Unterschleissheim, Germany
Unterschleissheim, Germany

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Havermann M.,French German Research Institute of Saint Louis | Havermann M.,Walvoil S.p.A | Seiler F.,French German Research Institute of Saint Louis | Hennig P.,MBDA LFK Lenkflugkorpersysteme GmbH
Notes on Numerical Fluid Mechanics and Multidisciplinary Design | Year: 2010

An experimental and numerical study of lateral jet interference with hypersonic cross flows was performed at ISL. The experiments were conducted with a generic high-velocity missile model in the ISL high-energy shock tunnel STA at Mach numbers of 4.5 and 6. For each Mach number two duplicated atmospheric altitude conditions, three angles of attack and three side jet pressure ratios were studied. The flow was visualized using differential interferometry and the surface pressure was measured with fast response pressure gauges. In parallel, a numerical simulation with a CFD code was done and the calculations were validated by the experiments. The CFD simulation allowed calculating the jet interaction amplification for the different experimental flow parameters. © 2010 Springer-Verlag Berlin Heidelberg.


Srulijes J.,French German Research Institute of Saint Louis | Seiler F.,French German Research Institute of Saint Louis | Hennig P.,MBDA LFK Lenkflugkorpersysteme GmbH | Gleich P.,MBDA LFK Lenkflugkorpersysteme GmbH
Notes on Numerical Fluid Mechanics and Multidisciplinary Design | Year: 2010

The heat loads during high-speed missile flight have to be considered in the design process by selecting appropriate geometries, structures and materials. To model these loads, especially at the nose, it is necessary to know the heat flux data in dependence of the time-dependent flow conditions. Therefore, great interest is focused on heat flux data gained from ISL shock tunnel experiments. These were done for Mach number between 3.5 and 10 for flight altitude conditions ranging from sea level up to 60 km. On the nose surface of a blunt and a sharp cone heat fluxes were measured with special, fast-reacting thin film temperature gauges. The results are compared with theoretical calculations based on the classical boundary layer theory for the laminar as well as for the turbulent boundary layer formation at a conical missile nose. Best agreement exists between the heat fluxes measured and the analytical solutions for a sharp cone. © 2010 Springer-Verlag Berlin Heidelberg.


Weinand K.,MBDA LFK Lenkflugkorpersysteme GmbH | Dahlem K.-J.,MBDA LFK Lenkflugkorpersysteme GmbH | Hold R.,MBDA LFK Lenkflugkorpersysteme GmbH | Stern D.,MBDA LFK Lenkflugkorpersysteme GmbH | And 2 more authors.
Notes on Numerical Fluid Mechanics and Multidisciplinary Design | Year: 2010

An experimental and computational study of a supersonic missile with a slender cylin drical airframe and a divert jet thruster system for attitude control was a co op eration of the French-German Research Institute of Saint-Louis and MBDA LFK. The aerodynamic of a defined missile model with lateral jet was calculated with Computational Fluid Dynamics (CFD) methods and the same configuration was measured in a shock tube for validation of the numerical procedure. The verified CFD flow field solutions allow an extensive analysis of the jet thruster control effectiveness, the complex fluid interactions of freestream and thruster cross flow and their physical effects on the airframe. It is possible to analyze the change of the pressure contours on the complete airframe or dedicated aero dyn amic surfaces of the missile and therefore the deviations of the missile aero dynamic caused by the lateral jet. © 2010 Springer-Verlag Berlin Heidelberg.


Patent
MBDA LFK Lenkflugkorpersysteme GmbH | Date: 2011-02-24

A device for launching unmanned missiles from an aircraft with a pallet, on which at least one container is provided to receive a missile. The container has an upper container section that has a pylon for the suspended, detachable support of the missile. The container has a lower container section that is embodied as a support area for the missile.

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