Adjustable rotational inertia reaction momentum wheel for satellite attitude control

Abstract

The invention discloses an adjustable rotational inertia reaction momentum wheel for satellite attitude control, and relates to the technical field of momentum wheels. Comprising an adjustable rotational inertia momentum wheel assembly and a double-rotor motor transmission system assembly. The momentum wheel assembly with the adjustable rotational inertia comprises a rotating disc and a momentum wheel body which are concentrically arranged, a plurality of through inclined sliding grooves are formed in the rotating disc in an annular array mode, a plurality of straight sliding grooves are formed in the momentum wheel body in an annular array mode, a sliding rod is arranged in each straight sliding groove in a sliding mode, and the ends, located outside the momentum wheel body, of the sliding rods are fixedly connected with mass blocks. A sliding column is fixedly arranged at the other end; the double-rotor motor transmission system assembly comprises an outer rotor motor and an inner rotor motor. The outer rotor motor is used for driving the momentum wheel body to rotate. The inner rotor motor is used for driving the rotating disc to rotate. The double-rotor motor transmission system assembly is adopted as an executing mechanism, the structure is more compact, the installation space in a satellite can be effectively saved, and meanwhile the leakage risk is avoided.

Description

Technical Field

[0001] The present invention relates to the technical field of momentum wheels, and particularly to an adjustable moment of inertia reaction momentum wheel for satellite attitude control. Background Art

[0002] With the explosive growth trend in the global commercial space field, satellites, as key application carriers therein, the improvement of their performance plays a crucial role in realizing diverse space missions. The satellite attitude control system is the core part to ensure the precise pointing and stable operation of the satellite, and the reaction momentum wheel is a key actuator in this system. Currently, most reaction momentum wheels have a fixed moment of inertia, which cannot provide a sufficiently powerful and precisely adaptable reaction torque and cannot flexibly change the angular acceleration response characteristics. To overcome the limitations of the fixed moment of inertia reaction momentum wheel, a few reaction momentum wheels with adjustable moment of inertia have been developed in the industry, and most of them use hydraulic drive as the actuator. However, in the space environment, the temperature changes drastically, and the performance of the sealing material may be affected, resulting in seal failure, which may cause leakage of hydraulic oil and affect the normal operation of the system. Summary of the Invention

[0003] The main purpose of the present invention is to provide an adjustable moment of inertia reaction momentum wheel for satellite attitude control to solve the above problems.

[0004] To achieve the above object, the present invention provides an adjustable moment of inertia reaction momentum wheel for satellite attitude control, including an adjustable moment of inertia momentum wheel assembly and a dual-rotor motor drive system assembly;

[0005] The adjustable moment of inertia momentum wheel assembly includes a rotating disk and a momentum wheel main body arranged concentrically. A plurality of through inclined chutes are annularly arrayed on the rotating disk, and a plurality of straight chutes are annularly arrayed on the momentum wheel main body. A sliding rod is slidably arranged in each straight chute. One end of the sliding rod located outside the momentum wheel main body is fixedly connected with a mass block, and the other end is fixedly provided with a sliding column. The plurality of sliding columns are arranged in the plurality of inclined chutes of the rotating disk in a one-to-one correspondence;

[0006] The dual-rotor motor drive system assembly includes an outer-rotor motor and an inner-rotor motor; the outer-rotor motor is used to drive the rotation of the momentum wheel main body, and the inner-rotor motor is used to drive the rotation of the rotating disk.

