Direct-drive-motor-driven sun orientation device for spacecraft

Abstract

The invention discloses a direct-drive motor-driven sun orientation device for a spacecraft. The direct-drive motor-driven sun orientation device comprises a driving module and an electric transmission module, the driving module comprises a brushless direct current motor, a driving shaft, a bearing assembly, a butt flange and a rotary transformer. Driving torque generated by the brushless direct current motor is directly transmitted to the butt flange through the driving shaft to achieve sun orientation. A motor rotation angle signal is measured through the rotary transformer, and closed-loop control of angle feedback is achieved. The electric transmission module comprises a conductive slip ring, a wire, a satellite inner side electric connector and a satellite outer side electric connector, and electric power and signal transmission between the solar wing and a satellite body is achieved.

Description

Technical Field

[0001] The invention relates to a solar orientation device driven by a direct-drive motor for a spacecraft, which is used for solar wings of the spacecraft to realize solar orientation and belongs to the technical field of space mechanisms. Background Art

[0002] In order to meet the energy demand of spacecraft in orbit and improve the energy utilization rate of solar panels, a solar orientation device is usually used to drive the solar panels to achieve solar orientation. The solar orientation device usually uses a stepper motor as the driving source, and drives the solar panels through a reducer to amplify the torque. When the solar orientation device drives the solar panels of the spacecraft to rotate, the solar array will produce certain forced vibrations due to the fluctuation of the motor speed and the stability of the transmission system. Due to the large inertia of the solar panels themselves, a certain disturbance torque is generated on the star, affecting the attitude of the spacecraft.

[0003] The current solar orientation device is driven by a stepper motor, decelerated and amplified by a reducer, and then the torque is transmitted to the docking flange through a slip ring shaft to drive the solar wing to orientate the sun. This driving method has the following disadvantages:

[0004] a. The clearance and rotation error of the reducer itself will affect the transmission stability, thereby generating interference torque that affects the spacecraft;

[0005] b. The transmission link is relatively complex. As part of the transmission link, the rotating shaft of the conductive slip ring is subject to the impact torque of the solar wing deployment, which places high requirements on the strength design of the conductive slip ring. Summary of the invention

[0006] The technical problem solved by the present application is: to overcome the deficiencies of the prior art, to provide a direct-drive motor-driven solar orientation device for a spacecraft, to achieve solar orientation of the solar wing, and to solve the problem of poor speed stability of the traditional stepper motor drive mechanism under heavy load.

[0007] The technical solutions provided by this application are as follows:

[0008] A direct-drive motor-driven solar orientation device for a spacecraft comprises a housing, a front end cover, a rear end cover, a drive module and an electric transmission module, wherein the front end cover and the rear end cover are respectively fixedly connected to two ends of the housing, and the housing is fixed on a spacecraft cabin;

[0009] The drive module includes a brushless DC motor and a drive shaft;

[0010] The electric transmission module comprises a satellite inner side electric connector, a first conductor, a conductive slip ring, a second conductor and a satellite outer side electric connector;

[0011] The conductive slip ring comprises a conductive slip ring rotating end and a conductive slip ring fixed end, the conductive slip ring fixed end is fixedly connected to the housing, the conductive slip ring rotating end is rotatably connected inside the conductive slip ring fixed end, the conductive slip ring rotating end is fixedly connected to the drive shaft, and one end of the drive shaft extends out of the front end cover;

[0012] The brushless DC motor includes a motor rotor and a motor stator. The motor stator is fixedly connected to the housing, and the motor rotor cooperates with the drive shaft and drives the drive shaft to rotate.

[0013] The star inner side electrical connector is fixedly connected to the rear end cover, and the star outer side electrical connector is fixedly connected to the docking flange; the first wire connects the star inner side electrical connector and the fixed end of the conductive slip ring, and the second wire connects the rotating end of the conductive slip ring and the star outer side electrical connector, and the second wire passes through the inside of the drive shaft;

[0014] The electrical connector on the outside of the satellite is used to connect the solar panels, and the electrical connector on the inside of the satellite is used to connect the onboard equipment.

[0015] The motor rotor is sleeved on the outside of the driving shaft, and the motor rotor is connected to the driving shaft through a flat key.

[0016] The driving module further includes a rotary transformer, which includes a rotary transformer rotor and a rotary transformer stator. The rotary transformer rotor is fixedly connected to the rotating end of the conductive slip ring, and the rotary transformer stator is fixedly connected to the fixed end of the conductive slip ring.

[0017] One end of the driving shaft extending out of the front end cover is connected with a docking flange, and the docking flange is used to connect the solar wing.

[0018] The drive shaft and the front end cover are supported by a pair of back-to-back angular contact bearing assemblies.

[0019] The end of the bearing assembly away from the rear end cover is provided with a bearing end cover, and the bearing end cover is fixedly connected to the front end cover.

[0020] The inner ring of the bearing assembly is axially positioned through the drive shaft shoulder and the mating flange boss.

[0021] The drive shaft is fixedly connected with a motor end cover, and the motor end cover presses the motor rotor tightly to limit the axial displacement of the motor rotor.

