WO2016088604A1 - 建設機械の管理システム - Google Patents
建設機械の管理システム Download PDFInfo
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- WO2016088604A1 WO2016088604A1 PCT/JP2015/082911 JP2015082911W WO2016088604A1 WO 2016088604 A1 WO2016088604 A1 WO 2016088604A1 JP 2015082911 W JP2015082911 W JP 2015082911W WO 2016088604 A1 WO2016088604 A1 WO 2016088604A1
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- construction machine
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- aircraft
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D41/00—Electrical control of supply of combustible mixture or its constituents
- F02D41/22—Safety or indicating devices for abnormal conditions
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- E—FIXED CONSTRUCTIONS
- E02—HYDRAULIC ENGINEERING; FOUNDATIONS; SOIL SHIFTING
- E02F—DREDGING; SOIL-SHIFTING
- E02F9/00—Component parts of dredgers or soil-shifting machines, not restricted to one of the kinds covered by groups E02F3/00 - E02F7/00
- E02F9/26—Indicating devices
- E02F9/267—Diagnosing or detecting failure of vehicles
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- E—FIXED CONSTRUCTIONS
- E02—HYDRAULIC ENGINEERING; FOUNDATIONS; SOIL SHIFTING
- E02F—DREDGING; SOIL-SHIFTING
- E02F9/00—Component parts of dredgers or soil-shifting machines, not restricted to one of the kinds covered by groups E02F3/00 - E02F7/00
- E02F9/20—Drives; Control devices
- E02F9/2058—Electric or electro-mechanical or mechanical control devices of vehicle sub-units
- E02F9/2062—Control of propulsion units
- E02F9/2066—Control of propulsion units of the type combustion engines
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- E—FIXED CONSTRUCTIONS
- E02—HYDRAULIC ENGINEERING; FOUNDATIONS; SOIL SHIFTING
- E02F—DREDGING; SOIL-SHIFTING
- E02F9/00—Component parts of dredgers or soil-shifting machines, not restricted to one of the kinds covered by groups E02F3/00 - E02F7/00
- E02F9/26—Indicating devices
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- E—FIXED CONSTRUCTIONS
- E02—HYDRAULIC ENGINEERING; FOUNDATIONS; SOIL SHIFTING
- E02F—DREDGING; SOIL-SHIFTING
- E02F9/00—Component parts of dredgers or soil-shifting machines, not restricted to one of the kinds covered by groups E02F3/00 - E02F7/00
- E02F9/26—Indicating devices
- E02F9/267—Diagnosing or detecting failure of vehicles
- E02F9/268—Diagnosing or detecting failure of vehicles with failure correction follow-up actions
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D29/00—Controlling engines, such controlling being peculiar to the devices driven thereby, the devices being other than parts or accessories essential to engine operation, e.g. controlling of engines by signals external thereto
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D29/00—Controlling engines, such controlling being peculiar to the devices driven thereby, the devices being other than parts or accessories essential to engine operation, e.g. controlling of engines by signals external thereto
- F02D29/02—Controlling engines, such controlling being peculiar to the devices driven thereby, the devices being other than parts or accessories essential to engine operation, e.g. controlling of engines by signals external thereto peculiar to engines driving vehicles; peculiar to engines driving variable pitch propellers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D45/00—Electrical control not provided for in groups F02D41/00 - F02D43/00
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- G—PHYSICS
- G07—CHECKING-DEVICES
- G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
- G07C5/00—Registering or indicating the working of vehicles
- G07C5/08—Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle or waiting time
- G07C5/0808—Diagnosing performance data
-
- G—PHYSICS
- G07—CHECKING-DEVICES
- G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
- G07C5/00—Registering or indicating the working of vehicles
- G07C5/08—Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle or waiting time
- G07C5/0816—Indicating performance data, e.g. occurrence of a malfunction
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D41/00—Electrical control of supply of combustible mixture or its constituents
- F02D41/22—Safety or indicating devices for abnormal conditions
- F02D2041/227—Limping Home, i.e. taking specific engine control measures at abnormal conditions
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D41/00—Electrical control of supply of combustible mixture or its constituents
- F02D41/22—Safety or indicating devices for abnormal conditions
- F02D2041/228—Warning displays
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D2400/00—Control systems adapted for specific engine types; Special features of engine control systems not otherwise provided for; Power supply, connectors or cabling for engine control systems
- F02D2400/08—Redundant elements, e.g. two sensors for measuring the same parameter
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D41/00—Electrical control of supply of combustible mixture or its constituents
- F02D41/02—Circuit arrangements for generating control signals
- F02D41/021—Introducing corrections for particular conditions exterior to the engine
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/40—Engine management systems
Definitions
- the present invention relates to a management system that performs processing such as failure analysis and failure / predictive diagnosis of construction machinery.
- Patent Document 1 Japanese Patent Laid-Open No. 2012-177319 discloses a technique related to failure diagnosis of an engine used in construction machinery, and an in-cylinder pressure sensor is installed in the engine as a prime mover to detect a failure of the fuel injection valve.
