CN113212807B - Control moment gyro frame rotor assembly for micro-nano satellite - Google Patents
Control moment gyro frame rotor assembly for micro-nano satellite Download PDFInfo
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- CN113212807B CN113212807B CN202110348506.1A CN202110348506A CN113212807B CN 113212807 B CN113212807 B CN 113212807B CN 202110348506 A CN202110348506 A CN 202110348506A CN 113212807 B CN113212807 B CN 113212807B
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- angular contact
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/28—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect
- B64G1/286—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect using control momentum gyroscopes (CMGs)
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
- H02K7/08—Structural association with bearings
- H02K7/083—Structural association with bearings radially supporting the rotary shaft at both ends of the rotor
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
- H02K7/14—Structural association with mechanical loads, e.g. with hand-held machine tools or fans
Abstract
The invention relates to a control moment gyro frame rotor assembly for a micro-nano satellite, which comprises the following components: the rotary mass body, the first angular contact ball bearing, the second angular contact ball bearing, the first bearing gland, the second bearing gland, the pre-tightening screw, the frame, the high-speed motor rotor and the high-speed motor stator; the rotary mass body, the first angular contact ball bearing, the second angular contact ball bearing, the first bearing gland, the second bearing gland and the frame form a sealing force system, and the pre-tightening screw applies pre-tightening force to the sealing force system through the bearing gland. The control moment gyro frame rotor assembly reduces the number of parts and the connecting links, saves the whole weight of the assembly, reduces the influence of wind resistance, shortens the time for the rotating mass body to reach the nominal rotating speed, realizes the function of controlling the moment gyro to quickly output the moment outwards, and solves the problem of quick and large-scale attitude maneuver of the micro-nano satellite.
Description
Technical Field
The invention relates to a control moment gyro frame rotor assembly for a micro-nano satellite, and belongs to the technical field of control moment gyroscopes for micro-nano satellites.
Background
The structure types of the control moment gyroscopes commonly used at present are of two types: a common gyroscopic structure and a cantilever structure. The large and medium control force gyroscopes mainly adopt a common gyroscopic structure, and the cantilever type structure is mainly applied to medium and small control force gyroscopes.
The common top structure has the advantages of strong resistance to chemical environment and suitability for realizing the infinite corner function of the frame, but has a slightly larger structural size. The cantilever structure has the advantages of compact structure, small volume and light weight, but has slightly poorer mechanical environment resistance. The cantilever type structural form is not suitable for the control moment gyro for the micro-nano satellite because a large frame shafting is required to be arranged to support the rotating mass body.
Disclosure of Invention
The invention solves the technical problems that: the invention provides the control moment gyro frame rotor component for the micro-nano satellite, which overcomes the defects of the prior art, realizes the lubrication life of the bearing in a space environment of 2 years under the condition that an oil supply system is not arranged, and can realize the rapid and large-scale attitude maneuver of the whole satellite.
The technical scheme of the invention is as follows: a control moment gyro frame rotor assembly for a micro-nano satellite comprising: the rotary mass body (1), the first angular contact ball bearing (2), the second angular contact ball bearing (6), the first bearing gland (3), the second bearing gland (5), the pre-tightening screw (4), the frame (7), the high-speed motor rotor (8) and the high-speed motor stator (9);
a rotating mass body (1), comprising: rim, spoke and center rotating shaft; the central rotating shaft is connected with the inner side of the wheel rim through spokes distributed along the circumferential direction, and the wheel rim and the central rotating shaft are coaxial;
the rim comprises an outer rim and an inner rim; the outer layer rim and the inner layer rim are coaxial hollow cylinders; a high-speed motor rotor (8) installation space is formed between the outer rim and the inner rim;
a frame (7) comprising: the motor comprises a U-shaped bracket (71), a first bearing mounting seat (72), a connecting beam (73), a motor stator mounting bracket (74) and a second bearing mounting seat (75);
one end of the U-shaped bracket (71) is provided with a first bearing mounting seat (72), and the first bearing mounting seat (72) is connected with a motor stator mounting bracket (74) through a connecting beam (73);
the other end of the U-shaped bracket is provided with a second bearing mounting seat (75);
one end of a central rotating shaft of the rotating mass body (1) is connected with a first bearing mounting seat (72) through a first angular contact ball bearing (2); the other end of the central rotating shaft of the rotating mass body (1) is connected with a second bearing mounting seat (75) through a second angular contact ball bearing (6);
the center of one side of the first bearing gland (3) is provided with a cylindrical boss which is contacted with the outer ring of the first angular contact ball bearing (2), and the edge of one side of the first bearing gland (3) is connected with the first bearing mounting seat (72) through a pre-tightening screw (4) so as to realize the pre-tightening function of the first angular contact ball bearing (2);
the center of one side of the second bearing cover (5) is provided with a column-shaped boss which is contacted with the outer ring of the second angular contact ball bearing (6), and the edge of one side of the second bearing cover (5) is connected with a second bearing mounting seat (75) through a pre-tightening screw (4) so as to realize the pre-tightening function of the second angular contact ball bearing (6);
the high-speed motor rotor (8) can be arranged in the installation space of the high-speed motor rotor (8), and the high-speed motor rotor (8) is a metal ring;
the high-speed motor stator (9) is arranged on the motor stator mounting bracket (74); the motor stator mounting bracket (74) is coaxial with the high-speed motor stator (9) and the high-speed motor rotor (8).
