A satellite structure provided with a momentum ball device

Abstract

An embodiment of the present invention discloses a satellite structure provided with a momentum ball device. The momentum ball device includes a sphere and six stators arranged on both sides of the sphere in the transverse, longitudinal, and vertical directions. The satellite structure includes: six central plates for correspondingly fixing the six stators and jointly forming a closed first cube; first-type rods vertically fixed at each corner of each face of the first cube; six second-type rod groups corresponding to the six faces of the first cube respectively. Each second-type rod group includes two second-type rods parallel to each other. Each second-type rod is fixed to the ends of two adjacent first-type rods and is perpendicular to the two second-type rods corresponding to two adjacent faces of the first cube respectively; six outer plates, each outer plate is fixed to each second-type rod in a single second-type rod group, and the six outer plates jointly form a closed second cube.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite attitude control, and in particular to a satellite structure provided with a momentum ball device. Background Art

[0002] For the attitude control of a satellite, a momentum exchange actuator can be used to achieve this, and for this purpose, 4 to 6 actuating components need to be installed to achieve redundant control. However, with the increasing requirements for attitude control accuracy, especially for micro-nano satellites performing rapid emergency tasks, the vibration of the satellite structure mechanism caused by the above-mentioned momentum exchange actuator can no longer meet the satellite attitude control accuracy requirements. At present, there is also a control method based on an inductive momentum ball device as an actuator to change the attitude of the satellite. This method can quickly realize the attitude maneuver control of the satellite in any direction by rotating the spherical rotor of the momentum ball in any direction of the three axes. The satellite structure and satellite based on the inductive momentum ball as an actuator have the advantages of simple structure mechanism, small weight, and strong attitude rapid maneuverability.

[0003] Specifically, the inductive momentum ball device includes a spherical rotor and six bowl-shaped stators arranged on the periphery of the spherical rotor. A disc-shaped winding is arranged in the stator. By passing three-phase alternating current through the winding, a rotating magnetic field that changes with time can be generated in the space near the stator. This magnetic field can generate an induced current in the ferromagnetic conductor spherical rotor, and the induced current generates a suspension force and a torque under the action of the magnetic field force, thereby driving the spherical rotor to rotate and suspend. When the six stators of the momentum ball are simultaneously energized, the spherical rotor in the center can be rotated in any direction of the three axes, so as to realize the attitude control of any angle of the satellite and the cancellation of the attitude disturbance torque.

[0004] On the other hand, a satellite generally includes a housing that defines an accommodation space and various satellite single units accommodated in the accommodation space. In this case, how to combine or assemble the above-mentioned inductive momentum ball device into the satellite in a simple, easy-to-implement and low-cost manner, so that the momentum ball device does not interfere with the accommodation space of various satellite single units and can achieve attitude control in an advantageous manner has become an urgent problem to be solved at present. Summary of the Invention

[0005] To solve the above technical problems, an embodiment of the present invention expects to provide a satellite structure provided with a momentum ball device, which can realize attitude control in any direction by rotating the momentum ball while combining the momentum ball device in the satellite in the simplest way.

[0006] The technical solution of the present invention is implemented as follows:

[0007] An embodiment of the present invention provides a satellite structure provided with a momentum ball device. The momentum ball device includes a sphere and six stators arranged on both sides of the sphere in the transverse, longitudinal, and vertical directions. The satellite structure includes:

[0008] Six central plates for correspondingly fixing the six stators and jointly forming a closed first cube;

[0009] First-type rods vertically fixed at each corner of each face of the first cube;

[0010] Six second-type rod groups corresponding to the six faces of the first cube respectively. Each second-type rod group includes two second-type rods parallel to each other. Each second-type rod is fixed at the ends of two adjacent first-type rods and the two second-type rods corresponding to two adjacent faces of the first cube are perpendicular to each other;

[0011] Six peripheral plates, each peripheral plate is fixed to each second-type rod in a single second-type rod group, and the six peripheral plates jointly form a closed second cube.

