• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a diurnal and nocturnal stellar sensor (1), comprising: - at least one camera (2) adapted for taking images of stars (3) from the sky, - a control unit (4), characterized in that it further comprises: - a polarizer (5), the control unit (4) being configured to: - obtain an estimate of a direction of polarization of the polarized light from the sky received by the camera (2 ), and - control the orientation of the polarizer (5) so that said polarizer (5) filters the polarized light from the sky towards the camera (2) and having said polarization direction.
    公开号:FR3031807A1
    申请号:FR1550488
    申请日:2015-01-21
    公开日:2016-07-22
    发明作者:Johan Montel
    申请人:Centre National dEtudes Spatiales CNES；
    IPC主号:
    专利说明:

    [0001] GENERAL TECHNICAL FIELD The invention relates to a day and night stellar sensor. The invention also relates to a method for measuring the attitude of a vehicle, in particular at low altitude, from the stellar sensor measurements. STATE OF THE ART Star sensors are devices making it possible to deduce the attitude of a vehicle (for example a spacecraft of the satellite type) from the taking of star images. The identification of the stars in the images, by comparison with a catalog of known stars, makes it possible to determine the desired attitude. In many missions, it is necessary to know the attitude of the aircraft day and night. However, the image of stars is more difficult during the day, because of a background noise in the images, resulting in particular from the light emitted by the sun and scattered by the particles of the stratosphere or the atmosphere. Various solutions have been proposed to ensure the success of taking pictures of daytime stars, from a stellar sensor. For example, patent FR1159021, of the applicant, describes a diurnal stellar sensor, to provide a measure of attitude day and night. However, at low altitude (altitude less than 25km) and by day, it is difficult to obtain images of stars that can be exploited, since the number of stars detectable by the sensor decreases with the altitude of the vehicle. In addition, the disturbances of the measurement (background noise of the sky) are more important at low altitude. The high sky background flow requires limiting the integration time (exposure time) which lowers the signal-to-noise ratio and therefore the ability to detect a sufficient number of stars.
    [0002] Current solutions are therefore not applicable to daytime measurement at low altitude. In addition, the attitude of a vehicle can also be determined using an inertial unit and / or gyrometers. However, this solution also has drawbacks, and in particular drifts of the measurements caused by the excesses of accelerometers and gyrometers. Recalculations of the inertial unit by satellite measurements (GPS / GNSS) are known, but remain vulnerable because they can be scrambled globally or locally. PRESENTATION OF THE INVENTION The invention relates to a day and night stellar sensor, comprising at least one camera adapted for taking images of stars from the sky, a control unit, characterized in that it further comprises a polarizer , the control unit being configured to obtain an estimate of a direction of polarization of the polarized light from the sky received by the camera, and to control the orientation of the polarizer so that said polarizer filters the polarized light from the sky. directing towards the camera and having said polarization direction. The invention is advantageously completed by the following features, taken alone or in any of their technically possible combination: the star sensor further comprises a light filter, allowing only light to pass through the infrared band; the light filter passes only light having a wavelength between 1.5 μm and 2 μm or between 0.9 μm and 1.4 μm; the stellar sensor comprises a device for measuring an angle between a viewing direction of the star sensor and the sun, the control unit being configured to estimate the polarization direction of the polarized light from the sky received by the camera from said angle; the control unit comprises a memory storing ephemeris and / or a solar direction model for calculating an angle between a direction of sight of the sensor and the sun, from which the control unit calculates the direction of polarization polarized light from the sky received by the camera; the stellar sensor comprises a first optical head, comprising a first camera and a first polarizer, and a second optical head, comprising a second camera and a second polarizer, the first optical head and the second optical head being arranged diametrically opposite in azimuth . The invention also relates to a device for measuring attitude of a vehicle, comprising an inertial unit and / or a gyrometer, for providing an estimate of the attitude of the vehicle, characterized in that the device further comprises a stellar sensor diurnal and nocturnal as described above, a memory storing a catalog of known stars, the device being configured to reset the estimate of the attitude of the vehicle provided by the inertial unit and / or the gyrometer from the images taken by the stellar sensor and catalog of known stars. This registration may for example be carried out by gyrostellar hybridization, using a Kalman type filter. The invention also relates to a vehicle (for example a marine, land or space vehicle, comprising propulsion means), characterized in that it comprises this attitude measuring device. The invention also relates to a method of taking images of stars in the daytime and at night, using a day and night stellar sensor comprising a camera and a polarizer, characterized in that it comprises the steps of controlling the orienting the polarizer so that said polarizer filters the polarized light from the sky toward the camera and having said polarization direction, take pictures of stars from the sky with the camera.
