Split type optical satellite platform for multiple application modes

Abstract

According to the split type optical satellite platform oriented to the multiple application modes, physical isolation of the load cabin and the service cabin is achieved through the innovative composite Lorentz force executing mechanism, and interference of vibration of the service cabin on the load cabin is effectively isolated. The composite Lorentz force actuating mechanism not only solves the nonlinear problem and the collision avoidance problem of a traditional actuating mechanism during rotation and large-angle maneuvering, but also has the advantages of being compact in structure, low in control rate, high in response speed, high in output force precision and the like. The platform supports multiple modes such as earth three-axis high-stability imaging, rotary optical imaging and large-angle maneuvering, and the on-orbit application efficiency of an optical satellite is remarkably improved. According to the invention, a new progress of the spaceflight technology in the aspects of high precision and high agility control is displayed, and powerful support is provided for future space tasks.

Description

Technical Field

[0001] The invention belongs to the field of aerospace technology, and in particular relates to a split optical satellite platform oriented to multiple application modes. Background Art

[0002] The concept of split satellites has been successfully verified in on-orbit experiments, and the technology has broad application prospects in fields such as high-precision aerospace observation.

[0003] The dual-supersatellite eight-rod six-degree-of-freedom satellite platform described in the authorized patent CN105059568B achieves static and dynamic isolation of the two cabins through non-contact actuators, which physically eliminates the adverse effects of high-frequency micro-vibration of the service cabin on the payload cabin. However, the relative attitude control and position control of the two cabins are collaboratively performed by multiple actuators, and there is a high probability of collision risk during the maneuver of the entire satellite. In addition, the high-precision linear output of the actuator is only valid within a small angle range. If the relative attitude of the two cabins exceeds this linear range, the output accuracy of the actuator will be reduced.

[0004] Authorized patent CN114962454B describes a non-contact magnetic levitation universal stabilization platform that is common to spacecraft and aircraft within the atmosphere. Its excitation coil system is suspended by electromagnetic force, which can effectively isolate the vibration generated by the aircraft body, and the excitation coil system can achieve three-degree-of-freedom translational suspension, universal deflection and circumferential non-rotational control. However, its translational control adopts a reluctance actuator, which has a large output stiffness, and the output force and current are in a nonlinear relationship. There is also a coupling problem in the translational control, which reduces the vibration isolation effect and control accuracy of the load. The control method of this platform can achieve ultra-quiet and ultra-stable control, but its structure is difficult to achieve large-angle maneuvers, and the structure of this platform is not suitable for large-angle maneuvering control coordinated by two cabins. In order to solve the above problems, the applicant proposes a split optical satellite platform for multiple application modes. Summary of the invention

[0005] The technical problem solved by the present invention is that, based on the existing technology, a split optical satellite platform for multiple application modes is proposed, which can eliminate the vibration interference transmitted from the service module to the payload module, and realize the six-degree-of-freedom high-steady-state ultra-precision and ultra-agile decoupling control of the two cabins through the Lorentz force generated in the composite actuator with a new coil topology structure, and can execute multiple task modes such as three-axis stabilization of the ground, rotational optical imaging, and large-angle coordinated maneuvering of the two cabins.

