CN110949691A - High-precision electromagnetic clutch type variable inertia reaction flywheel - Google Patents
High-precision electromagnetic clutch type variable inertia reaction flywheel Download PDFInfo
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- CN110949691A CN110949691A CN201911319505.3A CN201911319505A CN110949691A CN 110949691 A CN110949691 A CN 110949691A CN 201911319505 A CN201911319505 A CN 201911319505A CN 110949691 A CN110949691 A CN 110949691A
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- 238000000926 separation method Methods 0.000 claims abstract description 4
- 238000007789 sealing Methods 0.000 claims description 18
- 230000006698 induction Effects 0.000 claims description 15
- 230000006641 stabilisation Effects 0.000 claims description 9
- 238000011105 stabilization Methods 0.000 claims description 9
- 230000007704 transition Effects 0.000 claims description 6
- 238000005086 pumping Methods 0.000 claims description 5
- 230000008054 signal transmission Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 description 8
- 238000005461 lubrication Methods 0.000 description 4
- 239000007787 solid Substances 0.000 description 3
- 230000001050 lubricating effect Effects 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
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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
- B64G1/283—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect using reaction wheels
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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
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Abstract
In order to solve the technical problems that the existing variable inertia reaction flywheel has complex structure, large size and higher requirements on a control circuit and an algorithm and is difficult to realize aerospace productization, the invention provides a high-precision electromagnetic clutch type variable inertia reaction flywheel, which comprises an attitude maneuver additional flywheel body, an attitude stable flywheel body and a switching mechanism for realizing combination and separation of the attitude maneuver additional flywheel body and the attitude stable flywheel body; the posture maneuvering additional flywheel body and the posture stabilizing flywheel body are both of traditional flywheel structures, so that very high dynamic unbalance balancing can be realized, the reaction flywheel can be ensured to stably rotate no matter the reaction flywheel works at a high speed or at a low speed, the requirements on a control circuit and an algorithm of the control circuit are low, and the engineering realization is facilitated.
Description
Technical Field
The invention relates to a reaction flywheel for spacecraft attitude control, in particular to a variable inertia reaction flywheel of a driving actuating mechanism shared by spacecraft attitude stabilization and attitude maneuver.
Background
The reaction flywheel is used as an important attitude control driving execution mechanism of the spacecraft, the main working principle is the momentum moment law, and the attitude stability or attitude maneuver of the spacecraft is realized by driving the reaction flywheel to obtain the reaction moment.
Generally, the attitude stabilization of a spacecraft requires that the output torque of a reaction flywheel is small and fine, and the high-precision attitude stabilization and adjustment are carried out by a flywheel structure with small inertia and high rotating speed; the attitude maneuver of the spacecraft requires that the reaction flywheel has large output torque and is rapid, and the flywheel structure has large inertia and low rotating speed to realize large-angle rapid maneuvering attitude adjustment. Because the two control purposes are obviously different, two sets of systems are usually adopted in engineering to realize the control.
The variable inertia reaction flywheel is based on the same driving circuit and the same driving motor, can realize the posture stabilizing function of small inertia and high rotating speed by changing the inertia of the flywheel body, can also realize the novel reaction flywheel of the posture maneuvering function of large inertia and low rotating speed, and hopefully realizes the integration of two original systems, thereby improving the functional density and efficiency of the spacecraft and meeting the development trend and demand of the future spacecraft.
The principle of the variable inertia reaction flywheel disclosed in the existing domestic and foreign documents and patents is that a balancing weight in a flywheel assembly is driven to move along a guide rod through the matching transmission of a lead screw and a lead screw nut, and the inertia radius of the balancing weight is adjusted and controlled, so that the rotational inertia of the flywheel assembly is changed. Variable inertia reaction flywheels based on this principle suffer from the following disadvantages:
1. the structure size is large, the structure and the movement mechanism are complex, and when the reaction flywheel works in a high-speed state, a corresponding locking mechanism needs to be designed for the balancing weight;
2. the rotation stability at high speed is difficult to ensure, so the requirements on a control circuit and a control algorithm are high, and the engineering realization is not facilitated;
3. because the size is great, be difficult for realizing sealed, therefore lubricated mode can only adopt solid lubrication, and solid lubrication technique is high-speed under the space environment, long-life theory and technique are not mature yet, when the reaction flywheel is in high rotational speed operating mode, phenomena such as increase of friction torque, jamming, wearing and tearing aggravation appear easily, and the reliability is not high.
