PETER STURDZA
Pilots at Rutherford Ave, Redwood City, CA
License number
California A3818489
Issued Date
Jan 2016
Expiration Date
Jan 2017
Category
Airmen
Type
Authorized Aircraft Instructor
Address
Address
166 Rutherford Ave, Redwood City, CA 94061
Professional information
Generating Inviscid And Viscous Fluid Flow Simulations Over A Surface Using A Quasi-Simultaneous Technique
US Patent:
2012024, Sep 27, 2012
Filed:
Mar 23, 2011
Appl. No.:
13/070384
Inventors:
Peter STURDZA - Redwood City CA, US
Yoshifumi SUZUKI - Mountain View CA, US
Yoshifumi SUZUKI - Mountain View CA, US
Assignee:
DESKTOP AERONAUTICS, INC. - Palo Alto CA
International Classification:
G06G 7/57, G06F 17/11
US Classification:
703 2, 703 9
Abstract:
A fluid-flow simulation over a computer-generated surface is generated using a quasi-simultaneous technique. The simulation includes a fluid-flow mesh of inviscid and boundary-layer fluid cells. An initial fluid property for an inviscid fluid cell is determined using an inviscid fluid simulation that does not simulate fluid viscous effects. An initial boundary-layer fluid property a boundary-layer fluid cell is determined using the initial fluid property and a viscous fluid simulation that simulates fluid viscous effects. An updated boundary-layer fluid property is determined for the boundary-layer fluid cell using the initial fluid property, initial boundary-layer fluid property, and an interaction law. The interaction law approximates the inviscid fluid simulation using a matrix of aerodynamic influence coefficients computed using a two-dimensional surface panel technique and a fluid-property vector. An updated fluid property is determined for the inviscid fluid cell using the updated boundary-layer fluid property.
Predicting Transition From Laminar To Turbulent Flow Over A Surface
US Patent:
8538738, Sep 17, 2013
Filed:
Mar 22, 2011
Appl. No.:
13/069374
Inventors:
Dev Rajnarayan - Mountain View CA, US
Peter Sturdza - Redwood City CA, US
Peter Sturdza - Redwood City CA, US
Assignee:
Aerion Corporation - Reno NV
International Classification:
G06F 9/455
US Classification:
703 9, 244204, 244200
Abstract:
A prediction of whether a point on a computer-generated surface is adjacent to laminar or turbulent flow is made using a transition prediction technique. A plurality of boundary-layer properties at the point are obtained from a steady-state solution of a fluid flow in a region adjacent to the point. A plurality of instability modes are obtained, each defined by one or more mode parameters. A vector of regressor weights is obtained for the known instability growth rates in a training dataset. For each instability mode in the plurality of instability modes, a covariance vector is determined, which is the covariance of a predicted local growth rate with the known instability growth rates. Each covariance vector is used with the vector of regressor weights to determine a predicted local growth rate at the point. Based on the predicted local growth rates, an n-factor envelope at the point is determined.
Generating Inviscid And Viscous Fluid-Flow Simulations Over An Aircraft Surface Using A Fluid-Flow Mesh
US Patent:
8457939, Jun 4, 2013
Filed:
Dec 30, 2010
Appl. No.:
12/982744
Inventors:
David L. Rodriguez - Palo Alto CA, US
Peter Sturdza - Redwood City CA, US
Peter Sturdza - Redwood City CA, US
Assignee:
Aerion Corporation - Reno NV
International Classification:
G06F 17/50, G06F 7/60, G06G 7/48, G06G 7/50
US Classification:
703 9, 703 1, 703 2, 703 6, 703 7, 703 8
Abstract:
Fluid-flow simulation over a computer-generated aircraft surface is generated using inviscid and viscous simulations. A fluid-flow mesh of fluid cells is obtained. At least one inviscid fluid property for the fluid cells is determined using an inviscid fluid simulation that does not simulate fluid viscous effects. A set of intersecting fluid cells that intersects the aircraft surface are identified. One surface mesh polygon of the surface mesh is identified for each intersecting fluid cell. A boundary-layer prediction point for each identified surface mesh polygon is determined. At least one boundary-layer fluid property for each boundary-layer prediction point is determined using the at least one inviscid fluid property of the corresponding intersecting fluid cell and a boundary-layer simulation that simulates fluid viscous effects. At least one updated fluid property for at least one fluid cell is determined using the at least one boundary-layer fluid property and the inviscid fluid simulation.