[0006] The technical solution of the present invention is: a split optical satellite platform for multiple application modes, mainly composed of a payload cabin and a service cabin, which divides an integrated satellite into two parts. The inertia tensors of the two cabins are smaller than those of rigid satellites, which is more conducive to control. The load distribution of the satellite with two cabins is more reasonable than that of the integrated rigid satellite. The characteristics are: the payload cabin mainly includes: a payload cabin body, a satellite-borne computer, a payload cabin base, an actuator annular excitation coil mounting frame, an actuator annular excitation coil connecting frame, an actuator annular excitation coil, an actuator plate The service module mainly includes: the service module body, the service module base, the service module exciter mounting frame, the service module exciter connecting frame, the actuator rotating exciter, the actuator translation exciter, the translation laser rangefinder, the rotating laser rangefinder and the thruster, the flywheel, the antenna, the solar panels and other vibration source components; the exciter coil and the exciter of the composite Lorentz force actuator are connected by the rotating actuator and the translation actuator to achieve zero physical contact electromagnetic force connection. The annular actuator is located in the outer layer of the composite Lorentz force actuator. The exciter of the annular actuator is wrapped by the exciter mounting frame fixed to the service module base. The inner and outer permanent magnets of the exciter are arc-shaped, so that an arc-shaped air gap is formed in the middle, and the center of the arc is located on the rotating axis of the actuator. The excitation coil of the annular actuator is installed on an excitation coil mounting frame fixedly connected to the load cabin base. The excitation coil of the annular actuator is a thin-walled rotating body, and the rotating axis coincides with the rotating axis of the compound Lorentz force actuator. The thin wall of the excitation coil of the annular actuator extends to the air gap traveled by the inner and outer magnets of the exciter of the annular actuator. The excitation coil of the annular actuator is located in the air gap. The excitation coil of the annular actuator is divided into two parts. The rotating coil is located in the middle part of the thin wall of the excitation coil to control the rotation around the roll axis and the pitch axis. There are four groups in total. The installation of each group of rotating coils corresponds to each pair of magnets of the annular actuator one by one. Each group of rotating coils is completely in the uniform magnetic field generated by the corresponding permanent magnet magnets; the translation coils are located on the upper and lower sides of the thin wall of the excitation coil to control the translation around the yaw axis. There are two groups of translation coils, which are located on the upper and lower sides of the thin wall of the excitation coil respectively. The translation coil is 360° annular, and the rotation axis coincides with the rotation axis of the annular actuator. Only the coil in the magnetic field generated by the annular permanent magnet magnet is the working area, which can generate Lorentz force.

[0007] The flat plate actuator is located in the inner layer of the composite Lorentz force actuator, with a total of four groups. The exciter of the flat plate actuator is installed on the inner side of the exciter mounting frame of the service module, and the exciter is fixedly connected to the exciter mounting frame through the flat plate exciter connecting frame. The exciter of the flat plate actuator composed of four pairs of C-shaped magnets is evenly arranged at 90° around the rotation axis of the Lorentz force actuator. The installation center of each group of flat plate actuators and the line perpendicular to the actuator rotation axis coincide with the installation center of each group of annular actuators and the line perpendicular to the actuator rotation axis. The U-shaped magnet generates a uniform magnetic field parallel to the actuator rotation axis; there are four groups of excitation coils of the flat plate actuator, which are installed on the inner wall of the excitation coil mounting frame of the load module and fixed by bolts. The installation position of each group of excitation coils of the flat plate actuator corresponds to each group of exciters of the flat plate actuator. The coil of the flat-plate actuator has a double-layer spherical topology, the coil surface is perpendicular to the rotation axis of the compound Lorentz force actuator, and the middle coils in the double-layer spherical topology are arranged orthogonally and are parallel to the roll axis and the pitch axis respectively.

[0008] The principle of the above scheme is that the actuator separates the payload cabin from the service cabin by means of magnetic levitation to eliminate mechanical collisions, which can effectively isolate the interference generated by the vibration source components of the service cabin from propagating to the payload cabin, thereby meeting the requirements of the payload on the payload cabin for an ultra-high precision working environment. When the satellite platform maneuvers, a master-slave collaborative control strategy is adopted, that is, the coils in the uniform magnetic field are energized to generate Lorentz force to drive the payload cabin to move first, and the service cabin uses flywheels and thrusters to achieve tracking and coordinated movement of the payload cabin. This maneuvering method can achieve ultra-precise, ultra-stable, large-angle agile maneuvers, which can meet the mission requirements of various application modes.

