阅读说明：本技术 面向空间碎片监测的非接触扫描卫星平台及装配方法 (Non-contact scanning satellite platform for space debris monitoring and assembling method ) 是由 赵艳彬 廖波 张伟 徐毅 谢进进 唐忠兴 于 2019-09-19 设计创作，主要内容包括：本发明提供了一种面向空间碎片监测的非接触扫描卫星平台及装配方法,包括：敏捷机动舱(1)、非接触控制台(2)和空间碎片监测相机(3)。本发明通过非接触力控制空间碎片高精度探测成像载荷,消除影响卫星平台对空间碎片监测的干扰,创新地解决空间微小碎片和微流星体的捕获跟踪与高品质成像监测问题,可应用于未来空间碎片监测、在轨卫星对空间碎片的防护等技术领域。(The invention provides a space debris monitoring-oriented non-contact scanning satellite platform and an assembly method, wherein the space debris monitoring-oriented non-contact scanning satellite platform comprises the following steps: the device comprises an agile maneuvering cabin (1), a non-contact control console (2) and a space debris monitoring camera (3). The invention controls the high-precision detection imaging load of the space debris through non-contact force, eliminates the interference affecting the monitoring of the space debris by a satellite platform, innovatively solves the problems of capturing, tracking and high-quality imaging monitoring of the space tiny debris and the micro-fluidic star, and can be applied to the technical fields of future space debris monitoring, protection of the on-orbit satellite on the space debris and the like.)

1. A non-contact scanning satellite platform for space debris monitoring, comprising: the device comprises an agile maneuvering cabin (1), a non-contact control console (2) and a space debris monitoring camera (3);

the non-contact console (2) comprises: the device comprises a multi-rib circular truncated cone (201), a U-shaped outer frame (202), an O-shaped inner frame (203), a synchronous ultrasonic motor (204), a coaxial angular displacement sensor (205), a SiCp/Al substrate (206), a non-contact force driving mechanism (207), a linear displacement sensor (208), an electric control locking bolt (209) and a holder controller (210);

the multi-rib circular truncated cone (201) and the holder controller (210) are installed on a top plate of the agile motor cabin (1), the U-shaped outer frame (202) is connected with the multi-rib circular truncated cone (201) through a connecting hole, the synchronous ultrasonic motor (204) and the coaxial angular displacement sensor (205) are installed at two ends of the U-shaped outer frame (202) respectively, the O-shaped inner frame (203) is connected with one group of synchronous ultrasonic motors (204) and the coaxial angular displacement sensor (205) through a pair of rotating shafts, meanwhile, the other group of synchronous ultrasonic motors (204) and the coaxial angular displacement sensor (205) are installed on the other pair of rotating shafts of the inner frame orthogonal to the rotating shaft of the O-shaped inner frame (203), the other group of synchronous ultrasonic motors (204) and the coaxial angular displacement sensor (205) are connected with one pair of rotating shafts of the SiCp/Al substrate (206), the non-contact force driving mechanism (207) and, A linear displacement sensor (208) and an electric control locking bolt (209); the motion control of the non-contact precise control platform (2) is controlled by a pan-tilt controller (210).

2. The non-contact scanning satellite platform facing space debris monitoring as recited in claim 1, characterized in that the agility maneuvering chamber (1) is enclosed by a plurality of side plates a central bearing cylinder, a bottom plate, a middle plate, a bulkhead and a top plate;

the central bearing cylinder is a column-cone assembly.

3. Non-contact scanning satellite platform facing space debris monitoring according to claim 2, characterized in that the agile maneuvering capsule (1) is equipped with two-wing solar wings (118) on both sides.

