CN109543243A - Carrier-borne aircraft based on ADAMS blocks warship kinetics simulation analysis method - Google Patents
Carrier-borne aircraft based on ADAMS blocks warship kinetics simulation analysis method Download PDFInfo
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Abstract
The invention discloses a kind of carrier-borne aircrafts based on ADAMS to block warship kinetics simulation analysis method, comprising steps of establishing carrier-borne aircraft finite element model and calculating and export corresponding modal neutral file；Undercarriage and arrester hook model are simplified and save as general format；Merge the new modal neutral file of the node aerodynamic loading file generated of the modal neutral file and carrier-borne aircraft in ADAMS；By new modal neutral file, undercarriage and block hook part, ground file and tire file import assembly in ADAMS dynamics simulation environment and obtain the Rigid-flexible Coupling Dynamics simulation model that description carrier-borne aircraft blocks warship；Setting carrier-borne aircraft primary condition and boundary condition emulate to obtain dynamic response result.The present invention ensure that the accuracy that airframe structure dynamic response calculates, realize the unification of high efficiency and accuracy, to carrier-borne aircraft totality and analysis for dynamic strength and great significance for design, can be obviously shortened the lead time closer to true warship state.
Description
Technical field
The invention belongs to aircraft structure strength design fields, and in particular to CATIA, Patran, Nastran, Hypermesh
Warship overall process dynamical simulation analysis method is blocked with the carrier-borne aircraft of ADAMS, for instructing aircraft especially carrier-borne aircraft structure strong
The design of degree.
Technical background
Carrier-borne aircraft is the open sea aeroplane using aircraft carrier as base, is the main attacking and defending weapon of aircraft carrier.Aircraft carrier
Deck space limitations, it is desirable that carrier-borne aircraft is with shorter ground run distance warship.Carrier-borne aircraft block process load is big, acceleration is big, when
Between it is short, while being influenced by conditions such as aircraft carrier movement, flow perturbations, there is the complicated multidisciplinary Dynamics Coupling of strong nonlinearity and ask
Topic.Carrier-borne aircraft blocks accurate dynamic performance, the optimization machine established to further investigation carrier-borne aircraft fuselage of landing dynamic response model
Body structure and materials'use etc. have great importance.Therefore the dynamic response analysis of airframe structure becomes carrier-borne aircraft and designed
One of key technology in journey.
Studies in China person is mainly had using dynamic method at present:
1, carrier-borne aircraft dynamics problem is divided into the dynamics problem for studying several subsystems, that is, studies arrester hook dynamics, block
The carrier-borne aircrafts subsystem problems such as rope dynamics, undercarriage dynamics are hindered, airframe structure and subsystems phase mutual coupling are not accounted for
The influence of conjunction.
2, fuselage is primarily focused on into the mechanical movement, whole of each subsystem of aircraft as (non-deformable) processing of rigid body
Body posture (such as landing track) and load response (undercarriage and arrester hook buffer cushion effect).
3, fuselage is locally regarded to flexible body processing, calculates and blocks during warship the dynamic of flexible body in specific short time period
Response, fuselage is most of still to be handled as rigid body.
By the research to the above method, summarize disadvantage is that:
(1) carrier-borne aircraft system is divided into several subsystems and excessive idealization simplification is carried out to practical problem, it is whole to be unable to get fuselage
The dynamic response result of body structure.
(2) method 1 and method 2 do not account for the coupling that fuselage is integrally used as the rigid bodies such as flexible body and undercarriage,
Have ignored absorption and dissipation effect of the airframe structure to the energy that impact generates during blocking.
(3) method 3 only calculates the local location dynamic response intensity blocked during warship in specific short time period,
The full fuselage flexible body dynamic response blocked in warship overall process can not be calculated.
(4) three kinds of methods do not account for aerodynamic loading during blocking warship to the influence of carrier-borne aircraft.
In conclusion currently without a kind of hard and soft coupling for considering flexible airframe structure Yu carrier-borne aircraft rigidity subsystem simultaneously
The coupling of conjunction and aerodynamic loading and flexible airframe structure, to realize that carrier-borne aircraft blocks warship overall process Dynamics Simulation Analysis
Method.