[0009] The principle of the above scheme is that when the rotating coil of the actuator is energized, the two groups of coils positioned on the same axis produce opposite Lorentz force output couples, thereby controlling the actuator to rotate around an axis orthogonal to the axis. For example, the two groups of coils positioned on the roll axis produce opposite Lorentz force output couples, thereby controlling the actuator to rotate around the pitch axis, and vice versa. When the translational coil is energized, the two groups of coils located above and below produce the same Lorentz force, thereby controlling the actuator to translate along the yaw axis. When the flat-plate actuator drives the payload cabin to translate along the roll axis and the pitch axis, the coils of the flat-plate actuator produce Lorentz forces in the same direction, thereby driving the payload cabin to translate along the roll axis and the pitch axis relative to the service cabin. When the flat-plate actuator drives the payload cabin to rotate along the yaw axis, the two groups of coils positioned on the same axis produce opposite Lorentz force output couples, thereby controlling the actuator to rotate around the yaw axis. Figure 3As shown, the magnetic circuit of the magnetic steel of the rotating actuator of the present invention is: the magnetic flux starts from the N pole of the outer upper arc spherical permanent magnet, passes through the upper arc spherical air gap between the inner and outer double layers of permanent magnets, returns to the S pole of the inner upper arc spherical permanent magnet, passes through the inner upper magnetic ring and enters the S pole of the inner annular permanent magnet, passes through the inner lower magnetic ring and enters the N pole of the inner lower arc spherical permanent magnet, passes through the lower arc spherical air gap and reaches the S pole of the outer lower arc spherical permanent magnet, passes through the outer lower magnetic ring and enters the S pole of the outer annular permanent magnet, passes through the N pole of the outer annular permanent magnet, passes through the outer upper magnetic ring and enters the S pole of the outer upper arc spherical permanent magnet, and finally returns to the N pole of the outer upper arc spherical permanent magnet to form a closed loop. Figure 5 As shown, the flat-plate Lorentz force permanent magnet magnetic circuit of the present invention is: the magnetic flux starts from the N pole of the upper permanent magnet, passes through the air gap between the upper and lower permanent magnets, enters the S pole of the lower permanent magnet, enters the lower part of the C-shaped magnetic conductive ring through the lower permanent magnet, passes through the C-shaped magnetic conductive ring, reaches the top of the C-shaped magnetic conductive ring, enters the S pole of the upper permanent magnet, and finally returns to the N pole of the upper permanent magnet to form a closed loop. The advantages of the present invention compared with the prior art are: the present invention adopts a translational actuator and a rotational actuator to achieve full-degree-of-freedom control of the optical satellite platform, the coupling degree of the actuator is low, the structure is more compact, the control difficulty is reduced, and the stability is improved; the actuator is entirely composed of Lorentz force actuators, which significantly reduces the control stiffness and processing cost compared with the prior art; in addition, compared with the prior art, the magnets and coils of the rotational actuators of the roll axis and the pitch axis in the present invention are matched with an arc-shaped spherical structure, which improves the uniformity of the magnetic field intensity, improves the output force linearity, and significantly improves the control accuracy. Based on the composite Lorentz force actuator, the present invention comprehensively improves the control performance of the optical satellite platform, and improves the control stability, degree of freedom and accuracy of the optical satellite platform. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 A front cross-sectional view of a split optical satellite platform for multiple application modes, which is a technical solution of the present invention;

[0011] Figure 2 A front cross-sectional view of a composite Lorentz force actuator according to the technical solution of the present invention;

[0012] Figure 3 A front cross-sectional view of an annular Lorentz force actuator according to the technical solution of the present invention;

[0013] Figure 4 A front cross-sectional view of a flat-plate Lorentz force actuator according to the technical solution of the present invention;

[0014] Figure 5A structural comparison diagram of a Lorentz actuator and a reluctance actuator according to the solution of the present invention;

[0015] Figure 6 A top view of the magnetic field strength of a Lorentz-type annular rotary actuator that is a solution of the present invention.

[0016] In the figure: payload module body (7), payload module base (6), high-precision camera (8), service module body (2), thruster (3), flywheel (4), solar panel (1), composite Lorentz force actuator (5), actuator ring excitation coil mounting frame (503B), actuator excitation coil connecting frame (505), actuator ring exciter (503A), actuator flat exciter (504A), actuator flat excitation coil mounting frame frame (506), actuator flat excitation coil (504B), actuator annular excitation coil (503B), actuator flat excitation coil connecting frame (50405), outer upper arc spherical permanent magnet (50303), inner upper arc spherical permanent magnet (50305), inner upper magnetic conductive ring (50306), inner lower magnetic conductive ring (50308), inner annular permanent magnet (50307), inner lower arc spherical permanent magnet (50309), outer lower Arc spherical permanent magnet (50316), outer upper magnetic conductive ring (50302), outer lower magnetic conductive ring (50313), outer annular permanent magnet (50318), annular exciter mounting frame (50304), annular actuator connecting frame (50301), annular actuator inner magnetic steel washer (50310), annular actuator outer magnetic steel washer (50315), annular actuator excitation coil mounting frame washer (50314), annular rotating coil (50317), upper annular translational coil (50319), lower annular translational coil (50312), details of the actuator flat-plate exciter, C-shaped magnetic steel (50402), vertical upper magnetic steel (50403), vertical lower magnetic steel (50406), flat-plate exciter connecting frame (50401), translational laser rangefinder (501), rotating laser rangefinder mounting frame (508), rotating laser rangefinder (507), and shading plate (509). DETAILED DESCRIPTION

