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151results about How to "Shorter arrival time" patented technology

Vehicle surroundings monitoring apparatus

A vehicle surroundings monitoring apparatus which determines whether there is a possibility of contact between a vehicle and a monitored object around the vehicle with a single camera mounted thereon. It includes a monitored object extraction process unit (20) which extracts an image portion of the monitored object from an image taken by a single infrared camera (2), a rate-of-change calculation process unit (21) which calculates a rate of change in size of the image portion of an identical monitored object extracted by the monitored object extraction process unit (20) from a plurality of images taken by the infrared camera (2) at predetermined time intervals, an arrival time estimation process unit (22) which estimates the time to arrival of the monitored object at the vehicle based on the rate of change, a real space position calculation process unit (23) which calculates a position of the monitored object in the real space based on the rate of change, a movement vector calculation process unit (24) which calculates a movement vector from a displacement of the position of the monitored object in the real space, and a contact determination process unit (25) which determines whether there is a possibility of contact between the monitored object and the vehicle.
Owner:ARRIVER SOFTWARE AB

Message pushing method and system

ActiveCN105472400ASolve the problem of long push time delayShorter arrival timeSelective content distributionMessage queueArrival time
The invention discloses a message pushing method and system. The method comprises the following steps: acquiring a message to be pushed, subdividing the message to be pushed according to different dimensions, and saving messages generated after subdivision in a plurality of queues of a message queue server; resolving pushing dimension range conditions corresponding to the messages, inquiring all terminals according to the pushing dimension range conditions, filtering terminal identifiers which conform to the pushing dimension range conditions, grouping the terminal identifiers according to different access servers, and concurrently forwarding the messages and the terminal identifiers corresponding to different access servers to corresponding access servers according to different groups; and traversing corresponding terminal identifiers by the access servers, finding corresponding terminal sessions and connections according to the terminal identifiers, and sending the messages to corresponding terminals. Through adoption of the message pushing method and system, concurrent pushing of the messages is realized, and the message arrival time is shortened greatly. The message pushing method and system are particularly suitable for message pushing under the situation that millions of television terminals are online.
Owner:TCL CORPORATION

Air conditioner

An air conditioner for a vehicle includes a refrigerant cycle having an evaporator which is disposed in a blowing duct and cools air by refrigerant evaporation in the blowing duct; a compressor setting the evaporated refrigerant at a high temperature and high pressure; a refrigerant-to-water heat exchanger heating cooling water by heat transfer from the refrigerant discharged from the compressor; and an expansion device decompressing the refrigerant discharged from the refrigerant-to-water heat exchanger, The air conditioner also includes a cooling water cycle having a heater core which is disposed on the downstream side of the evaporator; a radiator cooling the cooling water; a pump circulating the cooling water cooled by the radiator; a power engine cooled by the cooling water fed by the pump; and the refrigerant-to-water heat exchanger. The refrigerant cycle performs cooling for dehumidification by performing the operation of heating.
Owner:PANASONIC CORP

Enhanced-type constant-speed reaching law sliding-mode control method for four-rotor-wing unmanned plane system

The invention discloses an enhanced-type constant-speed reaching law sliding-mode control method for a four-rotor-wing unmanned plane system. The enhanced-type constant-speed reaching law sliding-modecontrol method is designed for the four-rotor-wing unmanned plane system through combining with a constant-speed reaching law sliding-mode control method. The design of an enhanced-type index reaching law aims at guaranteeing that the sliding mode of the system can reach a sliding mode plane more quickly while the vibration of the system is not increased, thereby achieving the quick and stable control of the system.
Owner:ZHEJIANG UNIV OF TECH

Charging device maintenance method and system

PendingCN107133675ARepair directlyNo delay in tasksData processing applicationsComputer terminalGps positioning
The invention discloses a charging device maintenance system and method. The charging device maintenance system comprises charging device terminals, a service center and mobile terminals. The charging device terminals are configured to have a unique ID number and GPS positioning information and send fault information to the service center in the event of a fault. The mobile terminals are configured to record the skill level of maintenance personnel carrying the same, perform the GPS positioning at the same time, receive maintenance tasks assigned by the service center and perform maintenance. The service center is configured to receive and record the fault information, put the fault information into a fault database, select the fault information from the fault database, extract features in the fault information, mark the fault level according to fault symptoms, display the position of the mobile terminal in which the skill level is higher than the fault level, and send the maintenance task to the mobile terminal. According to the invention, the maintenance tasks of the charging devices are effectively managed and the service capability of the devices is improved.
Owner:DEZHOU POWER SUPPLY COMPANY OF STATE GRID SHANDONG ELECTRIC POWER +1