[0007] Furthermore, the dual-rotor motor drive system assembly includes an outer-rotor motor stator, an outer-rotor motor rotor, an inner-rotor motor stator, an inner-rotor motor rotor, a rotating housing, a first rotating end cover, a second rotating end cover, a stator housing, a first stator end cover, a second stator end cover, a third stator end cover, and a rotating shaft; the first rotating end cover and the second rotating end cover are respectively fixedly arranged at both ends of the rotating housing; the first stator end cover and the third stator end cover are respectively fixedly arranged at both ends of the stator housing, and the second stator end cover is fixedly arranged in the middle of the stator housing; the rotating housing is sleeved outside the stator housing, and the stator housing is sleeved outside the rotating shaft; the first rotating end cover and the second rotating end cover are respectively rotationally connected to the first stator end cover and the third stator end cover; the first stator end cover and the second stator end cover are both rotationally connected to the rotating shaft; the stepped shaft of the first stator end cover passes through the central through hole of the first rotating end cover and is fixedly connected to an external device; the outer-rotor motor stator is fixedly arranged outside the stator housing, the outer-rotor motor rotor is fixedly arranged inside the rotating housing, the inner-rotor motor stator is fixedly arranged inside the stator housing, and the inner-rotor motor rotor is fixedly arranged on the rotating shaft; the second rotating end cover is used to drive the momentum wheel body to rotate, and the rotating shaft is used to drive the rotating disk to rotate.

[0008] Furthermore, it further includes a three-stage planetary gear reducer assembly, and the rotating shaft is power-connected to the rotating disk through the three-stage planetary gear reducer assembly.

[0009] Furthermore, the three-stage planetary gear reducer assembly includes a first-stage planetary gear reducer, a second-stage planetary gear reducer, and a third-stage planetary gear reducer; the first-stage planetary gear reducer, the second-stage planetary gear reducer, and the third-stage planetary gear reducer share the same gear ring, and the gear ring is fixed inside the stator housing; the first-stage planetary gear reducer includes a first-stage planetary carrier, and planetary gear assemblies are arranged on the three support shafts of the first-stage planetary carrier, and a sun gear fixedly connected to the rotating shaft meshes in the middle of the three planetary gear assemblies of the first-stage planetary gear reducer; the second-stage planetary gear reducer includes a second-stage planetary carrier, and planetary gear assemblies are arranged on the three support shafts of the second-stage planetary carrier, and a sun gear fixedly connected to the output shaft of the first-stage planetary carrier meshes in the middle of the three planetary gear assemblies of the second-stage planetary gear reducer; the third-stage planetary gear reducer includes a third-stage planetary carrier, and planetary gear assemblies are arranged on the three support shafts of the third-stage planetary carrier, and a sun gear fixedly connected to the output shaft of the second-stage planetary carrier meshes in the middle of the three planetary gear assemblies of the third-stage planetary gear reducer; the output shaft of the third-stage planetary carrier passes through the central through hole of the third stator end cover and is fixedly connected to the rotating disk.

[0010] Furthermore, the planetary gear assembly includes a bearing end cover, a planetary gear, and a fourth bearing. The bearing end cover is fixedly connected to the planetary gear, and the fourth bearing is installed in the bearing installation groove of the planetary gear.

[0011] Further, a stepped shaft evenly distributed in a circumferential direction is arranged on one end face of the second rotating end cover, and a round hole fixedly matched with the stepped shaft is arranged on one end face of the momentum wheel main body.

[0012] The present invention has the following beneficial effects:

[0013] The present invention adopts a dual-rotor motor drive system assembly as an actuator. The adjustable moment of inertia reaction wheel can utilize a larger moment of inertia to resist external interference forces, enabling the satellite to reach a stable state faster. It can also reduce the moment of inertia to facilitate frequent, fast, and precise small attitude adjustments. The dual-rotor motor is more compact in structure, can effectively save the installation space inside the satellite, and at the same time avoids the risk of leakage. The inner-rotor motor is combined with a three-stage planetary gear reducer, which can convert the high-speed rotation of the motor into the low-speed and high-torque output required by the rotating disk, and can improve the adjustment accuracy of the moment of inertia of the reaction wheel. Description of the Drawings

[0014] Figure 1 It is a three-dimensional sectional view of an adjustable moment of inertia reaction wheel for satellite attitude control according to the present invention.

[0015] Figure 2 It is the front view and C-C sectional view of the adjustable moment of inertia reaction wheel assembly of an adjustable moment of inertia reaction wheel for satellite attitude control according to the present invention.

[0016] Figure 3 It is the front view of the dual-rotor motor drive system assembly of an adjustable moment of inertia reaction wheel for satellite attitude control according to the present invention.

