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公开(公告)号：US20220214039A1
公开(公告)日：2022-07-07
申请号：US17603694
申请日：2020-04-14
Applicant: SAAB AB
Inventor： Daniel NILSSON
Abstract: Provided is a heat generating arrangement and a method for generation of heat to be used in a heat consumer. The heat generating arrangement uses combustion of aluminium and hydrogen to raise the temperature of superheated steam inside the heat generating arrangement. The heat in the superheated steam can thereafter be used in a heat consumer, such as a heat exchanger.
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公开(公告)号：US11008099B2
公开(公告)日：2021-05-18
申请号：US16301282
申请日：2017-05-05
Applicant: SAAB AB
Inventor： Christer Zaetterqvist
IPC: B64D1/02 , F41H11/02 , F42B5/15 , F41F7/00 , F41F1/08 , F42B12/70 , F41A17/08 , F41A27/08 , F41A27/00 , B64D7/00
Abstract: Firing direction limitation device (15) for controlling the allowed launch angle range of a directable firing device (10) tiltable between at least two allowed maximum launch angles (MaxLA1, MaxLA2) defining a launch sector (4), wherein the firing direction limitation device (15) comprises a moveable limiting structure (16) configured to be arranged in connection to the directable firing device (10), where the limiting structure (16) is configured to be moveable between a first position (P1) and a second position (P2), wherein, when the limiting structure (16) is set in the first positon (P1), the directable firing device (10) is moveable within a first launch angle range (LARa1), and when the limiting structure (16) is set in the second positon (P2), the directable firing device (10) is moveable within a second launch angle range (LARa2), wherein the second launch angle range (LARa2) is limited in relation to the first launch angle range (LARa1), whereby the allowed launch angle of the directable firing device (10) is controllable.
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公开(公告)号：US10982970B2
公开(公告)日：2021-04-20
申请号：US16315209
申请日：2016-07-07
Applicant: SAAB AB
Inventor： Nigel Pippard , Robert Alexander Bennett , Jonas Dehlin , Adam Nilsson
Abstract: The present disclosure relates to a method (300) for displaying a perspective view of the surrounding of an aircraft (100) in an aircraft. The method comprises accessing (310) surrounding information from a database. The surrounding information is photo-based and three-dimensional. The method further comprises processing (320) the accessed surrounding information so that a perspective view of the surrounding of the aircraft is provided. The perspective view of the surrounding correlates to the position of the aircraft and is photo-based with spatially correlated photo-based textures. The method further comprises transmitting (360) the provided perspective view of the surrounding of the aircraft to a displaying unit so that it can be displayed in the aircraft. The present disclosure also relates to a system, an aircraft, a use, a computer program, and a computer program product.
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公开(公告)号：US10714807B2
公开(公告)日：2020-07-14
申请号：US16461838
申请日：2017-09-06
Applicant: SAAB AB
Inventor： Martin Blennius
Abstract: A stabilization arrangement (10) for stabilizing an antenna mast (3), comprising an antenna mast (3) and a gyroscopic stabilizer device (12), wherein the gyroscopic stabilizer device (12) in turn comprises a flywheel (11), a flywheel axis (14), wherein the flywheel (11) is arranged about the flywheel axis (14), and a gimbal structure (13), wherein the flywheel (11) is suspended in the gimbal structure (13) and the gimbal structure (13) is configured to permit flywheel precession or tilting about at least one gimbal output axis (16). The gyroscopic stabilizer device (12) is fixedly arranged in connection to a first end portion (31) of the antenna mast (3) and the antenna mast (3) is fastenable to a supporting structure at a second end portion (32) of the antenna mast (3), wherein the gyroscopic stabilizer device (12) is configured to reduce movements in a plane perpendicular to the extension of the antenna mast (3).
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公开(公告)号：US10705200B2
公开(公告)日：2020-07-07
申请号：US16092405
申请日：2016-04-20
Applicant: SAAB AB
Inventor： Lars Sundell , Per Wall , Bengt Svensson
Abstract: An antenna system for providing identification functionality comprising a main antenna and an auxiliary antenna, wherein the antennas are configured to at least transmit electromagnetic waves. The antenna system comprises a first channel interface and a second channel interface, a first switch and a transmission input means. The first switch is configured to switch between a first operation mode and a second operation mode. When set in the first operation mode the second channel interface is set to be in connection with the auxiliary antenna and when set in the second operation mode the second channel interface is set to be in connection with the main antenna. If transmission via the first transmission channel is expected the transmission input means is configured to set the first switch in the first operation mode. Thereby the main antenna can be used for transmission of signals both provided via the first and second channel interfaces and when transmission via the first and second channel interfaces simultaneously is required the signal provided via the first channel interface will be transmitted by the main antenna and the signal provided via the second channel interface will be transmitted by the auxiliary antenna.
