【作者】 周莹；

【导师】 宋汉文；

【作者基本信息】 复旦大学 ， 工程力学， 2008， 硕士

【摘要】 卫星及其部件在主动飞行段中都需要经历多种复杂动力学环境,可能发生失效。为了保证卫星能够经受这些恶劣的环境条件而不遭受损坏,必须把它们放在模拟这些力学环境的地面设备中进行环境试验。传统的加速度控制试验,由于试验条件定得太严格,会产生“过试验”现象,即造成产品原本在实际工作环境下能正常工作,却在振动试验中却受到不应有的损坏。力限控制试验技术是加速度和力的双重控制的试验方法,它是一种比较合理“过试验”改善试验技术。本文针对加速度试验的“过试验”原理,力限控制试验的“过试验”改善原理,力限控制试验条件,卫星振动台仿真试验,星-箭耦合载荷分析等相关问题展开了研究。本文主要工作如下:1.以被试卫星结构和振动台为统一研究对象进行星-台组合结构动力学建模针对不同台面控制方式展开分析,导出了“飞行环境”、“加速度控制”和“力限控制”三种不同环境模式下的界面加速度、界面力与卫星测点加速度等表达公式。通过分析比较,合理地解释了过试验的原因以及力限控制对于过试验的补偿作用。2.研究了力限控制条件的制定方法。采用复杂二自由度简化模型导出了星-箭组合结构界面力与加速度之间的动力学转换关系,给出了界面力限控制条件的计算公式。藉此,验证了美国航空航天局(NASA)文献中提供的计算公式的正确性,进一步给出了具体的计算步骤,并且数值算例验证了公式的合理性和可靠性。3.将复杂二自由度方法应用于卫星振动台仿真试验。进行了星-箭耦合飞行仿真计算,卫星振动台仿真计算。通过不同控制环境下界面力、界面加速度和卫星测点加速度响应数据的比较,进一步验证了复杂二自由度方法的合理性、可靠性和工程实用性,同时也验证了力限控制试验对于加速度“过试验”的改善效果。更多还原

【Abstract】 The satellite and its assemblies have to suffer from complicated dynamic environments in the active phase of flight, which is probably to cause failure. In order to protect the satellite from failures in such harsh environments, environmental vibration tests must be carried out in the laboratory first of all to simulate its performances in these environments. Due to the conservative conditions of traditional acceleration vibration tests, a so-called "over-test" phenomenon will occur. That is to say, although the satellite works well in practical working conditions, it suffers failure in the vibration test which should not happen. Force Limited Vibration Test (FLV) is a kind of test method to control the interface force and acceleration at the same time, which can reasonably compensate the over-test phenomenon. This article deals with issues such as over-test theory of acceleration tests, over-test compensation, test conditions for force limited control, simulation test of satellite vibration platform, satellite-rocket coupling analysis, etc.The main content of the article is as follows:1. To regard the tested satellite and the vibration platform as a united object and set dynamic models for the coupling system. Expressions of interface acceleration, interface force and satellite acceleration are deduced under three different working conditions: satellite-rocket flight condition, acceleration control vibration test condition and force limited control vibration test condition. By means of detailed analysis and comparison, the reasons for over-test and over-test compensation are reasonably explained.2. The method to establish force-limited conditions is investigated. A complex two degree of freedom (CTDOF) model is generated to deduce the relation of dynamics between the interface force and acceleration. A formula to calculate the force value is also given. In this way, the formula provided in the related NASA literatures is verified and proved to be correct. Further more, the rationality and reliability of the formula is verified by means of a numerical simulation example.3. The CTDOF method is applied to the simulation test of satellite vibration platform. The satellite-rocket coupled flight and the satellite vibration test are simulated in the article. The rationality, reliability and practicability of the CTDOF model are verified by means of the response data comparison among different kinds of simulations. At the same time, the compensation effect of the force limited control test to improve over-test phenomenon is also validated.更多还原