- a failure diagnosis apparatus for an internal combustion engine is disclosed.
- Patent Document 2 Japanese Patent Laid-Open No. 2008-196428
- frequency distribution information representing the relationship between the magnitude of a signal related to engine output and the appearance frequency is generated.
- Patent Document 1 in addition to various sensors that are installed in order to control the operation of the machine body of a construction machine, for example, information used for engine failure diagnosis such as an in-cylinder pressure sensor. There is a problem that separately installing measurement sensors for collecting leads to an increase in cost of the aircraft.
- the present invention has been made in view of the above, and an object of the present invention is to provide a construction machine management system capable of performing failure analysis and failure / predictive diagnosis of an aircraft at high accuracy and at low cost.
- the present invention provides at least one first information detection device including a first information detection device that detects first information related to an airframe of a construction machine and a second information detection device that detects second information.
- a construction machine body group including a machine body and at least one second machine body that has the first information detection device and does not have the second information detection device, a construction machine that manages the state of each machine body A management system, which is based on correlation information between first information and second information obtained from the first airframe, and first information on the second airframe, and a failure state related to second information on the second airframe It is assumed that an airframe state diagnosis device for performing a predictive diagnosis of the above is provided.
- Construction machine failure analysis and failure / predictive diagnosis can be performed with high accuracy and at low cost.
- FIG. 1 is a diagram schematically showing an overall configuration of a construction machine management system according to a first embodiment.
- FIG. BRIEF DESCRIPTION OF THE DRAWINGS It is a figure explaining the fundamental view of the construction machine management system which concerns on 1st Embodiment, and is a figure which shows the whole structure of the management system which connected each body and the center server of the construction machine with the information network. It is a figure explaining the basic idea of the management system of the construction machine which concerns on 1st Embodiment, and is a figure explaining the idea at the time of forming the construction machine group containing a some construction machine, respectively. It is a figure which shows the external appearance of the hydraulic shovel shown as an example of the construction machine which concerns on 1st Embodiment.
- FIG. 1 is a diagram schematically illustrating a diesel engine of a hydraulic excavator according to a first embodiment extracted with a related configuration. It is a figure which shows typically the diagnostic principle of the airtight deterioration in the airtight deterioration diagnostic process which is a failure and predictor diagnosis regarding the airtightness of a diesel engine. It is a figure which shows the correlation of the parameter regarding an airtight deterioration diagnostic process. It is a figure which shows typically the determination method of the airtight deterioration in an airtight deterioration diagnostic process.
- FIG. 1 is a diagram schematically showing an overall configuration of a construction machine management system according to a first embodiment of the present invention.
- the construction machine management system collects construction machine information obtained from a plurality of construction machines 1a to 1c (for example, hydraulic excavators to be described later in detail) through communication paths 505a to 505c of an information network.
- a machine condition diagnosis device that performs information processing to manage the entire construction machine group (in other words, the machine group of construction machines), and performs failure analysis, failure / predictive diagnosis, etc. based on information related to the construction machine bodies
- a center server 105 is provided.
- the center server 105 includes a failure-related data storage unit 501 for storing failure-analyzed data, a failure determination data analysis unit 502 for performing failure diagnosis processing, a failure prevention data analysis unit 503 for performing predictive diagnosis, and A failure-related warning issuing unit 504 is provided, which performs failure analysis and failure / predictive diagnosis processing based on information on the airframe collected from each construction machine.
- a hydraulic excavator using a diesel engine as a prime mover is shown as an example of a construction machine, and a case where failure analysis or failure / predictive diagnosis processing is performed based on various types of information collected as diesel engine information is described. To do.
- FIG. 2 and 3 are diagrams for explaining the basic concept of the construction machine management system according to the present embodiment.
- FIG. 2 is a diagram of the management system in which each machine body of the construction machine and the center server are connected by an information network.
- FIG. 3 is a diagram illustrating the overall configuration, and FIG. 3 is a view for explaining the concept when forming a construction machine group including a plurality of construction machines.
- a plurality of construction machines 1a to 1c connected to the same center server 105 through an information network are of the same model, and each represents a representative machine or a general machine. Each is assigned a role.
- the representative aircraft is an aircraft (referred to as construction machine 1a in the present embodiment) that is predicted to have a high operation rate and work load in the construction machine group (machine group), and other aircraft in the same machine group. It is a machine that is operated prior to (general machine: construction machines 1b and 1c in the present embodiment), and is previously set empirically from the machine group.
- the representative machine (construction machine 1a) is used for measurement separately from the control sensors installed for operation control in both the representative machine and general machines (construction machines 1b, 1c) in order to acquire various information on the machine.
- the number of sensors is increased compared to that of general aircraft, and a dedicated line corresponding to the increase in information amount is provided when connecting to the center server 105. It should be noted that both the representative aircraft and the general aircraft need only be one or more, and a plurality of aircraft may be set respectively.
