Attitude control module and micro-nano satellite

Abstract

The attitude control module comprises a frame, a momentum wheel assembly, a magnetic torquer assembly and a gyroscope, the frame comprises a bottom plate, a top plate and a plurality of side face supporting frames, the bottom plate and the top plate are arranged in parallel, the plurality of side face supporting frames are arranged along the circumferential direction of the bottom plate at intervals, and the momentum wheel assembly and the magnetic torquer assembly are arranged in parallel. Two ends of the side supporting frame are fixedly connected with the bottom plate and the top plate respectively; the momentum wheel assembly, the magnetic torquer assembly and the gyroscope are all fixed in an area defined by the side face supporting frames. The micro-nano satellite comprises the attitude control module. The attitude control module has the beneficial effects that the attitude control module adopts a modular structure and can be directly mounted on the micro-nano satellite, so that the steps during configuration and layout of the micro-nano satellite can be reduced, an attitude control subsystem can be quickly mounted during satellite assembly, and the final assembly time of the whole satellite is shortened. The attitude control module is high in integration level, and is especially suitable for micro-nano satellites with limited space.

Description

Technical Field

[0001] The utility model relates to the field of micro-nano satellites, and particularly relates to an attitude control module and a micro-nano satellite. Background Art

[0002] With the development of space technology, the demand for satellites is increasing, and spacecraft technology is becoming more and more mature. The attitude control system (abbreviated as attitude control) is a subsystem of a spacecraft and an important part of the spacecraft; the attitude control system refers to a system for controlling the attitude of a spacecraft, and its basic task is to ensure that the spacecraft has good stability and operability during flight.

[0003] For micro-nano satellites, the internal space is limited, the equipment layout is relatively compact, and the number of devices in the attitude control system is large. The assembly process is cumbersome, difficult, and inefficient. Summary of the Utility Model

[0004] The technical problem to be solved by the utility model is how to improve the assembly efficiency of the attitude control system.

[0005] The technical solution of the utility model to solve the above technical problem is as follows: An attitude control module includes a frame, a momentum wheel assembly, a magnetic torque actuator assembly, and a gyroscope. The frame includes a bottom plate, a top plate, and side support frames. The bottom plate and the top plate are arranged in parallel. There are multiple side support frames, and the multiple side support frames are arranged at intervals along the circumference of the bottom plate. Two ends of each side support frame are respectively fixedly connected to the bottom plate and the top plate; the momentum wheel assembly, the magnetic torque actuator assembly, and the gyroscope are all fixed in the area surrounded by the multiple side support frames.

[0006] The beneficial effect of the utility model is that the momentum wheel assembly, the magnetic torque actuator assembly, and the gyroscope are integrated in the frame to form an attitude control module. The modular structure can be directly installed on the micro-nano satellite without the need for separate installation of the momentum wheel assembly, the magnetic torque actuator assembly, and the gyroscope. It can reduce the steps in the configuration layout of the micro-nano satellite, and the attitude control subsystem can be quickly installed during satellite assembly, which can shorten the overall assembly time of the whole satellite to a certain extent. Moreover, the attitude control module has a high integration degree and is especially suitable for micro-nano satellites with limited space. Among them, the momentum wheel assembly, the magnetic torque actuator assembly, and the gyroscope are used to realize the attitude control of the satellite.

[0007] On the basis of the above technical solution, the utility model can be further improved as follows.

[0008] Further, the momentum wheel assembly includes a first momentum wheel, a second momentum wheel, a third momentum wheel, and a fourth momentum wheel. The axes of the first momentum wheel, the second momentum wheel, and the third momentum wheel are perpendicular to each other in pairs, and the axis of the fourth momentum wheel is inclined with respect to the axis of the first momentum wheel, the second momentum wheel, or the third momentum wheel.

[0009] Furthermore, the frame includes a first momentum wheel mounting bracket, a second momentum wheel mounting bracket, and an obliquely mounted momentum wheel bracket. The first momentum wheel mounting bracket is located between the bottom plate and the top plate, and its two ends are respectively fixedly connected to the bottom plate and the top plate. The second momentum wheel mounting bracket is located between the bottom plate and the top plate, and the two ends of the second momentum wheel mounting bracket are respectively fixedly connected to the bottom plate and the top plate. The first momentum wheel mounting bracket and the second momentum wheel mounting bracket are perpendicular to each other. The second momentum wheel is fixedly connected to the second momentum wheel mounting bracket, and the first momentum wheel is fixedly connected to the first momentum wheel mounting bracket; the third momentum wheel is fixedly connected to the bottom plate; the obliquely mounted momentum wheel bracket is fixedly connected to the bottom plate and has a mounting inclined surface, and the fourth momentum wheel is fixed on the mounting inclined surface.

