Satellite apparatus and method for detecting space objects, telescope device, colour filter unit, and computer-implemented method for evaluating images

Abstract

The invention relates to a satellite apparatus (100, 200) for detecting space objects (116), the satellite device comprising a telescope device (202) having a field of view (112, 205), the field of view (112, 205) being orientable such that the space objects pass through the field of view (112, 205) in a main observation direction (310), the telescope device (202) comprising a telescope lens (204), an imaging telescope sensor (206) which is arranged and designed to generate images (130) of the space objects (116) against a stellar background (134), and a colour filter unit (208, 300, 300') that is arranged in the beam path between the telescope lens (204) and the telescope sensor (206) and comprises at least one transparent filter region (312) and one monochromatic filter region (314-320), the transparent filter region (312) and the monochromatic filter region (314-320) being strip-shaped and aligned orthogonally to the main observation direction (310).

Description

[0001] Satellite device and method for detecting space objects, telescope device, color filter unit and computer-implemented method for evaluating images

[0002] The invention relates to a satellite device and a method for detecting space objects, a telescope device for a satellite device, a color filter unit for a telescope device and / or for a satellite device, a computer-implemented method for evaluating images, a data processing system, a computer program and a computer-readable data carrier.

[0003] The detection of space objects using telescopes is a well-established practice. Ground-based methods are particularly common. For example, panchromatic sensors are available for detecting space objects, maximizing the detectability of faint objects. Faint objects can include small objects and / or objects located at great distances.

[0004] The detectability is maximized, among other things, by preventing additional absorption of light in the optical system through filters.

[0005] Panchromatic sensors also enable high spatial resolution in position measurement. For position measurement and the typically

[0006] For subsequent orbit determination, panchromatic sensors are therefore preferably used. A disadvantage of panchromatic sensors is that they utilize the entire optical wavelength range, meaning that no color information about the observed space objects can be determined.

[0007] However, color recognition of observed space objects is advantageous in several applications. For example, color information can be used to infer the object's position, orientation, and / or movement. Furthermore, color information can characterize the surface of a space object, enabling the identification of different satellites, for instance. Additionally, color information can contribute to object classification.

[0008] The detection of space objects and the determination of their color are currently performed using optical color filters. However, optical color filters have the disadvantage that absorption within the filters reduces the brightness of the objects. Consequently, faint objects may not be detectable. Apart from sufficiently bright objects, such optical filters cannot be used to acquire either positional or color information for a given space object. Therefore, the use of such optical color filters is unsuitable for many applications.

[0009] One approach to mitigating the disadvantages of optical color filters is to use multispectral CCD or CMOS sensors that incorporate various color filters. These color filters are arranged in a regular pattern on the sensor's pixels. Such a sensor is also known as a Bayer sensor, as disclosed, for example, in US patent application US3971065A. Although such sensors can also have transparent areas, they still result in high absorption in the optical filters, limiting the detectability of faint objects. For example, a faint object would have to happen to pass directly over a transparent, unfiltered sensor pixel to be detectable. Furthermore, the filter pattern impairs spatial resolution. The detection of faint space objects is therefore not satisfactorily achievable with such sensors.

[0010] It is therefore an object of the invention to provide a satellite device and a method for detecting space objects, a telescope device for a satellite device, a color filter unit for a telescope device and / or for a satellite device, a computer-implemented method for evaluating images, a data processing system, a computer program, and a computer-readable data carrier that reduce or eliminate one or more of the aforementioned disadvantages. In particular, it is an object of the invention to provide a solution that enables precise positioning of space objects while simultaneously detecting color information.

[0011] This problem is solved by a satellite device and a method for detecting space objects, a telescope device for a satellite device, a color filter unit for a telescope device and / or for a satellite device, a computer-implemented method for evaluating images, a data processing system, a computer program, and a computer-readable data carrier according to the features of the independent claims. Further advantageous embodiments of these aspects are specified in the respective dependent claims. The features disclosed in the claims, the description, and the drawings can be combined individually in any technologically meaningful way, and further embodiments of the invention are shown.

