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Aeroelastic Optimization of Sounding Rocket Fins.

ADA502110

Publication Date	2009
Personal Author	Simmons, I. J.
Page Count	106
Abstract	This research effort develops a multidisciplinary design tool to optimize sounding rocket fin geometries that minimize the mass of the fins while maintaining aerodynamic performance. This research grew out of a design problem experienced by the US Air Force Academy's Falcon LAUNCH program. The Falcon LAUNCH program is a senior design capstone project during which Air Force Academy cadets design, build and fly a sounding rocket over the course of an academic year. In the Spring of 2007, the Falcon LAUNCH V vehicle experienced a catastrophic failure when three of its four fins sheared off due to flutter. When the following year's team developed the fins for Falcon LAUNCH VI, the design requirement that the fins not experience flutter led to substantially more massive fins. The Falcon LAUNCH team needs a design tool that can balance the competing needs for minimal mass sounding rocket components and aerodynamic performance. The tool developed during this research is designed to find an optimal solution for the fin geometry based on the competing needs of minimizing the fins' mass and ensuring the fins will not experience flutter. The design tool then provides for verification of the design throughout the designed flight profile.
Keywords	Optimization Aeroelasticity Sounding rockets Folding fins(Rockets) Theses Aerodynamics Geometry Catastrophic conditions Flutter Failure Finite element analysis Models Sounding rocket fins Geometry optimization Model center
Source Agency	Non Paid ADAS
NTIS Subject Category	79H - Rockets 46B - Fluid Mechanics 84G - Unmanned Spacecraft
Corporate Authors	Air Force Inst. of Tech., Wright-Patterson AFB, OH. Graduate School of Engineering and Management.
Supplemental Notes	The original document contains color images.
Document Type	Thesis
Title Note	Master's thesis.
NTIS Issue Number	200924

Aeroelastic Optimization of Sounding Rocket Fins.

Aeroelastic Optimization of Sounding Rocket Fins.
ADA502110

Publication Date	2009
Personal Author	Simmons, I. J.
Page Count	106
Abstract	This research effort develops a multidisciplinary design tool to optimize sounding rocket fin geometries that minimize the mass of the fins while maintaining aerodynamic performance. This research grew out of a design problem experienced by the US Air Force Academy's Falcon LAUNCH program. The Falcon LAUNCH program is a senior design capstone project during which Air Force Academy cadets design, build and fly a sounding rocket over the course of an academic year. In the Spring of 2007, the Falcon LAUNCH V vehicle experienced a catastrophic failure when three of its four fins sheared off due to flutter. When the following year's team developed the fins for Falcon LAUNCH VI, the design requirement that the fins not experience flutter led to substantially more massive fins. The Falcon LAUNCH team needs a design tool that can balance the competing needs for minimal mass sounding rocket components and aerodynamic performance. The tool developed during this research is designed to find an optimal solution for the fin geometry based on the competing needs of minimizing the fins' mass and ensuring the fins will not experience flutter. The design tool then provides for verification of the design throughout the designed flight profile.
Keywords	Optimization Aeroelasticity Sounding rockets Folding fins(Rockets) Theses Aerodynamics Geometry Catastrophic conditions Flutter Failure Finite element analysis Models Sounding rocket fins Geometry optimization Model center
Source Agency	Non Paid ADAS
NTIS Subject Category	79H - Rockets 46B - Fluid Mechanics 84G - Unmanned Spacecraft
Corporate Authors	Air Force Inst. of Tech., Wright-Patterson AFB, OH. Graduate School of Engineering and Management.
Supplemental Notes	The original document contains color images.
Document Type	Thesis
Title Note	Master's thesis.
NTIS Issue Number	200924