Picard Iteration for Parameter Estimation in Nonlinear Dynamic Models of Aircraft and Spacecraft
Aleksandr Talitckii, Matthew Peet

TL;DR
This paper introduces a parameter estimation method for nonlinear aircraft and spacecraft models using Picard iteration, avoiding direct derivative measurement and handling noisy, partial data.
Contribution
The paper presents a novel parameter estimation approach based on Picard iteration and gradient contraction, applicable to complex nonlinear ODE models of aircraft and spacecraft.
Findings
Successfully estimated spacecraft inertia tensor from experimental data.
Accurately identified 28 control surface coefficients for F/A-18 aircraft.
Method effectively handles noisy, sparse, and partial observational data.
Abstract
The attitude dynamics of aircraft and spacecraft exhibit significantly nonlinear behaviour. In spacecraft, torque is generated through reaction wheels and control moment gyros. In aircraft, torque is generated using lift on control surfaces. In both cases, complex geometries, unique configurations, and internal/environmental changes imply that models must be identified, verified, and updated using in-flight experimental data. However, this data is often noisy, sparsely sampled, and partial in that modeled states may not be directly measurable. In this paper, we propose a method for estimating key parameters in realistic Ordinary Differential Equation (ODE) models of both spacecraft and aircraft dynamics. This method avoids the need to directly measure state derivatives by coupling sampled outputs using the Picard mapping -- an integral constraint on the solution of the parameterized…
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