In conclusion, the existing variable inertia reaction flywheel is difficult to realize aerospace productization.
Disclosure of Invention
The invention provides a high-precision electromagnetic clutch type variable inertia reaction flywheel, which aims to solve the technical problems that the existing variable inertia reaction flywheel is complex in structure, large in size, high in requirements on a control circuit and an algorithm and difficult to realize aerospace productization.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
a high-precision electromagnetic clutch type variable inertia reaction flywheel is characterized in that: the device comprises a motor stator, a whole star interface flange, a vacuum sealing shell, a motor rotor, an attitude stabilizing flywheel body assembly, an attitude maneuvering additional flywheel body assembly and an electromagnetic clutch assembly;
the motor stator comprises a hollow long shaft, and the bottom of the hollow long shaft extends outwards to form a base; a cable connector is fixedly arranged at the bottom of the hollow long shaft of the motor stator and used for power supply and signal transmission, and a circular induction synchronizer rotor and stator is fixedly arranged at the top of the hollow long shaft of the motor stator;
the whole star interface flange is fixedly connected with a motor stator, and the joint surface is sealed by a vacuum sealing ring; the whole star interface flange is also provided with a vacuum pumping nozzle;
the vacuum sealing shell is fixedly connected with the whole star interface flange after being buckled, and the joint surface is sealed by a vacuum sealing ring;
the vacuum sealing shell, the whole star interface flange and the motor stator together form a mounting cavity of the motor rotor, the attitude stable flywheel body assembly and the attitude maneuver additional flywheel body assembly;
the motor rotor is a hollow long shaft, and a motor magnetic pole is arranged in the motor rotor; the motor rotor is sleeved outside the motor stator; a circular induction synchronizer rotor is arranged between the motor rotor and the motor stator, and a gap is formed between the circular induction synchronizer rotor and the motor stator;
the attitude stabilizing flywheel body assembly comprises an attitude stabilizing flywheel bearing, an attitude stabilizing flywheel bearing inner shaft sleeve, an attitude stabilizing flywheel body and an attitude stabilizing flywheel bearing outer shaft sleeve which are sequentially arranged from bottom to top;
the attitude maneuver additional flywheel body assembly comprises an outer shaft sleeve of a maneuvering flywheel bearing, an attitude maneuver additional flywheel body and a maneuvering flywheel bearing;
the attitude stabilizing flywheel bearing is sleeved outside the motor rotor, the inner ring of the attitude stabilizing flywheel bearing is in interference fit with the motor rotor, and the outer ring of the attitude stabilizing flywheel bearing is installed in the whole satellite interface flange in a transition fit manner;
the bottom of an inner shaft sleeve of the posture stabilizing flywheel bearing is fixedly connected with a motor rotor, the bottom of the inner shaft sleeve of the posture stabilizing flywheel bearing simultaneously compresses an inner ring of the posture stabilizing flywheel bearing, and the bearing pre-tightening force of the posture stabilizing flywheel bearing is adjusted by adjusting the size of the inner shaft sleeve of the posture stabilizing flywheel bearing; the upper part of the inner shaft sleeve of the attitude stabilizing flywheel bearing is fixedly connected with an attitude stabilizing flywheel body;
the outer shaft sleeve of the attitude stabilizing flywheel bearing is fixedly connected with the whole star interface flange; the outer shaft sleeve of the posture stabilizing flywheel bearing is of a hollow shaft-shaped structure, and the inner side wall and the outer side wall of the outer shaft sleeve are step surfaces; the inner side of the bottom of the outer shaft sleeve of the posture stabilizing flywheel bearing compresses an outer ring of the posture stabilizing flywheel bearing, and the outer side of the bottom compresses an inner ring of the motorized flywheel bearing; an electromagnetic clutch coil is fixedly arranged on the outer side of the outer shaft sleeve of the posture stabilizing flywheel bearing;
the lower part of the outer shaft sleeve of the motorized flywheel bearing is fixedly connected with the upper part of the attitude motorized additional flywheel body; the attitude maneuver additional flywheel body is in transition fit and fixed connection with the outer ring of the maneuvering flywheel bearing; the bottom of the outer shaft sleeve of the motorized flywheel bearing simultaneously presses the outer ring of the motorized flywheel bearing, and the bearing pre-tightening force of the motorized flywheel bearing is adjusted by finishing the size of the outer shaft sleeve of the motorized flywheel bearing; a second disc gear meshed with the first disc gear is arranged at the corresponding position of the top of the outer shaft sleeve of the motorized flywheel bearing;
the electromagnetic clutch assembly is arranged on the outer side wall of the inner shaft sleeve of the stable-posture flywheel bearing and used for realizing combination and separation of the inner shaft sleeve of the stable-posture flywheel bearing and the outer shaft sleeve of the motorized flywheel bearing.