    [0003] The invention also relates to a method for measuring the attitude of a vehicle, comprising the steps of taking images of stars from the sky according to the method as described above, and only in a wavelength band. between 0.9 pm and 2 pm, and compare the images of stars with a catalog of known stars, to reset an estimate of the attitude of the vehicle when it has an altitude between 0 and 25km. The invention has many advantages. The stellar sensor can significantly increase the signal-to-noise ratio in taking images of stars. In particular, the stellar sensor makes it possible to offer exploitable images in difficult shooting conditions, such as the day and / or at low altitude (between 0 and 25km). The stellar sensor measurements may especially be used for attitude measurement purposes, in particular for resetting attitude measuring devices. Thus, the registration can in particular be performed during the day and at low altitude, via the stellar sensor, without resorting to recalibration by satellite navigation systems. Finally, the proposed solution is inexpensive, flexible, and adapts to different types of vehicles, both marine, terrestrial, and space. PRESENTATION OF THE FIGURES Other characteristics, objects and advantages of the invention will emerge from the description which follows, which is purely illustrative and nonlimiting, and which should be read with reference to the appended drawings, in which: FIG. an embodiment of a stellar sensor, as well as an attitude measuring device comprising said stellar sensor; - Figure 2 is a representation of the polarization field of the sky according to the position of the sun relative to a terrestrial observer; FIG. 3 is a representation of an embodiment of a stellar sensor with a plurality of optical heads; Figure 4 is a representation of a method of taking images of stars; - Figure 5 is a representation of a method of measuring the attitude of a vehicle. DETAILED DESCRIPTION 1. Stellar sensor 1.1 Device presentation FIG. 1 shows an embodiment of a star sensor 1 according to the invention. This 1 stellar sensor is suitable for taking images of stars 3 day or night. The stellar sensor 1 comprises at least one camera 2 adapted for taking pictures of stars from the sky. As explained later, the type of camera 2 is chosen in particular according to the wavelength of the light that is to be measured. For example, in the near-infrared range (0.9-1.7pm), an InGaAs type camera can be used. The camera 2 can also be in accordance with the teaching of patent FR1159021 of the applicant. If necessary, the stellar sensor 1 comprises a lens 35 and an optical filter 7. The stellar sensor 1 comprises a control unit 4. The control unit 4 comprises, for example, a processor and a memory 11. The stellar sensor 1 further comprises a polarizer 5. A polarizer is a tool that selects a preferential polarization direction in an incident light wave. Therefore, the polarizer filters the light waves that do not have said preferred polarization direction.
    [0004] It has been found that the solar light diffused by the atmosphere is partly polarized linearly. The degree of polarization as well as the polarization angle (i.e. the direction of polarization in space) define the polarization field of the sky. This field is a function of the relative directions of the sun, the zenith and the direction targeted by the stellar sensor 1. On the other hand, the light coming from the stars is very little polarized. The control unit 4 is configured to obtain an estimate of a direction of polarization of the polarized light from the sky received by the camera 2. According to an exemplary embodiment, the control unit 4 receives an estimate of the angle between the aiming direction of the stellar sensor 1 and the direction of the sun. The control unit 4 calculates from this angle an estimate of the direction of polarization of the polarized light from the sky received by the camera 2. The angle between a direction of sight of the star sensor 1 and the sun can be provided in particular. by a stellar sensor 1 measuring device or by a measurement device on board the vehicle carrying said stellar sensor 1. For example, the control unit 4 receives an estimate of the angle between the aiming direction of the stellar sensor 1 with the direction of the Sun of an inertial unit 20 and / or a gyrometer 21 present in the stellar sensor 1. , or communicating with said stellar sensor 1. Alternatively, or in addition, the control unit 4 comprises a memory 11 storing ephemeris and / or a solar direction model, which make it possible to provide an estimate of the angle between the direction of sight of the stellar sensor 1 with the direction of the sun. The solar steering pattern depends on the date, time and position of the vehicle. In the case where the solar direction is not measured but calculated, the sensor requires to have knowledge (even very imprecise) of the date, the time (a few minutes of errors are acceptable) and the terrestrial position (a few tens of kilometers or a hundred are acceptable). The calculation of the direction of polarization from the angle between the direction