- the representative aircraft has detailed information on failures obtained by the measurement sensor during the previous operation period for general aircraft (for example, information on parts that are presumed to be prone to failure, information on operating conditions when various failures occur) , Information related to the correlation between the sensor value for measurement and the sensor value for control, etc. is collected and analyzed in the center server 105 via the information network, so that other aircraft connected to the same information network (other representative aircraft and general Applicable to machine failure analysis and failure / predictive diagnosis.
- grouping for each environmental condition is conceivable.
- the aircraft group for each environmental condition of a cold region, a desert region, a highland, or a wet region.
- a grouping for each soil quality as an index focusing on the engine load can be considered, for example, the airframe group for each work soil quality of the earth and sand zone, the soft rock zone, or the hard rock zone. It may be configured.
- grouping for each work content may be considered.
- the body group may be configured for each work content such as excavation and dismantling.
- the plurality of indices listed above may be combined in a matrix to form a more detailed grouping, and the similarity of operation conditions in each aircraft group may be increased.
- FIG. 4 is a diagram showing an external appearance of a hydraulic excavator shown as an example of the construction machine according to the present embodiment.
- FIG. 5 is a diagram schematically showing a configuration relating to a hydraulic drive system of the excavator.
- a hydraulic excavator 1 that is a construction machine includes a crawler type lower traveling body 5, an upper revolving body 4 that is turnable with respect to the lower traveling body 5, excavation work means, and the like.
- the work apparatus 2 is schematically configured.
- the upper swing body 4 includes a driver's cab 3 in which an operating device of the excavator 1 and a driver's seat on which an operator is seated are arranged, a diesel engine 21 as a prime mover of the excavator 1 as a construction machine, a hydraulic pump 22 and a swing hydraulic pressure. A motor 31 and the like are provided. Inside the cab 3 is provided a monitor unit 103 (see FIG. 6 below) as a display device for displaying various information such as instruments related to the hydraulic excavator 1 and an operation device (not shown) for performing various operations. It has been.
- the diesel engine 21 and the hydraulic pump 22 are mechanically connected, and the hydraulic pump 22 driven by the diesel engine 21 compresses the hydraulic oil in the hydraulic oil tank 24 into pressure oil and supplies it to the control valve 23.
- the control valve 23 controls and distributes the pressure oil necessary for the operation of the lower traveling body 5, the upper swing body 4 and the work device 2 based on an operation command from the operator, and the unnecessary pressure oil is distributed to the hydraulic oil tank 24. It is returning.
- the swing hydraulic motor 31 is driven by pressure oil supplied via the control valve 23, and the upper swing body 4 is moved rightward or leftward with respect to the lower traveling body 5 via the swing reduction device 32 and the forward gear 33. To turn.
- the lower traveling body 5 is provided with left and right traveling hydraulic motors 42 (only one is shown).
- the hydraulic oil sent from the hydraulic pump 22 via the control valve 23 and the center joint 41 causes the traveling hydraulic motor 42 and When the traveling speed reducing device 43 is driven, the crawler 44 is rotationally driven, and the excavator 1 travels forward or backward.
- the work device 2 includes a boom 6, an arm 7, and a bucket 8.
- the boom 6 is moved up and down by a boom cylinder 9, and the arm 7 is dumped (opened) or clouded (stucked) by an arm cylinder 10.
- the bucket 8 is operated to the dump side or the cloud side by the bucket cylinder 11.
- the boom cylinder 9, the arm cylinder 10, and the bucket cylinder 11 are driven by pressure oil supplied via the control valve 23.
- FIG. 6 is a diagram schematically illustrating the diesel engine of the hydraulic excavator according to the present embodiment together with related components.
- the diesel engine 21 of the excavator 1 is directly connected to the hydraulic pump 22 via the output shaft 305, and the hydraulic pump 22 is driven by the diesel engine 21.
- the diesel engine 21 includes an electronically controlled fuel injection device 301, a turbocharger 303 driven by exhaust gas discharged through an exhaust manifold 302, and a DPF (Diesel Particulate Filter) that is one type of exhaust gas purification device.
- a device 401 is provided.
- the DPF device 401 is installed in an exhaust pipe 304 following the exhaust manifold 302, and an oxidation catalyst 402 arranged on the upstream side thereof, and a particulate matter (PM: soot particle) contained in the exhaust gas arranged on the downstream side thereof.
- PM collection filter 403 that collects (Matter).
- the engine control unit 104 has a target engine speed transmitted from the main control unit 101, an actual engine speed detected by a speed sensor 306 provided on the output shaft 305, and supply of exhaust gas to the turbocharger 303.
- the exhaust temperature detected by 404 and the DPF differential pressure detected by the DPF differential pressure sensor 405 are input.
- the engine control unit 104 transmits the target fuel injection amount to the fuel injection device 301 based on the difference between the target engine speed transmitted from the main control unit 101 and the actual engine speed transmitted from the speed sensor 306. To control the engine speed.
- crankcase pressure sensor 308 as an information detecting device for detecting the crankcase pressure as information relating to the machine body of the construction machine is newly added / added only to the representative machine body, and is not provided to the general machine body.
