CN116079336A - Separated satellite and high-precision measurement and assembly method thereof - Google Patents

Separated satellite and high-precision measurement and assembly method thereof Download PDF

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Publication number
CN116079336A
CN116079336A CN202310073730.3A CN202310073730A CN116079336A CN 116079336 A CN116079336 A CN 116079336A CN 202310073730 A CN202310073730 A CN 202310073730A CN 116079336 A CN116079336 A CN 116079336A
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CN
China
Prior art keywords
cabin
satellite
assembly
plate
separated
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Pending
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CN202310073730.3A
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Chinese (zh)
Inventor
李彦之
张伟
陈建新
孟令杰
陈昌亚
王伟
陆希
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Shanghai Institute of Satellite Engineering
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Shanghai Institute of Satellite Engineering
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Application filed by Shanghai Institute of Satellite Engineering filed Critical Shanghai Institute of Satellite Engineering
Priority to CN202310073730.3A priority Critical patent/CN116079336A/en
Publication of CN116079336A publication Critical patent/CN116079336A/en
Pending legal-status Critical Current

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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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P11/00—Connecting or disconnecting metal parts or objects by metal-working techniques not otherwise provided for 
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
    • B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
    • B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Automatic Assembly (AREA)

Abstract

The invention provides a separated satellite and a separated satellite high-precision measurement and assembly method, which comprises the following steps: step S1: the coil part of the magnetic suspension actuator, electromagnetic chuck ends of the two-cabin connection release device, the reflecting surface of the displacement sensor and the bottoms of the two-cabin unlocking device are arranged on a platform cabin top plate; step S2: the magnetic steel part of the magnetic suspension actuator, the adsorption ends of the two cabin connection release devices, the displacement sensor probes and the tops of the two cabin unlocking devices are arranged on a load cabin suspension plate; step S3: the load cabin suspension plate and the platform cabin top plate are connected through the cabin height positioning tool, so that the distance between the load cabin suspension plate and the platform cabin top plate meets the preset requirement; step S4: and (5) dismantling the cabin height positioning tool, and finishing cabin assembly. The invention can realize the high-precision installation of a separate satellite single machine and the assembly requirements of different distances.

