CN108399297A - Aircraft flutter analysis grid model Legendre's modeling method - Google Patents

Aircraft flutter analysis grid model Legendre's modeling method Download PDF

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CN108399297A
CN108399297A CN201810172978.4A CN201810172978A CN108399297A CN 108399297 A CN108399297 A CN 108399297A CN 201810172978 A CN201810172978 A CN 201810172978A CN 108399297 A CN108399297 A CN 108399297A
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史忠科
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Xian Feisida Automation Engineering Co Ltd
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Abstract

In order to overcome the problems, such as complicated flutter model under the influence of the prior art is unable to effective expression aerodynamic force and Strength Changes,The present invention provides a kind of aircraft flutter analysis grid model Legendre's modeling methods,This method selects multiple mesh points in aircraft body shafting,In different flying speeds,Atmospheric density,Air-flow environment,Under the influence of the aerodynamic force such as different temperatures and Strength Changes complicated flutter grid model is indicated according to body shafting decomposition method,Installation sensor and data are proposed according to the requirement for establishing the model,Image recording requirement,Data are obtained by effective flutter flight test,Excitation function is obtained by gas flow transducer measured value,Oscillation variable is approached and equivalent description using Legendre function,Three axial vibration equation solutions at body shafting coordinate grid point are determined simultaneously according to discrimination method,Solves the technical issues of prior art is unable under the influence of effective expression aerodynamic force and Strength Changes complicated flutter model.

Description

Aircraft flutter analysis grid model Legendre's modeling method
Technical field
The present invention relates to the safe ground comprehensive testing methods of the aircraft flights such as civil aircraft, fighter plane, unmanned plane, especially It is related to aircraft flutter analysis grid model Legendre's modeling method, belongs to aerospace and information technology field.
Background technology
Flutter is that elastic construction is occurred in uniform air flow by the coupling of air force, elastic force and inertia force A kind of violent oscillatory motion phenomenon.For aircraft, it can awing be vibrated by after uncertain disturbance.At this point, by In the effect of air-flow, the elastic construction such as wing, empennage or control surface of aircraft will will produce Additional pneumatic power；As a kind of exciting Power, Additional pneumatic power will aggravate the vibration of structure.Air attempts to reduce vibration again to the damping force of aircaft configuration simultaneously；In low speed When flight, since damping force is dominant, the vibration after disturbance fades away；It quivers when reaching the i.e. flutter critical speed of a certain flying speed It shakes behind boundary, exciting force is dominant, and equilbrium position unstability will generate violent oscillatory motion, aircraft is caused to disintegrate in a few seconds, leads to calamity Difficulty consequence；It can be said that from that day that aircraft industry is started to walk, flutter is always just the popular problem of aeronautical chart research.
To avoid flutter accident from occurring, new machine development is subjected to flutter test link, and flutter test does not occur with determination Stabilized flight envelope curve；Carry out Flutter Problem research there are two main classes approach, first, numerical computations：This need to analysis object into Row mathematical modeling, this process need to introduce certain hypothesis in structure, pneumatic etc., it is difficult to consider the various non-of necessary being The influence of linear factor and modeling error, analysis result has certain reference value, but may have with actual conditions larger Deviation；Second is that research technique：Experiment related with flutter mainly has wind tunnel test and flight test.Gas can be considered in wind tunnel test Dynamic effect, but the method requires subjects carrying out contracting than design, scale model and real structure there are certain difference, And since the interference aerodynamics of wind tunnel wall and holder are inevitably distorted；Situations such as further for high speed, thermal environment, wind tunnel test mould Quasi- somewhat expensive and performance difficulty.Flight test can simulation test object completely real operating environments, but the condition tested It is limited, costly and risk is big, flutter once occurs in the air for aircraft, can disintegrate within several seconds even shorter time, fly It is substantially zeroed to escape probability almost without Deal with Time by member.
