Experiment on weight efficient support structure by using dynamic opinionto accommodate a typical sensor on spacecraft

Abstract

An artificial satellite is a human made structure, which is put into space around any planetary body to gather data and impart the equivalent information to ground stations. There is a huge requirement of several types of satellite sensors which are to be mounted on spacecraft or Satellite payloads. To accommodate sensors on Spacecraft, mounting structural elements are needed to support them. This project is mainly focused on the study of those mounting configurations with modeling and analysis of support structure used to mount Sensor in aerospace application. Different configuration of support structure modeled based on the frequency (100 Hz). These models were analyzed to optimize the mass. Work involves modal analysis of the structure made of aluminum and composite material (CFRP). The configuration of mounting structure for sensors is based on various constraints like interface requirements, functional requirement of sensor, stiffness, strength and most importantly the mass. Various configurations of the support structure have to be studied using modeling and analysis software keeping in view the stiffness requirement with minimum mass. For efficient design, composite materials are considered. Normal modal analysis will be carried out to understand the dynamic characteristics of the Mounting structure and the supporting structure was modeled using Al-7075 and CFRP (Composite) materials and the results are compared in the present study.