[0010] The beneficial effects of adopting the above further solution are as follows: The four momentum wheels are respectively mounted on the brackets or the bottom plate in corresponding directions, and the assembly and positioning are accurate and convenient. The third momentum wheel is directly mounted on the bottom plate, saving the number of brackets and making the module lightweight.

[0011] Furthermore, the first momentum wheel, the second momentum wheel, the third momentum wheel, and the fourth momentum wheel are evenly distributed along the circumferential direction of the bottom plate.

[0012] Furthermore, the magnet torque actuator assembly includes a first magnet torque actuator, a second magnet torque actuator, and a third magnet torque actuator, and the axes of the first magnet torque actuator, the second magnet torque actuator, and the third magnet torque actuator are perpendicular to each other pairwise.

[0013] Furthermore, the first magnet torque actuator is fixed on the second momentum wheel mounting bracket, the second magnet torque actuator is fixed on the bottom plate, and the third magnet torque actuator is fixed on the top plate.

[0014] The beneficial effects of adopting the above further solution are as follows: The first magnet torque actuator shares the second momentum wheel mounting bracket with the second momentum wheel, and the second magnet torque actuator and the third magnet torque actuator are directly mounted on the bottom plate and the top plate, saving the number of brackets and being beneficial to the lightweight design of the module. The three magnet torque actuators are installed using the assembly gaps of the four momentum wheels, and the overall structure of the attitude control module is compact and has a high integration degree.

[0015] Furthermore, both the first momentum wheel mounting bracket and the second momentum wheel mounting bracket are rectangular plates, and both are provided with relief grooves and stiffening ribs; the side support frame is a rectangular plate and has side frame weight reduction holes.

[0016] The beneficial effects of adopting the above further scheme are as follows: The relief slots are used to reduce the weight of the first momentum wheel mounting bracket and the second momentum wheel mounting bracket, and the reinforcing ribs increase the support strength of both. The frame structure formed by the side support frames, the top plate and the bottom plate is used to install, support and protect the internal momentum wheel assembly, magnetic torque actuator assembly and gyroscope. The side support frames are provided with side frame weight reduction holes to reduce the weight of the entire module.

[0017] Further, the gyroscope is fixed on the top plate.

[0018] The beneficial effects of adopting the above further scheme are as follows: The gyroscope is directly assembled on the top plate, and the attitude control module has a compact structure.

[0019] Further, the bottom plate has a plurality of mounting ears.

[0020] The beneficial effects of adopting the above further scheme are as follows: The bottom plate is installed on the micro-nano satellite through a plurality of mounting ears.

[0021] The present utility model also provides a micro-nano satellite, including the attitude control module described above. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 is a three-dimensional view of the attitude control module of the present utility model;

[0023] Figure 2 is a top view of the attitude control module of the present utility model after removing the top plate;

[0024] Figure 3 is an exploded view of the frame of the present utility model;

[0025] Figure 4 is a three-dimensional view of the bottom plate of the present utility model;

[0026] Figure 5 is a three-dimensional view of the top plate of the present utility model;

[0027] Figure 6 is an exploded view of the attitude control module of the present utility model.

[0028] In the drawings, the list of components represented by each reference numeral is as follows:

[0029] 1. Frame; 101. Bottom plate; 102. Top plate; 103. First momentum wheel mounting bracket; 104. Second momentum wheel mounting bracket; 105. Obliquely mounted momentum wheel bracket; 106. Side support frame; 2. First momentum wheel; 3. Second momentum wheel; 4. Third momentum wheel; 5. Fourth momentum wheel; 6. First magnetic torque actuator; 7. Second magnetic torque actuator; 8. Third magnetic torque actuator; 9. Gyroscope. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0030] The principles and features of the present utility model will be described below in conjunction with the accompanying drawings. The examples given are only used to explain the present utility model and are not intended to limit the scope of the present utility model.

