Reconnection electromagnetic launcher for space application

Cheng, Siyao; Li, Xiaopeng; Li, Liyi; Ge, Xin; Gao, Hanying; Hu, Yusheng

doi:10.1109/aero.2003.1235196

Cited by 3 publications

(1 citation statement)

References 4 publications

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“…This type of launcher has been developed in Sandia National Lab. in Albuquerque [9]- [10], and a detailed design guideline for space application is presented in [11]. The disadvantages of such a launcher, in the sense of space applications, are pulsed propulsion force, absence of levitation force and the need for synchronous operation.…”

Section: Introductionmentioning

confidence: 99%

Design of an Electromagnetic Launcher for Earth-to-Orbit (ETO) microsatellite systems

Hasırcı

Balıkçı

2009

2009 4th International Conference on Recent Advances in Space Technologies

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In this study, an alternative launcher design for Earth-to-Orbit (ETO) microsatellite systems is addressed. The main goal of the design is to reduce the cost of launching operation. For this aim, a new topology is introduced and a sample design is presented. The paper proposes a vertical takeoff Electromagnetic Launcher (EML) for ETO microsatellite systems. Design specifications are 6 km/s muzzle velocity and 20000 Gee's acceleration for a 100 kg payload. It is expected that proposed design presents a powerful alternative to conventional launchers and existing electromagnetic launchers for ETO systems.

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Section: Introductionmentioning

confidence: 99%

Design of an Electromagnetic Launcher for Earth-to-Orbit (ETO) microsatellite systems

Hasırcı

Balıkçı

2009

2009 4th International Conference on Recent Advances in Space Technologies

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Simulation and measurement on velocity of flat-plate projectiles in a three-stage reconnection electromagnetic launcher

Duan

Liao

Zou

et al. 2011

2011 IEEE Pulsed Power Conference

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For study the velocity characteristics of acceleration of the projectiles, a sketch of a three-stage reconnection electromagnetic launcher using flat-plate projectiles was introduced in this paper, A theoretical model of small scale 3-stage reconnection launcher was set up and the velocity of the projectile as well as the efficiency properties was simulated. A three-stage reconnection launcher was founded and the measurement system was designed to obtain the velocity of the projectile. A control system on the basis of a microcontroller and a computer was designed for the launcher, Groups of IT -shaped photocouplers were aligned at the preset spacing in the direction of the flyway in order to sense the arrival of the projectile and output signals to the control system for velocity measurement. Measures are taken to inhibit electromagnetic interference and to isolate high voltage. Three types of flat-plate projectiles with different configuration were prepared for experiments. The simulated results and experimental data show that when the 4.32mF capacitor banks were charged to 5000 V, a final velocity of 59 m/s for the 100g-hollow-plate projectile was acquired. For the 160g-solid-plate projectile and the 80g-gridded-plate projectile cases, the final velocity was 46 m/s and 43 m/s respectively. D

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Concerning the Design of a Novel Electromagnetic Launcher for Earth-to-Orbit Micro- and Nanosatellite Systems

Hasırcı

Balıkçı

Zabar

et al. 2011

IEEE Trans. Plasma Sci.

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Reconnection electromagnetic launcher for space application

Cited by 3 publications

References 4 publications

Design of an Electromagnetic Launcher for Earth-to-Orbit (ETO) microsatellite systems

Design of an Electromagnetic Launcher for Earth-to-Orbit (ETO) microsatellite systems

Simulation and measurement on velocity of flat-plate projectiles in a three-stage reconnection electromagnetic launcher

Concerning the Design of a Novel Electromagnetic Launcher for Earth-to-Orbit Micro- and Nanosatellite Systems

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