CN107844643A - Guided missile presses heart mutation analysis method under a kind of missile airframe elastic deformation - Google Patents
Guided missile presses heart mutation analysis method under a kind of missile airframe elastic deformation Download PDFInfo
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Abstract
The present invention discloses guided missile under a kind of missile airframe elastic deformation and presses heart mutation analysis method, and methods described includes：S1：The full spatial domain trajectory parameter of guided missile is counted, obtains calculating state set；S2：Full bullet center of pressure coefficient of the rigid body guided missile in the case where calculating each state of state set is obtained by fluid-dynamic analysis method；S3：Solve the moment of flexure that guided missile is subject under each state；S4：Body static elasticity deformation displacement of the guided missile under each state is calculated based on static(al) stiffness test, is fitted using amount of deflection multinomial, determines fitting coefficient；S5：Threedimensional model under each state after frame elastic deformation is obtained by 3 d modeling software；S6：The center of pressure coefficient of guided missile after frame elastic deformation is calculated by fluid-dynamic analysis method, determine the variable quantity of the guided missile pressure heart, the present invention analyzes influence of the missile airframe elastic deformation to the guided missile pressure heart by straightforward procedure, reduce amount of calculation while calculation error is reduced, calculating speed is improved, reduces engineer applied difficulty.
Description
Technical field
The present invention relates to aerodynamic characteristics of vehicle analysis field.More particularly, under a kind of missile airframe elastic deformation
Guided missile presses heart mutation analysis method.
Background technology
In low altitude high speed flight, its body structure is acted on slender missile by external applied loads such as aerodynamic force, mass forces
It can occur significantly to deform.This deformation can make the pressure heart of guided missile move forward, and reduce the stability of guided missile.Therefore, during Missile Design
The pressure heart variable quantity as caused by elastic deformation must be obtained, there is provided be totally used as with control system to guided missile and design input use.
The problem is classified as aeroelastic effect problem in engineering.
The analysis method that engineering circles and academia obtain the pressure heart variable quantity at present mainly has two classes：First, based on linear
The static aeroelastic analysis method of potential flow theories, second, the Numerical Analysis methods based on fluid structurecoupling.
First kind method mainly determines the aerodynamic characteristic of guided missile by linearization technique, in conjunction with the broad sense for solving linearisation
Structure motion equation provides the elastic deformation of guided missile, finally recycles linearization technique to calculate the aerodynamic characteristic of guided missile after deformation.
This kind of method major defect is that linearization technique determines that the aerodynamic characteristic precision of guided missile is low.Especially guided missile is super/hypersonic
Phenomena such as shock wave that occurs under the big angle of attack during flight, separation, causes flow field apparent altitude non-linear, and linearisation is assumed no longer to be applicable.
Computational fluid dynamics method (CFD) is coupled iteration by the second class method with computational structural dynamics (CSD) method
Calculate.Accurate aerodynamic force is obtained first with high-precision CFD approach, then aerodynamic force is high-precision as input utilization
CSD methods obtain malformation, then recycle CFD approach to obtain aerodynamic force on the guided missile after deformation.The process will back and forth change
In generation, is until meet convergence criterion.This kind of method pneumatically requires high and computationally intensive with structure Coupling method and technology, is not readily used for reality
Border engineering design.
Accordingly, it is desirable to provide guided missile presses heart mutation analysis method under a kind of missile airframe elastic deformation, missed reducing to calculate
Amount of calculation is reduced while poor, improves calculating speed, reduces engineer applied difficulty.
The content of the invention
It is an object of the invention to provide guided missile under a kind of missile airframe elastic deformation to press heart mutation analysis method, is reducing
Amount of calculation is reduced while calculation error, improves calculating speed, reduces engineer applied difficulty.
