Analysis and observation of spacecraft plume/ionosphere interactions during maneuvers of the space shuttle

Abstract

This work employs in situ measurement data and constructive simulations to examine the underlying physical mechanisms that drive spacecraft plume interactions with the space environment in low-Earth orbit. The study centers on observations of the enhanced flux of plasma generated during a maneuver of Space Shuttle Endeavour as part of the Sensor Test for Orion Relative Navigation Risk Mitigation experiment in May 2011. The Canary electrostatic analyzer (ESA) instrument mounted on the portside truss of the International Space Station indicated an elevated ion current during the shuttle maneuver. The apparent source of enhanced ion current is a result of interaction of the spacecraft thruster plume with the rarefied ambient ionosphere, which generates regions of relatively high density plasma through charge exchange between the neutral plume and ambient ions. To reconstruct this event, unsteady simulation data were generated using a combined direct simulation Monte Carlo/particle-in-cell methodology, which employed detailed charge exchange cross-section data and a magnetic field model. The simulation provides local plasma characteristics at the ESA sensor location, and a sensor model is subsequently used to transform the local properties into a prediction of measured ion current. The predicted and observed total currents are presented as a function of time over a 30 s period of pulsed thruster firings. A strong correlation is observed in the temporal characteristics of the simulated and measured total current, and good agreement is also achieved in the total current predicted by the model. These results support conclusions that (1) the enhanced flux of plasma observed by the ESA instrument is associated with Space Shuttle thruster firings and (2) the simulation model captures the essential features of the plume interactions based on the observation data.

A 3D particle model for the plume CEX simulation

“…However, in practical applications, it is found that the electric thruster plume will bring great harm to the spacecraft, and even lead to spacecraft failure. For example, Charge Exchange (CEX) ions of the plume can bring thermal loads and pollute electronic components of the spacecraft (1)(2)(3) . Therefore, how to reduce the impact of the plume on the spacecraft is critical to the future application of electric thrusters.…”

Unsteady Simulations of Rocket Plume Expansions in Geostationary Earth Orbit

“…2,3 This methodology has also been applied to the Space Shuttle rocket plume expansion into the ionosphere to explain the correlation between rocket firings and measured ion fluxes aboard the international space station (ISS). 4 Several others [5][6][7] have also investigated the interactions between spacecraft, rocket plumes, and the space environment, but are focused on interactions at LEO. The lower densities, higher energies of ambient ions, and lower geomagnetic field strength at GEO relative to LEO changes the relative importance of the various plume-atmosphere interactions, and therefore a separate analysis is required to better understand and predict plume behavior at GEO.…”

Spacecraft plume interactions with the magnetosphere plasma environment in geostationary Earth orbit

“…Incorporating these effects is critical for capturing the development of the spacecraft plume in the plasma environment, particularly over large distances. Recent efforts [ Stephani and Boyd , ; Stephani et al , ] investigating spacecraft plumes in low Earth orbit (LEO) have demonstrated that interaction of the spacecraft neutral plume with the ambient plasma forms a relatively high‐density spacecraft ion plume. The propagation of this ion plume is determined primarily by the interaction with the magnetic field, but the development of the neutral spacecraft plume is also affected (albeit indirectly) by the magnetic field interaction owing to secondary charge‐exchange reactions.…”

“…The present study aims to examine the interaction between spacecraft hydrazine thruster plumes and the ambient magnetosphere in geostationary Earth orbit (GEO) conditions. While previous efforts have developed a combined direct simulation Monte Carlo/particle‐in‐cell (DSMC/PIC) methodology to examine plumes in LEO [ Stephani and Boyd , ; Stephani et al , ], this study focuses on the additional physical model considerations involving nonequilibrium plasma mixtures. The rarefied nature of the magnetosphere, as well as the presence of the surrounding plasma environment, requires the use of a combined DSMC/PIC methodology, which is detailed next.…”