[0031] As Figures 1-6 shown, this embodiment provides an attitude control module, which includes a frame 1, a momentum wheel assembly, a magnetic torque actuator assembly, and a gyro 9. The frame 1 includes a bottom plate 101, a top plate 102, and side support frames 106. The bottom plate 101 and the top plate 102 are arranged in parallel. There are multiple side support frames 106, and the multiple side support frames 106 are arranged at intervals along the circumference of the bottom plate 101. Both ends of the side support frame 106 are fixedly connected to the bottom plate 101 and the top plate 102 respectively; the momentum wheel assembly, the magnetic torque actuator assembly, and the gyro 9 are all fixed within the area surrounded by the multiple side support frames 106.

[0032] The momentum wheel assembly, the magnetic torque actuator assembly, and the gyro 9 are integrated within the frame 1 to form an attitude control module. The modular structure can be directly installed on a nano-satellite without the need for separate installation of the momentum wheel assembly, the magnetic torque actuator assembly, and the gyro 9. It can reduce the steps in the configuration layout of the nano-satellite and enable the rapid installation of the attitude control subsystem during satellite assembly, which can, to a certain extent, shorten the overall assembly time of the entire satellite. Moreover, the attitude control module has a high integration degree and is particularly suitable for nano-satellites with limited space. Among them, the momentum wheel assembly, the magnetic torque actuator assembly, and the gyro 9 are used to achieve the attitude control of the satellite.

[0033] Optionally, the bottom plate 101 is a polygonal or circular plate. In one specific example, the bottom plate 101 is rectangular; the top plate 102 is a polygonal or circular plate. In one specific example, the top plate 102 is rectangular.

[0034] Specifically, both the top surface and the bottom surface of the side support frame 106 have bolt holes and are fixedly connected to the bottom plate 101 and the top plate 102 through bolts.

[0035] On the basis of the above solution, the momentum wheel assembly includes a first momentum wheel 2, a second momentum wheel 3, a third momentum wheel 4, and a fourth momentum wheel 5. The axes of the first momentum wheel 2, the second momentum wheel 3, and the third momentum wheel 4 are perpendicular to each other in pairs, and the axis of the fourth momentum wheel 5 is inclined with respect to the axis of the first momentum wheel 2, the second momentum wheel 3, or the third momentum wheel 4.

[0036] Specifically, the axes of the first momentum wheel 2, the second momentum wheel 3, and the third momentum wheel 4 are orthogonal to each other in pairs, that is, the axes of the first momentum wheel 2, the second momentum wheel 3, and the third momentum wheel 4 are arranged along the X, Y, and Z directions of the rectangular coordinate system respectively.

[0037] Based on the above solution, the frame 1 includes a first momentum wheel mounting bracket 103, a second momentum wheel mounting bracket 104, and an obliquely mounted momentum wheel bracket 105. The first momentum wheel mounting bracket 103 is located between the bottom plate 101 and the top plate 102, and its two ends are respectively fixedly connected to the bottom plate 101 and the top plate 102. The second momentum wheel mounting bracket 104 is located between the bottom plate 101 and the top plate 102, and the two ends of the second momentum wheel mounting bracket 104 are respectively fixedly connected to the bottom plate 101 and the top plate 102. The first momentum wheel mounting bracket 103 and the second momentum wheel mounting bracket 104 are perpendicular to each other. The second momentum wheel 3 is fixedly connected to the second momentum wheel mounting bracket 104, and the first momentum wheel 2 is fixedly connected to the first momentum wheel mounting bracket 103; the third momentum wheel 4 is fixedly connected to the bottom plate 101; the obliquely mounted momentum wheel bracket 105 is fixedly connected to the bottom plate 101 and has an installation inclined surface, and the fourth momentum wheel 5 is fixed on the installation inclined surface.

[0038] The four momentum wheels are respectively mounted on the brackets or the bottom plate 101 in corresponding directions, and the assembly positioning is accurate and convenient. The third momentum wheel 4 is directly mounted on the bottom plate 101, saving the number of brackets and making the module lightweight.

[0039] Specifically, the bottom and top of the first momentum wheel mounting bracket 103 are both provided with threaded holes, and the first momentum wheel mounting bracket 103 is connected to the bottom plate 101 and the top plate 102 by bolts. The bottom and top of the second momentum wheel mounting bracket 104 are both provided with threaded holes, and the second momentum wheel mounting bracket 104 is connected to the bottom plate 101 and the top plate 102 by bolts.