- the main control unit 101 controls the entire operation of the hydraulic excavator 1, and includes a signal from the key switch 201 related to engine start and stop, and an engine control dial 202 that specifies the rotational speed of the diesel engine 21.
- a signal, a signal from an auto idle switch 203 that optimizes the idling speed of the diesel engine 21, a signal from a power mode switch 204 that adjusts the output of the diesel engine 21, and the like are input. Based on these pieces of information, the target engine speed is calculated and transmitted to the engine control unit 104.
- a monitor unit 103 as a display device for providing information on hydraulic pressure and engine to the operator, an information control unit 102 for exchanging information on the body of the excavator 1 with the outside, and the like.
- the information control unit 102 can communicate with the center server 105 via the satellite communication 107 as a communication path.
- the information control unit 102 transmits information on the body of the hydraulic excavator 1 to the center server 105 and also from the center server 105.
- failure analysis and failure / predictive diagnosis processing in the construction machine management system of the present embodiment will be described in detail.
- a case where failure analysis and failure / predictive diagnosis relating to airtightness of a diesel engine are performed will be described as a specific example.
- the construction machine management system includes a cumulative stress detection device (a first sensor configured by various sensors, an engine control unit, an hour meter, etc., which will be described later) that detects cumulative stress (first information) relating to the machine body of the construction machine.
- An information detection device a crankcase pressure sensor 308 (second information detection device) for detecting crankcase pressure (second information), at least one representative aircraft (first aircraft), and a cumulative stress detection device (
- This is a state management system, and is obtained by the center server 105 (air condition diagnosis device) from the representative body (first body).
- crankcase of the general aircraft This is a predictive diagnosis of a failure state related to pressure (second information).
- FIG. 7 is a diagram schematically showing the diagnosis principle of the airtight deterioration in the airtight deterioration diagnosis process which is a failure / predictive diagnosis related to the airtightness of the diesel engine
- FIG. 8 is a diagram showing the correlation of parameters regarding the airtight deterioration diagnosis process
- FIG. 9 is a diagram schematically showing a method for determining airtight deterioration in the airtight deterioration diagnosis process.
- FIG. 7 schematically shows the crankcase 21a of the diesel engine 21 and its peripheral configuration.
- the diesel engine 21 for example, due to wear between parts due to long-term use, the clearance between the cylinder 21 b and the piston 21 c widens, the airtightness inside the engine (that is, the combustion chamber in the cylinder 21 b) deteriorates, and blow-by gas ( As the unburned gas blown from the combustion chamber to the crankcase 21a side increases, the internal pressure of the crankcase 21a increases when the diesel engine 21 deteriorates in airtightness compared to when it is normal. That is, if the internal pressure of the crankcase 21a is monitored by the crankcase pressure sensor 308, a predictive diagnosis can be made regarding the degree of airtight deterioration of the engine from the pressure value.
- FIG. 8 shows the relationship between the crankcase pressure and the cumulative stress in the diesel engine of the representative aircraft, and the vertical axis shows the crankcase pressure and the horizontal axis shows the cumulative stress.
- crankcase pressure P is the initial value P0, and the crankcase pressure P increases as the cumulative stress S increases.
- the crankcase pressure P rapidly increases, and when the cumulative stress S reaches a certain value S1, the crankcase pressure P becomes a normal limit value P1 (crankcase pressure allowable limit value).
- the crankcase pressure P reaches outside the allowable range.
- crankcase pressure correlated with the airtight deterioration of the diesel engine 21 is detected by the crankcase pressure sensor 308 installed in the diesel engine 21 of the representative aircraft.
- Cumulative stress is an hour meter that represents the average value of the engine load factor calculated by the engine control unit based on the detection values of various sensors provided on the representative aircraft and general aircraft, and the accumulated operating time of the construction equipment. The index is obtained by multiplying the values.
- the correlation between the crankcase pressure and the cumulative stress is acquired by storing the information in the database in the center server 105 while plotting the relationship between the cumulative stress and the crankcase pressure during the preceding operation period of the representative aircraft.
- crankcase pressure can be estimated based on the accumulated stress value that can be calculated by the engine control unit 104 from the detection values of various sensors of the general aircraft. It is possible to estimate the degree of hermetic deterioration of the gas and perform predictive diagnosis of the failure state.
- the information (correlation between the crankcase pressure and the accumulated stress) related to the airtight deterioration diagnosis obtained by the representative aircraft (see construction machine 1a) Deploy to general aircraft (construction machines 1b, 1c).
- the correlation between the crankcase pressure and the accumulated stress acquired in the representative aircraft is applied to another general aircraft via the center server 105, and the airtight deterioration diagnosis process of the diesel engine 21 is performed.
- the center server 105 issues a warning (airtight deterioration warning) regarding the airtight deterioration to the construction machine 1b, and the monitor unit (display) (Device) 103 and the like to prompt the operator to inspect the aircraft.
- the center server 105 when performing the airtight deterioration diagnosis process for other general aircraft (construction machine 1c), information on the accumulated stress of the construction machine 1c is taken into the center server 105, and based on the relationship between the accumulated stress and the crankcase pressure. To calculate the estimated crankcase pressure. As a result of the calculation, when it is determined that the estimated crankcase pressure is within the allowable range, the center server 105 does not take an action and ends the process of the security deterioration diagnosis process.