[0017] Figure 4 It is the A-A sectional view of the dual-rotor motor drive system assembly of an adjustable moment of inertia reaction wheel for satellite attitude control according to the present invention.

[0018] Figure 5 It is a schematic diagram of the first-stage planetary gear reducer of an adjustable moment of inertia reaction wheel for satellite attitude control according to the present invention.

[0019] Figure 6 It is a schematic diagram of the three-stage planetary gear reducer of an adjustable moment of inertia reaction wheel for satellite attitude control according to the present invention.

[0020] Figure 7 It is a schematic diagram of the first-stage planet carrier and the three-stage planet carrier of an adjustable moment of inertia reaction wheel for satellite attitude control according to the present invention.

[0021] Figure 8 It is the front view and A-A sectional view of the planetary gear assembly of an adjustable moment of inertia reaction wheel for satellite attitude control according to the present invention.

[0022] Among them, 1 - adjustable moment of inertia momentum wheel assembly; 2 - dual-rotor motor drive system assembly; 3 - three-stage planetary gear reducer assembly; 101 - momentum wheel body; 102 - sliding rod; 103 - mass block; 104 - pin; 105 - rotating disc; 106 - sliding column; 201 - outer-rotor motor stator; 202 - outer-rotor motor rotor; 203 - inner-rotor motor stator; 204 - inner-rotor motor rotor; 205 - rotating housing; 206 - first rotating end cover; 207 - second rotating end cover; 208 - stator housing; 209 - first stator end cover; 210 - second stator end cover; 211 - third stator end cover; 212 - first bearing; 213 - first bearing stopper; 214 - second bearing; 215 - second bearing stopper; 216 - rotating shaft; 301 - sun gear; 302 - planetary gear assembly; 303 - gear ring; 304 - first-stage planetary carrier; 305 - three-stage planetary carrier; 306 - third bearing; 307 - third bearing stopper; 3021 - bearing end cover; 3022 - planetary gear; 3023 - fourth bearing. Detailed implementation manners

[0023] To achieve the above purposes and effects, the technical means and structures adopted by the present invention are described in detail in conjunction with the drawings for the preferred embodiments of the present invention to illustrate their features and functions.

[0024] As Figure 1 shown, the present invention provides an adjustable moment of inertia reaction momentum wheel for satellite attitude control, including an adjustable moment of inertia momentum wheel assembly 1, a dual-rotor motor drive system assembly 2, and a three-stage planetary gear reducer assembly 3.

[0025] As Figure 2 shown, the adjustable moment of inertia momentum wheel assembly 1 includes a momentum wheel body 101, a sliding rod 102, a mass block 103, a pin 104, a rotating disc 105, and a sliding column 106. The rotating disc 105 is concentric with the momentum wheel body 101. A plurality of through inclined chutes are annularly arranged on the rotating disc 105, and a plurality of straight chutes are annularly arranged on the momentum wheel body 101. A sliding rod 102 is slidably arranged in each straight chute. One end of the sliding rod 102 outside the momentum wheel body 101 is fixedly connected with a mass block 103 through a pin 104, and the other end is fixedly provided with a sliding column 106. A plurality of sliding columns 106 are respectively placed in the inclined chutes of the rotating disc 105.

