DE102024114924B3 - Satellite device and method for detecting space objects, telescope device, color filter unit and computer-implemented method for evaluating images - Google Patents

Abstract

The invention relates to a 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) can be aligned such that the space objects cross 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) arranged and designed to generate 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 lens (204) and the telescope sensor (206), which color filter unit has at least one transparent filter area (312) and a monochrome filter area (314-320), wherein the transparent filter region (312) and the monochrome filter region (314-320) are aligned in a strip-like manner orthogonal to the main observation direction (310).

Description

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.

The detection of space objects with telescopes is generally well-known. Ground-based methods are particularly used for this purpose. Panchromatic sensors, for example, are available for detecting space objects, which maximize the detectability of faint space objects. Faint space objects can be, for example, small objects and/or objects at great observation distances.

Detectableness is maximized, among other things, by the fact that no additional light absorption occurs in the optical system due to filters. Panchromatic sensors also enable high spatial resolution in position measurement. Panchromatic sensors are therefore preferred for position measurement and the typically subsequent orbit determination. A disadvantage of panchromatic sensors is that they utilize the entire optical wavelength range, meaning no color information about the observed space objects can be determined.

However, color recognition of the observed space objects is advantageous for some applications. For example, based on the color information of the space object, the position, orientation, and/or positional movement can be deduced. Furthermore, color information can be used to characterize the surface of the space object, allowing, for example, the recognition of different satellites. Furthermore, the color information can contribute to object classification.

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 in the optical filters reduces the brightness of the objects. As a result, faint objects may not be detectable. Except for sufficiently bright objects, such optical filters cannot capture either location or color information for a specific space object. The use of such optical color filters is therefore unsuitable for many applications.

One approach to mitigating the disadvantages of optical color filters is to use multispectral CCD or CMOS sensors that contain different color filters. These color filters are applied to the sensor's pixels in a regular pattern. Such a sensor is also referred to as a Bayer sensor, as described, for example, in the US patent application US3971065A Although such sensors can also have transparent regions, these sensors also result in high absorption in the optical filters, which limits the detectability of faint objects. For example, a faint object would have to coincidentally pass directly over a transparent, unfiltered sensor pixel to be detectable. The filter pattern also impairs spatial resolution. The detection of faint space objects cannot be satisfactorily performed with such sensors.

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.

This object is achieved with 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 patent claims. Further advantageous embodiments of these aspects are specified in the respective dependent patent claims. The features disclosed in the patent claims, the description, and the drawings can be combined individually in any technologically expedient manner, with further embodiments of the invention being shown.

According to a first aspect, the object mentioned at the outset is achieved by a satellite device for detecting space objects with a telescope device which has a field of view, wherein the field of view can be aligned such that the space objects cross the field of view in a main observation direction, the telescope device comprising a telescope lens, an imaging telescope sensor which is arranged and designed to generate images of the 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 color filter unit comprises at least one transparent filter region and a single-color filter region, wherein the transparent filter region and the single-color filter region are aligned in a strip-like manner orthogonal to the main observation direction.

The invention is based on the finding that the color filter unit described above enables precise position and orbit determination of both faint and bright space objects, while simultaneously determining color information, at least for bright space objects. While the simultaneous determination of position and color is only possible for space objects that move through the field of view in the main observation direction, this can be predetermined by a suitable orbit and field of view alignment.

Furthermore, the invention was based on the finding that with the color filter unit, comprising a transparent filter area and a monochrome filter area, even faint space objects can be determined and recognized with regard to their position. This is made possible by the transparent filter area, which extends in a strip-like manner across the extent of the color filter unit orthogonal to the main observation direction. If this space object is also highly luminous, a color can additionally be determined using the monochrome filter area. 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 means and/or methods.

As a result, the satellite device can ensure that both high-luminosity and low-luminosity space objects can be determined with regard to their position and orbit, and at the same time, color information can be determined for sufficiently high-luminosity 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 high-luminosity space objects are possible.

The satellite device is designed to detect 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 can be recognized.