Flutter simulation experiment exactly a kind of flutter that can effectively make up insufficient, the great vitality of traditional experiment in ground is ground Study carefully method.Ground experiment is using aircraft ground flutter test system as research object, with multidisciplinary design optimization theory research Core is intimately associated the engineering characteristic of aircraft ground flutter test system, and it is distributed to break through equivalent test modeling method, multiple spot The key technologies such as Unsteady Aerodynamic Modeling and control, flutter test integrated detection method put forth effort to solve aircraft flutter aerodynamic force mould The problems such as type difficulty is realized, multi-point exciting power can not accurately control, flutter test result can not play back repeatedly improves master-plan water It is flat.
Although aeronautical chart, mechanics circle are relatively early to avoiding the problem that flutter is studied, current research or primary Stage does not form the theory and method system of a system；Existing method lacks aircraft equivalence ground flutter test method And evaluation；Especially art methods are difficult to describe aircraft in different flying speeds, atmospheric density, air-flow environment, difference Complicated flutter model under the influence of the aerodynamic force such as temperature and Strength Changes so that flutter ground experiment research be difficult to be engineered into Exhibition.
Invention content
In order to overcome the problems, such as complicated flutter model under the influence of the prior art is unable to effective expression aerodynamic force and Strength Changes, The present invention provides a kind of aircraft flutter analysis grid model Legendre's modeling method, this method is selected in aircraft body shafting Multiple mesh points are selected, are influenced in the aerodynamic force such as different flying speeds, atmospheric density, air-flow environment, different temperatures and Strength Changes Under according to body shafting decomposition method indicate complicated flutter grid model, installation sensor is proposed according to the requirement for establishing the model With data, image recording requirement, data are obtained by effective flutter flight test, are encouraged by gas flow transducer measured value Function, using Legendre function to oscillation variable approached with equivalent description, according to discrimination method simultaneously axis is determined It is three axial vibration equation solutions at coordinate net lattice point, solves the prior art and be unable to effective expression aerodynamic force and Strength Changes Under the influence of complicated flutter model the technical issues of.
The present invention solve its technical problem the technical solution adopted is that, a kind of aircraft flutter analysis grid model Legendre Modeling method, feature include the following steps：
Step 1：With the complicated flutter model of aircraft body shafting OXYZ analyses, n mesh point is chosen in body shafting: xi,yi,zi, i=1,2 ..., n, three shaft position component x (y, z, t) of mesh point dynamic when vibration, y (x, z, t), z (x, y, t) are The function of time t and other two shaft positions, for the ease of expression, with xixFor (y, z, t), subscript i=1,2 ..., n are grid Piont mark, subscript second letter x, y, z indicate that vibration in three axis components of body shafting OXYZ, is asked in order to simplified respectively Topic considers the i-th=1, when the x-axis direction of 2 ..., n mesh point is vibrated, x (y, z, t)=xix(t), y (x, z, t)=yix(x), Z (x, y, t)=zix(x), consider the i-th=1, when the y-axis direction of 2 ..., n mesh point vibrates, x (y, z, t)=xiy(y),y (x, z, t)=yiy(t), z (x, y, t)=ziy(y), consideration the i-th=1, when the z-axis direction of 2 ..., n mesh point vibrates, x (y, Z, t)=xiz(z), y (x, z, t)=yiz(z), z (x, y, t)=ziz(t)；
