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: A method for initializing a tracking algorithm for target objects, includes generating a 3D point cloud of the target object and iteratively determining a spatial position and orientation of the target object using a 3D model. A spatial position and orientation of the target object is first determined using an artificial neural network, thereafter the tracking algorithm is initialized with a result of this determination. A method for training an artificial neural network for initializing a tracking algorithm for target objects includes generating a 3D point cloud of the target object by a scanning method, and iteratively determining a spatial position and orientation of the using a 3D model of the target object. The artificial neural network is trained using training data to initially determine a spatial position and orientation of the target object and thereafter initialize the tracking algorithm with a result of this initial determination.

Abstract: A 3D scene is acquired using a LIDAR system including a transmitter, a receiver, and a pivotable mirror arrangement between the transmitter and the 3D scene. The transmitter is operated as a laser light source and the receiver is configured as a matrix sensor with an irradiation optical system and light sensors distributed over a surface. Light points reflected in a spatially resolved manner at pixels of a point cloud of the 3D scene are generated by light pulses of the transmitter and by pivoting the mirror arrangement. An input signal is acquired from each of the light points by the light sensors and a distance of the light points to the matrix sensor is determined based on a light propagation time measurement. A defocused input signal of a light point including a plurality of light sensors is displayed by the irradiation optical system and the input signals are compared.

Abstract: A method for detecting and autonomously tracking a target object using a LIDAR sensor that continuously emits laser pulses onto the target object and generates a 3-D point cloud from measurement points reflected by the target objects at predetermined time intervals. A current relative position of the target object is calculated for six degrees of freedom of movement of the target object at the predetermined time intervals based on algorithms estimating the position. The method includes acquiring a high-resolution initializing point cloud over a plurality of predetermined time intervals, generating a reference model with a small number of measurement points from the initializing point cloud, and, in subsequent iterative steps, determining temporal position clouds and comparing the position clouds with the reference model using the algorithms. Position information of the target object is calculated, wherein the reference model is continuously adapted to the changes in the point clouds.

Abstract: A method for increasing the reliability of sensor systems for determining the position of flying objects. Since the position determination is very decisive for the execution of planned missions, it is especially important to increase the reliability of such systems. The star sensors of the star systems are preferably structured identically and connected to each other by a bidirectional bus system. Due to the presence of several identical modules in the sensor system, there is an inner redundancy that can be utilized via the bus system. The bus system allows the transmission of signals of different data processing levels, so that the transmission of the data of the data processing levels can be adapted to modules that may have failed.

Abstract: A hybrid network of kinematic sensors of an AOCS, made up of a star sensor including an optical camera head, and a processing unit provided as the central master processing unit, and additional kinematic sensors, each made up of a sensor element and a processing unit connected to the central processing unit via a first bus. An additional processing unit is equivalent to the processing unit and is a redundant central processing unit. The central processing units and—are connected via an additional bus of a spacecraft provided with the hybrid network with the aid of a central computer. The particular active central processing units-provide all kinematic sensors with a uniform time pulse via a synchronization line, and supply the central computer with hybridized kinematic measuring data formed according to a method for hybridization based on the synchronous kinematic measuring data of the star sensor and the measuring data of the other sensors.

Abstract: A method and an apparatus for air-borne or space-borne radiometric measurement of object points present in an object scene on the surface of a astronomical body. A corrected recording of image points in an image plane in which object points from the object scene are imaged on a detector, is carried out by determining recording errors of the detector caused by systematically occurring spatial and temporal changes in a scanning movement of the detector, with reference to a measurement line relative to a recording field, then generally an actuation function along the measurement line in the form of different trigger times in which measurements of the individual object points are initiated exactly at that time. Based on the triggering of the detector elements due to the actuation function synchronized measurements of all of the object points of every row of an object matrix are carrying out along the designated measurement line.

Abstract: The invention is directed to a method and an apparatus for air-borne or space-borne radiometric measurement of object points present in an object scene on the surface of an astronomical body which are assigned to rows and columns of an object matrix during a scanning progressing systematically in a first scanning direction and a second scanning direction, wherein the object matrix points are imaged on a detector in an image plane generated by optics, and the image inside the image plane is recorded by at least one radiation-sensitive detector element of the detector.