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

The basic position of space objects, for example in the vicinity of the Earth, is known. For example, a large number of space objects, particularly space debris, can be observed above the Earth's North Pole because the volume density is particularly high there. In order to advantageously observe these space objects, the orbit of satellite devices for detecting these space objects is selected such that these space objects cross the field of view in a horizontal direction. Therefore, it is often preferred for the main observation direction to be oriented horizontally. During normal operation, this would mean, in particular, that the main observation direction is oriented at least orthogonal to a gravity axis of the satellite device. Thus, the telescope device can be pivoted to the right and left and advantageously detect space objects.

The telescope device comprises the telescope objective. The telescope objective has, for example, lenses and mirrors. Such telescope objectives are generally known to those skilled in the art and are therefore not explained further below. The telescope device further comprises the imaging telescope sensor. The imaging telescope sensor is arranged and configured to generate images of the space objects against the starry background. For this purpose, the field of view is moved past the Earth in a passer-by pattern, so that the field of view is directed onto the starry background 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 designed in such a way that the world focused by means of the telescope lens Space objects can be imaged with the telescope sensor. The telescope lens enables magnification of space objects in a manner known to those skilled in the art.

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

The color filter unit comprises at least the transparent filter region and the monochrome filter region. The monochrome filter region is particularly designed to transmit light within a predefined wavelength range and to block light outside the predefined wavelength range. For example, the monochrome filter region can be designed to transmit only blue, red, yellow, or green light. Alternatively or additionally, the monochrome filter region can be designed as a polarization filter region.

It is particularly preferred that the color filter unit has two or more single-color filter regions. The two or more single-color color filter regions can have the same width or different widths. The two or more single-color color filter regions can have the same color but with different intensities, for example, light red and dark red. The two or more single-color color filter regions can also have the same color but with the same intensity, for example, red. The single-color filter region can be, for example, red, blue, green, yellow, and/or near-infrared. The transparent filter region is, in particular, designed to have low light absorption. Furthermore, it is preferred that the transparent filter region does not absorb or absorbs essentially nothing. The transparent filter region is, in particular, designed such that it has essentially no filtering function for light.

The transparent filter area and the monochrome filter area are strip-shaped. The main extension direction of these strip-shaped filter areas is oriented orthogonally to the main observation direction. For example, the main observation direction can be oriented essentially horizontally, so that during normal operation of the satellite device and assuming an orientation of the field of view in the direction of 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.

In a preferred embodiment of the satellite device, it is provided that 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 side to a bottom side, and the filter areas extend from the top side to the bottom side, so that the number of space objects to be observed in the main observation direction is maximized with the transparent filter area.

The strip-like arrangement of the filter areas and the fact that, among other things, the transparent filter area extends from the top to the bottom allow a large number of space objects to pass through the transparent filter area, so that the detection density is particularly high. It is preferred that no single-color filter areas be provided in the transparent filter area adjacent to the top and/or adjacent to the bottom. Such a color filter unit maximizes the number of space objects to be detected, while also creating the possibility of obtaining their color information.

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

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

In a further preferred embodiment of the satellite device, that the monochrome filter area has two or more sub-areas, each of the two or more sub-areas having 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 a lower brightness can also be obtained.

In a further 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.

Such a transparent filter area makes it possible to obtain as many data points as possible from a single space object, so that the position and/or orbit can be determined with greater accuracy.

In a further preferred embodiment of the satellite device, it is provided that the transparent filter area is designed as an optical glass or as a recess.

In a further preferred embodiment of the satellite device, it is provided that it comprises a computing unit configured to control the telescope sensor such that an exposure duration is selected such that a space object is imaged using a line-shaped image with at least two filter areas. The advantage is, among other things, that at the transition from one filter area to the other, two pieces of color information are present with virtually no temporal offset, thus two color measurements are available almost simultaneously. Thus, optimal determination of the color information is possible despite the rotation of the space object.

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

The control device may be or include the aforementioned computing unit. Alternatively, the aforementioned computing unit may include or be the control device.

