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


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.

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