[0026] As Figures 3 - 4As shown, the dual-rotor motor drive system assembly 2 includes an outer-rotor motor stator 201, an outer-rotor motor rotor 202, an inner-rotor motor stator 203, an inner-rotor motor rotor 204, a rotating housing 205, a first rotating end cover 206, a second rotating end cover 207, a stator housing 208, a first stator end cover 209, a second stator end cover 210, a third stator end cover 211, a first bearing 212, a first bearing stopper 213, a second bearing 214, a second bearing stopper 215, and a rotating shaft 216. The outer-rotor motor stator 201 is concentrically fixed to the stator housing 208 by gluing. The inner-rotor motor stator 203 is concentrically fixed to the stator housing 208 by gluing. Step bosses are respectively provided on the inner and outer circumferential surfaces of the stator housing 208 for the axial positioning of the inner-rotor motor stator 203 and the outer-rotor motor stator 201. The outer-rotor motor rotor 202 is fixed to the rotating housing 205 by screws evenly distributed on the end circumference, and the circumferential contact surfaces of the two are in interference fit. The inner-rotor motor rotor 204 is fixed to the rotating shaft 216 by screws evenly distributed on the end circumference, and the circumferential contact surfaces of the two are in interference fit. The first rotating end cover 206 and the second rotating end cover 207 are respectively fixed to the two end faces of the rotating housing 205 by gluing and the three are concentric. The first stator end cover 209 and the third stator end cover 211 are respectively fixed to the two end faces of the stator housing 208 by gluing and the three are concentric. The second stator end cover 210 is fixed to the stator housing 208 by gluing to the circumferential surface at the axial middle and the two are concentric. The first stator end cover 209 is concentric with the first rotating end cover 206. The stepped shaft of the first stator end cover 209 passes through the central through-hole of the first rotating end cover 206 and is thus fixedly connected to an external device. The circumferential surfaces of the stepped shafts at both ends of the rotating shaft 216 are respectively fixed to the inner rings of the two first bearings 212. The inner circumferential surfaces of the bearing mounting circular grooves of the first stator end cover 209 and the second stator end cover 210 are respectively fixed to the outer rings of the two first bearings 212. The two first bearing stoppers 213 are in an annular shape. The two first bearing stoppers 213 and the stepped shafts at both ends of the rotating shaft 216 respectively limit the axial displacement of the two first bearings 212. The circumferential surfaces of the stepped shafts of the first stator end cover 209 and the third stator end cover 211 are respectively fixed to the inner rings of the two second bearings 214. The inner circumferential surfaces of the bearing mounting circular grooves of the first rotating end cover 206 and the second rotating end cover 207 are respectively fixed to the outer rings of the two second bearings 214. The two second bearing stoppers 215 are in an annular shape. The two second bearing stoppers 215 respectively limit the axial displacement of the two second bearings 214 with the stepped shafts of the first stator end cover 209 and the second stator end cover 210.

[0027] As Figures 4 - 7As shown in the figure, the three-stage planetary gear reducer assembly 3 includes a sun gear 301, a planetary gear assembly 302, a gear ring 303, a first-stage planetary carrier 304, a second-stage planetary carrier, a third-stage planetary carrier 305, a third bearing 306, and a third bearing abutment 307. One sun gear 301 + three planetary gear assemblies 302 + N-stage planetary carriers + one gear ring 303 = N-stage planetary gear reducer. The three-stage planetary gear reducer shares one gear ring 303. The gear ring 303 is concentrically glued and fixed to the stator housing 208. The sun gear 301 of the first-stage planetary gear reducer is fixed to one end of the rotating shaft 216 by interference fit. The planetary gear assembly 302 of the first-stage planetary gear reducer is concentrically fixed to the support shaft of the first-stage planetary carrier 304. The output shaft of the first-stage planetary carrier 304 is fixed to the sun gear 301 of the second-stage planetary gear reducer by interference fit. The planetary gear assembly 302 of the second-stage planetary gear reducer is concentrically fixed to the support shaft of the second-stage planetary carrier. The output shaft of the second-stage planetary carrier of the second-stage planetary gear reducer is fixed to the sun gear 301 of the third-stage planetary gear reducer by interference fit. The planetary gear assembly 302 of the third-stage planetary gear reducer is concentrically fixed to the support shaft of the third-stage planetary carrier 305. The circumferential surface of the output shaft of the third-stage planetary carrier 305 is fixed to the inner ring of the third bearing 306. The outer ring of the third bearing 306 is fixed to the inner circumferential surface of the bearing mounting circular groove of the third stator end cover 211. The third bearing abutment 307 limits the axial displacement of the third bearing 306 with the stepped shaft of the output shaft of the third-stage planetary carrier 305.

[0028] As Figure 8 shown, the planetary gear assembly 302 includes a bearing end cover 3021, a planetary gear 3022, and a fourth bearing 3023. The bearing end cover 3021 is fixed to the planetary gear 3022 using screws. The bearing mounting grooves of the bearing end cover 3021 and the planetary gear 3022 limit the axial displacement of the fourth bearing 3023.