[0017] The following describes the preferred embodiments of the present invention with reference to the drawings in the specification, so that the technical content is clearer and easier to understand. The present invention can be embodied in many different forms of embodiments, and the protection scope of the present invention is not limited to the embodiments mentioned in the text.

[0018] In the drawings, components with the same structure are indicated by the same numerical reference numerals, and components with similar structures or functions are indicated by similar numerical reference numerals. The size and thickness of each component shown in the drawings are arbitrarily shown, and the present invention does not limit the size and thickness of each component. In order to make the illustration clearer, the thickness of the components is appropriately exaggerated in some places in the drawings.

[0019] Example 1

[0020] like Figure 1 , 2 As shown in , 3, a split optical satellite platform for multiple application modes is mainly composed of a payload cabin and a service cabin. The two cabins are connected by a composite Lorentz force actuator (5). The characteristics are: the payload cabin mainly includes: a payload cabin body (7), a payload cabin base (6), an actuator annular excitation coil mounting frame (50311), an actuator excitation coil connecting frame (505), an actuator annular excitation coil (503B), an actuator flat excitation coil mounting frame (506), an actuator flat excitation coil (504B), a sunshade (509) and a high-precision camera (8) and other effective loads The service module mainly comprises: a service module body (2), a translation laser sensor (501), a rotation laser sensor (507), a rotation laser sensor mounting frame (508), a service module exciter mounting frame (50304), a service module exciter connecting frame (502), an actuator ring exciter (503A), an actuator flat plate exciter (504A) and a thruster (3), a flywheel (4), a solar panel (1) and other vibration source components; the two modules of the split optical satellite platform for multiple application modes are connected by a ring actuator and a flat plate actuator to realize non-contact magnetic suspension control of the two modules, Figure 2The front cross-sectional view of the composite Lorentz force actuator (5) of the technical solution of the present invention, the annular actuator (503) is located at the outer layer of the composite actuator, the annular actuator exciter is wrapped by the exciter connecting frame (502) fixedly connected to the base of the service module, the inner and outer permanent magnets of the exciter are arc-shaped, so that an arc-shaped air gap is formed in the middle, and the center of the arc is located on the rotating axis of the actuator. The annular actuator excitation coil (503B) is installed on the annular excitation coil mounting frame (50311) fixedly connected to the base of the payload module, and the annular actuator excitation coil is a thin-walled rotating body, and the rotating axis coincides with the rotating axis of the composite Lorentz force actuator. The thin wall of the excitation coil of the annular actuator extends to the air gap traveled by the inner and outer magnets of the exciter of the annular actuator. The excitation coil of the annular actuator is located in the air gap. The excitation coil of the annular actuator is divided into two parts. The rotating coil (50317) located in the middle of the thin wall of the excitation coil controls the rotation around the roll axis and the pitch axis. There are four groups in total. The installation of each group of rotating coils corresponds to each pair of magnets of the annular actuator one by one. Each group of rotating coils is completely in the uniform magnetic field generated by the corresponding permanent magnet. The translation coils (50312) and (50319) located on the upper and lower sides of the thin wall of the excitation coil control the translation around the yaw axis. There are two groups of translation coils, which are located on the upper and lower sides of the thin wall of the excitation coil respectively. The translation coil is 360° annular, and the rotation axis coincides with the rotation axis of the annular actuator. Only the coil in the magnetic field generated by the annular permanent magnet is the working area, which can generate the Lorentz force. The flat plate actuator (504) is located in the inner layer of the composite Lorentz force actuator, and there are four groups in total. The exciter of the flat plate actuator is installed on the inner side of the exciter mounting frame of the service module, and the exciter is fixedly connected to the exciter mounting frame (503) through a flat plate exciter connecting frame (50401). The exciter of the flat plate actuator composed of four pairs of C-shaped magnetic steels (50402) is evenly arranged at 90° around the rotation axis of the Lorentz force actuator. The installation center of each group of flat plate actuators is perpendicular to the line connecting the rotation axis of the actuator and the installation center of each group of annular actuators coincides with the line connecting the installation center of each group of annular actuators and the line connecting the installation center of each group of annular actuators and the line perpendicular to the rotation axis of the actuator. The vertical magnetic steels (50403) and (50406) connected to the C-shaped magnetic steel generate a uniform magnetic field parallel to the rotation axis of the actuator; the excitation coils of the flat plate actuator are four groups in total, which are installed on the inner wall of the flat plate excitation coil mounting frame (506) of the load compartment through the flat plate excitation coil mounting frame (50405) and fixed by bolts, and the installation position of each group of excitation coils of the flat plate actuator corresponds to each group of excitation subs of the flat plate actuator. The coils (50404) of the flat plate actuator are double-layered sun-shaped topology, the coil surface is perpendicular to the rotation axis of the compound Lorentz force actuator, and the arrangement of the middle coils in the double-layered sun-shaped topology is orthogonal, and are parallel to the roll axis and the pitch axis respectively.

