Abstract: To maximize the light capturing and imaging resolution capability of an imaging satellite while minimizing weight, the primary reflector and other elements of the optical path have a shape optimized to the shape of the satellite. For a nanosatellite with a square cross-section, the first mirror and other elements of the telescope section in the optical path have a square cross-section, as does the sensor array of the camera section.

Abstract: A satellite imaging system uses multiple cameras. For example, the incoming light from a telescope section of the satellite goes through a dichroic beam splitter, with the standard visible spectrum going to a first camera and wavelengths outside of the standard visible spectrum, such as in the infrared or coastal blue range, are sent to a second camera, allowing image data from multiple wavelength ranges to be captured simultaneously. The image data from the different wavelengths of the two cameras can then be selectively recombined. In a more general case, there is a first range of wavelengths and a second range of wavelengths.

Abstract: A satellite imaging system includes a camera with a pixel shifting mechanism, thermally stable imaging payload, and high-stability attitude determination and control system (ADCS) to improve image resolution. To address the overall stabilization requirement, the satellite incorporates a number of design elements that, in combination, provide the stable result required for good imaging.