Performance/sizing relationships for a short-wave/mid-wave infrared scanning point-source detection space sensor

Many next-generation infrared space sensor systems are currently in the planning and development stages for a variety of advanced DOD, NASA, and commercial applications. These systems generally share a common theme: users and customers that demand uncompromising high performance, and sponsoring agencies that have rather limited budgets. This situation ultimately forces tough choices. Making informed decisions under these circumstances requires detailed and technically credible insight into the relationship between system performance and system cost. System-level performance must be linked to specific system architectures with well-defined infrared sensor payload, spacecraft, communications, ground, and launch system elements. In this paper we focus on a key system element: the infrared sensor payload. Altitude, resolution, sensitivity, and revisit time drive the weight, power, and design configuration of the sensor which in turn determines spacecraft sizing and launch system selection, hence the strong relationship to system cost. We have developed a linked payload model of an infrared short-wave/mid-wave infrared scanning point-source detection sensor for use in theater missile warning applications. The purpose of the linked model is to establish a credible technical relationship between sensor system performance and payload and payload subsystem weight, power and configuration.