To reach above-mentioned purpose, the present invention uses following technical proposals：
The invention discloses guided missile under a kind of missile airframe elastic deformation to press heart mutation analysis method, and methods described includes：
S1：The full spatial domain trajectory parameter of guided missile is counted, obtains calculating state set；
S2：Complete suppress of the rigid body guided missile in the case where calculating each state of state set is obtained by fluid-dynamic analysis method to feel concerned about
Number；
S3：Solve the moment of flexure that guided missile is subject under each state；
S4：Body static elasticity deformation displacement of the guided missile under each state is calculated based on static(al) stiffness test, it is more using amount of deflection
Item formula is fitted, and determines fitting coefficient；
S5：Threedimensional model under each state after frame elastic deformation is obtained by 3 d modeling software；
S6：The center of pressure coefficient of guided missile after frame elastic deformation is calculated by fluid-dynamic analysis method, determines that guided missile presses the heart
Variable quantity.
Preferably, the calculating state set in the S1 includes height, missile velocity and the angle of attack of each state.
Preferably, guided missile is reduced to one-dimensional beam by the S3, solves the moment of flexure that guided missile is subject under each state.
Preferably, the S4 includes：
S41：According to guided missile static(al) stiffness test result, guided missile static(al) rigidity model is established.
S42：The moment of flexure is loaded on guided missile, frame elastic deformation displacement is calculated by equation of equilibrium.
S43：Body amount of deflection multinomial is fitted by frame elastic deformation displacement.
Preferably, using body as x-axis, using bullet point as origin, the equation of equilibrium is
Ku (x)=M (x)
Wherein, K is guided missile static(al) rigidity model, and u (x) is body static elasticity deformation displacement, and M (x) is moment of flexure.
Preferably, using body as x-axis, body static elasticity deformation displacement direction is y-axis, and the body amount of deflection multinomial is
Y=a1x5+a2x4+a3x3+a4x2+a5x+a6
Wherein, a1、a2、a3、a4、a5And a6For undetermined parameter.
Preferably, the S5 realizes the deformation of body by 3 d modeling software based on the body amount of deflection multinomial, obtains
Obtain the body 3-D geometric model after elastic deformation.
Preferably, the variable quantity of the guided missile pressure heart is
ΔXcp=Xcpe-Xcpr
Wherein, XcpeFor guided missile center of pressure coefficient, X after elastic deformationcprFor the leading bullet center of pressure coefficient of elastic deformation.
Beneficial effects of the present invention are as follows：
1st, the aerodynamic force before and after the present invention is deformed by fluid-dynamic analysis method acquisition frame elastic, computational accuracy height,
It is applied widely, the prediction error about 2% for the center of pressure coefficient that this method obtains, while this method is non-suitable for shock wave, separation etc.
Linear serious operating mode, has the characteristics of applied widely.
What the 2nd, the present invention provided is decoupling calculation method, and meter is coupled with computational structural dynamics compared to hydrodynamic method
Calculation method, there is the advantages of amount of calculation is small.
3rd, calculating process of the present invention is simple, the division of labor is clear and definite, is easy to Project Realization.
4th, the present invention is built by body three-dimensional geometry after combining amount of deflection multinomial and 3 d modeling software completion elastic deformation
Mould, the processing method are simple, efficient.
Brief description of the drawings
The embodiment of the present invention is described in further detail below in conjunction with the accompanying drawings.
Fig. 1 shows the flow chart according to guided missile pressure heart mutation analysis method under a kind of missile airframe elastic deformation of the present invention.
Embodiment
In order to illustrate more clearly of the present invention, the present invention is done further with reference to preferred embodiments and drawings
It is bright.Similar part is indicated with identical reference in accompanying drawing.It will be appreciated by those skilled in the art that institute is specific below
The content of description is illustrative and be not restrictive, and should not be limited the scope of the invention with this.
