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公开(公告)号：US10096256B2
公开(公告)日：2018-10-09
申请号：US15451969
申请日：2017-03-07
Applicant: Rosemount Aerospace Inc.
Inventor： Robert Rutkiewicz , Todd Anthony Ell , Joseph T. Pesik
Abstract: Apparatus and associated methods relate to calculating position and/or range data of object(s) in a scene external to an aircraft. A light projector is configured to project, from an aircraft projector location, a collimated beam of light in a controllable direction onto the scene. The light projector is further configured to control the intensity of the projected light, based on the controlled direction of the collimated beam of light. The reflected beam is detected by a camera located apart from the light projector. An image processor is configured to use triangulation, to calculate position values and/or range data of the object(s) in the scene. The image processor can be further configured to identify the object(s) in the scene and to produce, based in object(s) in the scene, one or more maps of the scene. The intensity of the collimated beam can be controlled based on the produced maps.
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公开(公告)号：USD829257S1
公开(公告)日：2018-09-25
申请号：US29583966
申请日：2016-11-10
Applicant: Rosemount Aerospace Inc.
Designer： Kevin J. Benning , Jonathan L. Boer , Wallace Johnson , Eric L. Lovaasen , Richard Alan Schwartz
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公开(公告)号：US20180261111A1
公开(公告)日：2018-09-13
申请号：US15451969
申请日：2017-03-07
Applicant: Rosemount Aerospace Inc.
Inventor： Robert Rutkiewicz , Todd Anthony Ell , Joseph T. Pesik
Abstract: Apparatus and associated methods relate to calculating position and/or range data of object(s) in a scene external to an aircraft. A light projector is configured to project, from an aircraft projector location, a collimated beam of light in a controllable direction onto the scene. The light projector is further configured to control the intensity of the projected light, based on the controlled direction of the collimated beam of light. The reflected beam is detected by a camera located apart from the light projector. An image processor is configured to use triangulation, to calculate position values and/or range data of the object(s) in the scene. The image processor can be further configured to identify the object(s) in the scene and to produce, based in object(s) in the scene, one or more maps of the scene. The intensity of the collimated beam can be controlled based on the produced maps.
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公开(公告)号：US10065853B2
公开(公告)日：2018-09-04
申请号：US15161724
申请日：2016-05-23
Applicant: Rosemount Aerospace Inc.
Inventor： Jim Golden , Robert Stuelke
Abstract: A differential pressure sensor is a body with first and second interior channels connected to process fluid inlets and separated by a barrier. Each side of a MEMS pressure sensing diaphragm in the barrier is fluidly connected to a process fluid inlet. The diaphragm is mounted on a hollow pedestal such that one side of the diaphragm is fluidly connected to a process fluid inlet through an interior channel in the pedestal that is adhesively attached to an annular bottom of a cylindrical cavity inside the body. The other side of the diaphragm is fluidly connected to the other process fluid inlet and is fluidly isolated from the first fluid inlet by the adhesive at the bottom of the pedestal. Deformation of the diaphragm due to a pressure difference between the process fluid inlets detected by sensors on the diaphragm indicates a differential pressure.
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公开(公告)号：US10060943B2
公开(公告)日：2018-08-28
申请号：US15074567
申请日：2016-03-18
Applicant: Rosemount Aerospace Inc.
Inventor： Weibin Zhang
IPC: G01P15/09
CPC classification number: G01P15/0922
Abstract: Apparatus and associated methods relate to maximizing a signal to noise ratio of an accelerometer by inhibiting signals arising from movements of a proofmass in directions perpendicular to a direction of intended sensitivity. The direction of intended sensitivity of the accelerometer is along an axis of the proofmass. The accelerometer is rendered substantially insensitive to lateral accelerations of the proofmass by making the accelerometer axially symmetric. Two axially-asymmetric acceleration sensing devices are axially engaged in such a manner as to render the coupled sensing devices substantially axially-symmetric. In some embodiments, each acceleration sensor has an axially-thin membrane portion extending from a proofmass portion. The two acceleration sensors can be engaged in an antiparallel fashion at projecting ends of the proofmass portions. An engagement surface will be located about halfway between the axially-thin membrane portions of the two acceleration sensors, thereby causing mechanical symmetry about the engagement surface.
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Patent Agency Ranking
公开(公告)号：US20180225540A1
公开(公告)日：2018-08-09
申请号：US15428638
申请日：2017-02-09
Applicant: Rosemount Aerospace Inc.
