Abstract:
The present invention regards a fluid actuator arrangement comprising a first and second cylinder of a cylinder arrangement, a piston rod arrangement, a first and second piston device associated with the piston rod arrangement, wherein respective first and second piston device divides respective first and second cylinder into a first and second chamber provided for connection to a valve device of a fluid supply device. The first piston device comprises a piston rod engagement and disengagement device, which is adapted to engage or disengage the first piston device to/from the piston rod arrangement. The invention can be put into use for aircraft, such as commercial aircraft designed for long distance flights, for construction industry, jacking systems for oil well drilling and service platforms, agricultural equipment industry, marine industry, crane manufacture industry, and others.
Abstract:
A container for packaging and storing ammunition units in tubes. A unit cargo includes such containers. A method for packaging and storing such containers. T-shaped detonation protections are introduced to separate adjacent tubes in order to prevent mass detonation.
Abstract:
A weapon including a barrel or barrel replica. A recoil generator arrangement is configured to generate a recoil or hammer cocking. The recoil generator arrangement includes a cylinder, a piston movably arranged in the cylinder and an oblong element arranged on the piston. The cylinder is removably attachable on a front end of the weapon so that the oblong element extends from the front end through the barrel or barrel replica to an element inside the weapon and moves the element when the piston is moved.
Abstract:
A system for monitoring movements of rotor blades attached by flapping hinges to a central head or hub of a helicopter. At least one sensor is arranged to continuously measure vertical angular movement of a rotor blade and/or the flapping hinge. Also a method for monitoring movements of rotor blades attached by flapping hinges to a central head or hub of a helicopter.
Abstract:
An antenna frame for reducing radar cross section of a vehicle provided with a flat microstrip patch antenna array comprising a number of microstrip patches arranged in an array pattern, the antenna frame: —being arranged to surround the outer periphery of the flat antenna array —the frame comprising a first conductive sheet; —the first conductive sheet extending from the most peripheral patches and outward in a sloping manner; wherein dielectric and magnetic absorbent material are arranged to improve impedance transition from a point of the antenna to a point on the periphery of the frame, which is also contemplated as adjoining a vehicle fuselage.
Abstract:
A head-up display system for a vehicle facilitating the use of night vision goggles for a person in the vehicle during night vision conditions, the system comprising a light source for providing light to an image source, which image source is arranged to project an image on a semi-transparent combiner mirror; the combiner mirror being arranged to superimpose the projected image onto a view of the environment in front of the vehicle by transmitting light rays from the environment and at the same time reflecting the projected image towards the eyes of an observer wherein the system comprises a first and a second light source for alternatively providing light to the image source; the first light source being arranged to emit light of a first colour to be used during daylight conditions, and the second light source being arranged to emit light of a second colour to be used during night vision conditions, wherein the first colour is in a first light emission spectrum and perceived as green and the second colour is in a second emission spectrum and perceived as yellow or orange.
Abstract:
A method for calculating a Time To Go value between a vehicle and an intruding object. First and second images of the object are retrieved at first and second points of time. A scaling factor is selected and the second image scaled with the scale factor. The scaled image is resampled to a set position. Correlation values are calculated between the first image and the resampled scaled image for different horizontal displacements and/or different vertical displacements for the resampled scaled image. A maximum correlation value is found based on the correlation values. Selecting the scaling factor, resampling, calculating the correlation values, and finding the maximum correlation values are repeated a second predetermined number of times. A largest maximum correlation value is found among the maximum correlation values and the scale factor associated with the largest maximum correlation value. The Time To Go is calculated based on the associated scale factor.
Abstract translation:一种用于计算车辆和入侵物体之间的“到达时间”值的方法。 在第一和第二时间点检索对象的第一和第二图像。 选择缩放因子,第二个图像用比例因子缩放。 缩放图像被重新采样到设置位置。 对于不同的水平位移和/或重采样的缩放图像的不同垂直位移,在第一图像和重采样的缩放图像之间计算相关值。 基于相关值找到最大相关值。 选择缩放因子,重采样,计算相关值和找到最大相关值重复第二预定次数。 在最大相关值和与最大最大相关值相关联的比例因子之间找到最大最大相关值。 Time to Go是根据相关的比例因子计算的。
Abstract:
The invention pertains to display method, a computer program for performing the steps of the display method and a display system (1), the display system having for example: at least one display unit (13, 16) arranged to present at least one display image, at least one memory unit (12, 15) comprising information related to for example descriptions of a set of default graphics display objects (W1-W3) and configuration data. The configuration data is arranged to define: at least one transparent display layer (L1-L3), at least one transparent display container (CO0-CO2) associated to the at least one transparent display layer and at least one display mode. Each of said at least one display mode comprising a predetermined selection of one or more of said at least one transparent display container of one or more of said at least one display layer.
Abstract:
A method of manufacture of a composite aircraft article aerodynamic surface by forming the composite aircraft article aerodynamic surface on an aircraft article composite forming tool. The aircraft article composite forming tool includes a matrix laminate including an upper ply including a forming surface for forming the composite aircraft article aerodynamic surface. The upper ply of the aircraft article composite forming tool includes a nano filament structure embedded therein. A blank is conformed onto the aircraft article composite forming tool. The aircraft article is formed on the upper ply of the forming surface. The forming surface of the aircraft article composite forming tool is adapted to form an aerodynamic surface of the aircraft article. The blank is cured into the aircraft article. The composite aircraft article is finished.
Abstract:
For adjustment of the direction of its thrust vector, an ejection seat rocket motor is mounted on the ejectable frame element for bodily angular motion, or has an adjustable gas deflector. The seat element, heightwise adjustable on the frame element, has a motion transmitting connection with the rocket motor whereby the thrust vector is maintained in desired relation to the center of gravity of the seat/occupant mass in every position of seat adjustment. At high speeds an airspeed responsive member transiently engages, during ejection, a sensing member associated with said connection, modifying the thrust vector adjustment.