The lateral sectional view elaborates on the internal components used in the 3U cubesat, while the Outer Body represents the structural collaboration with the Electric Power System or solar panels. Due to "Space Selfie" being our main objective, the Optical Payload becomes the most important part of the satellite. The cubesat is of 3U configuration i.e. 10cm x 10cm x 30cm in dimensions. The camera module takes upto 1.5U in volume, which is almost half the volume the cubesat provides! The rest of the components are designed and planned to be compact enough to fit within the remaining volume left. The camera module consists of several optical instruments such as the High Definition camera, teleconverter, Camera Circuit Board, CMOS Sensor, 500mm lens, etc. Together the camera module maps the surface of the earth and helps in Geospatial Imaging and Natual Disaster Monitoring. The cubesat consists of an Onboard Data Handling System (ODHS), also called the On-Board Computer (OBC), which acts as an hub for every component aboard the cubesat. It connects the components and handles the scientific instruments and calculations. It is part of middle section of the cubesat along with parts of the camera module. It also stores the images taken by the camera module till the cubesat enters within the range of communcations with our ground servers. A S-Band Transceiver handles the communications array of the satellite. The antennas needed for the uplink/downlink of data are integrated with the surface of the cubesat structure. The Power Distribution and Storage System consists of Two dual-layered High Density LiPo battery arrays that is connected to the Electric Power System. It provides the required power for the functioning of the necessary components when the satellite enters Eclipse Mode. The Electric Power System consists of space-degree proven Solar Panels that provides electric power to the satellite from the only available energy in space-solar radiation.
We need an efficient system aboard the satellite to prevent it from drifting itself away from the Low Earth Orbit it is placed in. This is handled with the help of the Attitude Determination Control System (ADHS) present in the last section of the cubesat structure. It consists of Magnetorquers, Reaction Wheels and an ADCS Circuit Board and provides high performance solution for the 3 axes control of the cubesat. The Magnetorquers are most essential in the de-tumbling process and use ambient magnetic fields to re-orient the cubesat. Reaction Wheels are a type of flywheels that create torque on a single axis on removal or addition of energy provided to the Reaction Wheels. The ADCS Circuit Board handles the cooperation between the magnetorquers and reaction wheels, while also storing the mathematical angular data needed for the precise rotation of the cubesat. To know the apparent position of the cubesat, there are sun sensors positioned on five sides of the cubesat surface. In any instant, there is atleast one sun sensor which detects the sun, which helps us to know which surface of the satellite is facing the sun. When no input is provided by the sun sensors, it inferes that the camera module is facing the sun. It is connected to the ODHS like all other components of the satellite. It is important for the Structural Material to provide the specific thermal and mechanical protection and sturdiness needed for the satellite to counter the harsh environments found in space. Regarding this problem statement, our cubesat is made of particular aluminium alloys like Al-7075-T6 or Al-6061. With the help of all these components, we achieve the necessity of all the basic components needed for any satellite sent upto space.