- FIG. 10 is a diagram showing a processing flow in the airtight deterioration diagnosis processing, and is a diagram showing a database update flow possessed by the failure-related data storage unit 501 of the center server 105.
- the failure-related data storage unit 501 of the center server 105 first determines whether or not a predetermined period has been reached in order to update the database relating to failure determination (step S601), and the determination result is YES
- the cumulative stress value in the representative aircraft is obtained (step S602), and the crankcase pressure sensor 308 newly provided in the representative aircraft obtains the average value of the crankcase pressure under a predetermined specific operating condition (step S603).
- Information on the relationship between accumulated stress and crankcase pressure in the database is updated (step S604), and the process is terminated. If the determination result in step S601 is NO, the process ends without updating the database.
- FIG. 11 is a diagram showing a process flow in the airtight deterioration diagnosis process, and shows a determination flow of the airtight deterioration in the airtight deterioration diagnosis process.
- the failure-related data storage unit 501 of the center server 105 first reads information on the relationship between the accumulated stress generated from the representative aircraft information and the crankcase pressure from the database (step S611), and further sets in advance. Information on the allowable crankcase pressure limit value is read from the database (step S612). Next, the failure determination data analysis unit 502 acquires the accumulated stress value of the airframe that is the target of the airtight deterioration determination process (step S613), and the relationship between the accumulated stress read in steps S611 and S612 and the crankcase pressure.
- step S614 uses the accumulated stress value acquired in step S613, the crankcase pressure to be processed in the airtight deterioration determination process is estimated, and the estimated crankcase pressure is acquired (step S614).
- the failure-related warning issuing unit 504 determines whether the estimated crankcase pressure is smaller than the crankcase pressure allowable limit value (step S615). If the determination result is NO, the airtightness of the diesel engine 21 is determined. It is determined that the battery has deteriorated, and the operator is warned to that effect via a display device or the like, or simultaneously with the warning, processing such as output restriction of the diesel engine 21 is performed (step S616). If the decision result in the step S615 is YES, the process is ended as it is.
- an engine control unit 104 that detects cumulative stress (first information) related to the machine body of the construction machine and a crankcase pressure (second information) are detected.
- At least one representative body first body having a crankcase pressure sensor 308 (second information detection device), an engine control unit 104, and not having a crankcase pressure sensor 308.
- a construction machine management system in which a center server 105 manages the state of each machine body in a machine group of construction machines including a general machine body (second machine body), and the accumulated stress and crankcase pressure obtained from a representative machine body
- the sensitivity of the crankcase pressure of the general aircraft based on the correlation of the A sign diagnostic fault condition since it is configured to perform airtightness deterioration diagnosis process performed for, it is possible to perform the failure analysis and failure-sign diagnosis of confidentiality of the airframe of the diesel engine 21 with high accuracy and low cost.
- the failure response capability of the entire aircraft group is improved by pre-operating a representative aircraft with additional failure analysis capabilities by adding sensors and deploying information related to failure analysis to other general aircraft. Can be made.
- the airtight deterioration diagnosis process is performed as the failure diagnosis related to the airtightness of the diesel engine.
- the overload diagnosis process is performed as the failure prevention related to the overload of the diesel engine. The case will be described.
- the same members and processes as those of the first embodiment are denoted by the same reference numerals, and description thereof is omitted.
- the construction machine management system in the present embodiment includes a supercharging pressure sensor 307 (first information detecting device) for detecting a supercharging pressure (first information) related to the machine body of the construction machine, and an in-cylinder pressure (second information).
- An in-cylinder pressure sensor 309 second information detection device to detect, at least one representative aircraft (first aircraft), a supercharging pressure sensor 307 (first information detection device), and an in-cylinder pressure sensor 309
- a machine group of a construction machine including at least one general machine body (second machine body) that does not have (second information detection device the state of each machine body is managed, and a center server 105 (airframe condition diagnosis) Device), the correlation information between the supercharging pressure (first information) and the in-cylinder pressure (second information) obtained from the representative airframe (first airframe), and the supercharging pressure (first airframe) of the general airframe (second airframe).
- Information and general aircraft (second And it performs sign diagnosis of a fault condition relating to the body) of the cylinder pressure (second information).
- FIG. 12 is a diagram schematically illustrating the principle of overload diagnosis in an overload diagnosis process that is a failure / predictor diagnosis related to overload of a diesel engine
- FIG. 13 is a diagram illustrating the correlation of parameters related to the overload diagnosis process
- FIG. 14 is a diagram schematically illustrating an overload determination method in the overload diagnosis process.
- FIG. 12 schematically shows the peripheral configuration of the diesel engine 21.
- the in-cylinder pressure (combustion pressure) of the diesel engine 21 is a representative index of stress applied to the diesel engine 21, and from the viewpoint of engine protection, a margin is provided so that the in-cylinder pressure does not become excessive, and the output of the diesel engine 21 is increased. Is adjusted.
