Microgravity sloshing dynamics in .NET Incoporate barcode code39 in .NET Microgravity sloshing dynamics

Microgravity sloshing dynamics using visual studio .net toattach code 3 of 9 with web,windows application ISO/IEC 18004:2000 2.0 RLC (cm) 1. USS Code 39 for .

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0 0 300 600 900 1200 1500. XLC YLC ZLC 600 900 Time (s). 1200 1500. Time (s) (b) Fl .net vs 2010 barcode 3 of 9 uid mass center (absolute value) 1.00 RSC (cm) 0.

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00 600 900 1200 1500 Time (s) (d) Spacecraft mass center (absolute value) 300 0. (a) Fluid mass center (rotational Frame) 1.0 0.5 0.

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XSC, YSC, ZSC (cm). XSC YSC ZSC 600 900 1200 15 .net framework USS Code 39 00 Time (s) (c) Spacecraft mass center (non-rotational flame). Figure 12.40 Ti me evolution of fluid and spacecraft mass centers due to coupling of lateral impulse and orbital dynamics. (Hung, Long and Zu, 1996).

response is ide Code 39 for .NET ntical for both types of model. Hung (1993b) conducted a simulation study to determine the forces and torques induced by cryogenic sloshing in a Dewar container.

Hung (1994a,b, 1995a, 1996, 1997) presented a series of studies dealing with the sloshing of cryogenic helium driven by different forms of excitations in a microgravity field. Liquid helium at a temperature of 1.8 K has been used on the Gravity Probe-B (GP-B).

The equilibrium shape of the interface is governed by a balance of capillary, centrifugal, gravitational, and dynamic forces. Sloshing waves can be excited by longitudinal and lateral residual accelerations such as the Earth s gravity gradient and g-jitter. Hung, Long, and Zu (1996) studied the transient phenomena of coupling between slosh reaction torques driven by three types of excitations and spacecraft orbital dynamics.

The three excitations are (a) lateral impulse, (b) gravity gradient and/or (c) g-jitter. They numerically solved the governing equations of slosh dynamics and orbital translational and rotational motions of spacecraft dynamics. The slosh dynamics were treated based on a rotational frame, while the orbital dynamics were associated with a nonrotational frame.

Under lateral impulse along the x-axis, the liquid vapor interface (bubble) time evolution was determined. The bubble is first shifted to be in the positive x-direction and the liquid to be in the negative direction. The bubble experiences motion to the positive y-direction due to the Coriolis force with rotation along the z-axis in the rotational frame.

The bubble also exhibits deformations with back-and-forth oscillations. Figure 12.40 shows the time evolutions of the growth and decay of fluid mass center fluctuations in response to a lateral impulse.

The figure also shows the time evolution of the spacecraft mass center. Under combined gravity gradient and g-jitter shown in Figure 12.41 over the entire orbit period of 6000 seconds.

The gravity gradient acceleration, agg, acting on the fluid mass of the spacecraft was given by Hung and Long (1995a) and Hung and Pan (1993, 1995a) in the form. 12.10 Sloshing problems of cryogenics z (z ) Y Y t. m (r. .z).

Qg (0, 0, L1/2). y y t. O(0, 0, 0). x x (a) Geometry of bar code 39 for .NET gravity gradient acceleration, see equation (12.71).

2 Ggx (10 7go) 1 0 1 2 2 Ggy (10 7go) 1 0 1 2 2 Ggz (10 7go) 1 0 1 2 0 1500 3000 4500 Time (s) 6000 (c) Ggx Gjz (10 8go) (b) Ggy Gjy (10 8go) (a) Ggx Gjx (10 8go) 2 1 0 1 2 2 1 0 1 2 2 1 0 1 2 0 1500 3000 4500 Time (s) 6000. (a) Gjx (b) Gjy (c) Gjx (b) Time variation of gravity gradient acceleration (c) Time variation of gravity jitter acceleration. Figure 12.41 Ti me evolution of gravity gradient and g-jitter accelerations on the spacecraft during a full orbit period acting on a fluid element located at (r, , z) (40 cm, p/4, 10 cm). (Hung, Long and Zu, 1996).

agg n2 3 rc d rc d (12:165). where n 2p/ VS .NET 3 of 9 0 is the orbit rate,  0 is the orbit period (5856 s), rc is a unit vector in the direction from the spacecraft mass center to the center of the Earth, d is a vector from the fluid element to the spacecraft mass center. Fluctuations in the residual gravity due to g-jitter acceleration were proposed in the form ! 1 g gB 1 sin 2pft (12:166) 2.

2 XLC, YLC, ZLC (cm).
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