Satellite configuration for operation in the thermosphere

An orbital satellite configured to operate at an orbital altitude that is least 50 miles above Earth, the orbital satellite comprising:

• a fuselage defining an interior area, the fuselage having a generally elongated configuration that extends along an axis of extension of the fuselage;
• an electric rocket engine coupled to the fuselage and positioned to provide a thrust force to propel the orbital satellite in a direction that generally coincides with the axis of extension, the thrust force sufficient to discourage orbital decay of the orbital satellite when operating at the orbital altitude;
• a remote sensing system positioned within the interior area, the remote sensing system including an telescopic system adapted to inwardly redirect light that enters while traveling in a first direction into the orbital satellite to a second direction, an angle between the first direction and the axis of extension being larger than an angle between the second direction and the axis of extension.