Furthermore, the electromagnetic clutch assembly comprises an electromagnetic clutch suction disc, a plate-shaped spring for resetting the suction disc, a first disc gear and a second disc gear which are meshed in a matched manner;
the electromagnetic clutch actuation disc is arranged on the outer side wall of the inner shaft sleeve of the posture stabilizing flywheel bearing in a sliding manner; one end of the plate-shaped spring is connected with the electromagnetic clutch actuation disc, and the other end of the plate-shaped spring is connected with the inner shaft sleeve of the attitude stabilizing flywheel bearing; the first disc gear is arranged at the bottom of the electromagnetic clutch attraction disc, and the first disc gear is arranged at the top of the outer shaft sleeve of the motorized flywheel bearing.
Furthermore, a spline groove is formed in the outer side wall of the inner shaft sleeve of the posture stabilizing flywheel bearing, a spline is formed in the side wall of the electromagnetic clutch actuation disc, and the electromagnetic clutch actuation disc can slide up and down along the inner shaft sleeve of the posture stabilizing flywheel bearing through the matching of the spline and the spline groove.
Furthermore, a clearance of more than 1mm is reserved between the outer shaft sleeve of the posture stabilizing flywheel bearing and the outer shaft sleeve of the motorized flywheel bearing.
Furthermore, a gap of more than 1mm is reserved between the whole satellite interface flange and the attitude maneuver additional flywheel body.
Furthermore, a clearance of more than 1mm is reserved between the inner shaft sleeve of the posture stabilizing flywheel bearing and the outer shaft sleeve of the posture stabilizing flywheel bearing.
Furthermore, a gap of more than 1mm is reserved between the attitude stabilization flywheel body and the attitude maneuver additional flywheel body.
Furthermore, a gap of more than 1mm is reserved between the whole star interface flange and the motor rotor.
The invention has the beneficial effects that:
1. the posture maneuvering additional flywheel body and the posture stabilizing flywheel body both adopt traditional flywheel structures, so that very high dynamic unbalance balancing can be realized, the reaction flywheel can be ensured to stably rotate no matter the reaction flywheel works at a high speed or at a low speed, the requirements on a control circuit and an algorithm of the control circuit are low, and the engineering realization is facilitated.
2. Compared with the traditional reaction flywheel which adopts 3 Hall sensors in a motor to acquire the rotating speed of the flywheel, the reaction flywheel provided by the invention is provided with a circular induction synchronizer coaxially with the motor to acquire the angle and the speed of the flywheel, and the angle measurement precision and the speed measurement precision of the circular induction synchronizer are far higher than those of the 3 Hall sensors, so that high-precision angle and speed feedback information is provided for a control circuit.
3. Because the invention has small size, the vacuum sealing process of the traditional counteractive flywheel is easy to adopt, the influence of air resistance can be not considered in the rotation process of the flywheel body (the influence of nonlinear air resistance is required to be considered in the rotation stability of the flywheel under non-vacuum), and the rotation speed and the torque precision are higher.