[0012] According to a first aspect, the aforementioned problem is solved by a satellite device for detecting space objects with a telescope device having a field of view, wherein the field of view is oriented such that the space objects cross the field of view in a principal observation direction, the telescope device comprising a telescope objective, an imaging telescope sensor arranged and configured to produce images of the space objects against a star background, and a color filter unit arranged in the beam path between the telescope objective and the telescope sensor, comprising at least one transparent filter area and one monochrome filter area, wherein the transparent filter area and the monochrome filter area are oriented in a strip-like manner orthogonal to the principal observation direction.

[0013] The invention is based on the understanding that the color filter unit described above enables precise position and orbit determination of faint and bright space objects, while simultaneously providing color information, at least for bright space objects. While the simultaneous determination of position and color is only possible for space objects moving through the field of view in the main observation direction, this can be predetermined by appropriate orbit and field-of-view alignment.

[0014] Furthermore, the invention was based on the understanding that even faint celestial objects can be determined and identified with regard to their position using the color filter unit, which comprises a transparent filter area and a monochrome filter area. This is made possible by the transparent filter area, which extends in a strip-like shape across the entire length of the color filter unit, perpendicular to the main line of observation. If this celestial object is also bright, its color can be additionally determined using the monochrome filter area. Furthermore, by fundamentally detecting a faint object with the transparent filter area, color information of the faint object can also be obtained from the images obtained with the monochrome filter area by applying specific evaluation tools and / or methods.

[0015] Consequently, the satellite device ensures that both bright and faint space objects can be determined with regard to their position and orbit, and that color information can be ascertained for sufficiently bright space objects. This avoids the disadvantages known in the prior art, namely that either only position determinations are possible or that only position and color determinations of bright space objects are possible. The satellite device is designed for detecting space objects. This means, in particular, that the satellite device is arranged and configured to create images of space objects and / or images in which space objects are recognizable.

[0016] The satellite device includes the telescope device. The telescope device has a field of view that can be oriented so that space objects cross the field of view in the main observation direction. The field of view can be shaped, for example, pyramid-shaped or conical.

[0017] The general position of space objects, for example near Earth, is known. For instance, a large number of space objects, especially space debris, are observable above the Earth's North Pole due to the particularly high volume density there. To advantageously observe these space objects, the orbit of satellites used to detect them is chosen such that these objects cross the field of view in a horizontal direction. Therefore, it is often preferred that the main observation direction is horizontally oriented. In intended operation, this would mean, in particular, that the main observation direction is at least orthogonal to a gravitational axis of the satellite. Thus, the telescope can be tilted to the right and left and advantageously detect space objects.

[0018] The telescope device comprises the telescope lens. The telescope lens includes, for example, reflectors and mirrors. Such telescope lenses are generally known to those skilled in the art and are therefore not described further below. The telescope device also comprises the imaging telescope sensor. The imaging telescope sensor is arranged and configured to produce images of space objects against the background of stars. For this purpose, the field of view is moved along the Earth in a pass-by-pass pattern, so that the field of view is directed towards the background of stars above the Earth's atmosphere. The telescope sensor can be, for example, a CCD or CMOS sensor. Furthermore, the telescope sensor can be a panchromatic sensor. The telescope lens and the telescope sensor are arranged and configured such that space objects focused by the telescope lens can be imaged by the telescope sensor.The telescope lens enables the magnification of space objects in a manner known to experts.

[0019] The telescope device further comprises the color filter unit, which is arranged in the beam path between the telescope objective and the telescope sensor. The fact that the color filter unit is arranged in the beam path between the telescope objective and the telescope sensor can mean, for example, that the color filter unit is located between the outermost lens of the telescope objective and the telescope sensor. The color filter unit is also arranged, for example, between a distal lens of the telescope objective and the telescope sensor, particularly with respect to the beam path. If mirrors are incorporated within the beam path, for example, to reduce the dimensions of the telescope device, the order may also be different.

[0020] The color filter unit comprises at least the transparent filter area and the monochromatic filter area. The monochromatic filter area is specifically designed to transmit light within a predefined wavelength range and to block light outside this range. For example, the monochromatic filter area may be configured to transmit only blue, red, yellow, or green light. Alternatively or additionally, the monochromatic filter area may be configured as a polarizing filter area.

