公开(公告)号：US10669045B1

公开(公告)日：2020-06-02

申请号：US15630795

申请日：2017-06-22

Applicant: USA as Represented by the Administrator of the National Aeronautics and Space Administration

Inventor： James Joseph Cockrell ,  Max Michael Briggs ,  David James Mayer ,  Aaron James Cohen

IPC: B64G1/00 ,  B64G1/36

Abstract: A system and method of providing an affordable navigation, guidance and control system for arbitrary nano/micro launch vehicles by integrating commercial grade sensors with advanced estimation algorithms in a manner that provides sufficient accuracy of the resulting vehicle state estimates to inject nano/micro satellites into low earth orbits. The system and method uses commercial grade sensors and an advanced sensor-fusion estimator software that estimates and removes the estimated measurement errors and filters noise produced by the commercial grade sensors, resulting in estimated states with suitable accuracy. The filtered data are sent to a guidance and control system where actuator commands are formulated based on the filtered data. A simulated launch and flight of the launch vehicle is performed using the filtered data to validate that the GNC system and launch vehicle are ready for launch.

公开(公告)号：US10564248B1

公开(公告)日：2020-02-18

申请号：US14922306

申请日：2015-10-26

Applicant: U.S.A., as represented by the Administrator of the National Aeronautics and Space Administration

Inventor： Rainee Simons ,  Edwin Wintucky

IPC: G01S1/04 ,  H03L7/20

Abstract: A multi-tone multi-band tunable millimeter-wave synthesizer is provided. In some embodiments, the multi-tone multi-band tunable millimeter-wave synthesizer is configured to simultaneously generate multiple frequency tones for space-borne beacon transmitter for atmospheric radio wave propagation studies. The apparatus includes a comb generator, which puts out evenly spaced harmonic frequencies of the input signal, which are coherent, tunable, and the number of tones or combs is scalable over a wide range of frequencies. These harmonics or tones are amplified to the power level needed for radio wave propagation studies. The amplified signals are transmitted as beacon signals from a satellite to a ground receiving station.

公开(公告)号：US10527717B2

公开(公告)日：2020-01-07

申请号：US14817843

申请日：2015-08-04

Applicant: U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration

Inventor： Joel F. Campbell ,  Bing Lin ,  Amin R. Nehrir

IPC: G01S13/32 ,  G01S17/32 ,  G01S17/95 ,  G01S13/95 ,  G01S15/32

Abstract: Systems, methods, and devices of the present invention use a single Pseudo Noise (PN) code to modulate multiple orthogonal carriers by Binary Phase Shift Keying (BPSK) modulation. The various embodiments enable closely spaced carriers to be modulated with the same periodic PN sequence using BPSK modulation. In this manner, even though the carriers may almost entirely share bandwidth, orthogonality of the carriers may not be lost, enabling the various embodiments to be used with limited bandwidth Intensity Modulated Continuous Wave (IM-CW) Light detection and ranging (Lidar), Radio detection and ranging (Radar), or Sound Navigation and Ranging (Sonar) systems. Additionally, by using orthogonal carriers the various embodiments enable measurements to be made simultaneously, thereby reducing the error compared to systems that require sequential measurements, such as pulsed Lidar systems.

公开(公告)号：US10513080B2

公开(公告)日：2019-12-24

申请号：US15345064

申请日：2016-11-07

Applicant: U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration

Inventor： Jae-Woo Kim ,  Godfrey Sauti ,  John M. Gardner ,  Emilie J. Siochi

IPC: B29C67/00 ,  B33Y10/00 ,  B29C64/106 ,  B33Y50/02 ,  B29K105/16 ,  B29C64/386

Abstract: A method of fabricating composite articles includes supplying electrical current to an electrically conductive filament. The electrically conductive filament may include a first material that is electrically conductive and a polymer second material. The polymer second material comprises at least one of a thermoplastic polymer and a partially cured thermosetting polymer. The heated filament is deposited according to a predefined pattern in successive layers to adhere the polymer material of the layers together and build up a three dimensional article. The article includes strands of the first material embedded in a substantially continuous polymer matrix of the second material.