Summary of the invention
In view of the deficiencies of the prior art, the present invention is intended to provide a kind of carrier-borne aircraft based on ADAMS blocks warship dynamics
Simulating analysis, at the same consider flexible airframe structure and carrier-borne aircraft rigidity subsystem Coupled Rigid-flexible and aerodynamic loading with
The coupling of flexible airframe structure is blocked the dynamic (dynamical) accurate description of warship to carrier-borne aircraft to realize, is designed for carrier-borne aircraft structure, machine
The wing composite plys design and fuselage materials'use provide suggestion, while improve computational efficiency shorten carrier-borne aircraft design grind
The iteration cycle of system.
To achieve the goals above, the present invention adopts the following technical scheme:
Carrier-borne aircraft based on ADAMS blocks warship kinetics simulation analysis method, comprising the following steps:
Step 1: establishing carrier-borne aircraft finite element model and calculating its mode, its corresponding modal neutral file is exported；
Step 2: to undercarriage and arrester hook model simplified and create each component center of gravity and junction hard spot after will be each
Component saves as general format；
Step 3: going out the aerodynamic loading of carrier-borne aircraft according to hydrokinetics calculation and being write by format and generate node aerodynamic loading
File, merges the modal neutral file in ADAMS and node aerodynamic loading file generated includes the aerodynamic loading of distribution
New modal neutral file；
Step 4: by the undercarriage handled in the new modal neutral file of third step generation, second step and blocking hook portion
Assembly obtains description carrier-borne aircraft and blocks the rigid of warship in part, ground file and tire file importing ADAMS dynamics simulation environment
Soft Coupled Dynamics simulation model；
Step 5: blocking the primary condition and boundary condition of warship requirement of actual working condition setting carrier-borne aircraft according to carrier-borne aircraft, pass through
The Rigid-flexible Coupling Dynamics simulation model, which emulates to obtain carrier-borne aircraft, blocks warship coasting distance, airframe structure ess-strain and packet
Include the dynamic response result of the mechanical structure of undercarriage.
Preferably, the first step specifically includes:
Carrier-borne aircraft three-dimensional entity model is established in 3 d modeling software CATIA environment, and establishes the whole of carrier-borne aircraft in CATIA
Body structure；
Finite element front and back processing software is imported into after carrier-borne aircraft three-dimensional entity model in CATIA is saved as general format and is led to
It crosses in the processing software Patran of finite element front and back；
To each component grid division, assembly and free boundary is defined about in processing software Patran environment before and after the finite element
Beam makes fuselage be in a free state；
Then define processing software Patran and ADAMS before and after finite element docks parameter, transformational relation, mode including unit
Order, ess-strain information；
Finally, finite element solving device software Nastran is submitted to carry out model analysis calculating, corresponding modal neutral file is generated.
Preferably, the second step specifically includes:
Undercarriage and arrester hook model are simplified in CATIA environment first, deletion does not have influential complexity to kinematics
Feature；
Then all parts of undercarriage and arrester hook model are saved as into general format export, and imports processing before and after finite element
Software Hypermesh；
Processing software Hypermesh is after the center of gravity of all parts and junction creation hard spot by each portion before and after the finite element
Part saves as general format.
Preferably, the 4th step specifically includes:
By the undercarriage handled in the new modal neutral file of third step generation, second step and block hook part importing
In ADAMS dynamics simulation environment, set environment parameter, Rigid Mass and rotary inertia parameter；
Then ground file is imported in ADAMS and tire document creation carrier-borne aircraft blocks alighting run runway and tire；
Between last set each rigid body kinematic pair type and apply kinematic pair assemble description carrier-borne aircraft blocks the rigid of warship
Soft Coupled Dynamics simulation model.
It preferably, include diameter of tyres in tire file described in third step, width, curvature and vertical reaction are with tire
Decrement change curve parameter.
Preferably, the primary condition of carrier-borne aircraft described in the 5th step and boundary condition include aircraft aerodynamic loading, block power,
Undercarriage cushion effect, motor power and arrester hook system buffer power.
