Los Alamos National Security, LLC

Triad National Security, LLC

U.S. Department of Energy

Stephen Judd

Nicholas Dallmann

Daniel Seitz

Kevin Peter McCabe

Michael Proicou

Steven Storms

Donald Enemark

John Martinez

Jerry Delapp

David Guenther

John Michel

Paul Stein

Gayle Kestell

Adam Warniment

Justin Tripp

Joseph Palmer

Janette Frigo

Alexandra Saari

Shawn Hinzey

Dean Prichard

Gerald J Seitz

Bruce Carlsten

Bradly J Cooke

Michael Shinas

Matthew Briggs

Joe J Tiee

Mervyn J Kellum

Nicholas L Olivas

Nina R Weisse-Bernstein

Thomas R Braun

Clifford M Fortgang

William Mairson

A tag enhances vehicle radar visibility of objects by increasing the effective radar cross-section of the object, allowing detection at longer ranges and providing the vehicle/driver with more time to avoid a collision. The tag may include a receive antenna and a bandpass filter configured to receive a signal from the receive antenna and to allow a portion of the frequency range of the signal from the receive antenna through. The tag may also include an amplifier configured to receive and amplify the signal with the portion of the frequency range from the bandpass filter. The tag may further include a transmit antenna configured to transmit the amplified signal. The receive antenna, the transmit antenna, and the amplifier may be configured such that antenna-to-antenna isolation between the receive antenna and the transmit antenna is greater than a gain of the amplifier.

Tag that enhances vehicle radar visibility of objects

Small cubesat systems may be available for a lower cost, have a higher reliability, and be much simpler to use than conventional cubesats. A complete turnkey system solution may be provided, including the ground station and remote field units. The satellite, ground station, and field unit may be provided separately as kits that are ready to go out-of-the-box as soon as they arrive. This enables universities, researchers, and hobbyists to obtain and deploy their own functional satellites. Furthermore, theoretical designs and functionality may be rapidly prototyped and demonstrated, which allows for proof-of-concept without needing to build a larger, more expensive satellite system and hope that the new design or functionality works as intended.

Cubesat system

A 'black box' space vehicle solution may allow a payload developer to define the mission space and provide mission hardware within a predetermined volume and with predetermined connectivity. Components such as the power module, radios and boards, attitude determination and control system (ADCS), command and data handling (C&DH), etc. may all be provided as part of a 'stock' (i.e., core) space vehicle. The payload provided by the payload developer may be plugged into the space vehicle payload section, tested, and launched without custom development of core space vehicle components by the payload developer. A docking station may facilitate convenient development and testing of the space vehicle while reducing handling thereof.

Space vehicle with customizable payload and docking station

Beacon-based Precision Navigation and Timing (PNT) may use a constellation of space vehicles (e.g., small, low cost satellites) coupled to a network of ground stations and a network of beacons. Such a system be provided at a cost that is approximately 100 times lower than GPS both to build and to operate. The resulting system may also provide fast acquisition, improved SNR, improved anti-jam and anti-spoofing capabilities, and six-inch scale location determination, making it applicable to both existing PNT applications and enabling new applications.

Beacon-based precision navigation and timing (PNT) system

A sensor system may be configured for continuous operation in a low resource environment and/or in extreme environmental conditions. The sensor system may have sufficient processing capabilities to provide scientific computing for pre-processing, quality control, statistical analysis, event classification, data compression and corrections (e.g., spikes in the data), autonomous decisions and actions, triggering other nodes, and information assurance functions that provide data confidentiality, data integrity, authentication, and non-repudiation. The hardware may have both mesh networking and satellite and cellular communication capability, and may be available for relatively low cost. Such a network provides the flexibility to have potentially any number of nodes be completely independent from one another. Thus, the network may scale across a diverse terrain.

