CN109726440A - A kind of aeroelastic analysis method considering internal flow dynamic characteristic - Google Patents
A kind of aeroelastic analysis method considering internal flow dynamic characteristic Download PDFInfo
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- CN109726440A CN109726440A CN201811476560.9A CN201811476560A CN109726440A CN 109726440 A CN109726440 A CN 109726440A CN 201811476560 A CN201811476560 A CN 201811476560A CN 109726440 A CN109726440 A CN 109726440A
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Abstract
The invention belongs to aircraft aeroelastic analysis technology, in particular to a kind of aeroelastic analysis method for considering internal flow dynamic characteristic；This method firstly generates the additional mass matrix for considering internal flow, and assembling considers the equation of motion after additional mass matrix later, subsequently accounts for the aeroelastic analysis of internal flow influence.Method proposed by the present invention can consider that the influence of internal flow dynamic characteristic preferably instructs aeroelastic design to help to improve the aeroelastic analysis precision of full machine in the dynamical simulation model with a large amount of internal flow aircrafts.The analysis method of proposition is easy to operate, there is higher engineering application value.
Description
Technical field
The invention belongs to aircraft aeroelastic analysis technologies, in particular to a kind of to consider the pneumatic of internal flow dynamic characteristic
Flexibility analysis method.
Background technique
In order to improve fighting efficiency, the especially large-scale fuel charger of modern aircraft, fighter plane all carry great amount of fuel oil.To this
The aeroelastic characteristic assessment of a little aircrafts, traditional calculation method using internal flow as lumped mass, only consider its quality with
Inertia Characteristics do not account for the influence between the dynamic characteristic and internal flow and container of internal flow.To this kind of internal flow
It is not clear with the influence of structural vibration problem and the elasticity of fluid to aircraft aeroelastic characteristic caused by structure Coupling.Mesh
Preceding domestic also few influences for considering these factors in aeroelastic analysis.
Summary of the invention
The purpose of the present invention:
It proposes to consider a kind of aeroelastic analysis method that internal flow dynamic characteristic influences.
The technical scheme is that.
A kind of aeroelastic analysis method considering internal flow dynamic characteristic；This method firstly generates consideration internal flow
Additional mass matrix, later assembling consider additional mass matrix after the equation of motion, subsequently account for internal flow shadow
Loud aeroelastic analysis.
The present invention have the advantage that and the utility model has the advantages that
Influence of the present invention to internal fluid dynamic properties to aircraft aeroelastic characteristic is analyzed, and one kind is given
Consider the aeroelastic analysis method that internal flow dynamic characteristic influences.This method can be dynamic with a large amount of internal flow aircrafts
The influence of internal flow dynamic characteristic is considered in power simulation model, so that the aeroelastic analysis precision of full machine is helped to improve,
Preferably instruct aeroelastic design.The analysis method of proposition is easy to operate, there is higher engineering application value.
Detailed description of the invention
Fig. 1 is present invention band internal flow region and interface definition,
Fig. 2 is present invention analysis result and fixed mass the model calculation correlation curve.
Specific embodiment
The present invention gives a kind of aeroelastic analysis methods that consideration internal flow dynamic characteristic influences.By moving
The mass matrix of equation increases additional mass matrix, realizes the considerations of influencing on internal fluid dynamic properties.
(1) the additional mass matrix for considering internal flow is generated
It is assumed that internal flow is without gluing, can not press, the region that solid occupies is ΩS, the region that internal flow occupies is ΩF,
Free Surface is Γ, and the interface of fluid and solid is ∑, and schematic diagram is shown in Fig. 1.The Eulerian equation of internal flow is
Wherein p, ρFAnd uFThe respectively pressure, density and displacement of fluid, t is the time；
It is without the continuity equation for gluing incompressible fluid
Wherein vFFor fluid velocity；
It can be derived by according to (a) and (b) equation in region ΩFIt is interior
Δ φ=0 (c)
Wherein φ is potential function, is met
It is assumed that fluid motion and structural vibration are simple harmonic oscillation, i.e.,It then flows dynamic at solid interface ∑
Measuring Conservation Relationship is
Wherein σSIndicate structure in solid area ΩSOn stress, ρsAnd uSRespectively indicate density of texture and displacement, nSFor knot
The normal direction on structure surface；
Nothing at fluid structurecoupling interface penetrates condition and is
Wherein nFTo flow the normal orientation for being directed toward solid side on solid interface ∑ from fluid side.
