CN105151321A - Follow-up tracking type dynamic and static isolation type double-super satellite platform and manufacturing method thereof - Google Patents
Follow-up tracking type dynamic and static isolation type double-super satellite platform and manufacturing method thereof Download PDFInfo
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Abstract
The invention provides a follow-up tracking type dynamic and static isolation type double-super satellite platform and a manufacturing method thereof. A brand new idea of a platform follow-up tracking effective load is adopted, super-precise and super-stable control is performed on the platform with the effective load being the center, and a follow-up tracking effective load coarse control mode is adopted for the platform. Meanwhile, by means of the dynamic and static isolation method, a satellite is divided into a load cabin and a service cabin; the load cabin guarantees that the effective load reaches expected super-precise and super-stable control through a high-performance magnetic levitation flywheel arranged on the load cabin; the service cabin resists environment interference and performs follow-up tracking on the load cabin through an outer executing mechanism installed on the service cabin; and the two cabins can reach expected opposite poses. The load cabin and the service cabin are connected in a non-contact manner through a levitation device, vibration interference of the service cabin can be effectively isolated, and the vibration isolation effect is not affected by sensor performance. The double-super satellite platform can be applied to spacecrafts, such as high-resolution remote sensing satellites and deep space exploration astronomical telescopes carrying high-resolution sensitive effective loads.
Description
Technical field
The present invention relates to satellite platform field, being specifically related to a kind of for there is the spacecraft of the super steady requirement of superfinishing and isolated satellite platform of servo follow-up tracing type sound designed and preparation method thereof.
Background technology
Large Spacecraft light structures is flexible large, and low frequency modal congestion problem becomes clear day by day, and greatly constrains the bandwidth Design of control system; The periodicity dynamic disturbance that the movable parts such as flywheel, gyro, driver train bring out is then the major cause causing load to vibrate.Along with the raising of spacecraft performance requriements, the gesture stability that the large flexibility of light structures and movable part obstacle of vibration cause and Flutter Suppression problem more and more outstanding, become the main restricting factor of follow-up advanced spacecraft development.
At present, passive and active two kinds of control devices are mainly contained for the shake of satellite flexible appendage and movable part obstacle of vibration.Passive vibration isolation system architecture is simple, reliable and stable, and does not need additionally to provide the energy and measurement mechanism, but low frequency inhibition is poor; Active vibration isolation system has better performance in theory, but control system is complicated, poor stability, and has water bed effect.Meanwhile, based on voice coil motor technology, the contactless unperturbed vibration-isolating platform of development abroad, can solve Platform Vibration interference problem, but bring the complexity of spacecraft attitude control system, practical application difficulty.At present, no matter be traditional active-passive vibration isolation means, still noncontact unperturbed vibration isolating method recently, be all the thought based on platform ACTIVE CONTROL capacity weight, the former vibration isolating effect is limited, the latter's structure, control complicated.In order to avoid loaded down with trivial details numerous all kinds of platform obstacle of vibration problems, method, system solves the super steady problem of satellite platform superfinishing, the invention provides isolated two super satellite platform of a kind of servo follow-up tracing type sound and preparation method thereof.
Summary of the invention
For defect of the prior art, the object of this invention is to provide a kind of satellite platform and preparation method thereof, this satellite platform and preparation method thereof is the brand-new thought based on the platform servo follow-up tracing capacity weight proposed, centered by capacity weight, the super steady control of superfinishing is carried out to it, and platform adopts thick control pattern servo follow-up tracing capacity weight, simultaneously realize sound be isolated into means so that magnetic is floating, realize completely isolated to Platform Vibration and disturbance response of capacity weight, very high precision remote sensing satellite can be applied to, survey of deep space astronomical telescope etc. carries fine resolution responsive capacity weight class spacecraft, to greatly improve spacecraft detection performance.
