53 results about "Auxiliary power unit" patented technology

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 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

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.

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 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.

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).

The disclosure relates to a drive arrangement (2) for a working machine (1). The drive arrangement (2) comprises a first electric machine (10) configured to drive a drive shaft assembly (30) of the working machine (1). The drive arrangement (2) also comprises a first coupling device (11) for coupling the first electric machine (10) to the drive shaft assembly (30). The drive arrangement (2) further comprises a second electric machine (20) configured to drive a power take-off assembly (40) of the working machine (1). In addition, the drive arrangement (2) comprises a second coupling device (21) for coupling the second electric machine (20) to the power take-off assembly (40). The first electric machine (10) and the second electric machine (20) are arranged coaxially with each other.Furthermore, the disclosure provides a working machine (1) with the auxiliary power unit (40), the at least one drive axle assembly (30) and the drive unit (2).

The application relates to an air intake system of an auxiliary power unit, comprising: an air intake door, which is attached to the fuselage of an aircraft and can rotate between an open position and a closed position; an air intake passage, which is arranged downstream of the air intake door to guide air entering through the air intake door to an air intake component of the auxiliary power unit; a partition passage, which is arranged in front of the air intake door along the fuselage of the aircraft and can move between an open position and a closed position; a cooling pipe, which is arranged downstream of the partition passage to guide air entering through the partition passage to a cooling component of the auxiliary power unit; and an actuating device, which is attached to the air intake door and the partition passage to control the opening and closing of the air intake door and the partition passage. By arranging the partition passage, the influence of the boundary layer of the airflow on the air intake system can be effectively isolated, so that the air intake quality is improved, and the working efficiency of the auxiliary power unit is further improved. In addition, the application also relates to an auxiliary power unit.

The application provides a kind of auxiliary power and engine combined debugging device and design method in test chamber, and the auxiliary power and engine combined debugging device in test chamber includes: support platform, box is provided, auxiliary power device is arranged in the inner chamber of box;Air inlet pipeline, the inlet end of air inlet pipeline is connected with altitude table air inlet pipeline mixer, the outlet end of air inlet pipeline is connected with the air inlet of auxiliary power device in the inner chamber of box;Exhaust pipeline, the inlet end of exhaust pipeline is connected with the air inlet of auxiliary power device in the inner chamber of box, and the outlet end of exhaust pipeline is connected with altitude chamber exhaust diffuser.Connecting with altitude table air inlet pipeline mixer through the design of air from the rear, the calculated pipeline parameter ensures that auxiliary power device obtains the inlet condition consistent with main engine, and steady-state simulation accuracy reaches pressure unevenness less than 1%, temperature unevenness less than 1%.

This invention provides an anti-surge venting structure and an auxiliary power device having the same, belonging to the field of engine technology. It includes: a venting pipe seat with a venting end, the venting end having a venting port on its side, the venting pipe seat being adapted to pass through a tailpipe, and the venting port of the venting end being adapted to face the tail of the tailpipe; a guide plate disposed at the end of the venting end for blocking gas from being ejected in a straight line from the end of the venting pipe seat. The anti-surge venting structure of this invention, by providing a guide plate at the end of the venting end of the venting pipe seat, can block gas from being ejected in a straight line from the end of the venting pipe seat, thereby avoiding the problem of high-pressure gas discharged from the anti-surge venting end directly blowing onto the exhaust temperature sensor installed on the tailpipe, causing exhaust temperature measurement distortion.

This disclosure relates to the field of aviation or civil auxiliary power unit / starter technology, and particularly to an air intake device for a gas turbine. In the prior art, during load-section flow control, when the inlet guide vanes are closed to their minimum, the compressor flow in the load section cannot be zero; otherwise, the compressor will flutter, potentially leading to compressor damage. However, the inherent clearance fit of this device allows air to flow into the load compressor through the gaps in the grille even when the load intake grille or mesh channel is completely closed, preventing a complete lack of flow and successfully avoiding potential flutter problems in the load compressor. Furthermore, under non-design operating conditions, the grille-type intake airflow is more uniform in the circumferential direction, while traditional compressors with guide vanes, due to separation on the guide vanes, generate uneven circumferential excitation sources, leading to blade vibration problems.

