Paul G Lichon

US Patent:

6432178, Aug 13, 2002

Filed:

Sep 14, 2001

Appl. No.:

09/952709

Inventors:

Paul G. Lichon - Bothell WA
Dieter M. Zube - Redmond WA

Assignee:

General Dynamics OTS (Aerospace), Inc. - Redmond WA

International Classification:

B01D 1900

US Classification:

96179, 602001, 96219, 210188

Abstract:

A gas arrestor separates entrained gas from a liquid medium. The gas arrestor is a porous member, such as a woven mesh screen having pores of a size sufficiently small to enable liquid transport while inhibiting gas transport. Since the trapped gas has a tendency to accumulate on the porous member impeding continued liquid flow, a wick extends in an upstream direction from the porous member. When used in spacecraft to provide substantially gas-free liquid to a thruster, the gas arrestor is located between a tank of pressurized liquid propellant and a gas generator. Improved results are obtained by locating the gas arrestor between a pressure reducing liquid fluid resistor and the gas generator.

US Patent:

54649617, Nov 7, 1995

Filed:

Sep 10, 1993

Appl. No.:

8/120615

Inventors:

Paul G. Lichon - Bothell WA

Assignee:

Olin Corporation - Redmond WA

International Classification:

B23K 1000

US Classification:

21912152

Abstract:

There is disclosed an anode for an arcjet thruster which resists erosion during start-up on constriction during steady-state operation. The anode includes a converging upstream portion, a diverging downstream portion and a constricted portion disposed therebetween. In one embodiment of the invention, rails formed in the constricted portion accelerate the passage of an arc during start-up reducing erosion. In a second embodiment, a higher strength material resists bulging as a result of the thermal gradient within the nozzle.

US Patent:

57460507, May 5, 1998

Filed:

Jan 19, 1996

Appl. No.:

8/588697

Inventors:

Christopher H. McLean - Seattle WA
Paul G. Lichon - Bothell WA
Joseph P. Morris - Bothell WA
Philip O. Flugstad - Bothell WA

Assignee:

Primex Technologies, Inc. - Redmond WA

International Classification:

F02C 330
F02K 942

US Classification:

602001

Abstract:

There is provided a system for the delivery of a gaseous product to a reaction chamber. The system includes a fuel tank containing a hypergolic liquid displaced from the fuel tank by a pressurized gas whose flow is controlled by a thruster control valve and directed to a gas generator. Pressurant gas entrained in the hypergolic liquid is not decomposed in the gas generator and causes pressure oscillations. The pressure oscillations are minimized by reducing the diameter of the gas bubbles or by disposing a gas fluid resistor between the gas generator and the reaction chamber.

US Patent:

49374567, Jun 26, 1990

Filed:

Oct 17, 1988

Appl. No.:

7/258618

Inventors:

Donald Grim - Renton WA
Paul G. Lichon - Bothell WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

H01J 3300

US Classification:

250427

Abstract:

An ion thruster for accelerating positively charged ions produced by the collision of free electrons with gas atoms. An ion thruster (10,100) includes a cathode chamber (12, 60, 118) and an ionization chamber (14, 106). The outer surface of an emitter tube (28, 61, 128) is coated with a dielectric material to protect the emitter tube from sputtering erosion. A plurality of bar magnets (20, 22; 108, 110) are arranged in a spaced apart circular array around the cathode chamber with a pole face of each of the magnets tangentially aligned with wall sections (16, 18; 102, 104) of the ionization chamber. The bar magnets thus define a picket fence, wherein the magnetic field between adjacent bar magnets is used to extend the mean path of an electron entering the ionization chamber, improving the probability that it will impact an atom, creating an ion. A grid plate (112) comprises an accelerator grid (204) coated on its inner and outer surfaces with a dielectric coating (206, 208). The inner dielectric coating assumes the potential of the plasma, functioning as a screen grid, while the outer dielectric coating assumes the generally neutral potential of the plasma beam, functioning as a decelerator grid.

US Patent:

20150345909, Dec 3, 2015

Filed:

May 30, 2014

Appl. No.:

14/291450

Inventors:

Joseph P. Morris - Bothell WA, US
Paul Lichon - Bothell WA, US
Douglas L. Smith - Bellevue WA, US

Assignee:

General Dynamics Ordnance and Tactical Systems, Inc. - St. Petersburg FL

International Classification:

F41G 7/22
G01S 19/13

Abstract:

An apparatus and system for controlling the trajectory of a projectile having two rotationally decoupled sections, wherein the first section is rotationally decoupled from the second section. The first section of the projectile contains a navigation system. The first section also contains an actuator by which aero-control surfaces on the second section are actuated. The second section may have external aero-spin surfaces which provide a torque counter to the rotation of the base projectile. The apparatus and system also includes embodiments having applications for nose sections of projectiles.