CN107229804A - Helicopter Main Reducer lubricating system dynamic simulation analysis method and device - Google Patents
Helicopter Main Reducer lubricating system dynamic simulation analysis method and device Download PDFInfo
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Abstract
The invention discloses a kind of Helicopter Main Reducer lubricating system dynamic simulation analysis method and device, by extracting the oil sump 3-D geometric model of Helicopter Main Reducer, the distribution space of lubricating oil is simulated in oil sump 3-D geometric model；The flight parameter of Helicopter Main Reducer is read, flight parameter is calculated and acts on the corresponding liquid level normal vector of the liquid level formed during lubricating oil；Using the real-time lubricating oil amount of level surface method vector sum oil sump as constraints, the lubricating oil level height data in oil sump 3-D geometric model are calculated；Abstract and parametrization is carried out to Helicopter Main Reducer lubricating system component, and builds lubricating system parametric simulation analysis model；Emulation and boundary condition parameter are set, and simulation analysis obtain each oil site pressure distribution and assignment of traffic in lubricating system.The Helicopter Main Reducer lubricating system dynamic simulation analysis method and device that the present invention is provided, simulation result and measured value error are small, can obtain the performance parameters such as pressure and flow in whole time history.
Description
Technical field
The present invention relates to Helicopter Main Reducer lubricating system field, especially, it is related to a kind of Helicopter Main Reducer profit
Sliding system dynamic simulation analysis method and device.
Background technology
Transmission system, engine and rotor system are three big crucial dynamic components of helicopter.The effect of transmission system be by
The power and rotating speed of engine are delivered to rotor, tail-rotor and each annex according to a certain percentage, are turboaxle motor power outputs
Essential power transmission component, is also sole power pipeline.Therefore, in helicopter transmission system reliability than
Engine calls are high, and helicopter performance depends greatly on the performance of transmission system.
Decelerator lubricating system is indispensable important component in Helicopter Transmission System, and lubricating system performance refers to
Mark (such as lubricating oil pressure) is one of the important technology index for monitoring helicopter reducer working condition, outfield take a flight test experience have shown that,
Decelerator lubricating system performance is influenceed larger by flight attitude change.Slided for example, once there is the decelerator when big posture is breakked away
The low phenomenon of oil pressure, or even there is the failure of the low alarm of lubricating oil pressure, cause helicopter to have to change current action, directly
Influence Helicopter Combat performance.Therefore it is badly in need of by means of lubricating system performance under the conditions of the different postures of simulation analysis means research.
At present, the emulation of lubricating system static properties is focused primarily upon with calculating on Lubrication System Simulation Analysis method, no
Consider the influence of flight attitude and acceleration to liquid level.By calculating the performance of the limited lubricating system under discrete state,
The performance of the lubricating system of the whole time history of lubricating system can not be obtained.It can be seen that, existing Lubrication System Simulation Analysis method
Because not considering attitudes vibration and acceleration influence, it is impossible to react truth.Therefore, existing Lubrication System Simulation Analysis method
Greasy property of the Helicopter Main Reducer under state of flight can not be assessed, is a technical problem urgently to be resolved hurrily.
The content of the invention
It is existing to solve the invention provides a kind of Helicopter Main Reducer lubricating system dynamic simulation analysis method and device
The technology that some Lubrication System Simulation Analysis methods can not assess greasy property of the Helicopter Main Reducer under state of flight is asked
Topic.
The technical solution adopted by the present invention is as follows：
According to an aspect of the present invention there is provided a kind of Helicopter Main Reducer lubricating system dynamic simulation analysis method,
Including step：
The oil sump 3-D geometric model of Helicopter Main Reducer is extracted, point of lubricating oil is simulated in oil sump 3-D geometric model
Cloth space；
The flight parameter of Helicopter Main Reducer is read, calculating flight parameter, to act on the liquid level formed during lubricating oil relative
The liquid level normal vector answered；
The real-time lubricating oil amount of level surface method vector sum oil sump to calculate calculates oil sump 3-D geometric model as constraints
In lubricating oil lubricating oil level height data；
Abstract and parametrization is carried out to the component of Helicopter Main Reducer lubricating system, and builds lubricating system parametrization
Simulation analysis model, simulation analysis model reads lubricating oil level height data in real time；
Emulation and boundary condition parameter are set, and simulation analysis obtain each oil site pressure distribution and flow point in lubricating system
Match somebody with somebody.
Further, the flight parameter of Helicopter Main Reducer includes three attitude angles and three directional accelerations, reads
The flight parameter of Helicopter Main Reducer, calculates flight parameter and acts on the corresponding liquid level normal direction of the liquid level formed during lubricating oil
The step of amount, includes：
Corresponding first per unit system of liquid level that lubricating oil is formed when calculating three attitude angle independent roles is constrained by geometrical relationship
Vector；
Liquid level corresponding second unit normal vector of lubricating oil formation when calculating three directional acceleration independent roles；
According to the first unit normal vector and the second unit normal vector calculated, liquid level normal vector is obtained.
Further, using the real-time lubricating oil amount of level surface method vector sum oil sump that calculates as constraints, oil sump three is calculated
The step of lubricating oil level height data of lubricating oil in dimension geometrical model, includes：
Liquid level normal level is adjusted using dichotomy, oil sump 3-D geometric model is progressively cut；
The oil sump tank volume of the plane institute envelope constituted with liquid level normal is solved, if oil sump tank volume is real with oil sump
When lubricating oil amount difference when being less than default calculating allowable error, then the plane drawn is liquid level, measures lubricating oil in liquid level
Lubricating oil level height data.
