Usage Conditions May Apply Usage Conditions Apply There are restrictions for re-using this media. For more information, visit the Smithsonian's Terms of Use page. IIIF provides researchers rich metadata and image viewing options for comparison of works across cultural heritage collections. More - https://iiif.si.edu View Manifest View in Mirador Viewer Usage Conditions May Apply Usage Conditions Apply There are restrictions for re-using this media. For more information, visit the Smithsonian's Terms of Use page. IIIF provides researchers rich metadata and image viewing options for comparison of works across cultural heritage collections. More - https://iiif.si.edu View Manifest View in Mirador Viewer Usage Conditions May Apply Usage Conditions Apply There are restrictions for re-using this media. For more information, visit the Smithsonian's Terms of Use page. IIIF provides researchers rich metadata and image viewing options for comparison of works across cultural heritage collections. More - https://iiif.si.edu View Manifest View in Mirador Viewer Usage Conditions May Apply Usage Conditions Apply There are restrictions for re-using this media. For more information, visit the Smithsonian's Terms of Use page. IIIF provides researchers rich metadata and image viewing options for comparison of works across cultural heritage collections. More - https://iiif.si.edu View Manifest View in Mirador Viewer

This is a scale model of a SERT (Space Electric Rocket Test) 2 cesium ion rocket engine. Developed in the mid-1960s for use as attitude control thrusters on spacecraft, engines like this one produced minute streams of ions generating extremely low levels of thrust. Unlike conventional chemical propulsion systems, ion engines could be fired for extremely long durations.

This model represents the type of engine test fired on February 3, 1970 aboard a Thor-Agena D launch vehicle. Unlike SERT I, which was battery powered, SERT 2 used solar cells. On this maiden flight into earth orbit, two SERT 2 thrusters operated continuously for 3,782 hours (more than five months) and 2,011 hours (nearly three months) respectively. Electrical malfunctions prevented both engines from firiing for their planned durations of six months.

Work on ion propulsion systems of this type continued at NASA into the mid-1970s.

 Display Status

This object is not on display at the National Air and Space Museum. It is either on loan or in storage.
Object Details
Country of Origin United States of America Type PROPULSION-Miscellaneous Manufacturer NASA, Lewis Research Center
 Dimensions Overall (Bottom Piece): 7.9 × 12.1cm (3 1/8 × 4 3/4 in.)
Overall (Top Piece): 13.7 × 7.6cm (5 3/8 × 3 in.)
Overall (As if assembled): 21.6 × 12.1cm (8 1/2 × 4 3/4 in.)
 Materials White metal (visually characteristic of stainless steel), iron alloy, copper alloy, glass, high-fired ceramic
 Inventory Number A19760724000 Credit Line Transferred from the National Aeronautics and Space Administration Data Source National Air and Space Museum Restrictions & Rights Usage conditions apply
For more information, visit the Smithsonians Terms of Use.