Design and development of inter-satellite separation mechanism for Twin Nano satellite — STUDSAT-2
This paper describes the detailed design, development and dynamic analysis of Separation Mechanism for Twin Nano-satellite “STUDSAT-2”. The separation mechanism system is interfaced between the two nano-satellites, STUDSAT-2A and STUDSAT-2B. After the ejection from the PSLV (Polar Satellite Launch Vehicle), due to stability constraints, the satellite is required to remain composite for an estimated period of 3 orbits before separation. Developing a reliable separation mechanism to sustain the launch vehicle vibrations and the space environment is of highest importance. Different design approaches and actuation strategies have been examined to ensure a uniform separation with least disturbance due to mechanically constrained surfaces. The analytical calculation to achieve the required relative velocity of the two satellite with respect to center of mass of the composite structure is performed and same has been validated using ANSYS rigid dynamics tool. Furthermore, the tool is also used to validate structural rigidity.
ANSYS Workbench Tutorial Release 13
The exercises in ANSYS Workbench Tutorial Release 13 introduce the reader to effective engineering problem solving through the use of this powerful modeling, simulation and optimization tool. Topics that are covered include solid modeling, stress analysis, conduction/convection heat transfer, thermal stress, vibration and buckling. It is designed for practicing and student engineers alike and is suitable for use with an organized course of instruction or for self-study. Table of Contents 1. Solid Modeling Fundamentals 2. Placed Features, Assembly 3. Modeling Techniques 4. ANSYS Mechanical I 5. ANSYS Mechanical II 6. Wizards & Tools 7. Heat Transfer & Thermal Stress 8. Surface & Line Models 9. Natural Frequencies & Buckling Loads
Reliability Analysis Method of Deployment Mechanism of a Satellite Solar Arrays
The reliability analysis method of deployment mechanism solar arrays was proposed.Firstly,the composing of solar arrays and its deployment mechanism were introduced and the fault tree of the deployment system was built in order to qualitative analysis and quantitative analysis.Form analysis there are conclusion that the shortage of moments of twisting spring and the seizure of mechanism are the key problems which lead to the invalidation of solar arrays deployment mechanism and some methods and suggestions that to prevent those problems are also presented in the paper.Furthermore,the reliability modeling and analysis method of deployment mechanism solar arrays were proposed from three aspects of static torque margin,torque and the power by torque.