Further, abstract and parametrization is carried out to the component of Helicopter Main Reducer lubricating system, and builds lubrication
The step of systematic parameter simulation analysis model, includes：
Component and part characteristic to Helicopter Main Reducer lubricating system carry out abstract and parametrization；
According to abstract and parametrization component and each component the actual order of connection, Helicopter Main Reducer is set up
Simulation analysis model, simulation analysis model can call lubricating oil level height data.
Further, according to simulation analysis model, each oil site pressure distribution and assignment of traffic in lubricating system are obtained
Step includes：
Lubrication System Simulation Analysis model, reads the flight parameter and corresponding oil sump lubricating oil oil of Helicopter Main Reducer
Position altitude information；
Emulation and boundary condition parameter are set in simulation analysis model, each lubrication point pressure of each moment and flow is calculated；
Point pressure and flow are respectively lubricated according to each moment calculated, the result of the real-time lubricating oil amount of oil sump is updated.
According to another aspect of the present invention there is provided a kind of Helicopter Main Reducer lubricating system dynamic simulation analysis device,
Applied in terminal, Helicopter Main Reducer lubricating system dynamic simulation analysis device includes：
Extraction module, the oil sump 3-D geometric model for extracting Helicopter Main Reducer, in oil sump 3-D geometric model
The distribution space of middle simulation lubricating oil；
First computing module, the flight parameter for reading Helicopter Main Reducer, calculates flight parameter and acts on cunning
The corresponding liquid level normal vector of the liquid level that is formed when oily；
Second computing module, the real-time lubricating oil amount of level surface method vector sum oil sump to calculate is calculated fuel-displaced as constraints
The lubricating oil level height data of lubricating oil in the 3-D geometric model of pond；
Module is set up, abstract and parametrization is carried out for the component to Helicopter Main Reducer lubricating system, and build
Lubricating system parametric simulation analysis model, simulation analysis model reads lubricating oil level height data in real time；
Acquisition module, for setting emulation and boundary condition parameter, simulation analysis obtain each lubrication in lubricating system and pressed
Power is distributed and assignment of traffic.
Further, the flight parameter of Helicopter Main Reducer includes three attitude angles and three directional accelerations, first
Computing module includes：
First computing unit, the liquid level that lubricating oil is formed when calculating three attitude angle independent roles for being constrained by geometrical relationship
Corresponding first unit normal vector；
Second computing unit, the liquid level corresponding second of lubricating oil formation during for calculating three directional acceleration independent roles
Unit normal vector；
Acquiring unit, according to the first unit normal vector and the second unit normal vector calculated, obtains liquid level normal vector.
Further, the second computing module includes：
Cutter unit, for adjusting liquid level normal level using dichotomy, progressively cuts oil sump 3-D geometric model；
Measuring unit, the oil sump tank volume for solving the plane institute envelope constituted with liquid level normal, if oil sump pond
When the difference of body volume and the real-time lubricating oil amount of oil sump is less than default calculating allowable error, then the plane drawn is liquid level, is measured
The lubricating oil level height data of lubricating oil in liquid level.
Further, setting up module includes：
Abstraction unit, for carrying out abstract and ginseng to each component of Helicopter Main Reducer lubricating system and part characteristic
Numberization, sets up the simulation analysis model of Helicopter Main Reducer lubricating system；
Unit is set up, for according to abstract and parametrization component and each component the actual order of connection, setting up straight
The simulation analysis model of owner's decelerator is risen, simulation analysis model can call lubricating oil level height data.
Further, acquisition module includes：
Reading unit, flight parameter and corresponding oil sump lubricating oil oil level for reading Helicopter Main Reducer；
3rd computing unit, for setting emulation and boundary condition parameter in simulation analysis model, calculates each moment each
Lubricate point pressure and flow；
Updating block, for respectively lubricating point pressure and flow according to each moment calculated, updates the real-time lubricating oil amount of oil sump
Result.
The invention has the advantages that：
The Helicopter Main Reducer lubricating system dynamic simulation analysis method and device that the present invention is provided, it is dynamic to lubricating system
State considers influence of the flight parameter to oil level when emulating, closer to actual conditions；And it can emulate and obtain lubricating system whole
Performance in individual time history.The Helicopter Main Reducer lubricating system dynamic simulation analysis method and device that the present invention is provided,
Simulation result and measured value error are small, can obtain the performances such as pressure and flow in the whole time history of decelerator lubricating system and join
Number.
In addition to objects, features and advantages described above, the present invention also has other objects, features and advantages.
Below with reference to figure, the present invention is further detailed explanation.
Brief description of the drawings
The accompanying drawing for constituting the part of the application is used for providing a further understanding of the present invention, schematic reality of the invention
Apply example and its illustrate to be used to explain the present invention, do not constitute inappropriate limitation of the present invention.In the accompanying drawings：
Fig. 1 is the flow signal of Helicopter Main Reducer lubricating system dynamic simulation analysis method preferred embodiment of the present invention
Figure；
Fig. 2 is the flight parameter of reading Helicopter Main Reducer in Fig. 1, calculates the flight parameter and acts on the cunning
The refinement schematic flow sheet of the step preferred embodiment of the corresponding liquid level normal vector of the liquid level that is formed when oily；
Fig. 3 is that corresponding first list of liquid level that lubricating oil is formed when calculating three attitude angle independent roles is constrained by geometrical relationship
Position normal vector V1Computing Principle schematic diagram；
Fig. 4 be the real-time lubricating oil amount of the level surface method vector sum oil sump in Fig. 1 to calculate as constraints, calculate institute
The refinement flow for stating the step preferred embodiment of the lubricating oil level height data of the lubricating oil in oil sump 3-D geometric model is shown
It is intended to；
Fig. 5 is to carry out abstract and parametrization to the component of Helicopter Main Reducer lubricating system in Fig. 1, and builds lubrication
Systematic parameter simulation analysis model, simulation analysis model reads the step preferred embodiment of lubricating oil level height data in real time
Refine schematic flow sheet；
Fig. 6 is setting emulation and boundary condition parameter in Fig. 1, and simulation analysis, which are obtained, respectively lubricates point pressure point in lubricating system
The refinement schematic flow sheet of cloth and the step preferred embodiment of assignment of traffic；
Fig. 7 is the functional block of Helicopter Main Reducer lubricating system dynamic simulation analysis device preferred embodiment of the present invention
Figure；
Fig. 8 is the high-level schematic functional block diagram of the first computing module preferred embodiment in Fig. 7；
Fig. 9 is the high-level schematic functional block diagram of the second computing module preferred embodiment in Fig. 7；
Figure 10 is the high-level schematic functional block diagram that module preferred embodiment is set up in Fig. 7；
Figure 11 is the high-level schematic functional block diagram of acquisition module preferred embodiment in Fig. 7.