As shown in figure 1, the invention discloses guided missile under a kind of missile airframe elastic deformation to press heart mutation analysis method, it is described
Method includes：
S1：The full spatial domain trajectory parameter of guided missile is counted, obtains calculating state set.In the full spatial domain trajectory parameter of statistics guided missile,
It can be formed by height H, missile velocity MaWith the calculating state table of angle of attack composition, the purpose of the inventive method is exactly to calculate at this
Pressure heart variation delta X caused by guided missile elastic deformation under a little statescp.Wherein, calculate each state in state table and be designated as P (H, Ma,
α)。
S2：Rigid body guided missile suppressing entirely in the case where calculating each state of state set is obtained by flow dynamics analysis (CFD) method
Feel concerned about several Xcpr.Rigid body guided missile refers to the guided missile of no elastic deformation.Generally usable ground wind tunnel test methods or theoretical calculation side
Method obtains the guided missile pressure heart.But there is difference in the result that both approaches obtain, CFD approach will be used in subsequent step of the present invention
The guided missile pressure heart after elastic deformation is obtained, CFD approach is preferably used herein, to obtain more reasonably pressing heart variable quantity.
CFD approach key step may include：The modeling of guided missile profile is completed first, obtains rigid body guided missile 3-D geometric model；
Then mesh modeling is completed for the model；Derived grid is input to CFD solvers iterative and obtains guided missile Flow Field ginseng
Number；The aerodynamic characteristics such as the guided missile pressure heart are achieved with finally by post processing.Wherein profile modeling can be used the CAD such as UG, ProE soft
The Grid Generation Softwares such as ICEM-CFD, Gridgen can be used in part, mesh modeling, and Fluent, CFD++ etc. can be used in iterative
Common commercial fluid analysis software.
As a preferred embodiment, the modeling of body geometric shape is completed (it is required that bullet using UG NX4.0 softwares
Body is horizontal positioned), geometric shape, which is input in ICEM-CFD softwares, completes mesh modeling, and derived grid is input in CFD++ and obtained
Rigid body guided missile is obtained in state P (H, Ma, α) under complete play center of pressure coefficient Xcpr.Because rigid body guided missile profile is not with state P (H, Ma, α) become
Change, therefore the grid of step generation is available for different calculating states to use.In addition, retain geometric shape file caused by the step
Block file (it is assumed that being named as gangti.blk) caused by (it is assumed that being named as gangti.prt) and mesh modeling, for walking below
Moulding and mess generation use after body deformation in rapid.
S3：Solve the moment of flexure that guided missile is subject under each state.In calculated bending moment, preferably guided missile is reduced to one-dimensional
Beam, the guided missile in motor-driven equilibrium state is solved in state P (H, Ma, α) under the bending moment vector M (x) that is subject to, wherein x is body
Axial coordinate, using bullet point as origin.Circular refers to《The force model load design of rocket and guided missile》(aerospace is published
Society, 1994.06).
S4：Body static elasticity deformation displacement of the guided missile under each state is calculated based on static(al) stiffness test, it is more using amount of deflection
Item formula is fitted, and determines fitting coefficient.The S4 further may include：
S41：According to guided missile static(al) stiffness test result, guided missile static(al) rigidity model is established；
S42：The moment of flexure is loaded on guided missile, frame elastic deformation displacement is calculated by equation of equilibrium.The balance
Formula is
Ku (x)=M (x)
Wherein, K is guided missile static(al) rigidity model, and u (x) is body static elasticity deformation displacement, and M (x) is moment of flexure.
S43：Body amount of deflection multinomial is fitted by frame elastic deformation displacement.Using body static elasticity deformation displacement direction as
Y-axis, the body amount of deflection multinomial are
Y=a1x5+a2x4+a3x3+a4x2+a5x+a6
Wherein, a1、a2、a3、a4、a5And a6For undetermined parameter.The present invention is made up of using the fitting of 5 rank multinomials a large amount of points
Sag curve, 3 d modeling software input service is simplified, as long as 6 multinomial coefficients of typing are obtained with controlling curve.
S5：Threedimensional model under each state after frame elastic deformation is obtained by 3 d modeling software.Using CAD software
Curved surface " moulded " function, body face is realized as controlling curve using the law curve based on body amount of deflection Polynomial generation
Deformation, body 3-D geometric model after being deformed, export the model and calculate use for lower step CFD.
