摘要：【中文】本发明属于飞机结构设计领域，具体涉及一种基于刚度的翼盒选型方法。本发明通过盒段剖面扭转刚度与剖面质量的效率比进行快速的盒段方案对比和选择，特别适合于翼盒中的重要承载结构梁的个数和位置的确定；本发明所具有的优点是能够实现不同翼盒布置方案的快速对比，有效提高了飞机设计初期方案的迭代速度且对翼盒的刚度指标进行了评估。 【EN】The invention belongs to the field of airplane structure design, and particularly relates to a wing box type selection method based on rigidity. The invention carries out rapid box section scheme comparison and selection through the efficiency ratio of the box section torsional rigidity to the section quality, and is particularly suitable for determining the number and the position of important bearing structural beams in a wing box; the method has the advantages that the rapid comparison of different wing box arrangement schemes can be realized, the iteration speed of the scheme at the initial stage of the airplane design is effectively improved, and the rigidity index of the wing box is evaluated.

摘要：【中文】本发明属于航空航天、交通运输载具、建筑工程、机械工程技术领域，涉及一种吸波蜂窝结构。本发明将浸有功能树脂的棉、化学或高分子或金属纤维分布在蜂窝芯的内部六边形面上，通过调整纤维材料、浸润的功能材料、纤维直径和纤维分布密度和分布图案，形成不同的谐振腔。利用形成谐振腔和纤维本身的作用，可以使声波在蜂窝结构中形成谐振和损耗，从而达到吸波的目的。 【EN】The invention belongs to the technical field of aerospace, transportation vehicles, construction engineering and mechanical engineering, and relates to a wave-absorbing honeycomb structure. The invention distributes cotton, chemical or macromolecule or metal fiber which is soaked with functional resin on the internal hexagonal surface of the honeycomb core, and forms different resonant cavities by adjusting fiber material, soaked functional material, fiber diameter and fiber distribution density and distribution pattern. By utilizing the functions of forming the resonant cavity and the fibers, the sound waves can form resonance and loss in the honeycomb structure, thereby achieving the purpose of absorbing the waves.

摘要：【中文】本发明属于复合材料强度技术领域，涉及一种复合材料胶接修理结构强度评估方法。本发明使用ABAQUS用户子程序VUMAT编写复合材料本构关系，cohesive界面单元模拟胶接界面，使用Hashin准则、二次名义应力准则，以及基于能量的连续退化方式，分别模拟复合材料、胶接界面的初始失效和渐进损伤过程；基于试验方法，设计轴压和剪切情况下复合材料加筋壁板三维模型的边界和载荷施加方法；采用ABAQUS显示动力学方法计算复合材料加筋壁板胶接修理结构的强度；采用稳定性分析与显示动力学方法相结合的方法计算复合材料加筋壁板完好结构的强度。利用上面的技术，用来对复合材料加筋壁板修理结构进行有限元仿真分析，并对其原始结构、损伤结构进行强度对比，实现修理方案的可设计性。 【EN】The invention belongs to the technical field of composite material strength, and relates to a method for evaluating the strength of a composite material cementing repair structure. The method comprises the steps of writing a composite material constitutive relation by using an ABAQUS user subprogram VUMAT, simulating a cementing interface by using a harmonic interface unit, and respectively simulating the initial failure and progressive damage processes of the composite material and the cementing interface by using a Hashin criterion, a secondary nominal stress criterion and an energy-based continuous degradation mode; designing a boundary and a load application method of a three-dimensional model of the composite material reinforced wall plate under the conditions of axial compression and shearing based on a test method; calculating the strength of the composite material reinforced wall plate cementing repair structure by using an ABAQUS display dynamics method; and calculating the strength of the intact structure of the composite material reinforced wall plate by adopting a method combining stability analysis and a display dynamics method. The technology is used for carrying out finite element simulation analysis on the repair structure of the composite material reinforced wall plate, and comparing the strength of the original structure and the damaged structure, so that the designability of the repair scheme is realized.

摘要：【中文】本发明属于航空航天、交通运输载具、建筑工程、机械工程技术领域，涉及一种消音蜂窝结构。本发明将棉、化学或高分子或金属纤维分布在蜂窝芯的内部六边形面上，通过调整纤维材料、纤维直径和纤维分布密度和分布图案，形成不同的谐振腔。利用形成谐振腔和纤维本身的作用，可以使声波在蜂窝结构中形成谐振和损耗，从而达到消声的目的。 【EN】The invention belongs to the technical field of aerospace, transportation vehicles, constructional engineering and mechanical engineering, and relates to a noise reduction honeycomb structure. The invention distributes cotton, chemical or macromolecule or metal fiber on the internal hexagonal surface of the honeycomb core, and forms different resonant cavities by adjusting fiber material, fiber diameter, fiber distribution density and distribution pattern. By utilizing the functions of forming a resonant cavity and fibers, the sound waves can form resonance and loss in the honeycomb structure, so that the aim of silencing is fulfilled.