Drawing reference numeral explanation：
10th, extraction module；20th, the first computing module；30th, the second computing module；40th, module is set up；50th, acquisition module；
21st, the first computing unit；22nd, the second computing unit；23rd, acquiring unit；31st, cutter unit；32nd, measuring unit；41st, abstract list
Member；42nd, unit is set up；51st, reading unit；52nd, the 3rd computing unit；53rd, updating block.
Embodiment
It should be noted that in the case where not conflicting, the feature in embodiment and embodiment in the application can phase
Mutually combination.Describe the present invention in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
Reference picture 1, the preferred embodiments of the present invention are there is provided a kind of Helicopter Main Reducer lubricating system dynamic simulation point
Analysis method, including step：
Step S100, the oil sump 3-D geometric model for extracting Helicopter Main Reducer, the mould in oil sump 3-D geometric model
Intend the distribution space of lubricating oil.
The master of Helicopter Main Reducer lubricating system is subtracted into oil sump and pipeline inner chamber is converted into 3D solid；Remove three-dimensional real
Each driving member entity and bearing member entity are taken up space in body, oil sump 3-D geometric model are obtained, in oil sump 3-D geometric model
The distribution space of middle simulation lubricating oil.
Step S200, the flight parameter for reading Helicopter Main Reducer, calculate when flight parameter acts on lubricating oil and are formed
The corresponding liquid level normal vector of liquid level.
The flight parameter of Helicopter Main Reducer is read, and according to the flight parameter of reading, calculates flight parameter effect
The corresponding liquid level normal vector of the liquid level that is formed when lubricating oil.Wherein, flight parameter is classified by type, can be divided into posture angular dimensions
With acceleration parameter etc..In the present embodiment, when acting solely on lubricating oil by calculating the flight parameter of each type respectively
The corresponding liquid level normal vector of the liquid level of formation, and the flight parameter of each type calculated respectively is acted solely on into lubricating oil
When the corresponding liquid level normal vector of the liquid level that is formed be added, obtain whole flight parameter and act on the liquid level formed during lubricating oil
Corresponding liquid level normal vector.
Step S300, the real-time lubricating oil amount of level surface method vector sum oil sump to calculate calculate oil sump three as constraints
Tie up the lubricating oil level height data of the lubricating oil in geometrical model.
The real-time lubricating oil amount of level surface method vector sum oil sump to calculate carries out secondary development as constraints in CATIA,
The lubricating oil oil level of the lubricating oil in oil sump 3-D geometric model is calculated using dichotomy.
Step S400, the component to Helicopter Main Reducer lubricating system carry out abstract and parametrization, and build lubrication
Systematic parameter simulation analysis model, simulation analysis model reads lubricating oil level height data in real time.
The component and part characteristic lubricated helicopter reducer carries out abstract and parametrization, and according to calculating
Lubricating oil oil level, sets up the simulation analysis model of helicopter reducer lubricating system in Flowmaster simulation analysis softwares.
Step S500, setting emulation and boundary condition parameter, simulation analysis obtain each lubrication point pressure in lubricating system and divided
Cloth and assignment of traffic.
Emulation analysis parameter and boundary condition are set, lubricating oil oil level is read, simulation analysis obtain main reducing gear lubricating system
In each oil site pressure and flow.
The Helicopter Main Reducer lubricating system dynamic simulation analysis method that the present embodiment is provided, it is dynamically imitative to lubricating system
Influence of the flight parameter to oil level is considered when true, closer to actual conditions；And it can emulate and obtain lubricating system when whole
Between performance in course.The Helicopter Main Reducer lubricating system dynamic simulation analysis method that the present embodiment is provided, simulation result
It is small with measured value error, it can obtain the performance parameters such as pressure and flow in the whole time history of decelerator lubricating system.
Preferably, as shown in Fig. 2 the Helicopter Main Reducer lubricating system dynamic simulation analysis side that the present embodiment is provided
Method, the flight parameter of Helicopter Main Reducer includes three attitude angles and three directional accelerations, and step S200 includes：
Step S210, the liquid level that is formed of lubricating oil when calculating three attitude angle independent roles corresponding the is constrained by geometrical relationship
One unit normal vector.
As shown in figure 3, reading three attitude angles in flight parameter, it is independent to calculate three attitude angles by geometrical relationship constraint
The liquid level corresponding first unit normal vector V of lubricating oil formation during effect1.Wherein, three attitude angles include angle of pitch α, yaw angle
β, roll angle γ.n1x、n1y、n1zRespectively the first unit normal vector V1Unit normal vector in x-axis, y-axis and z-axis.
