Abstract: A detector for image recording, in particular for an optoelectronic image recording system for a spacecraft, includes a carrier substrate and an optoelectronic element arranged on the carrier substrate. At least in one end region, the carrier substrate has at least one side surface running obliquely to the longitudinal direction of the carrier substrate. An optoelectronic image recording system for a spacecraft includes a carrier plate and such a detector. A spacecraft includes such a detector and/or such an optoelectronic image recording system.

Abstract: A method for determining the position of a spacecraft in space includes receiving image data from a plurality of differently oriented optics modules, processing the received image data and computing a position, a rate of rotation and/or direction of rotation from the processed image data. The method may be carried out with the aid of at least one image processing module, a device for carrying out such a method, and a computer program for carrying out such a method on such a device.

Abstract: A method for determining the position of a satellite rotating about an axis of rotation using at least a star tracker which is aligned along an optical axis with a recorded light object field, the axis of rotation and the optical axis being at a fixed angle relative to one another and a light sensor having a sensor surface which is perpendicular to the optical axis and contains a sensor coordinate system having an arrangement of light-sensitive pixels in rows being provided.

Abstract: A method for determining the position of a spacecraft in space includes receiving image data from a plurality of differently oriented optics modules, processing the received image data and computing a position, a rate of rotation and/or direction of rotation from the processed image data. The method may be carried out with the aid of at least one image processing module, a device for carrying out such a method, and a computer program for carrying out such a method on such a device.

Abstract: A vibrator arrangement for building soil improvement includes a sluice with a silo tube and a sluice drive for moving the sluice. The sluice is adapted to receive a bulk material and to guide the bulk material into the silo tube. A feed container for feeding the bulk material to the sluice is included and a feed container drive is provided for moving the feed container between a waiting position and an abutment position at the sluice. Also, a method for transferring bulk material from a feed container into a sluice with a silo tube of a vibrator device includes moving the sluice with a sluice drive and moving the feed container filled with the bulk material a between a waiting position and an abutment position at the sluice while the sluice is moving.

Abstract: A method for determining the position of a satellite rotating about an axis of rotation using at least a star tracker which is aligned along an optical axis with a recorded light object field, the axis of rotation and the optical axis being at a fixed angle relative to one another and a light sensor having a sensor surface which is perpendicular to the optical axis and contains a sensor coordinate system having an arrangement of light-sensitive pixels in rows being provided.

Abstract: The present disclosure relates to a calibrated constellation simulator, a system and a method for calibrating and/or testing a star sensor assembled on a spacecraft. The calibrated constellation simulator comprises an optical device configured to project a defined star formation (IRF) of a star catalog onto a star sensor assembled on a spacecraft. Further, the calibrated constellation simulator comprises an alignment unit with a position and/or location reference (ARF) of the calibrated constellation simulator configured to detect a position and/or location of the calibrated constellation simulator in space, wherein the defined star formation (IRF) and the position and/or location reference (ARF) are in a first fixed calibrated rotation (QOSPS) with respect to one another. The calibrated constellation simulator improves the calibration of the star sensor as an independent calibration standard. The constellation simulator becomes a calibration standard.

Abstract: An improved applicator and a method for applying two or more components which can be mixed together. They are intended to effectively prevent unintentional and unintentional mixing of the components at the discharge orifices and any associated uncontrolled or undesirable reaction of the components with each other during downtime of the applicator.

Abstract: A method for determining the position of a spacecraft in space, includes cyclically÷ repeating steps of capturing distorted star images; processing the distorted star images to form distorted star group data; storing the distorted star group data; determining a current rotation rate by comparing the distorted star group data of two consecutive cycles; transmitting the current rotation rate to a position control system; and/or the following steps are carried out: processing the distorted star images of a current cycle to form rectified star group data; determining position information by matching the rectified star group data with star group catalog data which is carried along; transmitting the position information to the position control system. A method for determining the position of a spacecraft in space, taking into account known system parameters of an optical system, includes: coding star group catalog data with n = 3...

Abstract: A method for detecting incident laser radiation on a spacecraft, whereby incident radiation is detected separately in several discrete spectral ranges, the radiation recorded in the spectral ranges is converted into further processable electrical signals, and the signals are evaluated together. A device for detecting incident laser radiation on a spacecraft is configured to perform such a method.