公开(公告)号：US10339114B2

公开(公告)日：2019-07-02

申请号：US14711137

申请日：2015-05-13

Applicant: The United States of America represented by the Administrator of the National Aeronautics and Space Administration

Inventor： John L. Schnase ,  Daniel Q. Duffy ,  Glenn S. Tamkin ,  Mark McInerney ,  Denis Nadeau ,  John H. Thompson ,  Scott Sinno ,  Savannah L. Strong

IPC: G06F16/21 ,  G06F16/182

Abstract: A system, method and computer-readable storage devices for providing an interface for an analytic service for Modern-Era Retrospective Analysis for Research and Applications (MERRA) datasets. An example system for providing the service includes a data analytics platform of an assemblage of compute and storage nodes that provide a compute-storage fabric upon which high-performance parallel operations are performed over a collection of climate data stored in a distributed file system, a sequencer that transforms the climate data, a desequencer that transforms serialized block compressed sequence files between data formats. The system includes a services library of applications that dynamically create data objects from the data as reduced final results, and a utilities library of software applications that process flat serialized block compressed sequence files. The system also includes a service interface through which a client device can access the climate data via the data analytics platform.

公开(公告)号：US10332405B2

公开(公告)日：2019-06-25

申请号：US14577272

申请日：2014-12-19

Applicant: The United States of America, as represented by the Administrator of the National Aeronautics & Space Administration (NASA)

Inventor： Parimal Kopardekar

IPC: G08G5/00

Abstract: The present invention provides a traffic management system for managing unmanned aerial systems (UASs) operating at low-altitude. The system includes surveillance for locating and tracking UASs in uncontrolled airspace, for example, in airspace below 10,000 feet MSL. The system also includes flight rules for safe operation of UASs in uncontrolled airspace. The system further includes computers for processing said surveillance and for applying the flight rules to UASs. The traffic management system may be portable, persistent, or a hybrid thereof.

公开(公告)号：US10309376B1

公开(公告)日：2019-06-04

申请号：US14858424

申请日：2015-09-18

Applicant: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration

Inventor： Rodger W. Dyson ,  Geoffrey A. Bruder

IPC: F02D29/06 ,  F03G7/00

Abstract: A thermo-acoustic engine and/or cooler is provided and includes an elongated tubular body, multiple regenerators disposed within the body, multiple heat exchangers disposed within the body, where at least one heat exchanger is disposed adjacent to each of the multiple regenerators, multiple transducers axially disposed at each end of the body, and an acoustic wave source generating acoustic waves. At least one of the acoustic waves is amplified by one of the regenerators and at least another acoustic wave is amplified by a second one of regenerators.

公开(公告)号：US10298060B2

公开(公告)日：2019-05-21

申请号：US15265308

申请日：2016-09-14

Applicant: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration

Inventor： Michael R. Wright

IPC: B60L11/18 ,  H02J50/10 ,  B64G1/42

Abstract: An apparatus and method of wirelessly powering an aerospace vehicle while the vehicle is on the ground is provided to solve a problem of supplying electric power for aircraft while idling on taxiways. Present systems typically require fuel-driven auxiliary power units (APU's) to generate electricity. Running APU's to power aircraft while idling requires over 443 million gallons of jet fuel annually at a cost of $1.3 billion dollars. This results in an estimated 4.7 megatons of carbon dioxide emissions annually. At the gate, shore power is provided via hardline connection.

公开(公告)号：US10273024B1

公开(公告)日：2019-04-30

申请号：US15277446

申请日：2016-09-27

Applicant: The United States of America as represented by the Adminstrator of the National Aeronautics and Space Administration

Inventor： Robert C. Youngquist ,  Mark A. Nurge

IPC: G02B5/08 ,  B64G1/58

Abstract: A multi-layer radiation reflector/emitter includes first and second materials. The first material is transparent to radiation in a wavelength spectrum ranging from approximately 0.2 microns to at last 6 microns. The first material is a self-supporting arrangement of randomized particles having an average dimension in a range of approximately 0.2 microns to approximately 0.4 microns and defining a fill factor of approximately 0.1 to approximately 0.5. The second material reflects radiation having a wavelength greater than approximately 2 microns.

公开(公告)号：US10272987B2

公开(公告)日：2019-04-30

申请号：US15005338

申请日：2016-01-25

Applicant: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration

Inventor： Travis L. Turner ,  Reggie T. Kidd ,  David P Lockard ,  Mehdi R. Khorrami ,  Craig L. Streett ,  Douglas Leo Weber

IPC: B64C3/48 ,  B64C9/22 ,  B64C9/24

Abstract: A slat cove filler is utilized to reduce airframe noise resulting from deployment of a leading edge slat of an aircraft wing. The slat cove filler is preferably made of a super elastic shape memory alloy, and the slat cove filler shifts between stowed and deployed shapes as the slat is deployed. The slat cove filler may be configured such that a separate powered actuator is not required to change the shape of the slat cove filler from its deployed shape to its stowed shape and vice-versa. The outer contour of the slat cove filler preferably follows a profile designed to maintain accelerating flow in the gap between the slat cove filler and wing leading edge to provide for noise reduction.