Stephen G Wurst

US Patent:

55182054, May 21, 1996

Filed:

Sep 6, 1994

Appl. No.:

8/300897

Inventors:

Stephen G. Wurst - Lancaster CA
Ray H. Bartlett - Orange CA
David S. Wright - Santa Clarita CA

Assignee:

Rockwell International Corporation - Seal Beach CA

International Classification:

B64B 120
B64D 4100

US Classification:

244 58

Abstract:

A novel, high-altitude, solar powered aircraft, capable of staying aloft at high altitudes for many months or even years to conduct around the clock surveillance and/or reconnaisance, includes a forward wing with solar energy capturing cells, a rear wing, inflated pontoons for keeping the aircraft aloft, suspension wires attached to the pontoons, a gondola suspended from and connected to the wires, control apparatus for moving the gondola along the wires, shifting the weight of the aircraft and thereby enabling banking to optimize exposure of the solar cells to the rays of the sun. The gondola preferably contains a sensor suite, power generating and storage apparatus, and synthetic aperture radar imaging apparatus.

US Patent:

6193187, Feb 27, 2001

Filed:

Dec 31, 1998

Appl. No.:

9/224190

Inventors:

Harry Scott - Hawthorn CA
Stephen G. Wurst - Lancaster CA

International Classification:

B64G 114

US Classification:

244 2

Abstract:

The reusable space launch system has a first stage vehicle or aerospacecraft, a second stage vehicle or reusable spacecraft and a third stage vehicle or reusable orbit transfercraft. All the stages have the basic aerodynamic vehicle elements of a fuselage, wings, and tail, with the incorporation of control surfaces to supply lift, stability and control. The aerospacecraft is configured to use ejector ramjet engines for powered flight and includes equipment to capture air to supplement oxidizer for the ejector ramjet engine during take-off and extreme high altitude In order to optimize aerospacecraft performance in a pull up movement to exit the sensible atmosphere, the aerospacecraft may include auxiliary ascent rocket engines. The aerospacecraft payload bay is accessed by nose load re-closable payload fairings. The reusable spacecraft is mounted on tracks on each lower side of the aerospacecraft payload bay.

US Patent:

55267521, Jun 18, 1996

Filed:

Sep 6, 1994

Appl. No.:

8/300888

Inventors:

Glenn E. Dahl - Torrance CA
Stephen G. Wurst - Lancaster CA

Assignee:

Rockwell International Corporation - Seal Beach CA

International Classification:

F42B 1200

US Classification:

102517

Abstract:

A projectile which includes multiple warheads separated one from another within a casing, each warhead having its own independent detonator. The warheads are arranged in spaced relationship along the longitudinal axis of the casing, and the detonators are linked with a fuzing mechanism located at the forward region of the casing. Upon reaching the target, the rearmost warhead in the projectile is detonated and the remaining warheads are then detonated sequentially forwardly, ad seriatim, by the fuzing mechanism.

US Patent:

57409854, Apr 21, 1998

Filed:

Sep 16, 1996

Appl. No.:

8/716807

Inventors:

Harry Scott - Hawthorne CA
Stephen G. Wurst - Lancaster CA

International Classification:

B64G 114
B64G 140

US Classification:

244 2

Abstract:

The orbital launch system is a three stage vehicle to launch orbital payloads. The system uses a turbofan powered aircraft as the first stage with an aerospacecraft attached by an underling aerospacecraft pylon at an aircraft engine mount for carriage. The aerospacecraft is the second stage and is powered by an ejector ramjet engine. The aerospacecraft has a cargo bay with cargo bay doors in its midsection. A booster rocket with payload is launched from the cargo bay by use of an ejection system. Normally the payload is mounted on a rocket booster to be placed in the proper orbit. The orbital launch system may also have a parachute drop recovery system to recover the booster rocket after it deorbits.