DERIVATION OF MASS, STIFFNESS AND DAMPING MATRICES OF A MODEL WING FROM EXPERIMENTAL MODAL DATA

Transcription

1 SCIENTIFIC RESEARCH AND EDUCATION IN THE AIR FORCE AFASES2017 DERIVATION OF MASS, STIFFNESS AND DAMPING MATRICES OF A MODEL WING FROM EXPERIMENTAL MODAL DATA Ionel POPESCU, Lică FLORE, Alber ARNAU CUBILLO Insiue for Theoreical and Experimenal Analysis of Aero-Asronauical Srucures STRAERO S.A., Buchares, Romania (ionel.popescu@sraero.ro, lica.flore@sraero.ro, alber.acubillo@gmail.com) DOI: / Absrac: This paper presens he resuls of he experimenal modal analysis of a wing srucure along wih he derivaion of full mass, damping and siffness marices from modal parameers. Using he derived marices, he naural frequencies of he srucure were compued and compared wih he experimenally deermined ones. Very good correlaion was found, which confirms he validiy of he mehod. Keywords: experimenal modal analysis, mass, siffness, damping, mode shapes, frequencies 1. INTRODUCTION The specialized sysems for experimenal modal analysis do no usually provide mass, siffness and damping marices in spaial coordinaes bu he ones in he modal space. While he modal marices are very useful in a large number of engineering applicaions, here are cases in which marices in spaial coordinaes are preferred. Such a case is he acive conrol of aeroelasic oscillaions and fluer phenomena in which i would be difficul o express he aerodynamic forces in he modal space. To avoid such complicaions and o use he measured modal daa, a mehod of deriving hese marices in spaial coordinaes from he ones in modal space is needed. Such a mehod is well presened in [2] and is applied in our sudy on experimenal modal daa obained for a model wing aimed for fluer conrol experimens in aerodynamic wind unnel. More han he derivaion of mass, siffness and damping marices in spaial coordinaes from modal daa, his paper aims o validae he obained marices. To accomplish ha, he naural frequencies of he free undamped wing srucure are compued by using he derived mass and siffness marices. Very good correlaion is found beween he compued and he experimenally deermined naural frequencies. 2. EQUIPMENT USED AND TEST CONFIGURATION The Prodera insallaion is a modal analysis equipmen ha uses up o 16 unidirecional acceleromeers simulaneously o deermine he vibraion parameers of a srucure. Is sofware feaures pre, real-ime and pos processing ools ha allow o prepare and perform impulse and harmonic vibraion ess and o calculae modal parameers using specific mehods (power complex mehod, quadraure mehod). This sysem also provides graphical represenaion during and afer ess. The equipmen is picured in Fig. 1 wih a general view of he daa acquisiion, conrol and compuing cabine in (a) and elecromechanical shaker conneced o he es specimen in (b). 323

2 MECHANICAL ENGINEERING. MATERIALS AND TECHNOLOGY The sudied srucure is a model wing developed in he frame of a research projec for acive conrol of fluer phenomena. The wing has a 1.2m span, a 0.3m chord and is equipped wih a piezoelecric-acuaed conrol surface. For he purpose of he vibraion es, he conrol surface has been blocked in he neural posiion. The wing has been mouned verically by clamping i o a very rigid seel base on he ground and excied wih an elecromechanic shaker mouned in he horizonal direcion, as deailed in Fig.1 (b). (a) (b) FIG. 1. (a) Prodera equipmen, (b) Mechanical link beween excier and wing srucure The wing srucure is insrumened wih 11 acceleraion ransducers which are posiioned on he wing surface according o Fig. 2 (a), (b) and able 1. (a) FIG. 2. (a) Tes configuraion, (b) Geomery of digiized srucure Table 1. Posiion of Transducers and Shaker Poin No. Coord. in x [mm] Coord. in y [mm] Commen Transducer Transducer Transducer Transducer Transducer Transducer Transducer Transducer 8 (b) 324