[0012] An embodiment of the present invention provides a satellite structure provided with a momentum ball device. While being able to set the momentum ball device, a satellite architecture with perfect functions is obtained only through four types of components, namely central plates, first-type rods, second-type rods, and peripheral plates. For example, satellite single machines can be installed in the space between the shells of the first cube and the second cube. Thus, when producing such a satellite structure, only four types of components need to be manufactured, which greatly simplifies the production process of the satellite structure and reduces the production cost. Moreover, the momentum ball device is installed at the geometric center of the satellite structure, so attitude control can be achieved in an advantageous manner. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 A three-dimensional schematic diagram of a satellite structure according to an embodiment of the present invention;

[0014] Figure 2 A three-dimensional schematic diagram of a momentum ball device applied to an embodiment of the present invention;

[0015] Figure 3 A three-dimensional schematic diagram of a stator of the momentum ball device fixed to a central plate of a satellite structure according to an embodiment of the present invention;

[0016] Figure 4 A three-dimensional schematic diagram showing the central plate, first-type rods, and second-type rods of a satellite structure according to an embodiment of the present invention;

[0017] Figure 5Schematic three-dimensional view of the first type of rod of the satellite structure according to an embodiment of the present invention;

[0018] Figure 6 Schematic three-dimensional view of the second type of rod of the satellite structure according to an embodiment of the present invention;

[0019] Figure 7 Schematic three-dimensional view of the mounting plate of the satellite structure according to an embodiment of the present invention;

[0020] Figure 8 Schematic three-dimensional view showing the positional relationship between two side plates of two first type of rods suitable for mounting the mounting plate in the satellite structure according to an embodiment of the present invention;

[0021] Figure 9 Schematic three-dimensional view showing that the mounting plate is mounted to Figure 8 two side plates in;

[0022] Figure 10 Schematic three-dimensional view showing the mutual positional relationship between each satellite unit and the central plate mounted to the satellite structure according to an embodiment of the present invention;

[0023] Figure 11 Schematic three-dimensional view of the peripheral plate of the satellite structure according to an embodiment of the present invention;

[0024] Figure 12 Schematic three-dimensional view of the satellite structure according to another embodiment of the present invention, in which the solar panel is shown in the deployed state;

[0025] Figure 13 For Figure 12 the schematic three-dimensional view of the satellite structure shown in, in which the solar panel is shown in the folded state. Detailed implementation manners

[0026] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention.

[0027] See Figure 1 and in conjunction with Figures 2 to 4 , the embodiments of the present invention provide a satellite structure 1 provided with a momentum ball device 10 as shown in Figure 2 , specifically referring to Figure 2 , the momentum ball device 10 includes a sphere 11 and six stators 12 arranged on both sides of the sphere 11 in the transverse X, longitudinal Y and vertical Z directions of the sphere 11, and the satellite structure 1 may include:

[0028] As shown in Figure 1 and in Figure 3Six central plates 20 shown more specifically therein for fixing the six stators 12 accordingly and jointly forming a closed first cube C1, whereby all the central plates 20 are identical or can be obtained by "copying", wherein in Figure 3 Only three central plates 20 are shown therein for clarity purposes. Exemplarily, the stator 12 can be bonded to the central plate 20 by high-strength steel bonding adhesive. Additionally, as shown in Figure 3 A driver 30 for driving the momentum ball device 10 to operate or for rotating the sphere 11 by the stator 12 can be provided on one of the central plates 20 forming the first cube C1;

[0029] As shown in Figure 1 and shown more specifically in Figure 4 Type-1 rods 40 vertically fixed at each corner of each face of the first cube C1, that is to say, the satellite structure 1 altogether includes 24 type-1 rods 40. Here, "type-1" means that all the type-1 rods 40 are also identical or can be obtained by "copying";

[0030] As shown in Figure 1 and shown more specifically in Figure 4 Six type-2 rod groups G corresponding to the six faces of the first cube C1 accordingly. Each type-2 rod group G includes two type-2 rods 50 parallel to each other. That is to say, the satellite structure 1 altogether includes 12 type-2 rods 50. Here, "type-2" means that all the type-2 rods 50 are also identical or can be obtained by "copying". Each type-2 rod 50 is fixed to the ends of two adjacent type-1 rods 40. As shown in Figure 4 In it, the type-2 rod 50-1 is fixed to the ends of the type-1 rods 40-1 and 40-2. Other type-2 rods 50 are similar and will not be elaborated here. And two type-2 rods 50 corresponding to two adjacent faces of the first cube C1 are perpendicular to each other. As shown in Figure 4 In it, if the face of the first cube C1 corresponding to the type-2 rod 50-1 and the face of the first cube C1 corresponding to the type-2 rod 50-2 are adjacent or not opposite, then the type-2 rod 50-1 is perpendicular to the type-2 rod 50-2. Other type-2 rods 50 are similar and will not be elaborated here;

[0031] As shown in Figure 1 Six peripheral plates 60 shown therein, wherein in Figure 1For the sake of clarity, only three peripheral plates 60 are shown, and each peripheral plate 60 is fixed to each second-type rod 50 in a single second-type rod group G. The six peripheral plates 60 together form a closed second cube C2. Thus, all the peripheral plates 60 are identical or can be obtained by "copying".

