Triad National Security, LLC

Los Alamos National Security, LLC

Nicholas Dallmann

Daniel Seitz

Stephen Judd

Michael Proicou

Kevin Peter McCabe

Paul Stein

John Martinez

Jerry Delapp

Steven Storms

Adam Warniment

Donald Enemark

John Michel

Jane Elizabeth Nordholt

Richard John Hughes

Charles Glen Peterson

Raymond Thorson Newell

Kush T Tyagi

Justin Tripp

Gayle Kestell

David Guenther

Joseph Palmer

James Wren

Hannah Mohr

Christopher C Wipf

Dean Prichard

Logan Ott

Mahlon Scott Wilson

Bryce Tappan

Danna Rosenberg

Joseph Lichthardt

David Hemsing

Malakai Coblentz

Kavitha Chintam

Ian Shelburne

Kimberly Katko

Donathan Ortega

William Mairson

Robert Wheat, Jr

An attitude determination and control system (ADCS) may include relatively large momentum wheels (i.e., reaction wheels) for improved momentum storage and magnetic torque rods that enable low power sun pointing and dissipate angular momentum imparted during deployment or by differential drag on the space vehicle. The momentum wheels, magnetic torque rods, or both may be algorithmically selected and driven to perform various maneuvers.

Attitude determination and control system (ADCS)

A system for multiple burns from a solid fuel rocket motor may extinguish rocket fuel after the rocket has been ignited. The motor may be extinguished via rapid decompression of the combustion chamber. The fuel may then be reignited by a suitable igniter, and the process of extinguishing and reigniting may be repeated, enabling multi-burn maneuvers. A decompressive extinguishing plug nozzle may extinguish solid rocket fuel after the rocket has been ignited and/or keep a rocket in a disarmed (zero thrust) state until the rocket is to be armed. The nozzle may include a plug that mostly impedes the opening of the nozzle and an outer cowl that is movable to rapidly decompress the combustion chamber. This rapid decompression extinguishes the solid rocket fuel. In some aspects, the fuel can be reignited and extinguished multiple times.

System for multiple burns from a rocket motor

Message authenticators for quantum-secured communications facilitate low-latency authentication with assurances of security. Low-latency message authenticators are especially valuable in infrastructure systems where security and latency constraints are difficult to satisfy with conventional non-quantum cryptography. For example, a message transmitter receives a message and derives an authentication tag for the message based at least in part on an authenticator that uses one or more quantum keys. The message transmitter outputs the message and its authentication tag. A message receiver receives a message and authentication tag for the message. The message receiver derives a comparison tag for the message based at least in part on an authenticator that uses one or more quantum keys. The message receiver checks whether the message is authentic based on a comparison of the authentication tag and the comparison tag. In example implementations, the authenticator uses stream-wise cyclic redundancy code operations.

Streaming authentication and multi-level security for communications networks using quantum cryptography

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

A payload interposer (PIP) board provides an interface for hosting payloads on a space vehicle platform. Payload development may be performed via the PIP board in a manner that 'abstracts' the hardware of the space vehicle from the payload developer. The PIP board may include a host side payload interface connector that connects to a space vehicle and a payload side payload interface connector that connects to a payload. Power, CDH, and other space vehicle functionality may thus be provided to the payload from the space vehicle via the PIP board.

Space vehicle system and payload interposer (PIP) board

A compact SFS may can be deployed in small space vehicles. The SFS may have a small size, weight, and low power requirements. The hardware, software, catalogs, and calibration algorithm of the SFS provide highly accurate attitude information that can be used for pointing. For instance, accurate attitude determination may be provided that supports pointing of a deployable high gain helical antenna. A full 'lost in space' attitude solution, accurate to about an arcminute, may be accomplished in under a minute. The SFS may be fully reprogrammable on orbit, allowing continued algorithm development and deployment after launch.

Compact star-field sensor (SFS)

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

A payload interposer (PIP) system and its control software provide an interface between a space vehicle and a payload. The PIP board facilitates power and communications between a command and data handler (CDH) of the space vehicle and the payload. A microcontroller of the PIP board may control operation of the payload, format messages between the space vehicle and the payload, and extract data from the payload for downlink via the space vehicle.

Payload interposer (PIP) system and control software

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 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

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Los Alamos, NM, United States of America

Nicholas Dallmann