[0029] As Figures 1 - 2 shown in FIGS. 4-8, the output shaft of the third-stage planetary carrier 305 passes through the central through hole of the third stator end cover 211 and is fixed to the central through hole of the rotating disk 105 by interference fit. One end face of the second rotating end cover 207 has stepped shafts evenly distributed in a circle. One end face of the momentum wheel body 101 has circular holes evenly distributed in a circle. The stepped shafts of the second rotating end cover 207 are fixed to the circular holes of the momentum wheel body 101 by interference fit.

[0030] The working principle of the present invention is:

[0031] 1. The rotating shaft 216 of the dual-rotor motor drive system 2 is fixed to the sun gear 301 of the first-stage planetary gear reducer of the three-stage planetary gear reducer assembly 3. The output shaft of the three-stage planet carrier 305 of the three-stage planetary gear reducer assembly is fixed to the rotating disk 105 of the adjustable moment of inertia momentum wheel assembly 1. The inner-rotor motor stator 203 of the dual-rotor motor drive system 2 drives the inner-rotor motor rotor 204 and the rotating shaft 216 to rotate, outputs low speed and high torque through the three-stage planetary gear reducer assembly 3, and drives the rotating disk 105 to rotate, so that the sliding column 106 slides outward or inward along the inclined chute of the rotating disk 105. The sliding column 106 simultaneously pushes the sliding rod 102 to slide outward or inward along the straight chute of the momentum wheel body 101, and adjusts the position of the mass block 103 to adjust the moment of inertia of the momentum wheel.

[0032] 2. The rotating housing 205 and the second rotating end cover 207 of the dual-rotor motor drive system 2 are concentrically fixed. The stepped shaft of the second rotating end cover 207 is fixed to the circular hole of the momentum wheel body 101 of the adjustable moment of inertia momentum wheel assembly 1. The outer-rotor motor stator 201 of the dual-rotor motor drive system 2 controls the rotational speeds of the outer-rotor motor rotor 202 and the rotating housing 205, thereby controlling the momentum wheel speed. According to the law of conservation of angular momentum, for a system composed of a satellite and a reaction momentum wheel, when the angular momentum of the reaction momentum wheel changes, the angular momentum of the satellite will change accordingly, obtaining a control torque, thereby realizing the attitude control of the satellite.

[0033] The above are only the preferred embodiments of the present invention, not all embodiments. Anyone should know that structural changes made under the inspiration of the present invention, as long as they have the same or similar technical solutions as the present invention, all belong to the protection scope of the present invention.

Claims

1. An adjustable moment of inertia reaction momentum wheel for satellite attitude control, characterized in that: It comprises an adjustable moment of inertia momentum wheel assembly (1) and a dual-rotor motor transmission system assembly (2); The adjustable moment of inertia momentum wheel assembly (1) comprises a rotating disk (105) and a momentum wheel body (101) which are arranged concentrically, the rotating disk (105) having a plurality of oblique sliding grooves extending therethrough in an annular array, the momentum wheel body (101) having a plurality of straight sliding grooves in an annular array, each straight sliding groove having a sliding rod (102) slidably arranged therein, one end of the sliding rod (102) located outside the momentum wheel body (101) being fixedly connected to a mass block (103), and the other end of the sliding rod (102) being fixedly arranged to have a sliding column (106), and the plurality of sliding columns (106) being arranged one by one in the plurality of oblique sliding grooves of the rotating disk (105); The dual-rotor motor transmission system component (2) comprises an outer rotor motor and an inner rotor motor; the outer rotor motor is used to drive the momentum wheel body (101) to rotate, and the inner rotor motor is used to drive the rotating disk (105) to rotate.