[0021] It is particularly preferred that the color filter unit comprises two or more monochromatic filter areas. The two or more monochromatic filter areas can have the same width or different widths. The two or more monochromatic filter areas can have the same color but with different intensities, for example, light red and dark red. The two or more monochromatic filter areas can also have the same color but with the same intensity, for example, red. The monochromatic filter area can be, for example, red, blue, green, yellow, and / or near-infrared. The transparent filter area is particularly designed to have low light absorption. Furthermore, it is preferred that the transparent filter area does not absorb light or absorbs only minimally. The transparent filter area is particularly designed such that it has essentially no filtering function for light.

[0022] The transparent filter area and the monochrome filter area are strip-shaped. The main direction of extension of these strip-shaped filter areas is oriented orthogonally to the main observation direction. For example, the main observation direction may be essentially horizontal, so that, in the intended operation of the satellite device and assuming an orientation of the field of view towards the orbit, the main observation direction is essentially parallel to the Earth's horizon. Under this assumption, the orientation of the strip-shaped filter areas would then be vertical.

[0023] In a preferred embodiment of the satellite device, the color filter unit extends in the main observation direction from a first side to a second side and orthogonally to the main observation direction from a top to a bottom, and the filter areas extend from the top to the bottom, so that the number of observable space objects in the main observation direction is maximized with the transparent filter area.

[0024] The strip-like arrangement of the filter areas, and the fact that the transparent filter area extends from the top to the bottom, allows a large number of space objects to pass through the transparent filter area, resulting in a particularly high detection density. It is preferred that no monochrome filter areas are provided adjacent to the top and / or bottom of the transparent filter area. Such a color filter unit maximizes both the number of detectable space objects and the ability to obtain their color information.

[0025] In a further preferred embodiment of the satellite device, it is provided that the color filter unit comprises at least two monochromatic filter areas selected from a red monochromatic filter area, a blue monochromatic filter area, a green monochromatic filter area, a yellow monochromatic filter area and a near-infrared monochromatic filter area, and that the transparent filter area is arranged between the at least two monochromatic filter areas.

[0026] Alternatively or additionally, the transparent filter area can be positioned between two monochrome filter areas of the same or a similar color. With two monochrome filter areas, especially two monochrome filter areas of different colors, the color information can become more complex. For example, blue and red color information can be obtained from a space object.

[0027] In a further preferred embodiment of the satellite device, the monochrome filter area is provided to have two or more sub-areas, each of which has a gradation of a color. A gradation of a color can, for example, be light red and dark red. As a result, on the one hand, more comprehensive color information can be obtained, and on the other hand, color information from a space object with lower brightness can also be obtained, if necessary.

[0028] In another preferred embodiment of the satellite device, it is provided that the transparent filter area is larger than the monochrome filter area or the sum of the monochrome filter areas.

[0029] Such a transparent filter area makes it possible to obtain as many data points as possible of a single space object, so that the position and / or orbit determination can be carried out with higher accuracy.

[0030] In another preferred embodiment of the satellite device, the transparent filter area is designed as an optical glass or as a recess.

[0031] In another preferred embodiment of the satellite device, it is provided that it includes a processing unit configured to control the telescope sensor in such a way that an exposure time is selected to image a space object using a line-shaped image with at least two filter areas. The advantage lies, among other things, in the fact that at the transition from one filter area to the other, two color measurements are available with virtually no time offset, thus enabling two color measurements to be taken almost simultaneously. This allows for optimal determination of the color information despite the rotation of the space object.

[0032] According to a preferred embodiment of the satellite device, it is provided that it includes a control device which is configured to control the satellite device in such a way that a predetermined pitch angle is established between a telescope axis and an orbit of the satellite device during intended operation, and to control the telescope sensor in such a way that continuous line-shaped images of space objects and stars are generated in order to obtain a large number of line-shaped images for generating a space object position image.

[0033] The control device can be or comprise the computing unit mentioned above. Alternatively, the computing unit mentioned above can comprise or be the control device.

[0034] In a preferred embodiment, the control device is configured to control the satellite device such that the pitch angle remains constant. In particular, the pitch angle is constant within an observation interval.

