David C Hull

US Patent:

20100242772, Sep 30, 2010

Filed:

Mar 24, 2009

Appl. No.:

12/410283

Inventors:

Phillip R. Martineau - Salt Lake City UT, US
Christopher J. Sullivan - Sandy UT, US
David W. Hull - Magna UT, US
Steven C. Sara - South Jordan UT, US

International Classification:

F42B 15/10
B64F 1/04

US Classification:

102380, 102374, 244 63

Abstract:

A missile component such as a rocket motor case, of an initial transverse cross-sectional shape flexible into another, different cross-section responsive to application of internal pressure from ignition of a propellant grain within the component. A missile launch assembly including at least one missile of a non-circular cross-section disposed within a segment of a partitioned circular launch tube. A multi-stage missile comprising at least a first stage and a second stage having rocket motor cases of non-circular transverse cross-section, the rocket motor case of at least one of the stages being deformable into another, different cross-section. A method of launching a missile including igniting a rocket motor of a component having a first cross-section, internally pressurizing the missile component substantially concurrently with motor ignition and flexing the component rocket motor into a second, different cross-sectional shape.

Address:

5570 Night Swim Ln, Las Vegas, NV 89113

VIN:

5NPET46C67H254721

Make:

HYUNDAI

Model:

SONATA

Year:

2007