Preferably, the mass body (1) is rotated, providing a moment of inertia to establish angular momentum; a high-speed motor rotor (8) and a high-speed motor stator (9) provide driving torque for the rotary mass body (1) so that the working rotation speed of the rotary mass body (1) reaches 8000r/min and 16000r/min; the high-speed rotor shaft system is formed by the first angular contact ball bearing (2), the second angular contact ball bearing (6), the first bearing gland (3), the second bearing gland (5), the pre-tightening screw (4) and the frame (7), and the high-speed rotor shaft system provides support for the rotating mass body (1).
Preferably, the rotary mass body (1), the first angular contact ball bearing (2), the second angular contact ball bearing (6) and the frame (7) form a closed force system.
Preferably, the nominal rotational speed of the rotating mass body (1) and the high-speed motor rotor (8) is 8000r/min.
Preferably, the integrated motor rotor assembly reduces the number of parts and the connecting links, saves the overall weight of the assembly, reduces the wind resistance influence, shortens the time for the rotating mass body (1) to reach the nominal rotating speed, and realizes the function of controlling the moment gyro to quickly output the moment outwards.
Preferably, the design is simplified, an external oil supply system is omitted, and the two-year service life of the bearing can be ensured by adding base oil into the first angular contact ball bearing (2) and the second angular contact ball bearing (6) and controlling the oil content of the retainer of the first angular contact ball bearing (2) and the retainer of the second angular contact ball bearing (6), so that the rapid assembly of the high-speed shafting can be realized, and the weight of the assembly is reduced.
Preferably, when the frame rotor assembly is assembled, the high-speed motor rotor (8) is firstly arranged in the rotary mass body (1) and glued; then, the high-speed motor stator (9) is arranged in the rotary mass body (1), the high-speed motor rotor (8) and the high-speed motor stator (9) are arranged in the frame (7) through radial grooves of the first bearing mounting seat (72) and the second bearing mounting seat (75), and the high-speed motor stator (9) is fixed on the motor stator mounting bracket (74) through screws; the first angular contact ball bearing (2) is installed in the first bearing installation seat (72), the second angular contact ball bearing (6) is installed in the second bearing installation seat (75), the two bearings are arranged face to face, one end of the central rotating shaft of the rotating mass body (1) is installed in the inner ring of the first angular contact ball bearing (2), and the other end of the central rotating shaft of the rotating mass body (1) is installed in the inner ring of the second angular contact ball bearing (6); the first bearing gland (3) and the second bearing gland (5) are respectively arranged on the outer sides of the first bearing mounting seat (72) and the second bearing mounting seat (75), and a pre-tightening force is applied to the bearings through pre-tightening screws (4).
Preferably, the motor stator mounting bracket (74) is arc-shaped with an open arc center angle of 270 degrees; the adjacent two connecting beams form an included angle of 90 degrees.
Preferably, as shown in fig. 2, the frame (7) is of a U-shaped structure made of 9Cr18 stainless steel, and is integrally designed with the first bearing mounting seat (72), the second bearing mounting seat (75) and the motor stator mounting bracket (74), so that the heat conduction and heat dissipation capacity of the structure are improved.