of sight of the star sensor 1 and the direction of the sun can be done with various models of the sky. In one exemplary embodiment, the model only considers the molecular scattering of Rayleigh. The direction of polarization of the sky light is then expressed deterministically as a function of the angle between the aiming direction of the star sensor 1 and the direction of the sun. Indeed, as illustrated in Figure 2, this direction is ortho-radial with respect to the direction of sight and the sun. The degree of polarization (DOP, which defines the percentage of the light of the sky which is polarized), according to the model of Rayleigh, has for expression: sin 2 y DOP = 1 + cos 2 y In this expression, y is the angle between the aiming direction of the stellar sensor 1 and the solar direction. It is therefore found that the degree of polarization is maximum at 900 from the Sun. Figure 2 shows the direction of polarization of the sky seen by a terrestrial observer 30 at different times of the day (6H, 9H and 12H). The position of the sun 31 is illustrated. The control unit 4 is configured to control the orientation of the polarizer 5 so that said polarizer 5 filters the polarized light from the sky towards the camera 2 and having said polarization direction. Thus, an active control of the direction of the polarizer 5 is achieved by the control unit 4 as a function of the estimate of the direction of polarization of the sky. This makes it possible to reduce the background noise of the sky.
    [0005] Typically, the control unit 4 controls the direction of the polarizer 5 so that it has a direction orthogonal to the direction of polarization of the polarized light from the sky received by the camera 2. In an exemplary embodiment, the polarizer 5 is a rotating polarizer, which receives commands from a motor 33 controlled by the control unit 4. Alternatively, it is possible to use the control unit 4 and the motor 33 to rotate all or part of the elements of the star sensor 1 via the screw of the polarizer 5. With this configuration implementing an active control, the noise from the sky background is better filtered, and this adaptively. It is desirable that the star sensor can take images regardless of the elevation and azimuth of the sun vis-à-vis the vehicle boarding the stellar sensor. However, a configuration with a single optical head will not be suitable for all cases of pointing, because of the glare solar. Therefore, in one embodiment, a configuration with at least two diametrically opposed optical heads in azimuth is implemented. As illustrated in FIG. 3, the stellar sensor 1 comprises a first optical head Ti, comprising in particular a first camera 21 and a first polarizer Si. Where appropriate, the first optical head Ti comprises other elements as described with reference to FIG. 1 (filter, lens, etc.). In addition, the stellar sensor 1 comprises a second optical head T2, comprising a second camera 21 and a second polarizer Si. A single control unit 4 can be used to control the two polarizers 51, 52, via two actuators specific to each head. optical Ti, T2. Alternatively, a control unit 4 specific to each optical head Ti, T2 is used.
    [0006] The same applies to the various measurement and processing means described with reference to Figure 1 (inertial unit, gyroscope, computer, etc.) which can be shared for the two optical heads, or specific to each optical head. The first optical head Ti and the second optical head T2 are arranged diametrically opposite in azimuth (angle 4) for the optical head T2 and -4) for the optical head Ti, with for example 4) = 90 °). In addition, the elevation angle 0 of the optical heads (angle between the axis of sight of the heads and a horizontal axis) is generally identical, and chosen to minimize the background noise of the sky. Simulations have shown that the elevation angle θ should generally be chosen between 200 and 700 in order to minimize sky background noise, and preferably around 40 °. Elevations higher than 700 are generally proscribed because they cause a dazzling of the two optical heads at the zenith. The simulations show that the gain in signal noise compared to a stellar sensor without active control polarizer is of the order of a ratio of three, which is considerable. In the appendix (paragraph 4) we provide a modeling of the number of stars seen by a stellar sensor of the prior art according to different parameters. The stellar sensor according to the invention makes it possible to substantially improve the number of stars seen by said star sensor with respect to the prior art, since it allows a greater attenuation of the sky background signal with respect to the signal. emitted by the stars. 