• 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 navigation satellite (10, 10 ', 10' '), in particular for a Medium Earth Orbit (MEO), has a housing (12) and a navigation antenna (16) connected to the housing (12) for the radiation of navigation signals in a preferred direction. In addition, the navigation satellite (10, 10 ', 10' ') has an optical communication device (22) for unidirectional or bidirectional signaling with at least one other satellite preceding in the direction of travel and / or with at least one other satellite following in the direction of travel. The navigation satellite (10, 10 ', 10' ') is provided with a retaining element (for example as a navigation antenna) which is arranged on the housing (12) in rotation about an axis of rotation. rotation (17), the optical communication device (22) being arranged on the retaining element.
    公开号:FR3068954A1
    申请号:FR1856491
    申请日:2018-07-13
    公开日:2019-01-18
    发明作者:Christoph Gunther；Christopher Schmidt
    申请人:Deutsches Zentrum fuer Luft und Raumfahrt eV；
    IPC主号:
    专利说明:

    NAVIGATION SATELLITE,
    GOOD TO KNOW FOR MEDIUM LAND ORBIT
    The invention relates to a navigation satellite which is preferably intended for a Medium Earth Orbit (MEO).
    The optical links between navigation satellites allow very precise synchronization of clocks (so-called Composite Clock), precise distance measurement and the transport of important data without external assistance. For this to be possible, navigation satellites must be equipped with optical transmission and reception equipment.
    The attitude of a navigation satellite in the Medium Earth Orbit constitutes a particular challenge. The attitude is determined by the fact that the navigation antenna must always be pointed towards the center of the Earth (Nadir-Pointing) and that the solar generators must always be oriented towards the sun. The first requirement determines the attitude until a rotation around the axis of the nadir, that is to say the connection between the centers of gravity of the Earth and the satellite. Two other axes are necessary for the orientation of the solar generators. One is the axis of the nadir, the other is the axis on which the generators are mounted and around which the generators can rotate. Since the satellite has one side to be kept cold and one side to be kept warm, it is also rotated 180 ° respectively around the axis of the nadir near the point closest to the sun and the point the further from the sun. The first rotation is called "noon-turn" and the second "mid-night turn".
    The state of the art consists of more or less orientable optical transmission and reception systems, for example. TESAT LCT (see eg BENZI, E. [et al.]: Optical Inter-Satellite Communication: the Alphasat and Sentinel1A in-orbit experience. In: Proc. SpaceOps 2016 Conference, 16.-20.05.2016, Daejeon, Korea , (A1AA 20162389) A1AA [online], DO1: 10.2514 / 6.2 016-238 9 [consulted on 06/14/2018] These are firstly complex to produce and involve variable geometry between the optical systems and the center phase of the L-band antenna for example. The navigation antenna of current navigation satellites is fixedly connected to the structure of the satellite, that is to say to the housing (also called satellite bus). such that a rotation of the satellite around the vertical axis also means a rotation of the navigation antenna and its radiation characteristic.
    US-A-2017/0005719 describes a constellation composed of a multiplicity of satellites for communication with each other as well as with ground stations.
    US-A-2004/0179847 relates to a satellite with mirror optics intended for communication with other satellites.
    The invention aims to create a navigation satellite which, despite the two rotations of 180 ° respectively required during a revolution around the Earth, allows to maintain an optical communication link with neighboring satellites in the same orbit.
    To achieve this objective, the invention proposes a navigation satellite for in particular a Medium
    Earth Orbit (MEO), which is provided with a housing (that is to say a structure of the satellite or respectively a satellite bus), of a navigation antenna connected to the housing for the radiation of navigation signals in a preferred direction, of an optical communication device intended for unidirectional or bidirectional signaling with at least one other satellite, which precedes in the direction of movement, towards a first axis of communication and / or with at least one another satellite, which follows in the direction of movement, in the direction of a second axis of communication, and of a retaining element which is arranged in rotation on the housing around an axis of rotation, the optical communication device being disposed on the retainer.
    The main characteristic of the navigation satellite according to the invention is a retaining element or respectively support for an optical communication device, the support or respectively retaining element being disposed on / in the housing in rotation about an axis.
    "Satellite housing" means the structure of the satellite (without payload - also called payload). It is also referred to as the satellite bus. The payload would therefore be the retaining element with the optical communication device and the navigation antenna. The optical communication device generally comprises two optical communication units which respectively define an optical communication axis, the communication axis of the first optical communication unit being directed for example towards a satellite which precedes in the direction of movement of the satellite of navigation concerned while the optical communication axis of the second optical communication unit targets a following satellite.
