Numerical Simulation in Science and Engineering: Proceedings by Nikolaus Fiebiger (auth.), Michael Griebel, Christoph Zenger

By Nikolaus Fiebiger (auth.), Michael Griebel, Christoph Zenger (eds.)

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Additional resources for Numerical Simulation in Science and Engineering: Proceedings of the FORTWIHR Symposium on High Performance Scientific Computing, München, June 17–18, 1993

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The agreement reached between the experimental and numerical data is satisfactory for most practical conclusions drawn from the investigations. Hence, the computation that a motion of the ground floor will yield a change in sign of the lift force enforced to the back of the vehicle can be taken as guaranteed for the corresponding large vehicle moving on the road. Aerodynamic of Airfoils and Wings A pronounced need exists for more sophisticated methods for scale-up and wind tunnel wall corrections in experimental aerodynamics of airfoils and wings in order to take into account the pressure distributions enforced by the wind tunnel geometry.

L is the position of the spacecraft at t = TO. The 125000 km-boundary is artificially introduced, but has no mathematical meaning except the change of the coordinate system for 26 technical reasons. The two coordinate systems are coupled by an interior point condition. VH L is optimized; optimization of its direction will further decrease fuel consumption [13]. The total final trajectory (spiraling-up and interplanetary flight) was calculated without splitting-up or simplification. Fig. 3 shows the projection of the optimal flight trajectory of the spacecraft to the base "''''~-L ",'" 1'/ '" '" '" '" '" '" " ,," '" '" , \ I \ \ "I " I I , I , Earth 1111 1," " I , \ \ II III' ....

_'"' Projection of the three-dimensional Earth escape maneuver. 9 kg, time for spiraling out 4 days. plane of a geocentric coordinate system. Solid lines mark those parts of the trajectory where thrusters are on, broken lines those with the thrust off. First thrust arc starts near the perigee of the GTO-ellipse on November 6th, 1992. After 4 orbits and slightly more than 4 days the spacecraft has reached its optimal escape velocity. 9 kg of fuel. 71 kmls. On the coast arcs the spacecraft is spin-stabilized with 5 rpm and the spacecraft main axis X3 has to be perpendicular to the plane of motion.

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