ROM should be validated against a full aircraft configurations and flight test data from subsonic through supersonic flight regimes to demonstrate readiness for Phase II. PHASE I: Research in this phase should focus on development and validation of the core ROM technology, assure that the technology is robust across a realistic range of flight conditions and inputs/surface deflections. There are models and data in the public domain that are appropriate for this research. If successful this research will not only provide a key analysis capability to enable future test programs to execute structures testing more efficiently, but will also provide the bases for training both discipline engineers as well as Test Pilot School students.īecause of proprietary issues the government will not be able to provide models or data to aid this research. The tool should be capable of implementing an arbitrarily complex control system and it is also highly desirable that the tool be capable of using flight test data to update the ROM in a way that will improve the accuracy for subsequent simulations. It is highly desirable that educational scenarios be developed for the pilot-in-the-loop simulator from mild onset flutter to sudden flutter onset. Third, it is to be operated as a pilot-in-the-loop aeroservoelastic/aeroelastic simulator. Second, it is to operate as a real time system that utilizes surface deflections and state parameters from live flight testing to provide an analytical estimate of aeroelastic/aeroservoelastic stability and aerodynamic loads for the maneuver as flown to be compared to flight test data. First, it is to operate as a predictive tool to estimate aeroelastic/aeroservoelastic stability and aerodynamic loads prior to testing. The resulting technology is to be operated in three capacities. The simulation should output 6DOF flight path, the deformation history at pre-specified points (arbitrary points specified prior to ROM creation) on the aircraft, aircraft load state histories at specified stations, and time histories of aircraft state parameters. The purpose of this topic is to research and develop innovative methods to adapt ROM techniques to rapidly solve the aeroservoelastic equations of motion for six degrees of freedom (6DOF) and flexible modes much faster than real time, given stick and rudder or surface deflections, and aircraft states (Mach number or airspeed, pressure altitude, initial side slip and angle of attack, etc.). The same real time technology could also be used in a pilot-in-the-loop simulator to improve the effectiveness of mission rehearsals. A real-time predictive analysis capability that can be run during a flight test sortie in order to compare flight test results to "as flown" predictive analysis results would help expedite test and improve safety by providing a better understanding of the aircraft being tested. In addition simulators used to prepare pilots and engineers often do not directly implement the aeroelastic effects into their algorithms limiting the effectiveness of these training sessions. This source of error adds to the other sources of error inherent in this type of testing resulting in tight tolerances and added test points. Consequently the "as flown" flight data is compared to the "as planned" predictive analysis. OBJECTIVE: Adapt reduced order modeling (ROM) techniques to develop a flight simulation and real time simulator capable of predicting aircraft aeroservoelastic response for pilot-in-the-loop simulations or from surface positions provided by a live flight test.ĭESCRIPTION: Currently predictive analysis for flutter and loads testing is accomplished using full order models that are expensive and time consuming to perform.
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