383results about "Aircraft power plants" patented technology

The invention discloses a transmission driving control method of a bimodal integrated engine. The transmission driving control method comprises the following steps: S1, state sensing; s2, mode decision making; S3, dynamic adjustment; s4, mode switching; S5, power optimization distribution; s6, adaptive learning is carried out; and S7, fault-tolerant guarantee. The invention further discloses a bimodal integrated engine transmission system which comprises the following modules: a power input module; a transmission adjusting module; a state sensing module; an intelligent control module; and a fault-tolerant guarantee module. Parameters are dynamically adjusted through fuzzy PID control according to speed deviation, meanwhile, real-time correction is conducted in combination with a multi-mode intelligent algorithm, speed fluctuation is precisely controlled within + / -3 km / h, flight stability is guaranteed, a model prediction control and multi-mode intelligent control cooperation mechanism is adopted, an optimal power output sequence is calculated in advance, coordinated distribution is completed, and the optimal power output sequence is controlled to be within + / -3 km / h. The dynamic response speed is increased by 40%, and the high-dynamic task requirement is met.

The invention discloses a hydrogen-lithium dual-power system structure optimization design and integrated control method applied to an unmanned aerial vehicle. The method comprises the following steps: constructing a hydrogen-lithium dual-power system of the unmanned aerial vehicle; setting an integrated control strategy according to the hydrogen-lithium dual-power system; the integrated control strategy comprises an energy management strategy and a life and safety management strategy; the energy management strategy comprises a rule-based strategy, a power following strategy and a self-adaptive optimization strategy; the service life and safety management strategy comprises a hydrogen fuel cell protection strategy, a lithium battery health management strategy, a thermal management strategy, a dual-power coupling safety management strategy and a redundancy and fault processing strategy. By optimizing the power system design and the energy management strategy, the mass of the unmanned aerial vehicle device is reduced, the cruising ability, the load capacity and the environmental adaptability of the unmanned aerial vehicle are improved, and optimization processing of the control strategy is achieved.

Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a system of an aircraft is disclosed, configured to determine one or more desired commands for the aircraft, retrieve engine information for at least one electric propulsion unit (EPU) of a plurality of EPUs of the aircraft, wherein the engine information includes at least one time-based metric for temperature associated with the at least one EPU, generates control commands based on the received engine information, and controls effectors according to the generated control commands to meet the desired commands of the aircraft.

The invention discloses a method for aircraft thrust imbalance warning and protection. The method comprises the following steps: acquiring thrust rod position angle signals and wheel load state signals of a plurality of engines after an aircraft lands and is grounded; determining whether the thrust states of the plurality of engines are consistent or not based on the thrust rod position angle signal and the wheel load state signal, wherein the thrust states of the plurality of engines comprise a positive thrust state and a negative thrust state; in response to the fact that one or more of the multiple engines are inconsistent with the remaining engine thrust state of the multiple engines, a warning instruction is sent out; and the reverse thrust cover corresponding to the engine in the negative thrust state is locked. The invention further provides a system for aircraft thrust imbalance warning and protection. By means of the method and device, the unbalanced thrust state of the aircraft can be prevented after the aircraft lands, an alarm is given to operation of a pilot, protection is provided, and the safety of the aircraft is guaranteed.

The invention provides a generator and battery power distribution method and device based on model prediction control, and belongs to the technical field of power distribution. The method provided by the invention comprises the following steps: loading a preset dynamic model library; generating and calibrating a total load power prediction sequence based on the flight plan and the rotor aerodynamic power model; calling the dynamic model library to predict and control the rolling optimization to output the optimal power instruction sequence of the generator; in the rolling optimization execution process, bus voltage dynamic characteristics are monitored in real time, a graded response mechanism is started based on a turboshaft engine dynamic model when load sudden change occurs, and the power of a generator and the power of a battery are adjusted; in the load abrupt change response process, rolling optimization is executed again based on the adjusted power and the corresponding system state, meanwhile, feed-forward compensation is carried out on the bus voltage deviation, and the voltage is controlled to be within a stable interval set by rolling optimization by adjusting the power of the generator; and circularly executing until the flight task is finished, and determining the generator power and the battery power.