It is in the built-in vertical approximate model of grid vertex neighborhood：
In formula, X [xix(t),yix(x),zix(x),Θt, t] and it is in body shafting coordinate xi,yi,ziIn grid neighborhood of a point X axis oscillating function, Axi[xix(t),yix(x),zix(x),Θt]、Bxi[xix(t),yix(x),zix(x),Θt] shake for X axis The structural coefficient function of dynamic equation, xix(t),yix(x),zix(x) it is respectively in body shafting coordinate grid point xi,yi,zi, i= 1,2 ..., correspond to x when X axis vibrates at ni,yi,ziChanging value；Y[xiy(y),yiy(t),ziy(y),Θt, t] and it is in machine Body shafting coordinate xi,yi,ziY-axis oscillating function, A in grid neighborhood of a pointyi[xiy(y),yiy(t),ziy(y),Θt]、Byi [xiy(y),yiy(t),ziy(y),Θt] be Y-axis vibration equation structural coefficient function, xiy(y),yiy(t),ziy(y) respectively For in body shafting coordinate grid point xi,yi,zi, i=1,2 ..., correspond to x when Y-axis is vibrated at ni,yi,ziChanging value；Z [xiz(z),yiz(z),ziz(t),Θt, t] and it is in body shafting coordinate xi,yi,ziZ axis is to oscillating function in grid neighborhood of a point, Azi[xiz(z),yiz(z),ziz(t),Θt]、Bzi[xiz(z),yiz(z),ziz(t),Θt] it is structure system of the Z axis to vibration equation Number function, xiz(z),yiz(z),ziz(t) it is respectively in body shafting coordinate grid point xi,yi,zi, i=1,2 ..., at n Z axis to Correspond to x when vibrationi,yi,ziChanging value；ui(xi,yi,zi,Θt, t) and it is in xi,yi,ziThe equivalent excitation function of mesh point, t For the time；Θt=[Ti H Ma Fzi ρ]TFor parameter vector, TiIndicate xi,yi,ziThe temperature of mesh point, H are flying height, Ma For Mach number, FziFor xi,yi,ziThe air-flow environment of mesh point influences, and ρ is atmospheric density；
Step 2：The body shafting coordinate grid point x of corresponding step 1i,yi,zi, i=1,2 ..., n, installation Miniature temperature biography Sensor, X, Y, Z axis are especially miniature in wing upper and lower and the installation of all rudder face both sides to air-flow, position and vibrating sensor X, Y, Z axis installs the image recording sensor sight more than 1000 frames/second additional to air-flow, position and vibrating sensor, while in fuselage Survey the vibration amplitude and frequency of wing tip, all rudder faces；Aircraft airborne sensor records time, flying height, Mach number, greatly Air tightness；
Step 3：The process of flutter test after aircraft arrival assigned altitute and Mach number is expressed as effective flutter flight Experiment, effective flutter flight test data sampling time are tk=0, Ts,2Ts,…,NTs, TsTo record the sampling period of data, N + 1 is total sampling number of effective flutter flight test；Discrete time t is obtained by flutter flight testk=0, Ts,2Ts,…, NTsMoment body shafting xi,yi,zi, i=1,2 ..., the x of n mesh pointsix(tk)、yiy(tk)、ziz(tk) and ΘtTest value；
Step 4：According to body shafting coordinate grid point xi,yi,zi, i=1,2 ..., n install miniature X, Y, Z axis to air-flow Sensor especially installs miniature X, Y, Z axis to gas flow transducer in wing upper and lower and all rudder face both sides, determines tk=0, Ts,2Ts,…,NTsMoment body shafting xi,yi,zi, i=1,2 ..., the excitation function of n