Four-rotor aircraft output-limited backstepping control method based on integral sliding mode obstacle Lyapunov function

Provided is a four-rotor aircraft output-limited backstepping control method based on an integral sliding mode obstacle Lyapunov function. For the dynamic system of a four-rotor aircraft, an integralsliding mode obstacle Lyapunov function is selected, and a four-rotor aircraft output-limited backstepping control method based on the integral sliding mode obstacle Lyapunov function is designed. Theintegral sliding mode obstacle Lyapunov function is designed in order to ensure that the output of the system is limited within a certain range, avoid too large overshoot and reduce the time of arrival. Therefore, the dynamic response performance of the four-rotor aircraft system is improved. The invention provides a four-rotor aircraft output-limited backstepping control method based on an integral sliding mode obstacle Lyapunov function, which enables the system to have a good dynamic response process.
Owner:ZHEJIANG UNIV OF TECH

Enhanced-type double-power reaching law sliding-mode control method for four-rotor-wing unmanned plane system

The invention discloses an enhanced-type double-power reaching law sliding-mode control method for a four-rotor-wing unmanned plane system. The enhanced-type double-power reaching law sliding-mode control method is designed for the four-rotor-wing unmanned plane system through combining with a double-power reaching law sliding-mode control method. The design of an enhanced-type double-power reaching law aims at guaranteeing that the sliding mode of the system can reach a sliding mode plane more quickly while the vibration of the system is not increased, thereby achieving the quick and stable control of the system.
Owner:ZHEJIANG UNIV OF TECH

Four-rotor aircraft output limited backstepping control method based on asymmetric time-varying obstacle Liapunov function

A four-rotor aircraft output limited backstepping control method based on an asymmetric time-varying obstacle Liapunov function; the invention aims at the four-rotor aircraft dynamics system, selectsthe asymmetric time-varying obstacle Liapunov function, and designs the four-rotor aircraft output limited backstepping control method based on the asymmetric time-varying obstacle Liapunov function;the asymmetric time-varying obstacle Liapunov function ensures the system output to be limited in a certain scope, can prevent overlarge overstrikes, and can reduce the arrival time, thus improving the four-rotor aircraft system dynamic response performance; the four-rotor aircraft output limited backstepping control method based on the asymmetric time-varying obstacle Liapunov function enables the system to have a good dynamic response process.
Owner:ZHEJIANG UNIV OF TECH

Four-rotor aircraft output limited backstepping control method based on the asymmetric time-invariant obstacle Liapunov function

A four-rotor aircraft output limited backstepping control method based on an asymmetric time-invariant obstacle Liapunov function; the invention aims at the four-rotor aircraft dynamics system, selects the asymmetric time-invariant obstacle Liapunov function, and designs the four-rotor aircraft output limited backstepping control method based on the asymmetric time-invariant obstacle Liapunov function; the asymmetric time-invariant obstacle Liapunov function ensures the system output to be limited in a certain scope, can prevent overlarge overstrikes, and can reduce the arrival time, thus improving the four-rotor aircraft system dynamic response performance; the four-rotor aircraft output limited backstepping control method based on the asymmetric time-invariant obstacle Liapunov functionenables the system to have a good dynamic response process.
Owner:ZHEJIANG UNIV OF TECH

Enhanced fast power reaching law sliding mode control method of quad-rotor UAV system

The invention relates to an enhanced fast power reaching law sliding mode control method of a quad-rotor UAV system. The enhanced fast power reaching law sliding mode control method is designed for the quad-rotor UAV system by combining with a fast power reaching law sliding mode control method. The design of an enhanced fast power reaching law is used for ensuring a sliding mode of the system canreach a sliding mode surface more quickly, does not increase the chattering phenomenon of the system, and achieves fast and stable control of the system.
Owner:ZHEJIANG UNIV OF TECH