4. Because the invention adopts the vacuum sealing process of the traditional reaction flywheel, the lubricating systems of the posture-stabilizing flywheel bearing and the motorized flywheel bearing can adopt mature oil lubricating modes. Compared with the common solid lubrication mode of the aerospace mechanism, the oil lubrication mode has the advantages of small friction force, small nonlinear gradient, high rotation precision and long service life. In summary, the bearings can be lubricated with oil to improve rotational accuracy.
5. The device has a simple structure and reasonable and feasible design, and can adjust the pretightening force of the attitude stabilizing flywheel bearing and the motorized flywheel bearing and the coaxiality of the attitude motorized additional flywheel body and the attitude stabilizing flywheel body by adjusting the sizes of the inner shaft sleeve of the attitude stabilizing flywheel bearing, the outer shaft sleeve of the attitude stabilizing flywheel bearing and the outer shaft sleeve of the motorized flywheel bearing, thereby ensuring the speed stability of the whole reaction flywheel in the bearing and rotating process and reducing the requirements on a control circuit and algorithm complexity.
Drawings
FIG. 1 is a cross-sectional view of a reaction flywheel of the present invention.
FIG. 2 is an overall three-dimensional cross-sectional view of the reaction flywheel of the present invention (shown with the connectors such as bolts, and plate springs, vacuum nozzles, cable connectors, vacuum seals, and electromagnetic clutch coils omitted).
FIG. 3 is a schematic diagram of the structure of the electromagnetic clutch engaging disk in the reaction flywheel of the present invention.
In the figure, 1-motor stator, 2-cable connector, 3-round induction synchronizer rotor, 4-star interface flange, 5-vacuum seal ring, 6-motor rotor, 7-round induction synchronizer rotor, 8-attitude stabilization flywheel bearing, 9-attitude stabilization flywheel bearing inner shaft sleeve, 10-attitude stabilization flywheel body, 11-electromagnetic clutch actuation disc, 12-plate spring, 13-attitude stabilization flywheel bearing outer shaft sleeve, 14-electromagnetic clutch coil, 15-motorized flywheel bearing, 16-attitude motorized additional flywheel body, 17-motorized flywheel bearing outer shaft sleeve, 18-vacuum pumping nozzle, 19-vacuum seal shell and 20-vacuum seal ring.
Detailed Description
To further clarify the objects, advantages and features of the present invention, a more particular description of the invention will be rendered by reference to the appended drawings. It is to be noted that the drawings are in a very simplified form and are not to precise scale, which is merely for the purpose of facilitating and distinctly claiming the embodiments of the present invention; secondly, the structures shown in the drawings are often the main components of the actual structures.
As shown in fig. 1, the variable inertia reaction flywheel of the present invention includes: the device comprises a motor stator 1, a cable connector 2, a round induction synchronizer rotor 3, a whole star interface flange 4, a vacuum sealing ring 5, a motor rotor 6, a round induction synchronizer rotor 7, a posture stabilizing flywheel bearing 8, a posture stabilizing flywheel bearing inner shaft sleeve 9, a posture stabilizing flywheel body 10, an electromagnetic clutch suction disc 11, a plate spring 12, a posture stabilizing flywheel bearing outer shaft sleeve 13, an electromagnetic clutch coil 14, a motorized flywheel bearing 15, a posture motorized additional flywheel body 16, a motorized flywheel bearing outer shaft sleeve 17, a vacuum pumping nozzle 18, a vacuum sealing shell 19 and a vacuum sealing ring 20.
