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公开(公告)号：US20240417109A1
公开(公告)日：2024-12-19
申请号：US18336333
申请日：2023-06-16
Applicant: The Boeing Company
Inventor： Andrew WALSH , Reid REYNOLDS
Abstract: Techniques for accounting for rotational bias of an inertial measurement unit in a setting where momentum is conserved are presented. The techniques include: obtaining, from an inertial measurement unit, an initial magnitude of momentum and initial directional rotational rates; iteratively updating an estimate of bias of magnitude of momentum and estimates of bias of directional rotational rates based at least on the obtaining and based at least on readings from the inertial measurement unit; adjusting directional rotational rates obtained from the inertial measurement unit to account for the estimates of bias of directional rotational rates, where bias adjusted directional rotational rates are determined; and providing the bias adjusted directional rotation rates.
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公开(公告)号：US11993401B2
公开(公告)日：2024-05-28
申请号：US17781936
申请日：2020-12-03
Applicant: THRUSTME
Inventor： Dmytro Rafalskyi , Javier Martinez Martinez , Elena Zorzoli Rossi
Abstract: Disclosed is a space cold gas thruster operating with a solid propellant. The cold gas thruster includes a tank suitable for containing a solid propellant and a tank heating device suitable for sublimating the solid propellant and forming gaseous propellant, the tank having an aperture for transferring the gaseous propellant outside the tank, such as a nozzle. Also disclosed is a process for determining the amount of remaining propellant in the propellant tank of the disclosed cold gas thruster.
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公开(公告)号：US20230418308A1
公开(公告)日：2023-12-28
申请号：US18243262
申请日：2023-09-07
Applicant: LOCKHEED MARTIN CORPORATION
Inventor： Wayne K. Schroeder
CPC classification number: G05D1/08 , B63G8/16 , B63H25/46 , B64C15/00 , B64G1/26 , F42B10/661 , F42B19/01 , G05D1/0858
Abstract: A monolithic attitude control motor frame includes a monolithic structure including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. Adjacent cavities of the plurality of cavities share a side wall or side wall portion therebetween. Each of the cavities is configured to receive an attitude control motor. A monolithic attitude control motor system includes a monolithic frame including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. The system further includes a plurality of attitude control motors corresponding to the plurality of cavities, such that an attitude control motor of the plurality of attitude control motors is disposed in each cavity of the plurality of cavities.
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公开(公告)号：US20230271729A1
公开(公告)日：2023-08-31
申请号：US17649258
申请日：2022-01-28
Applicant: Taiwan Happy Energy Co., Ltd.
Inventor： Chih Hung WANG
Abstract: A liquid-driven propulsion device includes a first and a second chamber. The first chamber includes a first seal movable or deformable within the first chamber, the first seal being configured to separate a working liquid in the first chamber from a first space having a first pressure. The second chamber includes a second seal movable or deformable within the second chamber and configured to separate a working liquid in the second chamber from a second space having a second pressure. The first and the second chambers are coupled to each other to enable a flow of liquid between the first and second chambers. When the first pressure is greater than the second pressure, the working liquid in the first chamber moves in a first direction and the working liquid in the second chamber moves in a second direction to provide a propulsion force applied to the liquid-driven propulsion device.
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公开(公告)号：US20230044244A1
公开(公告)日：2023-02-09
申请号：US17963632
申请日：2022-10-11
Applicant: LOCKHEED MARTIN CORPORATION
Inventor： Wayne K. Schroeder
Abstract: A monolithic attitude control motor frame includes a monolithic structure including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending from the outer surface of revolution. Adjacent cavities of the plurality of cavities share a side wall or side wall portion therebetween. Each of the cavities is configured to receive an attitude control motor. A monolithic attitude control motor system includes a monolithic frame including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. The system further includes a plurality of attitude control motors corresponding to the plurality of cavities, such that an attitude control motor of the plurality of attitude motors is disposed in each cavity of the plurality of cavities.
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Patent Agency Ranking
公开(公告)号：US20220297858A1
公开(公告)日：2022-09-22
申请号：US17572796
申请日：2022-01-11
Applicant: CubeRocket Inc.