The present invention completes body 3 d geometric modeling after elastic deformation by combining amount of deflection multinomial and 3 d modeling software,
The processing method is simple, efficient.By realizing body face based on the polynomial controlling curve of amount of deflection in 3 d modeling software
Deformation, the body 3-D geometric model of different distortion can very easily be obtained by changing 6 multinomial coefficients.This method is only required
Engineer grasps the simple moulded method of CAD curved surfaces, has cleverly avoided using complicated CAE software.
As a preferred embodiment, shape files outside the rigid body generated in preceding step can be opened in UG softwares
gangti.prt；The horizontal line section that insertion terminates from bullet point starting to afterbody on the body plane of symmetry, and it is horizontal to both sides
Stretching, stretched width requirement are more than body width, and the face of formation is referred to as base surface；Insertion originates from bullet point on the body plane of symmetry
The law curve (Law Curve) using amount of deflection multinomial as rule terminated to afterbody, it is wide to both sides horizontal stretch, stretching
Degree is consistent with base surface, and the face of formation is body Deformation control face；Use curved surface " moulded (Global Shaping) " work(
Edlin can be entered to rigid body guided missile three-dimensional profile, " in Overcrown by Surface " interfaces " Base " and " Control "
Above-mentioned base surface and chain of command are chosen successively.Rigid body guided missile profile is after " moulded " that above-mentioned amount of deflection multinomial controls
Just obtain body geometric shape after elastic deformation.When creating law curve, pay attention to carrying out curve using 6 multinomial coefficients
Parametrization.For different states, it is only necessary to change 6 multinomial coefficients, so that it may automatically update acquisition deformation body.
S6：The center of pressure coefficient of guided missile after frame elastic deformation is calculated by fluid-dynamic analysis method, determines that guided missile presses the heart
Variable quantity.Using guided missile center of pressure coefficient X after CFD approach acquisition elastic deformationcpe, determine state P (H, Ma, α) when frame elastic
Deformation pushes the variation delta X of the heartcpFor
ΔXcp=Xcpe-Xcpr
As a preferred embodiment, upper step can be obtained to deformation body imports ICEM-CFD, then import block file
(gangti.blk) calculating grid can, be generated after a small amount of editor；Derived grid, calculated using CFD++ after obtaining elastic deformation
Guided missile center of pressure coefficient Xcpe。
Different conditions are carried out respectively above-mentioned S2~S6 analysis calculate, can obtain calculate state table in it is stateful under
Pressure heart variation delta X caused by frame elastic deformationcp, used for totality and control system as design input.
Aerodynamics evaluation method precision is high, applied widely.The present invention is obtained using CFD approach before and after frame elastic deformation
Aerodynamic force.This method center of pressure coefficient predicts error about 2%, has the characteristics of precision is high；This method is applied to shock wave, divided simultaneously
From etc. non-linear serious operating mode, have it is applied widely the characteristics of.Traditional linearisation aerodynamics evaluation method precision is relatively low,
Center of pressure coefficient predicts error up to 5%, bigger for non-linear effects serious situation error.In addition, The present invention gives one kind
Decoupling calculation method, compared to CFD and CSD coupling calculations, there is the advantages of amount of calculation is small.LOAD FOR of the present invention
Calculated with elastic deformation and the guided missile of three-dimensional structure is all reduced to one-dimensional girder structure, its amount of calculation very little.Coupling process then will
CFD and CSD is asked all to be handled according to three-dimensional, amount of calculation is bigger than normal.In order to control amount of calculation, the present invention only considers pneumatically and structure
Between single order influence amount, ignore second order and the influence amount of higher order.Coupling calculation need to could meet to restrain by successive ignition
Standard, amount of calculation are very big.The technology of the present invention threshold is low, the division of labor is clear and definite, is easy to Project Realization.Aeroelastic effect problem be pneumatically with
The coupling of structure, it is related to the subject such as aerodynamic force, load, structure direction.Engineer's grasp is not required nothing more than using coupling calculation
All relevant professional knowledges and method, the tight fit between engineering unit all departments is also required, technical requirements are high, and Project Realization is difficult
Degree is big.After the present invention decouples problem, links work can clearly distribute to pneumatic, load and structural engineer, rely on
They complete work at respective professional speciality.This pattern requires low to designer, at the same with the portion of present most engineering units
Door division of labor management status matches.Therefore, the present invention is easy to realize in engineering unit.
