Infrared Imaging Sensor Payload for High Speed Flight Environments

OUSD (R&E) CRITICAL TECHNOLOGY AREA(S): Hypersonics; Trusted AI and Autonomy The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with the Announcement. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. OBJECTIVE: Build a prototype EO/IR sensor payload that can survive March 5+ flight conditions and collect infrared imagery through air vehicle window as well as internal vehicle conditions in flight experiment. DESCRIPTION: In recent years, several window cooling techniques have been demonstrated as feasible options for reducing wavefront distortion and boresight error in high speed and high temperature EO/IR imaging applications. As window technology advances, there is a need for development and demonstration of infrared sensor payloads capable of surviving high speed flight environments. The objective of this project is to build a prototype EO/IR sensor payload that can survive high temp flight conditions and collect infrared imagery through the vehicle window as well as measure the thermal gradient on the inside of the window in a flight experiment. A successful prototype could be used to 1) evaluate window cooling, 2)support seeker modeling (aero-optical, aero-thermal, radiometrics, long range effects), 3) demonstrate sensor performance, mounting, and environmental survivability to support the development of future EO/IR seekers. The following challenges must be addressed: - Sensor survivability/capability in high temperatures and extreme vibration profiles - Sensor waveband, location, mounting, isolation, and cooling - Data management hardware and software to interface with vehicle telemetry and power systems for camera data (and other sensors) must consider data buffering, compression, framerate, integration time, and resolution management, and encryption Project deliverables will include a complete sensor payload prototype, environmental testing, telemetry packaging, vehicle integration, flight support and post-test analysis. Phase III or follow-on projects will mature flight-proven sensor payload to EO/IR seeker package. PHASE I: As this is a Direct-to-Phase-II (D2P2) topic, no Phase I awards will be made as a result of this topic. To qualify for this D2P2 topic, the Air Force expects the applicant(s) to demonstrate feasibility by means of a prior Phase I-type effort that does not constitute work undertaken as part of a prior or ongoing SBIR/STTR funding agreement. Applicant(s) may demonstrate feasibility in the following manner(s): Sensor development and data management technique demonstrated through previous lab, field, or flight demonstration. Modeling or demonstration showing feasibility of hardware survivability in flight conditions (thermal, vibe, and pressure). Design schematics or hardware prototype of sensor payload and vehicle integration. PHASE II: The following objectives should be considered: -Work with government team to define requirements and design experiment. Coordinate with vehicle and/or window provider maybe required. -Provide a calibrated infrared sensor and optics for looking through window. Must be in transmissive waveband of window material. -Provide a calibrated infrared sensor and optics for looking at window to capture window temperature gradient. Depending on window material, the waveband should be in the absorption region of the window material, or a window coating may be required. -Design high speed/temp sensor experiment payload. Includes infrared camera(s), thermocouples, data acquisition modules, and supporting material. Complete prototype. -Design data management hardware and software to interface with vehicle telemetry and power systems for camera data and other sensors. -Design and manufacture mechanical brackets for controller and sensor mounting. -Environmental testing of the unit to include thermal cycle, vibration and possibly others based on budget, vehicle, and program needs. -Conduct vehicle integration of electronics to include power and telemetry. Coordinate with vehicle integration team on telemetry format. -Support high speed flight experimentation, including integration, testing, and post flight data analysis. PHASE III DUAL USE APPLICATIONS: Sensor payload demonstrated in high speed environment must transition to a USAF platform through industry partnership or DoD sponsorship. Phase 3 work will focus on transitioning from high speed payload to a complete seeker system, including IR sensor, window, structure, cooling mechanism, shroud, etc. This system must be developed and demonstrated through ground and/or flight testing in relevant high speed conditions. Elements of cooled windows will likely leverage industry partners for state-of-the-art window cooling technologies. The following objectives should be considered: - Sensor design - Window design - Cooling mechanism - Mounting / survivability - Host Vehicle platform - Testing REFERENCES: 1. Tucker, B. and J. Sole, Advanced Cooling Approach for an Aerodynamically Heated Weapon IR Window. 2016, Air Force Research Laboratory SBIR Phase II Final Report. 2. Brooks, L.C., Kalin, D.A., and Peters, B.R. Experimentally simulated aero-Optic measurements through multi-aperture windows. In Window and Dome Technologies and Materials III (San Diego, CA,1992), SPIE, pp.358 366. Volume 1760. 3. Harris, D.C. Materials for Infrared Windows and Domes. SPIE, 1999. KEYWORDS: Infrared imaging; sensor payload; seeker; EO/IR; high-speed