Description

Separated satellite and high-precision measurement and assembly method thereof
Technical Field
The invention relates to the technical field of separate satellite single machine assembly, in particular to a separate satellite and a separate satellite high-precision measurement and assembly method.
Background
The double super satellite is based on the design of 'dynamic and static isolation type ultra-high pointing precision and ultra-high stability', and consists of a platform cabin and a load cabin. The structural plate at the top of the platform cabin is a platform cabin top plate, the structural plate of the load cabin is a load cabin suspension plate, and a cabin space is formed between the platform cabin top plate and the load cabin suspension plate. The device comprises a load cabin, a platform cabin, a displacement sensor, a magnetic suspension actuator, a load cabin and a control system.
The patent document CN104290922A (application number: 201410464958.6) proposes a multifunctional bearing structure for satellites and an assembly method thereof, which realize the multiple purposes of the satellite structure, and the functions of the structure are not mutually affected, and the multifunctional bearing structure has high functional density, light weight, small volume and large bearing capacity. The invention differs from this patent in that there is a high degree of measurement and assembly accuracy.
Patent document CN104443431a (application No. 201410572299.8) provides a triangular satellite configuration, system and assembly method, employing an integrated design concept, embedding the payload and reservoir inside the body configuration of the satellite integrated configuration and providing a corresponding system and assembly method. The present invention differs from this patent in the different deck configurations.
Patent document CN202225188U (application number 201120346293.0) proposes a five-degree-of-freedom adjustment platform for satellite deck assembly, comprising a tilting mechanism, a middle sliding platform, a lower sliding platform, a guide rail, a slider and ball screw assembly, a slewing mechanism, a chassis, a lifting mechanism and casters. The present invention differs from this patent in the different assembly and measurement steps.
Patent document CN103793578A (application No. 201410066657.8) proposes a top-down assembly design method for a meteorological satellite. The present invention differs from this patent in the different deck configurations.
Patent document CN102642191a (application No. 201110425676.1) proposes a device for satellite assembly, which facilitates the quick installation of a single inverted crane and ensures the safety of the assembly. The invention differs from this patent in that there is a high degree of measurement and assembly accuracy.
Based on the two-cabin unlocking device, the two-cabin connecting and releasing device, the displacement sensor, the magnetic suspension actuator and other matched single machines, the following requirements are met in the assembly process:
1) The accuracy of the single machine installation surface is higher than that of other conventional single machines of satellites;
2) Different assembly intervals exist between the cabins;
3) Different single machine spacing requirements are different in the same assembly state;
4) Different auxiliary fixtures are required for assembly.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a separated satellite and a separated satellite high-precision measurement and assembly method.
The invention provides a separated satellite high-precision measurement and assembly method, which comprises the following steps:
step S1: the coil part of the magnetic suspension actuator, electromagnetic chuck ends of the two-cabin connection release device, the reflecting surface of the displacement sensor and the bottoms of the two-cabin unlocking device are arranged on a platform cabin top plate;
step S2: the magnetic steel part of the magnetic suspension actuator, the adsorption ends of the two cabin connection release devices, the displacement sensor probes and the tops of the two cabin unlocking devices are arranged on a load cabin suspension plate;
step S3: the load cabin suspension plate and the platform cabin top plate are connected through the cabin height positioning tool, so that the distance between the load cabin suspension plate and the platform cabin top plate meets the preset requirement;
step S4: and (5) dismantling the cabin height positioning tool, and finishing cabin assembly.
Preferably, the interval between the suction surfaces of the two cabin connection release devices after assembly is 3mm based on the cabin height positioning tool, and the magnetic suspension actuator is longitudinally positioned at the position of-1 mm.
Preferably, a scraper blade is reserved at the positions of the magnetic suspension actuator, the two-cabin unlocking device and the two-cabin connecting and releasing device of the planar cabin top plate and the load cabin suspension plate and is used for adjusting the structural installation precision.
Preferably, the mounting holes of the two-cabin unlocking device are matched with the drill templates, and the mounting holes on the load cabin suspension plates are matched with the drill templates, so that the mounting precision of the two-cabin unlocking device is ensured.
Preferably, the number of the magnetic suspension actuators is 8, and a single set of magnetic suspension actuators comprises magnetic steel and coils; a limiting device is arranged between the magnetic steel and the coil, and the magnetic steel and the coil can relatively move within a certain range and can not be completely separated.
Preferably, the magnetic steel and the coil of the magnetic suspension actuator are connected by a tool to limit the relative movement of the magnetic steel and the coil.
Preferably, the number of the two-cabin unlocking devices is 4.
Preferably, the number of the two-cabin connection and release devices is 4, and the single set of two-cabin connection and release devices consists of an electromagnetic chuck and an adsorption end, and the two devices are not connected or limited and can be completely separated.
Preferably, the number of the displacement sensors is 8, the single set of the displacement sensors consists of a sensor probe and a reflecting surface, and the two sensors are not connected or limited and can be completely separated.
