CN104075868B - Aerodynamic load loading method used for reliability tests on aircraft flap and slat system - Google Patents
Aerodynamic load loading method used for reliability tests on aircraft flap and slat system Download PDFInfo
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Abstract
本发明涉及一种用于飞机襟、缝翼系统可靠性试验的气动载荷加载方法，该具体过程为：步骤a，通过风洞试验或仿真计算获得缝翼在各个飞行状态下的气动载荷；步骤b，根据飞机缝翼在不同飞行状态下的气动载荷，计算各个飞行状态下缝翼翼面气动载荷的合力；步骤c，根据各个飞行状态下飞机缝翼翼面气动载荷的合力，将其分解为若干个分力，获得分力的大小与方向；步骤d，通过胶布带和杠杆系统，将上述步骤c的分力均布并加载至缝翼翼面。在本发明考虑了飞行周期内，缝翼各个状态下的气动载荷；试验或仿真获得的气动载荷能够有效地转换为在试验中实现的加载方式，并保证了气动载荷的真实。
The present invention relates to a kind of aerodynamic load loading method that is used for the reliability test of aircraft flap, slat wing system, and this specific process is: step a, obtain the aerodynamic load of slat wing under each flight state through wind tunnel test or simulation calculation; b. According to the aerodynamic load of the aircraft slat in different flight states, calculate the resultant force of the aerodynamic load on the slat surface in each flight state; step c, decompose it into several obtain the magnitude and direction of the component force; step d, distribute the force component of the above step c evenly and load it on the slat airfoil through the adhesive tape and the lever system. The present invention considers the aerodynamic loads of the slats in various states within the flight cycle; the aerodynamic loads obtained by tests or simulations can be effectively converted into the loading modes realized in the tests, and the authenticity of the aerodynamic loads is guaranteed.
Description
技术领域technical field
本发明涉及飞机零部件可靠性试验领域，尤其涉及一种用于飞机襟、缝翼系统可靠性试验的气动载荷随动加载方法。The invention relates to the field of reliability tests of aircraft components, in particular to an aerodynamic load follow-up loading method for reliability tests of aircraft flap and slat systems.
背景技术Background technique
飞机襟、缝翼在民用飞机的飞行过程中起着重要作用，其作用主要有两个：一是延缓机翼上的气流分离，提高了飞机的临界迎角，使得飞机在更大的迎角下才会发生失速；二是增大机翼的升力系数。飞机襟、缝翼运动机构发生故障会对飞机的安全产生很大影响，甚至造成机毁人亡的严酷后果。Aircraft flaps and slats play an important role in the flight process of civil aircraft. There are two main functions: one is to delay the separation of airflow on the wings, which increases the critical angle of attack of the aircraft, so that the aircraft can fly at a greater angle of attack. The second is to increase the lift coefficient of the wing. The failure of the aircraft flap and slat movement mechanism will have a great impact on the safety of the aircraft, and even cause severe consequences of aircraft crash and death.
基于襟、缝翼系统对飞机飞行安全的重要性，要求襟、缝翼系统具有较高的可靠度。而为评估现有襟、缝翼系统设计方案的可靠性指标，并获得提高襟、缝翼系统的可靠性水平的改进措施，实现襟、缝翼系统的可靠性增长，必须对襟、缝翼系统进行可靠性分析。针对机械产品的可靠性分析，目前主要存在两种手段，即仿真和试验。但由于技术水平的限制和大型复杂机械产品的复杂性，目前可靠性仿真并不能完全取代可靠性试验。Based on the importance of the flap and slat system to aircraft flight safety, the flap and slat system is required to have high reliability. However, in order to evaluate the reliability index of the existing flap and slat system design schemes, obtain improvement measures to improve the reliability level of the flap and slat system, and realize the reliability increase of the flap and slat system, it is necessary to study the flap and slat system. Perform a reliability analysis. For the reliability analysis of mechanical products, there are currently two main means, namely simulation and test. However, due to the limitation of technical level and the complexity of large and complex mechanical products, reliability simulation cannot completely replace reliability test at present.
