Affect upon Aeroballistic Parameter Identification from Flight Data Errors

Abate, Gregg; Klomfass, Arno

doi:10.2514/6.2005-439

Cited by 4 publications

(2 citation statements)

References 1 publication

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“…While this technique is the most accurate method for obtaining aerodynamic data on a specific projectile configuration, it is usually the most expensive alternative, requires a spark range facility, and strictly speaking is only valid for the specific projectile configuration tested. More recently, aerodynamic parameters have been estimated using a combination of radar data and on-board instrumentation [31,32].…”

Section: Introductionmentioning

confidence: 99%

Using computational fluid dynamic/rigid body dynamic results to generate aerodynamic models for projectile flight simulation

Costello

Gatto

Sahu

2008

Proceedings of the Institution of Mechanical Engineers, Part G:

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A method to efficiently generate a complete aerodynamic description for projectile flight dynamic modelling is described. At the core of the method is an unsteady, time accurate computational fluid dynamic simulation that is tightly coupled to a rigid projectile flight dynamic simulation. A set of short time snippets of simulated projectile motion at different Mach numbers is computed and employed as baseline data. For each time snippet, aerodynamic forces and moments and the full rigid body state vector of the projectile are known. With time synchronized air loads and state vector information, aerodynamic coefficients can be estimated with a simple fitting procedure. By inspecting the condition number of the fitting matrix, it is straightforward to assess the suitability of the time history data to predict a selected set of aerodynamic coefficients. The technique it is exercised on an exemplar fin-stabilized projectile with good results.

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Section: Introductionmentioning

confidence: 99%

Using computational fluid dynamic/rigid body dynamic results to generate aerodynamic models for projectile flight simulation

Costello

Gatto

Sahu

2008

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…At a discrete number of points during the flight of the projectile (< 30) the state of the projectile is measured using spark shadowgraphs [23][24][25][26][27]. The projectile state data is subsequently fit to a rigid 6 degree-of-freedom projectile model using the aerodynamic coefficients as the fitting parameters [28][29][30]. Spark range aerodynamic testing is considered the gold standard for projectile aerodynamic coefficient estimation.…”

Section: Introductionmentioning

confidence: 99%

Generating an aerodynamic model for projectile flight simulation using unsteady time accurate computational fluid dynamic results

Kokes¹,

Costello²,

Sahu³

2007

WIT Transactions on Modelling and Simulation, Vol 45

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A method to efficiently generate a complete aerodynamic description for projectile flight dynamic modeling is described. At the core of the method is an unsteady, time accurate computational fluid dynamics simulation that is tightly coupled to a rigid body dynamics simulation. A set of n short time snippets of simulated projectile motion at m different Mach numbers is computed and employed as baseline data. For each time snippet, aerodynamic forces and moments and the full rigid body state vector of the projectile are known. With time synchronized air loads and state vector information, aerodynamic coefficients can be estimated with a simple fitting procedure. By inspecting the condition number of the fitting matrix, it is straight forward to assess the suitability of the time history data to predict a selected set of aerodynamic coefficients. To highlight the merits of this technique it is exercised on example data for a fin stabilized projectile. The technique is further exercised for a fin and spin stabilized projectile using simulated data from a standard trajectory code.

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Generating an Aerodynamic Model for Projectile Flight Simulation Using Unsteady, Time Accurate Computational Fluid Dynamic Results

Kokes¹,

Costello²,

Sahu³

2006

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing the burden, SPONSOR/MONITOR'S ACRONYM(S)ARL-CR-577 SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)U.S. Army Research Laboratory ATTN: AMSRD-ARL-WM-BC Aberdeen Proving Ground, MD 21005-5066 SPONSOR/MONITOR'S REPORT NUMBER(S) DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution is unlimited. SUPPLEMENTARY NOTES ABSTRACTA method to efficiently generate a complete aerodynamic description for projectile flight dynamic modeling is described. At the core of the method is an unsteady, time accurate computational fluid dynamics simulation that is tightly coupled to a rigid body dynamics simulation. A set of n short time snippets of simulated projectile motion at m different Mach numbers is computed and employed as baseline data. For each time snippet, aerodynamic forces and moments and the full rigid body state vector of the projectile are known. With time synchronized air loads and state vector information, aerodynamic coefficients can be estimated with a simple fitting procedure. By inspecting the condition number of the fitting matrix, it is straightforward to assess the suitability of the time history data to predict a selected set of aerodynamic coefficients. To highlight the merits of this technique, it is exercised on example data for a fin-stabilized projectile. The technique is further exercised for a fin-and spinstabilized projectile using simulated data from a standard trajectory code. iii

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Affect upon Aeroballistic Parameter Identification from Flight Data Errors

Cited by 4 publications

References 1 publication

Using computational fluid dynamic/rigid body dynamic results to generate aerodynamic models for projectile flight simulation

Using computational fluid dynamic/rigid body dynamic results to generate aerodynamic models for projectile flight simulation

Generating an aerodynamic model for projectile flight simulation using unsteady time accurate computational fluid dynamic results

Generating an Aerodynamic Model for Projectile Flight Simulation Using Unsteady, Time Accurate Computational Fluid Dynamic Results

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