Inventor： Jeongrak LEE , Eunji LEE , Youngbin SON , Yoonju LEE , Hanseong JO
Abstract: A solar panel module includes a solar panel; a printed circuit board combined with a plane of the solar panel and including a microchamber and an ignition circuit; and a propellent inserted into the microchamber and connected to the ignition circuit.
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公开(公告)号：US11440683B2
公开(公告)日：2022-09-13
申请号：US16463125
申请日：2017-11-14
Applicant: L'Air Liquide, Societe Anonyme pour l'Etude et l'Exploitation des Procedes Georges Claude
Inventor： Francois Martin
Abstract: Device and method for regulating a flow rate of gas intended to supply a propulsion apparatus for a spacecraft comprising xenon tank, a circuit comprising a withdrawing pipe having an upstream end connected to the tank and a downstream end connected to a propulsion member, the withdrawing pipe comprising an isolation first valve, a regulating second valve and a member for measuring the pressure downstream of the regulating second valve. The regulating second valve regulates the flow rate and/or the determined pressure according to the pressure measured. The regulating second valve is a proportional valve of electrically operated variable throughout PCV type.
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公开(公告)号：US11346306B1
公开(公告)日：2022-05-31
申请号：US16733518
申请日：2020-01-03
Applicant: Ball Aerospace & Technologies Corp.
Inventor： Gordon C. Wu , Suzan Q. Green
Abstract: Integrated chemical propellant and cold gas propulsion systems and methods are provided. A storage or fuel tank containing the chemical propellant is pressurized by a pressurant. The chemical propellant is selective passed to a propellant thruster through a first port of the storage tank and a propellant valve. The pressurant is selectively passed to a cold gas thruster through a second port of the storage tank and a cold gas valve. In addition, a pressurant tank can be provided. Pressurant contained within the pressurant tank can be selectively placed in communication with the pressurant contained within the storage tank via a pressurant valve, or can be selectively passed to the cold gas thruster through the cold gas thruster valve. Systems can also include bi-propellant thrusters, with a first and second chemical compounds and volumes of pressurant stored in first and second storage tanks respectively.
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公开(公告)号：US11345488B2
公开(公告)日：2022-05-31
申请号：US15748951
申请日：2016-07-25
Applicant: D-Orbit SpA
Inventor： Luca Rossettini , Goncalo Daniel Albano Lopes
Abstract: A propulsion system for small artificial satellites comprises a plurality of engines (2) fixable to a frame (101) of a satellite (100); a control unit (3) connected functionally to the engines (2) for sending at least one activation signal (AS) for activating at least one engine (2); the system is selectively configurable at least between a first configuration in which at least one of the engines (2) is activated for correcting the orbit of the satellite (100) and a second configuration in which at least one of the engines (2) is activated for dispersing said satellite (100) relative to another adjacent satellite.
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公开(公告)号：US11174048B2
公开(公告)日：2021-11-16
申请号：US16266520
申请日：2019-02-04
Applicant: Raytheon Company
Inventor： Frederick B. Koehler , Jeremy C. Danforth , Ward D. Lyman , Mark T. Langhenry , Matt H. Summers , Paul E. Pontius , Brian M. Pape , Jared D. Stallings , James K. Villarreal , Thomas Villarreal
IPC: B64G1/40 , F02K9/24 , F02K9/95 , B33Y80/00 , B64G1/26 , F02K9/80 , B64G1/10 , F02K99/00 , F02K9/94 , B33Y70/00
Abstract: A satellite has thrusters that are integral parts of its frame. The frame defines cavities therein where thrusters are located. The thrusters may include an electrically-operated propellant and electrodes to activate combustion in the electrically-operated propellant. The frame may be additively manufactured, and the propellant and/or the electrodes may also be additively manufactured, with the frame and the propellant and/or the electrodes also being manufactured in a single process. In addition the thrusters may have nozzle portions through which combustion gases exit the thrusters. The thrusters may be located at corners and/or along edges of the frame, and may be used to accomplish any of a variety of maneuvers for the satellite. The satellite may be a small satellite, such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.
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