Abstract: This paper investigates the trajectory prediction and dispersion for unguided fin stabilized artillery rocket in order to explain the importance of the rocket production accuracy and the benefit of using guided rockets. The total dispersion results mainly from three effects. The first is the dispersion due to rocket production inaccuracy, which includes propellant mass, composition in...

The current drive efficiency for the ITER reference Scenario-2 has been calculated by the newly developed ray-tracing code TRAVIS for both the upper and equatorial launcher. For comparison, two adjoint approach models are applied, the high-speed-limit model and a model with the parallel momentum conservation taken into account. It is shown, that in the angle range expected as optimal launch ang...

This paper presents an ongoing work at the Institute of Aeronautics and Space (IAE) to provide a process and a system to support the management of knowledge and new technologies applied to the conception and development of the Brazilian Satellite Launcher Program. This management is not only necessary to organize the actual research efforts but also to identify communalities and necessities for...

In this paper we investigate the Hamilton-Jacobi-Bellman (HJB) approach for solving a complex real-world optimal control problem in high dimension. We consider the climbing problem for the European launcher Ariane V: The launcher has to reach the Geostationary Transfer Orbit with minimal propellant consumption under state/control constraints. In order to circumvent the well-known curse of dimen...

In this work, the design studies of a 60 GHz, 100 kW CW gyrotron have been presented. Mode selection is carefully studied with the aim of minimizing mode competition and to yield a perfect solid beam output through an RF window with a suitable dimpled-wall quasi-optical launcher. Cavity design and interaction computations are then carried out. In addition, preliminary design of the magnetron in...

FOREWORD On 4 June 1996, the maiden flight of the Ariane 5 launcher ended in a failure. Only about 40 seconds after initiation of the flight sequence, at an altitude of about 3700 m, the launcher veered off its flight path, broke up and exploded. Engineers from the Ariane 5 project teams of CNES and Industry immediately started to investigate the failure. Over the following days, the Director G...

Simulation research on the launch process of a ship-borne multiple launch rocket system is studied in this paper. First, the power spectrum density of the ship’s motion is calculated based on ocean wave energy spectrum, and the movement spectrums of the ship’s random motion are calculated. Then, the model of shipborne rocket launcher system is built by virtual prototype technology. The launch p...