To X [xix(t),yix(x),zix(x),Θt,t]、Y[xiy(y),yiy(t),ziy(y),Θt,t]、Z[xiz(z),yiz (z),ziz(t),Θt, t] and it given function is respectively adopted approaches, it obtains：
AndIt can continuously be led about x,It can continuously be led about y,Connect about z It is continuous to lead；In this way, can obtain：
And
Step 5：It enables：
And
(1) formula can be described as：
It enables
In formula：
px=[px(0) px(1) … px(mx-1) px(mx)],py=[py(0) py(1) … py(my-1) py(my)],
mx、my、mzTo correspond toLegendre expansion order；
For m=mx,my,mzThe recursive form of rank Legendre's orthogonal polynomial, b >=max (e) can be obtained
In formula,
Work as mx、my、mzFor odd number when, m=2,4 ..., mmax+ 1, mmax=mxOr mmax=myOr mmax=mz, work as mx、my、mz For even number when, m=3,5 ..., mmax+ 1, mmax=mxOr mmax=myOr mmax=mz；
It enables
Axi(xix,Θt)=paxξx(xix),Bxi(xix,Θt)=pbxξx(xix),Ayi(yiy,Θt)=payξy(yiy),Byi (yiy,Θt)=pbyξy(yiy),Azi(ziz,Θt)=pazξz(ziz),Bzi(ziz,Θt)=pbzξz(ziz),
In formula：
pax=[ax(0) ax(1) … ax(mx-1) ax(mx)],pbx=[bx(0) bx(1) … bx(mx-1) bx (mx)],
pay=[ay(0) ay(1) … ay(my-1) ay(my)],pby=[by(0) by(1) … by(my-1) by (my)],
paz=[az(0) az(1) … az(mz-1) az(mz)],pbz=[bz(0) bz(1) … bz(mz-1) bz (mz)],
It can obtain
Or it is write as
It is right by taking (3) formula first item as an example
Both sides It asksPartial derivative can obtain
The x obtained according to step 3 and step 4ix(tk)、yiy(tk)、ziz(tk) andtk=0, Ts,2Ts,…,NTsAnd ΘtTest value, can obtain：
In formula,
And then it can obtain：It brings into
It can be with According to the following formula and least-squares estimation obtains px
The present invention beneficial outcomes be：Multiple mesh points are selected in aircraft body shafting, consider different flying speeds, big Indicate complicated according to body shafting decomposition method under the influence of the aerodynamic force such as air tightness, air-flow environment, different temperatures and Strength Changes Flutter grid model proposes installation sensor and data, image recording requirement, by effectively quivering according to the requirement for establishing the model Flight test of shaking obtains data, obtains excitation function by gas flow transducer measured value, is obtained by gas flow transducer measured value Excitation function, using Legendre function to oscillation variable approached with equivalent description, according to discrimination method simultaneously machine is determined Three axial vibration equation solutions at body shafting coordinate net lattice point are built to give complete complicated flutter model grid model Mould technical solution solves the technology that the prior art is unable to complicated flutter model under the influence of effective expression aerodynamic force and Strength Changes Problem.
It elaborates to the present invention with reference to specific example.
Specific implementation mode
Step 1：With the complicated flutter model of aircraft body shafting OXYZ analyses, n mesh point is chosen in body shafting: xi,yi,zi, i=1,2 ..., n, three shaft position component x (y, z, t) of mesh point dynamic when vibration, y (x, z, t), z (x, y, t) are The function of time t and other two shaft positions, for the ease of expression, with xixFor (y, z, t), subscript i=1,2 ..., n are grid Piont mark, subscript second letter x, y, z indicate that vibration in three axis components of body shafting OXYZ, is asked in order to simplified respectively Topic considers the i-th=1, when the x-axis direction of 2 ..., n mesh point is vibrated, x (y, z, t)=xix(t), y (x, z, t)=yix(x), Z (x, y, t)=zix(x), consider the i-th=1, when the y-axis direction of 2 ..., n mesh point vibrates, x (y, z, t)=xiy(y),y (x, z, t)=yiy(t), z (x, y, t)=ziy(y), consideration the i-th=1, when the z-axis direction of 2 ..., n mesh point vibrates, x (y, Z, t)=xiz(z), y (x, z, t)=yiz(z), z (x, y, t)=ziz(t)；