Abstract: A method for detecting incident laser radiation on a spacecraft, whereby incident radiation is detected separately in several discrete spectral ranges, the radiation recorded in the spectral ranges is converted into further processable electrical signals, and the signals are evaluated together. A device for detecting incident laser radiation on a spacecraft is configured to perform such a method.

Abstract: The purpose of the invention is to provide a method and an applicator for the continuous sequential separate application of two or more viscous materials or fluids, whereby two or more adhesives can be applied continuously in one operation in a track or line in turn or alternately or sequentially and thus different adhesives can be applied in turn without intervals as a continuous track or line or as a ring thereof. A method for the continuous sequential application of two or more viscous materials or fluids, whereby control of the respective volume flows of the viscous materials or fluids is carried out so that the respective viscous materials or fluids are applied in turn.

Abstract: A detector for image recording, in particular for an optoelectronic image recording system for a spacecraft, includes a carrier substrate and an optoelectronic element arranged on the carrier substrate. At least in one end region, the carrier substrate has at least one side surface running obliquely to the longitudinal direction of the carrier substrate. An optoelectronic image recording system for a spacecraft includes a carrier plate and such a detector. A spacecraft includes such a detector and/or such an optoelectronic image recording system.

Abstract: A method is provided for producing a steel component assembly, wherein a steel component having a predetermined breaking point is provided and the predetermined breaking point of the steel component is punched through by way of a press-fit element in order to form an opening. Subsequently, the press-fit element is pressed into the opening of the steel component, and, at least in overlap with the press-fit element, a component is adhesively bonded to the steel component by an adhesive applied over an area. A friction-drilling hole is melted through the press-fit element, the steel component and the component by way of a friction-drilling element.

Abstract: A vibrator arrangement for building soil improvement includes a sluice with a silo tube and a sluice drive for moving the sluice. The sluice is adapted to receive a bulk material and to guide the bulk material into the silo tube. A feed container for feeding the bulk material to the sluice is included and a feed container drive is provided for moving the feed container between a waiting position and an abutment position at the sluice. Also, a method for transferring bulk material from a feed container into a sluice with a silo tube of a vibrator device includes moving the sluice with a sluice drive and moving the feed container filled with the bulk material a between a waiting position and an abutment position at the sluice while the sluice is moving.

Abstract: A method for detecting incident laser radiation on a spacecraft, whereby incident radiation is detected separately in several discrete spectral ranges, the radiation recorded in the spectral ranges is converted into further processable electrical signals, and the signals are evaluated together. A device for detecting incident laser radiation on a spacecraft is configured to perform such a method.

Abstract: A method for detecting incident laser radiation on a spacecraft, whereby incident radiation is detected separately in several discrete spectral ranges, the radiation recorded in the spectral ranges is converted into further processable electrical signals, and the signals are evaluated together. A device for detecting incident laser radiation on a spacecraft is configured to perform such a method.

Abstract: A material includes a transparent substrate coated with a stack of thin layers acting on infrared radiation including at least one functional layer. The stack includes a carbon-based upper protective layer within which the carbon atoms are essentially in an sp2 hybridization state and the upper protective layer is deposited above at least a part of the functional layer and exhibits a thickness of less than 1 nm.

Abstract: The present invention relates to a mixing device (1), especially for mixing solids in a mixing vessel (2), comprising a stirring element (4) having at least two helical stirrer blades (7, 8) connected to a motor-driven shaft (5), wherein the stirrer blades (7, 8) have a first portion (10), a second portion (11) and a third portion (12), every one of these portions (10, 11, 12) has a constant gradient (m1, m2, m3) of one steepness or a gradient (m1, m2, m3) which is different from the constant gradient and has a curvature, and at least one of the constant gradients (m1, m2, m3) has a steepness different from the at least one other constant gradient (m1, m2, m3), or one of the different gradients (m1, m2, m3) has a curvature that is different from the at least one other different gradient (m1, m2, m3).

Abstract: A method is provided for producing a steel component assembly, wherein a steel component having a predetermined breaking point is provided and the predetermined breaking point of the steel component is punched through by way of a press-fit element in order to form an opening. Subsequently, the press-fit element is pressed into the opening of the steel component, and, at least in overlap with the press-fit element, a component is adhesively bonded to the steel component by an adhesive applied over an area. A friction-drilling hole is melted through the press-fit element, the steel component and the component by way of a friction-drilling element.