【摘要】：復(fù)合材料憑借其比強度及比剛度高、抗疲勞及抗腐蝕性能好等優(yōu)越性在航空器的設(shè)計制造方面得到了極大應(yīng)用。隨著飛機(jī)結(jié)構(gòu)整體化設(shè)計的發(fā)展,構(gòu)件和緊固件數(shù)量的大大減少,連接傳遞的載荷變得更大,因此連接成為更加關(guān)鍵的結(jié)構(gòu)。復(fù)合材料連接中,因結(jié)構(gòu)的形狀和材料的間斷極易引起高應(yīng)力集中,加之鋪層方式導(dǎo)致其各向異性,更增加了連接結(jié)構(gòu)的復(fù)雜程度。沉頭螺栓在具有良好的氣動外形的同時可以減小孔邊應(yīng)力,還可抑制損傷向孔邊擴(kuò)展,在飛機(jī)連接中具有十分廣泛的應(yīng)用。本文對復(fù)合材料-鈦合金沉頭螺栓單剪搭接接頭進(jìn)行研究,分別建立單釘和雙釘兩種模型,采用改進(jìn)的Tserpes失效準(zhǔn)則,充分考慮了拉伸和擠壓狀態(tài)下的基體損傷、纖維斷裂、基體-纖維剪切和分層等失效模式,并采用其改進(jìn)的材料性能退化準(zhǔn)則,在纖維損傷擴(kuò)展至板寬或板端邊緣為接頭最終失效判據(jù)的基礎(chǔ)上,增加孔邊局部擠壓損傷導(dǎo)致復(fù)合材料板最終失效的判據(jù),同時,沉頭螺栓剪切斷裂也作為一種接頭最終失效的判據(jù)被考慮在內(nèi),利用ANSYS的二次開發(fā)語言APDL將上述準(zhǔn)則編程并嵌入到主程序中,實現(xiàn)參數(shù)化建模,并通過試驗對比,驗證了仿真模型的正確性;討論了鋪層方式、锪孔深度、擰緊力矩、板寬及端距等接頭參數(shù)對連接強度及初始損傷的影響,并利用MATLAB軟件對各參數(shù)與最終失效強度的關(guān)系進(jìn)行優(yōu)化處理,進(jìn)一步選出接頭的最優(yōu)參數(shù);對采用最優(yōu)參數(shù)的接頭進(jìn)行漸進(jìn)損傷過程的可視化分析,分別對比了單釘接頭鋪層角度為0°、45°、-45°和90°鋪層從產(chǎn)生初始損傷,到損傷擴(kuò)展最后導(dǎo)致接頭最終失效的損傷擴(kuò)展過程,對雙釘接頭不同角度鋪層分析的同時,更加詳盡地對沿復(fù)合材料板厚度方向不同位置鋪層的損傷擴(kuò)展情況進(jìn)行對比分析。
[Abstract]:The composite material has been widely used in the design and manufacture of aircraft because of its advantages such as high specific strength and stiffness, good fatigue resistance and corrosion resistance. With the development of aircraft structure integrated design, the number of components and fasteners is greatly reduced, and the load transferred by the connection becomes larger, so the connection becomes a more critical structure. Due to the high stress concentration caused by the shape and discontinuity of the structure and the anisotropy caused by the layering mode, the complex degree of the connection structure is increased. The countersunk head bolt has good aerodynamic shape and can reduce the stress of the hole edge and restrain the damage spreading to the edge of the hole. It is widely used in aircraft connection. In this paper, the single shear lap joint of composite material and titanium alloy countersunk bolt is studied. Two models of single nail and double nail are established, and the modified Tserpes failure criterion is adopted to fully consider the matrix damage and fiber fracture under the condition of tensile and extrusion. The matrix fiber shear and delamination failure modes are adopted, and the improved degradation criterion of material properties is adopted. The ultimate failure criterion of the joint is fiber damage extending to the width of the plate or the edge of the end of the plate. The ultimate failure criterion of composite plate caused by increasing the local extrusion damage at the hole edge is also taken into account as a criterion of ultimate failure of joint, and the shear fracture of countersunk bolt is also taken into account. The above criteria are programmed and embedded into the main program by using the secondary development language APDL of ANSYS, and the parameterized modeling is realized, and the correctness of the simulation model is verified by experiment and comparison. This paper discusses the influence of the joint parameters, such as laying mode, countersink depth, tightening torque, plate width and end distance, on the connection strength and initial damage, and optimizes the relationship between each parameter and the ultimate failure strength by using MATLAB software. The optimal parameters of the joint are further selected. The progressive damage process of joints with optimal parameters is analyzed visually, and the initial damage is compared between 0 擄, 45 擄, -45 擄and 90 擄laying angles of single nail joints, respectively. In the process of damage propagation which leads to the ultimate failure of the joint, the damage propagation in different positions along the thickness of the composite plate is compared and analyzed in more detail, while the different angles of the double nailed joint are analyzed.
【學(xué)位授予單位】：鄭州大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2017
【分類號】：TB33;TH131.3

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