- the engine output is managed by using, as alternative parameters, a supercharging pressure or a fuel injection amount that has a certain correlation with the in-cylinder pressure. Since the relationship between the supercharging pressure and the fuel injection amount with respect to the in-cylinder pressure may be shifted depending on the quality of the fuel, the intake air temperature, and the like, the existing supercharging pressure sensor 307 is connected to the representative aircraft that operates in advance.
- an in-cylinder pressure sensor 309 is newly added and added, and the relationship between the detected value of the boost pressure sensor 307 and the detected value of the in-cylinder pressure sensor 309 (correlation between the boost pressure and the in-cylinder pressure) during the preceding operation period
- the information is stored in a database in the center server 105 while plotting for each fuel brand A, B).
- the overload diagnosis for estimating the degree of overload to the diesel engine 21 under a wide range of conditions and performing a predictive diagnosis of a failure state is further performed. It becomes possible to carry out accurately.
- FIG. 13 the relationship between the supercharging pressure and the in-cylinder pressure in the diesel engine of the representative aircraft is shown for each fuel brand, the in-cylinder pressure is shown on the vertical axis, and the supercharging pressure is shown on the horizontal axis.
- the in-cylinder pressure Pt does not reach the allowable limit value Pt1 (in-cylinder pressure allowable limit value) even when the supercharging pressure Ps reaches a certain value Ps1, and the in-cylinder pressure Pt is allowable even if the supercharging pressure Ps exceeds the value Ps1. Does not reach out of range.
- the construction machine 1b when performing an overload diagnosis process for a certain general machine body (construction machine 1b), the construction machine 1b is included in the center server 105 based on the operating condition of the construction machine 1b (for example, when the fuel is a brand B).
- the information regarding the supercharging pressure is taken in, and the estimated value of the in-cylinder pressure is calculated based on the relationship between the supercharging pressure and the in-cylinder pressure.
- the center server 105 issues an overload warning (overload warning) to the construction machine 1b, and the monitor unit (display device) ) Prompt the operator to suppress the output by displaying on 103 or the like.
- construction machine 1c when performing an overload diagnosis process for another general machine (construction machine 1c), construction is performed in the center server 105 based on the operating conditions of the construction machine 1c (for example, when the fuel is a brand A). Information on the supercharging pressure of the machine 1c is taken in, and an estimated value of the in-cylinder pressure is calculated based on the relationship between the supercharging pressure and the in-cylinder pressure. As a result of the calculation, when it is determined that the estimated in-cylinder pressure is within the allowable range, the center server 105 does not take an action and ends the process of the overload diagnosis process.
- FIG. 15 is a diagram illustrating a processing flow in the overload diagnosis processing, and is a diagram illustrating a database update flow included in the failure-related data accumulation unit 501 of the center server 105.
- the failure-related data storage unit 501 of the center server 105 first determines whether or not a predetermined period has been reached in order to update the failure prevention database (step S621), and the determination result is YES
- step S622 fuel information (information such as fuel brand) on the representative aircraft is obtained, and the supercharging pressure sensor 307 already installed on the representative aircraft is used to supercharge the representative aircraft under a predetermined operating condition.
- the average value of the pressure is obtained (step S623), and the average value of the in-cylinder pressure under a specific operation condition determined in advance is obtained by the in-cylinder pressure sensor 309 newly installed in the representative aircraft (step S624), and the supercharging pressure in the database is obtained.
- step S625 the information on the relationship between the cylinder pressure and the in-cylinder pressure are updated (step S625), and the process is terminated. If the determination result in step S621 is NO, the process ends without updating the database.
- FIG. 16 is a diagram illustrating a processing flow in the overload diagnosis processing, and is a diagram illustrating an overload determination flow in the overload diagnosis processing.
- the failure-related data storage unit 501 of the center server 105 first reads information on the relationship between the supercharging pressure and the in-cylinder pressure generated from the information on the representative aircraft from the database (step S631), and further presets the information. Information relating to the in-cylinder pressure allowable limit value is read from the database (step S632).
- the failure prevention data analysis unit 503 acquires the fuel information of the airframe to be processed in the overload determination process (step S633), acquires the supercharging pressure (step S634), and in steps S631 and S632 The in-cylinder pressure of the processing target body of the overload determination process using the relationship between the read supercharging pressure and the in-cylinder pressure corresponding to the fuel information obtained in step S633 and the supercharging pressure obtained in step S613. And the estimated in-cylinder pressure is acquired (step S635).
- the failure-related warning issuing unit 504 determines whether the estimated in-cylinder pressure is smaller than the in-cylinder pressure allowable limit value (step S636). If the determination result is NO, the load on the diesel engine 21 is excessive.
- step S637 It is determined that there is, and an operator is warned to that effect via a display device or the like, or simultaneously with the warning, processing such as output restriction of the diesel engine 21 is performed (step S637). If the decision result in the step S636 is YES, the process is ended as it is.