The motor stator 1 comprises a hollow long shaft, and the bottom of the hollow long shaft extends outwards to form a base; the bottom of the hollow long shaft of the motor stator 1 is fixedly provided with a cable connector 2 for power supply and signal transmission;
a round induction synchronizer rotor and stator 3 is fixedly arranged at the top of the hollow shaft of the motor stator 1; the motor stator 1 and the whole star interface flange 4 are fixedly connected through screws and sealed by a vacuum sealing ring 5; after the reaction flywheel is debugged, the motor stator 1 and the whole satellite interface flange 4 are welded to realize sealing;
the motor rotor 6 is a hollow long shaft, a motor magnetic pole is installed inside the motor rotor 6, a round induction synchronizer rotor 7 is installed inside the hollow shaft of the motor rotor 6, and a gap is reserved between the installed round induction synchronizer rotor 7 and the motor stator 1 and between the installed motor rotor 6 and the motor stator 1;
the posture stabilizing flywheel bearing 8 is sleeved outside the motor rotor 6, and the motor rotor 6 and the inner ring of the posture stabilizing flywheel bearing 8 are connected in an interference fit manner to realize rotation together; the outer ring of the attitude stabilizing flywheel bearing 8 is installed in the whole star interface flange 4 in a transition fit mode, and the outer ring of the attitude stabilizing flywheel bearing 8 does not rotate;
the bottom of an inner shaft sleeve 9 of the posture stabilizing flywheel bearing is fixedly connected with the motor rotor 6 and rotates along with the motor rotor 6; the bottom of the inner shaft sleeve 9 of the posture stabilizing flywheel bearing simultaneously compresses the inner ring of the posture stabilizing flywheel bearing 8, and the bearing pre-tightening force of the posture stabilizing flywheel bearing 8 is adjusted by adjusting the size of the inner shaft sleeve 9 of the posture stabilizing flywheel bearing; the upper part of an inner shaft sleeve 9 of the attitude stabilizing flywheel bearing is fixedly connected with an attitude stabilizing flywheel body 10, so that the attitude stabilizing flywheel body 10 is ensured to rotate along with the motor rotor 6;
the spline of the electromagnetic clutch actuation disc 11 is matched with the spline groove of the inner shaft sleeve 9 of the posture stabilizing flywheel bearing, and can freely and smoothly slide;
the posture stabilizing flywheel bearing inner shaft sleeve 9 is fixedly connected with a plate-shaped spring 12; the electromagnetic clutch suction disc 11 is fixedly connected with the plate-shaped spring 12;
an electromagnetic clutch coil 14 is fixedly arranged on the posture stabilizing flywheel bearing outer shaft sleeve 13; the posture stabilizing flywheel bearing outer shaft sleeve 13 is fixedly connected with the whole star interface flange 4 through a screw;
the posture stabilizing flywheel bearing outer shaft sleeve 13 is of a hollow shaft-shaped structure, and the inner side wall and the outer side wall of the posture stabilizing flywheel bearing outer shaft sleeve are step surfaces; the inner side of the bottom of the outer shaft sleeve 13 of the posture stabilizing flywheel bearing presses the outer ring of the posture stabilizing flywheel bearing 8, the outer side of the bottom of the outer shaft sleeve 13 of the posture stabilizing flywheel bearing presses the inner ring of the motorized flywheel bearing 15, and the outer shaft sleeve 13 of the posture stabilizing flywheel bearing and the electromagnetic clutch coil 14 do not move in the whole working process;
the attitude maneuver additional flywheel body 16 is in transition fit with and fixed connection with the outer ring of the maneuver flywheel bearing 15 to realize the movement together;
the lower part of the outer shaft sleeve 17 of the motorized flywheel bearing is fixedly connected with the upper part of the attitude motorized additional flywheel body 16; the bottom of the external shaft sleeve 17 of the motorized flywheel bearing is tightly pressed on the external ring of the motorized flywheel bearing 15, and the bearing pretightening force of the motorized flywheel bearing 15 is adjusted by finishing the size of the external shaft sleeve 17 of the motorized flywheel bearing;
when the electromagnetic clutch coil 14 is electrified to execute the attracting and command, the electromagnetic clutch attracting disc 11 overcomes the pulling force of the plate-shaped spring 12 and slides downwards along the spline groove of the inner shaft sleeve 9 of the attitude stabilizing flywheel bearing, so that the disc gear at the bottom of the electromagnetic clutch attracting disc 11 is meshed with the disc gear at the top of the outer shaft sleeve 17 of the motorized flywheel bearing, and the attitude motorized additional flywheel body 16 and the attitude stabilizing flywheel body 10 rotate together with the motor rotor 6;
the vacuum pumping nozzle 18 is designed by opening a hole on the whole satellite interface flange 4, is used for vacuumizing the interior of a reaction flywheel and is finally arranged on a satellite and welded and sealed before launching;
the vacuum sealing shell 19 is fixedly connected with the whole star interface flange 4 through a vacuum sealing ring 20, and is welded and sealed after the debugging of the reaction flywheel is finished.