The liquid level corresponding second unit normal direction of lubricating oil formation when step S220, three directional acceleration independent roles of calculating
Amount.
Three directional accelerations in flight parameter are read, lubricating oil formation when calculating three directional acceleration independent roles
The corresponding second unit normal vector V of liquid level2.Wherein, three directional accelerations include the longitudinal angular speed a of bodyx, body lateral angle
Speed ayWith body normal direction angular speed az。
The first unit normal vector and the second unit normal vector that step S230, basis are calculated, obtain liquid level normal vector.
According to the first unit normal vector V calculated1With the second unit normal vector V2, calculate liquid level normal vector V, liquid level
Normal vector V is the first unit normal vector V1With the second unit normal vector V2Vector.
The Helicopter Main Reducer lubricating system dynamic simulation analysis method that the present embodiment is provided, is constrained by geometrical relationship and counted
Liquid level corresponding first unit normal vector of lubricating oil formation when calculating three attitude angle independent roles；Calculate three directional acceleration lists
Corresponding second unit normal vector of liquid level that solely lubricating oil is formed during effect；It is single according to the first unit normal vector calculated and second
Position normal vector, obtains liquid level normal vector.The Helicopter Main Reducer lubricating system dynamic simulation analysis method that the present embodiment is provided,
The influence of attitude angle and acceleration to oil level is considered during to lubricating system dynamic simulation, closer to actual conditions.
Preferably, as shown in figure 4, the Helicopter Main Reducer lubricating system dynamic simulation analysis side that the present embodiment is provided
Method, step S300 includes：
Step S310, using dichotomy adjust liquid level normal level, progressively cut oil sump 3-D geometric model.
The real-time lubricating oil amount of level surface method vector sum oil sump to calculate carries out secondary development as constraints in CATIA,
Liquid level normal level is adjusted using dichotomy, oil sump 3-D geometric model is progressively cut.
Step S320, the oil sump tank volume for solving the plane institute envelope constituted with liquid level normal, if oil sump pond body body
When the difference of product and the real-time lubricating oil amount of oil sump is less than default calculating allowable error, then the plane drawn is liquid level, measures liquid level
The lubricating oil oil level of interior lubricating oil.
When the oil sump tank volume of the plane institute envelope constituted with liquid level normal is equal with the real-time lubricating oil amount of oil sump, this puts down
Face is just liquid level.The volume function of solving entity is carried in CATIA, level progressively cutting oil is adjusted by using dichotomy
Pond 3-D geometric model, solves the oil sump tank volume of the plane institute envelope constituted with liquid level normal, until oil sump tank volume
When being less than default calculating allowable error ε with the difference of the real-time lubricating oil amount of oil sump, then the plane drawn is real-time liquid level, is surveyed
The lubricating oil oil level of the lubricating oil gone out in liquid level calls for Flowmaster.
The Helicopter Main Reducer lubricating system dynamic simulation analysis method that the present embodiment is provided, liquid is adjusted using dichotomy
Face plane normal height, progressively cuts oil sump 3-D geometric model；Solve the oil of the plane institute envelope constituted with liquid level normal
Pond tank volume, if the difference of oil sump tank volume and the real-time lubricating oil amount of oil sump is less than default calculating allowable error,
The plane gone out is liquid level, measures the lubricating oil oil level of the lubricating oil in liquid level.The Helicopter Main Reducer lube system that the present embodiment is provided
System dynamic simulation analysis method, using the attitude angle and acceleration of reading as according to the liquid level normal vector calculated, is measured in liquid level
Lubricating oil lubricating oil oil level, so as to consider the influence of attitude angle and acceleration to oil level during to lubricating system dynamic simulation, more
Close to actual conditions.
Preferably, as shown in figure 5, the Helicopter Main Reducer lubricating system dynamic simulation analysis side that the present embodiment is provided
Method, step S400 includes：
Step S410, each component and part characteristic to main reducing gear lubricating system carry out abstract and parametrization.
Abstract and parametrization is carried out to each component and part characteristic of main reducing gear lubricating system, wherein, component
Mainly include nozzle, straight tube, bend pipe, fuel tank, oil pump, pressure regulator valve, oil filter and radiator etc., part characteristic mainly includes
Nozzle bore, nozzle hole number, pipeline latus rectum, pipeline type of attachment, fuel tank shape, inlet port position, oil pump flow rate pressure are special
Property, pressure regulator valve pressure setting characteristic, oil filter flow resistance characteristic, radiator flow resistance and flow, temperature characterisitic etc..
Step S420, according to it is abstract and parametrization component and each component the actual order of connection, set up helicopter
The simulation analysis model of main reducing gear, simulation analysis model can call lubricating oil level height data.
Main reducing gear lubricating system rated pressure is relatively low, belongs to low-pressure system.Main reducing gear cast inside pipeline and outside
Influence of the connecting line flow resistance to lubricating system is larger, needs to consider shadow of the pipeline parameter to lubricating system in detail in simulation analysis
Ring.
The Helicopter Main Reducer lubricating system dynamic simulation analysis method that the present embodiment is provided, by moistening to main reducing gear
Sliding each component of system and part characteristic carry out abstract and parametrization, according to abstract and parametrization component and each first device
The actual order of connection of part, sets up main reducing gear Lubrication System Simulation Analysis model.The Helicopter Main that the present embodiment is provided slows down
Device lubricating system dynamic simulation analysis method, using the attitude angle and acceleration of reading as according to the liquid level normal vector calculated, is surveyed
The lubricating oil oil level of the lubricating oil gone out in liquid level, and lubricating oil oil level is called, the simulation analysis model of main reducing gear lubricating system is set up, from
And the influence of attitude angle and acceleration to oil level is considered during to lubricating system dynamic simulation, closer to actual conditions.
