Abstract: The invention is for a startup system for nuclear fusion engines in space. The combustion of hydrogen and oxygen produces heat that is used by a heat engine to produce electricity. This can be supplemented by electricity from other operating engines. The exhaust from the combustion is condensed and electrolyzed to produce hydrogen and oxygen once the engine is in operation. This provides a constant source of energy for future startups. The engine is started up at partial power in electricity generation mode and this power replaces the power from the combustion as it grows. The combustor uses the same heat engine as the nuclear engine uses for power generation.
Type:
Application
Filed:
January 17, 2019
Publication date:
January 23, 2020
Applicants:
PRINCETON SATELLITE SYSTEMS, INC., THE TRUSTEES OF PRINCETON UNIVERSITY
Inventors:
Michael A. Paluszek, Eric M. Ham, Yosef Razin, Samuel A. Cohen
Abstract: The invention is for a startup system for nuclear fusion engines in space. The combustion of hydrogen and oxygen produces heat that is used by a heat engine to produce electricity. This can be supplemented by electricity from other operating engines. The exhaust from the combustion is condensed and electrolyzed to produce hydrogen and oxygen once the engine is in operation. This provides a constant source of energy for future startups. The engine is started up at partial power in electricity generation mode and this power replaces the power from the combustion as it grows. The combustor uses the same heat engine as the nuclear engine uses for power generation.
Type:
Grant
Filed:
August 22, 2014
Date of Patent:
March 12, 2019
Assignees:
PRINCETON SATELLITE SYSTEMS, INC., THE TRUSTEES OF PRINCETON UNIVERSITY
Inventors:
Michael A. Paluszek, Eric M. Ham, Yosef Razin, Samuel A. Cohen
Abstract: A system and method for producing and controlling high thrust and desirable specific impulse from a continuous fusion reaction is disclosed. The resultant relatively small rocket engine will have lower cost to develop, test, and operate that the prior art, allowing spacecraft missions throughout the planetary system and beyond. The rocket engine method and system includes a reactor chamber and a heating system for heating a stable plasma to produce fusion reactions in the stable plasma. Magnets produce a magnetic field that confines the stable plasma. A fuel injection system and a propellant injection system are included. The propellant injection system injects cold propellant into a gas box at one end of the reactor chamber, where the propellant is ionized into a plasma. The propellant and fusion products are directed out of the reactor chamber through a magnetic nozzle and are detached from the magnetic field lines producing thrust.
Type:
Grant
Filed:
May 10, 2013
Date of Patent:
November 21, 2017
Assignees:
Princeton Satellite Systems, The Trustees of Princeton University
Inventors:
Samuel A. Cohen, Gary A. Pajer, Michael A. Paluszek, Yosef S. Razin
Abstract: The invention is for a sensor for use in spacecraft navigation and communication. The system has two articulated telescopes providing navigation information and orientation information as well providing communications capability. Each telescope contains a laser and compatible sensor for optical communications and ranging, and an imaging chip for imaging the star field and planets. The three optical functions share a common optical path. A frequency selective prism or mirror directs incoming laser light to the communications and ranging sensor. The Doppler shift or time-of-flight of laser light reflected from the target can be measured. The sensor can use the range and range rate measured from the incoming laser along with measurements from the imaging chip to determine the location and velocity of the spacecraft. The laser and laser receiver provide communications capability.
Abstract: A MultiSpectral Vision Sensor (MSVS) that employs three detectors which detect optical radiation in different frequency bands to permit target detection in a wide range of lighting conditions.
Abstract: A system for recharging electric vehicles that optimizes the distribution of power to the users. The system meets the requirements of all the users for charging within their available time window while minimizing the cost of charging for the charging station.
Type:
Application
Filed:
March 2, 2018
Publication date:
September 6, 2018
Applicant:
Princeton Satellite Systems, Inc.
Inventors:
Michael Paluszek, Marilyn Ham, Gary Pajer, Stephanie Thomas
Abstract: Disclosed a multi-sensor multiple hypotheses testing tracking system. The multi-hypothesis testing system associates measurements from multiple sensors with tracks. Measurements are incorporated using a Kalman Filter and the same filters are used to propagate the trajectories of the tracks.
