Ernest T Robinson

US Patent:

6494402, Dec 17, 2002

Filed:

May 14, 2001

Appl. No.:

09/855005

Inventors:

Ernest Y. Robinson - Altadena CA
Margaret H. Abraham - Los Angeles CA
Peter D. Fuqua - Redondo Beach CA

Assignee:

The Aerospace Corporation - El Segundo CA

International Classification:

B64G 126

US Classification:

244 52, 244169, 244172, 60223

Abstract:

A microthruster having an inverted exhaust system traps burst diaphragm fragments providing a clean exhaust while an exhaust port provides increased back pressure for efficient combustion of a propellant charge in a fuel cell. A converging diverging micronozzle provides a predictable exhaust vector for improved microthrusting well suited for propulsion system on small spacecraft.

US Patent:

6945499, Sep 20, 2005

Filed:

Mar 19, 2004

Appl. No.:

10/804911

Inventors:

Ernest Y. Robinson - Altadena CA, US

Assignee:

The Aerospace Corporation - El Segundo CA

International Classification:

B64G001/00

US Classification:

244158R, 212 76, 212 83, 1041731, 4141428

Abstract:

A tethered spacecraft is tethered to a base using a semirigid stand-off and a moving tether operated as a belt drive and operated in tension so that the tethered is precisely positioned in tension from the base spacecraft.

US Patent:

42429641, Jan 6, 1981

Filed:

Dec 18, 1978

Appl. No.:

5/970760

Inventors:

John B. Warren - Tustin CA
Ernest Y. Robinson - Altadena CA
Robert P. Kazanjy - Irvine CA

Assignee:

Ares, Inc. - Port Clinton OH

International Classification:

F42C 102

US Classification:

102275

Abstract:

A percussion type projectile nose fuse includes a generally conical fuse body having a cavity open only to the base thereof. Disposed within the cavity is a firing pin, a sleeve and a ball igniter. A fuse tip portion is defined by a weakened region, open to the fuse body exterior surface, which ruptures upon tip impact with a target, thereby causing at least partial rearward penetration of the tip into the cavity. Upon such tip penetration, the tip severs a flange on the firing pin by driving it against the sleeve, and propells the firing pin rearwardly along the sleeve and into engagement with the ball igniter. By forming the sleeve substantially longer than the length of the firing pin, a time delay before ignition, equal to the firing pin transit time, is provided. A forward opening recess formed in the apex of the tip, with a thin deformable wall thereabout, provides shock absorption so that accidental rupture of the weakened region does not occur during normal handling and loading of the projectile. The fuse is constructed of an aluminum alloy thereby permitting a relatively long fuse body to enhance the ballistic characteristics of an assembled projectile.

US Patent:

62849662, Sep 4, 2001

Filed:

Mar 6, 2000

Appl. No.:

9/520120

Inventors:

Edward J. Simburger - Agoura CA
David A. Hinkley - La Mirada CA
Ernest Y. Robinson - Altadena CA
David G. Gilmore - West Hollywood CA
Jon V. Osborn - Thousand Oaks CA

Assignee:

The Aerospace Corporation - El Segundo CA

International Classification:

H01L 31045
H01L 3104
B64G 100
B65D 5100

US Classification:

136244

Abstract:

A power sphere preferably used as part of a nanosatellite is formed using a plurality of flat panels solar arrays interconnected together by rotating hinges to approximate a spherical shape for use as an enclosure of a payload. The solar array panels are supported by an extending internal strut. The spherical shape provides attitude insensitive solar energy collection and heat radiation.