2. The adjustable rotational inertia reaction momentum wheel for satellite attitude control according to claim 1, characterized in that: The dual-rotor motor transmission system component (2) comprises an outer rotor motor stator (201), an outer rotor motor rotor (202), an inner rotor motor stator (203), an inner rotor motor rotor (204), a rotating housing (205), a first rotating end cover (206), a second rotating end cover (207), a stator shell (208), a first stator end cover (209), a second stator end cover (210), a third stator end cover (211) and a rotating shaft (216); The first rotating end cover (206) and the second rotating end cover (207) are respectively fixedly arranged at two ends of the rotating outer shell (205); the first stator end cover (209) and the third stator end cover (211) are respectively fixedly arranged at two ends of the stator shell (208), and the second stator end cover (210) is fixedly arranged in the middle of the stator shell (208); the rotating outer shell (205) is sleeved on the outside of the stator shell (208), and the stator shell (208) is sleeved on the rotating shaft (216). ) outside; the first rotating end cover (206) and the second rotating end cover (207) are rotatably connected to the first stator end cover (209) and the third stator end cover (211) respectively; the first stator end cover (209) and the second stator end cover (210) are both rotatably connected to the rotating shaft (216); the stepped shaft of the first stator end cover (209) passes through the central through hole of the first rotating end cover (206) to be fixedly connected to the external device; the stator (201) of the outer rotor motor is fixedly connected to the outer rotor motor; The outer rotor motor rotor (202) is fixedly arranged on the outside of the stator shell (208), the inner rotor motor stator (203) is fixedly arranged on the inside of the stator shell (208), and the inner rotor motor rotor (204) is fixedly arranged on the rotating shaft (216); the second rotating end cover (207) is used to drive the momentum wheel body (101) to rotate, and the rotating shaft (216) is used to drive the rotating disk (105) to rotate.

3. The adjustable rotational inertia reaction momentum wheel for satellite attitude control as claimed in claim 2, characterized in that: It also includes a three-stage planetary gear reducer assembly (3), and the rotating shaft (216) is connected to the rotating disk (105) through the three-stage planetary gear reducer assembly (3).

4. The adjustable rotational inertia reaction momentum wheel for satellite attitude control as claimed in claim 3, characterized in that: The three-stage planetary gear reducer assembly (3) comprises a first-stage planetary gear reducer, a second-stage planetary gear reducer and a third-stage planetary gear reducer; the first-stage planetary gear reducer, the second-stage planetary gear reducer and the third-stage planetary gear reducer share a same gear ring (303), and the gear ring (303) is fixed to the inner side of the stator housing (208); the first-stage planetary gear reducer comprises a first-stage planet carrier (304), and the three supporting shafts of the first-stage planet carrier (304) are all provided with planetary gear assemblies (302), and a sun gear (301) fixedly connected to the rotating shaft (216) is meshed between the three planetary gear assemblies (302) of the first-stage planetary gear reducer; the second-stage planetary gear reducer comprises a second-stage planet carrier, and ... The three supporting shafts of the planetary carrier are all provided with planetary gear assemblies (302), and a sun gear (301) fixedly connected to the output shaft of the first-stage planetary carrier (304) is meshed in the middle of the three planetary gear assemblies (302) of the second-stage planetary gear reducer; the three-stage planetary gear reducer comprises a three-stage planetary carrier (305), and the three supporting shafts of the three-stage planetary carrier (305) are all provided with planetary gear assemblies (302), and a sun gear (301) fixedly connected to the output shaft of the second-stage planetary carrier is meshed in the middle of the three planetary gear assemblies (302) of the three-stage planetary gear reducer; the output shaft of the three-stage planetary carrier (305) passes through the central through hole of the third stator end cover (211) and is fixedly connected to the rotating disk (105).

5. The adjustable rotational inertia reaction momentum wheel for satellite attitude control as claimed in claim 4, characterized in that: The planetary gear assembly (302) comprises a bearing end cover (3021), a planetary gear (3022) and a fourth bearing (3023); the bearing end cover (3021) is fixedly connected to the planetary gear (3022); and the fourth bearing (3023) is installed in a bearing installation groove of the planetary gear (3022).

6. The adjustable rotational inertia reaction momentum wheel for satellite attitude control as claimed in claim 5, characterized in that: One end surface of the second rotating end cover (207) is provided with stepped shafts evenly distributed around the circumference, and one end surface of the momentum wheel body (101) is provided with a circular hole fixedly matched with the stepped shaft.

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