摘要：【中文】本申请涉及一种航空发动机关键件使用寿命监控方法，通过在传统的关键件寿命监控方法基础上，增加考虑相关外部作用力参数的影响，对每种超机动飞行动作在飞行过程中机动过载和角速度的变化历程进行分析，将影响关键件寿命的参数如转速、过载系数、偏航角速度和俯仰角速度等分段进行统计，并按区间进行综合计数，将每个典型区间的外部作用力载荷参数与采用标准载荷谱的地面寿命试验结果建立数学公式表达的折算关系，定量给出了外部作用力对发动机关键件使用寿命的影响。本申请的方法为超机动飞行用法和关键件载荷分析、寿命监控提供了系统、有效的方法和操作流程，同时考虑外部作用力影响，提高工作效率，保证飞行安全，节约使用成本。 【EN】The application relates to a method for monitoring the service life of a key part of an aircraft engine, which is characterized in that on the basis of the traditional method for monitoring the service life of the key part, the influence of relevant external acting force parameters is additionally considered, the change process of the mechanical overload and the angular velocity of each type of super-maneuvering flight action in the flight process is analyzed, the parameters influencing the service life of the key part, such as the rotating speed, the overload coefficient, the yaw angular velocity, the pitch angular velocity and the like, are counted in sections, comprehensive counting is carried out according to the sections, the reduced relation expressed by a mathematical formula is established between the external acting force load parameters of each typical section and the ground service life test result adopting a standard load spectrum, and the influence of the external acting force on the service life of the key part of the engine is quantitatively given. The method provides a system, an effective method and an operation flow for the super-maneuvering flight usage, key part load analysis and service life monitoring, simultaneously considers the influence of external acting force, improves the working efficiency, ensures the flight safety and saves the use cost.

摘要：【中文】本申请属于航空发动机试验技术领域，具体涉及一种航空推力矢量发动机地面试车方法。所述方法包括：获取航空发动机的空中工况的第一油门杆位置载荷谱、第一偏转角载荷谱及第一方位角载荷谱；将第一方位角载荷谱在时间轴上划分为若干任务段；确定各任务段的地面试验偏转方位角，由此形成第二方位角载荷谱；将第一油门杆位置载荷谱及第一偏转角载荷谱进行任务段划分；确定由各任务段的地面试验的油门杆位置构成的第二油门杆位置载荷谱；计算空中工况下的矢量喷管侧向推力；根据矢量喷管侧向推力及第二油门杆位置载荷谱计算地面试验的第二偏转角载荷谱；根据第二油门杆位置载荷谱、第二偏转角载荷谱及第二方位角载荷谱进行矢量发动机地面试车试验。 【EN】The application belongs to the technical field of aero-engine tests, and particularly relates to a ground test run method of an aero-thrust vector engine. The method comprises the following steps: acquiring a first throttle lever position load spectrum, a first deflection angle load spectrum and a first azimuth angle load spectrum of an aerial working condition of the aircraft engine; dividing the first azimuth load spectrum into a plurality of task segments on a time axis; determining a ground test deflection azimuth angle of each task segment, thereby forming a second azimuth load spectrum; performing task segment division on the first throttle lever position load spectrum and the first deflection angle load spectrum; determining a second throttle lever position load spectrum formed by the throttle lever positions of the ground tests of each task segment; calculating the lateral thrust of the vectoring nozzle under the air working condition; calculating a second deflection angle load spectrum of the ground test according to the lateral thrust of the vectoring nozzle and the load spectrum of the position of the second throttle lever; and performing a vector engine ground test according to the second throttle lever position load spectrum, the second deflection angle load spectrum and the second azimuth angle load spectrum.