Preferably, as shown in fig. 6, the Helicopter Main Reducer lubricating system dynamic simulation analysis side that the present embodiment is provided
Method, step S500 includes：
Step S510, the flight parameter and corresponding oil sump lubricating oil level height data for reading Helicopter Main Reducer.
Because system mode changes, it is necessary to be calculated in each time changing simulation parameter continuous.Use
Vbscript (Visual Basic Script, Visual Basic scripts) carries out secondary development to Flowmaster, from
(yaw angle, the angle of pitch, roll angle, body longitudinal axis acceleration, body lateral-axis acceleration, body normal direction add dynamic reading flight parameter
Speed etc.) and corresponding oil sump lubricating oil level height data.
Step S520, setting emulation and boundary condition parameter in simulation analysis model, calculating each moment, respectively lubrication is pressed
Power and flow.
Emulation and boundary condition parameter (oil temperature, atmospheric pressure, atmospheric temperature and side are set in simulation analysis model
Opening of road valve etc.) simulation result (such as each injection differential pressure, the flow, ring at each moment are constantly calculated by simulation flow afterwards
Shape cavity pressure, oil pump outlet pressure, flow, liquid level etc.).
Each moment that step S530, basis are calculated respectively lubricates point pressure and flow, updates the knot of the real-time lubricating oil amount of oil sump
Really.
According to the simulation result calculated, lubricating oil amount result is updated, for being applied in simulation calculation next time.And one
It is straight to be carried out in each lubrication point pressure that lubricating oil oil level is calculated and simulation calculation goes out with iteration in flow, until terminating emulation.Finally
Simulation result everywhere (pressure, flow etc.) can be exported and stored to local computer.
The Helicopter Main Reducer lubricating system dynamic simulation analysis method that the present embodiment is provided, by reading Helicopter Main
Decelerator flight parameter and corresponding oil sump lubricating oil level height data, set emulation and perimeter strip in simulation analysis model
Part parameter, calculates each lubrication point pressure of each moment and flow；Point pressure and flow are respectively lubricated according to each moment calculated, updated
The result of the real-time lubricating oil amount of oil sump.The Helicopter Main Reducer lubricating system dynamic simulation analysis method that the present embodiment is provided, is adopted
With secondary development, circulation emulation and the automatic transmission and read-write of data flow are realized, simulation efficiency is greatly improved.
Preferably, as shown in fig. 7, the present invention also provides a kind of Helicopter Main Reducer lubricating system dynamic simulation analysis dress
Put, applied in terminal, Helicopter Main Reducer lubricating system dynamic simulation analysis device includes：Extraction module 10, for carrying
The oil sump 3-D geometric model of Helicopter Main Reducer is taken, the distribution space of lubricating oil is simulated in oil sump 3-D geometric model；The
One computing module 20, for reading flight parameter of the Helicopter Main Reducer under state of flight, calculates flight parameter effect
The corresponding liquid level normal vector of the liquid level that is formed when lubricating oil；Second computing module 30, with the level surface method vector sum oil calculated
The real-time lubricating oil amount in pond is constraints, calculates the lubricating oil level height data of the lubricating oil in oil sump 3-D geometric model；Set up
Module 40, carries out abstract and parametrization, and build lubricating system ginseng for the component to Helicopter Main Reducer lubricating system
Numberization simulation analysis model, simulation analysis model reads lubricating oil level height data in real time；Acquisition module 50, for setting emulation
With boundary condition parameter, simulation analysis obtain each oil site pressure distribution and assignment of traffic in lubricating system.
The master of Helicopter Main Reducer lubricating system is subtracted extraction module 10 into oil sump and pipeline inner chamber is converted into 3D solid；
Remove each driving member entity and bearing member entity in 3D solid to be taken up space, oil sump 3-D geometric model is obtained, in oil sump three
Tie up the distribution space that lubricating oil is simulated in geometrical model.
First computing module 20 reads the flight parameter of Helicopter Main Reducer, and according to the flight parameter of reading, calculates
Go out flight parameter and act on the corresponding liquid level normal vector of the liquid level formed during lubricating oil.Wherein, flight parameter is classified by type, can
It is divided into posture angular dimensions and acceleration parameter etc..In the present embodiment, by calculating the flight parameter list of each type respectively
Solely act on the corresponding liquid level normal vector of the liquid level formed during lubricating oil, and by the flight parameter of each type calculated respectively
Act solely on the corresponding liquid level normal vector of the liquid level formed during lubricating oil to be added, obtain whole flight parameter and act on cunning
The corresponding liquid level normal vector of the liquid level that is formed when oily.
Second computing module 30 is using the real-time lubricating oil amount of level surface method vector sum oil sump that calculates as constraints, in CATIA
Middle carry out secondary development, the lubricating oil oil level of the lubricating oil in oil sump 3-D geometric model is calculated using dichotomy.
Set up the component and part characteristic that module 40 lubricated helicopter reducer and carry out abstract and parametrization, and root
According to the lubricating oil oil level calculated, the emulation point of helicopter reducer lubricating system is set up in Flowmaster simulation analysis softwares
Analyse model.
Acquisition module 50 sets emulation analysis parameter and boundary condition, reads lubricating oil oil level, and simulation analysis obtain main deceleration
The pressure and flow of each oil site in device lubricating system.
The Helicopter Main Reducer lubricating system dynamic simulation analysis device that the present embodiment is provided, it is dynamically imitative to lubricating system
Influence of the flight parameter to oil level is considered when true, closer to actual conditions；And it can emulate and obtain lubricating system when whole
Between performance in course.The Helicopter Main Reducer lubricating system dynamic simulation analysis device that the present embodiment is provided, simulation result
It is small with measured value error, it can obtain the performance parameters such as pressure and flow in the whole time history of decelerator lubricating system.
