Mark A Bovankovich

US Patent:

8515611, Aug 20, 2013

Filed:

Aug 23, 2012

Appl. No.:

13/593402

Inventors:

Gene D. Tener - Oviedo FL, US
Andrew H. Hawkins - Orlando FL, US
Mark A. Bovankovich - Orlando FL, US
Louis N. Glaros - Orlando FL, US

Assignee:

Lockheed Martin Corporation - Bethesda MD

International Classification:

G01C 22/00

US Classification:

701 23, 356 403

Abstract:

The present invention relates to a system and method for determining vehicle attitude and position from image data detected by sensors in a vehicle. The invention uses calculated differences between the locations of selected features in an image plane and the location of corresponding features in a terrain map to determine the attitude of the vehicle carrying the sensors with respect to a ground frame of reference.

US Patent:

20100010741, Jan 14, 2010

Filed:

Jul 10, 2008

Appl. No.:

12/216758

Inventors:

Gene D. Tener - Oviedo FL, US
Andrew H. Hawkins - Orlando FL, US
Mark A. Bovankovich - Orlando FL, US
Louis N. Glaros - , US

International Classification:

G01C 21/16

US Classification:

701220

Abstract:

The present invention relates to a system and method for determining vehicle attitude and position from image data detected by sensors in a vehicle. The invention uses calculated differences between the locations of selected features in an image plane and the location of corresponding features in a terrain map to determine the attitude of the vehicle carrying the sensors with respect to a ground frame of reference.

US Patent:

20220372932, Nov 24, 2022

Filed:

Dec 4, 2018

Appl. No.:

16/209466

Inventors:

Judith Marie Bovankovich - Orlando FL, US
MARK BOVANKOVICH - ORLANDO FL, US

International Classification:

F02K 7/10

Abstract:

A method of propulsion includes providing a high-speed-launch ramjet boost (HSLRB) stage and HSLRB engine attached to a launch aircraft providing a speed ≥1.5 Mach. The HSLRB engine includes a combustion system and inlet(s) for air flow to the fuel injectors. A variable geometry (VG) nozzle having a nozzle actuator exhausts gas from combustion. A processor receives sensing signals from sensor(s) during flight that provides control signals to the nozzle actuator for dynamically controlling an aperture size of the VG nozzle, and if the inlet is a VG inlet to an inlet actuator to dynamically control the VG inlet shape. The HSLRB engine is ignited while attached to the aircraft at 1.5 to 1.99 Mach if assisting the aircraft to accelerate to 2.0 Mach, or at a speed of ≥2.0 Mach if the aircraft can accelerate to 2.0 Mach autonomously, then the HSLRB stage is separated from the aircraft.

US Patent:

20140331682, Nov 13, 2014

Filed:

Nov 1, 2013

Appl. No.:

14/069454

Inventors:

MARK BOVANKOVICH - ORLANDO FL, US

International Classification:

F02C 7/042
F02C 7/057

US Classification:

60768, 60205

Abstract:

A high-speed-launch ramjet boost (HSLRB) engine includes a combustion system for igniting fuel pumped by a fuel pump from a fuel tank, where the combustion system includes an igniter, fuel injectors and frame holders. An inlet provides a pathway for air to flow toward the fuel injectors. A variable geometry (VG) nozzle having a nozzle actuator is included for exhausting exhaust gas from combustion of the fuel by the combustion system. A processor is coupled to receive sensing signals from at least one of a pressure sensor and a temperature sensor during flight, wherein the processor provides control signals to the nozzle actuator for dynamically controlling an aperture size of the VG nozzle.