公开(公告)号：US20190341670A1

公开(公告)日：2019-11-07

申请号：US16461838

申请日：2017-09-06

Applicant: SAAB AB

Inventor： Martin BLENNIUS

IPC: H01Q1/12 ,  H01Q1/18

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).

公开(公告)号：US20190339518A1

公开(公告)日：2019-11-07

申请号：US16461855

申请日：2016-11-25

Applicant: SAAB AB

Inventor： Johan ZANDÉN ,  Anna-Karin HOLMER ,  Stefan ANDERSSON

IPC: G02B27/01 ,  G02B3/08 ,  B64D45/00

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).

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

IPC: B25J9/14 ,  B25J9/10 ,  F15B11/036 ,  F15B15/04 ,  F15B15/14 ,  F15B15/26 ,  F15B15/06

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.

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

IPC: B64D7/06 ,  F41A17/38

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.

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.

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

IPC: G01K11/00 ,  G01J5/00 ,  G01K3/00 ,  G01K1/00 ,  G01K13/00 ,  G01K11/32

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).

公开(公告)号：US20190092469A1

公开(公告)日：2019-03-28

申请号：US16301572

申请日：2017-05-05

Applicant: SAAB AB

Inventor： Christer ZAETTERQVIST

IPC: B64D1/02 ,  B64D7/00 ,  F41F1/08 ,  F41F7/00 ,  F41H11/02

Abstract: A dispenser for storing and launching countermeasures from an aircraft, comprising an elongate body provided with at least one launch opening where the countermeasures are stored in cartridges, where the cartridges are interconnect to each other in a slidable manner, and where the cartridges are adapted to be tilted by a tilting means to a selected angle, such that the openings of the cartridges 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.

公开(公告)号：US10131415B2

公开(公告)日：2018-11-20

申请号：US14646028

申请日：2012-11-20

Applicant: SAAB AB

Inventor： Pontus Nordin ,  Göte Strindberg

IPC: B64C1/06 ,  B64C3/28 ,  B64C1/12 ,  B64D45/00

Abstract: An airframe leading edge part designed to be replaceable fixed to a structural portion which during use moves through the air. The airframe leading edge part includes first and second longitudinal joint edges adapted to fit the structural portion. At least one joint is provided between the structural portion and at least one of the longitudinal joint edges. The joint is adapted to break in the event of a object strikes and deforms the airframe leading edge part during use. The joint is designed to break at beforehand determined maximum joint strength of the joint. Also a repair method for exchanging a damaged leading edge.

公开(公告)号：US09583841B2

公开(公告)日：2017-02-28

申请号：US15100844

申请日：2013-12-19

Applicant: SAAB AB

Inventor： Ola Forslund ,  Henrik Holter ,  Andreas Wikstroem

IPC: H01P5/10 ,  H03H7/42 ,  H01Q21/00 ,  H01Q21/06 ,  H01Q21/24 ,  H01Q1/50 ,  H05K1/02 ,  H05K1/16

CPC classification number: H01Q21/0006 ,  H01P5/10 ,  H01Q1/50 ,  H01Q21/061 ,  H01Q21/24 ,  H03H7/422 ,  H05K1/0298 ,  H05K1/16

Abstract: The present disclosure relates to a balun suitable for realizing a wideband transition in the radio frequency band from an unbalanced transmission line to a balanced transmission line. The balun comprises an input terminal; a two conductor output terminal; and a layered structure comprising a number of conducting layers and dielectric layers alternatingly arranged on top of each other. The layered structure comprises at least one ground plane layer and at least one signal transmission layer. The input terminal has a signal connection point and a screen connecting point. An unbalanced signal path is connected to the signal connection point and the screen connecting point of the input terminal. A balanced signal path is connected to the output terminal and being part of the layered structure. A balun transition region transforms the signal from an unbalanced signal to a balanced signal. The balun transition region comprises a non-conducting gap between the screen of the unbalanced signal and a dummy screen structure. The dummy screen structure is a mirror structure, mirrored in a plane of the gap, of a horizontal portion of the unbalanced signal path before the gap. A central conductor or signal conductor of the unbalanced signal path traverses the gap and enters a volume defined by the dummy screen structure. The screen of the unbalanced signal in the vicinity of the gap forms a first balanced conductor being part of the layered structure and the screen of the dummy screen structure, in vicinity of the gap, forms a second balanced conductor being part of the layered structure.

Abstract translation: 本公开涉及适用于实现从不平衡传输线到平衡传输线的无线电频带中的宽带转变的平衡 - 不平衡变压器。 平衡 - 不平衡转换器包括输入端子; 一个双线输出端子; 以及包括交替布置在彼此顶部的多个导电层和电介质层的分层结构。 分层结构包括至少一个接地层和至少一个信号传输层。 输入端子具有信号连接点和屏幕连接点。 不平衡信号路径连接到信号连接点和输入端子的屏幕连接点。 平衡信号路径连接到输出端并且是分层结构的一部分。 平衡不平衡转换转换区域将信号从不平衡信号转换为平衡信号。 平衡 - 不平衡变压器过渡区域包括不平衡信号的屏幕与虚拟屏幕结构之间的非导通间隙。 虚拟屏幕结构是在间隙之前的不平衡信号路径的水平部分的间隙的平面中的镜像结构。 不平衡信号路径的中心导体或信号导体穿过间隙并进入由虚拟屏幕结构限定的体积。 在间隙附近的不平衡信号的屏幕形成作为层状结构的一部分的第一平衡导体，并且在间隙附近的虚拟屏幕结构的屏幕形成作为层状结构的一部分的第二平衡导体。

公开(公告)号：US20160363427A1

公开(公告)日：2016-12-15

申请号：US15120894

申请日：2014-02-26

Applicant: SAAB AB

Inventor： Johan ÖSTLUND ,  Karl EDSTROM ,  Svante PERSSON

IPC: F42C19/02 ,  F42B33/02 ,  F42C11/00 ,  F42C19/08 ,  F42B1/028

CPC classification number: F42C19/02 ,  F42B1/028 ,  F42B33/0207 ,  F42B33/025 ,  F42C11/00 ,  F42C19/08 ,  F42C19/0803 ,  F42C19/0807

Abstract: An initiating device including at least one detonator, at least one booster charge and an action charge. The at least one booster charge is arranged such that, at the action charge initiates, the booster charge is free from disturbing edge effects that can have a disturbing effect on the action charge. A booster casing in which the booster charge is disposed is configured with a rear cylindrical part having a diameter D1, a front conical part delimited by a first circular limit face having the diameter D1, and a second circular limit face having a diameter D2, wherein the two limit faces are plane-parallel at a distance H1 from each other, wherein H1/D2 lies within a range 0.5-1.5. Also, a production method for producing the booster charge.

Abstract translation: 一种起动装置，包括至少一个雷管，至少一个增压器充电和动作电荷。 所述至少一个升压器充电被设置成使得在动作充电开始时，所述升压器电荷不受干扰的影响，所述边缘效应可能对动作电荷产生干扰。 其中设置有增压器的增压器外壳配置有具有直径D1的后圆柱形部分，由具有直径D1的第一圆形极限面限定的前锥形部分和具有直径D2的第二圆形极限面，其中 两个极限面在距离H1处彼此平行平行，其中H1 / D2在0.5-1.5的范围内。 而且，也是用于制造增压装置的制造方法。