[0040] Specifically, the obliquely mounted momentum wheel bracket 105 is triangular in shape and has triangular weight-reducing through holes. There are four threaded holes at the bottom of the obliquely mounted momentum wheel bracket 105. After installing the fourth momentum wheel 5 onto the obliquely mounted momentum wheel bracket 105, the obliquely mounted momentum wheel bracket 105 is then installed and fixed on the bottom plate 101 through the four threaded holes at the bottom.

[0041] Based on the above solution, the first momentum wheel 2, the second momentum wheel 3, the third momentum wheel 4, and the fourth momentum wheel 5 are evenly distributed along the circumferential direction of the bottom plate 101.

[0042] Based on the above solution, the magnetic torque actuator assembly includes a first magnetic torque actuator 6, a second magnetic torque actuator 7, and a third magnetic torque actuator 8, and the axes of the first magnetic torque actuator 6, the second magnetic torque actuator 7, and the third magnetic torque actuator 8 are perpendicular to each other in pairs.

[0043] On the basis of the above solution, the first magnet torque actuator 6 is fixed on the second momentum wheel mounting bracket 104, the second magnet torque actuator 7 is fixed on the bottom plate 101, and the third magnet torque actuator 8 is fixed on the top plate 102.

[0044] The first magnet torque actuator 6 shares the second momentum wheel mounting bracket 104 with the second momentum wheel 3, and the second magnet torque actuator 7 and the third magnet torque actuator 8 are directly mounted on the bottom plate 101 and the top plate 102, saving the number of brackets and facilitating the lightweight design of the module. The three magnet torque actuators are installed using the assembly gaps of the four momentum wheels, and the overall structure of the attitude control module is compact and has a high integration level.

[0045] Specifically, as Figure 2 shown, the first magnet torque actuator 6 is vertically arranged and located between the first momentum wheel 2 and the second momentum wheel 3; the second magnet torque actuator 7 is horizontally arranged and located between the first momentum wheel 2 and the third momentum wheel 4; the third magnet torque actuator 8 is horizontally arranged and located between the third momentum wheel 4 and the fourth momentum wheel 5.

[0046] On the basis of the above solution, both the first momentum wheel mounting bracket 103 and the second momentum wheel mounting bracket 104 are rectangular plates, and both are provided with relief grooves and stiffening ribs; the side support frame 106 is a rectangular plate and has side frame weight reduction holes.

[0047] The relief grooves are used to reduce the weight of the first momentum wheel mounting bracket 103 and the second momentum wheel mounting bracket 104, and the stiffening ribs increase the support strength of the two. The frame structure formed by the side support frame 106, the top plate 102 and the bottom plate 101 is used to install, support and protect the internal momentum wheel assembly, magnet torque actuator assembly and gyro 9. The side support frame 106 is provided with side frame weight reduction holes to reduce the weight of the entire module.

[0048] Specifically, the side frame weight reduction holes are triangular through holes. Alternatively, the side frame weight reduction holes are rectangular, circular or other shaped holes.

[0049] On the basis of the above solution, the gyro 9 is fixed on the top plate 102.

[0050] The gyro 9 is directly assembled on the top plate 102, and the structure of the attitude control module is compact.

[0051] Specifically, the gyro 9 is located above the third momentum wheel 4.

[0052] On the basis of the above solution, the bottom plate 101 has a plurality of mounting lugs.

[0053] The bottom plate 101 is mounted on the micro-nano satellite through a plurality of mounting lugs.

[0054] In one specific example, both ends of the bottom plate 101 each have three mounting lugs.

[0055] As Figure 4 shown, the surface of the bottom plate 101 has a weight reduction groove for the bottom plate to reduce the weight of the bottom plate 101. The third momentum wheel 4, the second magnetic torque actuator 7, the first momentum wheel mounting bracket 103, the second momentum wheel mounting bracket 104, the obliquely mounted momentum wheel bracket 105 and the side support frame 106 are installed on the area of the bottom plate 101 without the weight reduction groove for the bottom plate by screws, so as to ensure the structural strength of the connection position.

[0056] Specifically, the bottom surface of the top plate 102 is also provided with a weight reduction groove for the top plate. The third magnetic torque actuator 8, the gyroscope 9, the first momentum wheel mounting bracket 103, the second momentum wheel mounting bracket 104 and the side support frame 106 are installed on the area of the top plate 102 without the weight reduction groove for the top plate by screws to ensure the structural strength of the connection position.

[0057] The present utility model also provides a micro-nano satellite, including the attitude control module described above.

[0058] Specifically, the bottom plate 101 of the attitude control module is bolted to the micro-nano satellite housing through the mounting ears.