Abstract: A camera (1), in particular in a space vehicle, having a housing (2) which contains at least one optically sensitive exposure surface (7), and a base lens (9), having a first fixed focal length, connected thereto in each case, and which projects on the at least one exposure surface (7) and which is situated on a first optical axis (10) for the exposure surface (7). To provide the camera with various fields of view, in particular for the approach of two satellites toward one another over large distances, at least two afocal supplementary lenses (11, 12) which are each parallel with respect to their optical axes (15, 16) and spaced at a distance from the first optical axis (10) are situated in the housing (2), whose optical paths are alternately coupleable with the aid of a pivotable prism (17), to form further fixed focal lengths in an optical path of the base lens (9).

Abstract: A method for increasing the reliability of sensor systems for determining the position of flying objects. Since the position determination is very decisive for the execution of planned missions, it is especially important to increase the reliability of such systems. The star sensors of the star systems are preferably structured identically and connected to each other by a bidirectional bus system. Due to the presence of several identical modules in the sensor system, there is an inner redundancy that can be utilized via the bus system. The bus system allows the transmission of signals of different data processing levels, so that the transmission of the data of the data processing levels can be adapted to modules that may have failed.

Abstract: A camera (1), in particular in a space vehicle, having a housing (2) which contains at least one optically sensitive exposure surface (7), and a base lens (9), having a first fixed focal length, connected thereto in each case, and which projects on the at least one exposure surface (7) and which is situated on a first optical axis (10) for the exposure surface (7). To provide the camera with various fields of view, in particular for the approach of two satellites toward one another over large distances, at least two afocal supplementary lenses (11, 12) which are each parallel with respect to their optical axes (15, 16) and spaced at a distance from the first optical axis (10) are situated in the housing (2), whose optical paths are alternately coupleable with the aid of a pivotable prism (17), to form further fixed focal lengths in an optical path of the base lens (9).

Abstract: A Schiefspiegler telescope with three reflecting surfaces, preferably for observing the earth from space, particularly for imaging radiometers. A novel possibility for realizing a reflector telescope without vignetting which permits a simple construction and a simple adjustment of the reflecting surfaces relative to one another. In a Schiefspiegler telescope with three reflecting surfaces whose mirror axes are arranged within a plane, the primary reflecting surface and tertiary reflecting surface are convex surfaces of identical shape arranged symmetrically with respect to an axis of symmetry. The secondary reflecting surface is arranged symmetric to the primary reflecting surface and tertiary reflecting surface so as to be rotationally symmetric around the axis of symmetry so that all three reflecting surfaces have an axially symmetric mirror arrangement with respect to design in which the optical imaging is transmitted to a receiver in the manner of an off-axis telescope.

Abstract: An arrangement for the detection of the fluorescence radiation of matrix-shaped specimen carriers with a large number of individual specimens, in particular, for the analysis of chemical and biological specimen carriers is disclosed.

Abstract: An arrangement is disclosed for optically reading out the information from substrates having a multiplicity of individual samples, in particular for analyzing chemical and biological sample carriers. The arrangement presents a new possibility for optically reading out the information from matrix-type substrates having a multiplicity of individual samples which allows a fast read-out of a radiation which is influenced by the individual samples with a high degree of sensitivity.

Abstract: An arrangement is disclosed for reading out the fluorescent radiation of specimen carriers with a plurality of individual specimens which for purposes of exciting fluorescent radiation in selected individual specimens comprises a switchable electro-optical matrix for generating illumination which is limited in a spatially defined manner.

Abstract: An arrangement for determining with high accuracy the angle of incidence of light, in particular sunlight, has low cost electronic components and low susceptibility to sources of interference and other error signals. An elongated photodiode array has a slot for a band of light to illuminate the photodiode array. The slot is arranged with a predefined spacing above and orthogonally to a preset longitudinal direction of the sensor array, which primarily presets the light's maximally detectable angle of incidence. The sensor array includes rows of several aligned congruent photodiode areas having substantially the same length and width. Each photodiode area has a size that generates a maximum photoelectric current when illuminated by the band of light. This current is sufficient in amount to be divided into a selected number and size of digital resolution stages.