3 SCIENTIFIC RESEARCH AND EDUCATION IN THE AIR FORCE AFASES2017 Poin No. Coord. in x [mm] Coord. in y [mm] Commen Transducer Transducer Transducer 11 and Shaker 3. TEST PROCEDURE AND RESULTS The experimenal procedure aimed o idenify he modal parameers of he wing srucure in hree phases, based on phase exciaion echnique. Firsly, he srucure has been excied from 0 o 50Hz wih a 0.1Hz sep, and a sabilizing ime of 10 seconds. The mode indicaor funcion (MIF), which is based on he fac ha a resonance real par of he FRF is zero, was applied on he acquired daa. This provided a general view of he number and locaion of naural frequencies in he ineres range 0-50Hz. Secondly, he srucure has been excied around each of hese frequencies, in separae ess, in a narrow range (+/- 0.3Hz), wih a sep of 0.001Hz, and adequae force exciaion and sabilizing ime. The mode indicaor funcion has been again applied o accuraely idenify he naural frequencies. The hird phase was mainly auomaed and consised in he exciaion of he srucure around each naural frequency wih auomaically seleced range, sep and oher parameers. The mehods used by Prodera [1] were: auomaic complex power (compues naural frequency, modal damping, mass and siffness associaed o he sudied mode), auomaic logarihmic decremen (compues modal damping), readou of he mode shape (compues mode shape), and phase index (compues he real and imaginary par of he acceleraion for he seleced frequency). The es resuls used for he purpose of his paper are presened in able 2. The mode shapes are graphically represened in Fig.3. The modal mass, damping and siffness marices are assembled in ables 3, 4 and 5. Table 2. Experimenal Modal Daa Mode 1 Mode 2 Mode 3 Mode 4 Mode 5 Frequency [Hz] Modal damping Modal mass [Kg*m 2 ] Modal siffness [Kg*m 2 /s 2 ] Transducer Mode shapes (no normalized) E E E E E E E E E E E E

4 MECHANICAL ENGINEERING. MATERIALS AND TECHNOLOGY (a) (b) (c) (d) (e) FIG. 3. Mode shapes: (a) Mode 1, (b) Mode 2, (c) Mode 3, (d) Mode 4, (e) Mode 5 Table 3. Modal Mass Marix Table 4. Modal Damping Marix Table 5. Modal Siffness Marix E E E E E

5 SCIENTIFIC RESEARCH AND EDUCATION IN THE AIR FORCE AFASES DERIVATION OF [M], [C], [K] MATRICES FROM EXPERIMENTAL MODAL DATA Once a se of modal daa has been measured for he wing srucure, i is possible o compue he full mass, siffness and damping marices (marices in spaial coordinaes). Formulas derived from he relaionship beween he ime domain differenial equaions of moion and he ransfer funcion marix model of he srucure are provided in [2]: M 1 m 1 (1) C 1 c 1 (2) K 1 k 1 (3) where u u u 1, 2,..., m - mode shape marix m, c, k M, C, K - modal mass, damping and siffness marices - full mass, damping and siffness marices The direc use of hese equaions is prohibiively difficul, especially when using experimenal modal daa, since he mode shape marix is usually no square (in our case is 11x5). To overcome his problem, an assumpion can be made [2]: if he mode shape vecors are assured o be orhogonal wih respec o one anoher (and are also normalized o uni magniudes), hen he mode shape marix has he following properies: I 1 1 (5) To ake advanage of his properies we used classical Gram-Schmid algorihm o oronormalize he mode shape marix of he wing srucure. The resul is presened in he nex able. Table 6. Mode Shape Marix normalized wih Gram-Schmid algorihm Mode 1 Mode 2 Mode 3 Mode 4 Mode 5 DOF E E E E-02 DOF E DOF DOF DOF DOF DOF DOF DOF DOF E E E E E-02 DOF E E (4) 327