Compared with the prior art, the invention has the advantages that:
(1) According to the control moment gyro frame rotor assembly for the micro-nano satellite, a pair of angle contact ball bearings are arranged face to be used as a rotary support of a rotary mass body, and under the condition that an oil supply system is not arranged, the space environment lubrication service life of the bearing for 2 years is realized by adding bearing base oil and controlling the oil content of a bearing retainer.
(2) The invention embeds the high-speed motor rotor into the rotating mass body to form an integrated motor rotor assembly.
(3) The integrated frame is designed to realize precise support of the high-speed rotor assembly including the diagonal contact ball bearing, the rotating mass body, the high-speed motor stator and the like.
(4) The invention provides a control moment gyro frame rotor assembly for a micro-nano satellite, which adopts a pair of angle contact ball bearings to be installed face to face as a rotary support of a rotary mass body, realizes the lubrication life of the space environment of the bearing for 2 years by adding base oil and controlling the oil content of a bearing retainer under the condition of not arranging an oil supply system, embeds a high-speed motor rotor into the rotary mass body to form an integrated motor rotor assembly, designs an integrated frame to realize the precise support of the high-speed rotor assembly including the angle contact ball bearings, the rotary mass body, a high-speed motor stator and the like, and can realize the rapid and large-scale gesture maneuvering of the whole satellite.
Drawings
FIG. 1 is a perspective view of a control moment gyro frame rotor assembly for a micro-nano satellite of the present invention;
FIG. 2 is a perspective view of a frame of the present invention;
fig. 3 is a perspective view of a rotating mass body according to the present invention.
FIG. 4 is a cross-sectional view of the rotary mass body of the invention
Detailed Description
The invention is described in further detail below with reference to the drawings and the specific embodiments.
Along with the maturation and development of the micro-nano satellite technology, the application occasions of the micro-nano satellite are more and more, the load carried by the satellite is more and more complex, the requirement on the satellite stability index is also higher and higher, and the device based on angular momentum exchange is required to complete the fine control. The control moment gyro has the advantages of large output moment, continuous and adjustable output moment, high energy efficiency ratio, no fuel consumption and no pollution, and is a requisite choice for a new generation of fast maneuvering, high precision and high stability spacecraft platform. The control moment gyro is used as a gesture actuating mechanism of the micro-nano satellite, so that the whole satellite can realize rapid and large-scale gesture maneuver.
The frame rotor assembly is a key component for controlling the output angular momentum of the moment gyro, and has the main characteristics of light weight, large output angular momentum, simple structure and quick assembly. The invention mainly aims at the characteristics of the control moment gyro for the micro-nano satellite, and provides a control moment gyro frame rotor assembly for the micro-nano satellite, so that engineering prototype development is completed, and an authentication level force and heat environment test is passed.
As shown in fig. 1, a control moment gyro frame rotor assembly for a micro/nano satellite according to the present invention includes: the rotary mass body (1), the first angular contact ball bearing (2), the second angular contact ball bearing (6), the first bearing gland (3), the second bearing gland (5), the pre-tightening screw (4), the frame (7), the high-speed motor rotor (8) and the high-speed motor stator (9);
a rotating mass body (1), as shown in fig. 3 and 4, comprising: rim, spoke and center rotating shaft; the central rotating shaft is connected with the inner side of the wheel rim through spokes distributed along the circumferential direction, and the wheel rim and the central rotating shaft are coaxial; an outer circular surface at one end of the central rotating shaft is matched with an inner ring of the first angular contact ball bearing (2), so that a preferable bilateral gap is ensured to be 1-3 mu m; the outer circular surface of the other end of the central rotating shaft is matched with the inner ring of the second angular contact ball bearing (6), so that the preferable bilateral gap is ensured to be 1-3 mu m;
the rim comprises an outer rim and an inner rim; the outer layer rim and the inner layer rim are coaxial hollow cylinders; a high-speed motor rotor (8) installation space is formed between the outer rim and the inner rim;
a frame (7) comprising: the motor comprises a U-shaped bracket (71), a first bearing mounting seat (72), a connecting beam (73), a motor stator mounting bracket (74) and a second bearing mounting seat (75); FIG. 2 is a perspective view of a frame of the present invention;