[0035] Alternatively or additionally, it is preferred that the control device is configured to control the satellite device such that the pitch angle is set within a pitch angle range. The pitch angle range can, for example, extend between +20° and -20°, and in particular between +4° and -12°. An advantage of this embodiment is that the orbital altitudes to be observed can be focused.

[0036] Alternatively or additionally, it is preferred that the control device is configured to control the satellite device such that the telescope axis moves relative to the orbital axis in the pitch direction and / or the telescope axis oscillates relative to the orbital axis at a predefined angular velocity in the pitch direction. An advantage of this embodiment is that a large number of orbital planes and a large number of different particle sizes can be observed. The angular velocity during the oscillating motion can, for example, be between 27 and 67 rpm.

[0037] In a preferred embodiment of the satellite device, the control device is configured to steer the satellite device such that the telescope axis performs a yaw movement around the axis of gravity, allowing the field of view to be aligned with at least one predetermined orbital regime. From the perspective of the satellite device, the yaw movement of the telescope axis represents a change in the field of view to the right or left. Thus, the field of view can be aligned with orbital regimes where a high density of space objects is expected, for example, over the Earth's poles.

[0038] Another preferred embodiment of the satellite device is characterized in that the control device is configured to control the satellite device in such a way that a constant yaw angle is established between the telescope axis and the orbital axis in order to align the field of view with at least one predefined orbital regime.

[0039] In a further preferred embodiment of the satellite device, the control device is configured to control the satellite device in such a way that the telescope axis oscillates around the gravitational axis in a predefined angular range by means of the yaw motion, in particular oscillates discontinuously, wherein this yaw motion is performed with a first angular velocity in order to observe at least two predefined orbital regimes.

[0040] Particularly in orbits that do not pass directly over the Earth's poles, oscillation around the gravitational axis can be used to align the telescope axis with the area above the North Pole and the area above the South Pole. Furthermore, the yaw motion is preferably chosen to minimize the solar phase angle, allowing the observation of particularly small celestial objects. The oscillation is preferably not continuous, but rather performed at a high angular velocity from a first alignment to a second alignment, in order to minimize interference during image acquisition.

[0041] Another preferred embodiment of the satellite device is characterized in that the control device is configured to control the satellite device in such a way that the telescope axis can be pivoted by 180° between a first orientation and a second orientation depending on a solar phase angle by means of the yaw movement, so that the field of view can be aligned depending on a solar phase angle.

[0042] According to another aspect, the aforementioned problem is solved by a telescope device for a satellite device according to one of the embodiments described above, comprising the telescope lens, an imaging telescope sensor arranged and configured to produce images of space objects against a star background, and a color filter unit arranged in the beam path between the telescope lens and the telescope sensor, which includes at least one transparent filter area and one monochrome filter area, wherein the transparent filter area and the monochrome filter area are oriented in strip-like formations orthogonally to a principal observation direction. The details of the telescope device, the telescope lens, the telescope sensor, and the color filter unit mentioned above apply analogously here.

[0043] According to another aspect, the aforementioned problem is solved by a color filter unit for a telescope device according to one of the previously described embodiments and / or for a satellite device according to one of the previously described embodiments, which comprises at least one transparent filter area and one monochrome filter area, wherein the transparent filter area and the monochrome filter area are arranged in strips orthogonally to a principal observation direction. The previously mentioned details of the telescope device, the telescope lens, the telescope sensor, and the color filter unit apply analogously here.

[0044] According to another aspect, the aforementioned problem is solved by a method for detecting space objects, comprising the steps of: moving a satellite device in orbit around a planet with a telescope device having a field of view, a telescope lens, an imaging telescope sensor, and a color filter unit arranged in the beam path between the telescope lens and the telescope sensor, comprising at least one transparent filter area and one monochrome filter area, wherein the transparent filter area and the monochrome filter area are oriented in strip-like orthogonal arrangements to a principal viewing direction; aligning the field of view such that space objects in the principal viewing direction cross the field of view; and producing at least one image with the transparent filter area and at least one image with the monochrome filter area of ​​a single space object.The image with the transparent filter area and the image with the monochrome filter area can also be a combined image, for example by imaging the space object as a line using the transparent and monochrome filter areas.