During design, a large gap is reserved between the posture-stabilizing flywheel bearing outer shaft sleeve 13 and the motorized flywheel bearing outer shaft sleeve 17; a large gap is left between the whole satellite interface flange 4 and the attitude maneuver additional flywheel body 16; a larger gap is left between the inner shaft sleeve 9 of the posture stabilizing flywheel bearing and the outer shaft sleeve 13 of the posture stabilizing flywheel bearing; a large gap is left between the attitude stabilizing flywheel body 10 and the attitude maneuver additional flywheel body 16; a large gap is reserved between the whole star interface flange 4 and the motor rotor 6.
The working process of the invention is as follows:
1. when the reaction flywheel works in the attitude stabilizing mode, the coil 14 of the electromagnetic clutch is not electrified, the attraction disc 11 of the electromagnetic clutch slides upwards to the highest position along the spline groove of the inner shaft sleeve 9 of the attitude stabilizing flywheel bearing under the tension of the plate-shaped spring 12, the separation of the disc gear at the bottom of the attraction disc 11 of the electromagnetic clutch and the disc gear at the top of the outer shaft sleeve 17 of the motorized flywheel bearing is realized, and thus only the attitude stabilizing flywheel body 10 rotates along with the motor rotor 6. At the moment, the rotary inertia of the reaction flywheel driven by the motor is only the rotary inertia of the components of the attitude stabilizing flywheel body 10, the attitude stabilizing flywheel bearing inner shaft sleeve 9, the inner ring of the attitude stabilizing flywheel bearing 8, the motor rotor 6 and the like around the central axis, so that small inertia and high rotating speed can be realized.
2. When the reaction flywheel works in the attitude maneuver mode, after the coil 14 of the electromagnetic clutch is electrified to execute an actuation instruction, the actuation disc 11 of the electromagnetic clutch overcomes the pulling force of the plate spring 12 and slides downwards along the spline groove of the inner shaft sleeve 9 of the attitude stabilizing flywheel bearing, the meshing of the disc gear at the bottom of the actuation disc 11 of the electromagnetic clutch and the disc gear at the top of the outer shaft sleeve 17 of the attitude stabilizing flywheel bearing is realized, and the attitude maneuver additional flywheel body 16 and the attitude stabilizing flywheel body 10 rotate together with the motor rotor 6. At the moment, the rotational inertia of the reaction flywheel driven by the motor mainly comprises rotational inertia around the central axis, such as an attitude stabilizing flywheel body 10, an attitude stabilizing flywheel bearing inner shaft sleeve 9, an attitude maneuvering additional flywheel body 16, a maneuvering flywheel bearing outer shaft sleeve 17, an inner ring of an attitude stabilizing flywheel bearing 8, an outer ring of a maneuvering flywheel bearing 15, a motor rotor 6 and the like, so that high inertia and low rotating speed can be realized.