4. Non-contact scanning satellite platform for space debris monitoring according to claim 2, characterized in that the agile maneuvering capsule (1) is divided into two layers by a middle plate, the upper layer installation comprising: flywheel (101), observing and controlling transponder (102), two-dimentional solar array actuating mechanism (103), on-satellite computer (104), high accuracy fiber-optic gyroscope (105) and data memory (305), the installation of lower floor includes: the device comprises a storage battery (106), a magnetic rod (107), a power supply controller (108), a propelling storage box (109), a pressure sensor (110), a thruster (111) and a pentagonal pyramid moment gyro combination (112).

5. The non-contact scanning satellite platform for space debris monitoring as claimed in claim 4, wherein the flywheel (101), the measurement and control transponder (102), the two-dimensional solar cell array driving mechanism (103), the on-board computer (104) and the high-precision fiber-optic gyroscope (105) are mounted on the upper surface of the middle plate;

the installation of bottom plate reverse side central point puts including: the device comprises a pentagonal pyramid moment gyroscope combination (112), a horizon sensor (116) arranged on the periphery, a data transmission antenna (117) and a measurement and control antenna (113);

the front side of the bottom plate is provided with a storage battery (106), a magnetic rod (107) and a power supply controller (108), and the inverted cone section of the central bearing cylinder is provided with a propelling storage box (109);

a lower partition frame is arranged between the bottom plate and the middle plate, an upper partition frame is arranged between the middle plate and the top plate, and the upper partition frame and the lower partition frame are assembled by adopting high-strength carbon fiber rods and multidirectional glue joints; roof top central authorities installation non-contact control cabinet (2) to the installation includes all around in the roof top: the device comprises a measurement and control antenna (113), a GNSS antenna (114), a star sensor (115), a holder controller (210) and an electric cabinet (304).

6. Non-contact scanning satellite platform facing space debris monitoring according to claim 4, characterized in that the space debris monitoring camera (3) comprises: the camera comprises a light shield (301), an optical machine (302), a camera base (303), an electric cabinet (304) and a data memory (305);

the camera base (303) is connected with a non-contact force driving mechanism (207) of the non-contact control console (2) and an electric control locking bolt (209) to realize repeated contact and non-contact state switching, the light shield (301) and the optical machine (302) are installed on the camera base (303), the electric cabinet (304) is installed on a top plate of the agile maneuvering cabin (1), the data memory (305) is located on a middle layer plate of the agile maneuvering cabin (1), and observation data generated by the space debris monitoring camera (3) are stored and are transmitted with the onboard computer (104).

7. The non-contact scanning satellite platform for space debris monitoring as recited in claim 1, wherein the SiCp/Al substrate (206) comprises a carbon-carbon composite structure of aluminum-based silicon carbide.

8. The non-contact scanning satellite platform facing space debris monitoring as claimed in claim 1, wherein the non-contact force driving mechanism (207) comprises a permanent magnet electric control driving mechanism, one end of a permanent magnet of the permanent magnet electric control driving mechanism is connected with the SiCp/Al substrate (206), one end of an electric control winding is connected with the space debris monitoring camera (3), and the electric control winding is not in direct contact with the permanent magnet.

9. The non-contact scanning satellite platform facing space debris monitoring as claimed in claim 1, wherein the camera base (303) is made of carbon-carbon composite material, and the optical machine (302) is made of coaxial three-reflector structure.

10. A method for assembling a space debris monitoring-oriented non-contact scanning satellite platform, wherein the space debris monitoring-oriented non-contact scanning satellite platform is the space debris monitoring-oriented non-contact scanning satellite platform of claim 2, and the method comprises:

step 1: the bottom plate of the agile maneuvering cabin (1) is integrally assembled with the lower skirt and the central bearing cylinder;

step 2: connecting a middle plate and a partition frame of the agile maneuvering cabin (1) with a central bearing cylinder;

and step 3: connecting a top plate of the agile maneuvering cabin (1) with the central bearing cylinder and the partition frame;

and 4, step 4: installing, connecting and fixing a storage tank and a propelling pipeline in the central bearing cylinder;

and 5: corresponding equipment is installed on the bottom plate;

step 6: corresponding equipment is installed on the middle plate;

and 7: the top plate is provided with a pair of equipment;

and 8: enclosing the assembly obtained in the step 1-7 into a closed agile maneuvering cabin body through a side plate;

and step 9: a non-contact control console (2) is arranged on the top plate;

step 10: a space debris monitoring camera (3) is arranged on the non-contact control console (2);

step 11: solar wings are arranged on two outer sides of the agile maneuvering cabin body.

