Andrew C Nicholas

US Patent:

7948425, May 24, 2011

Filed:

May 14, 2008

Appl. No.:

12/120407

Inventors:

Paul A Bernhardt - Alexandria VA, US
Chuck Hoberman - New York NY, US
David L. Hysell - Ithaca NY, US
Andrew C. Nicholas - Olney MD, US
Michael W. Nurnberger - Alexandria VA, US

Assignee:

Cornell University - Ithaca

International Classification:

H01Q 15/00

US Classification:

342 5, 342 8, 342165

Abstract:

A high frequency signal calibration target deployable in outer space includes an expandable and electrically conductive symmetric structure. The structure may mechanically expand from a stowed configuration to a deployed configuration. Scatter of high frequency signal off of a substantially symmetric signal calibration target may be measured to accurately calibrate systems using high frequency signals.

US Patent:

8525110, Sep 3, 2013

Filed:

Sep 28, 2011

Appl. No.:

13/247168

Inventors:

Federico Herrero - Glenn Dale MD, US
Hollis H. Jones - Gassville AR, US
Theodore T. Finne - Fairfax VA, US
Andrew Nicholas - Olney MD, US

Assignee:

The United States of America as represented by the Administrator of the National Aeronautics Space Administration - Washington DC

International Classification:

H01J 49/26

US Classification:

250288, 250281, 250282

Abstract:

Embodiments of the present invention pertain to an apparatus that provides four simultaneous ion and neutral measurements as a function of altitude with variable sensitivity for neutral atmospheric species. The variable sensitivity makes it possible to extend the measurements over the altitude range of 100 to more than 700 kilometers. The four instruments included in the apparatus are a neutral wind-temperature spectrometer, an ion-drift ion-temperature spectrometer, a neutral mass spectrometer, and an ion mass spectrometer. The neutral wind-temperature spectrometer and ion-drift ion-temperature spectrometer are configured to separate O and Nand O+ from H+ while the neutral mass spectrometer and the ion mass spectrometer are configured to separate mass with a resolution of one in sixty-four to enable metallic ion identification in the lower thermosphere. The energy analyzer features of the wind-temperature spectrometer and ion-drift ion-temperature spectrometer also enable the measurement of the thermosphere-to-exosphere transition in the Earth's upper atmosphere.

US Patent:

20160377700, Dec 29, 2016

Filed:

Jun 23, 2016

Appl. No.:

15/190292

Inventors:

- Arlington VA, US
Andrew C. Nicholas - Glenelg MD, US

International Classification:

G01S 5/10

Abstract:

In a geolocation method and/or apparatus, a plurality of satellites is provided in a fixed Earth-Sun coordinate system or a fixed Earth-moon coordinate system. Two respective radio frequency band signals of the plurality of respective radio frequency band signals are received by at least one receiver from at least two satellites of the plurality of satellites, the at least one receiver comprising at least one respective geolocation. The at least one receiver generating at least two pluralities of equal Doppler shift contours corresponding to the at least two satellites of the plurality of satellites. The at least one receiver determines the at least one respective geolocation based at least in part on a universal time and intersections of the at least two pluralities of equal Doppler shift contours. The at least one receiver outputs the at least one respective geolocation.

US Patent:

20150100272, Apr 9, 2015

Filed:

Jul 25, 2014

Appl. No.:

14/341159

Inventors:

Andrew C. Nicholas - Glenelg MD, US
Nelson Creamer - Waldorf MD, US
Theodore T. Finne - Fairfax VA, US
Federico A. Herrero - Glenn Dale MD, US

Assignee:

The Government of the United States of America, as represented by the Secretary of the Navy - Washington DC

International Classification:

B64G 1/36
B64G 1/10

US Classification:

702154

Abstract:

A method and system is described for determining attitude for a satellite. A two-axis ram sensor head measures neutral winds and provides a density of the neutral winds. A three-axis magnetometer measures a geomagnetic field. A measurement interface module calculates attitude information, which includes three-axis attitude knowledge of a satellite relative to a local-vertical local-horizontal orbit frame, based on the combined ram measurements and magnetic field measurements, and provides the attitude information to a satellite that comprises the attitude sensor system.