[0032] In the satellite structure 1 according to an embodiment of the present invention, while the momentum ball device 10 can be provided, a satellite architecture with perfect functions is obtained only by four types of components, namely, the central plate 20, the first-type rod 40, the second-type rod 50, and the peripheral plate 60. For example, satellite single units can be installed in the space between the shells of the first cube C1 and the second cube C2. Thus, when manufacturing such a satellite structure 1, only four types of components need to be manufactured, greatly simplifying the production process of the satellite structure 1 and reducing the production cost. Moreover, the momentum ball device 10 is installed at the geometric center of the satellite structure 1, so attitude control can be achieved in an advantageous manner.

[0033] Exemplarily, the side length of the first cube C1 can be 10 cm, the side length of the second cube C2 can be 30 cm accordingly, and the distance between the central plate 20 and the peripheral plate 60 facing each other is 10 cm.

[0034] Preferably, the first-type rod 40 and the second-type rod can be made of aluminum alloy.

[0035] Preferably, the mounting plate central plate 20 and the peripheral plate 60 can be aluminum honeycomb sandwich structure plates. The advantages are that the honeycomb sandwich structure has great bending rigidity, excellent airtightness and heat insulation, and large structural attenuation, so that the damage caused by impact can be confined to a local area, and thus the crack is difficult to expand.

[0036] See Figure 5 and in combination with Figure 1 or Figure 4 , the first-type rod 40 can include a first end plate 41 perpendicular to the longitudinal direction 40L of the first-type rod 40 at the end opposite to the end. The first-type rod 40 is fixed in such a way that the first end plate 41 is in contact with the central plate 20. In this way, the fixation is achieved in the way of "surface-to-surface contact", so that the fixation between the first-type rod 40 and the central plate 2 can be made more firm or stable. For the specific fixation method, for example, the first end plate 41 can be glued to the central plate 20, or threaded holes 41H can be formed in the first end plate 41 and threaded holes (not shown in the drawings) can be formed in the central plate 20 to achieve fixation by screws (not shown in the drawings).

[0037] Continue to refer to Figure 5 and in combination with Figure 1 or Figure 4, the first type rod 40 may further include a second end plate 42 at the end perpendicular to the longitudinal direction of the first type rod 40, and then see Figure 6 and combined Figure 1 or Figure 4 The second-type rod 50 has a first fixing plane 51 and is fixed in such a manner that the first fixing plane 51 abuts against the second end plate 42. In this way, a "surface-to-surface" fixation is also achieved, thereby making the fixation between the second-type rod 50 and the first-type rod 40 more secure or stable. For specific fixing methods, for example, the first fixing plane 51 can be glued to the second end plate 42, or threaded holes 42H can be formed in the second end plate 42 and threaded holes 50H can be formed in the second-type rod 50, so that fixation can be achieved using screws (not shown in the drawings).

