Mark E Elkanick

8276570, Oct 2, 2012

Jan 22, 2010

12/692492

Mark E. Elkanick - Tucson AZ, US
Delmar L. Barker - Tucson AZ, US

Raytheon Company - Waltham MA

F02B 51/00

123536, 123606

A system and method to inject nanostructures into the fuel/oxidizer mixture, typically lean mixtures, to increase efficiency of internal combustion and/or decrease pollution. An electromagnetic pulse (suitably 1 to 100 GHz) couples energy to the nanostructures to produce a volumetric combustion of the fuel oxidizer mixture. The fuel/oxidizer mixture is substantially transparent to the band of the electromagnetic pulse. The nanostructures couple to the electromagnetic radiation, absorb the energy and heat rapidly producing many local ignitions that in turn produce volume combustion. The nanostructures may be filled or partially filled with energetic material.

8294072, Oct 23, 2012

May 27, 2010

12/789068

Chris E. Geswender - Green Valley AZ, US
Mark E. Elkanick - Tucson AZ, US
Craig O. Shott - Benson AZ, US

Raytheon Company - Waltham MA

F42B 15/00

244 329, 244 324, 244 327

Some embodiments pertain to a projectile that includes a casing and a plurality of fins which are secured to the casing. Each of the fins is movable between a stowed position and a deployed position. The fins are typically in the stowed position during storage and launch, and move to the deployed position as soon as possible after launch. Each fin includes a first foil that has a first set of openings and a second foil that includes a second set of openings. The first sets of openings in the first foils are aligned with the second sets of openings in the second foils when each of the fins is in the stowed position. The first sets of openings in the first foils are not aligned with the second sets of openings in the second foils when each of the fins is in the deployed position.

20140061364, Mar 6, 2014

Jul 17, 2012

13/551221

Doron Strassman - Vail AZ, US
Mark E. Elkanick - Tucson AZ, US

F42B 10/66
F42B 15/01

244 322

An interceptor is provided with an integrated propulsion and attitude control system (ACS) in which propellant burn forms a common pressure vessel for high-pressure gas. An aft port in the rocket motor directs gas through one or more main nozzles that expel high-velocity gas in a generally axial direction to propel the interceptor. A forward port directs gas through one or more attitude control nozzles that expel high-velocity gas in a generally radial direction to control the attitude of the interceptor. The main nozzle(s) and stabilization fins are fixed, there is no servo control to the main nozzles or fins to affect attitude control. The use of a common pressure vessel enables an integrated propulsion and ACS that can be compact, lightweight and inexpensive.

55908500, Jan 7, 1997

Jun 5, 1995

8/463603

James J. Cannon - Northridge CA
Mark Elkanick - Tucson AZ

Hughes Missile Systems Company - Los Angeles CA

F42B 1501

244 315

Blended missile autopilots for a missile employing direct lift and tail controlled autopilots coupled by way of a blending filter. The blended missile autopilots have movable tails aft of the center of gravity of the missile and side force thrusters or movable canards mounted forward of the center of gravity, and that are controlled using the direct lift and tail-controlled autopilots. Lift is generated from the tails and side force is generated by the thrusters or canards, such that the body of the missile maintains zero angle of attack and generates no lift. The present invention thus combines the fast response of a direct lift autopilot with the high acceleration capability of a body lift autopilot, and blends the two using the blending filter to achieve improved performance.

59754605, Nov 2, 1999

Nov 10, 1997

8/967158

Mark E. Elkanick - Tucson AZ
James A. Bacon - Tucson AZ

Raytheon Company - Lexington MA

F41G 700

244 315

A system (10') for generating a missile guidance gain factor adapted for use with guided missiles. The inventive system includes a guidance control system (52) for obtaining current guidance parameters(55, 57) including ideal navigation gain, closing rate, line of sight rate, missile maneuverability, and missile velocity parameters. Software (56) running on a guidance control processor (54) computes a current guidance gain factor reflective of the current maneuverability of the missile from the guidance parameters (55, 57). In the illustrative embodiment, the system 10' further includes a nonlinear notch circuit (56) that generates an acceleration command (59) from the guidance parameters (55, 57) that varies in response to varying missile maneuverability parameters (57). The guidance control system (10') includes a conventional guidance law computation circuit (54, 55) and electromagnetic sensing equipment (52). An autopilot circuit (58) included in the system (10') provides the missile maneuverability parameters (57).