The separated satellite device provided by the invention is prepared by adopting the separated satellite high-precision measurement and assembly method.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention meets the high-precision assembly requirement of a single machine, meets the assembly requirements of different intervals of the single machine, and realizes the high-precision connection of two cabins;
2. the method ensures the realization of the on-orbit ultra-high pointing precision and ultra-high stability index of the satellite;
3. the invention can realize the high-precision installation of a separate satellite single machine and the assembly requirements of different distances.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic diagram of the inter-pod connection method of the present invention.
FIG. 2 is a schematic diagram of a magnetic suspension actuator according to the present invention.
Fig. 3 is a schematic structural diagram of a two-cabin unlocking device in the invention.
Fig. 4 is a schematic structural view of a two-cabin connection release device in the present invention.
FIG. 5 is a schematic diagram of a displacement sensor according to the present invention.
Fig. 6 shows an assembly step in the present invention.
Wherein, the A-plane cabin roof; b-a load cabin suspension plate; C1-C8-magnetic suspension actuators; D1-D8-two cabins are connected with a release device; E1-E4-two cabin unlocking devices; F1-F4-cabin height positioning tool; G1-G4-displacement sensors; c01-a magnetic steel part of the magnetic suspension actuator; c02-a coil part of the magnetic suspension actuator; c03-a magnetic suspension actuator tool; d01-two cabins are connected with the adsorption end of the release device; d02-two cabins are connected with the electromagnetic chuck end of the release device; g01-a displacement sensor probe; g02-displacement sensor reflective surface.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.
Example 1
According to the invention, as shown in fig. 1 to 6, a method for measuring and assembling a separated satellite with high precision comprises the following steps:
step 1: the method comprises the steps that scraping blades are reserved at positions of magnetic levitation actuators C1-C8, two cabin unlocking devices E1-E4 and two cabin connection releasing devices D1-D8 on the front surface of a platform cabin top plate A and the back surface of a load cabin suspension plate B;
step 2: the inter-cabin height positioning tools F1-F4 are arranged between two cabins, the height of the tool is ensured to ensure that the suction surface distance of the connection and release devices of the two cabins after assembly is 3mm, and the longitudinal direction of the magnetic suspension actuator is at the position of-1 mm, namely the height difference between the central position of the magnetic steel part C01 and the central position of the coil part C02 is-1 mm;
step 3: installing a load adjusting cabin suspension plate through a cabin height positioning tool, and retesting the cabin spacing;
step 4: the mounting holes of the two cabin unlocking devices are matched with the drill templates, and the mounting holes on the load cabin suspension plates are matched with each other, so that the mounting precision of the two cabin unlocking devices is ensured;
step 5: installing a magnetic suspension actuator (with a tool C03), an electromagnetic chuck end D02 of a two-cabin connection release device and reflecting surfaces G02 of displacement sensors G1-G4 on a platform cabin top plate;
step 6: installing the adsorption end D01 and the displacement sensor probe G01 of the two-cabin connection release device on a load cabin suspension plate;
step 7: installing a load cabin suspension plate through a cabin height positioning tool, and connecting a magnetic suspension actuator with the load cabin suspension plate;
step 8: removing the tool of the magnetic suspension actuator;
step 9: and connecting the two cabin unlocking devices with the platform cabin top plate and the load cabin suspension plate, and dismantling the cabin height positioning tool to complete cabin assembly.
Specifically, the number of the magnetic suspension actuators is 8, the single magnetic suspension actuator consists of two parts, namely magnetic steel and a coil, a limiting device is arranged between the magnetic steel and the coil, the magnetic steel and the coil can move relatively in a certain range and cannot be completely separated, the magnetic steel part is connected with a suspension plate of a load cabin, and the coil part is connected with a top plate of a platform cabin.
Specifically, the magnetic steel and the coil of the magnetic suspension actuator can be connected by a tool to limit the relative movement of the magnetic steel and the coil, and the magnetic suspension actuator is formed into an independent whole.
Specifically, the number of the two cabin unlocking devices is 4, the bottom of the two cabin unlocking devices is connected with the top plate of the platform cabin, and the top of the two cabin unlocking devices is connected with the suspension plate of the load cabin.
Specifically, the number of the two-cabin connection and release devices is 4, the single set of two-cabin connection and release devices consists of an electromagnetic chuck and an adsorption end, the two devices are not connected or limited, the two devices can be completely separated, the electromagnetic chuck is connected with a platform cabin top plate, and the adsorption end is connected with a load cabin suspension plate.
Specifically, the number of the displacement sensors is 8, the single set of the displacement sensors consists of a sensor probe and a reflecting surface, the sensor probe and the reflecting surface are not connected or limited, the two sensors can be completely separated, the reflecting surface is connected with a platform cabin top plate, and the sensor probe is connected with a load cabin suspension plate.
The separated satellite device provided by the invention is prepared by adopting the separated satellite high-precision measurement and assembly method.
In the description of the present application, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, merely to facilitate description of the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and are not to be construed as limiting the present application.
The foregoing describes specific embodiments of the present invention. It is to be understood that the invention is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the invention. The embodiments of the present application and features in the embodiments may be combined with each other arbitrarily without conflict.