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

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 extend, for example, between +20° and -20°, in particular between +4° and -12°. An advantage of this embodiment is that the orbit heights to be observed can be focused.

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 orbit axis in the pitch direction and/or the telescope axis oscillates relative to the orbit axis at a predefined angular velocity in the pitch direction. An advantage of this embodiment is that a plurality of orbit planes and a plurality of different particle sizes can be observed. The angular velocity during the oscillating movement can be, for example, between 2°/min and 6°/min.

In a preferred embodiment of the satellite device, the control device is configured to control the satellite device such that the telescope axis executes a yaw movement around the gravity axis, so that the field of view can be aligned to 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 to orbital regimes in which a high density of space objects is expected, for example, over the Earth's poles.

A further 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 orbit axis in order to align the field of view to at least one predefined orbital regime.

In a further preferred embodiment of the satellite device, it is provided that the control device is configured to control the satellite device in such a way that the telescope axis oscillates, in particular oscillates discontinuously, around the gravity axis by means of the yaw movement in a predefined angular range, wherein this yaw movement is carried out at a first angular velocity in order to observe at least two predefined orbital regimes.

Particularly for orbits that do not directly pass over the Earth's poles, oscillation around the gravity axis can be used to align the telescope axis to the region above the North Pole and the region above the South Pole. Furthermore, the yaw motion is preferably selected to minimize the solar phase angle, allowing particularly small space objects to be observed. Oscillation is preferably not continuous, but rather is performed at a rapid angular velocity from a first orientation to a second orientation to minimize disturbances during image acquisition.

A further 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 by means of the yaw movement as a function of a solar phase angle, so that the field of view can be aligned as a function of a solar phase angle.

According to a further aspect, the object mentioned above is achieved 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 generate images of the space objects against a starry background, a color filter unit arranged in the beam path between the telescope lens and the telescope sensor, which color filter unit comprises at least one transparent filter region and a monochrome filter region, wherein the transparent filter region and the monochrome filter region are aligned in a strip-like manner orthogonal to a main observation direction. The details of the telescope device, the telescope lens, the telescope sensor, and the color filter unit mentioned above apply analogously here.

According to a further aspect, the object mentioned above is achieved by a color filter unit for a telescope device according to one of the embodiments described above and/or for a satellite device according to one of the embodiments described above, which comprises at least one transparent filter region and one monochrome filter region, wherein the transparent filter region and the monochrome filter region are aligned in a strip-like manner orthogonal to a main observation direction. The details of the telescope device, the telescope lens, the telescope sensor, and the color filter unit mentioned above apply analogously here.

According to a further aspect, the object mentioned above is achieved by a method for detecting space objects, comprising the steps of: moving a satellite device in an 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, which color filter unit comprises at least one transparent filter region and a monochrome filter region, wherein the transparent filter region and the monochrome filter region are aligned in a strip-like manner orthogonal to a main observation direction; aligning the field of view such that space objects in the main observation direction cross the field of view; and generating at least one image with the transparent filter region and at least one image with the monochrome filter region of an individual space object. The image with the transparent filter region and the image with the monochrome filter region can also be a combined image, for example, by imaging the space object in a line-like manner with the transparent and monochrome filter regions.

The fact that space objects cross the field of view in the main observation direction is to be understood in particular in such a way that the space objects can be imaged with the transparent filter area and the monochrome filter area. This means, among other things, that they sweep over the transparent filter area and the monochrome filter area during observation. The fact that space objects cross the field of view in the main observation direction can further be understood in such a way that an angle between a direction of movement of the space object and the main observation direction is smaller than an angle between the direction of movement of the space object and an orthogonal to the main observation direction.

According to a further aspect, the object mentioned at the outset is achieved by a computer-implemented method for evaluating images obtained from a satellite device, a telescope device, a color filter device unit and/or by a method according to one of the embodiments described above, comprising the steps of: determining orbit information of a space object based on images generated with the transparent filter area and determining color information of the space object based on images of the space object generated with the monochrome filter area and linking the orbit information and the color information to form object information.