Preferably, as shown in figure 8, the Helicopter Main Reducer lubricating system dynamic simulation analysis dress that the present embodiment is provided
Put, the flight parameter of 3D solid includes three attitude angles and three directional accelerations, and the first computing module 20 includes：First meter
Unit 21 is calculated, corresponding first list of the liquid level that lubricating oil is formed when calculating three attitude angle independent roles for being constrained by geometrical relationship
Position normal vector；Second computing unit 22, the liquid level of lubricating oil formation is corresponding during for calculating three directional acceleration independent roles
Second unit normal vector；Acquiring unit 23, according to the first unit normal vector and the second unit normal vector calculated, obtains liquid level
Normal vector.
As shown in figure 3, the first computing unit 21 reads three attitude angles in flight parameter, constrained and calculated by geometrical relationship
The liquid level corresponding first unit normal vector V of lubricating oil formation during three attitude angle independent roles1.Wherein, three attitude angles include
Angle of pitch α, yaw angle β, roll angle γ.n1x、n1y、n1zRespectively the first unit normal vector V1List in x-axis, y-axis and z-axis
Position normal vector.
Second computing unit 22 reads three directional accelerations in flight parameter, calculates three directional accelerations and individually makees
The corresponding second unit normal vector V of liquid level of used time lubricating oil formation2.Wherein, three directional accelerations include body longitudinal angle speed
Spend ax, the horizontal angular speed a of bodyyWith body normal direction angular speed az。
Acquiring unit 23 is according to the first unit normal vector V calculated1With the second unit normal vector V2, calculate level surface method
Vectorial V, liquid level normal vector V are the first unit normal vector V1With the second unit normal vector V2Vector.
The Helicopter Main Reducer lubricating system dynamic simulation analysis device that the present embodiment is provided, is constrained by geometrical relationship and counted
Liquid level corresponding first unit normal vector of lubricating oil formation when calculating three attitude angle independent roles；Calculate three directional acceleration lists
Corresponding second unit normal vector of liquid level that solely lubricating oil is formed during effect；It is single according to the first unit normal vector calculated and second
Position normal vector, obtains liquid level normal vector.The Helicopter Main Reducer lubricating system dynamic simulation analysis device that the present embodiment is provided,
The influence of attitude angle and acceleration to oil level is considered during to lubricating system dynamic simulation, closer to actual conditions.
Preferably, as shown in figure 9, the Helicopter Main Reducer lubricating system dynamic simulation analysis dress that the present embodiment is provided
Put, the second computing module 30 includes：Cutter unit 31, for adjusting liquid level normal level using dichotomy, progressively cuts
Oil sump 3-D geometric model；Measuring unit 32, the oil sump pond body body for solving the plane institute envelope constituted with liquid level normal
Product, if the difference of oil sump tank volume and the real-time lubricating oil amount of oil sump is less than default calculating allowable error, the plane drawn
For liquid level, the lubricating oil oil level of the lubricating oil in liquid level is measured.
Level surface method vector sum oil sump real-time lubricating oil amount of the cutter unit 31 to calculate is entered as constraints in CATIA
Row secondary development, liquid level normal level is adjusted using dichotomy, progressively cuts oil sump 3-D geometric model.
When the oil sump tank volume of the plane institute envelope constituted with liquid level normal is equal with the real-time lubricating oil amount of oil sump, this puts down
Face is just liquid level.Measuring unit 32 solves the volume function of entity using being carried in CATIA, and plane is adjusted by using dichotomy
Height progressively cuts oil sump 3-D geometric model, solves the oil sump tank volume of the plane institute envelope constituted with liquid level normal, directly
When being less than default calculating allowable error ε to oil sump tank volume and the difference of the real-time lubricating oil amount of oil sump, then the plane drawn
For real-time liquid level, the lubricating oil oil level of the lubricating oil in liquid level is measured so that Flowmaster is called.
The Helicopter Main Reducer lubricating system dynamic simulation analysis device that the present embodiment is provided, liquid is adjusted using dichotomy
Face plane normal height, progressively cuts oil sump 3-D geometric model；Solve the oil of the plane institute envelope constituted with liquid level normal
Pond tank volume, if the difference of oil sump tank volume and the real-time lubricating oil amount of oil sump is less than default calculating allowable error,
The plane gone out is liquid level, measures the lubricating oil oil level of the lubricating oil in liquid level.The Helicopter Main Reducer lube system that the present embodiment is provided
System dynamic simulation analysis device, using the attitude angle and acceleration of reading as according to the liquid level normal vector calculated, is measured in liquid level
Lubricating oil lubricating oil oil level, so as to consider the influence of attitude angle and acceleration to oil level during to lubricating system dynamic simulation, more
Close to actual conditions.
Preferably, as shown in Figure 10, the Helicopter Main Reducer lubricating system dynamic simulation analysis dress that the present embodiment is provided
Put, setting up module 40 includes：Abstraction unit 41, for each component and the part characteristic progress to main reducing gear lubricating system
Abstract and parametrization；Unit 42 is set up, for adjusting the actual connection according to the component and each component of abstract and parametrization suitable
Sequence, sets up the simulation analysis model of Helicopter Main Reducer, and simulation analysis model can call lubricating oil level height data.