现有技术中，若对襟、缝翼系统进行飞行试验，其不但成本高昂，而且风险较大，一旦出现襟、缝翼系统不能正常收放的故障，极有可能造成飞机坠毁的严重事故。因此需要一种能在地面对襟、缝翼系统进行可靠性试验的试验方法和装置；而针对此类机械产品的试验，现有试验方法往往没有考虑缝翼在飞行过程中气动载荷对襟、缝翼系统性能的影响，模拟的环境条件不够真实。In the prior art, if the flap and slat system is to be tested for flight, it is not only expensive, but also risky. Once the flap and slat system cannot be retracted normally, it is very likely to cause a serious accident of aircraft crash. Therefore need a kind of test method and device that can carry out reliability test on flap, slat system on the ground; And for the test of this kind of mechanical product, existing test method often does not consider the aerodynamic load of slat to flap, slat during flight. The impact of system performance, the simulated environmental conditions are not realistic enough.
鉴于上述缺陷，本发明创作者经过长时间的研究和实践终于获得了本创作。In view of the above-mentioned defects, the author of the present invention has finally obtained this creation through long-term research and practice.
发明内容Contents of the invention
本发明的目的在于提供一种用于飞机襟、缝翼系统可靠性试验的气动载荷加载方法，用以克服上述技术缺陷。The object of the present invention is to provide an aerodynamic load loading method for the reliability test of the aircraft flap and slat system, so as to overcome the above-mentioned technical defects.
为实现上述目的，本发明提供一种用于飞机襟、缝翼系统可靠性试验的气动载荷加载方法，该具体过程为：In order to achieve the above object, the present invention provides a kind of aerodynamic load loading method for the reliability test of aircraft flap, slat system, and this specific process is:
步骤a，通过风洞试验或仿真计算获得缝翼在各个飞行状态下的气动载荷；Step a, obtain the aerodynamic load of the slat in each flight state through wind tunnel test or simulation calculation;
步骤b，根据飞机缝翼在不同飞行状态下的气动载荷，计算各个飞行状态下缝翼翼面气动载荷的合力；Step b, according to the aerodynamic loads of the aircraft slats in different flight states, calculate the resultant force of the aerodynamic loads on the slat surface in each flight state;
步骤c，根据各个飞行状态下飞机缝翼翼面气动载荷的合力，将其分解为若干个分力，获得分力的大小与方向；Step c, according to the resultant force of the aerodynamic load on the slat wing surface of the aircraft in each flight state, decompose it into several component forces, and obtain the magnitude and direction of the component forces;
步骤d，通过胶布带和杠杆系统，将上述步骤c的分力均布并加载至缝翼翼面。Step d, uniformly distribute and load the component force of the above step c to the slat airfoil through the adhesive tape and the lever system.
进一步，上述步骤a中，飞机缝翼翼面气动载荷求取的具体过程为：Further, in the above step a, the specific process of calculating the aerodynamic load of the aircraft slat wing surface is as follows:
步骤a1，获得缝翼飞行周期内所有的工况；Step a1, obtain all operating conditions in the slat flight cycle;
步骤a2，根据飞机缝翼收放试验要求，编制飞行收放工况；Step a2, according to the requirements of the aircraft slat retraction test, prepare the flight retraction and deployment conditions;
步骤a3，使用风洞试验或数值计算确定各个工况下缝翼的气动载荷，得到的每个工况下气动载荷在翼面的分布情况；Step a3, using wind tunnel test or numerical calculation to determine the aerodynamic load of the slat under each working condition, and obtain the distribution of the aerodynamic load on the airfoil under each working condition;
每个工况下得到一个文件用于存储缝翼翼面气动载荷，文件内数据各列分别为翼面结点编号、翼面结点坐标位置、翼面结点气动载荷在X、Y、Z方向上的分力；In each working condition, a file is obtained to store the aerodynamic load of the slat wing surface. The data columns in the file are the number of the airfoil node, the coordinate position of the airfoil node, and the aerodynamic load of the airfoil node in the X, Y, and Z directions. on the component force;
步骤a4，判断全部工况是否计算完成，若没有完成，则继续进行缝翼气动载荷计算，若完成计算，则整理编号每个工况下缝翼气动载荷数据文件；Step a4, judging whether the calculation of all working conditions is completed, if not, continue to calculate the aerodynamic load of the slat wing, and if the calculation is completed, sort and number the data files of the aerodynamic load of the slat wing under each working condition;
其中，将缝翼沿翼展方向定义为Y向，垂直缝翼翼面方向定义为X向，与缝翼翼面相切并垂直翼展方向定义为Z向。Among them, the direction along the span of the slat is defined as the Y direction, the direction perpendicular to the slat surface is defined as the X direction, and the direction tangent to the slat surface and perpendicular to the span is defined as the Z direction.
