Miniature Visible-Band Video Camera for Afterburner Probes, Hypersonic Propulsion Systems, and Combustion Driven Test Facilities

TECHNOLOGY AREAS: Ground Sea; Sensors; Electronics; Air Platform OBJECTIVE: To develop a miniature visual-video camera technology with the advanced form factor and optical performance for embedding into small, water-cooled probes for evaluating and monitoring turbine engine augmentor performance, hypersonic propulsion systems, and combustion driven test facilities. DESCRIPTION: AEDC develops and implements multi-purpose probes that are inserted into the hot, high speed, exhaust streams of gas turbine engines and hypersonic systems in order to measure pressure, temperature, velocity, species concentrations, and other performance characteristics. In particular, development of camera viewing probes has allowed unprecedented optical access to the turbine engine augmentors but current needs far exceed the capability of available visual (400-700 nm) camera technologies. Camera technologies are unavailable that meet the requirements for size, form factor, optical quality and frame rates for embedding into probes used in combustion system performance evaluation, health monitoring and diagnosis. Camera technologies are required that meet the specifications below: Design Characteristic Threshold Objective Stretch Goals ---------------------------------------------------------------------------------------------------------------- Number of pixels 1280 x 960 1600 X 1200 2048 X 2048 Frame Rate 60 fps global shutter 100 fps, global shutter 1000 fps, global shutter Form factor Cylindrical Cylindrical Cylindrical Outer Diameter 0.25 inches 0.125 inches 0.10 inches Length 2.0 inches 1.5 inches 1.5 inches Performance Life 1000 hours at relevant 1000 hours at relevant 1000 hours at relevant conditions conditions conditions Video Interface Proprietary Interface Network Camera Interface Network Camera Interface Synchronization None Two cameras synchronization Multiple camera synchronization Remote Operation Local Computer Operation over remote link Operation over remote link Ethernet link link Ethernet link Lens Fixed Lens Variable Focal Length or Remotely Focused & Zoomed Lenses Interchangeable Fixed Lenses Innovative development techniques will be required to achieve the required form factor, size, and camera performance. The innovative camera technologies will replace existing small diameter NTSC cameras that do not meet these specifications. The camera technology must be remotely controlled over an Ethernet or equivalent data link. Since the cameras will be embedded into probes inserted into the extremely harsh environment of augmented engine exhaust flows and hypersonic flows, the camera must be rugged and robust (vibrationally insensitive for internal probe temperatures up to 160 oF). Remote manual adjustments over shutter speeds and gains must also be available. PHASE I: Develop a proof of principal camera technology design capable of satisfying all objective requirements. A laboratory demonstration that the prototype components meet the vibrational and temperature requirements for extended periods of time (2 hours) is desirable. PHASE II: Develop and a prototype camera system satisfying all objective requirements and demonstrate the camera performance in a relevant environment for 100 hours, or until failure. Sequentially produce and evaluate four more working prototype systems incorporating lessons learned into the following prototype system to achieve a sufficiently robust and reliable camera technology that meets all objective requirements and/or stretch goals. PHASE III DUAL USE APPLICATIONS: Formalize the production process and design the appropriate machinery/infrastructure to support full-scale commercial production. REFERENCES: 1. Hiers, R. S. Jr. and Hiers, R. S. III, Development of High Temperature Image Probes for Viewing Turbine Engine Augmentors, AIAA-2002-2912, 22nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference, St. Louis, Missouri, 24 - 27 June 2002. 2. Hiers, R. S. III and Hiers, R. S. Jr., Development of Exit-Plane Probes for Turbine Engine Condition Monitoring, AIAA-2002-4304, 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Indianapolis, Indiana, 7-10 July 2002. 3. Beitel, G. R., Jalbert, P. A., Plemmons, D., Hiers, R. S., and Catalano, D. R., Development of Embedded Diagnostics for Internal Flow-Field Measurements in Gas Turbine Engines, AIAA 2004-6865, AIAA/USAF Developmental Test & Evaluation Summit, Woodland Hills, California, 16-18 November 2004. KEYWORDS: viewing probes; turbine engines; diagnostics; augmentors