摘要：【中文】本发明实施例公开了一种主承力层压板的胶接修理方法，包括：对主承力层压板的待修补区域进行受力形式的工程分析，确定待修补区域的受力形式；根据主承力层压板的修补区域和已确定的受力形式，对待修补区域制定修理方案；根据待修补区域的受力形式，确定修理方案的修理方式；对修理方案的修理方式进行使用范围的分析，得到使用范围分析结果；根据主承力层压板的受力特点和使用范围分析结果，确定出满足主承力层压板受力要求的修补方式。本发明实施例可以对复合材料的主承力板确定出一个最优修补方案，从而实现有效减轻结构重量的效果。 【EN】The embodiment of the invention discloses a glue joint repairing method of a main bearing laminated board, which comprises the following steps: carrying out engineering analysis of the stress form on the region to be repaired of the main bearing laminated board to determine the stress form of the region to be repaired; according to the repairing area of the main bearing laminated board and the determined stress form, a repairing scheme is made for the area to be repaired; determining a repair mode of a repair scheme according to the stress form of the area to be repaired; analyzing the use range of the repair mode of the repair scheme to obtain a use range analysis result; according to the stress characteristics and the application range analysis result of the main bearing laminated board, a repairing mode meeting the stress requirement of the main bearing laminated board is determined. The embodiment of the invention can determine an optimal repairing scheme for the main bearing plate made of the composite material, thereby realizing the effect of effectively reducing the weight of the structure.

摘要：【中文】本发明属于航空航天技术领域，涉及一种用于飞机复合材料结构胶接修理装置及修理方法；包括便携加热装置、便携真空装置，便携温度测量装置、移动通信终端；便携温度测量装置上的温度监控装置通过热电偶连接导线连接便携式加热装置上的热电偶，监控电热毯上各处温度，并通过蓝牙发射系统发送至手机APP；手机APP通过与内部设置的加热历程曲线对比，计算出温度差值，并通过蓝牙发射装置控制加热装置上的电源系统来调整加热电量。与现有技术相比，本发明提供了用于飞机复合材料结构胶接修理的快速方法，通过便携装置和手机控制可以取消对一般使用热补仪修理的限制，更好的保证飞机运营时的快速修理，提高产品修理质量。 【EN】The invention belongs to the technical field of aerospace, and relates to a glue joint repairing device and a repairing method for an airplane composite material structure; the device comprises a portable heating device, a portable vacuum device, a portable temperature measuring device and a mobile communication terminal; the temperature monitoring device on the portable temperature measuring device is connected with a thermocouple on the portable heating device through a thermocouple connecting lead, monitors the temperature of each part on the electric blanket and sends the temperature to the mobile phone APP through the Bluetooth transmitting system; cell-phone APP calculates the temperature difference through the heating process curve contrast with inside setting to power system through bluetooth emitter control heating device goes up adjusts the heating electric quantity. Compared with the prior art, the invention provides a quick method for the adhesive joint repair of the composite material structure of the airplane, the limit on the repair of a general hot patching instrument can be eliminated through the control of the portable device and the mobile phone, the quick repair of the airplane during operation can be better ensured, and the repair quality of products is improved.

摘要：【中文】本发明实施例提供一种大中型飞机的双铰链方向舵结构，包括：前方向舵(1)和后方向舵(2)；前方向舵(1)连接在飞机的垂直安定面后缘悬挂支臂上；后方向舵(2)连接在前方向舵(1)上。该双铰链方向舵结构由前方向舵结构与后方向舵结构两部分组成，后方向舵的偏转角度为前方向舵的2倍。该双铰链方向舵结构增大了方向舵的舵面面积和偏转角度，提高了飞机的航向修正和转向速度。 【EN】The embodiment of the invention provides a double-hinge rudder structure of a large and medium-sized airplane, which comprises: a front rudder (1) and a rear rudder (2); the front rudder (1) is connected to a suspension support arm at the rear edge of a vertical stabilizer of the airplane; the rear rudder (2) is connected to the front rudder (1). The double-hinge rudder structure consists of a front rudder structure and a rear rudder structure, wherein the deflection angle of the rear rudder is 2 times of that of the front rudder. The double-hinge rudder structure increases the control surface area and the deflection angle of the rudder, and improves the course correction and the steering speed of the airplane.