Harry A Shortland

US Patent:

53059735, Apr 26, 1994

Filed:

Dec 7, 1989

Appl. No.:

7/447347

Inventors:

Harry Shortland - Torrance CA
Martin L. Shanken - Fountain Valley CA
Peter O. Paxson - Rancho Palos Verdes CA
C. Dwayne Johnston - Santee CA
Guillermo Mas - La Palma CA

Assignee:

Rockwell International Corporation - Seal Beach CA

International Classification:

B64C 138
B64D 3734

US Classification:

244117A

Abstract:

Circulation of temperature controlled fluid through cavities in structure stiffening members of hypersonic aerospace vehicles precludes destructive temperature gradients in such members and preserves stress residuals for functional requirements.

US Patent:

58531432, Dec 29, 1998

Filed:

Dec 23, 1996

Appl. No.:

8/771499

Inventors:

Marty K. Bradley - Downey CA
Kevin G. Bowcutt - Irvine CA
Harry Shortland - Torrance CA
Philip S. Dunlap - Rancho Palos Verdes CA

Assignee:

Boeing North American, Inc. - Seal Beach CA

International Classification:

F42B 1032
F42B 710

US Classification:

244 321

Abstract:

The flight vehicle includes an elongated central body having a central axis defined therein and a circumference. A plurality of elongated portions are positioned about the central body. A plurality of airbreathing engines are axisymetrically positioned about the central axis of the central body and between the respective elongated portions. Each flowpath includes a forebody, an inlet, an isolator duct, a combustor, a nozzle, and a mechanism for injecting fuel into the combustor. The forebody externally compresses the air flow. The inlet is downstream of the forebody to capture air flow. The isolator duct is downstream of the inlet to further reduce velocity of the air flow. The combustor is downstream of the isolator duct and finally, the nozzle is downstream of the combustor. The fuel/air mixture is burned in the combustor and expanded in the nozzle for providing thrust. A control mechanism is positioned about the central body for providing control of the flight vehicle.

US Patent:

54857872, Jan 23, 1996

Filed:

Jun 21, 1994

Appl. No.:

8/264207

Inventors:

Kevin G. Bowcutt - Irvine CA
Harry Shortland - Torrance CA

Assignee:

Rockwell International Corporation - Seal Beach CA

International Classification:

F42B 1500
F02K 710

US Classification:

102374

Abstract:

A gas gun-launched, propulsion-assisted scramjet projectile adapted to be fired from a gun, preferably at velocities greater than Mach 5, includes a body with an external compression section, an internal compression section, a combustion section, a nozzle section, and means for channeling ambient fluid to an engine in one of the sections of the body, the channeling means and the body cooperating with the engine to produce thrust greater than drag when the projectile travels at velocities greater than Mach 5. The projectile further includes a plurality of circumferentially spaced stabilization fins located at the nozzle region of the body and a sabot assembly releasably secured to the rear portion of the body, where the sabot assembly includes a plurality of elements joined together about the body rear portion to form a housing for protecting the body rear portion from explosive gases in the barrel of the gun.