    It is thus possible to permanently establish optical links with neighboring satellites in the same orbit (orbit) and to maintain them permanently.
    In a suitable embodiment of the invention, it is possible to provide that the navigation antenna serves as a retaining element for the optical communication device or is arranged on the retaining element and can rotate accordingly. Thanks to the simultaneous use of the retaining element for the optical communication device as a navigation antenna, no additional support element for the optical communication device is required in the structure of the satellite. On the contrary, the navigation antenna already present is used as a support or respectively a retaining element for the optical communication device and therefore for the optical communication units.
    The first and second optical communication units should advantageously be pivotable and to this extent be mobile on the retaining element or respectively on the navigation antenna so that the navigation system concerned can enter into communication with the neighboring satellite on the same orbit and maintain this communication link.
    In another suitable embodiment of the invention, it is possible to provide for the navigation antenna to have a radiation side of navigation signals and a rear side, distant from it, which faces the housing, and that the optical communication device is arranged on the rear side of the navigation antenna. Thanks to the arrangement of the optical communication device and its units on the rear side of the navigation antenna, the radiation side of the latter can be configured and used as is known previously.
    As already mentioned above, optical communication links between navigation satellites are advantageous. For time transfer as well as time adjustment (keyword Composite Clock) and / or for distance measurement and / or for communication, the optical communication device of a navigation satellite can send signals to at least one of the preceding satellites and / or at least one of the following satellites and / or receive corresponding signals.
    According to another aspect of the invention, which can be carried out independently of what has been said previously and without the implementation of the characteristics according to the invention described above, the optical communication device has a third optical communication unit intended for unidirectional or bidirectional signaling with a satellite placed in a lower orbit, in particular on a Low Earth Orbit (LEO). Thanks to this measure, it is possible, despite the two rotations of 180 degrees respectively required per revolution, to permanently establish and maintain an optical link of the navigation satellite in a first orbit with a satellite in a second orbit located lower . The navigation satellite according to the invention is suitably provided for a Medium Earth Orbit (MEO) while the satellite moving lower, and for which it is not necessarily also a navigation satellite, is located by example on a Low Earth Orbit (LEO).
    It is advantageous that the other optical communication unit is also arranged on the rotary retaining element.
    The other (third) optical communication unit is also advantageously located on the rear side of the rotary navigation antenna facing the satellite housing, that is to say the structure of the satellite, insofar as that -this serves as a retaining element for the optical communication device. Thus, the optical axis defined by the third optical communication unit passes through the navigation antenna. To this extent, it is appropriate that the third optical communication unit is pivotally disposed on or respectively in the navigation antenna, which can for example be achieved by a ball joint in which the transmitter and / or the receiver of the third optical communication unit is arranged. It is thus possible to orient the optical communication axis of the third optical communication unit accordingly in order to be able to communicate with a satellite moving lower.
    It is further advantageous that the other optical communication device is placed above the retaining element and that its optical communication axis is directed through an opening in the navigation antenna (and this in particular in the navigation antenna phase center). The axis of rotation of the navigation antenna is advantageously made as a hollow axis. This hollow axis can then for example allow both the passage of the navigation signals from the satellite to the navigation antenna as well as the integration of the third optical communication unit for optical communication between for example the MEO navigation satellite and a LEO satellite.
    It is possible to account for the two main variants according to the invention also by the groups of characteristics mentioned below, individual characteristics of each group of characteristics which can be combined with individual characteristics of another group of characteristics:
    1. Navigation satellite, in particular for a
    Medium Earth Orbit (MEO), with
    a housing, a antenna of navigation arranged in and or sure the housing ave c an axis of radiation destined at influence of signals navigation in a
    direction of radiation,
    - an optical communication device for one-way or two-way communication with at least one other satellite which precedes in the direction of movement and / or with at least one other satellite which follows in the direction of
    displacement, and an element of restraint which is willing on the accommodation in rotation around a axis of rotation
    placed in the direction of radiation,
    - the optical communication device being arranged on the retaining element.
    2. Navigation satellite according to number 1, the navigation antenna being configured as a plate-shaped retainer for the optical communication device.
