公开(公告)号：US20210286175A1

公开(公告)日：2021-09-16

申请号：US16332454

申请日：2016-09-16

Applicant: SAAB AB

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

IPC: G02B27/01 ,  G02B6/08

Abstract: The present disclosure relates to a head up or head mounted display arrangement and a method for presenting at least one image via at least one surface element of a head up or head mounted display arrangement. The arrangement comprises at least one image generating element (301, 302) arranged to generate an image in a first image plane (346′, 346″), at least one surface element, and a fibre optic face plate (340).The face plate is arranged in relation to the at least one image generating element such that the first surface lies at a first image plane. A second image plane lies at the second surface and the at least one surface element is arranged in the beam path from the second surface. The first image plane comprises a plurality of first part image planes each associated with an individual first part surface of the fibre optic face plate and/or the second image plane comprises a plurality of second part image planes each associated with an individual second part surface of the fibre optic face plate.

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：US20220324587A1

公开(公告)日：2022-10-13

申请号：US17620431

申请日：2020-06-17

Applicant: SAAB AB

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

IPC: B64F1/20 ,  G08G5/00 ,  G08G5/02

Abstract: The present disclosure relates to a landing assistance system and method (100) for assisting an airborne vehicle (1) during landing on a landing area (2). The landing assistance system (100) provides the airborne vehicle (1) with light signals. The landing assistance system comprises at least one geographically positioned light emitter (4, 6, 8) arranged at near ground level on the landing area (2). At least one first light emitter (6) of the at least one geographically positioned light emitter (4, 6, 8) is arranged to emit light to a designated position in space. The light comprises at least three light beams (B1-B3), wherein a first beam (B1) being a central beam, which indicates a designated glideslope, and at least a second beam (B2) and third beam (B3) indicating that said airborne vehicle (1) is positioned under or above the designated glideslope, respectively.

公开(公告)号：US20220026177A1

公开(公告)日：2022-01-27

申请号：US17309547

申请日：2018-12-13

Applicant: SAAB AB

Inventor： Per CEDERWALL ,  Stefan ANDERSSON

IPC: F41G3/26 ,  G01S13/75 ,  G01S17/02 ,  F41J2/00

Abstract: The invention relates to a reflector comprising a reflector cavity (110) having a front opening for receiving EMR into the reflector cavity (110) for subsequent reflection of the EMR by at least one reflector element (120) arranged within the reflector cavity (110), characterized in that the reflector further comprises a front cover (130) that has high EM R transmittance in at least parts of the EM spectrum, the front cover (130) being arranged to cover the front opening of the reflector cavity (110), and that the front cover (130) and front opening form a gastight seal (140) impermeable to gas to prevent transport of material into and out of the reflector cavity (110) through the front opening.