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Patent Agency Ranking
公开(公告)号：US10533585B2
公开(公告)日：2020-01-14
申请号：US15775941
申请日：2015-11-16
Applicant: SAAB AB
Inventor： Magnus Landberg
Abstract: A method for operating a telescopic device and the elongated telescopic device per se comprises a support element formed to encompass first and second telescopic element mounted so as to be telescopically slidable relative each other in a longitudinal direction; the support element comprises a support element fluid actuator assembly; the first telescopic element is arranged to encompass the second telescopic element and comprises a first fluid actuator assembly. The support element fluid actuator assembly is fixed to an interior portion of the support element and is arranged for engagement or disengagement to a first envelope surface of the first telescopic element and wherein the first fluid actuator assembly is fixed to a first interior portion of the first telescopic element and is arranged for engagement or disengagement to a second envelope surface of the second telescopic element.
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公开(公告)号：US20190337149A1
公开(公告)日：2019-11-07
申请号：US16349872
申请日：2016-11-17
Applicant: SAAB AB
Inventor： Magnus LANDBERG
Abstract: The present invention regards a fluid actuator arrangement comprising a first cylinder housing comprising a first piston body comprising a first through-bore and a first clamping element provided for releasable clamping onto a first piston rod. The first piston body comprises a second through-bore and a second clamping element provided for releasable clamping onto a second piston rod; a first static holding unit comprising a first clamping unit provided for releasable clamping onto the first piston rod; a second clamping unit provided for releasable clamping onto the second piston rod; a first base member coupled to the first piston rod via a first universal joint for providing a rotational motion of the first base member during longitudinal motion of the first piston rod. The present invention also regards a method for providing a rotational motion of a first base member.
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公开(公告)号：US20190193857A1
公开(公告)日：2019-06-27
申请号：US16301305
申请日：2017-05-05
Applicant: SAAB AB
Inventor： Christer ZÄTTERQVIST
Abstract: A magazine for storing and launching countermeasures arranged in cartridges, comprising a plurality of longitudinal cartridge cases forming the magazine, where each cartridge case comprises side walls and a front opening and a centre axis, where the magazine is adapted to be mounted on an aircraft, where the side walls of two adjacent cartridge cases are arranged to each other in a slidable manner in a longitudinal direction, and where the magazine comprises a tilting means adapted to tilt the cartridge cases, such that the openings of the cartridge cases can be directed in a selected direction. The advantage of the invention is that a countermeasure can be directed in a desired angle before it is launched.
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公开(公告)号：US10288438B2
公开(公告)日：2019-05-14
申请号：US14993876
申请日：2016-01-12
Applicant: SAAB AB
Inventor： Ingmar Andersson , Magnus Brege
IPC: G01C21/34
Abstract: The present invention relates to a system and method for route planning. The system is arranged to be mounted on a moving object. The system comprises a route planning module arranged to plan a route of the object upon request, wherein occasions of being visible from any point in the map within a shooting range during a predetermined time period is minimized. The system is characterized in that the route planning module is arranged to determine areas in the 3D map in which the object will be exposed to a potential threat during a predetermined time period based on line of sight calculations, and determining a re-planned route avoiding said potential threat areas.
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公开(公告)号：US10260964B2
公开(公告)日：2019-04-16
申请号：US15322369
申请日：2014-06-25
Applicant: SAAB AB
Inventor： Fredrik Fisk , Bjorn-Erik Andersson
Abstract: The present disclosure relates to an optical fiber sensor system (10) arranged to detect a temperature change in a zone (2, 3, 4) in an aircraft (1) having at least one zone (2, 3, 4). The optical fiber sensor system (10) comprises at least one optical fiber (11, 21, 31, 41) comprising a plurality of Fiber Bragg Gratings (20, 30, 40) for detecting a temperature change. Each of the Fiber Bragg Gratings (20, 30, 40) is reflecting radiation within a predetermined wavelength range. A radiation source unit (13) is arranged to emit radiation into the at least one optical fiber (11, 21, 31, 41). A radiation detector unit (14) is arranged to receive radiation from the at least one optical fiber (11, 21, 31, 41). A processing unit (15) is configured to identify a spectral response (22, 32, 42) of the received radiation and to determine a temperature change from the spectral response (22, 32, 42) of the received radiation in a predetermined wavelength range. Each of the at least one zone (2, 3, 4) solely has Fiber Bragg Gratings (20, 30, 40) which are reflecting radiation within the same predetermined wavelength range. The disclosure further relates to method for detecting a temperature change in a zone in an aircraft having at least one zone, by means of the optical fiber sensor system. Yet further the disclosure relates to an aircraft (1) comprising the optical fiber sensor system (10).
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