- the overload diagnosis process is performed as the prevention of the failure related to the overload of the diesel engine has been described.
- the overspeed diagnosis process is performed as the failure prevention related to the overspeed of the turbocharger. The case where it performs is demonstrated.
- the same members and processes as those in the first and second embodiments are denoted by the same reference numerals, and description thereof is omitted.
- the construction machine management system in the present embodiment includes a supercharging pressure sensor 307 (first information detection device) that detects a supercharging pressure (first information) related to the machine body of the construction machine, and a turbine speed (second information).
- a turbine rotation speed sensor 310 second information detection device for detecting the engine pressure, at least one representative aircraft (first aircraft), a supercharging pressure sensor 307 (first information detection device), and turbine rotation In a machine group of a construction machine including at least one general machine body (second machine body) that does not have the number sensor 310 (second information detection device), the state of each machine body is managed, and the center server 105 ( Correlation information between the supercharging pressure (first information) and the turbine speed (second information) obtained from the representative aircraft (first aircraft) and the supercharging of the general aircraft (second aircraft) by the machine body condition diagnosis device) Pressure ) And on the basis, and performs sign diagnosis of fault conditions relates to a turbine rotational speed of general machine body (second body) (second information).
- FIG. 17 is a diagram schematically showing the principle of the overspeed diagnosis in the overspeed diagnosis process which is a failure / predictive diagnosis related to the overspeed of the turbocharger of the diesel engine
- FIG. 18 is a correlation of parameters regarding the overspeed diagnosis process
- FIG. 19 is a diagram schematically illustrating a method for determining over-rotation in the over-rotation diagnosis process.
- FIG. 17 schematically shows the diesel engine 21 and the turbocharger 303 together with the peripheral configuration thereof.
- the supercharging pressure in the turbocharger depends on the turbine speed, but when working at high altitudes as shown in Fig. 3, the density of the air taken in is low, so compared with the same level at the same turbine speed, the supercharging is higher than on the flat ground. Pressure is lowered. Therefore, in order to obtain the same supercharging pressure as that on the flat ground, it is necessary to increase the turbine rotational speed. In other words, for example, when the engine is driven without lowering the target supercharging pressure at high altitudes, the turbine speed may increase and the turbocharger may be forced. Therefore, it is necessary to control the upper limit of the turbine speed. is there.
- the turbine speed is managed using a supercharging pressure having a certain correlation with the turbine speed as an alternative parameter.
- the relationship between the supercharging pressure and the turbine rotation speed may not be uniformly determined depending on the environment, the aging of the supercharger, and the like.
- a turbine speed sensor 310 is newly installed and added, and the relationship between the detected value of the boost pressure sensor 307 and the detected value of the turbine speed sensor 310 (correlation between the boost pressure and the turbine speed) is operated during the preceding operation period.
- the information is stored in the database in the center server 105 while plotting for each environment (for example, flat land or highland).
- the construction machine 1b when executing the over-rotation diagnosis process of a general machine body (construction machine 1b), the construction machine 1b is included in the center server 105 based on the operating environment of the construction machine 1b (for example, when the operating environment is high altitude).
- the information regarding the supercharging pressure is taken in, and the estimated value of the turbine rotational speed is calculated based on the relationship between the supercharging pressure and the turbine rotational speed.
- the center server 105 issues a warning (overspeed warning) about the overspeed to the construction machine 1b, and the monitor unit (display) (Device) 103 and the like are displayed to prompt the operator to suppress output.
- construction machine 1c when executing the over-rotation diagnosis process of another general machine (construction machine 1c), construction is performed in the center server 105 based on the operating conditions of the construction machine 1c (for example, when the operating environment is flat). Information on the supercharging pressure of the machine 1c is taken in, and an estimated value of the turbine rotational speed is calculated based on the relationship between the supercharging pressure and the turbine rotational speed. As a result of the calculation, when it is determined that the estimated turbine rotational speed is within the allowable range, the center server 105 does not take an action and ends the process of the overspeed diagnosis process.
- a representative aircraft is selected from a group of aircraft connected to an information network, and a measurement sensor is provided for the representative aircraft.
- the representative aircraft plays the role of a probe that collects information related to failures in the actual environment / actual work, and by sharing that information with other general aircraft via the information network, not only the representative aircraft, It becomes possible to improve the failure response capability of the entire group of aircraft connected to the network.
- by limiting the installation and addition of measurement sensors to the representative aircraft it is possible to reduce the cost of the entire construction machine management system and the increase in network load.
- the crankcase pressure sensor, the in-cylinder pressure sensor, and the turbine rotational speed sensor are exemplified as the measurement sensors.
- the present invention is not limited to these, and for example, an engine torque sensor, It goes without saying that other measurement sensors such as a humidity sensor and various temperature sensors can be applied.
- a measurement sensor is newly added and added to enhance failure analysis and predictive diagnosis capabilities.
- the number of information to be transmitted to the center server 105 may be increased as compared to other general aircraft, or the information transmission interval may be shortened compared to other general aircraft. It is done.