one end of the U-shaped bracket (71) is provided with a first bearing mounting seat (72), and the first bearing mounting seat (72) is connected with a motor stator mounting bracket (74) through a connecting beam (73); the motor stator mounting bracket (74) is arc-shaped with an arc core angle of 270 degrees; the adjacent two connecting beams form an included angle of 90 degrees;
the other end of the U-shaped bracket is provided with a second bearing mounting seat (75);
one end of a central rotating shaft of the rotating mass body (1) is connected with an inner hole of a first bearing mounting seat (72) through an outer ring of a first angular contact ball bearing (2), so that a preferable bilateral gap is ensured to be 3-5 mu m; the other end of the central rotating shaft of the rotating mass body (1) is connected with an inner hole of a second bearing mounting seat (75) through an outer ring of a second angular contact ball bearing (6), so that a preferable bilateral gap is ensured to be 3-5 mu m;
the center of one side of the first bearing gland (3) is provided with a cylindrical boss which is contacted with the outer ring of the first angular contact ball bearing (2), and the edge of one side of the first bearing gland (3) is connected with the first bearing mounting seat (72) through a pre-tightening screw (4) so as to realize the pre-tightening function of the first angular contact ball bearing (2);
the center of one side of the second bearing cover (5) is provided with a column-shaped boss which is contacted with the outer ring of the second angular contact ball bearing (6), and the edge of one side of the second bearing cover (5) is connected with a second bearing mounting seat (75) through a pre-tightening screw (4) so as to realize the pre-tightening function of the second angular contact ball bearing (6);
the high-speed motor rotor (8) can be arranged in the installation space of the high-speed motor rotor (8), and the high-speed motor rotor (8) is a metal ring;
the high-speed motor stator (9) is arranged on the motor stator mounting bracket (74); the motor stator mounting bracket (74) is coaxial with the high-speed motor stator (9) and the high-speed motor rotor (8).
The preferable scheme is as follows: -rotating the mass body (1), providing a moment of inertia to establish angular momentum; a high-speed motor rotor (8) and a high-speed motor stator (9) provide driving torque for the rotary mass body (1) so that the working rotation speed of the rotary mass body (1) reaches 8000r/min and 16000r/min; the high-speed rotor shaft system is formed by the first angular contact ball bearing (2), the second angular contact ball bearing (6), the first bearing gland (3), the second bearing gland (5), the pre-tightening screw (4) and the frame (7), and the high-speed rotor shaft system provides support for the rotating mass body (1).
The preferable scheme is as follows: the rotary mass body (1), the first angular contact ball bearing (2), the second angular contact ball bearing (6) and the frame (7) form a closed force system.
The preferable scheme is as follows: the nominal rotational speed of the rotating mass body (1) and the high-speed motor rotor (8) is preferably 8000r/min.
The preferable scheme is as follows: the integrated motor rotor assembly reduces the number of parts and the connecting links, saves the overall weight of the assembly, reduces the wind resistance influence, shortens the time for the rotating mass body (1) to reach the nominal rotating speed, and realizes the function of controlling the moment gyro to quickly output the moment outwards.
The preferable scheme is as follows: the design is simplified to high-speed shafting, has cancelled outside oil feeding system, through adding base oil and control first angular contact ball bearing (2) and second angular contact ball bearing (6) oil content of second angular contact ball bearing (6) holder in first angular contact ball bearing (2), can guarantee the two years life of bearing, can realize high-speed shafting's quick assembly, lighten the subassembly weight.
The preferable scheme is as follows: when the frame rotor assembly is assembled, firstly, the high-speed motor rotor (8) is arranged in the rotary mass body (1) and glued; then, the high-speed motor stator (9) is arranged in the rotary mass body (1), the high-speed motor rotor (8) and the high-speed motor stator (9) are arranged in the frame (7) through radial grooves of the first bearing mounting seat (72) and the second bearing mounting seat (75), and the high-speed motor stator (9) is fixed on the motor stator mounting bracket (74) through screws; the first angular contact ball bearing (2) is installed in the first bearing installation seat (72), the second angular contact ball bearing (6) is installed in the second bearing installation seat (75), the two bearings are arranged face to face, one end of the central rotating shaft of the rotating mass body (1) is installed in the inner ring of the first angular contact ball bearing (2), and the other end of the central rotating shaft of the rotating mass body (1) is installed in the inner ring of the second angular contact ball bearing (6); the first bearing gland (3) and the second bearing gland (5) are respectively arranged on the outer sides of the first bearing mounting seat (72) and the second bearing mounting seat (75), and a pre-tightening force is applied to the bearings through pre-tightening screws (4).