Technical Field

The invention relates to the field of on-orbit satellite and space debris monitoring, in particular to a non-contact scanning satellite platform for space debris monitoring and an assembly method.

Background

The existing space debris or micro-fluidic star monitoring system generally has two technical schemes of a ground monitoring system and a space monitoring system, the ground system has low observation precision due to the influence of factors such as monitoring equipment, ground environment and the like, and the observation range is limited; the space monitoring system has limited agility and mobility due to the reasons of large weight and inertia of the satellite platform, external vibration interference and the like, cannot guarantee the capturing and tracking precision of space debris, cannot meet the monitoring requirement of small-size space debris by a traditional satellite platform framework, and how to consider far-field capturing and tracking and near-field observation, so that the problem that the realization of high-quality imaging monitoring of the space debris is urgently needed to be solved in the field is solved.

The patent publication No. CN108459351A discloses a resistance type space debris detection device, which comprises a detection shell, a first membrane group, a second membrane group and a piezoelectric effect detection layer, wherein the first membrane group and the second membrane group have the same structure and are respectively formed by overlapping two layers of polymer films, each layer of polymer film is plated with parallel metal conductive wires at equal intervals on the polymer film, the metal conductive wires between the adjacent membrane layers are mutually vertical to form a square lattice close-packed structure, and the detection principle of a contact type is adopted in the device.

Disclosure of Invention

Aiming at the defects in the prior art, the invention aims to provide a non-contact scanning satellite platform for space debris monitoring and an assembling method thereof.

The invention provides a non-contact scanning satellite platform facing space debris monitoring, which comprises: the device comprises an agile maneuvering cabin (1), a non-contact control console (2) and a space debris monitoring camera (3);

the non-contact console (2) comprises: the device comprises a multi-rib circular truncated cone (201), a U-shaped outer frame (202), an O-shaped inner frame (203), a synchronous ultrasonic motor (204), a coaxial angular displacement sensor (205), a SiCp/Al substrate (206), a non-contact force driving mechanism (207), a linear displacement sensor (208), an electric control locking bolt (209) and a holder controller (210);

the multi-rib circular truncated cone (201) and the holder controller (210) are installed on a top plate of the agile motor cabin (1), the U-shaped outer frame (202) is connected with the multi-rib circular truncated cone (201) through a connecting hole, the synchronous ultrasonic motor (204) and the coaxial angular displacement sensor (205) are installed at two ends of the U-shaped outer frame (202) respectively, the O-shaped inner frame (203) is connected with one group of synchronous ultrasonic motors (204) and the coaxial angular displacement sensor (205) through a pair of rotating shafts, meanwhile, the other group of synchronous ultrasonic motors (204) and the coaxial angular displacement sensor (205) are installed on the other pair of rotating shafts of the inner frame orthogonal to the rotating shaft of the O-shaped inner frame (203), the other group of synchronous ultrasonic motors (204) and the coaxial angular displacement sensor (205) are connected with one pair of rotating shafts of the SiCp/Al substrate (206), the non-contact force driving mechanism (207) and, A linear displacement sensor (208) and an electric control locking bolt (209); the motion control of the non-contact precise control platform (2) is controlled by a pan-tilt controller (210).

Preferably, the agility maneuvering cabin (1) is formed by enclosing a central bearing cylinder, a bottom plate, a middle plate, a partition frame and a top plate by a plurality of side plates;

the central bearing cylinder is a column-cone assembly.

Preferably, two solar wings (118) are arranged on two sides of the agile maneuvering cabin (1).