According to the isolated two super satellite platform of a kind of servo follow-up tracing type sound provided by the invention, comprising: load cabin, service module and levitation device;
Levitation device connects load cabin and service module with noncontact form; Levitation device detects the relative pose information of load cabin and service module and is transferred to service module, and service module is resisted ambient interference according to relative pose information and followed the tracks of load cabin, makes the relative pose reaching expectation between load cabin and service module two cabin;
Levitation device comprises: pin-cellular type guide and limit structure, suspension mechanism, catch gear, upper flange plate, lower flange plate;
Pin-cellular type guide and limit structure comprises: support for the taper guide finger of limit load cabin and service module relative position relation and elastomeric spacing hole, taper guide finger and upper flange plate are connected, spacing hole supports and is connected with lower flange plate, spacing hole supports and adopts elastic damping material, with softly contacting and elastic compression of ensureing that taper guide finger and spacing hole support;
Suspension mechanism comprises: mast, sleeve, position transduser, electromagnetic unit, threshold decision unit, mast, the sleeve of free-running fit are connected with upper flange plate, lower flange plate respectively, position transduser is used for the relative position relation measured in real time between mast and sleeve, prevents from colliding between mast and sleeve;
Threshold decision unit is used for when determining the gap between mast and sleeve and exceeding the scope of regulation, triggers electromagnetic unit and produces electromagnetic repulsion force or gravitation, impel mast and sleeve gap to return in the scope of regulation;
Catch gear is installed and is connected between upper flange plate and lower flange plate, and can be unlocked by explosive bolt;
Levitation device is connected with load cabin, service module respectively by upper flange plate, lower flange plate.
Preferably, load cabin comprises: gyro, star sensor, magnetically levitated flywheel, capacity weight, capacity weight control unit;
The capacity weight directional information that capacity weight control unit provides according to gyro, star sensor produces action command, to drive magnetically levitated flywheel, makes capacity weight reach the sensing of expection;
Service module comprises relative Attitude Control for Spacecraft unit, exterior operator, relative Attitude Control for Spacecraft unit is used for the relative pose information of load cabin and the service module detected according to levitation device, control exterior operator opposing ambient interference and follow the tracks of load cabin, making load cabin and service module reach the relative pose of expectation.
Preferably, the isolated two super satellite platform of described servo follow-up tracing type sound at least have following any one or appoint multiple-working mode:
-emission mode;
The super steady pattern of-superfinishing;
-anti-collision pattern;
-maneuver model;
Described emission mode, refer to that the catch gear of levitation device is in the lock state, load cabin and service module are structure as a whole, and implement orbit maneuver and pose adjustment by service module exterior operator, suspension mechanism is in off-position;
The super steady pattern of described superfinishing, refers to that the catch gear of levitation device is unlocked by explosive bolt, and load cabin and service module are two body structures that are connected of suspending, and suspension mechanism is in off-position, and gap between its mast and sleeve within the limits prescribed; Now, load cabin realizes the sensing of capacity weight by magnetically levitated flywheel, and service module is resisted ambient interference by exterior operator and followed the tracks of load cabin, makes two cabins reach the relative pose of expectation, and relative pose change can not produce electromagnetic force, service module vibration and interference can not transfer to load cabin;
Described anti-collision pattern, refer to when the threshold decision unit judges gap gone out between the mast of suspension mechanism and sleeve exceeds the scope that defined threshold judging unit allows, electromagnetic unit is energized to produce electromagnetic repulsion force or gravitation automatically, prevent mast and sleeve from bumping against, electromagnetic unit and and serve portion's actuating unit combined action out of my cabin, impel mast and sleeve gap to return in the scope of regulation; In addition, if suspension mechanism self electromagnetism power and serve portion's actuating unit combined action out of my cabin when still can not stop the collision trend of mast and sleeve, the pin-cellular type guide and limit structure of levitation device can leading soft contact, to prevent suspension mechanism, hard damaged in collision occurs;
Described maneuver model, when referring to that satellite needs to implement fast railway or attitude maneuver, electromagnetic unit produces electromagnetic attraction, make mast and sleeve constantly close, until the guide finger of pin-cellular type guide and limit structure enters spacing hole and is in axially soft contact condition, and guide finger compresses elastic spacing hole further and supports, until reach the thrust of regulation, realize the electromagnetic locking of load cabin and service module, satellite becomes integrative-structure from two body structures, so that implement fast railway or attitude maneuver operation.