41 pairs of each components and part characteristic to main reducing gear lubricating system of abstraction unit carry out abstract and parametrization,
Wherein, component mainly includes nozzle, straight tube, bend pipe, fuel tank, oil pump, pressure regulator valve, oil filter and radiator etc., component
Characteristic mainly includes nozzle bore, nozzle hole number, pipeline latus rectum, pipeline type of attachment, fuel tank shape, inlet port position, lubricating oil
Pump discharge-pressure characteristic, pressure regulator valve pressure setting characteristic, oil filter flow resistance characteristic, radiator flow resistance and flow, temperature characterisitic
Deng.
Unit 42 is set up according to abstract and parametrization component and each component the actual order of connection, helicopter is set up
The simulation analysis model of main reducing gear, simulation analysis model can call lubricating oil level height data.Wherein, main reducing gear lube system
Rated pressure of uniting is relatively low, belongs to low-pressure system.Main reducing gear cast inside pipeline and external connection pipeline flow resistance are to lubricating system
Influence it is larger, need to consider influence of the pipeline parameter to lubricating system in detail in simulation analysis.
The Helicopter Main Reducer lubricating system dynamic simulation analysis device that the present embodiment is provided to main reducing gear by moistening
Sliding each component of system and part characteristic carry out abstract and parametrization, according to abstract and parametrization component and each first device
The actual order of connection of part, sets up main reducing gear Lubrication System Simulation Analysis model.The Helicopter Main that the present embodiment is provided slows down
Device lubricating system dynamic simulation analysis device, using the attitude angle and acceleration of reading as according to the liquid level normal vector calculated, is surveyed
The lubricating oil oil level of the lubricating oil gone out in liquid level, and lubricating oil oil level is called, the simulation analysis model of main reducing gear lubricating system is set up, from
And the influence of attitude angle and acceleration to oil level is considered during to lubricating system dynamic simulation, closer to actual conditions.
Preferably, as shown in figure 11, the Helicopter Main Reducer lubricating system dynamic simulation analysis dress that the present embodiment is provided
Put, acquisition module 50 includes：Reading unit 51, flight parameter and corresponding oil sump for reading Helicopter Main Reducer are slided
Oily level height data；3rd computing unit 52, sets emulation and boundary condition parameter in simulation analysis model, when calculating each
Carve each lubrication point pressure and flow；Updating block 53, for respectively lubricating point pressure and flow according to each moment calculated, updates
The result of the real-time lubricating oil amount of oil sump.
Because system mode changes, it is necessary to be calculated in each time changing simulation parameter continuous.Reading unit 51
Secondary open is carried out to Flowmaster using Vbscript (Visual Basic Script, Visual Basic scripts)
Hair, reads flight parameter (yaw angle, the angle of pitch, roll angle, body longitudinal axis acceleration, body lateral-axis acceleration, body method automatically
To acceleration etc.) and corresponding oil sump lubricating oil level height data.
3rd computing unit 52 sets emulation and boundary condition parameter (oil temperature, atmospheric pressure in simulation analysis model
Opening of power, atmospheric temperature and bypass valve etc.) simulation result (such as each nozzle at each moment is constantly calculated by simulation flow afterwards
Pressure drop, flow, annular pressure cavity, oil pump outlet pressure, flow, liquid level etc.).
Updating block 53 updates lubricating oil amount result, for entering in simulation calculation next time according to the simulation result calculated
Row application.And carried out always in each lubrication point pressure that lubricating oil oil level is calculated and simulation calculation goes out with iteration in flow, until knot
Beam is emulated.Finally simulation result everywhere (pressure, flow etc.) can be exported and stored to local computer.
The Helicopter Main Reducer lubricating system dynamic simulation analysis device that the present embodiment is provided, Helicopter Main Reducer flies
Row parameter and corresponding oil sump lubricating oil level height data, set emulation and boundary condition parameter in simulation analysis model,
Calculate each lubrication point pressure of each moment and flow；Point pressure and flow are respectively lubricated according to each moment calculated, oil sump is updated real
When lubricating oil amount result.The Helicopter Main Reducer lubricating system dynamic simulation analysis device that the present embodiment is provided, using secondary
Exploitation, realizes circulation emulation and the automatic transmission and read-write of data flow, greatly improves simulation efficiency.
The preferred embodiments of the present invention are the foregoing is only, are not intended to limit the invention, for the skill of this area
For art personnel, the present invention can have various modifications and variations.Within the spirit and principles of the invention, that is made any repaiies
Change, equivalent substitution, improvement etc., should be included in the scope of the protection.
Claims (10)
1. a kind of Helicopter Main Reducer lubricating system dynamic simulation analysis method, it is characterised in that including step：
The oil sump 3-D geometric model of Helicopter Main Reducer is extracted, point of lubricating oil is simulated in the oil sump 3-D geometric model
Cloth space；
The flight parameter of Helicopter Main Reducer is read, the flight parameter is calculated and acts on the liquid level formed during the lubricating oil
Corresponding liquid level normal vector；
The real-time lubricating oil amount of the level surface method vector sum oil sump to calculate calculates the oil sump three-dimensional geometry as constraints
The lubricating oil level height data of the lubricating oil in model；
Abstract and parametrization is carried out to the component of the Helicopter Main Reducer lubricating system, and builds lubricating system parametrization
Simulation analysis model, the simulation analysis model reads the lubricating oil level height data in real time；
Emulation and boundary condition parameter are set, and simulation analysis obtain each oil site pressure distribution and assignment of traffic in lubricating system.
2. Helicopter Main Reducer lubricating system dynamic simulation analysis method according to claim 1, it is characterised in that
The flight parameter of the Helicopter Main Reducer includes three attitude angles and three directional accelerations, and the reading is described straight
The flight parameter of owner's decelerator is risen, the flight parameter is calculated and acts on the corresponding liquid of the liquid level formed during the lubricating oil
The step of face normal vector, includes：
Corresponding first list of liquid level that the lubricating oil is formed when calculating three attitude angle independent roles is constrained by geometrical relationship
Position normal vector；
Calculate corresponding second unit normal vector of liquid level of lubricating oil formation during three directional acceleration independent roles；
According to first unit normal vector and second unit normal vector calculated, liquid level normal vector is obtained.