The invention relates to the technical field of unmanned aerial vehicles, and discloses a fuel cell unmanned aerial vehicle carrying double hydrogen cylinders, comprising: a hydrogen storage system comprising two independent gaseous hydrogen storage cylinders, the hydrogen storage system being connected with a fuel cell system through a hydrogen delivery pipeline to supply hydrogen to the fuel cell system; the fuel cell system is used for converting hydrogen into electric energy, and the fuel cell system is connected with the energy storage system through an electric energy transmission line so as to transmit the generated electric energy to the energy storage system; the control system is used for monitoring and regulating various functions of the unmanned aerial vehicle, and the control system is connected with the fuel cell system, the energy storage system and the power flight system through data transmission lines so as to receive and send control instructions. By adopting the double-gas-state hydrogen storage cylinder system, the unmanned aerial vehicle can carry more hydrogen, so that the flight endurance time and distance are prolonged, in addition, the hydrogen cylinders which are modularly designed are convenient to replace quickly, and continuous operation in a long-time task is further ensured.

An assembly is provided for an aircraft powerplant. This assembly includes an electric machine, an electric machine controller, an electric cable, a conduit and an air circuit. The electric machine controller is configured to control operation of the electric machine. The electric cable electrically couples the electric machine controller to the electric machine. The conduit extends longitudinally from a first end of the conduit to a second end of the conduit. The electric cable extends longitudinally through a bore of the conduit. The air circuit is configured to cool the electric cable within the conduit using a flow of air. The air circuit includes the bore of the conduit.

The invention discloses an energy management system of a hybrid power unmanned aerial vehicle, and relates to the technical field of hybrid power unmanned aerial vehicle energy management, comprising the following steps: collecting flight condition parameters of the hybrid power unmanned aerial vehicle in real time; synchronously obtaining energy unit state parameters of the hybrid power unmanned aerial vehicle; generating a power distribution strategy among N power sources in the hybrid power unmanned aerial vehicle; executing the power distribution strategy, predicting the energy of the hybrid power unmanned aerial vehicle, and completing the response and management of the energy. Intelligent coordination and real-time optimization of multi-energy input of the hybrid power unmanned aerial vehicle are achieved, thermal stress and mechanical loss of key components are remarkably reduced, the adaptability to complex or unknown flight scenes is enhanced, and therefore on the premise that the flight safety and task reliability are guaranteed, the flight speed of the hybrid power unmanned aerial vehicle is improved. And cooperative improvement of the endurance performance and the system life is realized.

A method of operating a propeller system for an aircraft, the propeller system comprising a propeller, the method comprising: receiving propeller speed information, the propeller speed information indicating propeller speed; receiving a target propeller speed; performing a propeller speed threshold adjustment process, the propeller speed threshold adjustment process comprising adjusting a propeller speed threshold as a function of the target propeller speed; comparing the propeller speed to the propeller speed threshold; and in response to propeller speed exceeding the propeller speed threshold, performing an overspeed protection process.

Embodiments of the present disclosure are directed to providing fuel emissions monitoring and / or management for an aerial vehicle. In an example, fuel consumption data and carbon emissions data for an aerial vehicle is determined. The fuel consumption data provides a comparison between (i) first fuel consumption data associated with a first type of aviation fuel being utilized by the aerial vehicle and (ii) second fuel consumption data associated with a second type of aviation fuel that is not being utilized by the aerial vehicle. The carbon emissions data is based on (i) volume data indicative of a real-time volume of the first type of aviation fuel, (ii) a first carbon emissions factor for the first type of aviation fuel, and (iii) a second carbon emissions factor for the second type of aviation fuel. In another example, a rendering of the fuel consumption data is caused via a display.

