Micro-satellite attitude adjustment driving device

Abstract

The utility model relates to the technical field of satellite attitude adjusting devices, in particular to a microsatellite attitude adjusting driving device which comprises a servo motor, a transmission shaft fixedly mounted at the tail end of an output shaft of the servo motor, a driving gear fixedly mounted on the transmission shaft, a first connecting rod arranged at the end of the transmission shaft, a long shaft arranged on one side of the servo motor, and a second connecting rod arranged on the other side of the long shaft. A front first driven gear and a rear first driven gear which are mutually symmetrical are fixedly installed on the long shaft, a shaft sleeve is arranged on the rear side of the servo motor, a second connecting rod is rotationally connected to the shaft sleeve, a second driven gear is fixedly installed on the second connecting rod, and the second driven gear and the driving gear are meshed with the corresponding first driven gears. Attitude adjusting plates are fixedly mounted at the ends of the first connecting rod and the second connecting rod, a rotating shaft is fixedly mounted at the end of the long shaft, and the rotating shaft is rotationally connected with a shell of the satellite. The satellite attitude adjusting device facilitates satellite attitude adjusting operation and is easy to operate and convenient to use.

Description

Technical Field

[0001] The utility model relates to the technical field of satellite attitude adjustment devices, in particular to a micro-satellite attitude adjustment driving device. Background Art

[0002] With the rapid development of aerospace technology, microsatellites have shown great application potential in scientific research, technical testing, environmental monitoring, communication relay and other fields due to their advantages such as small size, light weight, low cost and short development cycle. However, during the on-orbit operation of microsatellites, their attitude adjustment and control become key links to ensure the stable operation of the satellite and the execution of the scheduled mission. Due to the limitations of mass, volume and power consumption, microsatellites face many challenges in attitude adjustment and control. Traditional attitude control methods, such as the use of large gyroscopes and complex mechanical structures, are difficult to directly apply on microsatellites.

[0003] Currently, microsatellite attitude adjustment actuators primarily rely on traditional technologies such as magnetic torquers, momentum wheels, and jet systems. These technologies typically coordinate attitude adjustment operations by controlling the angle of an attitude adjustment plate in conjunction with the satellite's propulsion system. However, these technologies present several challenges in their application. For example, while magnetic torquers offer the advantage of low power consumption, they are susceptible to interference in complex magnetic fields and exhibit limited control accuracy. Momentum wheels, while capable of providing high control torque, are bulky and power-hungry, and long-term operation can lead to saturation of the momentum wheels, compromising control effectiveness. Jet systems, while offering rapid response, consume fuel, and frequent use can shorten the satellite's lifespan. Consequently, we propose a microsatellite attitude adjustment actuator. Utility Model Content

[0004] The purpose of the present invention is to provide a micro-satellite attitude adjustment drive device to solve the defects mentioned in the above background technology.

[0005] To achieve the above objectives, the present invention provides the following technical solutions:

[0006] A micro-satellite attitude adjustment drive device includes a servo motor, a transmission shaft is fixedly installed at the end of the output shaft of the servo motor, a driving gear is fixedly installed on the transmission shaft, a first connecting rod is provided at the end of the transmission shaft, a long shaft is provided on one side of the servo motor, two mutually symmetrical first driven gears are fixedly installed on the long shaft, a shaft sleeve is provided on the rear side of the servo motor, a second connecting rod is rotatably connected to the shaft sleeve, a second driven gear is fixedly installed on the second connecting rod, the second driven gear and the driving gear are meshed with each other with the corresponding first driven gear, and attitude adjustment plates are fixedly installed at the ends of the first connecting rod and the second connecting rod.

[0007] Preferably, a fixed base is fixedly mounted on the housing of the servo motor, and the fixed base is fixedly mounted on the housing of the satellite.

[0008] Preferably, a rectangular groove with its end connected to the outside is provided in the transmission shaft, and a rectangular rod is fixedly installed on the end of the first connecting rod. The rectangular rod is located in the rectangular groove and is plugged into the rectangular groove, and the rectangular rod is fixedly installed on the transmission shaft.

[0009] Preferably, the cross-sections of the rectangular rod and the rectangular groove are both rectangular, and the size of the rectangular rod is adapted to the size of the rectangular groove.

[0010] Preferably, a rotating shaft is fixedly mounted on the end of the long axis, and the rotating shaft is rotatably connected to the shell of the satellite.