Type:
Application
Filed:
August 25, 2015
Publication date:
February 25, 2016
Applicant:
PRINCETON SATELLITE SYSTEMS, INC.
Inventors:
Michael A. Paluszek, Joseph Mueller, Stephanie Thomas
Abstract: The invention is for a multi-sensor multiple hypotheses testing tracking system. The multi-hypothesis testing system associates measurements from multiple sensors with tracks. Measurements are incorporated using a Kalman Filter and the same filters are used to propagate the trajectories of the tracks.
Type:
Application
Filed:
March 13, 2019
Publication date:
July 11, 2019
Applicant:
PRINCETON SATELLITE SYSTEMS, INC.
Inventors:
Michael A. PALUSZEK, Joseph MUELLER, Stephanie THOMAS
Abstract: The invention is for a multi-sensor multiple hypotheses testing tracking system. The multi-hypothesis testing system associates measurements from multiple sensors with tracks. Measurements are incorporated using a Kalman Filter and the same filters are used to propagate the trajectories of the tracks.
Type:
Application
Filed:
March 9, 2020
Publication date:
November 12, 2020
Applicant:
PRINCETON SATELLITE SYSTEMS, INC.
Inventors:
Michael A. PALUSZEK, Joseph MUELLER, Stephanie THOMAS
Abstract: The invention is for a multi-sensor multiple hypotheses testing tracking system. The multi-hypothesis testing system associates measurements from multiple sensors with tracks. Measurements are incorporated using a Kalman Filter and the same filters are used to propagate the trajectories of the tracks.
Type:
Grant
Filed:
March 13, 2019
Date of Patent:
March 10, 2020
Assignee:
PRINCETON SATELLITE SYSTEMS, INC.
Inventors:
Michael A. Paluszek, Joseph Mueller, Stephanie Thomas
Abstract: Disclosed a multi-sensor multiple hypotheses testing tracking system. The multi-hypothesis testing system associates measurements from multiple sensors with tracks. Measurements are incorporated using a Kalman Filter and the same filters are used to propagate the trajectories of the tracks.
Type:
Grant
Filed:
August 25, 2015
Date of Patent:
March 26, 2019
Assignee:
PRINCETON SATELLITE SYSTEMS, INC.
Inventors:
Michael A. Paluszek, Joseph Mueller, Stephanie Thomas
Abstract: A solar power camouflage system and apparatus are disclosed. The system includes a number of solar panels coupled to a net. The panels colored to produce a camouflage effect. A maximum power point tracking device coupled to the solar panels to manage to maintain the optimal voltage and current drawn through the panels. An energy storage device is coupled to the maximum power point tracking device. A power interface is coupled to said energy storage device to deliver power to other electrical devices.
Type:
Grant
Filed:
December 14, 2012
Date of Patent:
December 30, 2014
Assignee:
Princeton Satellite Systems
Inventors:
Yosef Shmuel Razin, Michael A. Paluszek
Abstract: Provided is a method and system for maneuvering a first spacecraft relative to a nearby second spacecraft that occupies a finite volume of space including obstacles in the vicinity of the second from a measured present relative position to a desired ending relative position. A trajectory is computed for the first spacecraft from the present relative position to the ending relative position using the A* algorithm. One or more thrusters of the first spacecraft are then fired. The first spacecraft's relative position and velocity are then measured and compared to the computed trajectory.
Abstract: A route finding system comprising a memory, GPS device, library of maps, an optimization algorithm and means for capturing user input and outputting data. The user input includes points, goals, constraints and relative preferences. Goals and constraints include characteristics of the route such as the type of road, number of turns, and traffic. The relative preferences are converted into numerical weights, positive or negative. In addition, the system integrates social networks' ratings and comments to further enhance route selection.