    3. Navigation satellite according to figure 2, the navigation antenna having a radiation side of navigation signals and a rear side, away from it, which faces the housing, and the optical communication device being arranged on the rear side of the navigation antenna.
    4. Navigation satellite according to one of the digits 1 to
    3, the optical communication device having a first and a second optical communication unit which respectively define an optical communication axis which is oriented essentially at right angles to the axis of rotation.
    5. Navigation satellite according to figure 4, the two optical communication units being, relative to the axis of rotation of the navigation antenna or respectively of the retaining element, arranged essentially diametrically opposite.
    6. Navigation satellite according to one of the digits 1 to
    5, the optical communication device having a third optical communication unit intended for one-way or two-way communication with a satellite placed in a lower orbit, in particular on a Low Earth Orbit (LEO).
    Third navigation satellite according to number 6, the optical communication unit defining an optical communication axis placed in the direction of radiation of the navigation antenna.
    Navigation satellite according to number 7, the optical communication axis of the third optical communication unit extending through an opening in
    The navigation antenna or the retaining element respectively.
    9.
    Navigation satellite according to number 7 or the third optical communication unit being supported on and / or in the housing or on and / or in the navigation antenna in pivoting around the radiation axis in one-dimensional or two-dimensional manner.
    10.
    Navigation satellite according to
    9, the opening being arranged in the phase center of the navigation antenna.
    11. Navigation satellite according to one of the digits 1 to
    10, the axis of rotation of the navigation antenna being configured as a hollow shaft.
    12. Navigation satellite, in particular for a
    Medium Earth Orbit (MEO), with
    - housing,
    - a navigation antenna arranged in and / or on the housing with a radiation axis intended for the radiation of navigation signals in a preferred direction of radiation,
    - an optical communication device intended for unidirectional or bidirectional communication with at least one other satellite which precedes in the direction of movement and / or with at least one other satellite which follows in the direction of displacement,
    the navigation antenna being placed on the housing in rotation about an axis of rotation placed in the extension of the radiation axis, and
    - the optical communication device being installed on the rotary navigation antenna.
    The invention will be explained below in more detail using two embodiments as well as with reference to the drawing. In detail, fig. 1 shows a partial constellation of satellites composed of several MEO navigation satellites and of several LEO satellites moving lower;
    fig. 2 shows a schematic representation of a navigation satellite according to an exemplary embodiment of the invention, part of the navigation satellite being shown in enlarged form, and FIG. 3 shows a second embodiment of a navigation satellite according to the invention, part of the satellite also being shown in enlarged form.
    In the first embodiment of the invention, the optical transmission and reception systems are arranged on a rotary support above the navigation antenna. The rotary support creates an additional axis which makes it possible to maintain the two optical systems oriented towards the preceding or respectively following satellite; they "pass" in front of the navigation antenna, the two optical rays and the direction of the nadir are located in the same plane. This requires only small corrections which can be made with a movable mirror. In addition, the angle in the orbit can be brought to another position in order to illuminate the satellite located after the next one in case the nearest satellite breaks down. The navigation antenna can be mounted on the support. Therefore the azimuthal angle which is measured around the axis of the nadir remains fixed. In particular, the noon-turn and the mid-night-turn do not act on the navigation antenna with regard to the radiation of the signals. What is particularly important is the fixed relationship between the optical orientation and the orientation of the antenna which results from this arrangement.
    Another retaining element of the invention relates to an optical transmission and reception system above the navigation antenna which is arranged so that the ray "looks" through a hole in the center of the antenna . It can in particular be oriented towards one of several satellite positions respectively
    LEO possible (approx. +/- 18 degrees). The optical axis intersects the axis of the nadir. Ideally, this is done in the phase center of the navigation antenna.
    Fig. 1 shows a partial constellation of satellites composed of several MEO 10, 10 ', 10' 'navigation satellites and several LEO 11 satellites. Each navigation satellite 10, 10', 10 '' comprises a structure of the satellite with inter alia a housing 12 and solar generators 14, and is provided with a rotating navigation antenna 16 which maintains its orientation towards the Earth. The navigation antenna 16 has a front radiation side 16 'and a rear side 16' 'rear. On the rear side 16 '' of the rotary navigation antenna 16 (see the axis of rotation indicated by 17) are mounted optical communication units 18, 20 (with optical communication axes 19 or respectively 21) of an optical communication device 22 which guarantees an optical inter-satellite link with the preceding satellite and with the following satellite 10 ', 10' '.