Deployable sensor system using mesh networking and satellite communication

SAR imaging may be performed with range-resolved reflection data, where a spread-spectrum signal, such as a code division multiple access (CDMA) signal, is transmitted instead of a simple frequency chirp. The reflected spread-spectrum signal may be analyzed to gather range-resolved reflection data. Range-resolved reflection data may be gathered at each angular view. This data may be used to construct a more accurate approximation of the Fourier transform of the desired image than can be done by a conventional SAR approach. The image may be reconstructed from this Fourier transform using Fourier inversion techniques similar to those used in conventional SAR approaches. The range-resolved reflection scheme generally requires somewhat more processing to recover the image as compared with conventional SAR systems, but provides a significantly more stable image with less degradation from effects that plague conventional SAR systems. This can eliminate the need for phase coherency altogether and also eliminate 'phase drift,' which leads to image distortion. This may be especially well suited for high resolution imaging of relatively large targets.

Synthetic-aperture radar (SAR) imaging with range-resolved reflection data

A space vehicle may have a modular board configuration that commonly uses some or all components and a common operating system for at least some of the boards. Each modular board may have its own dedicated processing, and processing loads may be distributed. The space vehicle may be reprogrammable, and may be launched without code that enables all functionality and/or components. Code errors may be detected and the space vehicle may be reset to a working code version to prevent system failure.

Modular space vehicle boards, control software, reprogramming, and failure recovery

An ADCS module may be configured to use coordinate data fromD photodiodes in one or more sun sensors to determine a sun vector. The ADCS module may then use the sun vector in reference to its own body faced (BF) coordinate system to calculate a change in the orientation of the space vehicle. The change in orientation mechanism may be accomplished by reaction wheels, ion thrusters, or other orientation altering mechanisms. A miniature, intelligent star tracker may be included that improves satellite attitude determination and pointing accuracy. An improved reaction wheel assembly may be included that is more robust and suitable for inclusion in small space vehicles.

Attitude determination and control system (ADCS), sun sensor, and star tracker

A laser seismometer may measure the change in a phase modulated optical signal. Unlike traditional interferometers, the laser phase is first modulated by a radio frequency (RF) source, which is then demodulated following detection to provide the signal of interest. The net result is a direct measurement of displacement with the effects of amplitude noise eliminated via limiting and the effects of 1/f phase noise (frequency drift, etc.) eliminated by self-interfering the signal. Because the signal-to-noise ratio (SNR) of the optical signal is strong, the technique provides a strong measure of the displacement and avoids the extremely low voltages and associated problems of traditional sensors.

Low noise, high bandwidth, high sensitivity laser seismometer

A modular space vehicle chassis may facilitate convenient access to internal components of the space vehicle. Each module may be removable from the others such that each module may be worked on individually. Multiple panels of at least one of the modules may swing open or otherwise be removable, exposing large portions of the internal components of the space vehicle. Such chassis architectures may reduce the time required for and difficulty of performing maintenance or modifications, may allow multiple space vehicles to take advantage of a common chassis design, and may further allow for highly customizable space vehicles.

Space vehicle chassis

An adaptable, modular, multi-purpose (AMM) space vehicle backplane may accommodate boards and components for various missions. The AMM backplane may provide a common hardware interface and common board-to-board communications. Components, connectors, test points, and sensors may be embedded directly into the backplane to provide additional functionality, diagnostics, and system access. Other space vehicle sections may plug directly into the backplane.

Adaptable, modular, multi-purpose space vehicle backplane

A space vehicle electromechanical system may employ an architecture that enables convenient and practical testing, reset, and retesting of solar panel and antenna deployment on the ground. A helical antenna winding fixture may facilitate winding and binding of the helical antenna.

Space vehicle electromechanical system and helical antenna winding fixture

A field unit and ground station may use commercial off-the-shelf (COTS) components and share a common architecture, where differences in functionality are governed by software. The field units and ground stations may be easy to deploy, relatively inexpensive, and be relatively easy to operate. A novel file system may be used where datagrams of a file may be stored across multiple drives and/or devices. The datagrams may be received out of order and reassembled at the receiving device.

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Los Alamos, NM, United States of America

Stephen Judd