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1. Summary This paper will discuss a three year research program being conducted by the Boeing Phantom Works, St. Louis, MO. This program addresses the NASA Integrated Resilient Aircraft Control (IRAC) Topic 1.3, Dynamic Flight Envelope Assessment and Prediction. The Dynamic Flight Envelope Assessment and Prediction system will provide NASA with flight safety enhancements through a process to identify on-line fault anomalies for a damaged air vehicle, and measure changes in structure dynamics mode shapes due to the damage. The system also provides adaptive control to maintain the damaged aircraft within allowable structure limits and suppress any adverse, dynamic structural mode interaction with the flight control system. The primary focus of this paper is on ControlCentric Modeling, combining rigid body models with dynamic flexible structure and loads models to provide the basis for on-line adaptive control of the structure load properties of the aircraft. This system addresses structural anomalies caused by battle damage to military aircraft and structure failures to civil aircraft caused by incidents such as fatigue, composite structure delamination, corrosion, mid-air collisions, or improper assembly. Products will be algorithms and processes that can provide safe control of structures for damaged tactical and transport aircraft. The development approach builds on the NASA Intelligent Flight Control System technology, already demonstrated on a research F-15 for adaptive control of the aerodynamic capability of a damaged aircraft. This basis will be reviewed in the paper. The significance of this program is to add a control capability to prevent exceeding structure load limitations or dynamic interaction on an aircraft that experiences failures to structure elements, thereby increasing the safety and survivability of air vehicles. 2. Program Objectives The objectives of this program are to |