Short message sending method and system

The invention discloses a short message sending method and system. The method comprises the steps of recording short message trace information of each short message channel by a terminal; then, sending the short message trace information to a sever, so that the server establishes a short message channel weight database according to the short message trace information; and then, selecting the short message channels to send a short message according to weight data. Multiple short message channels are selected, so when the short message needs to be sent, the optimized short message channel meeting conditions in the weight database is called for sending; and therefore, the short message arrival rate can be improved, and the short message arrival time is shortened.
Owner:福建方维信息科技有限公司

Sudden traffic accident alarm device and method

The invention provides a sudden traffic accident alarm device and method. The device comprises a processor, a voice prompt module and a safety sensor. The safety sensor transmits a detection signal to the processor. The voice prompt module receives the signal transmitted by the processor. The processor judges occurrence of the traffic accident according to the signal acquired by the safety sensor and transmits a self-saving prompt signal to the voice prompt module when occurrence of the traffic accident is determined. The voice prompt module receives the self-saving prompt signal and then transmits self-saving prompt voice information. The method comprises the steps that the processor of the sudden traffic accident alarm device receives the signal transmitted by the safety sensor and judges occurrence of the traffic accident according to the acquired signal, the self-saving prompt signal is transmitted to the voice prompt module if the judgment result is yes, and the voice prompt module receives the self-saving prompt signal and transmits the self-saving prompt information. The self-saving prompt information can be timely transmitted to the people in the vehicle so as to assist the people in the vehicle to get out of danger in time.
Owner:广东利安达科技有限公司

Permanent magnet synchronous motor control method based on sliding mode load torque observer

The invention discloses a permanent magnet synchronous motor control method based on a sliding mode load torque observer, which comprises the steps of firstly, designing a dead-beat prediction controller according to a mechanical motion equation of a permanent magnet synchronous motor on the basis of a mathematical model of the permanent magnet synchronous motor; then designing a sliding mode loadtorque observer; and finally, analyzing the sliding mode load torque observer to realize accurate control of the permanent magnet synchronous motor. According to the method, the sliding mode load torque observer is combined with the dead-beat prediction controller, so that the dynamic response speed of the sliding mode load torque observer is improved; and meanwhile, the constant-speed approach law containing a sign function in the traditional sliding mode observer is replaced by a smooth approach law based on a sine function, so that the sliding mode buffeting in the traditional sliding modeobserver is restrained, and the arrival time of a sliding mode surface is shortened.
Owner:XIAN UNIV OF TECH

Tandem type vacuum generator

InactiveCN103527527AShorter arrival timeImprove the rapidity of adsorptionJet pumpsMachines/enginesEngineeringSorption
The invention relates to a vacuum generator, in particular to a tandem type vacuum generator. The tandem type vacuum generator comprises at least two sets of vacuum generator bodies and a vacuum generator outer shell. Each vacuum generator body comprises a nozzle and an expansion tube, and a vacuum opening is formed in each expansion tube. According to the at least two sets of vacuum generator bodies, the nozzle of the previous vacuum generator body is connected with the expansion tube of the next vacuum generator body to form serial connection, and the at least two sets of vacuum generator bodies are together arranged in the vacuum generator outer shell. The vacuum generator outer shell comprises a compressed air inlet, a compressed air outlet and a vacuum opening, and compressed air enters the tandem type vacuum generator from the compressed air inlet of the vacuum generator outer shell, sequentially passes through the at least two sets of vacuum generator bodies and is discharged from the compressed air outlet of the vacuum generator outer shell. Multiple vacuum generator bodies are connected in series, the energy of the compressed air discharged from the previous vacuum generator body is recycled, and therefore the time for achieving vacuum is shortened, and the sorption rapidity of the vacuum generator is improved.
Owner:SUZHOU SUPERLIGHT MICROELECTRONICS

