Space Communications and Navigation (SCaN) Network Simulation Tool Development and its Use Cases
No abstract available
Jennings, E.↗
Engineering topics
Wang, S.-Y.
Publications and source records attributed to Wang, S.-Y..
Primary propulsion of electrothermal, ion, and chemical systems for space-based radar orbit transfer
An orbit transfer mission concept has been studied for a Space-Based Radar (SBR) where 40 kW required for radar operation is assumed available for orbit transfer propulsion. Arcjet, pulsed electrothermal (PET), ion, and storable chemical systems are considered for the primary propulsion. Transferring two SBR per shuttle flight to 1112 km/60 deg using eiectrical propulsion systems offers an increased payload at the expense of increased trip time, up to 2000 kg each, which may be critical for survivability. Trade offs between payload mass, transfer time, launch site, inclination, and height of parking orbits are presented.
Wang, S.-Y.↗
Effect of vacuum exhaust pressure on the performance of MHD ducts at high B-field
The effect of area ratio variation on the performance of a supersonic Hall MHD duct showed that for a given combustion pressure there exists an area ratio below which the power generating region of the duct is shock free and the power output increases linearly with the square of the magnetic field. For area ratios greater than this, a shock forms in the power generating region which moves upstream with increasing magnetic field strength resulting in a less rapid raise in the power output. The shock can be moved downstream by either increasing the combustion pressure or decreasing the exhaust pressure. The influence of these effects upon duct performance is presented in this paper.
Smith, J. M.↗
Characteristics of a CW water vapor laser at 118 and 28 microns
The characteristics of a CW water vapor laser operating at 118 and 28 microns are reported. By monitoring the discharge current, helium gas pressure, and water vapor pressure, a criterion for optimum power output has been obtained. Peak powers of 6 and 114 mW are obtained, respectively, for the 118- and 28-micron lines for a 4.5-m discharge tube.
Yasuoka, Y.↗
An exact solution of a simplified two-phase plume model
An exact solution of a simplified two-phase, gas-particle, rocket exhaust plume model is presented. It may be used to make the upper-bound estimation of the heat flux and pressure loads due to particle impingement on the objects existing in the rocket exhaust plume. By including the correction factors to be determined experimentally, the present technique will provide realistic data concerning the heat and aerodynamic loads on these objects for design purposes. Excellent agreement in trend between the best available computer solution and the present exact solution is shown.
Wang, S.-Y.↗