162 results about "Auxiliary power unit" patented technology

The invention relates to an air system for an aircraft, that includes air consumers; air sources and a network of ducts and associated control valves controlled by a control unit. The air system is characterized in that: the network of ducts and associated valves includes at least one isolation valve, arranged between an air bleed device and an air duct connecting an air conditioning pack and an auxiliary power unit; the control unit is configured to be able to determine an ideal configuration of the control valves according to the identified requirements of each consumer and a degraded configuration that makes it possible to supply air to predetermined air consumers from the available air sources when the ideal configuration is not attainable.

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.

A propulsion system comprises a propulsive hydrogen-burning gas turbine engine, a fuel cell stack auxiliary power unit (APU) and a first tank arranged to store liquid hydrogen with an ullage. A first fuel line includes a first pump and a first vaporiser and transports hydrogen from the first tank to combustion apparatus of the engine during operation of the propulsion system. A second fuel line includes a second fuel pump and a second vaporiser and transports hydrogen from the first tank to the fuel cell stack APU. A duct connects the second fuel line at a position thereon between the second vaporiser and the fuel cell stack to the ullage of the first tank, providing for pressure in the first tank to be maintained therein as liquid hydrogen within the first tank is depleted, thus avoiding cavitation of liquid hydrogen within the first fuel pump.

An auxiliary power generator system for an aircraft including an auxiliary power unit (APU) with dual and fully redundant starter and electrical power generation systems that connects independently to a normal electric network or an emergency electric network of an aircraft. A method for supplying electric power to an aircraft by means of the system.

The application discloses a system for controlling an auxiliary power unit of an aircraft to perform an automatic start operation in the air, characterized by comprising: an auxiliary power unit (APU) for providing an air source and a power source for the aircraft; an integrated modular avionic system (IMA) for receiving an emergency state signal and an operating state signal associated with the aircraft, and generating an APU auto-start signal according to a preset decision logic based at least in part on the emergency state signal and the operating state signal; and the APU controller is in communication connection with the IMA and is used for controlling the APU to execute an automatic starting operation after receiving the APU automatic starting signal. A method for controlling an auxiliary power plant (APU) of an aircraft to perform an autostart operation in the air, as well as numerous other aspects, is also disclosed.

The invention belongs to the technical field of device test, and discloses a gas turbine auxiliary power device test data processing method and system, and the method comprises the steps: reading the test data of a gas turbine auxiliary power device, recognizing the test data, calculating the signal characteristics of the test data, and obtaining the test data of the gas turbine auxiliary power device according to the signal characteristics of the test data. Dividing a steady-state interval and a transition-state interval of the test data, representing a switching point of the steady-state interval and the transition-state interval of the test data by using step characteristics of a plurality of signals, calculating interval signal characteristics of the test data according to the test data of each interval, and determining the interval signal characteristics of the test data according to the interval signal characteristics of the test data. And calculating data processing parameters of each interval, smoothing the data curve of the test data of the transition state interval by using a filter, and averaging the test data of the steady state interval to obtain a unique steady state value. According to the method, test original data features are calculated, steady-state and transition-state data processing intervals are divided, data processing parameters of each interval are calculated, and data are processed. Compared with the prior art, the method has the advantages that the test data of the auxiliary power device are efficiently processed in a self-adaptive signal feature extraction mode, the obtained processing result has uniqueness, subjective deviation is avoided, meanwhile, the labor cost is saved, and the test analysis period is shortened.

The invention discloses a method for quickly verifying the capability of an auxiliary power device based on a rack, and the operation environment of the method comprises the steps: carrying out a simulation test on the rack, and simulating an inlet throat of an air turbine starter through a contraction nozzle in the test; before a test, a total pressure recovery coefficient sigma and a conversion inlet area At * of an air turbine starter are calculated, the minimum throat area At'of the shrinkage nozzle is determined, during the test, a test total pressure recovery coefficient sigma'and a conversion area At * 'of the shrinkage nozzle are calculated, and the minimum throat area At'of the shrinkage nozzle is determined by adjusting the test total pressure recovery coefficient sigma' or the minimum area At 'of the shrinkage nozzle. Enabling At * to be equal to At * ', obtaining the required power Pt of the auxiliary power device at the moment, calculating the test power Pt' of the auxiliary power device at the moment, and judging whether the capability of the auxiliary power device meets the requirement or not by comparing Pt with Pt '. Through the method, the verification method and difficulty are simplified, the capability of the auxiliary power device can be rapidly verified under the rack condition, and the verification efficiency is effectively improved.

The invention provides a start controller for an aviation auxiliary power device and a test run control method. The start controller comprises a case, a start button, a stop button, a signal input port, a signal conversion processing module, a warning indication unit, a buffer relay and a signal output port. The starting and stopping button is used for receiving starting and stopping instructions of the aviation auxiliary power device, and the signal input port is used for collecting engine rotating speed, exhaust temperature, lubricating oil pressure signals and cold running, false starting instruction and starting driving instruction signals. The signal conversion processing module is used for processing according to the received signal, judging whether the rotating speed of the engine, the exhaust temperature and the lubricating oil pressure meet safety threshold values or not, and outputting a warning signal and a stop signal, so that the engine is emergently stopped, and a corresponding indicator lamp is lightened; protection parking under emergency conditions in the test run process of the aviation auxiliary power device is achieved, control precision is high, and operation is easy. The device is compact and small in structure, high in integration level and low in manufacturing cost.

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.