According to the method for making of the isolated two super satellite platform of a kind of servo follow-up tracing type sound provided by the invention, it comprises step: make levitation device, makes levitation device connect load cabin and service module with noncontact form;
Levitation device detects the relative pose information of load cabin and service module and is transferred to service module, and service module is resisted ambient interference according to relative pose information and followed the tracks of load cabin, makes the relative pose reaching expectation between load cabin and service module two cabin;
Levitation device comprises: pin-cellular type guide and limit structure, suspension mechanism, catch gear, upper flange plate, lower flange plate;
Pin-cellular type guide and limit structure comprises: support for the taper guide finger of limit load cabin and service module relative position relation and elastomeric spacing hole, taper guide finger and upper flange plate are connected, spacing hole supports and is connected with lower flange plate, spacing hole supports and adopts elastic damping material, with softly contacting and elastic compression of ensureing that taper guide finger and spacing hole support;
Suspension mechanism comprises: mast, sleeve, position transduser, electromagnetic unit, threshold decision unit, mast, the sleeve of free-running fit are connected with upper flange plate, lower flange plate respectively, position transduser is used for the relative position relation measured in real time between mast and sleeve, prevents from colliding between mast and sleeve;
Threshold decision unit is used for when determining the gap between mast and sleeve and exceeding the scope of regulation, triggers electromagnetic unit and produces electromagnetic repulsion force or gravitation, impel mast and sleeve gap to return in the scope of regulation;
Catch gear is installed and is connected between upper flange plate and lower flange plate, and can be unlocked by explosive bolt;
Levitation device is connected with load cabin, service module respectively by upper flange plate, lower flange plate.
Preferably, load cabin comprises: gyro, star sensor, magnetically levitated flywheel, capacity weight, capacity weight control unit;
The capacity weight directional information that capacity weight control unit provides according to gyro, star sensor produces action command, to drive magnetically levitated flywheel, makes capacity weight reach the sensing of expection;
Service module comprises relative Attitude Control for Spacecraft unit, exterior operator, relative Attitude Control for Spacecraft unit is used for the relative pose information of load cabin and the service module detected according to levitation device, control exterior operator opposing ambient interference and follow the tracks of load cabin, making load cabin and service module reach the relative pose of expectation.
Compared with prior art, the present invention has following beneficial effect:
1) this satellite platform adopts the brand-new thought of platform servo follow-up tracing capacity weight, centered by capacity weight, carries out the super steady control of superfinishing to it, and platform adopts the thick control pattern of servo follow-up tracing capacity weight;
2) this satellite platform is isolated into means with sound, satellite is divided into load cabin and service module two parts, the configuration of load cabin capacity weight, star sensor and magnetically levitated flywheel etc., the super steady task of absorbed superfinishing; Service module is provided with the moving obstacle such as solar array, storage tank parts, in order to provide infrastructure service, is connected between two cabins by levitation device with noncontact form, and its vibration and interference can not transfer to load cabin, reach in moving and get quiet object;
3) service module is by exterior operator, opposing ambient interference servo follow-up tracing load cabin, makes two cabins reach the relative pose of expectation, simultaneously by the connection constraints of levitation device, realize two cabins divide and not from effect;
4) load cabin is noiseless, and kinetic model is simple, and control bandwidth does not retrain by flexible appendages such as windsurfings, and controller performance can obtain larger performance.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is the isolated two super satellite platform composition schematic diagram of servo follow-up tracing type sound.
Fig. 2 is levitation device composition schematic diagram.
Fig. 3 is servo follow-up tracing type sound isolated satellite platform gesture stability block diagram.
In figure:
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, some distortion and improvement can also be made.These all belong to protection scope of the present invention.
The invention provides isolated two super satellite platform of a kind of servo follow-up tracing type sound and preparation method thereof, adopt and carry out the super steady control of superfinishing centered by load, the brand-new thought of platform servo follow-up tracing capacity weight.Simultaneously, means are isolated into sound, the levitation device noncontact with vibration isolation function is adopted to connect load cabin and service module, the obstacle of vibration of service module can be down to zero hertz, and vibration isolating effect is not by payload sensor and two cabin relative position sensor performance impacts, can be applied to the responsive capacity weight class spacecraft with the super steady requirement of superfinishing.
As shown in Figure 1 and Figure 2, the isolated two super satellite platform of a kind of servo follow-up tracing type sound provided by the invention is made up of load cabin 1, service module 2 and levitation device 3.
