Projectile Parameter Estimation Using Meta-Optimization

Gross, Matthew; Costello, Mark

doi:10.2514/6.2016-0538

Cited by 2 publications

(4 citation statements)

References 21 publications

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“…We differ from traditional linear theory here in keeping time as the independent variable. The linear epicyclic model is given in equations ( 9), (10), (11), ( 12), ( 13), ( 14), (15), and (16).…”

Section: Fixed-plane Linear Modelmentioning

confidence: 99%

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Spark range data reduction using a Gauss collocation method

Burchett

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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A new method is proposed for reducing spark range data using a Gauss pseudospectral collocation. Existing methods use numerical integration to propagate the differential equation model and its sensitivities forward in time. Here, a collocation method is used to transcribe the differential equations into algebraic ones that are easily solved. Realizing that the auxiliary equations used to find model sensitivities are linear, a second transcription renders a set of linear algebraic equations that solve exactly for the needed sensitivities without iteration. Thus, measurement sensitivities with respect to initial conditions and aerodynamic parameters are easily found through solution of a set of linear algebraic equations. The method is demonstrated on a set of actual data from the M898 155-mm projectile. For models using fixed-plane coordinates, and only the 10 most influential aerodynamic coefficients, the new method produces results that rival established commercial codes in accuracy.

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Section: Fixed-plane Linear Modelmentioning

confidence: 99%

“…13 A recent work also explored meta-optimization of the search algorithm itself. 11 All of these studies use time proven numerical integration techniques, however, and do not break with this 50 year old paradigm. When these methods are implemented apart from compiled code, they can be extremely slow.…”

Section: Introductionmentioning

confidence: 99%

Spark range data reduction using a Gauss collocation method

Burchett

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…The four baseline projectiles were tested in order to gather aerodynamic data for the basic airframe, which could then be used to extract microspoiler forces and moments from the controlled shots. Given the spark range data, aerodynamic coefficient estimation was performed using the Projectile Aerodynamic Coefficient Estimation (PACE) tool developed by Montalvo and Costello [27] and Gross and Costello [28]. PACE is an advanced parameter estimation tool that compares simulation data from a projectile dynamic model to observed experimental data using the output error method (or maximum likelihood).…”

Section: Flight Experimentsmentioning

confidence: 99%

“…Using a set of spark range data, the PACE tool runs a projectile simulation and optimizes the underlying aerodynamic parameters until the error between the simulated trajectory and the spark range trajectory is minimized in the least-squares sense. The code uses a so-called meta-optimization routine to choose between a suite of different solvers in order to obtain the globally optimal solution for the aerodynamic parameters [28].…”

Section: Flight Experimentsmentioning

confidence: 99%

Actuator Design and Flight Testing of an Active Microspoiler-Equipped Projectile

Kim

Strickland

Gross

et al. 2017

Journal of Dynamic Systems, Measurement, and Control

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Actively controlled gun-launched projectiles require a means of modifying the projectile flight trajectory. While numerous potential mechanisms exist, microspoiler devices have been shown to be a promising control actuator for fin-stabilized projectiles in supersonic flight. These devices induce a trim force and moment generated by the boundary layer–shock interaction between the projectile body, rear stabilizing fins, and microspoilers. Previous investigations of microspoiler mechanisms have established estimates of baseline control authority, but experimental results have been restricted to cases in which the mechanism was statically deployed. This paper details the design and flight testing of a projectile equipped with a set of active microspoilers. A mechanical actuator is proposed that exhibits unique advantages in terms of robustness, simplicity, gun-launch survivability, and bandwidth compared to other projectile actuator mechanisms considered to date. A set of integrated test projectiles is constructed using this actuator design, and flight experiments are performed in which the microspoilers are oscillated near the projectile roll frequency. Data obtained from these flight tests are used in parameter estimation studies to experimentally characterize the aerodynamic effects of actively oscillating microspoilers. These predictions compare favorably with estimates obtained from computational fluid dynamics (CFD). Overall, the results presented here demonstrate that actively controlled microspoilers can generate reasonably high levels of lateral acceleration suitable for trajectory modification in many smart-weapons applications.

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Projectile Parameter Estimation Using Meta-Optimization

Cited by 2 publications

References 21 publications

Spark range data reduction using a Gauss collocation method

Spark range data reduction using a Gauss collocation method

Actuator Design and Flight Testing of an Active Microspoiler-Equipped Projectile

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