An apparatus and method for distributing consumption nodes to messages in an MQ

Disclosed are an apparatus and method for distributing consumption nodes to messages in a message queue (MQ). According to the embodiment, the apparatus can comprise a monitor subsystem and a distribution subsystem. The monitor subsystem can be configured to monitor accumulation measurement of various messages in the MQ and processing pressure measurement of various consumption nodes in a consumption end system, to distribute a new consumption node to one kind of messages when the accumulation measurement of the kind of messages exceed a first threshold value and / or to distribute a new consumption node to the kind of messages having the maximum accumulation measurement in a certain consumption, of which a processing pressure exceeds a second threshold value. The distribution subsystem can be configured to update subscription information of the consumption nodes according to the distribution result of monitor subsystem.
Owner:厦门见福连锁管理有限公司

Enhanced exponential reaching law sliding mode control method for quadrotor UAV system

The invention provides an enhanced exponential reaching law sliding mode control method for a quadrotor UAV system. Based on the exponential reaching law sliding mode control method for a quadrotor UAV system, an enhanced exponential reaching law sliding mode control method for the quadrotor UAV system is designed. The design of the enhanced exponential reaching law is to ensure that the sliding mode of the system can reach the sliding mode surface faster, without increasing the chattering phenomenon of the system and realizing the system's fast and stable control.
Owner:ZHEJIANG UNIV OF TECH

Output limited backstepping control method for four-rotor aircraft based on symmetrical time-invariant barrier Lyapunov function

The invention relates to an output limited backstepping control method for a four-rotor aircraft based on a symmetrical time-invariant barrier Lyapunov function. Aimed at a dynamic system of the four-rotor aircraft, the symmetrical time-invariant barrier Lyapunov function is selected, and the output limited backstepping control method for the four-rotor aircraft based on the symmetrical time-invariant barrier Lyapunov function is designed to ensure that system output is limited within certain range, avoid excessive overshoot, and reduce arrival time, and further to improve the dynamic responseperformance of the four-rotor aircraft system. The method provided by the invention enables that the system has a better dynamic response process.
Owner:ZHEJIANG UNIV OF TECH

Four-rotor aircraft total-state constrained control method based on symmetric time varying tangent constraint Lyapunov function

The present invention provides a four-rotor aircraft total-state constrained control method based on a symmetric time varying tangent constraint Lyapunov function. For a dynamic system of a four-rotoraircraft, a symmetric time varying tangent constraint Lyapunov function is selected, and a four-rotor aircraft total-state constrained control method based on the symmetric time varying tangent constraint Lyapunov function is designed. The design of the symmetric time varying tangent constraint Lyapunov function is to ensure state and output of the system can be limited in a certain range to avoid too large overshoot and reduce the arriving time so as to improve the dynamic response performances of a four-rotor aircraft system. The method provided by the invention allows the system to have agood dynamic response process.
Owner:ZHEJIANG UNIV OF TECH

Four-rotor aircraft self-adaptive control method based on exponential enhancement type fast power reaching law and fast terminal sliding mode surface

The invention provides a four-rotor aircraft self-adaptive control method based on an exponential enhancement type fast power reaching law and a fast terminal sliding mode surface. The method comprises the following steps that 1, a transfer matrix from a machine body coordinate system based on a four-rotor aircraft to an inertial coordinate system based on the earth is determined; 2, a dynamics model of the four-rotor aircraft is analyzed according to a Newton euler formula; 3, tracking errors are calculated, and a controller is designed according to the fast terminal sliding mode surface anda first-order derivative thereof. According to the method, sliding mode control and fast terminal sliding mode control which are based on the exponential enhancement type fast power reaching law are combined so that the reaching speed can be increased when the four-rotor aircraft is away from the sliding mode surface, vibration can be reduced, the rapidity of a system are improved, and rapid and stable control can be achieved; meanwhile, limited time control over the tracking errors can be achieved, and the problem that only when the time approaches the infinity, the tracking errors approach the infinity in a traditional sliding mode surface is solved. Meanwhile, the interference boundary is estimated in a self-adaptive mode, so that the stability of the system is improved.
Owner:ZHEJIANG UNIV OF TECH

Finite-time control method for four-rotor aircraft based on hyperbolic tangent enhanced exponential approach law and fast terminal sliding mode surface