    Fig. 2 shows a detailed representation of the constitution of the rotary navigation antenna 16 together with the optical communication units 18, 20. In this case, the navigation antenna 16 is rotated in its phase center 24 around a hollow axis 26 which allows both the passage of signals from the satellite to the navigation antenna 16 and the integration of another optical communication unit for communication between a MEO satellite 10, 10 ′,
    10 '' and LEO 11 satellites.
    The third additional optical communication unit described above is shown in the embodiment of the MEO navigation system shown in FIG. 3. Insofar as the elements of the satellite according to FIG. 3 correspond to those of the satellite according to FIG. 2, they are provided with the same references. The third additional optical communication unit 28 is, for example, placed above the navigation antenna 16, that is to say on its rear side 16 ''. Its optical communication axis 30 crosses the phase center 24 of the navigation antenna 16. Thanks to the use of a compact construction, it is possible to ensure that the opening 32 necessary for this purpose in the antenna navigation 16 has no influence on its radiation characteristic and that at the same time an optical communication link with a LEO satellite 11 evolving lower can be established. Depending on the trajectory geometry, the third optical communication unit must cover only a limited angular range and can thus be integrated inside the navigation antenna 16 as shown in FIG. 3.
    LIST OF REFERENCES
    10 '
    10 ''
    16 '
    16 ''
    Navigation satellites
    Navigation satellites
    Navigation satellites
    LEO Satellite
    Housing
    Solar generators
    Navigation antenna
    Radiation side of the navigation antenna
    Rear side of the navigation antenna
    Rotation axis
    First optical communication unit
    Optical communication axis
    Second optical communication unit
    Optical communication axis
    Optical communication device
    Phase center
    Hollow axis
    Third optical communication unit
    Communication way
    Opening in the phase center
    权利要求:
    Claims (4)
    [1]
    1. Navigation satellite, in particular for a
    Medium Earth Orbit (MEO), with a housing (12), a navigation antenna (16) connected to the housing (12) for the radiation of navigation signals in a preferred direction, an optical communication device (22) for unidirectional or bidirectional signaling with at least one other satellite, which precedes in the direction of movement, towards a first communication axis (19) and / or with at least one other satellite, which follows in the direction of movement, towards a second communication axis (20), and a retaining element which is arranged in rotation on the housing around an axis of rotation (17), the optical communication device (22) being arranged on the retainer.
    [2]
    2. Navigation satellite according to claim 1,
    characterized in what 1'antenne navigation ( 16) serves as element restraint for the device of communication optical (22) or is willing sure the element of re outfit. Navigation satellite according to 1 to claim 2 characterized in what 1'antenne navigation ( 16)
    has a radiation side for navigation signals (16 ') and a rear side (16' '), remote from it, which faces the housing (12), and in that the optical communication device (22) is arranged on the rear side (16 '') of the navigation antenna (16).
    [3]
    4. Navigation satellite according to one of claims 1 to 3, characterized in that, for time transfer as well as time adjustment and / or for distance measurement and / or for communication, the optical communication device (22) sends signals to at least one of the preceding satellites and / or to at least one of the following satellites and / or receives such signals
    from at least one of the satellites who previous and / or from at minus one of the satellites that follow. 5. Satellite navigation according to 1 'a of the
    Claims 1 to 4, characterized by another optical communication device (22) intended for one-way or two-way signaling with a satellite placed in a lower orbit, in particular on a Low Earth
    Orbit (LEO),communication towards a third axis(28). of 6. Satellite of navigation by claim 5 characterized in that the other device of communication optics (28) is also willing sure The element of rotary retainer.7. Satellite of navigation by claim 5 or 6 and either claim 3, either one of the previous claims, insofar as it depends on claim 3, characterized in that than
    the other optical communication device (28) is disposed above the retaining element and is directed through an opening in the navigation antenna (16) for unidirectional or bidirectional signaling with its communication axis (28 ).
    [4]
    5 8. Navigation satellite according to claim 7, characterized in that the opening is arranged in the phase center of the navigation antenna (16).
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    法律状态:
    2019-06-21| PLFP| Fee payment|Year of fee payment: 2 |
    2019-10-11| PLSC| Search report ready|Effective date: 20191011 |
    2020-06-19| PLFP| Fee payment|Year of fee payment: 3 |
    2021-06-29| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    DE102017212092.4|2017-07-14|
    DE102017212092|2017-07-14|
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