine, which is applied to the field of aviation power technology and comprises a fuel supply system, a heat exchanger, a preheater, a methanol fuel cell auxiliary power device system and a turbofan engine core system; the fuel supply system is connected with the methanol fuel cell auxiliary power device system and the heat exchanger respectively; the heat exchanger and the methanol fuel cell auxiliary power device system are connected with the preheater; and the preheater is connected with the turbofan engine core system. The methanol fuel cell auxiliary power device can utilize the electric power generated by the fuel cell to drive an electric auxiliary turbocharger to generate high-pressure gas when the main engine is started, so that the high-pressure gas is led to the combustion chamber of the main engine and the combustion efficiency is improved; on the other hand, the electric power generated by the fuel cell can be utilized to preheat the fuel led to the main engine, so that the atomization quality of the fuel is improved and the combustion efficiency is further improved.

The invention provides an automatic control system for a civil aircraft auxiliary power unit (APU), and the system can comprise a scene recognition module which is configured to receive aircraft operation scene information and fault information from an avionics network system, and determine and send APU usage scene information based on the aircraft operation scene information and the fault information; an automatic control module configured to: receive APU usage scenario information, determine an operation to be automatically executed based on the APU usage scenario information and the position information of the cockpit control switch, and generate an operation instruction based on the determined operation to be automatically executed; and the state monitoring module is configured to collect information related to APU automatic control, the collected information comprises APU use scene information and an operation instruction, and the working state of the APU is visually displayed based on the collected information. The invention further provides an automatic control method for the civil aircraft auxiliary power unit APU.

The invention provides a rotational speed comprehensive control method for a civil auxiliary power device. The rotational speed comprehensive control method comprises the following steps: step 1, periodically acquiring a sampling rotational speed and a turbine exhaust temperature of a rotor of the auxiliary power device; 2, calculating the fuel flow in each period through PI control; 3, calculating the acceleration of each period through a derivation algorithm; fourthly, the fuel flow of each period is calculated through a control algorithm; 5, calculating the fuel flow of each period by using a correction algorithm; step 6, calculating the fuel flow of each period through a compensation algorithm; and 7, the fuel quantity calculated through PI control in each period, the fuel quantity calculated through the control algorithm corresponding to the period and the fuel flow calculated through the compensation algorithm are added, and the added fuel flow serves as a fuel flow instruction value to be used for controlling the rotating speed of the APU. According to the method, small control errors can still be guaranteed under the severe air entraining condition and the condition that parameters of the auxiliary power device change.

The invention provides a fuel cell auxiliary power device based on diesel reforming, which comprises an air supply unit, a water supply unit, a diesel supply unit, a diesel reforming unit and a power generation unit, the air supply unit is connected with the power generation unit and the diesel reforming unit, and is used for supplying gas to the power generation unit and the diesel reforming unit; the water supply unit is connected with the diesel oil reforming unit and used for supplying water to the diesel oil reforming unit, the diesel oil supply unit is connected with the diesel oil reforming unit and used for supplying diesel oil to the diesel oil reforming unit, and the diesel oil reforming unit is connected with the power generation unit and used for reforming the diesel oil and supplying the diesel oil to the power generation unit. The power generation unit receives the reformed diesel oil and the air supplied by the air supply unit and generates power. Diesel oil carried by an automobile is taken and reformed, chemical energy of the diesel oil is directly converted into electric energy to be used by the automobile, and energy carried by the automobile can be used for meeting the requirement for energy under the long-time stopping or parking working condition.