[0021] Figure 3The front cross-sectional view of the annular Lorentz force actuator (503) of the technical solution of the present invention comprises an annular excitation coil and an annular excitation element. The annular excitation coil portion comprises an annular actuator connecting frame (50301), an annular actuator inner magnetic steel gasket (50310), an annular actuator outer magnetic steel gasket (50315), an annular actuator excitation coil mounting frame (50311), an annular actuator excitation coil mounting frame gasket (50314), an annular rotating coil (50317), an upper annular translational coil (50319), and a lower annular rotating coil (50319). The annular exciter part includes: an annular exciter mounting frame (50304), an outer upper arc spherical permanent magnet (50303), an inner upper arc spherical permanent magnet (50305), an inner upper magnetic conductive ring (50306), an inner lower magnetic conductive ring (50308), an inner annular permanent magnet (50307), an inner lower arc spherical permanent magnet (50309), an outer lower arc spherical permanent magnet (50316), an outer upper magnetic conductive ring (50302), an outer lower magnetic conductive ring (50313), and an outer annular permanent magnet (50318). Four pairs of annular actuator rotating coils are evenly arranged at 90° around the rotation axis of the Lorentz force actuator.

[0022] Figure 4 The front cross-sectional view of the flat-plate Lorentz force actuator of the technical solution of the present invention mainly includes two parts: a flat-plate excitation coil and a flat-plate excitation sub. The flat-plate excitation coil part includes a double-layer Japanese-shaped flat-plate coil (50404), a flat-plate excitation coil mounting frame (506), and a flat-plate excitation coil connecting frame (50401); the flat-plate excitation sub part includes a C-shaped magnetic steel (50402), a vertical upper magnetic steel (50403), a vertical lower magnetic steel (50406), and a flat-plate excitation sub connecting frame (50401). The excitation sub of the flat-plate actuator composed of four pairs of C-shaped magnetic steels is evenly arranged at 90° around the rotation axis of the composite Lorentz force actuator, and the installation center of each group of flat-plate actuators is perpendicular to the line connecting the rotation axis of the actuator and the installation center of each group of annular actuators and the line connecting the rotation axis of the actuator.

[0023] The contents not described in detail in the specification of the present invention belong to the prior art known to the professional and technical personnel in this field.

[0024] The above shows and describes the basic principles and main features of the present invention and the advantages of the present invention. It is obvious to those skilled in the art that the present invention is not limited to the details of the above exemplary embodiments, and the present invention can be implemented in other specific forms without departing from the spirit or basic features of the present invention. Therefore, no matter from which point of view, the embodiments should be regarded as exemplary and non-restrictive. The scope of the present invention is defined by the attached claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims are included in the present invention. Any figure mark in the claims should not be regarded as limiting the claims involved.