Claims (8)
1. A high accuracy electromagnetic clutch type variable inertia reaction flywheel which characterized in that: the device comprises a motor stator (1), a whole star interface flange (4), a vacuum sealing shell (19), a motor rotor (6), an attitude stabilizing flywheel body assembly, an attitude maneuvering additional flywheel body assembly and an electromagnetic clutch assembly;
the motor stator (1) comprises a hollow long shaft, and the bottom of the hollow long shaft extends outwards to form a base; the bottom of the hollow long shaft of the motor stator (1) is fixedly provided with a cable connector (2) for power supply and signal transmission, and the top of the hollow long shaft of the motor stator (1) is fixedly provided with a circular induction synchronizer rotor-stator (3);
the whole star interface flange (4) is fixedly connected with the motor stator (1), and the joint surface is sealed by a vacuum sealing ring (5); the whole star interface flange (4) is also provided with a vacuum pumping nozzle (18);
the vacuum sealing shell (19) is fixedly connected with the whole star interface flange (4) after being buckled, and the joint surface is sealed by a vacuum sealing ring (20);
the vacuum seal shell (19), the whole star interface flange (4) and the motor stator (1) jointly form a mounting cavity of the motor rotor (6), the attitude stable flywheel body assembly and the attitude maneuver additional flywheel body assembly;
the motor rotor (6) is a hollow long shaft, and a motor magnetic pole is arranged in the motor rotor; the motor rotor (6) is sleeved outside the motor stator (1); a circular induction synchronizer rotor (7) is arranged between the motor rotor (6) and the motor stator (1), and a gap is formed between the circular induction synchronizer rotor (7) and the motor stator (1);
the posture stabilizing flywheel body assembly comprises a posture stabilizing flywheel bearing (8), a posture stabilizing flywheel bearing inner shaft sleeve (9), a posture stabilizing flywheel body (10) and a posture stabilizing flywheel bearing outer shaft sleeve (13) which are sequentially arranged from bottom to top;
the attitude maneuver additional flywheel body component comprises an outer shaft sleeve (17) of a maneuvering flywheel bearing, an attitude maneuver additional flywheel body (16) and a maneuvering flywheel bearing (15);
the posture stabilizing flywheel bearing (8) is sleeved outside the motor rotor (6), the inner ring of the posture stabilizing flywheel bearing (8) is in interference fit with the motor rotor (6), and the outer ring of the posture stabilizing flywheel bearing (8) is installed in the whole star interface flange (4) in a transition fit manner;
the bottom of an inner shaft sleeve (9) of the posture stabilizing flywheel bearing is fixedly connected with a motor rotor (6), the bottom of the inner shaft sleeve (9) of the posture stabilizing flywheel bearing simultaneously compresses an inner ring of the posture stabilizing flywheel bearing (8), and the bearing pretightening force of the posture stabilizing flywheel bearing (8) is adjusted by adjusting the size of the inner shaft sleeve (9) of the posture stabilizing flywheel bearing; the upper part of an inner shaft sleeve (9) of the posture stabilizing flywheel bearing is fixedly connected with a posture stabilizing flywheel body (10);
an outer shaft sleeve (13) of the posture stabilizing flywheel bearing is fixedly connected with a whole star interface flange (4); the posture stabilizing flywheel bearing outer shaft sleeve (13) is of a hollow shaft-shaped structure, and the inner side wall and the outer side wall of the posture stabilizing flywheel bearing outer shaft sleeve are step surfaces; the inner side of the bottom of the outer shaft sleeve (13) of the posture stabilizing flywheel bearing compresses the outer ring of the posture stabilizing flywheel bearing (8), and the outer side of the bottom compresses the inner ring of the motorized flywheel bearing (15); an electromagnetic clutch coil (14) is fixedly arranged on the outer side of the outer shaft sleeve (13) of the posture stabilizing flywheel bearing;
the lower part of the outer shaft sleeve (17) of the motorized flywheel bearing is fixedly connected with the upper part of the attitude motorized additional flywheel body (16); the attitude maneuver additional flywheel body (16) is in transition fit and fixed connection with the outer ring of the maneuver flywheel bearing (15); the bottom of the outer shaft sleeve (17) of the motorized flywheel bearing simultaneously presses the outer ring of the motorized flywheel bearing (15), and the bearing pretightening force of the motorized flywheel bearing (15) is adjusted by finishing the size of the outer shaft sleeve (17) of the motorized flywheel bearing; a second disc gear meshed with the first disc gear is arranged at the corresponding position of the top of the outer shaft sleeve (17) of the motorized flywheel bearing;
the electromagnetic clutch assembly is arranged on the outer side wall of the inner shaft sleeve (9) of the posture stabilizing flywheel bearing and used for realizing the combination and separation of the inner shaft sleeve (9) of the posture stabilizing flywheel bearing and the outer shaft sleeve (17) of the motorized flywheel bearing.
