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Satellites are intended to be of massive cost, hard, or hard to keep up and fix in circle. The point of this task is to decide an effective strategy to decide the orbital and heading data for the Nano satellite. To design the exact trajectory and circle for a satellite, information regarding the components which are liable for the deviation in the method of satellites. The factors that should be taken into account to determine the exact location of the satellite. It could be accomplished with the assistance of software responsible for orbit simulation, to do programming with Orbitron so as to get the required output. Orbitron is a simple 2D solver in which TLE files are uploaded, for AAUSAT CUBESAT. The various impacts on the satellite in space are slight deviation in the satellite from its orbit. The motion of the body with includes the disturbing forces in the orbit. However, a satellite has deviated from its normal path due to several forces. This deviation is termed as orbital perturbation. The changes in the orbital element with respect to secular variations are considered using orbital quaternions. The output from satellite dynamic model is received from attitude sensor. The comparative data (Input and Feedback) will generate error signal. To minimize the error signal using proportional integral and derivative (PID) is proposed controller implemented with MATLAB environment. [ABSTRACT FROM AUTHOR]

The aim of this research paper is to develop an artificial intelligence (AI) brain for a 2D vehicle to help it navigate in a certain environment. The goal of the 2D car is to do round trips between two defined checkpoints while avoiding obstacles that are created by the user. The two defined checkpoints are the top left corner of the screen and the bottom right corner of the screen. This project makes use of PyTorch API to design the brain of the car and of Kivy API to design the environment of the car. Spyder, a cross-platform integrated development environment is used to visualize the project. [ABSTRACT FROM AUTHOR]

This research presents an error estimation approach with the combination of traditional multilevel techniques used to minimize errors for an accurate prediction and to investigate the behavior of such an algorithm for a satellite. The traditional techniques mentioned above are a combination derived from multiple regression techniques and perform a case study for data analysis. A linear plot can easily be predicted, however if a system tends to deviate toward non-linearity the overall result derived from such an algorithm can be non-reliable since each value would depict a completely different output at different levels. The stability of the fixed regression derived is used to determine the accuracy of the system. [ABSTRACT FROM AUTHOR]