Howard V Eller

US Patent:

20020134423, Sep 26, 2002

Filed:

Mar 23, 2001

Appl. No.:

09/815811

Inventors:

Howard Eller - Redondo Beach CA, US
Martin Giebler - Redondo Beach CA, US

International Classification:

H01L031/00

US Classification:

136/245000, 136/244000, 136/251000, 136/292000

Abstract:

A spacecraft solar array structure including at least one sheet of amorphous silicon () formed on a flexible backing film, a supporting structure (), and a mechanism for reducing the bulk of the solar array structure to facilitate storage for launch and deployment of the structure in space. One disclosed embodiment of the invention includes a sheet of solar array material that deploys as cylindrical array () that does not need to be mounted on gimbals. In another embodiment, the solar array () is disposed on a rear surface of an antenna dish (). In yet another embodiment, the supporting structure of the solar array () includes multiple antenna dipole elements ().

US Patent:

60270772, Feb 22, 2000

Filed:

Jul 27, 1998

Appl. No.:

9/123135

Inventors:

Howard S. Eller - Redondo Beach CA
Ramon Coronel - Torrance CA
John W. Spargo - Redondo Beach CA
Larry R. Eaton - Huntington Beach CA
Andrew D. Smith - Redondo Beach CA

International Classification:

B64G 110

US Classification:

244173

Abstract:

A spacecraft (10) having a cryogenic cooler (24) that maintains different temperatures in thermally insulated and nested enclosures (26, 28, 12). In the coldest enclosure (26), which is maintained, for example, approximately 10. degree. K, low-temperature superconducting (LTS) processors (32, 34) perform bus and payload processing functions at very high speed. The next-coldest enclosure (28) is maintained at approximately 77. degree. K and houses high-temperature superconducting (HTS) electronic modules, such as for power regulation and distribution (40) and a payload sensor processing module (38). The third of the enclosures (12) is maintained at approximately 300. degree. K and houses other modules operating at room temperature, including a transponder (44), power control (46), energy storage (48), a propulsion subsystem (22), a downlink data processing module (49) and the cryogenic cooler (24) itself. Thermal functions of the spacecraft are effectively centralized in the cryogenic cooler (24) and the bus and payload functions of the spacecraft are provided very efficiently in a small, compact an potentially low-cost configuration.

US Patent:

60989300, Aug 8, 2000

Filed:

Jul 27, 1998

Appl. No.:

9/123136

Inventors:

Howard S. Eller - Redondo Beach CA
Ramon Coronel - Torrance CA

Assignee:

TRW Inc. - Redondo Beach CA

International Classification:

B64G 110
B64G 122

US Classification:

244172

Abstract:

A compact spacecraft (10, 22) having a potentially long life in orbit as a result of its use of non-moving and solid-state components entirely or wherever possible. Amorphous silicon arrays (14, 24, 44) are used for solar energy collection. Because the arrays are not limited to a flat panel configuration, no movement is needed except for possible initial deployment. Phased arrays (12, 26) are used wherever possible for antenna arrays, in combination with torque rods (18, 3) for coarse attitude control of the spacecraft. Avionics modules (30, 50) are fabricated using large wafer-scale techniques and energy storage using long life battery or a solid-state capattery (52) technology. Propulsion is also effected with no moving parts, using waffle propulsion modules (20, 28, 54), which use elemental containers of propellant that is selectively ignited to supply propulsive force. This combination of features extends the useful life of the spacecraft beyond limits imposed primarily by mechanical moving parts, and by high levels of redundancy.

US Patent:

59610760, Oct 5, 1999

Filed:

Dec 20, 1996

Appl. No.:

8/771464

Inventors:

Howard S. Eller - Redondo Beach CA
Ramon Coronel - Torrance CA

Assignee:

TRW Inc. - Redondo Beach CA

International Classification:

B64G 100

US Classification:

244158R

Abstract:

A process for designing and producing spacecraft more efficiently, without the excessive time, complexity and expense usually associated with spacecraft design. The process moves the design complexity usually associated with spacecraft design to payload modules whose designs are potentially reusable in other spacecraft missions. Each module is designed to be largely independent of a parent spacecraft structure, the design of which can be simplified to accommodate multiple modules that connect to the parent structure through a standardized backbone interface. Each module is designed for independent structural integrity, and to provide its own thermal management. Modules may also provide their own power regulation and, optionally, their own power storage and generation capabilities. Modules may also provide their own attitude control systems. Attachment of modules to the parent structure is simplified because of the modules' independence.