This vehicle control system provides a system that suppresses the output of an alarm when the power supply from the auxiliary power unit is cut off. [Solution] The vehicle control system 1, which can be powered by the auxiliary power supply unit 12, includes an alarm unit 28 that outputs an alarm when it is detected that the auxiliary power supply unit 12 is abnormal, an acquisition unit 22 that acquires a cutoff request signal to cut off power supply from the auxiliary power supply unit 12, an arbitration processing unit 26 that performs arbitration processing to cut off power to the auxiliary power supply unit 12 when it acquires the cutoff request signal, and a control unit 24 that sends information to the auxiliary power supply unit 12 indicating whether or not the power can be cut off according to the arbitration processing result. The control unit 24 stops the output of an alarm by the alarm unit 28 between acquiring the cutoff request signal and sending information to the auxiliary power supply unit 12 indicating whether or not the power can be cut off.

An auxiliary power unit for an electric vehicle is provided. The unit comprises a power source and power connection means for delivering power from the source to a vehicle.

The application discloses a novel integrated auxiliary power device for an aircraft, a valve body and an auxiliary power assembly arranged at two ends of the valve body, wherein the auxiliary power assembly comprises a high-pressure cylinder, an air cavity, a high-pressure cavity, an electromagnetic valve, an oil storage cylinder, a logic valve, an oil storage cavity, a high-pressure piston, a low-pressure piston, a logic one-way valve and an electromagnetic one-way valve, the high-pressure cylinder and the oil storage cylinder are respectively sleeved at the two ends of the valve body, the air cavity is arranged on the inner wall of the high-pressure cylinder, and the air cavity is arranged on the inner wall of the valve body. In the application, the electromagnetic valve, the logic valve and the one-way valve with different functions are integrated in the valve body, the accumulator and the oil storage unit composed of the high-pressure cylinder and the oil storage cylinder are utilized, the structure is compact, the installation space is reduced, the required power is reduced, the application working condition is wider, only a small-power unit is needed, large-power working condition can be realized, pilot control is adopted for large-flow switching, and large-flow electromagnetic switching impact is avoided.

The invention relates to the technical field of engine combustion, in particular to a double-helix double-pipe auxiliary power combustion chamber, an aircraft and a control method. A double-helix double-pipe auxiliary power combustion chamber comprises a gas inlet pipeline, a gas outlet pipeline, a gas inlet pipeline, a gas outlet pipeline and a gas outlet pipeline, the combustion chamber assembly comprises a combustion chamber case shell, a first flame tube and a second flame tube, the combustion chamber case shell is provided with a containing space and communicates with the air outlet, the first flame tube and the second flame tube are arranged in the containing space, first fuel flows into the first flame tube, and second fuel flows into the second flame tube. Second fuel can flow into the second flame tube, and the first fuel and the second fuel are different. The invention provides a double-helix double-tube auxiliary power combustion chamber, an aircraft and a control method, and aims to solve the problem that different working conditions of an engine cannot be met due to the fact that only one full-ring flame tube is arranged in a super combined auxiliary power device.

This invention relates to a composite repair method for bevel drive gears, belonging to the field of gear repair technology. This invention combines the structure of the bevel drive gear with continuous drive friction welding technology, using additive manufacturing through continuous drive friction welding to repair the gear. This solves the problems of difficult procurement and high cost of using bevel drive gears in auxiliary power units, achieving cost reduction and efficiency improvement.

The utility model discloses a vehicle power supply system and vehicle, system includes: main power unit, first auxiliary power unit, second auxiliary power unit, isolation unit, main power unit and the first end electricity connection of electric load, and through the electricity connection of isolation unit and the second end of electric load, first auxiliary power unit, second auxiliary power unit and the second end electricity connection of electric load, and through the electricity connection of isolation unit and the first end of electric load, isolation unit is used for with second end communication or disconnect of main power unit, and with first end communication or disconnect of first auxiliary power unit, second auxiliary power unit.

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 present application relates to underwater salvage technical field, specifically underwater gun salvage equipment, including floating on the water surface of the water surface ship, still including buoyancy and auxiliary power device and salvage device, the water surface ship is connected with buoyancy and auxiliary power device through cable line, the buoyancy and auxiliary power device and salvage device are connected through flexible chain and cable, the buoyancy and auxiliary power device is immersed in water, and the salvage device is located in the bottom of water.The buoyancy and auxiliary power device and salvage device are arranged separately, the buoyancy and auxiliary power device is immersed in water, the salvage device is located in the bottom of water, the problem that the visibility is further made poor can be effectively avoided because the propulsion power of salvage main body is stirred muddy in the bottom of water;the buoyancy and auxiliary power device and salvage device are connected through flexible chain and cable, and the problem of salvage in complex bottom topography is solved.