It is in the built-in vertical approximate model of grid vertex neighborhood：
In formula, X [xix(t),yix(x),zix(x),Θt, t] and it is in body shafting coordinate xi,yi,ziIn grid neighborhood of a point X axis oscillating function, Axi[xix(t),yix(x),zix(x),Θt]、Bxi[xix(t),yix(x),zix(x),Θt] shake for X axis The structural coefficient function of dynamic equation, xix(t),yix(x),zix(x) it is respectively in body shafting coordinate grid point xi,yi,zi, i= 1,2 ..., correspond to x when X axis vibrates at ni,yi,ziChanging value；Y[xiy(y),yiy(t),ziy(y),Θt, t] and it is in machine Body shafting coordinate xi,yi,ziY-axis oscillating function, A in grid neighborhood of a pointyi[xiy(y),yiy(t),ziy(y),Θt]、Byi [xiy(y),yiy(t),ziy(y),Θt] be Y-axis vibration equation structural coefficient function, xiy(y),yiy(t),ziy(y) respectively For in body shafting coordinate grid point xi,yi,zi, i=1,2 ..., correspond to x when Y-axis is vibrated at ni,yi,ziChanging value；Z [xiz(z),yiz(z),ziz(t),Θt, t] and it is in body shafting coordinate xi,yi,ziZ axis is to oscillating function in grid neighborhood of a point, Azi[xiz(z),yiz(z),ziz(t),Θt]、Bzi[xiz(z),yiz(z),ziz(t),Θt] it is structure system of the Z axis to vibration equation Number function, xiz(z),yiz(z),ziz(t) it is respectively in body shafting coordinate grid point xi,yi,zi, i=1,2 ..., at n Z axis to Correspond to x when vibrationi,yi,ziChanging value；ui(xi,yi,zi,Θt, t) and it is in xi,yi,ziThe equivalent excitation function of mesh point, t For the time；Θt=[Ti H Ma Fzi ρ]TFor parameter vector, TiIndicate xi,yi,ziThe temperature of mesh point, H are flying height, Ma For Mach number, FziFor xi,yi,ziThe air-flow environment of mesh point influences, and ρ is atmospheric density；
Step 2：The body shafting coordinate grid point x of corresponding step 1i,yi,zi, i=1,2 ..., n, installation Miniature temperature biography Sensor, X, Y, Z axis are especially miniature in wing upper and lower and the installation of all rudder face both sides to air-flow, position and vibrating sensor X, Y, Z axis installs the image recording sensor sight more than 1000 frames/second additional to air-flow, position and vibrating sensor, while in fuselage Survey the vibration amplitude and frequency of wing tip, all rudder faces；Aircraft airborne sensor records time, flying height, Mach number, greatly Air tightness；
Step 3：The process of flutter test after aircraft arrival assigned altitute and Mach number is expressed as effective flutter flight Experiment, effective flutter flight test data sampling time are tk=0, Ts,2Ts,…,NTs, TsTo record the sampling period of data, N + 1 is total sampling number of effective flutter flight test；Discrete time t is obtained by flutter flight testk=0, Ts,2Ts,…, NTsMoment body shafting xi,yi,zi, i=1,2 ..., the x of n mesh pointsix(tk)、yiy(tk)、ziz(tk) and ΘtTest value；
Step 4：According to body shafting coordinate grid point xi,yi,zi, i=1,2 ..., n install miniature X, Y, Z axis to air-flow Sensor especially installs miniature X, Y, Z axis to gas flow transducer in wing upper and lower and all rudder face both sides, determines tk=0, Ts,2Ts,…,NTsMoment body shafting xi,yi,zi, i=1,2 ..., the excitation function of n
To X [xix(t),yix(x),zix(x),Θt,t]、Y[xiy(y),yiy(t),ziy(y),Θt,t]、Z[xiz(z),yiz (z),ziz(t),Θt, t] and it given function is respectively adopted approaches, it obtains：
AndIt can continuously be led about x, It can continuously be led about y,It can continuously be led about z；In this way, can obtain：
