Real-time Parameter-Varying AeroThermoServoElasticity Reduced Order Model for Control System Design

ABSTRACT:The overall goal of the project is to develop reliable reduced order modeling technologies to automatically generate parameter-varying aerothermoservoelastic (ATSE) reduced-order models (ROMs) for fast Fluid-Thermal-Structural Interactions (FTSI) assessment and control system design. The Phase I effort will focus on developing several key components, including parameter-varying formulation of hypersonic FTSI, aerothermodynamic ROMs, thermostructural dynamics ROMs, as well as a strategy to integrate these ROMs along with sensor, actuator, and control law for closed-loop control analysis in broader hypersonic flight envelope. A modular software framework will be established for automated data exchange, aerothermodynamic and thermostructural ROM generation, ROM integration, computation, and verification. The feasibility of the proposed technology will be demonstrated for several ATSE test problems of AFRL interest. The Phase II effort will focus on: (1) ROM engine optimization in terms of functionality, execution efficiency, and automated parameter selection; and (2) software environment enhancements with direct interfacing to AFRL-relevant software architecture for closed-loop guidance and control simulation, and fully automated ROM process for facile technology insertion and transition; and (3) extensive software validation and demonstration for ATSE and flight control analysis of complex airframe configuration of current AFRL interest. BENEFIT:The proposed technology will provide a fast and accurate ROM tool for FTSI analysis and closed-loop ATSE simulations of aerospace vehicles and aircrafts. USAF applications of the technology include: (1) comprehensive studies and understanding of FTSI, its trajectory path dependence, and its impact on aeroelastic instability and control system; (2) rapid and computationally affordable assessment (sensitivity analysis, uncertainty quantification, etc.) for optimal aerodynamic, thermal, and structural design of high-speed aerospace vehicles; (3) development of advanced, reliable control strategies (such as controlled flight parameter, surface controls, etc.); and (4) arrangement of test procedures for rational use of instruments and facilities. The success in the proposed research will markedly reduce the development cycles of aerospace vehicles and aircrafts at reduced costs. Among non-DoD applications, the proposed software will find use in various engineering sectors, including NASA, aerospace, automobile, combustion, power, chemical plants, biomedical, among others. The product would directly contribute to these vital areas by enabling accurate, real-time, parametric analysis and prediction capabilities, which can be used in (1) efficient simulation for concept evaluation and optimized design with dramatically shorter turnaround time; (2) on-field system diagnostics and troubleshooting, (3) sensitivity analysis and correlation identification of system parameters; and (4) advanced control strategies for on-line process monitoring and control.