Load cabin 1 includes but not limited to that capacity weight 14, magnetically levitated flywheel 13, capacity weight control unit 15 and payload sensor are as relative quiet parts such as star sensor 12, gyros 11.Service module 2 is made up of general satellite modules, includes but not limited to that driver train 23 and exterior operator are as various movable parts such as thruster 21, momentum wheels 22, solar cell array 24 flexible appendage such as grade and relative Attitude Control for Spacecraft unit 25.
Levitation device 3 mainly comprises suspension mechanism 32, catch gear 33, pin-cellular type guide and limit structure 31, upper flange plate 34 and lower flange plate 35 etc.; Wherein suspension mechanism 32 main body is made up of mast 321 and sleeve 322, and pin-cellular type guide and limit structure 31 supports 312 compositions primarily of taper guide finger 311 and elastic spacing hole.
The capacity weight 14 that load cabin 1 realizes expecting by the high-performance magnetism suspending flywheel 13 self configured points to; Service module 2 resists ambient interference and servo follow-up tracing load cabin 1 by exterior operator mounted thereto, makes two cabins reach the relative pose of expectation; Levitation device 3 connects load cabin 1 and service module 2 with noncontact form, and the relative pose that service module 1 is implemented adjustment can not be pointed to capacity weight 14 and produce interference.
Capacity weight 14 points to and is achieved in that and provides capacity weight 14 to point to according to sensors such as star sensor 12, gyros 11, based on this directional information, effective posture control unit 15 produces action command, drives magnetically levitated flywheel 13, makes capacity weight 14 reach the sensing of expection.
Service module 2 connects load cabin 1 by levitation device 3 with noncontact form, levitation device 3 detects the relative pose information of load cabin 1 and service module 2 and is transferred to relative Attitude Control for Spacecraft unit 25, the latter produces control command, drive service module 2 exterior operator, opposing ambient interference also follows the tracks of load cabin 1, makes two cabins reach the relative pose of expectation.
Levitation device 3 is between load cabin 1 and service module 2, be made up of by necessarily regularly arranged one or more groups suspension mechanism 32, often organize suspension mechanism 32 main body to be made up of the mast 321 of free-running fit and sleeve 322, mast 321 and sleeve 322 are connected with upper flange plate 34 and lower flange plate 35 respectively.Levitation device 3 is also connected with load cabin 1 and service module 2 respectively by upper flange plate 34 and lower flange plate 35.
Suspension mechanism 32 utilizes but is not limited to electromagnetic force or electrostatic force mode, regulates the gap between mast 321 and sleeve 322 by control curent change, prevents both collisions.
Suspension mechanism 32, except the mast 321 cooperatively interacted and sleeve 322, is also integrated with position transduser 323, measures the relative position relation between mast 321 and sleeve 322 in real time.
Be provided with many group catch gears 33 between the upper flange plate 34 of levitation device 3 and lower flange plate 35, for resisting severe transmitter section mechanical environment, it can be unlocked by explosive bolt in-orbit.
Several pin to mechanical engagement-cellular type guide and limit structure 31 is also installed, for the relative position relation of limit load cabin 1 and service module 2 between the upper flange plate 34 of levitation device 3 and lower flange plate 35.
Pin-cellular type guide and limit structure 31 mainly comprises taper guide finger 311 and spacing hole supports 312 two parts, taper guide finger 311 and upper flange plate 34 are connected, spacing hole supports 312 and is connected with lower flange plate 35, spacing hole supports 312 and adopts elastic damping material, ensures that taper guide finger 311 and the soft of spacing hole's support 312 contact and elastic compression.
In the isolated two super satellite platform of this servo follow-up tracing type sound, the energy between the load cabin 1 that noncontact connects and service module 2 and information transmission realize through but not limited to radio transmitting methods such as undesirable mutual electromagnetic inductance device 41 and photoelectric conversion devices 42.
As shown in Figure 3, the isolated satellite platform attitude control system of a kind of servo follow-up tracing type sound mainly includes effect load gesture stability loop 100 and two cabin relative pose control loops 200; Wherein capacity weight gesture stability loop 100 comprises the modules such as capacity weight instruction output unit 101, capacity weight control unit 15, load posture control unit 103, magnetically levitated flywheel 13, load cabin 1 and star sensor-gyro 106; Two relative Attitude Control for Spacecraft loop, cabins 200 comprise the modules such as relative attitude operating order 201, relative Attitude Control for Spacecraft unit 25, relative Attitude Control for Spacecraft algorithm performance element 203, exterior operator 204, service module 2 and relative position sensor 206.