6 MECHANICAL ENGINEERING. MATERIALS AND TECHNOLOGY Checking orogonaliy yields very good resuls: E E E E E E E E E E E E E E E E E E E E 17 I (6) Because he inverse of he mode shape marix is now equal o is ranspose, he formulas for full mass, siffness and damping marices are sraighforward [2]: M m (7) C c (8) K k (9) The resuled marices are presened in ables 7, 8 and 9: Table 7. Mass Marix in spaial coordinaes E E E E E E E E E E E E E E E E E E E E E E E E E E E E Table 8. Damping Marix in spaial coordinaes 1.01E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E

7 SCIENTIFIC RESEARCH AND EDUCATION IN THE AIR FORCE AFASES2017 Table 9. Siffness Marix in spaial coordinaes 2.56E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E E VALIDATION OF [M], [C], [K] MATRICES In absence of damping and exernal load, he equaion of moion in marix form for a given srucure is [3]: Mq Kq 0 (10) which, for solving, we assume a harmonic soluion of he form: q usin (11) Through differeniaion and subsiuion in equaion 10, he following is obained: M u sin K u sin 0 (12) 2 which afer simplifying becomes: 2 K M u 0 (13) This reduces o an eigenvalue problem of he basic form: AIx 0 By solving he eigenvalues problem we find he eigenvalues and eigenvecors associaed o he srucure. The i h eigenvalue i is relaed o he i h naural frequency f i as follows: i f i, i i (15) 2 The naural frequencies f i have been compued using mass [M] and siffness [K] marices, previously derived for he wing srucure, and he resuls are presened in he nex able along wih he experimenally deermined frequencies. Very good correlaion is found. (14) 329

8 MECHANICAL ENGINEERING. MATERIALS AND TECHNOLOGY Table 10. Compued and experimenal frequencies No. Compued frequencies Experimenal frequencies No CONCLUSIONS The experimenally deermined frequencies are all found hrough he numerical procedure wih very good accuracy. This confirms ha [M] and [K] marices accuraely describe he wing srucure (up o he fifh vibraion mode). This also confirms ha [C] marix, which was negleced in equaion 10, is indeed negligible, in line wih he small values presened in able 8. As can be seen in able 10, he compued frequencies no. 3,4,6,7,9 and 11 do no have correspondence in he se of experimenal frequencies. The experimenal modal analysis was performed in a very accurae manner and no oher naural frequency has been found beween he experimenal frequencies lised above. The values of hese addiional (compued) frequencies vary wih he qualiy of he mode shape marix orhonormalizaion (for example by using classical Gram-Schmid or modified Gram-Schmid mehods) and are a direc consequence of consrucing 11x11 mass, siffness and damping marices from experimenal modal daa gahered from only 5 modes of vibraion. AKNOWLEDGMENT This work was financially suppored by UEFISCDI wihin he frame of he research projec AFDPA - Ani fluer Demonsraor wih Piezoelecric Acuaion, conrac no. 289/2014. The es specimen was provided by INCAS - Naional Insiue for Aerospace Research "Elie Carafoli", he coordinaor of he aforemenioned projec. The ess were performed a STRAERO faciliies. REFERENCES [1] K. Dijksra, B. Marinez Vasquez, Modal Analysis Mehods, Prodera Manual, [2] M. H. Richardson, Derivaion of Mass, Siffness and Damping Parameers From Experimenal Modal Daa, Hewle Packard Company, Sana Clara Division, June, [3] SIEMENS, NASTRAN NX, Basic Dynamic Analysis User's Guide / Chaper 4: Real Eigenvalue Analysis (SOL 103) / 4.3 Overview of Normal Modes Analysis. Available a hps://docs.plm.auomaion.siemens.com/daa_services/resources/nxnasran/10/help/en_us/docex/pd f/basic_dynamics.pdf, accessed on 9 May