If the space object is bright enough to be visible in the monochrome filter area, the orbit information can also be determined using the monochrome filter area.

One result of the method can be, for example, that a certain space object A orbits the Earth in orbit O. When detected at time t from the relative viewing direction α in the color bands blue, green, red, yellow and near-infrared, the brightness of the object was x/y/z.

In a preferred embodiment of the computer-implemented method, it is provided that it comprises the step of outputting the object information.

In a further preferred embodiment of the method, it is provided that it comprises one or more of the steps of the method for detecting space objects.

In a further preferred embodiment of the method, it is provided that it comprises the step of: second determination of color information of the space object, based on images of the space object generated with the monochrome filter area in the event that the space object was not recognizable during the first determination of the color information with the monochrome filter area, wherein the second determination is carried out with a Kalman filter or a machine learning method.

For example, a detection threshold can be reduced at the edges, especially the monochrome filter areas, to detect space objects there as well, especially those previously captured with the transparent filter area. For example, a signal-to-noise ratio can be reduced at the edges.

According to a further aspect, the object mentioned at the outset is achieved by a data processing system comprising means for carrying out the method according to one of the embodiments described above.

According to a further aspect, the object mentioned at the outset is achieved by a computer program comprising instructions which, when the program is executed by a computer, cause the computer to carry out the method according to one of the embodiments described above.

According to a further aspect, the object mentioned at the outset is achieved by a computer-readable data carrier on which the computer program according to the previous aspect is stored.

For further advantages, design variants and details of the individual aspects and their possible further training, please refer to the description of the other aspects, the corresponding features and further training.

• 1: eine schematische, zweidimensionale Ansicht einer beispielhaften Ausführungsform einer Satellitenvorrichtung, die sich entlang einer Umlaufbahn um die Erde bewegt;
• 2: eine schematische, zweidimensionale Ansicht einer Abbildungsdarstellung;
• 3: eine schematische, zweidimensionale Ansicht einer Satellitenvorrichtung;
• 4: eine schematische, zweidimensionale Ansicht einer Farbfiltereinheit;
• 5: eine schematische, zweidimensionale Ansicht einer Farbfiltereinheit;
• 6: eine schematische Darstellung eines Verfahrens zur Erfassung von Weltraumobjekten;
• 7: eine schematische Darstellung eines Verfahrens zum Auswerten von Abbildungen.

Preferred embodiments are explained using the accompanying figures. They show:

• 1 : a schematic, two-dimensional view of an exemplary embodiment of a satellite device moving along an orbit around the Earth;
• 2 : a schematic, two-dimensional view of an imaging representation;
• 3 : a schematic, two-dimensional view of a satellite device;
• 4 : a schematic, two-dimensional view of a color filter unit;
• 5 : a schematic, two-dimensional view of a color filter unit;
• 6 : a schematic representation of a method for detecting space objects;
• 7 : a schematic representation of a method for evaluating images.

In the figures, identical or essentially functionally identical or similar elements are designated by the same reference numerals.

The exemplary embodiments explained below are preferred embodiments of the invention. In the exemplary embodiments, the described components of the embodiments each represent individual features of the invention that are to be considered independently of one another, which also further develop the invention independently of one another and are also to be considered as part of the invention individually or in a combination other than that shown. Furthermore, the described embodiments forms can also be supplemented by further features of the invention already described.

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

A second exemplary telescope axis 110' is also 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 orbit axis 106.

When the satellite device 100 orbits the Earth 1 in a clockwise direction, it becomes clear that the satellite device 100 continuously rotates in the image plane to set a constant pitch angle 114 between the telescope axis 110, 110' and the orbital axis 106, since the orbital axis 106 continuously moves. 1 The telescope is aligned opposite to the direction of flight, so-called backward pointing is set. Alternatively, forward pointing can be set. Furthermore, the field of view 112 is oriented toward the North Pole 2, since there is usually a higher object density above the North Pole 2. A space object 116 is also shown.