[0025] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. A split optical satellite platform for multiple application modes, characterized in that: It comprises a load compartment (7), a service compartment (2) and a split-type actuator connected between the load compartment and the service compartment (Fig. 2); The payload compartment comprises: The load compartment body (7) can be regarded as a rigid body; The load compartment body base (6) is connected to the actuator excitation coil connecting frame (505); The attitude sensor and the payload (8) are fixedly connected to the payload cabin body; The service module comprises: A service module body (2), and a power supply component, a posture component and a communication component arranged on the service module body; The service module body is connected to the exciters (503A) and (504A) of the composite Lorentz force actuator; The composite Lorentz force actuator comprises: An actuator annular excitation coil mounting frame (503B), one side of which is connected to the base of the corresponding load compartment body (6) via an actuator excitation coil connecting frame (505); A service module exciter connection frame (502), the service module exciter connection frame is annular, the upper layer of the service module exciter connection frame is connected to the service module body base (2), and the inner side of the service module exciter connection frame is connected to the service module annular exciter mounting frame (50304); An actuator annular exciter (503A), the actuator annular exciter being connected to the other side of the annular exciter mounting frame (50304); An actuator flat plate exciter (504A), the actuator flat plate exciter being connected to the inner wall of the annular exciter mounting frame (50304) via a flat plate exciter connecting frame (50401); An actuator annular excitation coil (503B), the actuator annular excitation coil (503B) being connected to the other side of the actuator excitation coil connecting frame (505); An actuator flat plate excitation coil (504B), the actuator flat plate excitation coil (504B) being connected to the actuator flat plate excitation coil mounting frame (506); The actuator annular excitation coil (503B) and the actuator annular exciter (503A) are installed in a coaxial manner; The position of the actuator flat plate excitation coil (504B) matches that of the actuator flat plate exciter (504A).

2. The structure of the split optical satellite platform according to claim 1 is characterized in that: The actuator annular exciter (503A) comprises: An outer upper arc spherical permanent magnet (50303), wherein the inner side of the outer upper arc spherical permanent magnet is a spherical surface, and the center of the sphere coincides with the annular excitation coil (503B) of the actuator; An inner upper arc spherical permanent magnet (50305), the outer side of the inner upper arc spherical permanent magnet is a spherical surface, and the center of the sphere coincides with the annular excitation coil (503B) of the actuator; An inner upper magnetic conductive ring (50306), the inner upper magnetic conductive ring is a 360° ring, the rotation axis coincides with the rotation axis of the composite Lorentz force actuator, and the inner upper magnetic conductive ring connects the inner upper arc spherical permanent magnet (50305) and the inner ring permanent magnet (50307); An inner lower magnetic conductive ring (50308), the inner lower magnetic conductive ring is a 360° ring, the rotation axis coincides with the rotation axis of the composite Lorentz force actuator, and the inner lower magnetic conductive ring connects the inner lower arc spherical permanent magnet (50309) and the inner ring permanent magnet (50307); An inner annular permanent magnet (50307), the inner annular permanent magnet is a 360° annular shape, and the rotation axis coincides with the rotation axis of the composite Lorentz force actuator; An inner lower arc spherical permanent magnet (50309), wherein the outer side of the inner lower arc spherical permanent magnet is a spherical surface, and the center of the sphere coincides with the annular excitation coil (503B) of the actuator; An outer lower arc spherical permanent magnet (50316), wherein the inner side of the outer lower arc spherical permanent magnet is a spherical surface, and the center of the sphere coincides with the annular excitation coil (503B) of the actuator; An outer upper magnetic conductive ring (50302), the outer upper magnetic conductive ring is a 360° ring, the rotation axis coincides with the rotation axis of the composite Lorentz force actuator, and the outer upper magnetic conductive ring connects the outer upper arc spherical permanent magnet (50303) and the outer ring permanent magnet (50318); An outer lower magnetic conductive ring (50313), the outer lower magnetic conductive ring is a 360° ring, the rotation axis coincides with the rotation axis of the composite Lorentz force actuator, and the outer lower magnetic conductive ring connects the outer lower arc spherical permanent magnet (50316) and the outer ring permanent magnet (50318); An outer annular permanent magnet (50318), the outer annular permanent magnet is a 360° annular shape, and the rotation axis coincides with the rotation axis of the composite Lorentz force actuator.

