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• W2322888973 abstract "Estimation of aerodynamic models of damaged aircraft using an innovative differential vortex lattice method tightly coupled with extended Kalman filters is discussed. The approach exploits prior knowledge about the undamaged aircraft to reduce the order of the estimation problem. Three different extended Kalman filter formulations are given, together with a comparative analysis. An approach for designing test maneuvers to improve the observability of the system dynamics is also discussed. Algorithms given in this paper can be used as the basis for online derivation of aircraft performance model, which can then form the basis for designing safe landing guidance laws for damaged aircraft. I. Introduction daptive control of damaged aircraft is being investigated at NASA and other aerospace research laboratories in the U.S. 1,2 The focus of these research efforts has been in maintaining control over the attitude dynamics of the damaged aircraft. Assuming that the aircraft remains controllable at its current flight conditions, it is important to be able to predict its performance at other flight conditions in order to derive maneuver constraints that should be enforced to ensure safe transition of the aircraft to landing configuration. The objective of the research discussed in this paper is to develop estimation schemes for rapidly extracting the aerodynamic parameters of damaged aircraft to enable the assessment of aircraft performance. The performance data of interest include flight envelope boundaries and maneuver limits. This data can form the basis for the design of safe landing guidance laws. Several innovative concepts have been advanced in this paper. Firstly, a rapid approach for deriving aerodynamic models of damaged aircraft termed as the Differential Vortex Lattice Method (DVLM) was developed. This approach recasts the well known Vortex Lattice Method (VLM) 3 to reduce the dimension of the aerodynamic problem. The DVLM formulation exploits prior knowledge about the airframe to create a low-order computational methodology for relating the changes in the vehicle geometry due to damage to its aerodynamic parameters. This low-order method can be implemented in real-time onboard for the aircraft to provide estimates of the aerodynamic parameters for use in the computation of flight envelope and maneuver limits, and for adaptive guidance law synthesis. Approaches for estimating the maneuver limits and structural dynamic characteristics are also outlined. Secondly, the Extended Kalman filtering (EKF) approach 4-6 is employed for online estimation of damaged aircraft parameters based on the DVLM. Design of maneuvers for enhancing the observability of the damaged aircraft model parameters is also discussed. The model parameters derived from the estimator can be used for computing the flight envelope and the maneuver limits. These can then be used in the synthesis of safe guidance laws for landing the aircraft. Unlike the airframe stabilization problem, the guidance task is almost entirely based on predictive information about the aircraft dynamics. For instance, landing guidance requires the aircraft to slow down to the approach speeds while descending to the correct altitude at a specified heading. Since damaged aircraft may have a high drag and lower stall angle of attack, the aircraft energy has to be carefully managed to ensure that adequate lift is maintained until flare altitude and touchdown. This will require energy conservative maneuvers and descent strategies. Since damaged aircraft may not be able to employ all its high-lift devices, its speed must be carefully managed to avoid premature loss of lift. These factors make it important to derive a reasonably accurate performance model of the aircraft for the design of a viable guidance system. It may be noted that although most inner-loop flight control systems operate well within the limits of controllability most of the time, the guidance task often involves operating near the edges of the operational envelope." @default.
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• W2322888973 date "2009-06-14" @default.
• W2322888973 modified "2023-09-22" @default.
• W2322888973 title "Nonlinear Filter Formulation for Rapid Estimation of Damaged Aircraft Performance" @default.
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• W2322888973 doi "https://doi.org/10.2514/6.2009-6087" @default.
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