Inventor： Todd Anthony Ell
IPC: G06K9/46 , G06T7/73 , G06T7/246 , G01C19/5776
CPC classification number: G06K9/4604 , G01C19/5776 , G06T7/246 , G06T7/277 , G06T7/30 , G06T7/73 , G06T2207/10004 , G06T2207/10016 , G06T2207/30212
Abstract: An imager device disposed on a moving body captures first image data at a first time and second image data at a second, subsequent time. An inertial measurement unit (IMU) disposed on the moving body senses motion of the moving body between the first time and the second time. The first image data is registered to the second image data based on inertial measurement data corresponding to the sensed motion to produce first registered image data. In response to identifying that image features are common to both the first registered image data and the second image data, the first registered image data is registered to the second image data based on the identified common features to produce output registered image data. In response to determining that no image features are common to both the first registered image data and the second image data, the first registered image data is output.
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公开(公告)号：US20180209887A1
公开(公告)日：2018-07-26
申请号：US15411520
申请日：2017-01-20
Applicant: Rosemount Aerospace Inc.
Inventor： Mark Ray , Kaare Josef Anderson
CPC classification number: G01N15/0211 , B64D15/20 , G01N21/49 , G01N2015/0026 , G01S7/4811 , G01S7/4815 , G01S7/4818 , G01S17/95 , G01W1/00
Abstract: Apparatus and associated methods relate to determining a size and/or density of Super-cooled Large Droplets (SLDs) in a cloud atmosphere by comparing detected optical signals reflected from small and large sampling volumes of a cloud atmosphere. In some embodiments, an optical pulse is generated and divergently projected from a first optical fiber. A collimating lens is aligned within the divergently projected optical pulse collimating a portion thereof. The collimated and uncollimated portions of the optical pulse are projected into the small and large sampling volumes of the cloud atmosphere, respectively. The ratio of the collimated to the uncollimated portions can be optically controlled. Signals corresponding to optical pulses having different collimated/uncollimated ratios are backscattered by the cloud atmosphere, detected and compared to one another. A processor is configured to calculate, based on scintillation spike differences between the optical pulses of different collimated/uncollimated ratios, a size and/or density of SLDs.
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公开(公告)号：US20180209764A1
公开(公告)日：2018-07-26
申请号：US15337932
申请日：2016-10-28
Applicant: Rosemount Aerospace Inc.
Inventor： David Ginsberg , William A. Veronesi , Joseph V. Mantese , Todd Ell , Martin Krucinski
CPC classification number: F41G7/2233 , F41G7/2246 , F41G7/226 , F41G7/2293 , G01S7/4815 , G01S17/89 , G05D1/12
Abstract: Apparatus and associated methods relate to coordinating guided-missile targeting among multiple guided missiles using inter-missile optical communications. An inter-missile communications channel is optically established with a first guided missile illuminating a first target within a scene aligned along a first missile axis, and a second guided missile receiving the illumination reflected by the first target. By illuminating the first target within the scene, the first guided missile designates the first target. The second guided missile can be configured to navigate to the designated first target or to select a second target not designated by the first guided missile. In some embodiments, the second guided missile can be configured to illuminate its selected second target so as to designate the selected second target and to communicate the designation to other guided missiles. By facilitating communications among a plurality of guided missiles, missile targeting can be coordinated during a flight portion of a guided-missile operation.
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公开(公告)号：US10012477B1
公开(公告)日：2018-07-03
申请号：US15452295
申请日：2017-03-07
Applicant: Rosemount Aerospace Inc.
Inventor： Todd Anthony Ell , Martin Krucinski
IPC: F41G7/22
CPC classification number: F41G7/2233 , F41G7/008 , F41G7/2246 , F41G7/2253 , F41G7/226 , F41G7/2293
Abstract: Apparatus and associated methods relate to coordinating targeting among multiple guided ordnances using inter-ordnance optical communications. An inter-ordnance communications channel is optically established between leading and trailing guided ordnances travelling in substantially the same direction. The leading guided ordnance emits an optical beacon in a direction aft of the direction of ordnance travel, and a trailing guided ordnance captures images that contain the optical beacon emitted by the leading guided ordnance. The trailing guided ordnance is configured to chart a trajectory of the leading guided ordnance. The trailing guided ordnance is configured to predict which, among multiple targets identified in the captured images, is a first target consistent with the charted trajectory of and therefore selected by the leading ordnance. The trailing guided ordnance is further configured to select, based on the captured images, a second target that is within a navigable range of the trailing guided ordnance.
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公开(公告)号：US20180170572A1
公开(公告)日：2018-06-21
申请号：US15897537
申请日：2018-02-15
Applicant: Rosemount Aerospace Inc.
Inventor： Kaare Josef Anderson , Brian Daniel Matheis , Derrick D. Hongerholt , William Kunik
Abstract: In one example, a method includes receiving, over an aircraft data communications bus, a plurality of non-pneumatic inputs corresponding to aircraft operational parameters. The method further includes processing the plurality of non-pneumatic inputs through an artificial intelligence network to generate an air data output value, and outputting the air data output value to a consuming system for use when a pneumatic-based air data output value is determined to be unreliable.
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