3. The split optical satellite platform structure according to claim 1, characterized in that: The actuator annular excitation coil (503B) comprises: An actuator annular excitation coil mounting frame (50311), the actuator annular excitation coil mounting frame is a single-layer annular frame, and the portion extending to the actuator annular excitation sub-horizontal magnetic yoke is provided with 6 grooves evenly arranged around the rotation axis of the actuator annular excitation coil mounting frame, which are used to place the annular rotating coil (50317) and the upper annular translational coil (50312) and the lower annular translational coil (50319); An annular rotating coil (50317), the annular rotating coil being placed in a groove inside the annular excitation coil mounting frame (50311); The annular rotating coil (50317) is evenly placed at 90° around the rotation axis of the composite Lorentz force actuator; The annular translational coil is 360° annular, and its rotation axis coincides with the rotation axis of the composite Lorentz force actuator; The actuator annular excitation coil is completely wrapped by the magnetic field generated by the actuator annular exciter (503A).

4. The split optical satellite platform structure according to claim 1, characterized in that: The actuator plate exciter (504A) comprises: A C-shaped magnetic steel (50402), wherein the front view of the C-shaped magnetic steel is C-shaped, the upper end of the C-shaped magnetic steel is connected to the vertical upper magnetic steel (50403), and the lower end of the C-shaped magnetic steel is connected to the vertical lower magnetic steel (50403); A vertical upper magnetic steel (50403), the vertical upper magnetic steel is a rectangular parallelepiped, and the bottom surface generates a magnetic field parallel to the rotation axis of the composite Lorentz force actuator; A vertical lower magnetic steel (50406), wherein the vertical lower magnetic steel is a rectangular parallelepiped, and the top surface generates a magnetic field parallel to the rotation axis of the composite Lorentz force actuator; A flat plate exciter connection frame (50401), wherein the front view of the flat plate exciter connection frame is stepped, and two stepped surfaces are respectively connected to the C-shaped magnetic steel (50402) and the annular exciter mounting frame (50304).

5. The structure of the split optical satellite platform for multiple application modes according to claim 1 is characterized in that: The actuator flat plate excitation coil (504B) comprises: A flat plate excitation coil (50404), the flat plate excitation coil is a double-layer sun-shaped coil, the middle winding parts of the two layers of coils are orthogonal, and the arrangement directions are respectively parallel to the roll axis and the pitch axis, and the flat plate excitation coil is connected to the flat plate excitation coil connecting frame (50405); A flat plate excitation coil mounting frame (506), wherein the flat plate excitation coil mounting frame is a hollow cylinder, and the rotation axis of the flat plate excitation coil mounting frame coincides with the rotation axis of the composite Lorentz force actuator; Flat plate excitation coil connecting frame (50405); there are four flat plate excitation coil connecting frames in total, which are evenly placed on the outer wall of the flat plate excitation coil mounting frame around the rotation axis of the flat plate excitation coil mounting frame.

6. The split optical satellite platform structure according to claim 1, characterized in that: A translational laser rangefinder (501) is provided on the inner wall of the service module exciter connection frame (502).

7. The split optical satellite platform structure according to claim 1, characterized in that: A rotating laser rangefinder mounting frame (508) is provided on the inner wall of the service module exciter connecting frame (502).

8. The split optical satellite platform structure according to claim 1, characterized in that: A rotating laser rangefinder (507) is provided on the wall surface of the rotating laser rangefinder mounting frame (508).

9. The split optical satellite platform structure according to claim 1, characterized in that: The number of the annular rotating coils (50317) is 4, and the number of the annular translational coils is 2, including an upper annular translational coil (50319) and a lower annular translational coil (50312).

10. The split optical satellite platform structure according to claim 1, characterized in that: The number of the actuator flat plate exciter (504A) and the actuator flat plate excitation coil (504B) is four.

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