The preferable scheme is as follows: the rotary mass body (1), preferably a wheel body structure made of 2Cr13 stainless steel, consists of a rim, spokes and a central rotating shaft, wherein the central rotating shaft is connected with the rim through 5 rectangular cylindrical spokes which are evenly distributed in the circumference, so that a large inertia/mass ratio is realized, the cross section of the rotary mass body (1) passing through the spokes is I-shaped, and the cross section of the rotary mass body is shown in FIG. 4. In order to improve the running stability of the frame rotor assembly, the following design indexes of the rotary mass body are controlled: as shown in fig. 4, the concentricity of the cylindrical surface 1 and the cylindrical surface 2 is preferably Φ3 μm, the verticality of the side surface 3 and the cylindrical surface 1 is preferably 3 μm, the verticality of the side surface 4 and the cylindrical surface 2 is preferably 3 μm, the verticality of the side surface 5 and the cylindrical surface 1 is preferably 3 μm, the verticality of the side surface 6 and the cylindrical surface 2 is preferably 3 μm, and the concentricity of the cylindrical surface 7 and the cylindrical surfaces 1 and 2 is preferably Φ5 μm; a groove is formed in one side face of the rim, and is a high-speed motor rotor installation space, so that an integrated motor rotor assembly is formed. Because the high-strength stainless steel material is adopted as the wheel body material, the wheel body can still maintain higher structural stability at the rotating speed of 8000r/min and even 16000 r/min.
The preferable scheme is as follows: the first bearing gland (3) is of a 9Cr18 stainless steel structure, and has good heat matching performance with the first bearing mounting seat (72) and the first angular contact ball bearing (2).
The preferable scheme is as follows: the second bearing cap (5), preferably 9Cr18 stainless steel, has good thermal matching with the second bearing mount (75) and the second angular ball bearing (6).
The preferable scheme is as follows: the frame (7) is preferably of a U-shaped structure made of 9Cr18 stainless steel, is integrally designed with the first bearing mounting seat (72), the second bearing mounting seat (75) and the motor stator mounting bracket (74), and increases the heat conduction and heat dissipation capacity of the structure; to ensure stable operation of the bearing, as shown in fig. 2, which is a cross-sectional view of the frame (7), the relative concentricity of the inner hole cylindrical surface of the first bearing mount (72) and the inner hole cylindrical surface of the second bearing mount (75) is designed to be preferably phi 3 μm; in order to ensure the accurate loading of the first angular contact ball bearing (2) by the first bearing gland (3), the perpendicularity of the designed side surface relative to the cylindrical surface is preferably 3 mu m; in order to ensure the accurate loading of the second angular contact ball bearing (6) by the bearing cap (5), the perpendicularity of the design side surface relative to the cylindrical surface is preferably 3 mu m; the span between the first bearing mount (72) and the second bearing mount (75) is preferably 38.5mm, which ensures that the maximum gyroscopic moment generated by the frame rotor assembly during operation produces a counter force to the bearing within the range allowed by the bearing design life.
The preferable scheme is as follows: the high-speed motor rotor (8) is nested in the rotating mass body (1) to form an integrated motor rotor assembly, so that the number of parts and connecting links are reduced, the overall weight of the assembly is saved, the influence of wind resistance is reduced, the time for the rotating mass 1 to reach the nominal rotating speed is shortened, and the function of controlling the moment gyro to rapidly output moment outwards is realized.
The frame is a frame (7) with integrated design, and one side of the frame is provided with a motor stator mounting bracket (74) with a circumferential angle of 270 degrees for fixing a high-speed motor stator (9); the radial positions of the first bearing mounting seat (72) and the second bearing mounting seat (75) on the frame (7) are grooved, and the grooves can ensure that the rotary mass body (1) is smoothly installed in the frame (7).