And
Step 5：It enables：
And
(1) formula can be described as：
It enables
In formula：
px=[px(0) px(1) … px(mx-1) px(mx)],py=[py(0) py(1) … py(my-1) py(my)],
mx、my、mzTo correspond toLegendre expansion order；
For m=mx,my,mzThe recursive form of rank Legendre's orthogonal polynomial, b >=max (e) can be obtained
In formula,
Work as mx、my、mzFor odd number when, m=2,4 ..., mmax+ 1, mmax=mxOr mmax=myOr mmax=mz, work as mx、my、mz For even number when, m=3,5 ..., mmax+ 1, mmax=mxOr mmax=myOr mmax=mz；
It enables
Axi(xix,Θt)=paxξx(xix),Bxi(xix,Θt)=pbxξx(xix),Ayi(yiy,Θt)=payξy(yiy),Byi (yiy,Θt)=pbyξy(yiy),Azi(ziz,Θt)=pazξz(ziz),Bzi(ziz,Θt)=pbzξz(ziz),
In formula：
pax=[ax(0) ax(1) … ax(mx-1) ax(mx)],pbx=[bx(0) bx(1) … bx(mx-1) bx (mx)],
pay=[ay(0) ay(1) … ay(my-1) ay(my)],pby=[by(0) by(1) … by(my-1) by (my)],
paz=[az(0) az(1) … az(mz-1) az(mz)],pbz=[bz(0) bz(1) … bz(mz-1) bz (mz)],
It can obtain
Or it is write as
It is right by taking (3) formula first item as an example
Both sides It asksPartial derivative can obtain
The x obtained according to step 3 and step 4ix(tk)、yiy(tk)、ziz(tk) andtk=0, Ts,2Ts,…,NTsAnd ΘtTest value, can obtain：
In formula,
And then it can obtain：It brings into
It can be with According to the following formula and least-squares estimation obtains px

Claims (1)

1. a kind of aircraft flutter analysis grid model Legendre's modeling method, feature include the following steps：
Step 1：With the complicated flutter model of aircraft body shafting OXYZ analyses, n mesh point is chosen in body shafting:xi,yi, zi, i=1,2 ..., n, mesh point dynamic three shaft position component x (y, z, t), y (x, z, t), z (x, y, t) they are time t when vibration With the function of other two shaft positions, for the ease of expression, with xixFor (y, z, t), subscript i=1,2 ..., n are mesh point mark Number, subscript second letter x, y, z indicate that vibration is examined in three axis components of body shafting OXYZ in order to simplify problem respectively Consider the i-th=1, when the x-axis direction of 2 ..., n mesh point is vibrated, x (y, z, t)=xix(t), y (x, z, t)=yix(x),z(x, Y, t)=zix(x), consider the i-th=1, when the y-axis direction of 2 ..., n mesh point vibrates, x (y, z, t)=xiy(y),y(x,z, T)=yiy(t), z (x, y, t)=ziy(y), consider the i-th=1, when the z-axis direction of 2 ..., n mesh point vibrates, x (y, z, t) =xiz(z), y (x, z, t)=yiz(z), z (x, y, t)=ziz(t)；
It is in the built-in vertical approximate model of grid vertex neighborhood：
In formula, X [xix(t),yix(x),zix(x),Θt, t] and it is in body shafting coordinate xi,yi,ziX axis in grid neighborhood of a point Oscillating function, Axi[xix(t),yix(x),zix(x),Θt]、Bxi[xix(t),yix(x),zix(x),Θt] it is X axis vibration equation Structural coefficient function, xix(t),yix(x),zix(x) it is respectively in body shafting coordinate grid point xi,yi,zi, i=1,2 ..., Correspond to x when X axis vibrates at ni,yi,ziChanging value；Y[xiy(y),yiy(t),ziy(y),Θt, t] and it is to be sat in body shafting Mark xi,yi,ziY-axis oscillating function, A in grid neighborhood of a pointyi[xiy(y),yiy(t),ziy(y),Θt]、Byi[xiy(y),yiy (t),ziy(y),Θt] be Y-axis vibration equation structural coefficient function, xiy(y),yiy(t),ziy(y) it is respectively in axis It is coordinate net lattice point xi,yi,zi, i=1,2 ..., correspond to x when Y-axis is vibrated at ni,yi,ziChanging value；Z[xiz(z),yiz (z),ziz(t),Θt, t] and it is in body shafting coordinate xi,yi,ziZ axis is to oscillating function, A in grid neighborhood of a pointzi[xiz(z), yiz(z),ziz(t),Θt]、Bzi[xiz(z),yiz(z),ziz(t),Θt] it is structural coefficient function of the Z axis to vibration equation, xiz (z),yiz(z),ziz(t) it is respectively in body shafting coordinate grid point xi,yi,zi, i=1,2 ..., Z axis is to when vibration pairs at n It should be in xi,yi,ziChanging value；ui(xi,yi,zi,Θt, t) and it is in xi,yi,ziThe equivalent excitation function of mesh point, t are the time； Θt=[Ti H Ma Fzi ρ]TFor parameter vector, TiIndicate xi,yi,ziThe temperature of mesh point, H are flying height, MaFor Mach Number, FziFor xi,yi,ziThe air-flow environment of mesh point influences, and ρ is atmospheric density；