The satellite of the isolated two super platform of this servo follow-up tracing type sound is adopted at least to have super steady, the anti-collision of transmitting, superfinishing, the multiple different mode of operation such as motor-driven.
Emission mode refers to that levitation device 3 is in catch gear 33 lock-out state, load cabin 1 and service module 2 are structure as a whole, comprise the whole process from satellite launch to orbit determination, satellite implements orbit maneuver and pose adjustment by service module 1 exterior operator, and now suspension mechanism 32 is in off-position.
The super steady pattern of superfinishing refers to that the catch gear 33 of levitation device 3 is unlocked by explosive bolt, load cabin 1 and service module 2 are two body structures be connected that suspend, suspension mechanism 32 is in off-position, and the gap between its mast 321 and sleeve 322 is in threshold decision unit 400 allowed bands of regulation.Now, load cabin 1 realizes capacity weight 14 by magnetically levitated flywheel 13 and points to, service module 2 is resisted ambient interference by exterior operator and is followed the tracks of load cabin, two cabins are made to reach the relative pose of expectation, and relative pose change can not produce electromagnetic force, service module 2 vibrates and disturbs and can not transfer to load cabin 1.
When the gap that anti-collision pattern refers between the mast 321 and sleeve 322 of suspension mechanism 32 exceeds the scope that defined threshold judging unit 400 allows, it is energized automatically, electromagnetic repulsion force or gravitation is produced by levitation device 3, prevent mast 321 and sleeve 322 from bumping against, and and the combined action of service module 2 exterior operator, in the scope that the threshold decision unit 400 impelling mast 321 and sleeve 322 gap to return to regulation allows.In addition, if when suspension mechanism 32 self electromagnetism power and the combined action of service module 2 exterior operator still can not stop the collision trend of mast 321 and sleeve 322, pin-leading soft the contact of hole elastic damping position limiting structure 31 meeting of levitation device 3, can prevent suspension mechanism 32 from hard damaged in collision occurring.
When maneuver model refers to that satellite needs to implement fast railway or attitude maneuver, suspension mechanism 32 regulates direction of current, electromagnetic attraction is produced by electromagnetic attraction unit 300, make mast 321 and sleeve 322 constantly close, until the guide finger 311 of pin-cellular type guide and limit structure 31 enters spacing hole 312 and is in axially soft contact condition.Now, increase the intensity of current of suspension mechanism 32, electromagnetic attraction increases thereupon, guide finger 311 compresses elastic spacing hole further and supports 312, until reach the thrust of regulation, realize the electromagnetic locking of load cabin 1 and service module 2, satellite becomes integrative-structure from two body structures, is convenient to implement fast railway or attitude maneuver operation.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (5)
1. the isolated two super satellite platform of servo follow-up tracing type sound, is characterized in that, comprising: load cabin (1), service module (2) and levitation device (3);
Levitation device (3) connects load cabin (1) and service module (2) with noncontact form; Levitation device (3) detects the relative pose information of load cabin (1) and service module (2) and is transferred to service module (2), service module (2) is resisted ambient interference according to relative pose information and is followed the tracks of load cabin (1), makes the relative pose reaching expectation between load cabin (1) and service module (2) two cabin;
Levitation device (3) comprising: pin-cellular type guide and limit structure (31), suspension mechanism (32), catch gear (33), upper flange plate (34), lower flange plate (35);
Pin-cellular type guide and limit structure (31) comprising: support (312) for the taper guide finger (311) of limit load cabin (1) and service module (2) relative position relation and elastomeric spacing hole, taper guide finger (311) and upper flange plate (34) are connected, spacing hole supports (312) and is connected with lower flange plate (35), spacing hole supports (312) and adopts elastic damping material, to ensure that taper guide finger (311) and spacing hole support the soft of (312) and contact and elastic compression;
Suspension mechanism (32) comprising: mast (321), sleeve (322), position transduser (323), electromagnetic unit, threshold decision unit (400), mast (321), the sleeve (322) of free-running fit are connected with upper flange plate (34), lower flange plate (35) respectively, position transduser (323), for measuring the relative position relation between mast (321) and sleeve (322) in real time, prevents from colliding between mast (321) and sleeve (322);
Threshold decision unit (400) is for when determining the gap between mast (321) and sleeve (322) and exceeding the scope of regulation, trigger electromagnetic unit and produce electromagnetic repulsion force or gravitation, impel mast (321) and sleeve (322) gap to return in the scope of regulation;
Catch gear (33) is installed and is connected between upper flange plate (34) and lower flange plate (35), and can be unlocked by explosive bolt;
Levitation device (3) is connected with load cabin (1), service module (2) respectively by upper flange plate (34), lower flange plate (35).