A vehicle power system including a fuel cell auxiliary power unit for providing clean, efficient power to a vehicle. The system generally includes a fuel cell with a first DC output and a heat output, a pressure vessel adapted to contain and provide pressurized hydrogen to the fuel cell, an electrical storage unit with a DC input coupled to the first DC output of the fuel cell. The electrical storage unit also has a second DC output. An inverter is coupled to the second DC output of the electrical storage unit to receive power, the inverter having a first AC output. The system can provide heat, AC power, and DC power to the vehicle.

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 present invention provides an ejector, an auxiliary power unit for an aircraft, and an aircraft, wherein the ejector includes a main spray unit, a bleed unit, a cooling unit, an ejector unit, and a mixing section; wherein the main spray unit, the ejector unit, and the mixing section are connected in sequence, the cooling unit is connected to the ejector unit, the bleed unit is connected to the ejector unit, and the mixing section is located at the most downstream part of the fluid passage; furthermore, the main airflow from the main spray unit, the cooling airflow from the cooling unit, and the bleed airflow from the bleed unit are mixed together and discharged through the mixing section. The present invention can make good use of the bleed gas energy, while significantly improving the uniformity of the flow field inside the ejector, thereby improving the ejection capacity and strength life of the ejector.

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 present invention discloses a load compressor configuration, comprising: a rotor assembly, and a first bearing casing and an air intake casing relatively spaced apart and installed on the outer circles at both ends of the rotor assembly. The power input end of the rotor assembly is supported on the first bearing casing through a front bearing, and the power output end of the rotor assembly is supported on the air intake casing through a rear bearing to form an independent rotor support structure. The power input end of the rotor assembly can also be detachably connected to the upstream power input system, and the power output end of the rotor assembly can also be detachably connected to the downstream power output system to ensure the input and output of the load compressor power. The present invention can form an independent rotor system, ensure an independent unit design, and then can be quickly adapted to auxiliary power units of different models and powers, with a wide range of adaptability; the rotor assembly has a short fulcrum span and strong rigidity, ensuring that the rotor system has sufficient critical speed margin.

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

Thermal heat management system The present invention discloses a thermal heat management system (1) comprising: at least one auxiliary power unit (2), at least one thermal heat exchange system (3) connected to the at least one auxiliary power unit (2), wherein the at least one thermal heat management system (1) is configured to absorb and use thermal heat from the at least one auxiliary power unit (2).

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.

One embodiment of the present invention may provide an unmanned vehicle comprising: a power supply unit having a main power supply unit and an auxiliary power supply unit and supplying driving power; a power management unit for controlling power switching and power supply of the main power supply unit and the auxiliary power supply unit of the power supply unit; a storage unit for storing a first recovery module for performing a communication recovery operation when communication is disconnected; a control unit which drives the first recovery module when the communication is disconnected; and an auxiliary control unit which is driven by power from the auxiliary power unit when main power is cut off, and performs the communication recovery operation.

The utility model provides an air inlet air door actuating system, the air inlet air door actuating system is used for an airplane auxiliary power device, the airplane auxiliary power device comprises an air inlet air door, the air inlet air door actuating system comprises an actuating push rod, the actuating push rod is constructed to enable the air inlet air door to move between a closing position and an opening position, the air inlet air door actuating system comprises an ice removing and preventing component which is connected with an actuating push rod or arranged in the actuating push rod, and therefore ice removing and preventing can be at least conducted on the actuating push rod. Through the deicing and anti-icing component, at least deicing and anti-icing of the actuating push rod can be achieved, ice layers accumulated on the actuating push rod during operation in the low-temperature and high-cold environment are reduced or avoided, the clamping stagnation phenomenon of the actuating push rod is avoided, and the normal function of the air inlet damper actuating system is ensured.

An auxiliary power unit (10) for a vehicle is configured to provide cool or heated air within the vehicle with the main engine off. The auxiliary power unit (10) includes an auxiliary diesel engine (45) that receives fuel from the fuel tank (100) of the vehicle. The auxiliary diesel engine (45) is connected to a hydraulic pump of a hydraulic power system (300) by a first magnetic clutch (60) to provide mechanical power. The hydraulic pump converts the mechanical power to hydraulic power. The hydraulic power system (300) delivers the hydraulic power to a hydraulic compressor drive motor that converts it back to mechanical power. The hydraulic power system (300) is connected to a compressor drive (170) via a second magnetic clutch (168). The compressor drive (170) provides power to an air conditioner (AC) compressor (185) of the vehicle such that the AC compressor (185) activates while the auxiliary power unit (10) is operating.

The present invention discloses a continuous pulse incremental ignition fuel supply method for aircraft engines. The method comprises: setting multiple fuel supply pulses, each fuel supply pulse including adjacent fuel supply time periods at a fixed fuel flow rate and fuel supply time periods at an incremental fuel flow rate, dynamically detecting the ignition state, terminating the ignition program when ignition is successful, and performing the next fuel supply pulse when ignition fails, with a preset time interval between the two fuel supply pulses, and the incremental fuel flow rate increasing in the order of the fuel supply pulses. The ignition fuel supply method provided by the present invention has enhanced compatibility with the auxiliary power unit body, improved the ignition success rate of the auxiliary power unit, enhanced environmental adaptability, and ensured that the auxiliary power unit can reliably ignite in extreme environments; when ignition is unsuccessful in a fuel supply pulse, the next fuel supply pulse ignition can be quickly and safely started, which not only achieves automatic and rapid ignition, but also eliminates the risk of deflagration or overheating at start-up caused by fuel accumulation.

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.