2. A high precision electromagnetic clutch type variable inertia reaction flywheel according to claim 1, characterized in that: the electromagnetic clutch assembly comprises an electromagnetic clutch attraction disc (11), a plate-shaped spring (12) for resetting the attraction disc (11), a first disc gear and a second disc gear which are meshed in a matched mode;
an electromagnetic clutch suction disc (11) is arranged on the outer side wall of an inner shaft sleeve (9) of a posture stabilizing flywheel bearing in a sliding manner; one end of a plate-shaped spring (12) is connected with an electromagnetic clutch attracting disc (11), and the other end is connected with an inner shaft sleeve (9) of a posture stabilizing flywheel bearing; the first disc gear is arranged at the bottom of the electromagnetic clutch attraction disc (11), and the first disc gear is arranged at the top of the outer shaft sleeve (17) of the motorized flywheel bearing.
3. A high precision electromagnetic clutch type variable inertia reaction flywheel according to claim 2, characterized in that: the outer side wall of the inner shaft sleeve (9) of the posture stabilizing flywheel bearing is provided with a spline groove, the side wall of the electromagnetic clutch actuation disc (11) is provided with a spline, and the electromagnetic clutch actuation disc (11) can slide up and down the inner shaft sleeve (9) of the posture stabilizing flywheel bearing through the matching of the spline and the spline groove.
4. A high precision electromagnetic clutch type variable inertia reaction flywheel according to any one of claims 1 to 3, characterized in that: a clearance of more than 1mm is reserved between the outer shaft sleeve (13) of the posture stabilizing flywheel bearing and the outer shaft sleeve (17) of the motorized flywheel bearing.
5. A high accuracy electromagnetic clutch type variable inertia reaction flywheel according to claim 4, characterized in that: a gap of more than 1mm is reserved between the whole satellite interface flange (4) and the attitude maneuver additional flywheel body (16).
6. A high accuracy electromagnetic clutch type variable inertia reaction flywheel according to claim 5, characterized in that: and a clearance of more than 1mm is reserved between the inner shaft sleeve (9) of the posture stabilizing flywheel bearing and the outer shaft sleeve (13) of the posture stabilizing flywheel bearing.
7. A high accuracy electromagnetic clutch type variable inertia reaction flywheel according to claim 6, characterized in that: a clearance of more than 1mm is left between the attitude stabilization flywheel body (10) and the attitude maneuver additional flywheel body (16).
8. A high accuracy electromagnetic clutch type variable inertia reaction flywheel as set forth in claim 7, wherein: a gap of more than 1mm is reserved between the whole star interface flange (4) and the motor rotor (6).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911319505.3A CN110949691A (en) | 2019-12-19 | 2019-12-19 | High-precision electromagnetic clutch type variable inertia reaction flywheel |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911319505.3A CN110949691A (en) | 2019-12-19 | 2019-12-19 | High-precision electromagnetic clutch type variable inertia reaction flywheel |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111268178A (en) * | 2020-03-16 | 2020-06-12 | 北京微动航科技术有限公司 | Satellite attitude control flying wheel pair, satellite attitude control system and satellite |
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| CN211810308U (en) * | 2019-12-19 | 2020-10-30 | 中国科学院西安光学精密机械研究所 | High-precision electromagnetic clutch type variable inertia reaction flywheel |
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| CN107182237B (en) * | 2005-09-30 | 2012-08-15 | 上海新跃仪表厂 | Satellite counteraction flyback |
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| CN111268178A (en) * | 2020-03-16 | 2020-06-12 | 北京微动航科技术有限公司 | Satellite attitude control flying wheel pair, satellite attitude control system and satellite |
| CN111268178B (en) * | 2020-03-16 | 2021-10-15 | 北京微动航科技术有限公司 | Satellite attitude control flying wheel pair, satellite attitude control system and satellite |
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