Richard D Colgren

D596267, Jul 14, 2009

Apr 21, 2006

29/246547

Richard D. Colgren - Palmdale CA, US
Lance C. Holly - Lawrence KS, US
William R. Donovan - Lawrence KS, US
Luke A. Thompson - Lynnwood WA, US

2301

D23233

7922115, Apr 12, 2011

Apr 23, 2007

11/789079

Richard D. Colgren - Palmdale CA, US
Lance C. Holly - Lawrence KS, US
William R. Donovan - Lawrence KS, US

B64C 1/00
B64C 3/00

244 13, 244 45 R, 244120, 2441231

The present invention is an unmanned air vehicle designed for reconnaissance, surveillance, data acquisition, and general research. The air vehicle is a monoplane that consists of several pieces that can easily be assembled using a minimal amount of tools. The air vehicle consists of a forward and aft fuselage section, two identical horizontal stabilizers, and four identical wing sections. The aircraft can fly with all four wing sections, or with just two wing sections (the short wing configuration). Each of the four wing sections of the air vehicle can be interchanged with any of the other wing sections for the purpose of minimizing assembly time and spare parts.

62733702, Aug 14, 2001

Nov 1, 1999

9/431948

Richard D. Colgren - Palmdale CA

Lockheed Martin Corporation - Palmdale CA

B61L 300
G05D 100
G06F 1700

244181

A method and system is disclosed for using inertial sensors in an Inertial Navigation System (INS) to obtain analytic estimates of angle-of-attack (. sub. alpha. ) and sideslip angle (. sub. alpha. ). The inertial sensors consist of one or more accelerometers which produce the estimated signals for angle-of-attack (. sub. alpha. ) and sideslip angle (. sub. beta. ). Three methods are shown for obtaining. sub. alpha. and. sub. beta. estimates from INS information and are programmed into a nonlinear simulation of a relaxed stability aircraft requiring a high level of artificial stability augmentation in its flight control system. Simulation results from the nonlinear simulation for each of the three methods were compared with the results obtained when conventional probes were used to obtain direct measurements of. sub. alpha. and. sub. beta. Based on these comparisons, a method for determining. sub. alpha. and. sub. beta. analytically which estimates the turbulence level in each axis is combined with one of the three methods to provide derived inertial values for providing control system feedback to an aircraft.

50637355, Nov 12, 1991

Oct 18, 1990

7/599722

Richard D. Colgren - Palmdale CA
Christopher C. Criss - Palmdale CA
Russell J. Criss - Palmdale CA

F02K 500

60246

The invention is a propulsion system. In detail, the invention comprises a hollow housing having a longitudinal axis and an inlet end and an exhaust nozzle end. A shaft is rotatively mounted along the longitudinal axis within the housing, extending from the inlet end to the exhaust nozzle end. A fan is attached to one end of the shaft in proximity to the inlet end of the housing. A turbine, having a plurality of blades, is attached to the opposite end of the shaft in proximity to the exhaust nozzle end of the housing. A solid propellant rocket motor is detachably mounted to the housing, having a thrust axis alignable with the longitudinal axis of the housing such that, when the motor is ignited, at least a portion of any exhaust gases therefrom are intercepted by the blades of the turbine for driving same.