[0045] The fact that space objects cross the field of view in the main observation direction is to be understood, in particular, as meaning that the space objects can be imaged using the transparent filter area and the monochrome filter area. This means, among other things, that they sweep across the transparent filter area and the monochrome filter area during observation. Furthermore, the fact that space objects cross the field of view in the main observation direction can be understood as meaning that the angle between the direction of motion of the space object and the main observation direction is smaller than the angle between the direction of motion of the space object and a line perpendicular to the main observation direction.

[0046] According to another aspect, the aforementioned task is solved by a computer-implemented method for evaluating images obtained from a satellite device, a telescope device, a color filter unit and / or by a method according to one of the previously described implementation variants, comprising the steps of: determining orbital information of a space object based on images produced with the transparent filter area, determining color information of the space object based on images of the space object produced with the monochrome filter area, and combining the orbital information and the color information to form object information.

[0047] If the space object is bright enough to be visible even in the monochrome filter area, the orbital information can also be determined using the monochrome filter area.

[0048] One result of the procedure could be, for example, that a specific space object A orbits the Earth in orbit O. When recorded at time t from the relative viewing direction a in the color bands blue, green, red, yellow, and near-infrared, the brightness of the object was x / y / z.

[0049] In a preferred implementation variant of the computer-implemented method, it is provided that this includes the step: output of the object information.

[0050] In another preferred embodiment of the method, it is provided that it includes one or more of the steps of the method for detecting space objects.

[0051] In a further preferred embodiment of the method, it is provided that it includes the step: Second determination of color information of the space object, based on images of the space object generated with the monochromatic filter area, in the case that the space object was not recognizable when first determining the color information with the monochromatic filter area, wherein the second determination is carried out with a Kalman filter or a machine learning method.

[0052] For example, the detection threshold at the edges, especially in the monochrome filter areas, can be reduced to enable the detection of space objects there as well, particularly those previously detected with the transparent filter area. For example, the signal-to-noise ratio at the edges can be reduced.

[0053] According to another aspect, the aforementioned task is solved by a data processing system comprising means for executing the procedure according to one of the execution variants described above. According to yet another aspect, the aforementioned task is solved by a computer program comprising instructions that, when executed by a computer, cause it to execute the procedure according to one of the execution variants described above.

[0054] According to another aspect, the aforementioned task is solved by a computer-readable data carrier on which the computer program is stored according to the previous aspect.

[0055] For further advantages, design variants and design details of the individual aspects and their possible further training, reference is also made to the description of the further aspects, the corresponding characteristics and further training.

[0056] Preferred embodiments are illustrated by way of example with reference to the enclosed

[0057] Figures explained. They show:

[0058] Figure 1: a schematic, two-dimensional view of an exemplary

[0059] Design of a satellite device that moves along an orbit around the Earth;

[0060] Figure 2: a schematic, two-dimensional view of a

[0061] Illustration;

[0062] Figure 3: a schematic, two-dimensional view of a

[0063] Satellite device;

[0064] Figure 4: a schematic, two-dimensional view of a

[0065] Color filter unit;

[0066] Figure 5: a schematic, two-dimensional view of a

[0067] Color filter unit;

[0068] Figure 6: a schematic representation of a method for detecting space objects;

[0069] Figure 7: a schematic representation of a method for evaluating images. In the figures, identical or essentially functionally equivalent or similar elements are designated with the same reference symbols.

[0070] The exemplary embodiments described below are preferred embodiments of the invention. In these exemplary embodiments, the described components each represent individual features of the invention, which can be considered independently of one another. Each of these features further develops the invention independently and can be regarded as part of the invention individually or in a combination other than that shown. Furthermore, the described embodiments can also be supplemented by other features of the invention already described.

[0071] Figure 1 shows a view in which the pitch axis is perpendicular to the image plane, so that only the orbital axis 106 and the gravity axis 108 of the orbital coordinate system 104 of orbit 102 are shown. Figure 1 shows that the origin of the orbital coordinate system 104 is located at the satellite device 100. The satellite device 100 comprises a telescope with a telescope axis 110, which in Figure 1 has a pitch angle of 0° and is thus aligned parallel to the orbital axis 106. The telescope also defines a field of view 112.

