Parameter Performance Comments

• Main Authors: Development Alan Delamere, Ira Becker, Jim Bergstrom, Jon Burkepile, Joe Day, David Dorn, Charlie Hamp, Jeffrey Lasco, Bill Meiers, Andrew Sievers, Scott Streetman, Steven Tarr, Paul Volmer, Ball Aerospace, Technology Corp, Near Infra-red (nir
• Other Authors: The Pennsylvania State University CiteSeerX Archives
• Format: Text
• Language: English
• Subjects: Data storage 28 Gbits All channels; South Pole; South pole
• Online Access: http://citeseerx.ist.psu.edu/viewdoc/summary?doi=10.1.1.694.4438; http://hirise.lpl.arizona.edu/HiRISE/papers/6th_mars_conf/Delemere_HiRISE_InstDev.pdf

The primary functional requirement of the HiRISE imager, figure 1 is to allow identification of both predicted and unknown features on the surface of Mars to a much finer resolution and contrast than previously possible [1], [2]. This results in a camera with a very wide swath width, 6km at 300km altitude, and a high signal to noise ratio,>100:1. Generation of terrain maps, 30 cm vertical resolution, from stereo images requires very accurate geometric calibration. The project limitations of mass, cost and schedule make the development challenging. In addition, the spacecraft stability [4] must not be a major limitation to image quality. The nominal orbit for the science phase of the mission is a 3pm orbit of 255 by 320 km with periapsis locked to the south pole. The track velocity is approximately 3,400 m/s. HiRISE Design Features The HiRISE instrument performance goals are listed in Table 1. The design features a 50 cm aperture and a detector with 128 lines of Time Delay and Integration (TDI) to create very high (100:1) signal noise ratio images.