PROJECT TITLE :

Thermal Protection, Aerodynamics, and Control Simulation of an Electromagnetically Launched Projectile

ABSTRACT:

In recent years, several ideas to apply electromagnetic launch technology to spaceflight applications have come up. The employment of electrical energy to propel a payload carrier promises savings of propellant and, thus, price reduction for the transfer to orbit. Previous studies largely comprised a rough estimation of the launcher and also the vehicle size. Generally, a -budget is given to illustrate the energy expenditure. Some studies neglect the need of a rocket engine. Only by means of an electromagnetic launch, without the potential to maneuver reaching an orbit isn't achievable. As well as a propulsion system, an attitude management system and a flight controller are required to bring the vehicle into a circular orbit. The high acceleration and high velocities at low altitudes have set high demands on the payload-carrying vehicle. Its structure must withstand the high acceleration forces during launch and also the tremendous aerodynamic heat fluxes during ascent through the dense atmosphere. This paper presents a vehicle concept that addresses of these demands. The vehicle consists of a 2-stage hybrid rocket engine system, a thermal protection system (TPS), and high-test peroxide monopropellant thrusters for an attitude control system and a steering, navigation, and control system. A simulation model is created, which consists of a half dozen-DOF flight mechanics module, an aerodynamic module, propulsion module, TPS simulation, also a steering and flight control simulation. So, the entire ascent with all its aspects can be simulated. The simulation results show that a 710-kg vehicle launched with 2586 g and an initial velocity of 3642 m/s will carry 31.5 kg of payload into a three hundred-km circular orbit. The configuration of the vehicle will be outlined by a set of input parameters. This allows the employment of the model at intervals an optimization tool.