2 shows an image 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. Due to the constant pitch angle 114, the space object 132 and the stars 134 are represented equally in line form. The image of the space object 132 extends from the right edge to a central region. In the region to the right in the image representation 130, color information is also determined. In the regions 314', 316', 318', 320', color information of the space objects 132 was also obtained due to the upstream color filter unit 300. In the central region, in front of which the transparent region of the color filter unit 300 is arranged, the images of the space objects have a higher brightness.

3 shows a satellite device 200 with a telescope device 202. The satellite device 200 further comprises a solar panel 212, which supplies the components of the satellite device 200 with electrical energy.

The telescope device 202 comprises a telescope lens 204 and an imaging telescope sensor 206. The telescope lens spannes the field of view 205. The telescope sensor 206 is arranged and configured to generate images of the space objects 116 against a starry background.

In addition, the telescope device 202 comprises a color filter unit 208 arranged in the beam path between the telescope lens 204 and the telescope sensor 206. The details of the color filter unit 208 are described in the 4 and 5 explained in more detail. Furthermore, the telescopic axis 214 of the telescopic device 202 is shown.

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

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

A transparent filter area 312 is provided between the monochrome filter areas, more precisely between the green monochrome filter area 316 and the red monochrome filter area 318. The transparent filter area 312 is many times larger than the sum of the monochrome filter areas 314, 316, 318, 320. A further advantage of the color filter unit 300 is that, in addition to the selection of the monochrome color filter units, the arrangement of the monochrome color filter units and the transparent filter area as well as the relative width of the monochrome color filter units and the transparent filter area can be adjusted depending on the application and priority.

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, 320 of the color filter unit 300. In particular, the information obtained within the transparent filter area 312 enables position and orbit information to be obtained or determined. Because the space object 116 also passes through the monochrome filter areas 314, 316, 318, 320, color information can also be obtained from the space object 116.

In 5 An alternative embodiment of a color filter unit 300' is shown. The red, single-color filter area 318 is divided 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.

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 in the main observation direction 310.

In step 404, it is provided 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.

In 7 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 is shown. The computer-implemented method comprises step 410: determining orbit information of a space object 116 based on images generated with the transparent filter region 312. In step 412, color information of the space object 116 is determined based on images of the space object 116 generated with the monochrome filter region 314, 316, 318, 320. In step 414, a second determination of color information of the space object 116 takes place, based on images of the space object 116 generated with the monochrome filter area 314, 316, 318, 320 in the event that the space object 116 was not recognizable during the first determination of the color information with the monochrome filter area 314, 316, 318, 320, wherein the second determination is carried out using a Kalman filter or a machine learning method.

In step 416, the orbit information and the color information are combined to form object information.

The satellite device 100 described above and the corresponding methods enable the precise position and orbit determination of a space object 116, as well as the simultaneous determination of color information of the space object. The disadvantages currently encountered in the industry, in particular that either no color information can be obtained or the position determination is less accurate, can be avoided with the satellite device 100 and the methods described above.

REFERENCE SYMBOL

1

Earth

2

North Pole

100

Satellite device

102

orbit

104

Orbital coordinate system

106

Railway axis

108

axis of gravity

110, 110'

Telescopic axis

112

field of vision

114

Pitch angle

116

space object

130

Illustration representation

132

space object

134

star

200

Satellite device

202

Telescopic device

204

Telescope lens

205

field of vision

206

Telescopic sensor

208

Color filter unit

210

Control device

212

solar panel

214

Telescopic axis

300, 300'

Color filter unit

302

first page

304

second page

306

Top

308

bottom

310

Main observation direction

312

transparent filter area

314

blue monochrome filter area

316

green monochrome filter area

318

red monochrome filter area

320

near-infrared monochrome filter range

322

Space object movement direction

324

Space object movement direction

326

first red sub-area

328

second red sub-area

330

third red sub-area

Claims (16)