1.2 Presentation of a method for taking images of stars An embodiment of a method for taking images of stars in the daytime and at night periods, using a diurnal and nocturnal stellar sensor as described previously. As illustrated in FIG. 4, the method comprises a step E0 of obtaining an estimate of a direction of polarization of the polarized light from the sky received by the camera 2. This step is implemented by the control unit 4 which calculates from the angle between the direction of view of the camera 2 and the sun, an estimate of a direction of polarization of the polarized light from the sky received by the camera, for example on the basis of a Rayleigh model of the sky. The method comprises a step E1 of controlling the orientation of the polarizer 5 so that said polarizer 5 filters the polarized light from the sky towards the camera 2 and having said polarization direction. For this purpose, the control unit 4 estimates the direction of polarization of the polarized light from the sky, and directs, via the actuator 33, the polarizer 5 so that it filters the light having said direction. In general, the control unit 4 orients the polarizer 5 orthogonally to said direction. Control by the control unit 4 is generally in open loop. When the vehicle on which the star sensor 1 moves, the control unit 4 adapts the orientation of the polarizer 5 to estimate the direction of polarized light from the sky. Thus a dynamic adaptation, if necessary in real time, is realized. 2. Attitude measurement of a vehicle 2.1 Presentation of a vehicle attitude measuring device The measurements made by the star sensor 1 can in particular be used for the purpose of measuring the attitude of a vehicle. Examples of vehicles involved include, for example: drone, aircraft, balloon, satellite, land vehicle, marine, etc. Thus, a device 12 for measuring the attitude of a vehicle includes the day and night stellar sensor 1. It also includes an inertial unit 20, configured to provide an estimate of the attitude of the vehicle. Alternatively, or in addition, the device 12 comprises a gyroscope 21. A calculator 40 can in particular perform a hybridization, for example via a Kalman filter, of the measurements of the inertial unit 20 and the gyrometer 21, in order to obtain an estimate of the attitude of the vehicle. This type of hybridization is known in the art. The device 12 further comprises at least one memory 18 storing a catalog 22 of known stars (that is to say, whose characteristics are known, such as position and magnitude). The memory 18 and the memory 11 may correspond, if necessary, to a single memory. The comparison of the images taken by the stellar sensor 1 with the catalog 22 of known stars makes it possible to provide an attitude measurement, which is used by the device 12 to readjust the estimation of the attitude of the vehicle provided by the inertial unit. 20, or by the gyrometer 21, or by their hybridization. 2.2 Presentation of a vehicle attitude measurement method An embodiment of an attitude measurement method (see FIG. 5) comprises the steps of estimating the polarization direction of the polarized light of the sky received by the camera 2, and taking images of stars 3 from the sky, according to the steps E0, E1 and E2 described above. A further step E4 comprises comparing the images of the stars 3 with the catalog 22 of known stars. This comparison is for example carried out by the computer 40. This comparison makes it possible to provide an attitude value, which is used to readjust the calculated attitude from the measurements provided by the inertial unit and / or the gyrometer. This registration is typically performed in the computer 40, which integrates into its filter the data produced by the stellar measurements. In particular, the measurement bias caused by the measurement drift of the inertial unit and / or the gyrometer are reduced or even eliminated by this registration.
    [0007] As explained later, it is advantageous to carry out measurements in the infrared length band, and in particular in the near infrared (between 0.9 pm and 2 pm), in order to allow diurnal measurements at low altitude. In this case, the attitude of the vehicle is calculated in particular at low altitude, that is to say when it has an altitude of between 0 and 25km. 3. Observation in the near infrared Observation of stars, especially during the day and at low altitude, is difficult to achieve. The Applicant has developed various configurations that make it possible to optimize this observation from analyzes she has carried out. The stars are classified according to their spectral class and brightness class (classes I to VI, class III corresponding to the Giants and class V to the Dwarfs). The diagram in Figure 6 illustrates the proportion of the most visible star types (among the 4000 most visible stars) according to the spectral bands observed. The J band (1 to 1.5 μm) and the H band (1.5 to 2 μm) belong to the near infrared. The Applicant has calculated, from satellite measurements, an empirical law giving the number of stars of magnitude less than m (mv for the visible range, mj for the band J, and for the band H), for these different bands. spectral. Band Visible Band J Band H Number Nv = 5.13 10050'n Nj = 57.0 10050mJ NH = 150.0 10048m »of stars We thus note that the law of evolution in magnitude has a similar evolution in the three ranges of wavelengths ( the number of stars is multiplied by 3 when rising by a magnitude). But, at equal maximum magnitude, the number of stars in the J and H bands is about 11 and 29 times larger than in the visible band.
