James Kevin Wechsler, 6261 Asilomar Rd, Laguna Niguel, CA 92677

6557803, May 6, 2003

Aug 31, 2001

09/944811

Jon J. Carpenter - Redondo Beach CA
Jeffrey J. Cronick - Huntington Beach CA
Jennifer L. Green - Houston Safety Harbor TX
Brian R. Lindley - Corona del Mar CA
James K. Wechsler - Irvine CA
Thomas R. Smith - Westminister CA

The Boeing Company - Chicago IL

B64G 114

244162, 244158 R

A returnable and reusable space vehicle including a main body separate from and releasably mounted to a booster rocket assembly. A crew compartment module is provided that is separate from and releasably mounted to the main body. A propellant system is operably coupled to the crew compartment module so as to propel the crew compartment module from the main body during an emergency procedure. An orientation control system is coupled to the propellant system such that the orientation control system maintains the crew compartment module in a predetermined attitude during the emergency procedure. A pair of aerodynamic lifting wings extend from the main body to provide aerodynamic lift to the main body to permit the main body to return from the orbit and land.

6568639, May 27, 2003

Aug 31, 2001

09/945090

Jon J. Carpenter - Redondo Beach CA
Jeffrey J. Cronick - Huntington Beach CA
Jennifer L. Green - Safety Harbor FL
Brian R. Lindley - Corona del Mar CA
James K. Wechsler - Irvine CA

The Boeing Company - Chicago IL

B64G 110

244172

An orbit transfer vehicle for transporting cargo between a low Earth orbit and a higher Earth orbit having a body and an engine operably coupled to the body. A reaction control system is further provided and is operably coupled to the body. The reaction control system having a plurality of thrusters capable of maneuvering the orbit transfer vehicle. The orbit transfer vehicle further includes an energy absorbing panel operable to gather energy and an energy storage device operable to store the energy. Still further, a payload interface mechanism is provided having a payload container area and a payload retaining device. The payload retaining device is connectable to the cargo. Lastly, a controller for autonomously controlling the engine, the reaction control system, and the payload interface mechanism to control the orbit transfer vehicle so as to transport the cargo between a low Earth orbit to a higher Earth orbit.

6666409, Dec 23, 2003

Feb 26, 2003

10/374292

Jon J. Carpenter - Redondo Beach CA
Jeffrey J. Cronick - Huntington Beach CA
Jennifer L. Green - Safety Harbor FL
Brian R. Lindley - Corona del Mar CA
James K. Wechsler - Irvine CA
Thomas R. Smith - Westminister CA

The Boeing Company - Chicago IL

B64G 114

244162, 244158 R

A returnable and reusable space vehicle including a main body separate from and releasably mounted to a booster rocket assembly. A crew compartment module is provided that is separate from and releasably mounted to the main body. A propellant system is operably coupled to the crew compartment module so as to propel the crew compartment module from the main body during an emergency procedure. An orientation control system is coupled to the propellant system such that the orientation control system maintains the crew compartment module in a predetermined attitude during the emergency procedure. A pair of aerodynamic lifting wings extend from the main body to provide aerodynamic lift the the main body to permit the main body to return from the orbit and land.

5381985, Jan 17, 1995

Apr 23, 1992

7/872336

James K. Wechsler - Irvine CA
John W. Rutherford - Scottsdale AZ

McDonnell Douglas Helicopter Co. - Mesa AZ

B64C 1148
B64C 2708
B64C 2722
B64C 2752

244 7C

A tiltwing aircraft, capable of in-flight conversion between a hover and forward cruise mode, employs a counter-rotating proprotor arrangement which permits a significantly increased cruise efficiency without sacrificing either the size of the conversion envelope or the wing efficiency. A benefit in hover is also provided because of the lower effective disk loading for the counter-rotating proprotor, as opposed to a single rotation proprotor of the same diameter. At least one proprotor is provided on each wing section, preferably mounted on the wingtip, with each proprotor having two counter-rotating blade rows. Each blade row has a plurality of blades which are relatively stiff-in-plane and are mounted such that cyclic pitch adjustments may be made for hover control during flight.