The invention discloses a self-adaptive energy management method for a hydrogen-sodium hybrid power system of an unmanned aerial vehicle, and the method comprises the steps: S1, building an MPC state space model of the hybrid power system; s2, collecting a flight control instruction sequence and state data; s3, based on the flight control instruction, generating a predicted total load power sequence through a pre-trained neural network model; s4, resetting the MPC state space model based on the state data collected at the moment k; s5, constructing an objective function and constraint conditions; and S6, solving an optimal hydrogen fuel cell output power sequence, adopting a rolling strategy to obtain the power set value output of the hydrogen fuel cell at the k moment, and determining the power set value of the sodium ion battery in real time according to an energy conservation equation. According to the method, a self-adaptive hybrid power system energy management scheme is established by deeply fusing feedforward prediction based on a flight control instruction, multi-target self-adaptive optimization and closed-loop feedback correction.

An aircraft having a plurality of independent yaw control mechanisms includes an airframe having a central fuselage sized to hold at least one operator or payload and a wing extending from the fuselage. The aircraft includes a distributed thrust array coupled to the airframe, the thrust array having at least a first, second, and third pair of propulsion assemblies. Each propulsion assembly includes a rotor and is operable for at least single-axis thrust vectoring. The aircraft further includes a flight control system operable to independently control and combine each yaw mechanism of the propulsion assemblies. The yaw mechanisms for inducing a yaw moment include: canting at least one pair of propulsion assemblies away from the fuselage, selectively tilting at least one pair of propulsion assemblies forwards and backwards, varying an aerodynamic control surface of at least one propulsion assembly, and varying a rotational speed of at least one propulsion assembly.

Provided are a method and a system for cooperative airborne meteorological perception with multiple aircraft. The method includes: determining a training set based on a spatial position, motion data, weather, an observation image, and static information of each of multiple aircraft; determining a fusion performance function based on an objective of a cooperative perception network; generating a fusion model based on the training set and the fusion performance function; generating a perception result image based on the fusion model; determining flight risk information based on the perception result image; determining a route alarm command and sending the route alarm command to a management user interface and an interactive device of a target aircraft; after receiving the route alarm command, generating, by the management user interface, a route adjustment parameter; in response to obtaining the route adjustment parameter, performing at least one of the following operations: adjusting an engine velocity, adjusting an aileron pressure, adjusting an elevator deflection, and adjusting a rudder deflection.

The invention provides a hybrid power unmanned aerial vehicle system and method based on multistage emergency control, and the system comprises an engine state monitoring and failure detection module which collects the operation parameters of an engine in real time through a vibration sensor, a rotating speed sensor and a temperature sensor; the multi-state machine emergency control module is in communication connection with the engine state monitoring and failure detection module; the intelligent ignition control module is in communication connection with the engine state monitoring and failure detection module and the multi-state machine emergency control module; the VTOL mode conversion control module is in communication connection with the multi-state machine emergency control module; the dynamic energy management unit is in communication connection with the multi-state machine emergency control module; and the navigation and communication interface module integrates a receiver and a multi-mode communication link and is in communication connection with the multi-state machine emergency control module. According to the invention, full-automatic closed-loop processing from engine failure prediction and intelligent restart to multi-mode emergency decision and execution is realized.

The invention discloses a hybrid power system energy management method during VTOL unmanned aerial vehicle dual-mode switching, and the method comprises the steps: S1, dual-mode switching prediction parameters are collected, the dual-mode switching prediction parameters are obtained from a flight control system in real time, and the dual-mode switching prediction parameters comprise a mode switching instruction, a pitch angle change rate and a height change rate; s2, pre-judging a flight switching mode: pre-judging the flight switching mode of the VTOL unmanned aerial vehicle based on the dual-mode switching prediction parameters, the flight switching mode including vertical horizontal switching and horizontal vertical switching; and S3, energy strategy adjustment: triggering a corresponding energy adjustment strategy 5-10 seconds in advance based on the flight switching mode, and dynamically adjusting the power output of the hydrogen fuel cell and the sodium cell to realize progressive power handover. Energy distribution is adjusted in advance through flight trend pre-judgment, the control belongs to feed-forward-feedback composite control, and efficient cooperation of the hydrogen fuel cell and the sodium cell of the hybrid power system is achieved.