[0059] In the description of the present utility model, it should be noted that the orientation or positional relationship indicated by the terms "upper", "lower", "vertical", "horizontal", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present utility model.

[0060] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present utility model, the meaning of "a plurality" is at least two, such as two, three, etc., unless otherwise specifically defined.

[0061] In the description of this specification, the descriptions referring to terms such as "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present utility model. In this specification, the schematic expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0062] In the description of the present utility model, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be directly connected, or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific situations.

[0063] The above are only the preferred embodiments of the present utility model, and are not intended to limit the present utility model. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present utility model shall be included in the protection scope of the present utility model.

Claims

1. A posture control module, characterized in that: The invention comprises a frame (1), a momentum wheel assembly, a magnetic torquer assembly and a gyroscope (9); the frame (1) comprises a bottom plate (101), a top plate (102) and a side support frame (106); the bottom plate (101) and the top plate (102) are arranged in parallel; there are a plurality of side support frames (106); the plurality of side support frames (106) are arranged at intervals along the circumference of the bottom plate (101); two ends of the side support frames (106) are respectively fixedly connected to the bottom plate (101) and the top plate (102); the momentum wheel assembly, the magnetic torquer assembly and the gyroscope (9) are all fixed in an area surrounded by the plurality of side support frames (106).

2. A posture control module according to claim 1, characterized in that: The momentum wheel assembly comprises a first momentum wheel (2), a second momentum wheel (3), a third momentum wheel (4) and a fourth momentum wheel (5); the axes of the first momentum wheel (2), the second momentum wheel (3) and the third momentum wheel (4) are perpendicular to each other; and the axis of the fourth momentum wheel (5) is inclined relative to the axis of the first momentum wheel (2), the second momentum wheel (3) or the third momentum wheel (4).

3. A posture control module according to claim 2, characterized in that: The frame (1) comprises a first momentum wheel mounting bracket (103), a second momentum wheel mounting bracket (104) and an oblique momentum wheel bracket (105); the first momentum wheel mounting bracket (103) is located between the bottom plate (101) and the top plate (102), and its two ends are respectively fixedly connected to the bottom plate (101) and the top plate (102); the second momentum wheel mounting bracket (104) is located between the bottom plate (101) and the top plate (102), and its two ends are respectively fixedly connected to the bottom plate (101) and the top plate (102); The top plate (102) is fixedly connected, the first momentum wheel mounting bracket (103) and the second momentum wheel mounting bracket (104) are perpendicular to each other, the second momentum wheel (3) is fixedly connected to the second momentum wheel mounting bracket (104), and the first momentum wheel (2) is fixedly connected to the first momentum wheel mounting bracket (103); the third momentum wheel (4) is fixedly connected to the bottom plate (101); the obliquely mounted momentum wheel bracket (105) is fixedly connected to the bottom plate (101) and has an installation inclined surface, and the fourth momentum wheel (5) is fixed on the installation inclined surface.

4. A posture control module according to claim 3, characterized in that: The first momentum wheel (2), the second momentum wheel (3), the third momentum wheel (4) and the fourth momentum wheel (5) are evenly distributed along the circumference of the bottom plate (101).

5. The attitude control module according to claim 3, characterized in that: The magnetic torquer assembly comprises a first magnetic torquer (6), a second magnetic torquer (7) and a third magnetic torquer (8), wherein the axes of the first magnetic torquer (6), the second magnetic torquer (7) and the third magnetic torquer (8) are perpendicular to each other.

6. A posture control module according to claim 5, characterized in that: The first magnetic torquer (6) is fixed on the second momentum wheel mounting bracket (104), the second magnetic torquer (7) is fixed on the bottom plate (101), and the third magnetic torquer (8) is fixed on the top plate (102).

7. The attitude control module according to claim 3, characterized in that: The first momentum wheel mounting bracket (103) and the second momentum wheel mounting bracket (104) are both rectangular plates and are both provided with lightening grooves and reinforcing ribs; the side support frame (106) is a rectangular plate and has side frame weight-reducing holes.

8. The attitude control module according to claim 1, characterized in that: The gyroscope (9) is fixed on the top plate (102).

9. A posture control module according to any one of claims 1 to 8, characterized in that: The base plate (101) has a plurality of mounting ears.

10. A micro-nano satellite, characterized in that: It comprises a posture control module as described in any one of claims 1-9.

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