进一步，在上述步骤b中，飞机缝翼翼面气动载荷合力求取的具体过程为：Further, in the above step b, the specific process of obtaining the resultant force of the aerodynamic load on the slat surface of the aircraft is as follows:
步骤b1，把缝翼气动载荷数据文件依照一个试验周期的先后次序编号；Step b1, numbering the slat aerodynamic load data files according to the sequence of a test cycle;
步骤b2，根据第一个工况下缝翼气动载荷数据，使用力的合成原则，列出四个分力X、Y、Z方向上气动载荷合力方程；Step b2, according to the aerodynamic load data of the slat wing under the first working condition, using the combination principle of force, list the resultant force equation of the aerodynamic load in the directions of four component forces X, Y, and Z;
步骤b3，根据第一个工况下缝翼气动载荷数据，使用压心位置力矩为零原则，列出X、Y、Z方向上气动载荷合力矩方程；Step b3, according to the aerodynamic load data of the slat under the first working condition, using the principle that the pressure center position moment is zero, list the aerodynamic load resultant moment equations in the X, Y, and Z directions;
步骤b4，求解前两个步骤的方程，分别获得此工况下缝翼气动载荷的合力大小与方向以及合力在缝翼翼面的位置坐标；Step b4, solving the equations of the first two steps, respectively obtaining the magnitude and direction of the resultant force of the aerodynamic load on the slat under this working condition and the position coordinates of the resultant force on the slat wing surface;
步骤b5，去除每个工况下合力Y向力，记录存储此工况下缝翼气动载荷的合力大小与方向以及合力在缝翼翼面的位置坐标；Step b5, remove the resultant Y-direction force under each working condition, record and store the resultant force magnitude and direction of the slat aerodynamic load under this working condition and the position coordinates of the resultant force on the slat wing surface;
步骤b6，判断全部工况合力计算是否完成，如未完成，则执行步骤b7，依次进行下一个工况合力计算，如完成，则执行步骤b8，结束缝翼气动载荷合力计算。Step b6, judging whether the calculation of the resultant force of all operating conditions is completed, if not, execute step b7, and proceed to the calculation of the resultant force of the next operating condition in turn, if completed, execute step b8, and end the calculation of the resultant force of the slat aerodynamic load.
进一步，在上述步骤c中，飞机缝翼翼面气动载荷分配的具体过程为：Further, in the above step c, the specific process of aerodynamic load distribution on the slat surface of the aircraft is:
步骤c1，在缝翼翼面上标注全部工况下合力作用点位置；Step c1, mark the position of the resultant force action point under all working conditions on the slat airfoil;
步骤c2，拟定加载点围成的平行四边形的上下边，与Y轴平行，并在全部工况下合力作用点位置的两侧，并且此对平行边位置不能在缝翼的大曲率前缘和薄后缘处；Step c2, the upper and lower sides of the parallelogram surrounded by the loading points are drawn up, parallel to the Y axis, and on both sides of the point where the resultant force acts under all working conditions, and the position of the pair of parallel sides cannot be between the large curvature leading edge of the slat and at the thin trailing edge;
步骤c3，拟定加载点围成的平行四边形的另一对平行边，将合力作用点到平行四边形的与Y轴平行的两条边距离比值记为a(a＜1)，将合力作用点到平行四边形的与另一对边距离比值记为b(b＜1)；Step c3, draw another pair of parallel sides of the parallelogram surrounded by loading points, record the ratio of the distance between the resultant force point and the two sides of the parallelogram parallel to the Y axis as a (a<1), and set the resultant force point to The ratio of the distance between the parallelogram and the opposite side is recorded as b (b<1);
步骤c4，把全部合力作用点的a和b求出；Step c4, calculate a and b of all resultant force points;
步骤c5，若不满足要求则调整加载点构成的平行四边形的平行Y轴的对边，若满足要求则执行下述步骤；Step c5, if the requirements are not met, then adjust the opposite side of the parallelogram formed by the loading point parallel to the Y axis, and if the requirements are met, perform the following steps;
步骤c6，若不满足要求则调整加载点构成的平行四边形的另一对边，若满足要求，则执行下述步骤；Step c6, if the requirements are not met, then adjust the other pair of sides of the parallelogram formed by the loading point, if the requirements are met, then perform the following steps;
步骤c7，进行全部气动载荷合力的分配；Step c7, performing distribution of all aerodynamic load resultant forces;
步骤c8，获取四个加载载荷；Step c8, obtain four loading loads;
步骤c9，整理四个加载点随襟翼试验周期内的力大小与方向。Step c9, arrange the force magnitude and direction of the four loading points along with the flap test cycle.