    [0008] Therefore, in one embodiment, the stellar sensor 1 further comprises at least one optical light filter 7, allowing only light to pass through the infrared band. More particularly, in one embodiment, the light filter 7 allows only light having a wavelength between 0.9 μm and 2 μm (near infrared) to pass. More particularly, in one embodiment, the light filter 7 only passes light having a wavelength of between 1.5 μm and 2 μm and / or between 0.9 μm and 1.4 μm. The "hole" voluntarily left between 1.4 pm and 1.5 pm corresponds to the absorption band of the water, which makes the atmosphere opaque in this band. These spectral bands make it possible to increase the signal to noise and to allow diurnal measurements at low altitude. An example of a camera that can work in the near infrared bands is a camera 2 based on InGaAs. The main advantages of working in the near infrared, compared to the visible, include the following: a reduced sky background noise (because the Rayleigh effect is in 1 / À4); an abundance of "red giant" stars; a good spectral response of InGaAs type detectors; a large depth of wells ("FWC") according to the acronym "Full Well Capacity" of said detectors. A camera 2 which includes an InGaAs type detector (0.9- 1.7pm), with a matrix of 640x512 pixels of 25pm, is suitable for altitudes of the order of 10km. If you want to go down to sea level, a matrix of at least 1 million pixels of 25pm meets the need. If the camera 2 observed wavelengths in the visible, it would not be possible to observe stars in the daytime and at low altitude, except to: - use very large detectors of several tens of millions of pixels; - increase the surface depth of wells by a very large factor; perform summation of images, that is to say several dozens of images. This will prove difficult if the vehicle is driven by a strong angular kinematics (fast rotation). The table below compares the solution in the visible (including a silicon-based camera) with the near-infrared solution (including an InGaAs-based camera). Visible (Silicon) Near infrared (InGaAs) Size of each pixel (pm) 4 to 7 25 Number of pixels max -10 to 20 million - 0.3 million Detector size (mm) 18 to 36 15 Surface FWC 400 3000 to 4000 The invention finds many applications in star imaging, especially for attitude measurement and registration, for day and night periods, even at low altitude. 4. Annex The number of stars Ne of magnitude less than m seen by a stellar sensor of the prior art can be modeled by the following formula: 0.25 (1.25 N toti 0; 5 frp) 0.625 f 0.5 N = N e 16 B (h) SB In this formula: - NB depends on the density of stars present in the sky in the spectral band under consideration (examples: visible, Nv - 5, band J, Nj - 57, band H, Nh - 150) ; - Po depends on the signal of Vega in the band considered; - Ta is the atmospheric transmission; IB is the fraction of sky background collected in the spectral band; - The value L (h) is given by the molecular diffusion, and depends on the altitude h, the elevation and the angle in the sun. However, this value does not depend on the spectral band (the spectral effect being integrated in the variable IB); - Sb is a signal to noise constant. An order of magnitude of this value to optimize the detection probability is 25 to 30. - Ntot (= Nx.Ny) is the total number of pixels of the detector (number of pixels per line Nx multiplied by number of pixels per column Ny) . - Lp is the size of a side of a pixel; - rp is the well depth per unit area (unit: e- / m2); - f is the focal length. For a given detector, the number of stars increases with the number of pixels, decreases with the square root of the field. At a constant opening number, the number of stars increases with the square root of the size of the objective (one-dimensional). If we replace L (h) by its altitude expression, we obtain: L (h) = Ke-h17, with K a constant. The number of stars evolves with altitude according to the law: h Ne oc el.25h / 7.5 24.2 The number of detectable stars doubles every 4.2km. The stellar sensor according to the invention makes it possible to substantially improve the number of stars seen by said star sensor with respect to the prior art, since it allows a greater attenuation of the sky background signal with respect to the signal. emitted by the stars: we increase the star signal more than we reduce the sky background signal.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Sensor (1) stellar diurnal and nocturnal, comprising: at least one camera (2) adapted for taking pictures of stars (3) from the sky, a control unit (4), characterized in that it comprises in furthermore: - a polarizer (5), the control unit (4) being configured to: obtain an estimate of a direction of polarization of the polarized light from the sky received by the camera (2), and to control the orientation of the polarizer (5) so that said polarizer (5) filters the polarized light from the sky towards the camera (2) and having said polarization direction.