[0022] In summary, this application at least includes the following beneficial technical effects:

[0023] The present invention adopts a modular design, and divides the solar orientation device into a drive module and an electric transmission module according to function. In actual use, suitable drive modules and electric transmission modules can be selected for assembly according to the actual driving torque and electric transmission capacity required. The design is simple, the interchangeability is good, and it is easy to standardize.

[0024] The present invention adopts a brushless DC motor for direct drive and a rotary transformer for angle closed-loop control, which greatly improves the speed stability of the transmission and reduces the interference of the rotation of the driving mechanism on the attitude of the spacecraft.

[0025] The present invention adopts a brushless DC motor to directly drive the solar wing through a driving shaft to achieve sun orientation without using a reducer, and has a simple transmission chain, a compact transmission structure, fewer connecting links, high reliability, and less axial runout.

[0026] The present invention places the conductive slip ring on the other side of the transmission chain, so the slip ring shaft does not bear the bending moment and torque caused by the load, and only plays a follow-up role as a component of electrical transmission, which makes the slip ring have better mechanical resistance and higher overall reliability.

[0027] The present invention adopts a pair of back-to-back angular contact bearings located on one side of the driving load, directly bearing the loads such as bending moment, radial force and axial force at the male wing equivalent to the docking flange, so that the driving mechanism can withstand a larger external load. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 This is a schematic diagram of the structure of the solar orientation device driven by a direct drive motor;

[0029] Figure 2 This is a functional schematic diagram of the direct-drive motor-driven solar orientation device.

[0030] Figure 3 This is a cross-sectional view of a solar orientation device driven by a direct-drive motor.

[0031] Illustration Description:

[0032] 1-housing, 2-conductive slip ring, 3-star inner connector, 4-rotating transformer, 5-brushless DC motor, 6-driving shaft, 7-front cover, 8-bearing assembly, 9-joint flange, 10-star outer connector, 11-bearing end cover, 12-motor end cover, 13-flat key, 14-rear end cover. 2a-conductive slip ring rotating end, 2b-conductive slip ring fixed end, 4a-rotating transformer rotor, 4b-rotating transformer stator, 5a-motor rotor, 5b-motor stator. DETAILED DESCRIPTION

[0033] In order to make the objectives, technical solutions and advantages of the present invention more clear, the embodiments disclosed in the present invention will be further described in detail below with reference to the accompanying drawings.

[0034] The embodiment of the present application discloses a direct-drive motor driven solar orientation device for driving a solar wing to orient itself toward the sun and transmit electrical power and signals.

[0035] like Figure 1The figure shows a schematic diagram of the structure of a direct-drive motor-driven solar orientation device of the present invention; as can be seen from the figure, the direct-drive motor-driven solar orientation device is fixed to the spacecraft cabin through a shell 1, the front end cover 7 is fixedly connected to the shell 1, and the rear end cover 14 is fixedly connected to the shell 1.

[0036] like Figure 2 As shown, it is a cross-sectional view of a direct-drive motor-driven solar orientation device of the present invention; the direct-drive motor-driven solar orientation device of this embodiment includes: a drive module and an electric transmission module, the drive module realizes the solar orientation of the solar wing, and the electric transmission module realizes the transmission of electric power and electric signals between the solar wing and the star body.

[0037] like Figure 3 As shown, the drive module includes a brushless DC motor 5, a drive shaft 6, a bearing assembly 8, a docking flange 9, and a rotary transformer 4. The brushless DC motor generates a driving torque which is directly transmitted to the docking flange 9 through the drive shaft to achieve solar orientation. The rotary transformer 4 detects the motor rotation angle signal in real time to achieve closed-loop control of angle feedback.

[0038] The electric transmission module includes a conductive slip ring 2, a wire, a star inner side electric connector 3, and a star outer side electric connector 10. The conductive slip ring fixed end 2b is fixedly connected to the housing 1, and the conductive slip ring rotating end 2a is fixedly connected to the drive shaft 6, and rotates with the drive shaft 6. The star inner side connector 3 is fixedly connected to the rear end cover 14, and the star outer side connector 10 is fixedly connected to the docking flange 9. Through the star inner side connector-wire-slip ring-wire-star outer side connector 10, the star outer side connector 10 is used to connect the solar wing to realize the electric power and signal transmission function between the solar wing and the star body.

[0039] The brushless DC motor 5 is divided into a motor rotor 5a and a motor stator 5b. The motor stator 5b is fixedly connected to the housing 1, and the motor rotor 5a cooperates with the drive shaft 6 to transmit torque through the flat key 13. The motor end cover 12 is fixedly connected to the drive shaft 6, and the motor rotor 5a is pressed by repairing the end cover step to limit the axial displacement of the motor rotor 5a. One end of the drive shaft 6 is fixedly connected to the rotating end 2a of the conductive slip ring, and the other end is fixedly connected to the docking flange 9. The brushless DC motor 5 receives the drive signal and directly drives the solar wing to achieve sun orientation through the drive shaft 6.