The present disclosure relates generally to flight control of electric aircraft and other powered aerial vehicles. In one embodiment, a method is disclosed, comprising: receiving a descent rate command from a pilot input device, determining a proximity of each propeller of at least two propellers to a vortex ring state; and controlling the aircraft's descent rate to be less than the commanded descent rate when at least one of the at least two propellers is within a first threshold proximity to the vortex ring state.

Powertrains and related methods for an aerial vehicle may include a torque control system associated with the powertrain and configured to receive torque signals indicative of engine torque supplied by a mechanical power source or generator torque generated by an electric power generation device resisting the engine torque. The torque control system may be configured to generate, based in part on torque signals, a torque control signal configured to change the engine torque or change the generator torque. When torque signals indicate a relative reduction in the engine torque supplied by the mechanical power source, torque control signals may be configured to cause a relative reduction in the generator torque resisting the engine torque. When torque signals indicate a relative increase in the engine torque supplied by the mechanical power source, torque control signals may be configured to cause a relative increase in the generator torque resisting the engine torque.

Described herein is an active throttle quadrant assembly. The active throttle assembly comprises a lever mounted via a first pivot at a proximal end of the lever and a grip on a distal end of the lever. An actuator assembly is coupled to the lever and the assembly further comprises a sensor positioned close to the grip and arranged to detect force applied to the grip to rotate the lever about the first pivot.

The application discloses a reverse thrust device locking mechanism and an aero-engine comprising the same, the reverse thrust device locking mechanism comprising a shell, a liquid supply part and a locking rod, the shell comprising an internal cavity, a liquid inlet and a liquid outlet which are in communication with each other, the first end of the locking rod being arranged in the internal cavity, the second end of the locking rod extending to the outside of the shell and being capable of engaging with a moving cover, the locking rod being arranged to switch between a locking position and an unlocking position according to the pressure on the side of the liquid inlet; in the locking position, the locking rod engages with the moving cover, and the reverse thrust device locking mechanism is in a locked state; in the unlocking position, the locking rod moves along the axial direction thereof to the side away from the moving cover, and the reverse thrust device locking mechanism is in an unlocked state. The application drives the movement of the locking rod through hydraulic pressure, and has the advantages of simple working principle, high stability, simple structure of hydraulic transmission, no need to arrange electrical control equipment such as electromagnetic valves, no need to design a complex circuit layout, and effective reduction of production and assembly costs.

The invention relates to the technical field of motor control, in particular to a brushless motor electronic speed regulation circuit for an unmanned aerial vehicle and a control method of the brushless motor electronic speed regulation circuit. The brushless motor electronic speed regulation circuit comprises a printed circuit board, a power supply module and a grid driving module. The printed circuit board is provided with a plurality of wiring layers which are stacked, and comprises a first power supply layer and a second power supply layer which are adjacent to each other in the vertical direction and are overlapped and aligned, and an electrical control layer. The power supply module is arranged on the first power supply layer and the second power supply layer, the first power supply layer and the second power supply layer are electrically connected through a matrix via hole array, and the power supply module is used for being electrically connected with an external power supply and supplying power to a circuit after processing. The grid driving module is arranged on the electrical control layer, is powered by the power supply module and is used for outputting driving voltage to the brushless motor, large current transmission and balanced distribution of the multi-channel motor controller can be realized on a single printed circuit board, and electromagnetic interference of a power loop on a control signal is inhibited.

An assembly is described which may be an active stick or throttle assembly or may be connected to mechanical linkage within an aircraft. The assembly comprises an actuator assembly comprising a motor body casing, and a gearbox; and a lever connected, via a proximal end of the lever, to an output stage of the gearbox. The assembly further comprises trunnion bearings configured to mount the motor body casing to a chassis and a link configured to connect the motor body casing to the chassis, wherein the link comprises a force sensor.

A jet aircraft maneuvering characteristic simulation system for a single propeller aircraft includes a power lever, speed brakes, and a controller. The power lever is configured to change a thrust of the single propeller aircraft. The speed brakes are provided on respective right and left sides of the single propeller aircraft. The controller is configured to, in response to an operation of the power lever to raise the thrust of the single propeller aircraft, deploy both the right and the left speed brakes to cause an increase in speed of the single propeller aircraft to be moderate, and control the speed brakes to cause a force in a yaw direction and a force in a roll direction to be generated that act against a turning tendency of the single propeller aircraft by making amounts of the deployment of the right and the left speed brakes different from each other.

