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Harford, NY, United States

Grant
Agency: Department of Defense | Branch: Air Force | Program: SBIR | Phase: Phase I | Award Amount: 100.00K | Year: 2007

Clear Science Corp. proposes to design wind tunnel and computational experiments for testing feedback systems that control flow over a three-dimensional turret, motivated by the relationship between flow dynamics and the performance of an optical system housed in the turret. The closed-loop control system that will be developed in Phase I consists of a reduced-order model of the flow, measurement-based estimators, and control input-performance output algorithms and regulators that relate variables in the low-dimensional model to actuator inputs and the control objective. The measurement system will utilize a small array of sensors located on the turret to estimate the flow dynamics above the turret. Several representations of performance output will be evaluated beginning with direct relationships between flow dynamics and the low-dimensional model variables. A computational platform will be developed for designing control systems through control-in-the-loop CFD simulations. The experimental test design will consist of two stages: controller design through off-line data acquisition and control-in-the-loop wind tunnel runs. In the first stage, three-component Particle Image Velocimetry measurements and surface measurements will provide data for constructing the low-dimensional model and measurement-based estimator. In the second stage, the estimators, input-output algorithms, and regulators will be integrated into a command-and-control system for controlling flow over the three-dimensional turret in a series of wind tunnel tests.


Grant
Agency: Department of Defense | Branch: Air Force | Program: STTR | Phase: Phase II | Award Amount: 750.00K | Year: 2005

Clear Science Corp. and the University of California at Los Angeles propose to develop a versatile and comprehensive computational toolbox for designing feedback flow controllers in aerodynamic applications. Target objectives include separation control to manage lift and drag, control of transition to turbulence, turbulence control to reduce skin friction drag, increase mixing, or reduce heat transfer, and control of acoustical output (noise suppression). The software is designed to meet important military objectives including greater stealth, agility, and mission scope in aircraft and weapon systems. The toolbox will be modular with interchangeable low-dimensional models and controller designs. During Phase I, our team has developed and demonstrated the technical merit and feasibility of four major components of the flow control system: the plant estimator, the performance output algorithm, the measurement algorithm, and the compensator. Phase II objectives include controller-in-the-loop CFD simulations that demonstrate robust, closed-loop control of aerodynamic forces on an airfoil using the system components developed in Phase I, advanced algorithms to extend control effectiveness over a wide range of flow conditions, and a toolbox framework of interfaces with CFD codes, model and controller libraries, and interfaces with control design software.


Grant
Agency: Department of Defense | Branch: Air Force | Program: SBIR | Phase: Phase II | Award Amount: 739.49K | Year: 2015

ABSTRACT:Clear Science Corp. proposes to develop and demonstrate software that enables safer, more efficient and accurate flight testing of military aircraft. The computational tool is designed to reduce costs by identifying critical and benign areas in the operational envelope and using the information to streamline testing. The proposed technology systematically merges modeling and simulation (M&S) and test and evaluation (T&E) to optimize the warfighters that are designed, produced, and tested by the U. S. military. The modeling technology will also reduce risk by providing reliable predictions to clear aircraft for successive test points prior to flight sorties. The proposed modeling technology is physics-based, leveraging the accuracy of high-fidelity models at a fraction of the computational expense. The software will be developed and tested with existing data from the X-53 Active Aeroelastic Wing (AAW) Flight Test Program. The program included a comprehensive set of flutter, loads, and handling qualities tests of a modified F-18A fighter aircraft, generating data that are representative of the types typically produced during military aircraft certification. Models will be calibrated in near real time in a series of tests that utilize flight data in the same chronological sequence that they became available during the flight tests.BENEFIT:The commercial product to be developed is flight test support software that enables near real-time predictions and model updating with flight data. The primary customers will be flight test facilities including the 412th Test Wing at Edwards Air Force Base. The tool will be configured for the full range of fixed-wing aircraft that undergo flight testing by the U. S. military. Applications include flutter, loads and handling qualities tests. Defense budget constraints require expanding mission roles in the existing military fleet with adaptable external store configurations and flight envelopes that require a continuing series of flight testing. The proposed software is designed to make this process safer, more reliable, and less expensive through more accurate and faster predictions during the course of each flight test, along with the ability to quickly adjust test plans based on systematic identification of the critical drivers of static and dynamic loading on the aircraft. Commercial opportunities for the software exist with military aircraft manufacturers including Lockheed Martin, Boeing, and Northrop Grumman. Non-military applications extend to commercial aircraft with a large potential commercial market. Other applications include loads testing on rotorcraft and launch vehicles.


