RECONSTRUCTION AND CONTROL DESIGN USING THRUST VECTORING CONTROL ON THE FALCON 9 LAUNCH VEHICLE IN THE REENTRY PHASE

• Main Author: Yazid Taufiqi, Achmad
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/67297
• Institution: Institut Teknologi Bandung

The rise of satellite launches encourages the development of a more economical satellite launch technology such as reusable launch vehicles. Companies like SpaceX and Blue Origin have developed launch vehicle that can be used repeatedly. For example, Falcon 9, which is developed by SpaceX, is capable of vertical landing. Indonesia, through LAPAN, wants to develop reusable launch vehicles. However, the development is constrained due to the lack of mastery in the technology. Therefore, as a first step in mastering this technology, the topic of this research is to develop a mathematical model that can simulate the vertical landing of Falcon 9. This simulation will be equipped with weight and balance model, environment model, aerodynamic and propulsion model. This model will be used as a basis in designing the control system using thrust vectoring control. The simulation shows that the rocket is stable during reentry phase until landing using thrust vectoring control. This conclusion is taken from the results of linear and non-linear simulation that is done in six analytical points which coincide with reentry burn startup, reentry burn shutdown, aerodynamic guidance (supersonic speed), start of the transonic speed, landing burn startup, and landing burn shutdown or landing. However, the simulation shows that the attitude of the rocket is not perpendicular to the ground therefore a better control and tracking design is needed.