[0011] Preferably, a fixing plate is fixedly mounted on the shaft sleeve, and the fixing plate is fixedly mounted on the housing of the satellite.

[0012] Preferably, the second connecting rod passes through the shaft sleeve and is rotatably connected to the shaft sleeve, and the size of the second connecting rod is adapted to the size of the shaft sleeve.

[0013] Preferably, a bearing seat is provided at the end of the second connecting rod, and the bearing seat is fixedly mounted on the housing of the satellite.

[0014] Compared with the prior art, the beneficial effects of the present invention are:

[0015] 1. The utility model provides a servo motor, a driving gear, a first driven gear and a second driven gear, so that when the servo motor works, the first connecting rod and the second connecting rod can be driven to rotate in the same direction. After rotating in the same direction, the angle of the attitude adjustment plate is adjusted, and the satellite attitude adjustment operation is realized in conjunction with the power thruster on the satellite, thereby facilitating the satellite attitude adjustment.

[0016] 2. The utility model achieves the effect of easy fixed installation by inserting and fitting the rectangular rod and the rectangular groove, and fixing the rectangular rod and the transmission shaft by fastening bolts. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0018] Figure 2 This is a schematic diagram of the explosion structure of the utility model;

[0019] Figure 3 It is a partial structural diagram of the utility model;

[0020] Figure 4 For this utility model Figure 2 Enlarged view of point A in the middle;

[0021] The meaning of each number in the figure is:

[0022] 1. Servo motor; 10. Fixed base; 11. Transmission shaft; 111. Rectangular slot; 12. Driving gear; 13. First connecting rod; 131. Rectangular rod;

[0023] 2. Long shaft; 20. First driven gear; 21. Rotating shaft;

[0024] 3. Bushing; 30. Fixed plate; 31. Second connecting rod; 32. Bearing seat; 33. Second driven gear;

[0025] 4. Posture adjustment board. DETAILED DESCRIPTION

[0026] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts shall fall within the scope of protection of the present invention.

[0027] See also Figures 1-4 The utility model provides a technical solution: a micro-satellite attitude adjustment drive device, including a servo motor 1, a transmission shaft 11 is fixedly installed at the end of the output shaft of the servo motor 1, and a driving gear 12 is fixedly installed on the transmission shaft 11, and a first connecting rod 13 is provided at the end of the transmission shaft 11. A long shaft 2 is provided on one side of the servo motor 1, and two mutually symmetrical first driven gears 20 are fixedly installed on the long shaft 2. A shaft sleeve 3 is provided on the rear side of the servo motor 1, and a second connecting rod 31 is rotatably connected to the shaft sleeve 3. A second driven gear 33 is fixedly installed on the second connecting rod 31, and the second driven gear 33 and the driving gear 12 are meshed with the corresponding first driven gear 20. The ends of the first connecting rod 13 and the second connecting rod 31 are fixedly installed with an attitude adjustment plate 4 to ensure that when in use, the servo motor 1 can be used to work to adjust the angle of the attitude adjustment plate 4. After the angle of the attitude adjustment plate 4 is changed, the airflow direction when the satellite moves can be adjusted, and the attitude adjustment operation of the micro-satellite can be realized by cooperating with the power thruster on the satellite.

[0028] In this embodiment, a fixed base 10 is fixedly mounted on the housing of the servo motor 1 . The fixed base 10 is fixedly mounted on the housing of the satellite by a plurality of fastening screws, so as to facilitate the fixed installation operation.

[0029] Specifically, a rectangular groove 111 whose end is connected to the outside world is provided in the transmission shaft 11, and a rectangular rod 131 is fixedly installed at the end of the first connecting rod 13. The rectangular rod 131 is located in the rectangular groove 111 and is plugged into and matched with the rectangular groove 111. The rectangular rod 131 is fixedly installed on the transmission shaft 11 by a plurality of fastening bolts, which is convenient for plug-in and fixed assembly operations; the cross-sections of the rectangular rod 131 and the rectangular groove 111 are both rectangular, and the size of the rectangular rod 131 is adapted to the size of the rectangular groove 111 for stable connection operation.

[0030] Furthermore, a rotating shaft 21 is fixedly installed at the end of the long axis 2 , and the rotating shaft 21 is rotatably connected to the shell of the satellite, thereby supporting the long axis 2 .

