American Journal of Aerospace Engineering 2016; 3(3): 43-49 http://www.sciencepublishinggroup.com/j/ajae doi: 10.11648/j.ajae.20160303.14 ISSN: 2376-4813 (Print); ISSN: 2376-4821 (Online) Electrodynamic Launch System Takeoff-Elevating Platforms for Deck-Based Aircraft Carriers Concept Development and Design Volodymyr Chumakov, Oleksandr Stolarchuk Independent Scholar, Kharkiv, Ukraine Email address: v.i.ch@mail.ru (V. Chumakov) To cite this article: Volodymyr Chumakov, Oleksandr Stolarchuk. Electrodynamic Launch System Takeoff-Elevating Platforms for Deck-Based Aircraft Carriers Concept Development and Design. American Journal of Aerospace Engineering. Vol. 3, No. 3, 2016, pp. 43-49. doi: 10.11648/j.ajae.20160303.14 Received: December 3, 2016; Accepted: December 22, 2016; Published: January 7, 2017 Abstract: The results of the development of the deck-based takeoff-elevating platforms of electrodynamic launch system are given. The research results of electrodynamic railguns with pulsed-dynamic biasing of acceleration channel and their modifications are used as the basis for the development and design. Comparative characteristics of the developed systems EMALS criteria are shown. Keywords: Electromagnetic Aircraft Launch System, Coaxial Electrodynamic Railgun, Pulse-Dynamic Biasing System, Rotor, Traction Force 1. Introduction The perspective launch system from the deck of the aircraft carrier "Gerald R. Ford” with the electromagnetic catapults (Electromagnetic Aircraft Launch System-EMALS) is widely covered by the media. Having sufficient experience in the design of electrodynamic accelerators, as the example of their practical application, our authors team proposed the concept of a design embodiment of the electrodynamic launch system for deck-based takeoff-elevating platforms based on electrodynamic railgun (EDRG) with the distributed pulse-dynamic biasing system (PDBS) [1–4]. EMALS requirements were taken as the initial data, published in [5, 6]. It should be noted that in recent years the EMALS development is becoming increasingly relevance [7, 8]. According to the technical specifications EMALS should provide the following parameters of the aircraft launch:  ultimate velocity of the aircraft-28-102,8 m/s;  deviation of traction (strain)-less than 5%;  energy of launch aircraft-122 MJ;  duration of the cycle starts-45 s;  system weight–less 225 tonn;  system volume (overall dimensions)-less 425 m 3 ;  max. aircraft final velocity deviation-±1.5 m/s. Calculation of EDRG parameters was carried out for the hardest regime of the start-the maximum mass of the aircraft is launched with a minimum track length:  minimal track length–91 m;  starting aircraft mass–40 000 kg;  final velocity–300 km/h. To gather velocity from 0 to 300 km/h at a track length of 91 m, the aircraft should move with an acceleration of about 38 m/s 2 . For further evaluation the value of acceleration was accepted of 40 m/s 2 . Besides for the given acceleration regime of the aircraft at a weight of 40 tons, the EDRG catapult rotor should develop a traction force of 1.6 MN. Calculations of various railgun modifications have been carried out precisely for this value of traction [9]. Simulation results analysis of the large masses EDRG given in [9] showed that the required specifications match the coaxial embodiment of EDRG the most. The decisive advantages of this design are the minimum current consumption as the most critical parameter for the onboard systems and the minimum of the magnetic field intensity outside the acceleration channel, which greatly