A soundproof dog kennel includes a housing with noise-dampening walls and a noise-dampening door for dog ingress / egress. One or more walls has a ventilation assembly with noise-dampening baffles that permits inflow of breathable air with dampened sound waves when the door is closed, featuring hollow corridors, an air intake end, and an exhaust end. Fans force air through the sound-dampening ventilation ducts to reduce ambient noise while removing stale air. The kennel is equipped with cameras, carbon dioxide sensors, and other safety and monitoring devices. A smartphone application enables remote monitoring through live camera feeds, real-time sensor data display, and remote control of kennel functions. The system can automatically open the door if air quality or temperature reaches predetermined thresholds. This kennel protects dogs from noise pollution sources like fireworks, engines, and airplane auxiliary power units, providing a safe, quiet, and remotely monitored space for dogs.

The application provides a lubricating oil electromagnetic valve capable of reducing the starting load of an aviation auxiliary power device, comprising a blocking block, a driving mechanism and a mounting shell; the mounting shell is detachably connected to the auxiliary power device; the mounting shell has a communication chamber, a first through hole and a second through hole which are in communication with each other; the communication chamber is in communication with the lubricating oil pump inlet of the auxiliary power device through the first through hole; the communication chamber is in communication with the air inlet of the auxiliary power device through the second through hole; the blocking block is arranged in the communication chamber and has a blocking state and a communication state; the driving mechanism is arranged on the mounting shell and is used to drive the blocking block to move along the length direction of the mounting shell, so that the blocking block is switched from the blocking state to the communication state or from the communication state to the blocking state. In this way, the state of the blocking block is changed through the driving mechanism, the switching of the lubricating oil path and the air path is realized, and the working reliability and service life of the auxiliary power device are improved.

An aircraft is disclosed, including a fuselage having a compartment configured to house refueling apparatus. An auxiliary power unit is mounted in the compartment.

To provide an air compressor capable of efficiently obtaining compressed air without requiring an auxiliary power unit.SOLUTION: The conversion mechanism 20 includes the rack gear 12 provided on one of the axle-side member 92 and the vehicle-body-side member 91, the at least one input gear 21 that is provided on the other of the axle-side member 92 and the vehicle-body-side member 91, meshes with the rack gear 12, and is rotated forward and backward in accordance with a moving direction of the rack gear 12, and the intermediate gear 22 that converts a rotation direction of the input gear 21 into a reverse direction. In the air compression device 10, the pump 50 includes a drive gear 23 to which rotary motion of an input gear 21 and an intermediate gear 22 is transmitted, an air compression member 55 operated by the rotary motion of the drive gear 23, and a casing 15 forming a compression chamber 56 between the casing 15 and the air compression member 55.SELECTED DRAWING: Figure 2

A method and a system for surveillance of equipment in a fuel supply circuit of an auxiliary power unit of an aircraft. The method includes determining if the fuel supply circuit was during a predetermined period in a configuration such that these conditions were satisfied: (i) the auxiliary power was in an “on” operating state, and ii) the fuel supply circuit was in a “trim tank fueling” operating mode, and (iii) the trim tank had an “empty” fuel filling status, then determining a duration for which the configuration was maintained and, if the duration is above a first predetermined threshold, storing an event, and if a number of events stored is above a second predetermined threshold generating an alert message.

The application relates to an auxiliary power unit (APU) exhaust pipe fireproof mounting assembly and an airplane. The APU exhaust pipe fireproof mounting assembly is mounted at a firewall behind an APU cabin and comprises a connecting piece, a bellows, an APU exhaust pipe front support and an APU exhaust pipe. The connecting piece is used for sealing connection between an APU body exhaust ejector and the bellows. The bellows is connected between an outlet of the APU body exhaust ejector and the APU exhaust pipe front support. The APU exhaust pipe front support is used for connecting the bellows, the APU exhaust pipe and the firewall respectively. The APU exhaust pipe is connected with the APU exhaust pipe front support at a front end and communicates with the outside atmosphere at a rear end to discharge high-temperature exhaust gas of the APU body. According to the above technical scheme, the application has the following beneficial technical effects: simple layout, easy installation, light overall weight and meeting the fireproof requirement.