Claims (10)

1. The method for measuring and assembling the separated satellite with high precision is characterized by comprising the following steps of:
step S1: the coil part of the magnetic suspension actuator, electromagnetic chuck ends of the two-cabin connection release device, the reflecting surface of the displacement sensor and the bottoms of the two-cabin unlocking device are arranged on a platform cabin top plate;
step S2: the magnetic steel part of the magnetic suspension actuator, the adsorption ends of the two cabin connection release devices, the displacement sensor probes and the tops of the two cabin unlocking devices are arranged on a load cabin suspension plate;
step S3: the load cabin suspension plate and the platform cabin top plate are connected through the cabin height positioning tool, so that the distance between the load cabin suspension plate and the platform cabin top plate meets the preset requirement;
step S4: and (5) dismantling the cabin height positioning tool, and finishing cabin assembly.
2. The method for measuring and assembling the separated satellite with high precision according to claim 1, wherein the distance between the suction surfaces of the two-cabin connection release device after assembly is 3mm based on the inter-cabin height positioning tool, and the magnetic suspension actuator is longitudinally positioned at the position of-1 mm.
3. The method for measuring and assembling the separated satellite with high precision according to claim 1, wherein a scraper blade is reserved at a magnetic suspension actuator of a plane cabin top plate and a load cabin suspension plate, a two-cabin unlocking device and a two-cabin connection releasing device for adjusting the structure installation precision.
4. The method for measuring and assembling the separated satellite with high precision according to claim 1, wherein the mounting hole of the two-cabin unlocking device is matched with the drill plate, and the mounting hole on the load cabin suspension plate is matched with the drill plate, so that the mounting precision of the two-cabin unlocking device is ensured.
5. The method for measuring and assembling the separated satellite with high precision according to claim 1, wherein the number of the magnetic suspension actuators is 8, and a single set of magnetic suspension actuators comprises magnetic steel and a coil; a limiting device is arranged between the magnetic steel and the coil, and the magnetic steel and the coil can relatively move within a certain range and can not be completely separated.
6. The method for high-precision measurement and assembly of a split satellite according to claim 1, wherein the magnetic steel and the coil of the magnetic suspension actuator are connected by a fixture to limit the relative movement of the two.
7. The method for high-precision measurement and assembly of split satellites according to claim 1, wherein the number of the two-compartment unlocking devices is 4.
8. The method for high-precision measurement and assembly of the separated satellite according to claim 1, wherein the number of the two-cabin connection release devices is 4, and the single set of two-cabin connection release devices consists of an electromagnetic chuck and an adsorption end, and the two devices are not connected or limited and can be completely separated.
9. The method for measuring and assembling the separated satellite with high precision according to claim 1, wherein the number of the displacement sensors is 8, and the single set of the displacement sensors consists of a sensor probe and a reflecting surface, and the two sensors are not connected or limited and can be completely separated.
10. A split satellite prepared by the method of any one of claims 1 to 9.
CN202310073730.3A 2023-01-17 2023-01-17 Separated satellite and high-precision measurement and assembly method thereof Pending CN116079336A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202310073730.3A CN116079336A (en) 2023-01-17 2023-01-17 Separated satellite and high-precision measurement and assembly method thereof

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202310073730.3A CN116079336A (en) 2023-01-17 2023-01-17 Separated satellite and high-precision measurement and assembly method thereof

Publications (1)

Publication Number Publication Date
CN116079336A true CN116079336A (en) 2023-05-09

Family

ID=86208022

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202310073730.3A Pending CN116079336A (en) 2023-01-17 2023-01-17 Separated satellite and high-precision measurement and assembly method thereof

Country Status (1)

Country Link
CN (1) CN116079336A (en)

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