Grant
Agency: National Aeronautics and Space Administration | Branch: | Program: SBIR | Phase: Phase I | Award Amount: 125.00K | Year: 2016

Clear Science Corp. proposes to develop and demonstrate computational fluid dynamics (CFD)-based, reduced-order aeroservoelasticity modeling and simulation technology for fast and accurate predictions of nonlinear flight dynamics, enabling real-time, piloted and unpiloted flight simulations and providing a tool to design flight controllers for highly flexible, lightweight aircraft. Physics-based, reduced-order models (ROMs) will be developed and demonstrated with data from CFD models of the X-56, an experimental aircraft that NASA and the U. S. Air Force are using to test systems for flutter suppression and gust-load alleviation. Extended range and low fuel consumption through lightweight materials and large wing spans (high lift-to-drag ratios) are the drivers in next-generation aircraft like the X-56, but these attributes create challenges in maintaining flight safety, ride quality, and long-term structural durability. The development of flight controllers that can actively manage aeroservoelastic effects (body-freedom flutter, control reversal, gust loading) without compromising safety and aerodynamic performance is a key objective of both the X-56 Program and the proposed project. Through the proposed technology, nonlinear, aeroservoelastic ROMs can be coupled to other components of a flight simulator (six-degrees-of-freedom flight mechanics models and control software) to improve the fidelity of simulations that support controller design for a wide range of operating conditions.


Grant
Agency: Department of Defense | Branch: Air Force | Program: SBIR | Phase: Phase II | Award Amount: 749.96K | Year: 2009

Clear Science Corp. proposes to develop Aeroelastic Model Updating (AMU) software that enables safer, more efficient and accurate flutter testing of military aircraft. Aircraft certification involves a battery of expensive and sometimes risky flight tests. The proposed tool will reduce costs by reducing required hours of flutter testing and will reduce risk by providing supplemental aeroelastic-response data to test personnel prior to and during flight tests. The software consists of low-dimensional, computationally efficient models that predict aeroelastic responses in aircraft during flight tests and that can be calibrated or updated with flight data as they become available. The computational efficiency of the reduced-order models facilitates the required quick turnaround of predictions that is not possible with high-dimensional aeroelastic models. Phase I applied the method in predicting aeroelastic responses of an AGARD 445.6 wing, demonstrating the technical merit and feasibility of the approach. Phase II will transition the technology to applications involving full aircraft configurations with large, computationally intensive simulations and large numbers of aeroelastic modes. Using the software to fuse data from multiple sources will facilitate more informed decisions during the aircraft certification process, will lower program costs, and will reduce risk to pilots and aircraft. BENEFIT: The commercial product that Clear Science Corp will develop is a computational toolbox for modeling aeroelastic responses in flight vehicles and using data from different sources to update and calibrate the models. The software is designed to enhance and streamline flight certification testing required in military aircraft by providing model predictions in real time during tests. Potential military applications range from fixed-wing aircraft to rotorcraft, munitions, and next-generation air platforms like micro-air vehicles. The design process relies on a mixture of laboratory testing, computational modeling, and final performance evaluations in a variety of products. The proposed software is designed to accommodate data from both simulations and field tests in a range of engineering problems with the intent of maximizing marketability. Potential uses extend from aeroelasticity analyses to CFD-based aerodynamic, aerothermodynamic, and aero-acoustic analyses and beyond to a host of engineering disciplines in and outside the aerospace industry. The primary pool of potential customers consists of DoD agencies, NASA, US government contractors, and commercial businesses that develop, design, and test products involving fluid-structure interaction as it relates to efficient and safe operation. Commercial business sectors include the aerospace, automotive, medical, and manufacturing industries.

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