[0038] Still see Figure 5 and combined Figure 1 or Figure 4 The first type rod 40 may be in the shape of a rectangular parallelepiped as a whole and further include two side panels 43 adjacent to each other. The first type rod 40 is fixed in such a manner that the two side panels 43 are coplanar with the corresponding surfaces of the first cube C1, and see Figure 7 and combined Figure 8 、 Figure 9 and Figure 10 The satellite structure 1 further comprises a mounting plate 70 for mounting a satellite subsystem unit 80, the mounting plate 70 being fixed to the two side plates 43 of the two first type rods 40 in the same plane, as in Figure 8 As shown in the figure, the side panels 43-1 and 43-2 are in the same plane, the side panels 43-2 and 43-3 are in the same plane, and the side panels 43-3 and 43-4 are in the same plane. Figure 9 The three mounting plates 70 can be fixed between the side plates 43-1 and 43-2, between the side plates 43-2 and 43-3, and between the side plates 43-3 and 43-4, respectively. In this way, a "face-to-face" fixation is also achieved, thereby making the fixation between the mounting plates 70 and the first type rods 40 more secure or stable. As for the specific fixing method, for example, the mounting plates 70 can be glued to the side plates 43, or threaded holes 70H can be formed in the mounting plates 70 and threaded holes 43H can be formed in the side plates 43 to achieve fixation by screws (not shown in the drawings). For details, see Figure 10 The satellite subsystem unit 80 may include a measurement, control and data transmission integrated unit 80-1, an integrated electronic module 80-2, a lithium-ion battery 80-3 and a payload module 80-4, etc. Figure 10For the sake of clarity, only the positional relationship of various satellite subsystem single units 80 relative to the first cube C1 is shown, while the first type of rod 40 and the second type of rod 50 are omitted, for example.

[0039] In the above case, by way of example, the length of the first type of rod 50 can be 95 mm, the width and height can be equal at 10 mm. That is to say, the first end plate 41 and the second end plate 42 can be square as a whole, the thickness of these two plates can be 2 mm, and the thickness of the side plate 43 can be 1 mm.

[0040] Preferably, the mounting plate 70 can also be an aluminum honeycomb sandwich structure plate. Preferably, the satellite subsystem single unit 80 can be fixed to the embedded parts of the mounting plate 70 by screws, and heat pipes for thermal control can be laid at appropriate positions on the surface of the mounting plate 70.

[0041] Refer back to Figure 7 The mounting plate 70 can include a plate body 71 and a limiting member 72 provided on the plate body 71 for limiting the cables (not shown in the drawings) of the satellite subsystem single unit 80. Among them, the limiting member 72 and the plate body 71 together define a channel 70T, and the cables are limited by passing through the channel 70T.

[0042] Refer back to Figure 7 and in combination with Figure 1 The second type of rod 50 can also have a second fixing plane 52 parallel to the first fixing plane 51, and the peripheral plate 60 is fixed in a manner of fitting with the second fixing plane 52. Similarly, since the fixing is also achieved in the way of "surface-to-surface fitting", the fixing between the peripheral plate 60 and the second type of rod 50 is more firm or stable, which will not be elaborated here.

[0043] Preferably, the second type of rod 50 can be generally in the shape of a cuboid. By way of example, the length of the second type of rod 50 can be 300 mm, the width can be 10 mm, and the height can be 5 mm.

[0044] Refer to Figure 11 and in combination with Figure 1 The peripheral plate 60 can include a plate body 61 and reinforcing ribs 62 provided at two edges of the plate body 61. The two edges are parallel to the second type of rod 50 to which the peripheral plate 60 is fixed, and two adjacent reinforcing ribs 62 in the satellite structure 1 are fixed to each other, as shown by the fixing of the reinforcing ribs 62-1 and 62-2 shown in Figure 1 In this way, the satellite structure 1 includes a total of 12 reinforcing ribs 62, and they respectively correspond to the 12 edges of the second cube C2. Thus, not only the strength of each peripheral plate 60 can be enhanced, but also the stability of the second cube C2 formed by the six peripheral plates 60 can be enhanced.

[0045] Preferably, the length of the reinforcing rib 62 can be 290 mm, and the width and height can both be 5 mm.

[0046] See Figure 11 and Figure 6 and in combination with Figure 1 , the reinforcing rib 62 can be formed with a concave joint portion 62E, and a convex joint portion 50E for cooperating with the concave joint portion 62E is formed at the end of the second type of rod 50. Thus, through the cooperation between the reinforcing rib 62 and the second type of rod 50, the stability of the second cube C2 formed by the six peripheral plates 60 is further enhanced.

[0047] Preferably, the depth at which the concave joint portion 62E is recessed into the reinforcing rib 62 can be 2 mm.

[0048] See Figure 12 and Figure 13 , the satellite structure 1 may further include a solar panel 90, and the solar panel is hinged on the peripheral plate 60 so as to be capable of switching between a folded state in which it fits against the peripheral plate 60 as shown in Figure 13 and an unfolded state in which it does not fit against the peripheral plate 60 as shown in Figure 12 . Thus, in the launch phase, the solar panel 90 can be in the folded state to reduce the accommodation space for easy launch, and in the operation phase, the solar panel 90 can be in the unfolded state to receive sunlight irradiation to obtain electric energy.