[0072] Furthermore, a second exemplary telescope axis 110' is shown, which is aligned approximately 350 km above the Earth's horizon. The pitch angle 114 is set between the telescope axis 110' and the orbital axis 106.

[0073] When the satellite device 100 orbits the Earth 1 clockwise, it becomes clear that the satellite device 100 continuously rotates in the image plane to establish a constant pitch angle 114 between the telescope axis 110, 110' and the orbital axis 106, since the orbital axis 106 moves continuously. In Figure 1, the telescope is oriented opposite to the direction of travel, so that a so-called backward pointing is set. Alternatively, a forward pointing can be set. Furthermore, the field of view 112 is oriented towards the North Pole 2, since there is usually a higher object density above the North Pole 2. Figure 2 also shows a representation 130 of line-shaped images of space objects 132 and stars 134, which was created using the satellite device 100 described above with the corresponding control system.The constant pitch angle 114° ensures that both the space object 132 and the stars 134 are depicted as lines. The image of the space object 132 extends from the right edge into a central area. Color information is also determined in the right-hand area of ​​the image 130. In the areas 314', 316', 318', and 320', color information for the space object 132 was also obtained due to the upstream color filter unit 300. In the central area, in front of which the transparent section of the color filter unit 300 is positioned, the images of the space objects exhibit higher brightness.

[0074] Figure 3 shows a satellite device 200 with a telescope device 202. The satellite device 200 also has a solar panel 212, which supplies the components of the satellite device 200 with electrical energy.

[0075] The telescope device 202 comprises a telescope lens 204 and an imaging telescope sensor 206. The telescope lens defines the field of view 205. The telescope sensor 206 is arranged and configured to produce images of the space objects 116 against a star background.

[0076] Furthermore, the telescope device 202 includes a color filter unit 208 arranged in the beam path between the telescope objective 204 and the telescope sensor 206. Details of the color filter unit 208 are explained in more detail in Figures 4 and 5. The telescope axis 214 of the telescope device 202 is also shown.

[0077] Figure 4 shows a schematic representation of a color filter unit 300, which extends horizontally from a first side 302 to a second side 304. Vertically, the color filter unit 300 extends from a top surface 306 to a bottom surface 308. Naturally, the color filter unit 300 can also be rotated so that it extends horizontally from the top surface 306 to the bottom surface 308. In normal operation, the color filter unit 300 is used such that the space objects 116 move through the field of view with a horizontal component of movement. In particular, the horizontal component of movement is greater than the vertical component of movement. The main observation direction 310 is therefore horizontally oriented in this case. For illustrative purposes, the space object movement directions 322 and 324 are shown.

[0078] The color filter unit 300 has a blue monochrome filter area 314 and a green monochrome filter area 316 adjacent to the first side 302. Adjacent to the second side 304, the color filter unit 300 has a near-infrared monochrome filter area 320 and a red monochrome filter area 318.

[0079] A transparent filter area 312 is provided between the single-color filter areas, specifically between the green single-color filter area 316 and the red single-color filter area 318. The transparent filter area 312 is many times larger than the sum of the single-color filter areas 314, 316, 318, and 320. A further advantage of the color filter unit 300 is that, in addition to the choice of single-color filter units, the arrangement of the single-color filter units and the transparent filter area, as well as the relative width of the single-color filter units and the transparent filter area, can be adjusted according to the application and priority.

[0080] When a space object 116 moves into the field of view of the telescope device 202, it moves, as viewed from the telescope sensor 206, through the filter areas 312, 314, 316, 318, and 320 of the color filter unit 300. In particular, the information obtained within the transparent filter area 312 provides, or enables, position and orbit information. Because the space object 116 also traverses the monochrome filter areas 314, 316, 318, and 320, color information about the space object 116 can also be obtained.

[0081] Figure 5 shows an alternative embodiment of a color filter unit 300'. The red monochrome filter area 318 is subdivided into a first red sub-area 326, a second red sub-area 328, and a third red sub-area 330, each representing different shades of red. Figure 6 shows a method for detecting space objects 116. In step 400, the satellite device 100 is moved in an orbit 102 around a planet 1. In step 402, the field of view 112 is aligned such that space objects 116 cross the main observation direction 310.

