## 1 Introduction
The resistivity of the ejected material is instrumental in reducing the eddy current. Researchers in [25] changed the projectile's shape and material to drop the projectile conductivity because lower resistance would result in higher eddy currents and more significant Lorentz force. As a result, highly conductive materials will reduce the resultant propulsion force. This problem has been restricted by the laminating method. In this paper, the projectile is solid and made of medium carbon steel material, to preserve the projectile strength while hitting the obstacles. However, the saturation of this material is a problem that led to a poor increase in the projectile velocity at higher voltages. The iron yoke developed in this work is made of laminated soft iron sheets. The authors of [26] found that improving the discharge circuit of the launcher coil leads to a reduction in the suck-back force. The suck-back force is a reverse force that appears when the projectile crosses the coil's first half. They used an IGBT switch to control the turning on and turning off time. Suck-back force is the leading cause of magnetic projectile damping when the projectile centerline coincides with the launcher coil centerline. There is a challenge in introducing new discharging circuits. In [24], a previous work of the same authors of this work, the effect of suck-back force was addressed by decreasing the number of magnetic flux lines that pass through the projectile after reaching the second half of the coil by changing the shape of the coil into a conical shape. The application targeted by this work is micro- and nanosatellite launching. But this kind of launcher is limited in its efficiency which may force an increase in the number of stages to achieve the Earth escape velocity as in the case of the Sandia launcher [4]. A flying launchpad could be used to use the merits of this launcher and decrease the number of stages. The flying launchpad transmits the launcher to the required height to reduce the needed energy to propel the satellite with its available capabilities. The velocity of the launcher introduced in this paper is extendable to any required velocity. But to prove the concept of improving the launcher by adding an iron yoke and verifying security and safety constraints, the speed in all experiments was limited as in this work. Heat generated through the launching process can be estimated by the analysis that was performed in [27]. All mentioned references use higher input voltage or the number of stages to raise the output velocity which requires much energy. In addition, these methods do not contribute to increasing efficiency further. But no one has used the same input voltage and tried to decrease the magnetic reluctance (by adding an iron yoke) and save a huge amount of energy. The research work in this paper mainly contributes to a new design idea for the launcher. To demonstrate this idea, the main parts of the launcher must be illustrated. This launcher consists of four main parts:  
1. Launcher coil: this part generates the needed magnetic flux lines and has many parameters to control the number of these flux lines. 2. Capacitor bank: this component stores a large amount of energy to discharge in the launcher coil to generate a time-changing current. 3. Launching circuit: this circuit controls the current that passes from the capacitor to the launching coil by using a high-current thyristor and its firing circuit. 4. Control circuit: this circuit is responsible for managing the charging time and firing signal to the thyristor and measuring the exit velocity. The modifications are to add an iron yoke around the launcher coil and carry this launcher on a flying launchpad. This design idea mainly contributes to:  
1. Launching a satellite from a flying launchpad may reduce many stresses on the satellite while launching. In addition, less money is required compared to building a massive launchpad on the ground to launch the satellites with the escape velocity of the Earth.