Control of Velocity Projectile on Multistage Coil gun

Winarno, Bambang; Putra, R. G.; Yuwono, Indarto; Gunawan, Agus; Sumantri, Bambang

doi:10.1109/icast1.2018.8751558

Cited by 2 publications

(3 citation statements)

References 12 publications

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“…Table 5 shows the settings for experiment parameters. The experiment results are listed in Table 6 and the efficiencies are calculated using Equation (11).…”

Section: Experimental Work 61 Verification Of the Magnetic Dipoles Modelmentioning

confidence: 99%

“…According to the experimental results shown in Table 6 and Figure 15, a significant improvement in the velocity of the projectile reaches 17% compared to the launcher without an iron yoke. Moreover, the efficiency in Table 6 is calculated using Equation (11) in the case of with/without iron yoke to highlight the improvement that rises by 36% over the ordinary launcher's efficiency. In addition, it is proven through Figures 15 and 16 that higher velocities can be achieved by the same voltages by adding an iron yoke.…”

Section: Examination Of the New Design Performancementioning

confidence: 99%

“…It rapidly accelerates ferromagnetic projectiles using electrical energy converted to kinetic energy. Electromagnetic science has contributed to many applications, such as Earth-to-orbit (ETO) microsatellite systems [1]; powerful launchers that can propel small satellites to settle at low Earth orbit [2]; low-speed and high-speed trains, high-speed, long-range fire support naval guns, and direct satellite launch to space [3]; launch of lunar liquid oxygen (LLOX) from the Moon to the stationary Lagrangian point L2 [4]; and electromagnetic guns [5][6][7][8][9][10][11][12].…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Design of A New Electromagnetic Launcher Based on the Magnetic Reluctance Control for the Propulsion of Aircraft-Mounted Microsatellites

Abdo,

El-Hussieny,

Miyashita

et al. 2023

ASI

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Recent developments in electromagnetic launchers have created potential applications in transportation, space, and defense systems. However, the total efficiency of these launchers has yet to be fully realized and optimized. Therefore, this paper introduces a new design idea based on increasing the magnetic flux lines that facilitate high output velocity without adding any excess energy. This design facilitates obtaining a mathematical equation for the launcher inductance which is difficult to analytically represent. This modification raises the launcher efficiency to 36% higher than that of the ordinary launcher at low operating voltage. The proposed design has proven its superiority to traditional launchers, which are limited in their ability to accelerate microsatellites from the ground to low Earth orbit due to altitude and velocity constraints. Therefore, an aircraft is used as a flying launchpad to carry the launcher and bring it to the required height to launch. Meanwhile, it is demonstrated experimentally that magnetic dipoles in the projectile material allow the launcher coil’s magnetic field to accelerate the projectile. This system consists of the launcher coil that must be triggered with a high amplitude current from the high DC voltage capacitor bank. In addition, a microcontroller unit controls all processes, including the capacitor bank charging, triggering, and velocity measurement.

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“…Table 5 shows the settings for experiment parameters. The experiment results are listed in Table 6 and the efficiencies are calculated using Equation (11).…”

Section: Experimental Work 61 Verification Of the Magnetic Dipoles Modelmentioning

confidence: 99%

Section: Examination Of the New Design Performancementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Design of A New Electromagnetic Launcher Based on the Magnetic Reluctance Control for the Propulsion of Aircraft-Mounted Microsatellites

Abdo,

El-Hussieny,

Miyashita

et al. 2023

ASI

View full text Add to dashboard Cite

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Analysis of the Influence of System Parameters on Launch Performance of Electromagnetic Induction Coil Launcher

Guan

et al. 2022

Energies

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The influence of electromagnetic induction coil launcher (EICL) system parameters on the launch performance was analyzed, and a method for measuring the launch performance of an EICL system with a muzzle velocity and energy conversion efficiency was proposed. The EICL system mainly includes a pulse power supply and launcher. The parameters of the pulse power supply mainly include the discharge voltage and the capacitance value of the capacitor bank. The structural parameters of the launcher mainly include the bore size of the launcher, the air gap length between the armature and the drive coil, the length and width of the drive coil, and the trigger position of the armature. Change in single or multiple parameters in the launch system will influence the launch performance. The influence of single or multiple parameters on the launch performance was summarized, and the physical law as analyzed. The influence law of the EICL system parameters on the launch performance was obtained, which lays a theoretical foundation for the optimization design of EICL. Finally, experimental verification was carried out by a single-stage test platform.

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Control of Velocity Projectile on Multistage Coil gun

Cited by 2 publications

References 12 publications

Design of A New Electromagnetic Launcher Based on the Magnetic Reluctance Control for the Propulsion of Aircraft-Mounted Microsatellites

Design of A New Electromagnetic Launcher Based on the Magnetic Reluctance Control for the Propulsion of Aircraft-Mounted Microsatellites

Analysis of the Influence of System Parameters on Launch Performance of Electromagnetic Induction Coil Launcher

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