[0082] Step 404 provides that at least one image with the transparent filter area 312 and at least one image with the monochrome filter area 314, 316, 318, 320 of a single space object 116 is generated.

[0083] Figure 7 shows a computer-implemented method for evaluating images obtained from a satellite device 100, 200, a telescope device 202, a color filter unit 208, 300, 300' and / or by a method 400, 402, 404. The computer-implemented method comprises step 410: determining orbital information of a space object 116 based on images produced with the transparent filter area 312. In step 412, color information of the space object 116 is determined based on images of the space object 116 produced with the monochrome filter area 314, 316, 318, 320.In step 414, a second determination of color information for the space object 116 is performed, based on images of the space object 116 generated with the monochrome filter range 314, 316, 318, 320, in the case that the space object 116 was not recognizable during the first determination of the color information with the monochrome filter range 314, 316, 318, 320, wherein the second determination is performed with a Kalman filter or a machine learning method.

[0084] In step 416, the orbit information and the color information are linked together to form object information.

[0085] The satellite device 100 described above and the corresponding methods enable the precise determination of the position and orbit of a space object 116, as well as the simultaneous determination of the object's color. The disadvantages currently encountered in industry, particularly the inability to obtain color information or the lower accuracy of the position determination, can be avoided with the satellite device 100 and the methods described above.

[0086] REFERENCE MARK

[0087] 1 Earth

[0088] 2 North Pole

[0089] 100 satellite devices

[0090] 102 orbit

[0091] 104 Orbital Coordinate System

[0092] 106 railway axis

[0093] 108 Gravity axis

[0094] 110, 110' telescopic axis

[0095] 112 field of vision

[0096] 114 pitch angle

[0097] 116 Space Object

[0098] 130 Illustration

[0099] 132 Space Object

[0100] 134 stars

[0101] 200 satellite device

[0102] 202 T telescopic device

[0103] 204 Telescope lens

[0104] 205 field of view

[0105] 206 Telescope sensor

[0106] 208 Color filter unit

[0107] 210 Control device

[0108] 212 solar panels

[0109] 214 Telescopic axis 300, 300' Color filter unit

[0110] 302 first page

[0111] 304 second page

[0112] 306 Top side 308 Bottom side

[0113] 310 Main observation direction

[0114] 312 transparent filter area

[0115] 314 blue monochrome filter area

[0116] 316 green single-color filter area 318 red single-color filter area

[0117] 320 near-infrared monochrome filter range

[0118] 322 Direction of movement of space objects

[0119] 324 Direction of movement of space objects

[0120] 326 first red sub-area 328 second red sub-area

[0121] 330 third red sub-area

Claims

REQUIREMENTS 1. Satellite device (100, 200) for detecting space objects (116) with a telescope device (202) having a field of view (112, 205), wherein the field of view (112, 205) is oriented such that the space objects cross the field of view (112, 205) in a principal observation direction (310), the telescope device (202) comprising a telescope objective (204), an imaging telescope sensor (206) arranged and configured to produce images (130) of the space objects (116) against a star background (134), and a color filter unit (208, 300, 300') arranged in the beam path between the telescope objective (204) and the telescope sensor (206), comprising at least a transparent filter area (312) and a monochromatic filter area (314-320) comprising, wherein the transparent filter area (312) and the monochrome filter area (314-320) are oriented in strip form orthogonally to the main observation direction (310).

2. Satellite device (100, 200) according to claim 1, wherein the color filter unit (208, 300, 300') extends in the main observation direction (310) from a first side (302) to a second side (304) and orthogonally to the main observation direction (310) from a top (306) to a bottom (308), and the filter areas (312-320) extend from the top (306) to the bottom (308) such that the number of observable space objects (116) in the main observation direction (310) is maximized with the transparent filter area (312).