When the frame rotor assembly is assembled, firstly, the high-speed motor rotor (8) is arranged in the rotary mass body (1) and glued; then, the high-speed motor stator (9) is arranged in the rotary mass body (1), the high-speed motor rotor (8) and the high-speed motor stator (9) are arranged in the frame (7) through radial grooves of the first bearing mounting seat (72) and the second bearing mounting seat (75), and the high-speed motor stator (9) is fixed on the motor stator mounting bracket (74) through screws; the first angular contact ball bearing (2) is installed in the first bearing installation seat (72), the second angular contact ball bearing (6) is installed in the second bearing installation seat (75), the two bearings are arranged face to face, one end of the central rotating shaft of the rotating mass body (1) is installed in the inner ring of the first angular contact ball bearing (2), and the other end of the central rotating shaft of the rotating mass body (1) is installed in the inner ring of the second angular contact ball bearing (6); the first bearing gland (3) and the second bearing gland (5) are respectively arranged on the outer sides of the first bearing mounting seat (72) and the second bearing mounting seat (75), and a pre-tightening force is applied to the bearings through pre-tightening screws (4).
The design is simplified to high-speed shafting, has cancelled outside oil feeding system, through adding base oil and control first angular contact ball bearing (2) and second angular contact ball bearing (6) oil content of second angular contact ball bearing (6) holder in first angular contact ball bearing (2), can guarantee the two years life of bearing, can realize high-speed shafting's quick assembly, lighten the subassembly weight.
The frame rotor assembly adopts a double-end supporting structural form to improve the supporting rigidity of a shafting, and comprises a rotary mass body (1), a first angular contact ball bearing (2), a second angular contact ball bearing (6), a first bearing gland (3), a second bearing cover (5), a pre-tightening screw (4), a frame (7), a high-speed motor rotor (8) and a high-speed motor stator (9), wherein the frame (7), the first angular contact ball bearing (2), the second angular contact ball bearing (6) and the rotary mass body (1) form a closed force system, and the bearings are positioned and pre-tightened by the first bearing gland (3) and the second bearing cover (5).
The invention realizes the further scheme of improving the running stability of the frame rotor assembly: repairing and grinding the first bearing gland (3) and the second bearing gland (5) to load the first angular contact ball bearing (2) and the second angular contact ball bearing (6), wherein the pre-load is 15N, and the consistent protruding amount of the gland is ensured as much as possible; the cylindrical surface at one end of the central rotating shaft of the rotating mass body (1) is matched with the inner ring of the first angular contact ball bearing (2), so that the bilateral gap is ensured to be 1-3 mu m; the cylindrical surface at the other end of the central rotating shaft of the rotating mass body (1) is matched with the inner ring of the second angular contact ball bearing (6), so that the bilateral gap is ensured to be 1-3 mu m; an inner hole of the first bearing mounting seat (72) is matched with an outer ring of the first angular contact ball bearing (2), so that a bilateral gap is ensured to be 3-5 mu m; the second bearing mounting seat (75) is matched with the outer ring of the second angular contact ball bearing (6) to ensure that the bilateral gap is 3-5 mu m; satisfying the above-described preferable constraint conditions, further improvement in the operational stability of the frame rotor can be achieved.
According to the control moment gyro frame rotor assembly for the micro-nano satellite, a pair of angle contact ball bearings are arranged face to be used as a rotary support of a rotary mass body, and under the condition that an oil supply system is not arranged, the lubrication life of the bearing in a space environment for 2 years is realized by adding bearing base oil and controlling the oil content of a bearing retainer; and the invention embeds the high-speed motor rotor into the rotating mass body to form an integrated motor rotor assembly.
The integrated frame is designed to realize precise support of the high-speed rotor assembly including the diagonal contact ball bearing, the rotating mass body, the high-speed motor stator and the like; the invention provides a control moment gyro frame rotor assembly for a micro-nano satellite, which adopts a pair of angle contact ball bearings to be installed face to face as a rotary support of a rotary mass body, realizes the lubrication life of the space environment of the bearing for 2 years by adding base oil and controlling the oil content of a bearing retainer under the condition of not arranging an oil supply system, embeds a high-speed motor rotor into the rotary mass body to form an integrated motor rotor assembly, designs an integrated frame to realize the precise support of the high-speed rotor assembly including the angle contact ball bearings, the rotary mass body, a high-speed motor stator and the like, and can realize the rapid and wide-range gesture maneuvering of the whole satellite.