Preferably, the aircraft aerodynamic loading is the distributed force being distributed on each finite elements node, is divided into pneumatic liter
Power, aerodynamic drag and pitching moment；The power of blocking is that power time-history curves are blocked in the actual measurement of III type arresting gear of MK7-.
Preferably, the undercarriage cushion effect and arrester hook system buffer power are decomposed into air bullet relevant to compression travel
Spring force, oil liquid damping force relevant to compression speed and structure restraint relevant with structure stroke maximum value.
Preferably, the air spring force, oil liquid damping force and structure restraint fall ram-jolt for undercarriage and test measured data.
Preferably, carrier-borne aircraft actual condition described in the 5th step includes different pitch attitude angle, different initial velocities, no
With subsidence velocity, different hook first angles and different block power application time.
Compared with prior art, the beneficial effects of the invention are that:
1. CATIA, Patran, Nastran, Hypermesh and ADAMS is used in combination in this method, while considering flexible fuselage
The coupling of the Coupled Rigid-flexible and aerodynamic loading of structure and carrier-borne aircraft rigidity subsystem and flexible airframe structure establishes and reality
Operating condition is close, or even the carrier-borne aircraft of more extreme warship condition blocks warship physical model, realizes and blocks to carrier-borne aircraft
The dynamic (dynamical) accurate description of warship, can be obtained carrier-borne aircraft block warship coasting distance, airframe structure ess-strain and undercarriage etc. its
The dynamic response result of his mechanical structure.For the design of carrier-borne aircraft structure, the design of wing composite plys and fuselage materials'use
It provides and suggests.
2. this method, which uses mode superposition method, carries out accurate description to flexible deformation and elastic stress strain, avoid straight
It connects and analyzes bring large-scale calculations using the methods of finite element, not only ensure that computational accuracy but also greatly improve calculating effect
Rate to block carrier-borne aircraft warship whole process simulation and to the full fuselage fatigue resistance during this, accelerates warship
The iteration speed of carrier aircraft design process.
3. warp and dynamic response ground test result comparative analysis, emulation mode acquired results provided by the invention accurately may be used
It leans on, solves many limitations of the prior art, the analysis of warship process dynamic response and fatigue resistance design can be blocked for carrier-borne aircraft
Important reference is provided.
Detailed description of the invention
Fig. 1 is the flow chart of the embodiment of the present invention.
Fig. 2 is carrier-borne aircraft many-body dynamics schematic diagram.
Fig. 3 is to block Landing gear force curve.
Fig. 4 is aerodynamic loading coefficient curve.
Fig. 5 is node aerodynamic loading file.
Fig. 6 is that flextk module synthesizes new mnf file.
Fig. 7 is mechanics of tire performance curve.
Fig. 8 is to overload to be distributed along fuselage.
Fig. 9 is fuselage stress curve.
Figure 10 is wing strain curve.
Specific embodiment
Below with reference to attached drawing, the invention will be further described, it should be noted that the present embodiment is with this technology side
Premised on case, the detailed implementation method and specific operation process are given, but protection scope of the present invention is not limited to this reality
Apply example.
As shown in Figure 1, the carrier-borne aircraft based on ADAMS blocks warship kinetics simulation analysis method, comprising the following steps:
Step 1: establishing carrier-borne aircraft finite element model and calculating its mode, its corresponding modal neutral file (mnf text is exported
Part)；
Step 2: to undercarriage and arrester hook model simplified and create each component center of gravity and junction hard spot after will be each
Component saves as general format；
Step 3: calculating the aerodynamic loading of carrier-borne aircraft according to fluid dynamics (CFD) and being write by format and generate node gas
Dynamic loading file calls the flextk module merging modal neutral file and node pneumatically to carry in the command interface of ADAMS
Lotus file generated includes the new modal neutral file (mnf file) of the aerodynamic loading of distribution；
Step 4: by the undercarriage handled in the new modal neutral file of third step generation, second step and blocking hook portion
It assembles to describe carrier-borne aircraft in part, ground file and tire file importing ADAMS dynamics simulation environment and blocks the hard and soft of warship
Coupled Dynamics simulation model；
Step 5: blocking the primary condition and boundary condition of warship requirement of actual working condition setting carrier-borne aircraft according to carrier-borne aircraft, pass through
The Rigid-flexible Coupling Dynamics simulation model, which emulates to obtain carrier-borne aircraft, blocks warship coasting distance, airframe structure ess-strain and packet
Include the dynamic response result of the mechanical structure of undercarriage.