3. Satellite device (100, 200) according to one of the preceding claims, wherein the color filter unit (208, 300, 300') has at least two monochromatic filter areas (314-320) selected from a red monochromatic filter area (318), a blue monochromatic filter area (314), a comprising a green monochrome filter area (316), a yellow monochrome filter area and a near-infrared monochrome filter area (320), and the transparent filter area (312) is arranged between the at least two monochrome filter areas (314-320).

4. Satellite device (100, 200) according to one of the preceding claims, wherein the monochromatic filter area (314-320) has two or more sub-areas (326, 328, 330), wherein the two or more sub-areas (326, 328, 330) each have a gradation of a color.

5. Satellite device (100, 200) according to one of the preceding claims, wherein the transparent filter area (312) is larger than the monochrome filter area (314-320) or the sum of the monochrome filter areas (314-320).

6. Satellite device (100, 200) according to one of the preceding claims, wherein the transparent filter area (312) is designed as an optical glass or as a recess.

7. Satellite device (100, 200) according to one of the preceding claims, comprising a computing unit configured to control the telescope sensor (206) in such a way that an exposure time is selected so that a space object (116) is imaged by means of a line-shaped image with at least two filter areas.

8. Satellite device (100, 200) according to one of the preceding claims, comprising a control device (210) configured to control the satellite device (100, 200) such that a predetermined position is achieved during intended operation. sets the pitch angle between a telescope axis (110, 110') and an orbit (102) of the satellite device (100, 200), and o controls the telescope sensor (206) in such a way that continuous line-shaped images of space objects (132) and stars (134) are generated in order to obtain a large number of line-shaped images for generating a space object position image.

9. Telescope device (202) for a satellite device (100, 200) according to one of the preceding claims, comprising a telescope objective (204), an imaging telescope sensor (206) arranged and configured to produce images of the space objects (116) against a star background, a color filter unit (208, 300, 300') arranged in the beam path between the telescope objective (204) and the telescope sensor (206), comprising at least one transparent filter area (312) and one monochrome filter area (314-320), wherein the transparent filter area (312) and the monochrome filter area (314-320) are oriented in a strip-like manner orthogonal to a principal observation direction (310).

10. Color filter unit (208, 300, 300') for a telescope device (202) according to the preceding claim and / or for a satellite device (100, 200) according to one of the preceding claims, comprising at least one transparent filter area (312) and one monochrome filter area (314-320), wherein the transparent filter area (312) and the monochrome filter area (314-320) are oriented in a strip-like manner orthogonal to a principal observation direction (310).

11. Procedure for detecting space objects (116), comprising the steps: Moving a satellite device (100, 200) in an orbit (102) around a planet with a telescope device (202) comprising a viewing field (112, 205), a telescope objective (204), an imaging telescope sensor (206) and a color filter unit (208, 300, 300') arranged in the beam path between the telescope objective (204) and the telescope sensor (206), comprising at least one transparent filter area (312) and one monochrome filter area (314-320), wherein the transparent filter area (312) and the monochrome filter area (314-320) are oriented in strip form orthogonally to a principal viewing direction (310), - Aligning the field of view (112, 205) such that space objects in the main observation direction (310) cross the field of view (112, 205), and Generating at least one image using the transparent filter area (312) and at least one image using the monochrome filter area (314-320) of a single space object (116).

12. Computer-implemented method for evaluating images received from a satellite device (100, 200), a telescopic device (202), a color filter unit (208, 300, 300') and / or by a method according to the preceding claim, comprising the steps: Determining orbital information of a space object (116) based on images generated with the transparent filter area (312), and Determining color information of the space object (116) based on images of the space object produced with the monochrome filter range (314-320), and - Linking orbit information and color information to create object information.

13. Computer-implemented method according to the preceding claim, comprising the step: - second determination of color information of the space object (116) based on images of the space object (116) generated with the monochrome filter range (314-320) in the case that the The space object (116) was not detectable during the first determination of the color information with the monochrome filter range (314-320), with the second determination being carried out using a Kalman filter or a machine learning method.

14. Data processing system comprising means for carrying out the method according to any of the preceding claims.

15. Computer program comprising instructions which, when the program is executed by a computer, cause it to execute the method according to any of the preceding claims.

16. Computer-readable data carrier on which the computer program according to the preceding claim is stored.

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