Provided is a gas turbine system in which electricity consumption of a battery when starting or stopping a gas turbine engine is reduced and sufficient battery power during flight can be secured. The present invention includes a plurality of gas turbine engines 21, 22, and 23, generators 41, 42, and 43, a battery 5, and a controller 7. The controller 7 decides at least one main starting gas turbine engine 21 from the plurality of gas turbine engines before the plurality of gas turbine engines are started, starts the main starting gas turbine engine 21 using electricity from the battery 5, and starts the secondary starting gas turbine engines 22 and 23 of the plurality of gas turbine engines other than the main starting gas turbine engine 21 using electricity from the generator 41 connected to the main starting gas turbine engine 21 after the main starting gas turbine engine 21 reaches a steady state.

An active throttle assembly 100 is disclosed. The active throttle assembly comprises a linear motor 120, the linear motor comprising a linearly extending track 124 and a carriage 122. The active throttle assembly further comprises a grip 110, wherein the grip is affixed to the carriage. A controller 140 is configured to control a current or voltage provided by a power supply to at least one of the linearly extending track or the carriage in order to control movement of the carriage with respect to the linearly extending track. A detector 130 configured to measure at least one of a kinematic variable of the grip or a force applied to the grip. The controller may provide haptic feedback to a user of the throttle assembly to indicate an operating condition of an engine of a vehicle containing the active throttle assembly and may be used as part of a fly by wire system.

A power distribution system and method of operation for an aircraft includes determining, by a supplemental power system, an operation mode of the aircraft, selecting, by the supplemental power system, at least one supplemental power source of a set of at least two supplemental power sources, and at least one of receiving a first current from the main power bus by the selected at least one supplemental power source, or selectively providing a second current to the main power bus from the selected at least one supplemental power source, based on an operating mode of the aircraft.

An electrical power system and an aircraft including an electrical power system are provided. The electrical power system includes: an electrical power source; a DC electrical network; a power converter including at least one input terminal and first and second DC output terminals, the at least one input terminal connected to the electrical power source, the first and second DC output terminals connected to the DC electrical network; a DC link capacitor connected between the first and second DC output terminals; a power semiconductor switch connected in series with the DC link capacitor between the first and second DC output terminals; and a control unit configured to respond to a fault in the DC electrical network by opening the power semiconductor switch, whereby discharge of the DC link capacitor is prevented.

The invention provides a linkage protection method and system for a battery and an electronic speed controller of a high-voltage unmanned aerial vehicle and a medium, and the method comprises the steps: synchronously collecting the multi-dimensional state data of a battery management system and the electronic speed controller based on a preset period, and fusing the data into an operation state sequence set; meanwhile, a safety threshold group set is dynamically adjusted in combination with environment temperature information; then, identifying an abnormal state by sequentially comparing each state parameter with a threshold range, and further calculating a dynamic change trend of an abnormal parameter to evaluate a risk level; meanwhile, the risk level is intelligently improved based on a preset parameter association rule; then, integrating all the abnormal information into an abnormal level distribution diagram, and inputting the abnormal level distribution diagram into a fault level instruction obtained by a fault analysis model; and finally, executing a corresponding hierarchical control strategy. Therefore, serial comparison and comprehensive analysis of multi-parameter thresholds are realized, and the continuous operation capability and task reliability of equipment are guaranteed on the premise of ensuring the safety of a flight control system.

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.

Provide a system. 【Solution means】 Means for receiving visual data acquired by an unmanned aircraft, Means for analyzing the acquired visual data to detect the existence of illegal acts or waste, Means for notifying in real time information regarding detected illegal acts or waste, Means for providing an interface that enables residents to monitor problems and participate in countermeasure actions, Means for receiving complaints from residents, Means for analyzing the complaints and determining the priority of problems, Means for automating the provision of information to residents, Means for automatically generating and sending countermeasure plans to locations with problems, A system including the above.