2. the isolated two super satellite platform of servo follow-up tracing type sound according to claim 1, it is characterized in that, load cabin (1) comprising: gyro (11), star sensor (12), magnetically levitated flywheel (13), capacity weight (14), capacity weight control unit (15);
The capacity weight directional information that capacity weight control unit (15) provides according to gyro (11), star sensor (12) produces action command, to drive magnetically levitated flywheel (13), capacity weight (14) is made to reach the sensing of expection;
Service module (2) comprises relative Attitude Control for Spacecraft unit (25), exterior operator, relative Attitude Control for Spacecraft unit (25) is for the load cabin (1) that detects according to levitation device (3) the relative pose information with service module (2), control exterior operator opposing ambient interference and follow the tracks of load cabin (1), making load cabin (1) and service module (2) reach the relative pose of expectation.
3. the isolated two super satellite platform of servo follow-up tracing type sound according to claim 2, is characterized in that, the isolated two super satellite platform of described servo follow-up tracing type sound at least have following any one or appoint multiple-working mode:
-emission mode;
The super steady pattern of-superfinishing;
-anti-collision pattern;
-maneuver model;
Described emission mode, refer to that the catch gear (33) of levitation device (3) is in the lock state, load cabin (1) and service module (2) are structure as a whole, implement orbit maneuver and pose adjustment by service module (1) exterior operator, suspension mechanism (32) is in off-position;
The super steady pattern of described superfinishing, refer to that the catch gear (33) of levitation device (3) is unlocked by explosive bolt, load cabin (1) and service module (2) are two body structures be connected that suspend, suspension mechanism (32) is in off-position, and gap between its mast (321) and sleeve (322) within the limits prescribed; Now, load cabin (1) realizes the sensing of capacity weight (14) by magnetically levitated flywheel (13), service module (2) is resisted ambient interference by exterior operator and is followed the tracks of load cabin, two cabins are made to reach the relative pose of expectation, and relative pose change can not produce electromagnetic force, service module (2) vibration and interference can not transfer to load cabin (1);
Described anti-collision pattern, when referring to that the gap judging between the mast (321) of suspension mechanism (32) and sleeve (322) when threshold decision unit (400) exceeds the scope that defined threshold judging unit (400) allows, electromagnetic unit is energized to produce electromagnetic repulsion force or gravitation automatically, prevent mast (321) and sleeve (322) from bumping against, electromagnetic unit and and service module (2) exterior operator combined action, impel mast (321) and sleeve (322) gap to return in the scope of regulation; In addition, if when suspension mechanism (32) self electromagnetism power and service module (2) exterior operator combined action still can not stop the collision trend of mast (321) and sleeve (322),, there is hard damaged in collision to prevent suspension mechanism (32) in the pin-leading soft contact of cellular type guide and limit structure (31) meeting of levitation device (3);
Described maneuver model, when referring to that satellite needs to implement fast railway or attitude maneuver, electromagnetic unit produces electromagnetic attraction, make mast (321) and sleeve (322) constantly close, until the guide finger (311) of pin-cellular type guide and limit structure (31) enters spacing hole (312) and is in axially soft contact condition, and guide finger (311) compresses elastic spacing hole further and supports (312), until reach the thrust of regulation, realize the electromagnetic locking of load cabin (1) and service module (2), satellite becomes integrative-structure from two body structures, so that implement fast railway or attitude maneuver operation.