进一步，在上述步骤c8中，Further, in the above step c8,
每个工况下四个加载点的载荷分别是 The loads of the four loading points in each working condition are
进一步，在上述步骤d中，飞机缝翼翼面胶布带和杠杆系统分布的具体过程为：Further, in the above step d, the specific process of the distribution of the aircraft slat wing surface adhesive tape and the lever system is:
步骤d1，选取一个加载点；Step d1, selecting a loading point;
步骤d2，在此加载点的平行Y轴的直线上，以此点为中点，两边各安装二个胶布带，此四个胶布带位置应均匀在此加载点所在的四分之一缝翼翼面区域内；Step d2, on the straight line parallel to the Y-axis of this loading point, with this point as the midpoint, install two adhesive tapes on each side, and the four adhesive tapes should be evenly positioned on the quarter of the slat wing where the loading point is located. within the surface area;
步骤d3，在此四个胶布带上安装杠杆系统，使用一根钢索连接杠杆系统上端，实现气动载荷加载；Step d3, install a lever system on the four tapes, and use a steel cable to connect the upper end of the lever system to realize aerodynamic loading;
步骤d4，判断四个加载点的胶布带和杠杆系统是否全部安装完毕，如未安装完成，则执行步骤d5，继续依次安装，如安装完成，则执行步骤d6，完成加载。Step d4, judging whether the adhesive tapes and lever systems at the four loading points are all installed, if not, execute step d5, and continue to install sequentially, if the installation is complete, execute step d6, to complete loading.
与现有技术相比较本发明的有益效果在于：在本发明飞机襟、缝翼系统试验中，考虑了飞行周期内，缝翼各个状态下的气动载荷；试验或仿真获得的气动载荷能够有效地转换为在试验中实现的加载方式，并保证了气动载荷的真实；缝翼受到的气动载荷通过转换为若干个分布在翼面若干块区域内的载荷，在缝翼运动的每个工况下，该若干个分力的方向始终相同，试验加载过程中容易控制与实现，在襟、缝翼运动过程中能根据襟、缝翼位置实时控制所模拟的气动力大小、方向、压心等参量；在试验加载中，通过加载点周围胶布带的分布，保证了缝翼结构受力均匀，不会产生与实际不符的过大载荷而导致试验件的破坏。Compared with the prior art, the present invention has the beneficial effects that: in the test of the aircraft flap and slat system of the present invention, the aerodynamic loads in each state of the slats have been considered in the flight cycle; the aerodynamic loads obtained by the test or simulation can effectively It is converted to the loading method realized in the test, and the aerodynamic load is guaranteed to be true; the aerodynamic load on the slat is converted into several loads distributed in several areas of the airfoil, and in each working condition of the slat movement , the direction of the several force components is always the same, and it is easy to control and realize during the test loading process. During the movement of the flaps and slats, the parameters such as the magnitude, direction, and center of pressure of the simulated aerodynamic force can be controlled in real time according to the positions of the flaps and slats. ;During the test loading, the distribution of the adhesive tape around the loading point ensures that the slat structure is evenly stressed, and will not cause damage to the test piece due to excessive load that is inconsistent with the actual situation.