Specifically, the first step specifically includes:
Carrier-borne aircraft three-dimensional entity model is established in 3 d modeling software CATIA environment, and establishes the whole of carrier-borne aircraft in CATIA
Body structure；
Finite element front and back processing software is imported into after carrier-borne aircraft three-dimensional entity model in CATIA is saved as general format and is led to
It crosses in the processing software Patran of finite element front and back；
To each component grid division, assembly and free boundary is defined about in processing software Patran environment before and after the finite element
Beam makes fuselage be in a free state；
Then define processing software Patran and ADAMS before and after finite element docks parameter, transformational relation, mode including unit
Order, ess-strain information；
Finally, finite element solving device software Nastran is submitted to carry out model analysis calculating, corresponding modal neutral file is generated.
Specifically, the second step specifically includes:
Undercarriage and arrester hook model are simplified in CATIA environment first, deletion does not have influential complexity to kinematics
Feature；
Then all parts of undercarriage and arrester hook model are saved as into general format export, and imports processing before and after finite element
Software Hypermesh；
Processing software Hypermesh is after the center of gravity of all parts and junction creation hard spot by each portion before and after the finite element
Part saves as general format.
Specifically, the 4th step specifically includes:
By the undercarriage handled in the new modal neutral file of third step generation, second step and block hook part importing
In ADAMS dynamics simulation environment, set environment parameter, Rigid Mass and rotary inertia parameter；
Then ground file is imported in ADAMS and tire document creation carrier-borne aircraft blocks alighting run runway and tire；
Between last set each rigid body kinematic pair type and apply kinematic pair assemble description carrier-borne aircraft blocks the rigid of warship
Soft Coupled Dynamics simulation model.
It preferably, include diameter of tyres in tire file described in third step, width, curvature and vertical reaction are with tire
Decrement change curve parameter.
Preferably, the primary condition of carrier-borne aircraft described in the 5th step and boundary condition include aircraft aerodynamic loading, block power,
Undercarriage cushion effect, motor power and arrester hook system buffer power.
Preferably, the aircraft aerodynamic loading is the distributed force being distributed on each finite elements node, is divided into pneumatic liter
Power, aerodynamic drag and pitching moment；The power of blocking is that power time-history curves are blocked in the actual measurement of III type arresting gear of MK7-.
Preferably, the undercarriage cushion effect and arrester hook system buffer power are decomposed into air bullet relevant to compression travel
Spring force, oil liquid damping force relevant to compression speed and structure restraint relevant with structure stroke maximum value.
Preferably, the air spring force, oil liquid damping force and structure restraint fall ram-jolt for undercarriage and test measured data.
Preferably, carrier-borne aircraft actual condition described in the 5th step includes different pitch attitude angle, different initial velocities, no
With subsidence velocity, different hook first angles and different block power application time.
Advantages of the present invention can be further illustrated by following emulation:
Carrier-borne aircraft based on ADAMS is blocked into warship overall process dynamical simulation analysis method, is designed in certain model Shipborne UAV
Stage carries out simulation analysis, simplification figure as shown in Figure 2, which is flexible body, and undercarriage cushion effect blocks
Resistance hook cushion effect is decomposed into air spring force, oil liquid damping force and structure restraint.
Fig. 3, which block for the mass block of the quality such as III type arresting gear pair of MK7- and Shipborne UAV, tests resulting block
The dimensionless curve of drag measurement result.Warship Dynamics Simulation Analysis is blocked to block power progress carrier-borne aircraft shown in Fig. 3.Accurately
The force data that blocks improve Computer Simulation Efficiency and accuracy.
