• Aerodynamic drag
• Analysis of sensitivity
• Center of pressure
• Falcon 9 V.1.2
• First stage Re-entry trajectory
• Hypersonic Grid fins
• MLV
• Re-entry sub systems
• Reusable Launch Vehicle
• Sound pressure level.
• Structural stability
• Vectoring of re-entry

The construction of medium-lift launch vehicle can be classified into one being the reusable launch vehicle system. The concept of completely reusable is related to the efficiency of the system being 100 percent. In reality, that would be an ideal system. In consideration of this point, a brief overview is provided based on previously published papers. The current studies and evaluations about RLV partially hold some validity in the concept of rocket science. A two-stage to orbit launch vehicle is adapted in the scope of work.
For the study purposes, we have considered the Falcon - 9. In addition, we have the classification of V.1.2 for the chosen falcon - 9. Concerned about the constraints, we have the 'extra weight' that follows the reentry phase. Also, the 'refurbishment' which follows after the mission success, and this falls out of our scope. The re-entry phase shall be defined within the boundaries of available information. Some of the required information shall be extracted from the principle of the ballistic vehicles currently in use. The focus of the work is mainly on the configuration of the sub-systems that are involved during the re-entry phase. At the MECO (Main Engine Cut Off), the initiation of the sub-systems of re-entry and landing begins. On this context, we have the design specifications of the Falcon 9.

The main intent of the thesis shall be definition of the aerodynamic grid fins used at the interstage of the mission. Falcon - 9 is equipped with four hypersonic grid fins positioned at the base of the interstage. They orient rocket during reentry by moving the center of pressure. The aerodynamic analysis of these fins, sensitivity analysis and the calculation of the sound pressure level is to be analyzed and arrive at a conclusion. To finally build the results obtained on the grid fins that guide the process of reverse thrust vectoring and positioning of the vehicle is substantial.