- the diesel engine which is the prime mover of the construction machine
- the present invention is not limited to this, and for example, a hydraulic device or a structure in the construction machine It can also be applied to body diagnosis.
- 1 Excavator (construction machine) 1a Construction machinery (representative aircraft) 1b, 1c Construction machinery (general aircraft) 101 Main control unit (information detection device) 102 Information control unit (information network) 103 Monitor unit (display device) 104 Engine control unit (information detection device) 105 Center server (air condition diagnosis device) 107 Satellite communications (information network) 306 Rotational speed sensor (information detection device) 307 Supercharging pressure sensor (information detection device) 308 Crankcase pressure sensor (information detection device) 404 Exhaust temperature sensor (information detection device) 405 DPF differential pressure sensor (information detection device) 501 Failure-related data storage unit (air condition diagnosis device) 502 Data analysis unit for failure determination (air condition diagnosis device) 503 Failure prevention data analysis unit (air condition diagnosis device) 504 Failure related warning issuing unit (air condition diagnosis device)
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Abstract
Description
本発明の第1の実施の形態を図1~図11を参照しつつ説明する。
本発明の第2の実施の形態を図12~図15を参照しつつ説明する。
本発明の第3の実施の形態を図17及び図19を参照しつつ説明する。
1a 建設機械(代表機体)
1b、1c 建設機械(一般機体)
101 メインコントロールユニット(情報検出装置)
102 情報コントロールユニット(情報ネットワーク)
103 モニターユニット(表示装置)
104 エンジンコントロールユニット(情報検出装置)
105 センターサーバー(機体状態診断装置)
107 衛星通信(情報ネットワーク)
306 回転数センサ(情報検出装置)
307 過給圧センサ(情報検出装置)
308 クランクケース圧センサ(情報検出装置)
404 排気温度センサ(情報検出装置)
405 DPF差圧センサ(情報検出装置)
501 故障関連データ蓄積部(機体状態診断装置)
502 故障判定用データ解析部(機体状態診断装置)
503 故障防止用データ解析部(機体状態診断装置)
504 故障関連警告発令部(機体状態診断装置)
Claims (9)
- 建設機械の機体に関する第1情報を検出する第1情報検出装置、及び第2情報を検出する第2情報検出装置を有する、少なくとも1つの第1機体と、前記第1情報検出装置を有し、かつ前記第2情報検出装置を有しない、少なくとも1つの第2機体とを含む建設機械の機体群を構成する各機体の状態を管理する建設機械の管理システムであって、
前記第1機体から得られた前記第1情報と前記第2情報の相関情報と、前記第2機体の前記第1情報とに基づいて、前記第2機体の第2情報に関する故障状態の予兆診断を行う機体状態診断装置を備えたことを特徴とする建設機械の管理システム。 - 請求項1記載の建設機械の管理システムにおいて、
市場に投入される建設機械である前記第1機体は、前記第2機体に比べて稼働率または負荷率が高いことを特徴とする建設機械の管理システム。 - 請求項1記載の建設機械の管理システムにおいて、
前記第1機体と前記第2機体とは、同機種であることを特徴とする建設機械の管理システム。 - 請求項1記載の建設機械の管理システムにおいて、
前記第1機体と前記第2機体とは、同じ情報ネットワークに接続されていることを特徴とする建設機械の管理システム。 - 請求項1記載の建設機械の管理システムにおいて、
前記機体群は、前記建設機械の機体の稼働環境、作業負荷、又は、作業種類のいずれかに基づいて組分けの設定がなされたことを特徴とする建設機械の管理システム。 - 請求項1記載の建設機械の管理システムにおいて、
前記第1機体の第2情報検知装置は、前記建設機械のエンジンの燃焼室の内圧を検知する筒内圧センサ、前記エンジンの過給機のタービン回転数を検知するタービン回転数センサ、前記エンジンのクランクケースの内圧を検知するクランクケース内圧センサ、前記エンジンのトルクを検知するエンジントルクセンサ、湿度を検知する湿度センサのうちの少なくとも何れか1つを有することを特徴とする建設機械の管理システム。 - 請求項1記載の建設機械の管理システムにおいて、
前記第1機体は、前記第2機体よりも機体状態診断装置に発信する情報の種類が多いことを特徴とする建設機械の管理システム。 - 請求項1記載の建設機械の管理システムにおいて、
前記第1機体から前記機体状態診断装置に情報が送信される周期は、前記第2機体よりも短いことを特著とする建設機械の管理システム。 - 請求項1記載の建設機械の管理システムにおいて、
前記機体状態診断装置は、
前記第2機体が故障であると診断した場合、又は前記第2機体が故障に至る可能性が高い状況と診断した場合には、診断内容を表示装置に表示する、又は診断内容に基づいて建設機械の原動機の出力制限を行うことを特徴とする建設機械の管理システム。
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EP15865507.6A EP3228849B1 (en) | 2014-12-05 | 2015-11-24 | Construction machine management system |
KR1020177004141A KR101918424B1 (ko) | 2014-12-05 | 2015-11-24 | 건설 기계의 관리 시스템 |
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