附图说明Description of drawings
图1为本发明可靠性试验的气动载荷加载方法的流程图；Fig. 1 is the flowchart of the aerodynamic load loading method of reliability test of the present invention;
图2a为本发明飞机缝翼翼面试验或仿真获得气动载荷分布图；Fig. 2 a obtains aerodynamic load distribution figure for aircraft slat wing surface test or simulation of the present invention;
图2b为本发明飞机缝翼翼面气动载荷合力分布图；Fig. 2 b is the resultant force distribution diagram of the aerodynamic load on the aircraft slat wing surface of the present invention;
图2c为本发明飞机缝翼翼面四个加载力的分布图；Fig. 2c is the distribution diagram of four loading forces on the aircraft slat airfoil of the present invention;
图2d为本发明飞机缝翼翼面上胶布带分布图；Fig. 2 d is the distribution diagram of adhesive tape on the aircraft slat wing surface of the present invention;
图3为本发明飞机缝翼翼面气动载荷求取的流程图；Fig. 3 is the flow chart that the aerodynamic load of aircraft slat wing surface of the present invention obtains;
图4为本发明飞机缝翼翼面气动载荷合力求取的流程图；Fig. 4 is the flow chart that the resultant force of aircraft slat surface aerodynamic load of the present invention seeks;
图5为本发明飞机缝翼翼面气动载荷分配的流程图；Fig. 5 is the flow chart of aircraft slat wing surface aerodynamic load distribution of the present invention;
图6为本发明飞机缝翼翼面胶布带和杠杆系统分布的流程图。Fig. 6 is the flowchart of the distribution of the adhesive tape and the lever system of the aircraft slat wing surface of the present invention.
具体实施方式detailed description
以下结合附图，对本发明上述的和另外的技术特征和优点作更详细的说明。The above and other technical features and advantages of the present invention will be described in more detail below in conjunction with the accompanying drawings.
请参阅图1所示，其为本发明可靠性试验的气动载荷加载方法的流程图，该具体过程为：Please refer to shown in Fig. 1, it is the flowchart of the aerodynamic load loading method of reliability test of the present invention, and this specific process is:
步骤a，通过风洞试验或仿真计算获得缝翼在各个飞行状态下的气动载荷；Step a, obtain the aerodynamic load of the slat in each flight state through wind tunnel test or simulation calculation;
步骤b，根据飞机缝翼在不同飞行状态下的气动载荷，计算各个飞行状态下缝翼翼面气动载荷的合力；Step b, according to the aerodynamic loads of the aircraft slats in different flight states, calculate the resultant force of the aerodynamic loads on the slat surface in each flight state;
步骤c，根据各个飞行状态下飞机缝翼翼面气动载荷的合力，将其分解为若干个分力，获得分力的大小与方向；Step c, according to the resultant force of the aerodynamic load on the slat wing surface of the aircraft in each flight state, decompose it into several component forces, and obtain the magnitude and direction of the component forces;
步骤d，通过胶布带和杠杆系统，将上述步骤c的分力均布并加载至缝翼翼面。Step d, uniformly distribute and load the component force of the above step c to the slat airfoil through the adhesive tape and the lever system.
本发明实施例，将缝翼沿翼展方向定义为Y向，垂直缝翼翼面方向定义为X向，与缝翼翼面相切并垂直翼展方向定义为Z向。In the embodiment of the present invention, the direction along the span of the slat is defined as the Y direction, the direction perpendicular to the slat airfoil is defined as the X direction, and the direction tangent to the slat airfoil and perpendicular to the span is defined as the Z direction.
将气动载荷合力分为四个分力，四个分力的位置构成一个平行四边形，将合力作用点到平行四边形的与Y轴平行的两条边距离比值记为a(a＜1)，将合力作用点到平行四边形的与另一对边距离比值记为b(b＜1)。Divide the resultant force of the aerodynamic load into four components, and the positions of the four components form a parallelogram. The ratio of the distance between the resultant force point and the two sides parallel to the Y-axis of the parallelogram is recorded as a (a<1), and The ratio of the distance between the resultant force point to the parallelogram and the other opposite side is denoted as b (b<1).