The application provides a method and device for displaying the state of an aircraft battery, electronic equipment and a storage medium. The method comprises: calculating the average temperature of the aircraft battery; calculating the temperature difference between the temperature of each single battery and the average temperature; if the absolute value of the temperature difference corresponding to any single battery exceeds a first temperature threshold, determining whether the starting duration of the auxiliary power unit of the aircraft exceeds a starting time threshold; if the starting duration exceeds the starting time threshold and the aircraft is in a ground state, issuing a battery pack maintenance instruction; determining whether the average temperature reaches a second temperature threshold; if the average temperature reaches the second temperature threshold, determining whether the average temperature reaches a third temperature threshold; if the average temperature reaches the third temperature threshold, issuing a first-level alarm instruction of the battery pack; and if the average temperature does not reach the second temperature threshold, heating the aircraft battery; and if the average temperature of the heated aircraft battery reaches a fourth temperature threshold, issuing a usable instruction of the battery pack.

A transport power system is provided. The system includes a prime mover separate from a vehicle engine; a global positioning system (GPS) receiver configured to receive GPS data; and a controller configured to communicate with the prime mover and the GPS receiver. The controller is configured to determine the altitude of the transportation power system relative to the sea level based on the GPS data received by the GPS receiver; determining a power output of the prime mover; adjusting a power output upper limit of the prime mover based on the determined altitude; comparing the power output of the prime mover with the adjusted power output upper limit; and operating the prime mover of the transport power system so that the prime mover does not exceed the adjusted power output upper limit.

The application is a kind of aircraft auxiliary power device turbine blade rotating radius measurement method based on mass deviation and unbalance decoupling. The application relates to the field of mechanical measurement technology, the application uses a dynamic balancing machine to measure a turbine rotor assembled with two blades, and reversely deduces and calculates the rotating radius of the turbine blades according to the measured unbalance error, the blade mass and the unbalance parameters of the blade disc. The application first offsets the unbalance of the blade disc by using the method of counterweight, then weighs the blades, selects two blades with a large mass difference for assembly, measures the unbalance of the whole rotor, and finally deduces the blade rotating radius calculation method of the rotor with an odd number of blades and the rotor with an even number of blades. The application does not need to use other equipment for measurement or scanning, which saves the economic cost; and the application has no requirements on the shape of the blades and is suitable for various shapes of blades.

The modular electronic and electrical system comprises a whole vehicle controller, a serial communication bus and a plurality of double-shaft vehicle units, and each double-shaft vehicle unit comprises a power domain controller, a battery pack, an auxiliary power unit, a high-voltage bus, a motor and vehicle-mounted equipment; the vehicle control unit is connected with the power domain controllers through the serial communication bus, the power domain controllers are connected with the battery pack, the auxiliary power unit and the motor, and the high-voltage bus is connected with the battery, the auxiliary power unit, the motor and the vehicle-mounted equipment. Compared with the prior art, the number of axles of the modularized double-axle vehicle unit can be freely expanded; operation of other units is not affected when the independent single double-shaft vehicle unit breaks down, and fault tolerance is good; and the high-voltage buses are independently distributed on each double-shaft vehicle unit, so that the problems that physical modules cannot be added in the existing functional domain architecture, and the number of driving shafts is limited by the load of the central bus are solved.

An auxiliary power unit system for an aircraft is provided, comprising: an auxiliary power unit (APU) (1); a cooling device for the auxiliary power unit (1) comprising a heat exchanger (2); an air intake (3) in fluid communication with the auxiliary power unit (APU) (1) and / or the cooling device; an air intake door device (4) located at the air intake (3); a first duct (5) configured to draw air into the auxiliary power unit (APU) (1) and having an inlet in communication with the air intake (3); a second duct (6) having an inlet in communication with the air intake (3), the heat exchanger (2) being at least partially located within the second duct (6); an air turbine (7) located downstream of the heat exchanger (2) within the second duct (6); a generator coupled to the air turbine (7).