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Institution

Saab AB

CompanyThun, Switzerland
About: Saab AB is a company organization based out in Thun, Switzerland. It is known for research contribution in the topics: Antenna (radio) & Signal. The organization has 862 authors who have published 928 publications receiving 8807 citations. The organization is also known as: Saab AB & Svenska Aeroplan AB.


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Patent
20 Dec 2005
TL;DR: In this paper, a method for manufacturing an elongate structural element and a rigid shell structure integrated with at least one elongate stiffening element is presented, which includes the steps of providing a preformed, form-stable former (16), which has a hat profile with two inwardly directed, opposing flange portions (20), covering the former with a curable composite material to form an external hat profile (24, 26) having outwardly directed flanges (26).
Abstract: Method for manufacturing an elongate structural element and a rigid shell structure integrated with at least one elongate stiffening element. The method includes the steps of providing a preformed, form-stable former (16), which has a hat profile with two inwardly directed, opposing flange portions (20), covering the former with a curable composite material to form an external hat profile (24, 26) having outwardly directed flanges (26), and integrating this assembly (16, 24, 26) with either a curable or preformed shell structure (10) of composite material.

21 citations

Patent
Andersson Ingmar1, Brege Magnus1
08 Nov 2011
TL;DR: In this article, the authors present a system and method for route planning on a moving object, which consists of 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.
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.

20 citations

Patent
Eilef Roeed Age1
28 Nov 1967
TL;DR: In this paper, the inboard half of an aircraft wing is composed of a trailing edge flap, a gas turbine engine mounted on the wing forward of the flap and the slot, a lower flap 23 movable (e.g. about axis 23) in dependence on the movement of the flaps, and an upper flap 25 movable from a position A where it forms a smooth continuation of the wing contour, and a position D at an acute angle with the upper surface of the aircraft.
Abstract: 1,212,705. Propulsion jet deflection by blown flaps. SAAB A.B. 28 Nov., 1967 [29 Nov., 1966], No. 54071/67. Heading B7G. [Also in Division F2] An aircraft wing 2 comprises a trailing edge flap 9 pivotable about an axis 13 below the wing from a first position A where it forms a smooth continuation of the wing to a second position D where it forms an acute angle with the undersurface of the wing, a slot 21 between the forward edge of the flap and the main body of the wing, a gas turbine engine 5 mounted on the wing forward of the flap and the slot, a lower flap 23 movable (e.g. about axis 23) in dependence on the movement of the flap 9 (e.g. via a link 24 between a first position where it closes the slot to a second position corresponding to position D of the flap 9 where exhaust air flow from the engine 5 is deflected upwardly through the slot, an upper flap 25 movable from a position A where it forms a smooth continuation of the wing contour, and a position D at an acute angle with the upper surface of the wing, and control means 18 to co-ordinate the flap movements. The above arrangement may comprise the inboard halves of the wings, the outboard halves comprising further trailing edge flaps 7, upper flaps 8 and also leading edge flaps 6 which when extended provide further slots 6a and 6b through the wing. These flaps together with the undercarriage 30 may have their movements also controlled by the pilot's control means 18. All flap and undercarriage movement may be provided by hydraulic actuators 16, 26, 31, 32, 33 and 34. The lower end of the forward wall of the passage 21 may be rounded, and the flap 23 may itself be slotted. When the trailing edge flaps 7, 9, lower flaps 23 and leading edge flaps 6 are moved to the positions B, the left of the wing is increased due to increased camber and boundary layer control provided by air passing through the slots 6a, 6b, 12 and 21.

20 citations

Journal ArticleDOI
TL;DR: The design of combat aircraft with high military effectiveness, affordability and military suitability requires balancing the efforts of many engineering disciplines during all phases of the developmen ...

20 citations

Journal ArticleDOI
TL;DR: The use of an optical fiber as a real-time distributed microphone is demonstrated employing a phase-OTDR with direct detection of a sinusoidal disturbance through a 300 m long optical fiber.
Abstract: The use of an optical fiber as a real-time distributed microphone is demonstrated employing a phase-OTDR with direct detection. The method comprises a sample-and-hold circuit capable of both tuning the receiver to an arbitrary section of the fiber considered of interest and to recover in real-time the detected acoustic wave. The system allows listening to the sound of a sinusoidal disturbance with variable frequency, music and human voice with ~60 cm of spatial resolution through a 300 m long optical fiber.

20 citations


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Performance
Metrics
No. of papers from the Institution in previous years
YearPapers
20231
20222
202120
202029
201942
201828