请结合图2a、2b、2c和2d所示，其分别为飞机缝翼翼面试验或仿真获得气动载荷分布图；飞机缝翼翼面气动载荷合力分布图；飞机缝翼翼面四个加载力的分布图；飞机缝翼翼面上胶布带分布图。Please combine Figures 2a, 2b, 2c and 2d, which are the aerodynamic load distribution diagram obtained from the test or simulation of the aircraft slat wing surface; the distribution diagram of the resultant force of the aerodynamic load on the aircraft slat wing surface; ; The distribution map of the adhesive tape on the aircraft slat wing surface.
请参阅图3所示，其为本发明飞机缝翼翼面气动载荷求取的流程图，该具体过程为：Please refer to shown in Fig. 3, it is the flow chart that the aircraft slat wing surface aerodynamic load of the present invention obtains, and this specific process is:
步骤a1，获得缝翼飞行周期内所有的工况；Step a1, obtain all operating conditions in the slat flight cycle;
步骤a2，根据飞机缝翼收放试验要求，编制飞行收放工况；Step a2, according to the requirements of the aircraft slat retraction test, prepare the flight retraction and deployment conditions;
步骤a3，使用风洞试验或数值计算确定各个工况下缝翼的气动载荷，得到的每个工况下气动载荷在翼面的分布情况如图2a所示，每个工况下得到一个.dat文件用于存储缝翼翼面气动载荷，文件内数据各列分别为翼面结点编号、翼面结点坐标位置、翼面结点气动载荷在X、Y、Z方向上的分力；Step a3, using wind tunnel test or numerical calculation to determine the aerodynamic load of the slat under each working condition, the distribution of the aerodynamic load on the airfoil under each working condition is shown in Figure 2a, and one is obtained for each working condition. The dat file is used to store the aerodynamic load of the slat wing surface, and each column of the data in the file is the number of the airfoil node, the coordinate position of the airfoil node, and the components of the aerodynamic load of the airfoil node in the X, Y, and Z directions;
步骤a4，判断全部工况是否计算完成，若没有完成，则继续进行缝翼气动载荷计算，若完成计算，则整理编号每个工况下缝翼气动载荷.dat数据文件。Step a4, judge whether the calculation of all working conditions is completed, if not, continue to calculate the aerodynamic load of the slat wing, if the calculation is completed, sort and number the aerodynamic load of the slat wing under each working condition.dat data file.
请参阅图4所示，其为本发明飞机缝翼翼面气动载荷合力求取的流程图，该具体过程为：Please refer to shown in Fig. 4, it is the flow chart that the resultant force of aircraft slat wing surface aerodynamic load of the present invention seeks, and this specific process is:
步骤b1，把缝翼气动载荷.dat数据文件依照一个试验周期的先后次序编号；Step b1, numbering the slat aerodynamic load.dat data file according to the sequence of a test cycle;
步骤b2，根据第一个工况下缝翼气动载荷数据，使用力的合成原则，列出四个分力X、Y、Z方向上气动载荷合力方程；Step b2, according to the aerodynamic load data of the slat wing under the first working condition, using the combination principle of force, list the resultant force equation of the aerodynamic load in the directions of four component forces X, Y, and Z;
步骤b3，根据第一个工况下缝翼气动载荷数据，使用压心位置力矩为零原则，列出X、Y、Z方向上气动载荷合力矩方程；Step b3, according to the aerodynamic load data of the slat under the first working condition, using the principle that the pressure center position moment is zero, list the aerodynamic load resultant moment equations in the X, Y, and Z directions;
步骤b4，求解前两个步骤的方程，分别获得此工况下缝翼气动载荷的合力大小与方向以及合力在缝翼翼面的位置坐标；Step b4, solving the equations of the first two steps, respectively obtaining the magnitude and direction of the resultant force of the aerodynamic load on the slat under this working condition and the position coordinates of the resultant force on the slat wing surface;
步骤b5，去除该工况下合力Y向力，记录存储此工况下缝翼气动载荷的合力大小与方向以及合力在缝翼翼面的位置坐标；Step b5, remove the resultant Y-direction force under this working condition, record and store the resultant force magnitude and direction of the slat aerodynamic load under this working condition and the position coordinates of the resultant force on the slat wing surface;
由于Y向力相对于X和Z向力来看，很小，可忽略。Since the Y-direction force is small relative to the X- and Z-direction forces, it can be ignored.