    [0002]
    2. Sensor (1) stellar according to claim 1, further comprising a filter (7) of light, letting only light in the infrared band.
    [0003]
    3. Sensor (1) stellar according to claim 2, wherein the filter (7) of light passes only light having a wavelength between 1.5 pm and 2 pm or between 0.9 pm and 1.4 pm.
    [0004]
    4. sensor (1) stellar according to one of claims 1 to 3, comprising a device for measuring an angle between a direction of sight of the sensor (1) stellar and the sun, the control unit (4) being configured to estimate the polarization direction of the polarized sky light received by the camera (2) from said angle.
    [0005]
    5. sensor (1) stellar according to one of claims 1 to 3, wherein the control unit (4) comprises a memory (11) storing ephemeris and / or a solar direction model for computing a An angle between a direction of view of the sensor and the sun, from which the control unit (4) calculates the polarization direction of the polarized light from the sky received by the camera (2).
    [0006]
    6. stellar sensor (1) according to one of claims 1 to 5, comprising: - a first optical head (Ti), comprising a first camera (21) and a first polarizer (Si), and a second optical head (T2). ), comprising a second camera (21) and a second polarizer (Si), the first optical head (Ti) and the second optical head (T2) being arranged diametrically opposite in azimuth.
    [0007]
    A vehicle attitude measuring device (12), comprising: an inertial unit (20) and / or a gyrometer (21), for providing an estimate of the attitude of the vehicle, characterized in that the device (12) further comprises: a diurnal and nocturnal stellar sensor (1) according to one of claims 1 to 6, a memory (18) storing a catalog (22) of known stars, the device (12) being configured to recalibrate the estimate of the attitude of the vehicle provided by the inertial unit (20) and / or the gyrometer (21) from the images taken by the stellar sensor (1) and the catalog (22) of known stars.
    [0008]
    Vehicle, characterized in that it comprises an attitude measuring device (12) according to claim 7.
    [0009]
    9. A method for taking images of stars in the daytime and at night, using a day and night stellar sensor (1) comprising a camera (2) and a polarizer (5), characterized in that it comprises the steps of: controlling (E1) the orientation of the polarizer (5) so that said polarizer (5) filters the polarized light from the sky toward the camera (2) and having said polarization direction, take ( E2) images of stars (3) from the sky with the camera (2).
    [0010]
    10. A method of measuring the attitude of a vehicle, comprising the steps of: taking (E1, E2) images of stars (3) from the sky according to the method of claim 9, only in a strip of length wavelength range between 0.9 pm and 2 pm, compare (E3) the images of the stars (3) with a catalog of known stars, to reset an estimate of the attitude of the vehicle when it has an altitude between 0 and 25km.
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    CN108981691B|2018-06-08|2020-12-22|北京航空航天大学|Sky polarized light combined navigation on-line filtering and smoothing method|
    CN109668567B|2019-01-02|2021-09-24|中国人民解放军国防科技大学|Polarized light orientation method and system under multi-cloud condition of unmanned aerial vehicle and polarized light sensor|
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    法律状态:
    2016-02-01| PLFP| Fee payment|Year of fee payment: 2 |
    2016-07-22| PLSC| Publication of the preliminary search report|Effective date: 20160722 |
    2017-01-31| PLFP| Fee payment|Year of fee payment: 3 |
    2018-01-31| PLFP| Fee payment|Year of fee payment: 4 |
    2020-01-30| PLFP| Fee payment|Year of fee payment: 6 |
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    2022-01-31| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1550488A|FR3031807B1|2015-01-21|2015-01-21|SENSOR STEEL DIURN AND NIGHTLIGHT ACTIVE POLARIZER|FR1550488A| FR3031807B1|2015-01-21|2015-01-21|SENSOR STEEL DIURN AND NIGHTLIGHT ACTIVE POLARIZER|
    PCT/EP2016/051146| WO2016116511A1|2015-01-21|2016-01-20|Daytime and nighttime stellar sensor with active polarizer|
    EP16701137.8A| EP3247977A1|2015-01-21|2016-01-20|Daytime and nighttime stellar sensor with active polarizer|
    US15/542,691| US10302433B2|2015-01-21|2016-01-20|Daytime and nighttime stellar sensor with active polarizer|
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