Generating A Simulated Fluid Flow Over An Aircraft Surface Using Anisotropic Diffusion
US Patent:
8437990, May 7, 2013
Filed:
Mar 11, 2011
Appl. No.:
13/046469
Inventors:
David L. Rodriguez - Palo Alto CA, US
Peter Sturdza - Redwood City CA, US
Peter Sturdza - Redwood City CA, US
Assignee:
Aerion Corporation - Reno NV
International Classification:
G06F 17/10
US Classification:
703 2
Abstract:
A fluid-flow simulation over a computer-generated aircraft surface is generated using a diffusion technique. The surface is comprised of a surface mesh of polygons. A boundary-layer fluid property is obtained for a subset of the polygons of the surface mesh. A pressure-gradient vector is determined for a selected polygon, the selected polygon belonging to the surface mesh but not one of the subset of polygons. A maximum and minimum diffusion rate is determined along directions determined using a pressure gradient vector corresponding to the selected polygon. A diffusion-path vector is defined between a point in the selected polygon and a neighboring point in a neighboring polygon. An updated fluid property is determined for the selected polygon using a variable diffusion rate, the variable diffusion rate based on the minimum diffusion rate, maximum diffusion rate, and angular difference between the diffusion-path vector and the pressure-gradient vector.
Predicting Transition From Laminar To Turbulent Flow Over A Surface Using Mode-Shape Parameters
US Patent:
2013028, Oct 24, 2013
Filed:
Mar 26, 2013
Appl. No.:
13/850628
Inventors:
Dev Rajnarayan - Mountain View CA, US
Peter Sturdza - Redwood City CA, US
Peter Sturdza - Redwood City CA, US
Assignee:
AERION CORPORATION - Reno NV
International Classification:
G06F 17/50, G06N 99/00
US Classification:
706 12
Abstract:
In accordance with embodiments disclosed herein, there are provided methods, systems, and apparatuses for predicting whether a point on a computer-generated aircraft or vehicle surface is adjacent to laminar or turbulent flow is made using a transition prediction technique. A plurality of boundary-layer properties at the point are obtained from a steady-state solution of a fluid flow in a region adjacent to the point. Included in the list of boundary-layer properties are computed coefficients or weights of mode shapes that describe the boundary-layer profiles. A plurality of instability modes are obtained, each defined by one or more mode parameters. A vector of regressor weights is obtained for the known instability growth rates in a training dataset. For each instability mode in the plurality of instability modes, a covariance vector is determined, which is the covariance of a predicted local growth rate with the known instability growth rates. Each covariance vector is used with the vector of regressor weights to determine a predicted local growth rate at the point. Based on the predicted local growth rates, an n-factor envelope at the point is determined.
Generating Inviscid And Viscous Fluid-Flow Simulations Over A Surface Using A Fluid-Flow Mesh
US Patent:
2013024, Sep 19, 2013
Filed:
May 3, 2013
Appl. No.:
13/887189
Inventors:
Peter STURDZA - Redwood City CA, US
Assignee:
AERION CORPORATION - Reno NV
International Classification:
G06F 17/50
US Classification:
703 9
Abstract:
Fluid-flow simulation over a computer-generated surface is generated using inviscid and viscous simulations. A fluid-flow mesh of fluid cells is obtained. At least one inviscid fluid property for the fluid cells is determined using an inviscid fluid simulation that does not simulate fluid viscous effects. A set of intersecting fluid cells that intersects the surface are identified. A surface mesh polygon of the surface mesh is identified for each intersecting fluid cell. At least one boundary-layer fluid property for each identified surface mesh polygon is determined using the at least one inviscid fluid property of the corresponding intersecting fluid cell and a boundary-layer simulation that simulates fluid viscous effects.
Generating A Simulated Fluid Flow Over A Surface Using Anisotropic Diffusion
US Patent:
2013024, Sep 19, 2013
Filed:
May 3, 2013
Appl. No.:
13/887199
Inventors:
Peter STURDZA - Redwood City CA, US
Assignee:
AERION CORPORATION - Reno CA
International Classification:
G06F 17/50
US Classification:
703 2
Abstract:
A fluid-flow simulation over a computer-generated surface is generated using a diffusion technique. The surface is comprised of a surface mesh of polygons. A boundary-layer fluid property is obtained for a subset of the polygons of the surface mesh. A gradient vector is determined for a selected polygon, the selected polygon belonging to the surface mesh but not one of the subset of polygons. A maximum and minimum diffusion rate is determined along directions determined using the gradient vector corresponding to the selected polygon. A diffusion-path vector is defined between a point in the selected polygon and a neighboring point in a neighboring polygon. An updated fluid property is determined for the selected polygon using a variable diffusion rate, the variable diffusion rate based on the minimum diffusion rate, maximum diffusion rate, and the gradient vector.
Predicting Transition From Laminar To Turbulent Flow Over A Surface
US Patent:
2014001, Jan 16, 2014
Filed:
Sep 5, 2013
Appl. No.:
14/019448
Inventors:
Peter STURDZA - Redwood City CA, US
Assignee:
AERION CORPORATION - Reno NV
International Classification:
G06F 17/50
US Classification:
703 9
Abstract:
A prediction of whether a point on a computer-generated surface is adjacent to laminar or turbulent flow is made using a transition prediction technique. A plurality of instability modes are obtained, each defined by one or more mode parameters. A vector of regressor weights is obtained for the known instability growth rates in a training dataset. For an instability mode in the plurality of instability modes, a covariance vector is determined. A predicted local instabilty growth rate at the point is determined using the covariance vector and the vector of regressor weights. Based on the predicted local instability growth rate, an n-factor envelope at the point is determined.