[0049] Continuing to refer to Figure 12 and Figure 13 , the solar panel 90 may include at least two panel units 91, where Figure 12 and Figure 13 exemplarily shows two panel units 91, and the at least two panel units 91 are hinged to each other so that the solar panel 90 can switch between a folded state in which the at least two panel units 91 fit against each other as shown in Figure 13 and an unfolded state in which the at least two panel units 91 do not fit against each other as shown in Figure 12 . Thus, similarly, in the launch phase, the at least two panel units 91 can be in the folded state to reduce the accommodation space for easy launch, and in the operation phase, the at least two panel units 91 can be in the unfolded state to receive sunlight irradiation to obtain electric energy.

[0050] It should be noted that: among the technical solutions recorded in the embodiments of the present invention, they can be arbitrarily combined without conflict.

[0051] As described above, it is only the specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily think of changes or substitutions, which should all be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims described above.

Claims

1. A satellite structure provided with a momentum ball device, the momentum ball device comprising a sphere and six stators arranged on both sides of the sphere in the transverse, longitudinal, and vertical directions of the sphere, characterized in that, The satellite structure includes: Six central plates for correspondingly fixing the six stators and jointly forming a closed first cube; First-type rods vertically fixed at each corner of each face of the first cube; Six second-type rod groups correspondingly corresponding to the six faces of the first cube, each second-type rod group including two second-type rods parallel to each other, each second-type rod being fixed to the ends of two adjacent first-type rods, and the two second-type rods corresponding to two adjacent faces of the first cube being perpendicular to each other; Six peripheral plates, each peripheral plate being fixed to each second-type rod in a single second-type rod group, and the six peripheral plates jointly forming a closed second cube, wherein the first-type rods and the second-type rods are made of aluminum alloy.

2. The satellite structure according to claim 1, characterized in that The first-type rod includes a first end plate perpendicular to the longitudinal direction of the first-type rod at an end opposite to the end, and the first-type rod is fixed in such a way that the first end plate is in contact with the central plate.

3. The satellite structure according to claim 2, characterized in that, The first-type rod further includes a second end plate perpendicular to the longitudinal direction of the first-type rod at the end, and the second-type rod has a first fixing plane and is fixed in such a way that the first fixing plane is in contact with the second end plate.

4. The satellite structure according to claim 3, characterized in that, The first-type rod is integrally in the shape of a cuboid and further includes two side plates adjacent to each other. The first-type rod is fixed in such a way that the two side plates are coplanar with the corresponding faces of the first cube respectively, and the satellite structure further includes a mounting plate for mounting a satellite subsystem unit, and the mounting plate is fixed to the two side plates in the same plane of the two first-type rods.

5. The satellite structure according to claim 4, characterized in that, The mounting plate includes a plate body and a limiting member provided on the plate body for limiting the cables of the satellite subsystem unit. Wherein, the limiting member and the plate body together define a channel, and the cables are limited by passing through the channel.

6. The satellite structure according to claim 3, characterized in that, The second-type rod further has a second fixing plane parallel to the first fixing plane, and the peripheral plate is fixed in such a way that it is in contact with the second fixing plane.

7. The satellite structure according to claim 1, characterized in that The peripheral plate includes a plate body and reinforcing ribs provided at two edges of the plate body. The two edges are parallel to the second-type rod to which the peripheral plate is fixed, and adjacent reinforcing ribs in the satellite structure are fixed to each other.

8. The satellite structure according to claim 7, wherein The reinforcing rib is formed with a concave engaging portion, and a convex engaging portion for cooperating with the concave engaging portion is formed at the end of the second-type rod.

9. The satellite structure according to claim 1, wherein, The satellite structure further includes a solar panel, and the solar panel is hinged to the peripheral plate so as to be able to switch between a folded state in contact with the peripheral plate and an unfolded state not in contact with the peripheral plate.

10. The satellite structure according to claim 9, characterized in that, The solar panel includes at least two panel units, and the at least two panel units are hinged to each other so that the solar panel can switch between a folded state in which the at least two panel units are in contact with each other and an unfolded state in which the at least two panel units are not in contact with each other.

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