Saab AB

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

Explicit modelling of multiple intervals in a constraint generation procedure for multiprocessor scheduling

Abstract: Multiprocessor scheduling is a well studied NP-hard optimisation problem that occurs in variety of forms. The focus of this paper is explicit modelling of multiple task intervals. This work extends a constraint generation procedure previously developed for an avionics scheduling context. We here address a relaxation of the original problem and this relaxation can be considered as multiprocessor scheduling with precedence relations and multiple intervals. The explicit modelling of multiple intervals strengthens the formulation used in the constraint generation procedure and we illustrate the computational effects on an industrial relevant avionics scheduling problem.

Display device and display method

Abstract: The invention concerns a device for displaying an image directly on the retina (6) of the eye (5). The device comprises means (1) arranged to emit laser radiation and modulating means (2) arranged in the beam path between the laser-radiation-emitting means (1) and the eye (5) so as to modulate the laser radiation. The device is characterized in that the modulating means (2) are arranged so as to modulate the phase front of the laser beam so that, when it strikes the refracting elements of the eye, it is deflected in a direction distinct from the direction obtained with unmodulated radiation. The invention also includes a method of displaying a retinal image.

Range control of a rocket-propelled projectile

Abstract: The invention relates to a method and an arrangement for controlling the range of a projectile propelled by a rocket motor. An actual value of a quantity clearly correlating with the distance covered by the projectile is continuously determined during the propulsion. The actual value thus determined is continuously compared with a predefined set-point value, which for the projectile in question corresponds to a predetermined range. When the actual value has been found to be at least equal to the set-point value the propulsion capability of the rocket motor is instantaneously terminated. The arrangement according to the invention comprises a calculation element arranged outside the projectile and preferably stationary, which is designed on the basis of a predetermined range and using known mechanical correlations to calculate a set-point quantity corresponding to the predetermined range. Located on board the projectile are a memory element designed to store the set-point value transmitted from the calculation element, an element measuring the acceleration of the projectile after firing, a second calculation element connected to the acceleration measuring element and designed to continuously calculate an actual range value from the acceleration, a comparing element designed to continuously compare the range set-point quantity with the actual range value and to terminate the propulsion capability of the rocket motor instantaneously when the actual value is at least equal to the set-point value.

Cooling device for cooling combustion gases from recoilless anti-tank weapons

Abstract: The present invention relates to a cooling device (2) for cooling combustion gases from a rocket motor (1) in an antitank weapon. The cooling device (2) comprises a coolant reservoir (3, 21) containing a coolant (4). The coolant reservoir (3, 21) is arranged such that the coolant (4) is transferred from the coolant reservoir (3, 21) to the combustion gases in the gas outlets (6) of the rocket motor (1) in response to a pressure increase in the rocket motor (1). The coolant reservoir (3, 21) constitutes an integral part of the rocket motor (1) and is connected to the combustion chamber (7) by at least two gas inlets (8) for pressurization of the coolant (4). The coolant reservoir is furthermore connected to the rocket motor nozzle (9) by at least two coolant outlets (10) for transfer of coolant (4) from the coolant reservoir (3, 21) to the rocket motor nozzle (9).

A method for variable control of a zone sensor in a combat aircraft

Abstract: The invention relates to a method for controlling a sensor in a combat aircraft (1) comprising the steps of: a) determining (3) direction and size of a defence zone around the combat aircraft (1) based on a plurality of characteristic parameters of an enemy combat aircraft (2), b) determining (4) direction and size of at least one offence zone around the combat aircraft (1) based on the plurality of characteristic parameters of the enemy combat aircraft (2), and c) controlling (5) the sensor in the combat aircraft (1) according to emission level and detection capacity within at least one of the defence zone and the at least one offence zone. In this way, the sensors are controlled reliably and thus the pilot can act and react mission-oriented.