[0040] The rotary transformer is divided into a rotary transformer rotor 4a and a rotary transformer stator 4b. The rotary transformer rotor 4a is fixedly connected to the rotating end 2a of the conductive slip ring, and the rotary transformer stator 4b is fixedly connected to the fixed end 2b of the conductive slip ring.

[0041] The drive shaft 6 and the front end cover 7 are supported by a pair of back-to-back angular contact bearing assemblies 8. The inner ring of the bearing assembly 8 is axially positioned by the shoulder of the drive shaft 6 and the boss of the docking flange 9, and the inner ring of the bearing is pressed by adjusting the height of the boss of the docking flange 9. The outer ring of the bearing assembly 8 is axially positioned by the end face of the front end cover 7 and the boss of the bearing end cover 11, and the outer ring of the bearing is pressed by adjusting the height of the boss of the bearing end cover 11. The bearing end cover 11 is fixedly connected to the front end cover 7.

[0042] The contents not described in detail in this application specification belong to the common knowledge of those skilled in the art.

[0043] The present application is described in detail above in conjunction with specific implementation methods and exemplary examples, but these descriptions cannot be understood as limiting the present application. Those skilled in the art understand that, without departing from the spirit and scope of the present application, a variety of equivalent replacements, modifications or improvements can be made to the technical solution of the present application and its implementation methods, all of which fall within the scope of the present application. The scope of protection of the present application shall be subject to the attached claims.

Claims

1. A solar orientation device driven by a direct drive motor for a spacecraft, characterized in that: The invention comprises a shell (1), a front end cover (7), a rear end cover (14), a drive module and an electric transmission module, wherein the front end cover (7) and the rear end cover (14) are respectively fixedly connected to two ends of the shell (1), and the shell (1) is fixed on a spacecraft cabin. The driving module comprises a brushless DC motor (5) and a driving shaft (6); The electric transmission module comprises an inner-star electric connector (3), a first conductor, a conductive slip ring (2), a second conductor and an outer-star electric connector (10); The conductive slip ring (2) comprises a conductive slip ring rotating end (2a) and a conductive slip ring fixed end (2b); the conductive slip ring fixed end (2b) is fixedly connected to the housing (1); the conductive slip ring rotating end (2a) is rotatably connected inside the conductive slip ring fixed end (2b); the conductive slip ring rotating end (2a) is fixedly connected to a drive shaft (6); and one end of the drive shaft (6) extends out of a front end cover (7); The brushless DC motor (5) comprises a motor rotor (5a) and a motor stator (5b), wherein the motor stator (5b) is fixedly connected to the housing (1), and the motor rotor (5a) cooperates with the drive shaft (6) and drives the drive shaft (6) to rotate; The star inner side electrical connector (3) is fixedly connected to the rear end cover (14), and the star outer side electrical connector (10) is fixedly connected to the docking flange (9); a first wire connects the star inner side electrical connector (3) and the fixed end (2b) of the conductive slip ring, and a second wire connects the rotating end (2a) of the conductive slip ring and the star outer side electrical connector (10), and the second wire passes through the interior of the drive shaft (6); The satellite outer side electrical connector (10) is used to connect the solar wing, and the satellite inner side electrical connector (3) is used to connect the onboard equipment.

2. A direct-drive motor-driven solar orientation device for a spacecraft according to claim 1, characterized in that: The motor rotor (5a) is sleeved on the outside of the drive shaft (6), and the motor rotor (5a) is connected to the drive shaft (6) via a flat key (13).

3. A direct-drive motor-driven solar orientation device for a spacecraft according to claim 1, characterized in that: The drive module further comprises a rotary transformer (4), the rotary transformer (4) comprising a rotary transformer rotor (4a) and a rotary transformer stator (4b), the rotary transformer rotor (4a) being fixedly connected to the rotating end (2a) of the conductive slip ring, and the rotary transformer stator (4b) being fixedly connected to the fixed end (2b) of the conductive slip ring.

4. The solar orientation device driven by a direct-drive motor for a spacecraft according to claim 1, characterized in that: One end of the drive shaft (6) extending out of the front end cover (7) is connected to a docking flange (9), and the docking flange (9) is used to connect the solar wing.

5. The solar orientation device driven by a direct-drive motor for a spacecraft according to claim 1, characterized in that: The drive shaft (6) and the front end cover (7) are supported by a pair of back-to-back angular contact bearing assemblies (8).

6. A direct-drive motor-driven solar orientation device for a spacecraft according to claim 5, characterized in that: A bearing end cover (11) is provided at the end of the bearing assembly (8) away from the rear end cover (14), and the bearing end cover (11) is fixedly connected to the front end cover (7).

7. The solar orientation device driven by a direct-drive motor for a spacecraft according to claim 5, characterized in that: The inner ring of the bearing assembly (8) is axially positioned by means of a shoulder of the drive shaft (6) and a boss of the mating flange (9).

8. The solar orientation device driven by a direct-drive motor for a spacecraft according to claim 1, characterized in that: The drive shaft (6) is fixedly connected to a motor end cover (12), and the motor end cover (12) presses the motor rotor (5a) to limit the axial displacement of the motor rotor (5a).

Images