Charles W Schertz

US Patent:

44896387, Dec 25, 1984

Filed:

Mar 14, 1983

Appl. No.:

6/474994

Inventors:

Thomas W. Bastian - Fullerton CA
Charles W. Schertz - Claremont CA

Assignee:

General Dynamics, Pomona Division - Pomona CA

International Classification:

F41F 306

US Classification:

89 1815

Abstract:

A missile launching system adapted for installation in a standard commercial aircraft without modification of the aircraft structure. The system comprises a plurality of frame members, linear tracks which are movable longitudinally relative to the frame members, a plurality of launch tubes for storing the missiles, an exit port for installation in an pre-established aircraft fuselage opening, and associated equipment for selectively launching the missiles from the launch tubes through the exit port. The entire system is assembled from individual components, all of which are sized to be placed on board the aircraft through a standard passenger door opening. In preparation for installing the system in a commercial aircraft, the passenger seats and related equipment conventionally installed in the interior of such an aircraft are removed. The frame members of the system are then mounted to the standard seat tracks in the floor of the aircraft. The remaining portions of the system are thereafter assembled and installed on the frame.

US Patent:

40407446, Aug 9, 1977

Filed:

Oct 5, 1973

Appl. No.:

5/404077

Inventors:

Charles W. Schertz - Claremont CA
Edward H. Ritter - Claremont CA

Assignee:

General Dynamics

International Classification:

G01B 1126

US Classification:

356152

Abstract:

A sight system for providing closed-loop differential tracking control over gun aiming, utilizing visual and non-visual optical radiation to assist the gunner in acquiring and destroying targets as well as providing information to the gun control computer for automatic acquisition and firing. The sight is used in conjunction with a cooperative ammunition round which emits pulsed flashes at a timed interval after firing and upon impact. Portions of these signals are in the non-visible spectrum, and an invisible-to-visible converter is utilized to signal the relative location of the flashes to the gunner. A similar conversion is utilized to provide information on laser designator illumination and other non-visible radiation emanating from the target.

US Patent:

42022460, May 13, 1980

Filed:

Jun 23, 1975

Appl. No.:

5/591381

Inventors:

Charles W. Schertz - Claremont CA
Edward H. Ritter - Claremont CA

Assignee:

General Dynamics Pomona Division - Pomona CA

International Classification:

F41G 322

US Classification:

89 41EA

Abstract:

A sight system for providing closed-loop differential tracking control over gun aiming, utilizing visual and non-visual optical radiation to assist the gunner in acquiring and destroying targets as well as providing information to the gun control computer for automatic acquisition and firing. The sight is used in conjunction with a cooperative ammunition round which emits pulsed flashes at a timed interval after firing and upon impact. Portions of these signals are in the non-visible spectrum, and an invisible-to-visible converter is utilized to signal the relative location of the flashes to the gunner. A similar conversion is utilized to provide information on laser designator illumination and other non-visible radiation emanating from the target.

US Patent:

48673579, Sep 19, 1989

Filed:

Dec 21, 1987

Appl. No.:

7/135210

Inventors:

Ronald T. Inglis - Laguna Beach CA
Thomas W. Bastian - Placentia CA
Charles W. Schertz - Bakersfield CA

Assignee:

General Dynamics Corp., Pomona Division - Pomona CA

International Classification:

F42B 1946

US Classification:

244121

Abstract:

An in-flight jettisonable protective cover device for protecting fragile, accurate, radomes or signal-responsive components for the major portion of a flight which is capable of being jettisoned in one piece at supersonic speeds from a guided missile, other air vehicles, or space vehicles. The cover device is for use, for example, in combination with a guided missile having a shell structure, a nose portion, and a radome in the missile nose. The cover device is attached to the missile nose for covering the radome such that an inner space is defined. A plurality of shear pins or other quick-release mechanisms attach and retain the cover device to the missile shell. A source of low pressure gas pressurizes the inner space to approximately 50 psi. A rapid-discharging, high pressure gas cartridge produces a high pressure gas for exerting a pressure force on the aft face of the cover device. The pressure forces are sufficient to shear the retaining pins and accelerate the cover device sufficiently forward to clear the missile body at supersonic speeds.

US Patent:

49643398, Oct 23, 1990

Filed:

Dec 23, 1987

Appl. No.:

7/137226

Inventors:

Thomas W. Bastian - Placentia CA
Charles W. Schertz - Bakersfield CA

Assignee:

General Dynamics Corp., Pomona Division - Pomona CA

International Classification:

F42B 1500

US Classification:

102376

Abstract:

A rocket propelled missile assembly comprises an outer casing defining an internal solid rocket propellant chamber, the casing having an opening at its forward end aligned with an internal tube submerged in the rocket propellant chamber, and at least one exhaust nozzle at its rear end for venting exhaust gases from the propellant chamber. Solid propellant is contained within the propellant chamber surrounding the internal tube, and a separate terminal stage missile is partially or fully submerged in the tube with the capacity to separate from the tube forwardly through the front end of the casing. The missile separates from the remainder of the system on booster burn out.