Claims (7)
1. The utility model provides a control moment gyro frame rotor subassembly for micro-nano satellite which characterized in that includes: the rotary mass body (1), the first angular contact ball bearing (2), the second angular contact ball bearing (6), the first bearing gland (3), the second bearing gland (5), the pre-tightening screw (4), the frame (7), the high-speed motor rotor (8) and the high-speed motor stator (9);
a rotating mass body (1), comprising: rim, spoke and center rotating shaft; the central rotating shaft is connected with the inner side of the wheel rim through spokes distributed along the circumferential direction, and the wheel rim and the central rotating shaft are coaxial;
the rim comprises an outer rim and an inner rim; the outer layer rim and the inner layer rim are coaxial hollow cylinders; a high-speed motor rotor (8) installation space is formed between the outer rim and the inner rim;
a frame (7) comprising: the motor comprises a U-shaped bracket (71), a first bearing mounting seat (72), a connecting beam (73), a motor stator mounting bracket (74) and a second bearing mounting seat (75);
one end of the U-shaped bracket (71) is provided with a second bearing mounting seat (75), and the second bearing mounting seat (75) is connected with a motor stator mounting bracket (74) through a connecting beam (73);
the other end of the U-shaped bracket is provided with a first bearing mounting seat (72);
one end of a central rotating shaft of the rotating mass body (1) is connected with a first bearing mounting seat (72) through a first angular contact ball bearing (2); the other end of the central rotating shaft of the rotating mass body (1) is connected with a second bearing mounting seat (75) through a second angular contact ball bearing (6);
the center of one side of the first bearing gland (3) is provided with a cylindrical boss which is contacted with the outer ring of the first angular contact ball bearing (2), and the edge of one side of the first bearing gland (3) is connected with the first bearing mounting seat (72) through a pre-tightening screw (4) so as to realize the pre-tightening function of the first angular contact ball bearing (2);
the center of one side of the second bearing cover (5) is provided with a column-shaped boss which is contacted with the outer ring of the second angular contact ball bearing (6), and the edge of one side of the second bearing cover (5) is connected with a second bearing mounting seat (75) through a pre-tightening screw (4) so as to realize the pre-tightening function of the second angular contact ball bearing (6);
the high-speed motor rotor (8) can be arranged in the installation space of the high-speed motor rotor (8), and the high-speed motor rotor (8) is a metal ring;
the high-speed motor stator (9) is arranged on the motor stator mounting bracket (74); the motor stator mounting bracket (74) is coaxial with the high-speed motor stator (9) and the high-speed motor rotor (8);
repairing and grinding a first bearing gland (3) and a second bearing gland (5), loading a first angular contact ball bearing (2) and a second angular contact ball bearing (6), and ensuring consistent gland protrusion; the cylindrical surface at one end of the central rotating shaft of the rotating mass body (1) is matched with the inner ring of the first angular contact ball bearing (2); the cylindrical surface at the other end of the central rotating shaft of the rotating mass body (1) is matched with the inner ring of the second angular contact ball bearing (6); an inner hole of the first bearing mounting seat (72) is matched with an outer ring of the first angular contact ball bearing (2); the second bearing mounting seat (75) is matched with the outer ring of the second angular contact ball bearing (6);
the rotary mass body (1), the first angular contact ball bearing (2), the second angular contact ball bearing (6) and the frame (7) form a closed force system;
the motor stator mounting bracket (74) is arc-shaped with an arc core angle of 270 degrees; the adjacent two connecting beams form an included angle of 90 degrees.
2. The control moment gyro frame rotor assembly for micro-nano satellites according to claim 1, wherein: -rotating the mass body (1), providing a moment of inertia to establish angular momentum; a high-speed motor rotor (8) and a high-speed motor stator (9) provide driving torque for the rotary mass body (1) so that the working rotation speed of the rotary mass body (1) reaches 8000r/min and 16000r/min; the high-speed rotor shaft system is formed by the first angular contact ball bearing (2), the second angular contact ball bearing (6), the first bearing gland (3), the second bearing gland (5), the pre-tightening screw (4) and the frame (7), and the high-speed rotor shaft system provides support for the rotating mass body (1).
3. The control moment gyro frame rotor assembly for micro-nano satellites according to claim 1, wherein: the nominal rotation speed of the rotary mass body (1) and the high-speed motor rotor (8) is 8000r/min.