步骤b6，判断全部工况合力计算是否完成，如未完成，则执行步骤b7，依次进行下一个工况合力计算，如完成，则执行步骤b8，结束缝翼气动载荷合力计算；全部工况合力分布参见图2b。Step b6, judge whether the calculation of the resultant force of all working conditions is completed, if it is not completed, perform step b7, and proceed to the calculation of the resultant force of the next working condition in turn, if completed, perform step b8, and end the calculation of the resultant force of the slat aerodynamic load; See Figure 2b for the distribution.
请参阅图5所示，其为本发明飞机缝翼翼面气动载荷分配的流程图，该具体过程为：Please refer to shown in Fig. 5, it is the flow chart of aircraft slat wing surface aerodynamic load distribution of the present invention, and this specific process is:
步骤c1，在缝翼翼面上标注全部工况下合力作用点位置；Step c1, mark the position of the resultant force action point under all working conditions on the slat airfoil;
步骤c2，拟定加载点围成的平行四边形的上下边，与Y轴平行，并在全部工况下合力作用点位置的两侧，并且此对平行边位置不能在缝翼的大曲率前缘和薄后缘处；Step c2, the upper and lower sides of the parallelogram surrounded by the loading points are drawn up, parallel to the Y axis, and on both sides of the point where the resultant force acts under all working conditions, and the position of the pair of parallel sides cannot be between the large curvature leading edge of the slat and at the thin trailing edge;
步骤c3，拟定加载点围成的平行四边形的另一对平行边；Step c3, drawing up another pair of parallel sides of the parallelogram surrounded by the loading points;
步骤c4，把全部合力作用点的a和b求出；Step c4, calculate a and b of all resultant force points;
步骤c5，若不满足要求，则调整加载点构成的平行四边形的平行Y轴的对边，若满足要求则执行下述步骤；Step c5, if the requirements are not met, then adjust the opposite side of the parallelogram formed by the loading points parallel to the Y axis, and if the requirements are met, perform the following steps;
步骤c6，若不满足要求则调整加载点构成的平行四边形的另一对边，若满足要求，则执行下述步骤；Step c6, if the requirements are not met, then adjust the other pair of sides of the parallelogram formed by the loading point, if the requirements are met, then perform the following steps;
步骤c7，进行全部气动载荷合力的分配；Step c7, performing distribution of all aerodynamic load resultant forces;
步骤c8，获取四个加载载荷；Step c8, obtain four loading loads;
每个工况下四个加载点的载荷分别是 The loads of the four loading points in each working condition are
步骤c9，整理四个加载点随襟翼试验周期内的力大小与方向；分配后的分力位置参见图2c所示。Step c9, arrange the force magnitude and direction of the four loading points along with the flap test cycle; the position of the component force after distribution is shown in Figure 2c.
请参阅图6所示，其为本发明飞机缝翼翼面胶布带和杠杆系统分布的流程图；该具体过程为：Please refer to shown in Fig. 6, it is the flow chart of aircraft slat wing surface adhesive tape of the present invention and lever system distribution; This specific process is:
步骤d1，选取一个加载点；Step d1, selecting a loading point;
步骤d2，在此加载点的平行Y轴的直线上，以此点为中点，两边各安装二个胶布带，此四个胶布带位置应均匀在此加载点所在的四分之一缝翼翼面区域内；Step d2, on the straight line parallel to the Y-axis of this loading point, with this point as the midpoint, install two adhesive tapes on each side, and the four adhesive tapes should be evenly positioned on the quarter of the slat wing where the loading point is located. within the surface area;
步骤d3，在此四个胶布带上安装杠杆系统，使用一根钢索连接杠杆系统上端，实现气动载荷加载；Step d3, install a lever system on the four tapes, and use a steel cable to connect the upper end of the lever system to realize aerodynamic loading;
步骤d4，判断四个加载点的胶布带和杠杆系统是否全部安装完毕，如未安装完成，则执行步骤d5，继续依次安装，如安装完成，则执行步骤d6，完成加载；胶布带安装分布参见图2d。Step d4, judge whether the adhesive tapes and lever systems at the four loading points are all installed, if not, proceed to step d5, and continue to install in sequence, if the installation is complete, proceed to step d6, to complete the loading; refer to Figure 2d.