Step 2：The body shafting coordinate grid point x of corresponding step 1i,yi,zi, i=1,2 ..., n, installation Miniature temperature sensing Device, X, Y, Z axis to air-flow, position and vibrating sensor, especially wing upper and lower and all rudder face both sides install miniature X, Y, Z axis installs the image recording sensor observation more than 1000 frames/second additional to air-flow, position and vibrating sensor, while in fuselage Wing tip, the vibration amplitude of all rudder faces and frequency；Aircraft airborne sensor records time, flying height, Mach number, air Density；
Step 3：The process of flutter test after aircraft arrival assigned altitute and Mach number is expressed as effective flutter flight test, Effective flutter flight test data sampling time is tk=0, Ts,2Ts,…,NTs, TsTo record the sampling period of data, N+1 is Total sampling number of effective flutter flight test；Discrete time t is obtained by flutter flight testk=0, Ts,2Ts,…,NTsWhen Carve body shafting xi,yi,zi, i=1,2 ..., the x of n mesh pointsix(tk)、yiy(tk)、ziz(tk) and ΘtTest value；
Step 4：According to body shafting coordinate grid point xi,yi,zi, i=1,2 ..., n install miniature X, Y, Z axis and are sensed to air-flow Device especially installs miniature X, Y, Z axis to gas flow transducer in wing upper and lower and all rudder face both sides, determines tk=0, Ts, 2Ts,…,NTsMoment body shafting xi,yi,zi, i=1,2 ..., the excitation function of n
To X [xix(t),yix(x),zix(x),Θt,t]、Y[xiy(y),yiy(t),ziy(y),Θt,t]、Z[xiz(z),yiz(z), ziz(t),Θt, t] and it given function is respectively adopted approaches, it obtains：
AndIt can continuously be led about x,It closes It can continuously be led in y,It can continuously be led about z；In this way, can obtain：
And
Step 5：It enables：
And
(1) formula can be described as：
It enables
In formula：
px=[px(0) px(1) … px(mx-1) px(mx)],py=[py(0) py(1) … py(my-1) py(my)],
pz=[pz(0) pz(1) … pz(mz-1) pz(mz)],
mx、my、mzTo correspond toLegendre expansion order；
For m=mx,my,mzThe recursive form of rank Legendre's orthogonal polynomial, b >=max (| e |), it can obtain
In formula,
Work as mx、my、mzFor odd number when, m=2,4 ..., mmax+ 1, mmax=mxOr mmax=myOr mmax=mz, work as mx、my、mzFor idol When number, m=3,5 ..., mmax+ 1, mmax=mxOr mmax=myOr mmax=mz；
It enables
Axi(xix,Θt)=paxξx(xix),Bxi(xix,Θt)=pbxξx(xix),Ayi(yiy,Θt)=payξy(yiy),Byi(yiy, Θt)=pbyξy(yiy),Azi(ziz,Θt)=pazξz(ziz),Bzi(ziz,Θt)=pbzξz(ziz),
In formula：
pax=[ax(0) ax(1) … ax(mx-1) ax(mx)],pbx=[bx(0) bx(1) … bx(mx-1) bx(mx)],
pay=[ay(0) ay(1) … ay(my-1) ay(my)],pby=[by(0) by(1) … by(my-1) by(my)],
paz=[az(0) az(1) … az(mz-1) az(mz)],pbz=[bz(0) bz(1) … bz(mz-1) bz(mz)],
It can obtain
Or it is write as
It is right by taking (3) formula first item as an example
It asks on both sidesPartial derivative can obtain
The x obtained according to step 3 and step 4ix(tk)、yiy(tk)、ziz(tk) andtk=0, Ts, 2Ts,…,NTsAnd ΘtTest value, can obtain：
In formula,
And then it can obtain：It brings intoIt can be with According to the following formula and least-squares estimation obtains px
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