Potential function φ meets boundary condition on Free Surface Γ
φ=0 (f)
It is derived according to formula (a)~(f), obtains matrix equation system
Wherein MSFor architecture quality matrix, K is structural stiffness matrix, MFFor internal flow mass matrix, λ=ω2, ω is
Circular frequency, T are the condition of transmitting matrix (equation (d) and (e)) at fluid structurecoupling interface, and subscript T is transposition, and u is structure bit
The amount of shifting to, Φ are fluid potential function.
Second row of matrix equation (g) obtains
Reduced equation (g) is
K11-λ(MS+MA)11=0 (i)
Wherein
As one considers the additional mass matrix of internal flow quality.
(2) assembling considers the equation of motion after additional mass matrix
The equation of motion of system for being derived by internal flow and its container composition is
KU-λ(MS+MA) u=0
That is equation (i), wherein MSFor architecture quality matrix, K is structural stiffness matrix, λ=ω2, ω is circular frequency, and u is knot
Structure motion vector.
(3) aeroelastic analysis of internal flow influence is accounted for
The aeroelastic characteristic for considering that internal flow influences is calculated using updated mass matrix.
This analysis method is characterized in that the mass matrix in the equation of motion increases the shadow for considering internal flow dynamic characteristic
It rings.
Table 1 is that calculating state of the invention defines, and state 1 is to consider that internal flow influences the analysis of model as a result, state 2
For the calculated result of fixed mass model.
The definition of the calculating state of the present invention of table 1
| Status number | State definition |
| 1 | Consider that internal flow influences model |
| 2 | Lumped-mass model |
Claims (3)
1. a kind of aeroelastic analysis method for considering internal flow dynamic characteristic；It is characterized by: steps are as follows:
Step 1: the additional mass matrix for considering internal flow is generated,
Step 2: assembling considers the equation of motion after additional mass matrix,
Step 3: accounting for the aeroelastic analysis of internal flow influence.
2. the aeroelastic analysis method according to claim 1 for considering internal flow dynamic characteristic, it is characterised in that: institute
State the derivation method of additional mass matrix in step 1 are as follows: it is assumed that internal flow is without gluing, can not press, the region that solid occupies is
ΩS, the region that internal flow occupies is ΩF, the interface of Free Surface Γ, fluid and solid are ∑, and schematic diagram is shown in Fig. 1.
The Eulerian equation of internal flow is
Wherein p, ρFAnd uFThe respectively pressure, density and displacement of fluid, t is the time；
It is without the continuity equation for gluing incompressible fluid
Wherein νFFor fluid velocity；
It can be derived by according to (a) and (b) equation in region ΩFIt is interior
Δ φ=0 (c)
Wherein φ is potential function, is met
It is assumed that fluid motion and structural vibration are simple harmonic oscillation, i.e. p=ρFω2φ then flows the conservation of momentum at solid interface ∑
Relationship is
σSnS=ρFω2φnF (d)
Wherein σSIndicate structure in solid area ΩSOn stress, ρSAnd uSRespectively indicate density of texture and displacement, nSFor structure table
The normal direction in face；
Nothing at fluid structurecoupling interface penetrates condition and is
Wherein nFTo flow the normal orientation for being directed toward solid side on solid interface ∑ from fluid side.
Potential function φ meets boundary condition on Free Surface Γ
φ=0 (f)
It is derived according to formula (a)~(f), obtains matrix equation system
Wherein MSFor architecture quality matrix, K is structural stiffness matrix, MFFor internal flow mass matrix, λ=ω2, ω is circle frequency
Rate, T are the condition of transmitting matrix (equation (d) and (e)) at fluid structurecoupling interface, and subscript T is transposition, u be displacement structure to
Amount, Φ are fluid potential function.
Second row of matrix equation (g) obtains
Reduced equation (g) is
Ku-λ(MS+MA) u=0 (i)
Wherein
As one considers the additional mass matrix of internal flow quality.
3. the aeroelastic analysis method according to claim 1 for considering internal flow dynamic characteristic, it is characterised in that: institute
State the equation of motion in step 2 are as follows:
Ku-λ(MS+MA) u=0
Wherein MSFor architecture quality matrix, K is structural stiffness matrix, λ=ω2, ω is circular frequency, and u is displacement structure vector.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110887636A (en) * | 2019-11-21 | 2020-03-17 | 中国特种飞行器研究所 | Hydrodynamic model test device and method for additional mass of airship |
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