Design, Analysis And Experimental Study Of One Kind Of Strain Sensor For Vibration Measurement On Solar Wing

The solar wing is the most widely used in space vehicle among varieties of solar arrays. With the development of large space vehicles, such as observation satellites and space stations, the solar wings as the power of vehicles become more large with lower mass. For example, the solar wing of International Space Station is a typical kind of solar wing with large flexible blanket. Profited from low mass blankets, the mass of the solar wing decreases and the ratio of power to mass increases, which satisfied large vehicles.Nevertheless, the solar wings with large deployable structures generally have extremely low base frequency, poor damping and dense frequencies. As a result, it is difficult for solar wings to stop vibrating once the vibration occurs that threatens normal operation of the space vehicle. So it is necessary to control the vibration of solar wings. Vibration control of solar wings is based on the real time effective vibration measurement. Thus, for vibration control of solar wings, it does make sense to design a kind of sensor for vibration measurement which can be used in extreme space environment.The studies included in this thesis are as follows:Firstly, the difficulties of vibration measurement on solar wings and the literature of sensor for vibration measurement are reviewed.Secondly, the theory of strain measurement is stated, and the design principle of the stain sensor which is suitable for vibration measurement on solar wings is explained. Based on that, a kind of stain sensor named stain gauge array is designed.Thirdly, based on the modal analysis of solar wings, the method and the key index of the strain sensor’s position selection on solar wings is puted forward. In addition, the position where strain sensors fixed on is determined by the numerical analysis of strain sensor’s position selection on solar wings. And then, the contrast test and study of the strain sensors in different positions of solar wings is maken.Lastly, based on the analysis of thermal expansion of composites, the substrate which is suitable for the strain sensor is confirmed via the vacuum thermo-cycling experiments of strain sensors with different substrates. And the effectiveness, reliability, and stability of the strain sensor is evaluated via the vibration measurement on solar wings and the vacuum thermo-cycling experiments of strain sensors fixed on the solar wing.