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) can be aligned such that the space objects cross 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) arranged and designed to generate images (130) of the space objects (116) against a starry background (134), and - a color filter unit (208, 300, 300') arranged in the beam path between the telescope lens (204) and the telescope sensor (206), which color filter unit has at least one transparent filter area (312) and one monochrome filter area (314-320), wherein the transparent filter region (312) and the monochrome filter region (314-320) are aligned in a strip-like manner orthogonal to the main observation direction (310). 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 side (306) to a bottom side (308), and - the filter areas (312-320) extend from the top side (306) to the bottom side (308) such that the number of space objects (116) to be observed in the main observation direction (310) is maximized with the transparent filter area (312). Satellite device (100, 200) according to one of the preceding claims, wherein the color filter unit (208, 300, 300') comprises at least two monochrome filter areas (314-320) selected from a red monochrome filter area (318), a blue monochrome filter area (314), 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). Satellite device (100, 200) according to one of the preceding claims, wherein the single-color filter region (314-320) has two or more sub-regions (326, 328, 330), the two or more sub-regions (326, 328, 330) each having a gradation of a color. 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). Satellite device (100, 200) according to one of the preceding claims, wherein the transparent filter region (312) is formed as an optical glass or as a recess. Satellite device (100, 200) according to one of the preceding claims, comprising a computing unit which is configured to control the telescope sensor (206) in such a way that an exposure time is selected such that a space object (116) is imaged by means of a line-shaped image with at least two filter areas. Satellite device (100, 200) according to one of the preceding claims, comprising - a control device (210) configured to o control the satellite device (100, 200) such that, during normal operation, a predetermined pitch angle is established between a telescope axis (110, 110') and an orbit (102) of the satellite device (100, 200), and ◯ control the telescope sensor (206) such that line-shaped images of space objects (132) and stars (134) are continuously generated in order to obtain a plurality of line-shaped images for generating a space object position image. Telescope device (202) for a satellite device (100, 200) according to one of the preceding claims, comprising - a telescope lens (204), - an imaging telescope sensor (206) which is arranged and designed to generate images of the space objects (116) against a starry background, - a color filter unit (208, 300, 300') arranged in the beam path between the telescope objective (204) and the telescope sensor (206), which color filter unit comprises at least one transparent filter region (312) and a monochrome filter region (314-320), wherein the transparent filter region (312) and the monochrome filter region (314-320) are aligned in a strip-like manner orthogonal to a main observation direction (310). 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 region (312) and one monochrome filter region (314-320), wherein the transparent filter region (312) and the monochrome filter region (314-320) are aligned in a strip-like manner orthogonal to a main observation direction (310). A method for detecting space objects (116), comprising the steps of: - moving a satellite device (100, 200) in an orbit (102) around a planet with a telescope device (202) having a field of view (112, 205), a telescope lens (204), an imaging telescope sensor (206), and a color filter unit (208, 300, 300') arranged in the beam path between the telescope lens (204) and the telescope sensor (206), which color filter unit comprises at least one transparent filter region (312) and a monochrome filter region (314-320), wherein the transparent filter region (312) and the monochrome filter region (314-320) are aligned in a strip-like manner orthogonal to a main observation direction (310), - aligning the field of view (112, 205) such that space objects in the Main observation direction (310) crosses the field of view (112, 205), and - generating at least one image with the transparent filter area (312) and at least one image with the monochrome filter area (314-320) of an individual space object (116). 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 according to the preceding claim, comprising the steps of: - determining orbit information of a space object (116) based on images generated with the transparent filter region (312), and - determining color information of the space object (116) based on images of the space object generated with the monochrome filter region (314-320), and - linking the orbit information and the color information to form object information. 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 event that the space object (116) was not recognizable during the first determination of the color information with the monochrome filter range (314-320), wherein the second determination is carried out using a Kalman filter or a machine learning method. A data processing system comprising means for carrying out the method according to any one of the preceding claims. A computer program comprising instructions which, when executed by a computer, cause the computer to carry out the method according to any one of the preceding claims. Computer-readable data carrier on which the computer program according to the previous claim is stored.