A Review on Composite Bonded Repair Technique for Damaged Aircraft Structures
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1 ( ) ( ) 30, 10,,,,, A Review on Composite Bonded Repair Technique for Damaged Aircraft Structures Tong Gusheng Sun Liangxin ( School of Aircraft Aerospace, Nanjing University of Aeronautics and Astronautics Nanjing ) Liu Yingwei ( Hongdu Aviation Industry Groups Nanchang ) Abstract To extend the service life of aging or damaged aircraft, the damaged components must be replaced or re2 paired. A adhesively bonded technique of composite to repair damaged aircraft has been developed since 1970s. By using a series of character of the advanced composites, such as high strength ratio and stiffness ratio, the damaged component can be effectively repaired. Research achievements of the composite bonded repair technique applied to damaged aircraft structure are reviewed,and problems to be solved in the future are presented. Key words Damage repair,composite material,aircraft structure,nondestructive testing,smart structure 1,, / /,,, :; [ 13 ], (AMRL) Alan Baker, (CFRP) (BFRP) (RAAF) C 130 F C 141 C 141B, 1989, : ,1962,,
2 500 [4 ] [5 ],Boeing Turaga [3 ],1998, ,, 2,,, ( ),,,,,,,,,,,,, [6 ] : (1) ( ) ; (2) (, ) ; (3) () ; (4) ; (5), (1) (2) 2. 1,,, : (1), ; (2), ; (3),,, Lamb Michael [7 ],Lamb, Lamb Vary [8 ], 2. 2 (),,, Mirage [9 ],, : (1) ; (2) ; (3) [6 ] (1) K K = 0 (1) = E P t P /(1 + t P E P / E r t r ) (2) 0 =E P t P / ( E P t P + E r t r ) (3) = t A / G A + t r / 3 G r + t P / 3 G P ( t A / G A + 3 t r / 8 G r + 3 t P / 8 G P ) 2 (4) 21
3 t A t P t r, E G, A P r (1) (2) f f = t P (1 + P) / t r (5) P = ( q - 1) / D[2 qm (1 - ) q ] (6) D = (2 q/ m + 1) (2 qm + 1) - [+ (1 - ) q ] 2 (7) q = E I / E P (8) E I = E P + E r t r / t P (9) m = a/ b ; (1) (2) (3) K max BC K max = (1 + 2 BC) K (10) BC = y max a (1 - K P K S ) t P ( t P + t r ) / I (11) K S ; K P ; y max ; I ; a (10),(1) (4) max max = K 0 / 2 E P (12) K= 1/ ( t A / G A + 3 t r / G r + 3 t P / 8 G P ) (13) W [10 ] W = P 2 / (16 Et r t A ) (14), Mitchell [11 ],,,, AMRL Jones Callinan [12 ], Callinan [13 ],,,,Jones [14 ], [15 ], [16 ] Sun [17,18 ],Mindlin, [17 ], [ 18 ] Mindlin 10 %, Naboulsi Mall [19 ],, Sun [18 ],,, [20 ] ( ) Naboulsi [21 ], Naboulsi Mall [22 ],, : (1)
4 ,, ; (2), ; (3) Chue [23 ],,, Frank [24 ] NASTRAN,,,, ; 3. 2 Rose [25 ] Zhu Lam [26 ],, 6 Schubbe Mall [27 ] mm 2024 T3 / (),, Young [28 ],Liu Fam [29 ] Green, , 20 80,, 1995 AIAA,Chaudhly [30 ] /, Baker, [9 ],Chiu [31 ],, [ 32 ],( FAA) (RAPID),, 3. 3, [ 32 ] 20 80, [33 ] : (1), ; (2),; (3), [34 ] Robson [34 ],0. 5 %, 1. 3 %20 %, Ahn Springer [35 ] Soutis [36 ] 23
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6 ,, 1,..,1988 ;15 (4) : Yang J M, Ma CL, Chou T W. Fiber inclination of three2 dimensional structural composites. Journal of Composite Material, 1986 ;20 (9) : ,..,1993 ;14 (3) : Kalidindi Surya R, Eric Franco. Numerical evaluation of isostrain and weighted2average models for elastic moduli of three2di2 mensional composite. Composite Science and Technology,1997 ;57 : ,,..,1999 ;16 (3) : ,,..,2000 ;17 (2) : Soheil Mohajerjasbi. Predictions for coefficients of thermal expansion of three2dimensional braided composites. AIAA,1997 ; 35 (1) : Pandey R,Hahn H T. Visualization of representative vol2 ume elements for three2dimensional four2step braided composites. Composite Science and Technology,1996 ;56 : ,..,2000 ;17 (3) :15 10 Pandey R, Hahn H T. Designing with 42step braided fab2 ric composites. Composite Science and Technology ;56 : ( ) (24 ) bonded reinforcements. Int. J. Solids Struct.,1981 ;17 : Zhu C,Lam Y C. Analysis of one side repair to a cracked thick plate. In : Proceedings of international conference on fracture, ICF29,1997 : Schubbe J J,Mall S. Investigation of a cracked thick alu2 minum panel repaired with a bonded composite patch. Engineering Fracture Mechanics,1999 ;63 : Young A,Rooke D P,Cartwright D J. Numericcal study of balanced repairs to cracked sheets. Aero. J, 1989 ;93 : Liu T, Fan W. Analysis for an adhesively bonded finite strip repair to a cracked plate. Engng. Fract. Mech.,1994 ;47 : Chaudhry Z etc. Monitoring the integrity of composite patch structural repair via piezoelectric actuators/ sensors. In : Pro2 ceedings of AIAA/ ASME/ AHS/ ASC 36 th SDM conference, New Or2 leans,la,1995 ;4 : Chiu W K etc. Smart structure application in bonded re2 pairs. Composite Structures,2000 ;50 : Backukas J etc. Engineering approach to damage tolerance analysis of fuselage skin repairs. DOT/ FAA/ AR295/ 75, Finn S R etc. Compressive strength of damaged and re2 paired composite plate. Journal of Composite Materials, 1992 ; 26 (12) : John S J etc. Measuring and predicting the durability of bonded carbon fibre/ epoxy composite joint. Composites, 1991 ; 22 (2) : Ahn S H etc. Repair of composite laminates2 :models. Journal of Composite Materials,1998 ;32 (11) : Hu F Z, Soutis C. Strength prediction of patch2repaired CFRP laminates loaded in compression. Technology,2000 ;60 : Composite Science and ( )
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