Obviously, the above embodiment of the present invention is only intended to clearly illustrate example of the present invention, and is not pair
The restriction of embodiments of the present invention, for those of ordinary skill in the field, may be used also on the basis of the above description
To make other changes in different forms, all embodiments can not be exhaustive here, it is every to belong to this hair
Row of the obvious changes or variations that bright technical scheme is extended out still in protection scope of the present invention.
Claims (8)
1. guided missile presses heart mutation analysis method under a kind of missile airframe elastic deformation, it is characterised in that methods described includes：
S1：The full spatial domain trajectory parameter of guided missile is counted, obtains calculating state set；
S2：Full bullet center of pressure coefficient of the rigid body guided missile in the case where calculating each state of state set is obtained by fluid-dynamic analysis method；
S3：Solve the moment of flexure that guided missile is subject under each state；
S4：Body static elasticity deformation displacement of the guided missile under each state is calculated based on static(al) stiffness test, uses amount of deflection multinomial
It is fitted, determines fitting coefficient；
S5：Threedimensional model under each state after frame elastic deformation is obtained by 3 d modeling software；
S6：The center of pressure coefficient of guided missile after frame elastic deformation is calculated by fluid-dynamic analysis method, determines the change of the guided missile pressure heart
Change amount.
2. guided missile presses heart mutation analysis method under a kind of missile airframe elastic deformation according to claim 1, its feature exists
In the calculating state set in the S1 includes height, missile velocity and the angle of attack of each state.
3. guided missile presses heart mutation analysis method under a kind of missile airframe elastic deformation according to claim 1, its feature exists
In guided missile is reduced to one-dimensional beam by the S3, solves the moment of flexure that guided missile is subject under each state.
4. guided missile presses heart mutation analysis method under a kind of missile airframe elastic deformation according to claim 1, its feature exists
In the S4 includes：
S41：According to guided missile static(al) stiffness test result, guided missile static(al) rigidity model is established.
S42：The moment of flexure is loaded on guided missile, frame elastic deformation displacement is calculated by equation of equilibrium.
S43：Body amount of deflection multinomial is fitted by frame elastic deformation displacement.
5. guided missile presses heart mutation analysis method under a kind of missile airframe elastic deformation according to claim 4, its feature exists
In using body as x-axis, using bullet point as origin, the equation of equilibrium is
Ku (x)=M (x)
Wherein, K is guided missile static(al) rigidity model, and u (x) is body static elasticity deformation displacement, and M (x) is moment of flexure.
6. guided missile presses heart mutation analysis method under a kind of missile airframe elastic deformation according to claim 4, its feature exists
In using body as x-axis, body static elasticity deformation displacement direction is y-axis, and the body amount of deflection multinomial is
Y=a1x5+a2x4+a3x3+a4x2+a5x+a6
Wherein, a1、a2、a3、a4、a5And a6For undetermined parameter.
7. guided missile presses heart mutation analysis method under a kind of missile airframe elastic deformation according to claim 4, its feature exists
In the S5 realizes the deformation of body by 3 d modeling software based on the body amount of deflection multinomial, after obtaining elastic deformation
Body 3-D geometric model.
8. guided missile presses heart mutation analysis method under a kind of missile airframe elastic deformation according to claim 1, its feature exists
In the variable quantity of the guided missile pressure heart is
ΔXcp=Xcpe-Xcpr
Wherein, XcpeFor guided missile center of pressure coefficient, X after elastic deformationcprFor the leading bullet center of pressure coefficient of elastic deformation.
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