3. Helicopter Main Reducer lubricating system dynamic simulation analysis method according to claim 2, it is characterised in that
The real-time lubricating oil amount of the level surface method vector sum oil sump to calculate calculates the oil sump three-dimensional as constraints
The step of lubricating oil level height data of the lubricating oil in geometrical model, includes：
Liquid level normal level is adjusted using dichotomy, the oil sump 3-D geometric model is progressively cut；
The oil sump tank volume of the plane institute envelope constituted with liquid level normal is solved, if the oil sump tank volume and the oil
When the difference of the real-time lubricating oil amount in pond is less than default calculating allowable error, then the plane drawn is liquid level, measures the liquid
The lubricating oil level height data of the lubricating oil in face.
4. Helicopter Main Reducer lubricating system dynamic simulation analysis method according to claim 3, it is characterised in that
The component to the Helicopter Main Reducer lubricating system carries out abstract and parametrization, and builds lubricating system ginseng
The step of numberization simulation analysis model, includes：
Component and part characteristic to the Helicopter Main Reducer lubricating system carry out abstract and parametrization；
According to abstract and parametrization component and each component the actual order of connection, the Helicopter Main Reducer is set up
Simulation analysis model, the simulation analysis model can call lubricating oil level height data.
5. Helicopter Main Reducer lubricating system dynamic simulation analysis method according to claim 4, it is characterised in that
It is described according to the simulation analysis model, the step of obtaining in lubricating system each oil site pressure distribution with assignment of traffic is wrapped
Include：
Read the flight parameter and corresponding oil sump lubricating oil level height data of the Helicopter Main Reducer；
Emulation and boundary condition parameter are set in the simulation analysis model, each lubrication point pressure of each moment and flow is calculated；
Point pressure and flow are respectively lubricated according to each moment calculated, the result of the real-time lubricating oil amount of oil sump is updated.
6. a kind of Helicopter Main Reducer lubricating system dynamic simulation analysis device, applied in terminal, it is characterised in that described
Helicopter Main Reducer lubricating system dynamic simulation analysis device includes：
Extraction module (10), the oil sump 3-D geometric model for extracting Helicopter Main Reducer, in the oil sump three-dimensional geometry
The distribution space of lubricating oil is simulated in model；
First computing module (20), the flight parameter for reading the Helicopter Main Reducer, calculates the flight parameter
Act on the corresponding liquid level normal vector of the liquid level formed during the lubricating oil；
Second computing module (30), the real-time lubricating oil amount of the level surface method vector sum oil sump to calculate is calculated as constraints
The lubricating oil level height data of the lubricating oil gone out in the oil sump 3-D geometric model；
Module (40) is set up, abstract and parametrization is carried out for the component to the Helicopter Main Reducer lubricating system, and
Lubricating system parametric simulation analysis model is built, the simulation analysis model reads the lubricating oil level height data in real time；
Acquisition module (50), for setting emulation and boundary condition parameter, simulation analysis obtain each lubrication in lubricating system and pressed
Power is distributed and assignment of traffic.
7. Helicopter Main Reducer lubricating system dynamic simulation analysis device according to claim 6, it is characterised in that
The flight parameter of the Helicopter Main Reducer includes three attitude angles and three directional accelerations, and described first calculates mould
Block (20) includes：
First computing unit (21), lubricating oil shape during for calculating three attitude angle independent roles by geometrical relationship constraint
Into corresponding first unit normal vector of liquid level；
Second computing unit (22), the liquid level pair for calculating lubricating oil formation during three directional acceleration independent roles
The second unit normal vector answered；
Acquiring unit (23), according to first unit normal vector and second unit normal vector calculated, obtains liquid level
Normal vector.
8. Helicopter Main Reducer lubricating system dynamic simulation analysis device according to claim 7, it is characterised in that
Second computing module (30) includes：
Cutter unit (31), for adjusting liquid level normal level using dichotomy, progressively cuts the oil sump three-dimensional geometry
Model；
Measuring unit (32), the oil sump tank volume for solving the plane institute envelope constituted with liquid level normal, if the oil
When the difference of pond tank volume and the real-time lubricating oil amount of the oil sump is less than default calculating allowable error, then the plane drawn
For liquid level, the lubricating oil level height data of the lubricating oil in the liquid level are measured.
9. Helicopter Main Reducer lubricating system dynamic simulation analysis device according to claim 8, it is characterised in that
The module (40) of setting up includes：
Abstraction unit (41), it is abstract for being carried out to each component of Helicopter Main Reducer lubricating system and part characteristic
And parametrization, set up the simulation analysis model of the Helicopter Main Reducer lubricating system；
Unit (42) is set up, for according to abstract and parametrization component and each component the actual order of connection, setting up institute
The simulation analysis model of Helicopter Main Reducer is stated, the simulation analysis model can call lubricating oil level height data.
10. Helicopter Main Reducer lubricating system dynamic simulation analysis device according to claim 9, it is characterised in that
The acquisition module (50) includes：
Reading unit (51), flight parameter and corresponding oil sump lubricating oil level height number for reading Helicopter Main Reducer
According to；
3rd computing unit (52), for setting emulation and boundary condition parameter in the simulation analysis model, when calculating each
Carve each lubrication point pressure and flow；
Updating block (53), for respectively lubricating point pressure and flow according to each moment calculated, updates the oil sump real
When lubricating oil amount result.
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