The invention relates to a finite-time control method for a four-rotor aircraft based on the hyperbolic tangent enhanced exponential approach law and a fast terminal sliding mode surface. The method comprises steps that S1, a transfer matrix from a body coordinate system based on the four-rotor aircraft to an Earth-based inertial coordinate system is determined; S2, a four-rotor aircraft dynamicsmodel is analyzed according to the Newton Euler formula; and S3, a tracking error is calculated, and a controller is designed according to the fast terminal sliding mode surface and a first order derivative thereof. For the four-rotor aircraft system, in combination with hyperbolic tangent enhanced exponential approaching law sliding mode control and fast terminal sliding mode control, not only can the approaching speed be increased during movement away from the sliding mode surface, but also chattering can be reduced, the speed and robustness of the system are improved, fast and stable control is achieved, moreover, finite time control of the tracking error can be achieved, and a problem that the tracking error only tends to zero in a traditional sliding mode surface only when the time tends to infinity is solved.
Owner:ZHEJIANG UNIV OF TECH

Finite time control method for quadrotor aircraft based on exponentially enhanced exponential approach law and fast terminal sliding mode surface

The invention discloses a finite time control method for a quadrotor aircraft based on an exponentially enhanced exponential approach law and a fast terminal sliding mode surface. The method comprisesthe following steps: 1, determining a transfer matrix from a body coordinate system based on the quadrotor aircraft to an inertial coordinate system based on the earth; 2, analyzing a quadrotor aircraft kinetic model according to the Newton-Euler equation; 3, calculating a tracking error, and designing a controller according to the fast terminal sliding mode surface and a first-order derivative thereof. Aiming at a quadrotor aircraft system, the method combines the exponentially enhanced exponential approach law control and the fast terminal sliding mode control, so the method can increase the approach speed during departing from the sliding mode surface, also can reduce the jitter, improves the quickness and robustness of the system, achieves the quick and stable control, also can achieve the finite time control of the tracking error, and solves a problem that only when time approaches to infinity in the conventional sliding mode surface, can the tracking error approach to zero.
Owner:ZHEJIANG UNIV OF TECH

Four-rotor aircraft output-restricted backstepping control method based on symmetric time-variable obstacle Lyapunov function

The invention provides a four-rotor aircraft output-restricted backstepping control method based on a symmetric time-variable obstable Lyapunov function. For aiming at a dynamic system of the four-rotor aircraft, the symmetric time-variable Lyapunov function is selected, and the four-rotor aircraft output-restricted backstepping control method based on the symmetric time-variable Lyapunov functionis designed. The symmetric time-variable Lyapunov function is designed for restricting the state and the output of the system in a certain range, thereby preventing overlarge overshoot, reducing arrival time and improving dynamic response performance of the four-rotor aircraft system. The four-rotor aircraft output-restricted backstepping control method based on the symmetric time-variable Lyapunov function realizes relatively high dynamic response process of a system.
Owner:ZHEJIANG UNIV OF TECH

Adaptive control method of quad-rotor aircraft based on sliding mode surface of index enhanced double-power reaching law and rapid terminal

Provided is an adaptive control method of a quad-rotor aircraft based on the sliding mode surface of an index enhanced double-power reaching law and a rapid terminal. The method comprises the following steps that 1) a transfer matrix from a body coordinate system based on the quad-rotor aircraft to an inertia coordinate system based on the earth is determined; 2) a dynamic model of the quad-rotoraircraft is analyzed according to a Newton-Euler formula; and 3) a tracking error is calculated, and a controller is designed according to the sliding mode surface of the rapid terminal and a first-order derivative thereof. Sliding mode control via the index enhanced double-power reaching law is combined with sliding mode control of the rapid terminal, the reaching speed is increased when being far from the sliding mode surface, jittering is reduced, a system is rapider and more robust, rapid and stable control is realized, the tracking error is controlled in limit time, and the problem that the tracking error reaches 0 only if time reaches infinite in a traditional sliding mode surface. The interference boundary is estimated via adaption, and the system stability is improved.
Owner:ZHEJIANG UNIV OF TECH

Adaptive control method for four-rotor aircraft based on enhanced bipower reaching law of inverse proportional function and rapid terminal sliding mode surface