Fig. 4 is the dimensionless result of the aerodynamic loading parameter for the Shipborne UAV that fluid dynamics (CFD) is calculated.It is pneumatic to carry
Lotus acts on Shipborne UAV and blocks in the overall process of warship, so that emulating closer to the Shipborne UAV practical shape of warship moment
State improves the dynamic response of Landing Gear System and the accuracy of airframe structure intensity.
Fig. 5 is carrier-borne aircraft part of nodes aerodynamic loading file.What the first row " %C " symbol indicated to apply is load.Following
In data, first is classified as body nodal point number, and second is classified as aerodynamic loading direction, and third is classified as aerodynamic loading numerical value.
Fig. 6 is that flextk module synthesizes new mnf file.
Into ADAMS prompt command window, it is panel load file and the mnf being previously generated text that current directory, which is arranged,
The file of part, input order:
"ADAMS2014_x64flextkmnfloadoldmnf.mnfnewmnf.mnfqidongzaihe.txt".Wherein
ADAMS2014_x64 is ADAMS version number, and flextk is into flextk module, and oldmnf.mnf is the mnf text being previously generated
Part, newmnf.mnf are the new mnf file generated after merging, and qidongzaihe.txt is node aerodynamic loading file.
Fig. 7 is the tire compression amount-vertical load curve nondimensionalization curve obtained by tire static pressure bearing test.
Accurate tire compression amount-vertical load determines the accuracy for the contact force that Shipborne UAV and collision on the ground generate, and guarantees
Shipborne UAV blocks the reliability of warship emulation.
Fig. 8 is to be obtained by this method simulation calculation along fuselage overload distribution, it is known that carrier-borne aircraft fuselage is blocked
Power blocks power transmitting and energy attenuation.
Fig. 9 is the nondimensionalization stress time curve of the fuselage part material obtained by this method simulation calculation, can be with
Know stress of fuselage part material during carrier-borne aircraft blocks warship, and then instructs the material selection and structure of dangerous position
Design.
Figure 10 is nondimensionalization strain-time graph of the wing composite material obtained by this method simulation calculation, can
To know strain of wing composite material during carrier-borne aircraft blocks warship, so instruct wing composite material selection and
Lay up design.
In conclusion simulating analysis provided by the invention can successfully solve consider in existing simulating analysis
The problems such as dynamic response of flexible fuselage during warship, is blocked in influence of the aerodynamic loading to carrier landing and can not considering, solves
The computationally intensive problem of conventional finite element method, it is contemplated that carrier-borne aircraft blocks the effect of aerodynamic loading during warship, carrier-borne
Machine stress ensure that the accuracy that airframe structure dynamic response calculates closer to true warship state, realize high efficiency and
The unification of accuracy can be obviously shortened the lead time to carrier-borne aircraft totality and analysis for dynamic strength and great significance for design.
The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；Although referring to above-described embodiment
Invention is explained in detail, those skilled in the art should understand that;It still can be to above-mentioned each implementation
Technical solution documented by example is modified, or carries out equivalent substitute to part of technical characteristic;And these modification or
It replaces, scope described in various embodiments of the present invention technology that it does not separate the essence of the corresponding technical solution.
Claims (10)
1. the carrier-borne aircraft based on ADAMS blocks warship kinetics simulation analysis method, which comprises the following steps:
Step 1: establishing carrier-borne aircraft finite element model and calculating its mode, its corresponding modal neutral file is exported；
Step 2: to undercarriage and arrester hook model simplified and create each component center of gravity and junction hard spot after will be each
Component saves as general format；
Step 3: going out the aerodynamic loading of carrier-borne aircraft according to hydrokinetics calculation and being write by format and generate node aerodynamic loading
File, merges the modal neutral file in ADAMS and node aerodynamic loading file generated includes the aerodynamic loading of distribution
New modal neutral file；
Step 4: by the undercarriage handled in the new modal neutral file of third step generation, second step and blocking hook portion
Assembly obtains description carrier-borne aircraft and blocks the rigid of warship in part, ground file and tire file importing ADAMS dynamics simulation environment
Soft Coupled Dynamics simulation model；
Step 5: blocking the primary condition and boundary condition of warship requirement of actual working condition setting carrier-borne aircraft according to carrier-borne aircraft, pass through
The Rigid-flexible Coupling Dynamics simulation model, which emulates to obtain carrier-borne aircraft, blocks warship coasting distance, airframe structure ess-strain and packet
Include the dynamic response result of the mechanical structure of undercarriage.