4. The control moment gyro frame rotor assembly for micro-nano satellites according to claim 1, wherein: the integrated motor rotor assembly reduces the number of parts and the connecting links, saves the overall weight of the assembly, reduces the wind resistance influence, shortens the time for the rotating mass body (1) to reach the nominal rotating speed, and realizes the function of controlling the moment gyro to quickly output the moment outwards.
5. The control moment gyro frame rotor assembly for micro-nano satellites according to claim 1, wherein: the design is simplified to high-speed shafting, has cancelled outside oil feeding system, through adding base oil and control first angular contact ball bearing (2) and second angular contact ball bearing (6) oil content of second angular contact ball bearing (6) holder in first angular contact ball bearing (2), can guarantee the two years life of bearing, can realize high-speed shafting's quick assembly, lighten the subassembly weight.
6. The control moment gyro frame rotor assembly for micro-nano satellites according to claim 1, wherein: when the frame rotor assembly is assembled, firstly, the high-speed motor rotor (8) is arranged in the rotary mass body (1) and glued; then, the high-speed motor stator (9) is arranged in the rotary mass body (1), the high-speed motor rotor (8) and the high-speed motor stator (9) are arranged in the frame (7) through radial grooves of the first bearing mounting seat (72) and the second bearing mounting seat (75), and the high-speed motor stator (9) is fixed on the motor stator mounting bracket (74) through screws; the first angular contact ball bearing (2) is installed in the first bearing installation seat (72), the second angular contact ball bearing (6) is installed in the second bearing installation seat (75), the two bearings are arranged face to face, one end of the central rotating shaft of the rotating mass body (1) is installed in the inner ring of the first angular contact ball bearing (2), and the other end of the central rotating shaft of the rotating mass body (1) is installed in the inner ring of the second angular contact ball bearing (6); the first bearing gland (3) and the second bearing gland (5) are respectively arranged on the outer sides of the first bearing mounting seat (72) and the second bearing mounting seat (75), and a pre-tightening force is applied to the bearings through pre-tightening screws (4).
7. The control moment gyro frame rotor assembly for micro-nano satellites according to claim 1, wherein: an outer circular surface at one end of the central rotating shaft is matched with an inner ring of the first angular contact ball bearing (2); the outer circular surface of the other end of the central rotating shaft is matched with the inner ring of the second angular contact ball bearing (6).
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| CN202110348506.1A CN113212807B (en) | 2021-03-31 | 2021-03-31 | Control moment gyro frame rotor assembly for micro-nano satellite |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104075700A (en) * | 2014-06-26 | 2014-10-01 | 北京控制工程研究所 | Small-size speed change control moment gyroscope |
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| DE3241373A1 (en) * | 1982-11-09 | 1984-05-10 | Anschütz & Co GmbH, 2300 Kiel | Spring joint |
| FR2837580B1 (en) * | 2002-03-21 | 2005-06-03 | Astrium Sas | GYROSCOPIC ACTUATOR FOR PILOTTING THE ATTITUDE OF A SPATIAL VEHICLE |
| CN102435182B (en) * | 2012-01-04 | 2015-10-21 | 洛阳轴研科技股份有限公司 | A kind of high speed rotor and use the control-moment gyro of this rotor |
| CN107539498B (en) * | 2017-07-28 | 2019-10-22 | 北京控制工程研究所 | A kind of Modularized micro control-moment gyro overall structure |
| CN107741746B (en) * | 2017-10-13 | 2020-10-16 | 北京航空航天大学 | Frame system for control moment gyroscope |
| CN108945525B (en) * | 2018-05-24 | 2024-02-13 | 南京航空航天大学 | Small frame type control moment gyro driven by hollow ultrasonic motor |
| CN108562285A (en) * | 2018-05-28 | 2018-09-21 | 南京航空航天大学 | A kind of control-moment gyro driven by parallel linear type ultrasound motor |
| CN112039244B (en) * | 2020-08-12 | 2021-09-07 | 北京控制工程研究所 | Control moment gyro frame rotor assembly of precise support and assembling method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104075700A (en) * | 2014-06-26 | 2014-10-01 | 北京控制工程研究所 | Small-size speed change control moment gyroscope |
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