ActiveCN108536018ALimited Time Control DecreaseReduce buffetingAdaptive controlDynamic modelsTransfer matrix
The invention relates to an adaptive control method for a four-rotor aircraft based on an enhanced bipower reaching law of an inverse proportional function and a rapid terminal sliding mode surface. The method comprises the following steps that 1) a transfer matrix from a body coordinate system based on the four-rotor aircraft to the earth based inertia coordinate system is determined; 2) a dynamic model of the four-rotor aircraft is analyzed according to a Newton-Euler formula; and 3) a tracking error is calculated, and a controller is designed according to the rapid terminal sliding mode surface and a first-order derivative thereof. According to the method, sliding mode control of the enhanced bipower reaching law of the inverse proportional function is combined with rapid terminal sliding mode control, the reaching speed can be increased far from the sliding mode surface, buffeting is reduced, the system is rapider and more robust, rapid and stable control is realized, the trackingerror is controlled with limited time, and the problem that the tracking error tends to 0 only when time tends to infinite in a traditional sliding mode surface is solved. The interference boundary isestimated via adaption, and the system stability is improved.
Owner:ZHEJIANG UNIV OF TECH

Asymmetrical time-varying constrained aircraft attitude control method

The invention provides an asymmetrical time-varying constrained aircraft attitude control method. In view of a dynamic system of a four-rotor aircraft, an asymmetrical time-varying arctangent constraint Lyapunov function is selected, and a four-rotor aircraft output constraint control method based on the asymmetrical time-varying tangent cosine composite constraint Lyapunov function is designed. The design of the asymmetrical time-varying arctangent constraint Lyapunov function is to ensure the output of the system to be constrained in a certain range, too large overshooting is avoided, and the arrival time can also be reduced. The dynamic response performance of the four-rotor aircraft system is further improved. According to the asymmetrical time-varying constrained aircraft attitude control method provided in the invention, the system thus has a good dynamic response process.
Owner:ZHEJIANG UNIV OF TECH

Four-rotor aircraft total state constrained control method based on symmetric time-invariant exponential tangent compound constraint Lyapunov function

A four-rotor aircraft total state constrained control method based on a symmetric time-invariant exponential tangent compound constraint Lyapunov function. For the dynamic system of a four-rotor aircraft, a symmetric time-invariant exponential tangent compound constraint Lyapunov function is selected, and a four-rotor aircraft total state constrained control method based on the symmetric time-invariant exponential tangent compound constraint Lyapunov function is designed. The design of the symmetric time-invariant exponential tangent compound constraint Lyapunov function ensures that the stateand the output of a system can be restricted to a certain range, avoids excessive overshoot and shortens arrival time, thereby improving the dynamic response performance of the four-rotor aircraft system. The four-rotor aircraft total state constrained control method based on a symmetric time-invariant exponential tangent compound constraint Lyapunov function provides the system with a good dynamic response process.
Owner:ZHEJIANG UNIV OF TECH

Four-rotor aircraft self-adaptive control method based on hyperbolic sine exponential enhancement type power reaching law and fast terminal sliding mode surface

The invention relates to a four-rotor aircraft self-adaptive control method based on a hyperbolic sine exponential enhancement type power reaching law and a fast terminal sliding mode surface. The method comprises the following steps that 1, a transfer matrix from a machine body coordinate system based on a four-rotor aircraft to an inertial coordinate system based on the earth is determined; 2, adynamics model of the four-rotor aircraft is analyzed according to a Newton euler formula; 3, tracking errors are calculated, and a controller is designed according to the fast terminal sliding modesurface and a first-order derivative thereof. According to the method, the hyperbolic sine exponential enhancement type power reaching law, sliding mode control and fast terminal sliding mode controlare combined so that the reaching speed can be increased when the four-rotor aircraft is away from the sliding mode surface, vibration can be reduced, the rapidity and robustness of a system are improved, and rapid and stable control can be achieved; meanwhile, limited time control over the tracking errors can be achieved, and the problem that only when the time approaches the infinity, the tracking errors approach the infinity in a traditional sliding mode surface is solved. Meanwhile, the interference boundary is estimated in a self-adaptive mode, so that the stability of the system is improved.
Owner:ZHEJIANG UNIV OF TECH
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