2. the carrier-borne aircraft according to claim 1 based on ADAMS blocks warship kinetics simulation analysis method, feature exists
In the first step specifically includes:
Carrier-borne aircraft three-dimensional entity model is established in 3 d modeling software CATIA environment, and establishes the whole of carrier-borne aircraft in CATIA
Body structure；
Finite element front and back processing software is imported into after carrier-borne aircraft three-dimensional entity model in CATIA is saved as general format and is led to
It crosses in the processing software Patran of finite element front and back；
To each component grid division, assembly and free boundary is defined about in processing software Patran environment before and after the finite element
Beam makes fuselage be in a free state；
Then define processing software Patran and ADAMS before and after finite element docks parameter, transformational relation, mode including unit
Order, ess-strain information；
Finally, finite element solving device software Nastran is submitted to carry out model analysis calculating, corresponding modal neutral file is generated.
3. the carrier-borne aircraft according to claim 1 based on ADAMS blocks warship kinetics simulation analysis method, feature exists
In the second step specifically includes:
Undercarriage and arrester hook model are simplified in CATIA environment first, deletion does not have influential complexity to kinematics
Feature；
Then all parts of undercarriage and arrester hook model are saved as into general format export, and imports processing before and after finite element
Software Hypermesh；
Processing software Hypermesh is after the center of gravity of all parts and junction creation hard spot by each portion before and after the finite element
Part saves as general format.
4. the carrier-borne aircraft according to claim 1 based on ADAMS blocks warship kinetics simulation analysis method, feature exists
In the 4th step specifically includes:
By the undercarriage handled in the new modal neutral file of third step generation, second step and block hook part importing
In ADAMS dynamics simulation environment, set environment parameter, Rigid Mass and rotary inertia parameter；
Then ground file is imported in ADAMS and tire document creation carrier-borne aircraft blocks alighting run runway and tire；
Between last set each rigid body kinematic pair type and apply kinematic pair assemble description carrier-borne aircraft blocks the rigid of warship
Soft Coupled Dynamics simulation model.
5. the carrier-borne aircraft according to claim 1 based on ADAMS blocks warship kinetics simulation analysis method, feature exists
In bent with the variation of tire compression amount comprising diameter of tyres, width, curvature and vertical reaction in tire file described in third step
Line parameter.
6. the carrier-borne aircraft according to claim 1 based on ADAMS blocks warship kinetics simulation analysis method, feature exists
In the primary condition and boundary condition of carrier-borne aircraft described in the 5th step include aircraft aerodynamic loading, block power, undercarriage buffering
Power, motor power and arrester hook system buffer power.
7. the carrier-borne aircraft according to claim 6 based on ADAMS blocks warship kinetics simulation analysis method, feature exists
In, the aircraft aerodynamic loading is the distributed force being distributed on each finite elements node, be divided into aerodynamic lift, aerodynamic drag and
Pitching moment；The power of blocking is that power time-history curves are blocked in the actual measurement of III type arresting gear of MK7-.
8. the carrier-borne aircraft according to claim 6 based on ADAMS blocks warship kinetics simulation analysis method, feature exists
In the undercarriage cushion effect and arrester hook system buffer power are decomposed into air spring force relevant to compression travel and compression
The relevant oil liquid damping force of speed and structure restraint relevant to structure stroke maximum value.
9. the carrier-borne aircraft according to claim 8 based on ADAMS blocks warship kinetics simulation analysis method, feature exists
In the air spring force, oil liquid damping force and structure restraint fall ram-jolt for undercarriage and test measured data.
10. the carrier-borne aircraft according to claim 1 based on ADAMS blocks warship kinetics simulation analysis method, feature
It is, carrier-borne aircraft actual condition described in the 5th step includes different pitch attitude angles, different initial velocities, different lower settling velocities
Degree, different hook first angles and different blocks power application time.
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