[0031] In addition, a fixing plate 30 is fixedly mounted on the shaft sleeve 3 , and the fixing plate 30 is fixedly mounted on the housing of the satellite, so as to facilitate fixing the fixing plate 30 and achieve the effect of fixing the shaft sleeve 3 .

[0032] It is worth noting that the second connecting rod 31 passes through the shaft sleeve 3 and is rotationally connected to the shaft sleeve 3 . The size of the second connecting rod 31 is adapted to the size of the shaft sleeve 3 , which is used for stable rotation operation of the second connecting rod 31 .

[0033] It is worth noting that a bearing seat 32 is provided at the end of the second connecting rod 31, and the bearing seat 32 is fixedly mounted on the shell of the satellite to support the second connecting rod 31 and ensure that the second connecting rod 31 can rotate normally.

[0034] When the micro-satellite attitude adjustment drive device of the present invention is in use, the servo motor 1 is connected to an external power supply and is put into operation. When the servo motor 1 is in operation, the output shaft thereon rotates to drive the transmission shaft 11, the driving gear 12 and the first connecting rod 13 to rotate. The driving gear 12 rotates to drive the first driven gear 20 to rotate. The first driven gear 20 rotates to drive the second driven gear 33 to rotate, and further drives the second connecting rod 31 to rotate, thereby adjusting the angle of the attitude adjustment plate 4 and cooperating with the power thrusters on the satellite to complete the attitude adjustment operation.

[0035] The above shows and describes the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The above embodiments and descriptions are merely preferred examples of the present invention and are not intended to limit the present invention. Various changes and improvements may be made to the present invention without departing from the spirit and scope of the present invention, and such changes and improvements fall within the scope of the present invention. The scope of protection claimed in the present invention is defined by the appended claims and their equivalents.

Claims

1. A micro-satellite attitude adjustment drive device, comprising a servo motor (1), characterized in that: A transmission shaft (11) is fixedly mounted on the end of the output shaft of the servo motor (1), a driving gear (12) is fixedly mounted on the transmission shaft (11), a first connecting rod (13) is provided at the end of the transmission shaft (11), a long shaft (2) is provided on one side of the servo motor (1), two mutually symmetrical first driven gears (20) are fixedly mounted on the long shaft (2), a shaft sleeve (3) is provided on the rear side of the servo motor (1), a second connecting rod (31) is rotatably connected to the shaft sleeve (3), a second driven gear (33) is fixedly mounted on the second connecting rod (31), the second driven gear (33) and the driving gear (12) are meshed with the corresponding first driven gear (20), and attitude adjustment plates (4) are fixedly mounted on the ends of the first connecting rod (13) and the second connecting rod (31).

2. The micro-satellite attitude adjustment drive device according to claim 1, characterized in that: A fixed base (10) is fixedly mounted on the housing of the servo motor (1), and the fixed base (10) is fixedly mounted on the housing of the satellite.

3. The micro-satellite attitude adjustment drive device according to claim 1, characterized in that: A rectangular groove (111) whose end is connected to the outside is provided in the transmission shaft (11); a rectangular rod (131) is fixedly mounted on the end of the first connecting rod (13); the rectangular rod (131) is located in the rectangular groove (111) and is plugged into and engaged with the rectangular groove (111); and the rectangular rod (131) is fixedly mounted on the transmission shaft (11).

4. The micro-satellite attitude adjustment drive device according to claim 3, characterized in that: The cross-sections of the rectangular rod (131) and the rectangular groove (111) are both rectangular, and the size of the rectangular rod (131) is adapted to the size of the rectangular groove (111).

5. The micro-satellite attitude adjustment drive device according to claim 1, characterized in that: A rotating shaft (21) is fixedly mounted on the end of the long shaft (2), and the rotating shaft (21) is rotationally connected to the shell of the satellite.

6. The micro-satellite attitude adjustment drive device according to claim 1, characterized in that: A fixing disk (30) is fixedly mounted on the shaft sleeve (3), and the fixing disk (30) is fixedly mounted on a housing of the satellite.

7. The micro-satellite attitude adjustment drive device according to claim 1, characterized in that: The second connecting rod (31) passes through the shaft sleeve (3) and is rotatably connected to the shaft sleeve (3); the size of the second connecting rod (31) is adapted to the size of the shaft sleeve (3).

8. The micro-satellite attitude adjustment drive device according to claim 1, characterized in that: A bearing seat (32) is provided at the end of the second connecting rod (31), and the bearing seat (32) is fixedly mounted on the housing of the satellite.

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