在本发明飞机襟、缝翼系统试验中，考虑了飞行周期内，缝翼各个状态下的气动载荷；试验或仿真获得的气动载荷能够有效地转换为在试验中实现的加载方式，并保证了气动载荷的真实；缝翼受到的气动载荷通过转换为若干个分布在翼面若干块区域内的载荷，在缝翼运动的每个工况下，该若干个分力的方向始终相同，试验加载过程中容易控制与实现，在襟、缝翼运动过程中能根据襟、缝翼位置实时控制所模拟的气动力大小、方向、压心等参量；在试验加载中，通过加载点周围胶布带的分布，保证了缝翼结构受力均匀，不会产生与实际不符的过大载荷而导致试验件的破坏。In the test of the aircraft flap and slat system of the present invention, the aerodynamic loads under the various states of the slats have been considered in the flight cycle; the aerodynamic loads obtained by the test or simulation can be effectively converted into the loading mode realized in the test, and ensured The reality of the aerodynamic load; the aerodynamic load on the slat is converted into several loads distributed in several areas of the airfoil. In each working condition of the slat movement, the direction of the several component forces is always the same. The test load The process is easy to control and realize. During the movement of the flaps and slats, the simulated aerodynamic force, direction, pressure center and other parameters can be controlled in real time according to the positions of the flaps and slats; The distribution ensures that the slat structure is evenly stressed and will not cause damage to the test piece due to excessive load that is inconsistent with the actual situation.
以上所述仅为本发明的较佳实施例，对发明而言仅仅是说明性的，而非限制性的。本专业技术人员理解，在发明权利要求所限定的精神和范围内可对其进行许多改变，修改，甚至等效，但都将落入本发明的保护范围内。The above descriptions are only preferred embodiments of the present invention, and are only illustrative rather than restrictive to the present invention. Those skilled in the art understand that many changes, modifications, and even equivalents can be made within the spirit and scope defined by the claims of the invention, but all will fall within the protection scope of the present invention.
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| CN106557599B (en) * | 2015-09-29 | 2019-11-15 | 中国飞机强度研究所 | A kind of space force system loading spectrum preparation method |
| CN106021781B (en) * | 2016-05-31 | 2020-10-23 | 中国航空工业集团公司西安飞机设计研究所 | Universal airplane fuselage axis type load processing method |
| CN106586029B (en) * | 2016-12-28 | 2019-06-11 | 中国航空工业集团公司西安飞机设计研究所 | A test system for high lift control system |
| CN107063837A (en) * | 2017-03-23 | 2017-08-18 | 西安飞机工业（集团）有限责任公司 | A kind of radome test load(ing) point determines method |
| CN108999890B (en) * | 2018-08-31 | 2019-08-30 | 西北工业大学 | A spline combination sequence selection method and spline assembly for improving spline life |
| CN109387357B (en) * | 2018-11-02 | 2020-02-21 | 北京航空航天大学 | A kind of wing aerodynamic load simulation loading device and method |
| CN109612697B (en) * | 2018-12-07 | 2020-06-30 | 中国飞机强度研究所 | Distributed pressure water load test loading method |
| CN110543687A (en) * | 2019-08-02 | 2019-12-06 | 西安飞机工业（集团）有限责任公司 | airplane load design method |
| CN113063570B (en) * | 2019-12-27 | 2023-09-05 | 中国航空工业集团公司西安飞机设计研究所 | Slat load loading method in full-size fatigue test of aircraft |
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