Charge coupled devices (ccds) have been the dominant optical-wavelength detector architecture for high-end optical imaging applications for decades. However, ccds are inoperable below 120K due to…

This federal contract award, valued at $199,534.00, was issued by the National Aeronautics and Space Administration (NASA) to the Rochester Institute of Technology (RIT) under a Cooperative Agreement. The purpose of the contract is to develop and fly a cryogenic Complementary Metal-Oxide-Semiconductor (CMOS) camera instrument for attitude sensing and control of low-temperature sub-orbital payloads. This technology is intended to enable new instrument capabilities for spacecraft and sounding rockets operating in cryogenic environments. The project will involve an undergraduate student-led team, who will be responsible for the design, development, and testing of the instrument, as well as integration with the sounding rocket. This contract does not have a set-aside designation, and the period of performance is from May 2016 to May 2019.

Charge coupled devices (ccds) have been the dominant optical-wavelength detector architecture for high-end optical imaging applications for decades. However, ccds are inoperable below 120K due to electron freeze-out effects, prohibiting their use in space exploration applications requiring cryogenic temperatures. Mega-pixel complementary metal-oxide-semiconductor (cmos)devices are known to work at temperatures as low as 10 k, suggesting that imaging devices based on this technology would operate in cryogenic environments without requiring active heating. In this program, we will take the first step to maturing this technology for flight applications in the cryogenic regime by developing and flying an attitude-sensing camera employing a low noise, high quantum efficiency cryogenic cmos detector. By implementing an alternative imaging technology, we address NASA's major objective to "transform NASA missions and advance the nation's capabilities by maturing crosscutting and innovative space technologies." this technology WIU enable instruments ranging from actively-cooled star trackers for sounding rockets to low-temperature deep space cameras. As proof of this potential, we propose to use this instrument to enable a scientific study in which we MIL search for diffuse light around galaxies. This investigation is a hands-on experiential learning experience that will develop the technical and leadership skills of a diverse and multi-disciplinary undergraduate student-led team. The team will consist of at least six undergraduates, one graduate student mentor, a faculty principal investigator, and TV/o faculty mentors. The undergraduates WIH execute the project, with responsibility for the mechanical, optical and electrical engineering systems; firmware/algorithm development; flight planning and operations; and documentation and administration. The graduate student and faculty mentors will help train and advise the team. The principal investigator, who has significant experience working on a variety of space-flight projects, WUI guide and provide oversight for the project, which will span an 18 month period beginning in january 2016. In this investigation, we will develop and fly an instrument for attitude regulation of cryogenic payloads. Images from the 5.5 megapixelcmos sensor operating at 77K will be processed by on-board software, and pointing information will be used to determine control inputs to a celestial attitude control system. The instrument will flrst fly on a black brant IX technology demonstration flight, followed by a second deployment on a black brant IX science mission. Successful implementation of this instrument requires the development of various sub-systems. The mechanical/optical sub-system comprises a cryostat, optical camera, and interfaces to the sounding rocket. The electrical sub-system requires interface, control, and readout/processing components. Finally, the attitude sensing and control sub-system comprises the on-board flrmware and software designed to detect STARS, track the payload drift, and compute control inputs to the on-board attitude control systems. After each sub-system is built and tested at the component level, IT will be integrated into the full instrument. When the instrument is operational and has been fully characterized, the student team will travel to wallops flight facility in virginia to integrate IT with the rocket systems. Launch readiness will be achieved by the end of september 2016. The technology demonstration flight is currently scheduled for november 2016, giving 6 weeks of schedule reserve. Following a successful initial flight, we will modify the attitude correction algorithms in response to the achieved system performance, and a revised version of the camera WIU be flown as part of the science payload by late february 2017.