US Patent:

59798335, Nov 9, 1999

Filed:

Jul 10, 1998

Appl. No.:

9/113442

Inventors:

Howard S. Eller - Redondo Beach CA
Ramon Coronel - Torrance CA
Lee E. Elliott - Rancho Palos Verdes CA
Alfred Barrett - Santa Monica CA

Assignee:

TRW Inc. - Redondo Beach CA

International Classification:

B64G 100
B64G 144

US Classification:

244158R

Abstract:

A spacecraft structure using functionally independent modules assembled around a lightweight core structure to provide a vehicle that is lighter, uses less volume, and is easier to design, manufacture and test than a conventional spacecraft. In the disclosed embodiments, the modules are formed on generally flat panels, which serve as thermal radiators. The modules extend radially from the core structure and are attached to the core structure either in coplanar rows that extend axially along the core structure or in a coplanar set that extends circumferentially around the core structure. Interconnection between modules is achieved through a backbone interface, through which the modules are connected to the core structure. A large number of variant configurations may be implemented using the modular approach, by selecting a core, components and modules of number and size to meet mission requirements. The modular spacecraft may be easily designed and adapted to operate with its radiating modules facing in north-south directions for maximum thermal radiation, or in other orientations as needed for specific missions.

US Patent:

63300931, Dec 11, 2001

Filed:

Oct 21, 1998

Appl. No.:

9/176718

Inventors:

Howard S. Eller - Redondo Beach CA
Ramon Coronel - Torrance CA
Gary T. Harkness - Hermosa Beach CA

Assignee:

TRW Inc. - Redondo Beach CA

International Classification:

H04B 1002

US Classification:

359172

Abstract:

A standardized interface between a spacecraft backbone structure (48) and multiple spacecraft modules (26) that are coupled to the backbone structure mechanically, electrically and optically. The interface structure includes power connection pins (42 or 50) that connect to a power bus in the backbone structure, data signal pins (44) that connect to a conventional data bus in the backbone structure, and an optical connection (46 or 56) that connects to an optical data bus (60) in the backbone structure. Optionally, the interface also includes a wireless data bus (54) using infrared propagation along the backbone structure, and a radio-frequency (RF) microstrip connector (52) for transmission of data at radio frequencies. The optical data connection employs an optical interface unit (62) in each spacecraft module (26) to convert optical signals from the optical data bus (60) to corresponding electrical signals, and a cross-point switch (74) to distribute the signals to appropriate destinations on the module. The optical interface unit (62) also converts electrical signals to optical signals for transmission back onto the optical data bus (60).

US Patent:

59314184, Aug 3, 1999

Filed:

Dec 20, 1996

Appl. No.:

8/771084

Inventors:

Howard S. Eller - Redondo Beach CA
Ramon Coronel - Torrance CA
Martin M. Giebler - Redondo Beach CA

Assignee:

TRW Inc. - Redondo Beach CA

International Classification:

B64G 166

US Classification:

244158A

Abstract:

A spacecraft avionics module that is for the most part functionally independent of a core spacecraft structure, and provides its own structural integrity, thermal management and some level of power management. The illustrative embodiment of the module is formed as a flat panel that also serves as a thermal radiator. Electronic components are mounted directly onto the panel, which is normally attached by mounting hardware to the core spacecraft structure, through a backbone interface that provides data interconnection between modules and, in some cases, supplies unregulated power to the module. The module may include a power regulation function, or may also include power storage and power generation functions. For complete independence, the module may also include its own attitude control system.

US Patent:

20230028055, Jan 26, 2023

Filed:

Sep 28, 2022

Appl. No.:

17/936199

Inventors:

- FALLS CHURCH VA, US
HOWARD S. ELLER - REDONDO BEACH CA, US

International Classification:

B64G 4/00
F27B 14/14
F27B 14/10
B64G 1/22
B22F 5/00
F27B 14/06
B22F 3/00

Abstract:

A system and method for manufacturing a space-based component in space. The method includes collecting and capturing space debris directly from and suspended in space, heating the collected space debris using solar radiation in a manner that separately and independently melts different constituent elements and compounds in the space debris, collecting the different constituent elements and compounds as they are being separately melted, storing the elements and compounds in a molten, solid or vapor form, and fabricating the space-based component using the stored elements and compounds.