Type:
Application
Filed:
August 29, 2012
Publication date:
February 28, 2013
Applicant:
Princeton Satellite Systems
Inventors:
Michael Adam Paluszek, Mary Breton, Stephanie Thomas
Abstract: The invention is for a startup system for nuclear fusion engines in space. The combustion of hydrogen and oxygen produces heat that is used by a heat engine to produce electricity. This can be supplemented by electricity from other operating engines. The exhaust from the combustion is condensed and electrolyzed to produce hydrogen and oxygen once the engine is in operation. This provides a constant source of energy for future startups. The engine is started up at partial power in electricity generation mode and this power replaces the power from the combustion as it grows. The combustor uses the same heat engine as the nuclear engine uses for power generation.
Type:
Grant
Filed:
January 17, 2019
Date of Patent:
October 20, 2020
Assignee:
PRINCETON SATELLITE SYSTEMS, INC.
Inventors:
Michael A. Paluszek, Eric M. Ham, Yosef Razin, Samuel A. Cohen
Abstract: A dipole cancellation system and method may include a plurality of magnetometers for measuring a device magnetic field associated with a plurality of device coils generating a device magnetic field having a primary magnetic dipole moment. A compensating coil carrying a compensating current running a first direction that generates a compensating magnetic field having a compensating magnetic dipole moment. The compensating coil may be positioned and the first current may be selected so that the compensating magnetic dipole moment completely cancels the primary magnetic dipole moment. A method may use the system to stabilize a spacecraft by calculating an estimated torque of the spacecraft, receiving a value for an external magnetic field, receiving a value for a device magnetic field, and calculating and applying a compensating current may be then applied to the compensating coil to cancel the primary magnetic dipole moment, wherein the spacecraft is stabilized.
Abstract: A vertical axis wind turbine that can be actively controlled is provided. This invention includes mechanisms and methods for enabling high-efficiency wind energy extraction by a vertical axis wind turbine using active pitch and camber control of individual blades. Blade control is further integrated with generator control and power electronics. Integrated control algorithms are systematically constructed, and transmitted to the wind turbine through a wireless communications interface. The interface also allows the user to continuously monitor the state of the wind turbine system. This invention includes sensors and procedures for periodic self-calibration of wind turbine parameters for preserving the long-term efficiency of wind energy extraction. Furthermore, a capability to intelligently interact with other wind turbine systems in a wind-farm setting is incorporated.
Abstract: A dipole cancellation system and method may include a plurality of magnetometers for measuring a device magnetic field associated with a plurality of device coils generating a device magnetic field having a primary magnetic dipole moment. A compensating coil carrying a compensating current running a first direction that generates a compensating magnetic field having a compensating magnetic dipole moment. The compensating coil may be positioned and the first current may be selected so that the compensating magnetic dipole moment completely cancels the primary magnetic dipole moment. A method may use the system to stabilize a spacecraft by calculating an estimated torque of the spacecraft, receiving a value for an external magnetic field, receiving a value for a device magnetic field, and calculating and applying a compensating current may be then applied to the compensating coil to cancel the primary magnetic dipole moment, wherein the spacecraft is stabilized.
Abstract: A vertical axis wind turbine that can be actively controlled has the potential to extract wind energy efficiently, and consequently be economically viable for distributed harvesting of wind energy. This invention includes mechanisms and methods for enabling high-efficiency wind energy extraction by a vertical axis wind turbine using active pitch and camber control of individual blades. Blade control is further integrated with generator control and power electronics. Integrated control algorithms are systematically constructed, and transmitted to the wind turbine through a wireless communications interface. The interface also allows the user to continuously monitor the state of the wind turbine system. This invention includes sensors and procedures for periodic self-calibration of wind turbine parameters for preserving the long-term efficiency of wind energy extraction. Furthermore, a capability to intelligently interact with other wind turbine systems in a wind-farm setting is incorporated.
Abstract: The invention is for spacecraft reaction wheel with an axial flux dual Halbach rotor with an air coil stator. This wheel is more efficient and has fewer disturbances than a conventional reaction wheel with a brushless DC motor.
Type:
Application
Filed:
October 3, 2012
Publication date:
April 4, 2013
Applicant:
PRINCETON SATELLITE SYSTEMS, INC.
Inventors:
Eloisa Mae De Castro, Michael A. Paluszek