Title :
25 Years of ionospheric modification with Space Shuttle OMS burns
Author :
Bernhardt, Paul A.
Author_Institution :
Plasma Phys. Div., Naval Res. Lab., Washington, DC, USA
Abstract :
The Space Shuttle Orbital Maneuver Subsystem (OMS) is the largest engine to be fired in the F-region ionosphere. The OMS thruster provides 10 kg/s of exhaust materials exiting at a speed of 3 km/s. The OMS nozzle can be pointed in the ram, wake or out-of-plane relative to the Space Shuttle orbit. The vector addition of the exhaust velocity and the orbit velocity provides possible injections speeds of between 4.7 and 10.7 km/s. When the exhaust impacts the ionosphere, neutral-ion collisions and ion-molecule charge exchange yields ions moving at hyper-acoustic speeds. A ten second burn of two OMS engines deposits over 1 Giga-Joule of energy into the upper atmosphere. The ionosphere reacts to an OMS burn by exciting a large number of plasma wave modes including the whistler, fast and slow MHD, Alfven, ion acoustic, lower hybrid, and ion Bernstein waves. These waves have been detected by both radar scatter and in situ electric field plasma probes. Field aligned irregularities are produced by the exhaust interactions. The exhaust pickup ions eventually thermalize with the background atmosphere and they recombine with ambient electrons leaving an electron hole. All these phenomena were obtained first in July 1985 during STS-51F and were detected for the next 25 years through STS-129 with 18 flights of the Space Shuttle. These experiments have demonstrated the (1) Space Shuttle OMS burns can change the HF radio propagation characteristics of the F-layer, (2) artificial ionospheric holes may be used to trigger plasma instabilities that scatter radar and possibly affect GPS propagation, (3) space based electric field sensors can detect OMS burns in the ionosphere for ranges over 400 km, and (4) optical emissions are produced as the pickup ions recombine with F-region electrons. This type of ionospheric modification has been studied with computer models that employ direct simulation Monte Carlo (DSMC) techniques for the neutral exhaust expansion, plasma fluid theory for the p- - lasma density effects and kinetic theory with Maxwell´s equations for the plasma wave generation.
Keywords :
F-region; Global Positioning System; Maxwell equations; Monte Carlo methods; ion recombination; ionospheric electromagnetic wave propagation; plasma Alfven waves; plasma Bernstein waves; plasma collision processes; plasma density; plasma hybrid waves; plasma ion acoustic waves; plasma kinetic theory; plasma magnetohydrodynamic waves; plasma probes; plasma simulation; plasma transport processes; radiowave propagation; space vehicles; whistlers; AD 1985 07; Alfven wave; F-layer characteristics; F-region electrons; F-region ionosphere; GPS; HF radio propagation characteristics; MHD wave; Maxwell equation; OMS nozzle; OMS thruster; artificial ionospheric holes; background atmosphere; direct simulation Monte Carlo technique; exhaust velocity analysis; field aligned irregularities; hyperacoustic speed analysis; in situ electric field plasma probes; ion Bernstein wave; ion acoustic wave; ion-molecule charge exchange yield; ionospheric modification analysis; kinetic theory; lower hybrid wave; neutral exhaust expansion method; neutral-ion collision process; optical emission analysis; pickup ion recombination process; plasma density; plasma fluid theory; plasma instability; plasma wave generation; plasma wave modes; radar scatter detection method; space shuttle orbit; space shuttle orbital maneuver subsystem; space-based electric field sensors; whistler wave; Electric fields; Engines; Ionosphere; Plasma waves; Plasmas; Satellites; Space shuttles;
Conference_Titel :
General Assembly and Scientific Symposium, 2011 XXXth URSI
Conference_Location :
Istanbul
Print_ISBN :
978-1-4244-5117-3
DOI :
10.1109/URSIGASS.2011.6051129