4. the method for making of the isolated two super satellite platform of servo follow-up tracing type sound, it is characterized in that, make levitation device (3), make levitation device (3) connect load cabin (1) and service module (2) with noncontact form;
Levitation device (3) detects the relative pose information of load cabin (1) and service module (2) and is transferred to service module (2), service module (2) is resisted ambient interference according to relative pose information and is followed the tracks of load cabin (1), makes the relative pose reaching expectation between load cabin (1) and service module (2) two cabin;
Levitation device (3) comprising: pin-cellular type guide and limit structure (31), suspension mechanism (32), catch gear (33), upper flange plate (34), lower flange plate (35);
Pin-cellular type guide and limit structure (31) comprising: support (312) for the taper guide finger (311) of limit load cabin (1) and service module (2) relative position relation and elastomeric spacing hole, taper guide finger (311) and upper flange plate (34) are connected, spacing hole supports (312) and is connected with lower flange plate (35), spacing hole supports (312) and adopts elastic damping material, to ensure that taper guide finger (311) and spacing hole support the soft of (312) and contact and elastic compression;
Suspension mechanism (32) comprising: mast (321), sleeve (322), position transduser (323), electromagnetic unit, threshold decision unit (400), mast (321), the sleeve (322) of free-running fit are connected with upper flange plate (34), lower flange plate (3) 5 respectively, position transduser (323), for measuring the relative position relation between mast (321) and sleeve (322) in real time, prevents from colliding between mast (321) and sleeve (322);
Threshold decision unit (400) is for when determining the gap between mast (321) and sleeve (322) and exceeding the scope of regulation, trigger electromagnetic unit and produce electromagnetic repulsion force or gravitation, impel mast (321) and sleeve (322) gap to return in the scope of regulation;
Catch gear (33) is installed and is connected between upper flange plate (34) and lower flange plate (35), and can be unlocked by explosive bolt;
Levitation device (3) is connected with load cabin (1), service module (2) respectively by upper flange plate (34), lower flange plate (35).
5. the method for making of the isolated two super satellite platform of servo follow-up tracing type sound according to claim 4, it is characterized in that, load cabin (1) comprising: gyro (11), star sensor (12), magnetically levitated flywheel (13), capacity weight (14), capacity weight control unit (15);
The capacity weight directional information that capacity weight control unit (15) provides according to gyro (11), star sensor (12) produces action command, to drive magnetically levitated flywheel (13), capacity weight (14) is made to reach the sensing of expection;
Service module (2) comprises relative Attitude Control for Spacecraft unit (25), exterior operator, relative Attitude Control for Spacecraft unit (25) is for the load cabin (1) that detects according to levitation device (3) the relative pose information with service module (2), control exterior operator opposing ambient interference and follow the tracks of load cabin (1), making load cabin (1) and service module (2) reach the relative pose of expectation.
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| CN106249749A (en) * | 2016-09-08 | 2016-12-21 | 上海卫星工程研究所 | The double super satellite platform Moving Variable inertia attitude control system of principal and subordinate's noncontact |
| CN106314827A (en) * | 2016-09-08 | 2017-01-11 | 上海卫星工程研究所 | Master-slave non-contact ultra-precise ultra-stable satellite platform inter-cabin energy transmission system |
| CN106742070A (en) * | 2016-11-30 | 2017-05-31 | 上海卫星工程研究所 | Possesses the satellite platform of dynamic middle imaging capability |
| CN107298185A (en) * | 2017-05-18 | 2017-10-27 | 上海卫星工程研究所 | The magnetic buoyancy device of high accuracy big bandwidth long-life big moving range |
| CN107804482A (en) * | 2017-09-25 | 2018-03-16 | 上海卫星工程研究所 | Non-contact double super satellite platform and its optimal decoupling control methods of principal and subordinate |
| CN108945524A (en) * | 2018-06-15 | 2018-12-07 | 上海卫星工程研究所 | A kind of spacecraft magnetic buoyancy device |
| CN110861788A (en) * | 2019-11-06 | 2020-03-06 | 上海卫星工程研究所 | High-precision high-stability ground remote sensing micro satellite platform based on magnetic levitation control |
| CN111193112A (en) * | 2020-02-17 | 2020-05-22 | 中国科学院国家天文台 | In-orbit satellite interference pre-evaluation method for radio telescope |
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