Preferably, the agility maneuvering compartment (1) is divided into two layers by a middle plate, and the upper layer installation comprises: flywheel (101), observing and controlling transponder (102), two-dimentional solar array actuating mechanism (103), on-satellite computer (104), high accuracy fiber-optic gyroscope (105) and data memory (305), the installation of lower floor includes: the device comprises a storage battery (106), a magnetic rod (107), a power supply controller (108), a propelling storage box (109), a pressure sensor (110), a thruster (111) and a pentagonal pyramid moment gyro combination (112).

Preferably, a flywheel (101), a measurement and control transponder (102), a two-dimensional solar cell array driving mechanism (103), an on-board computer (104) and a high-precision fiber-optic gyroscope (105) are arranged on the upper surface of the middle plate;

the installation of bottom plate reverse side central point puts including: the device comprises a pentagonal pyramid moment gyroscope combination (112), a horizon sensor (116) arranged on the periphery, a data transmission antenna (117) and a measurement and control antenna (113);

the front side of the bottom plate is provided with a storage battery (106), a magnetic rod (107) and a power supply controller (108), and the inverted cone section of the central bearing cylinder is provided with a propelling storage box (109);

a lower partition frame is arranged between the bottom plate and the middle plate, an upper partition frame is arranged between the middle plate and the top plate, and the upper partition frame and the lower partition frame are assembled by adopting high-strength carbon fiber rods and multidirectional glue joints; roof top central authorities installation non-contact control cabinet (2) to the installation includes all around in the roof top: the device comprises a measurement and control antenna (113), a GNSS antenna (114), a star sensor (115), a holder controller (210) and an electric cabinet (304).

Preferably, the space debris monitoring camera (3) comprises: the camera comprises a light shield (301), an optical machine (302), a camera base (303), an electric cabinet (304) and a data memory (305);

the camera base (303) is connected with a non-contact force driving mechanism (207) of the non-contact control console (2) and an electric control locking bolt (209) to realize repeated contact and non-contact state switching, the light shield (301) and the optical machine (302) are installed on the camera base (303), the electric cabinet (304) is installed on a top plate of the agile maneuvering cabin (1), the data memory (305) is located on a middle layer plate of the agile maneuvering cabin (1), and observation data generated by the space debris monitoring camera (3) are stored and are transmitted with the onboard computer (104).

Preferably, the SiCp/Al substrate (206) comprises a carbon-carbon composite structure of aluminum-based silicon carbide.

Preferably, the non-contact force driving mechanism (207) comprises a permanent magnet electric control driving mechanism, one end of a permanent magnet of the permanent magnet electric control driving mechanism is connected with a SiCp/Al substrate (206), one end of an electric control winding is connected with the space debris monitoring camera (3), and the electric control winding is not in direct contact with the permanent magnet.

Preferably, the camera base (303) is made of carbon-carbon composite material, and the optical machine (302) is of a coaxial three-reflector structure.

According to the invention, there is provided an assembling method of a non-contact scanning satellite platform for space debris monitoring, the non-contact scanning satellite platform for space debris monitoring is the non-contact scanning satellite platform for space debris monitoring of claim 2, the assembling method includes:

step 1: the bottom plate of the agile maneuvering cabin (1) is integrally assembled with the lower skirt and the central bearing cylinder;

step 2: connecting a middle plate and a partition frame of the agile maneuvering cabin (1) with a central bearing cylinder;

and step 3: connecting a top plate of the agile maneuvering cabin (1) with the central bearing cylinder and the partition frame;

and 4, step 4: installing, connecting and fixing a storage tank and a propelling pipeline in the central bearing cylinder;

and 5: corresponding equipment is installed on the bottom plate;

step 6: corresponding equipment is installed on the middle plate;

and 7: the top plate is provided with a pair of equipment;

and 8: enclosing the assembly obtained in the step 1-7 into a closed agile maneuvering cabin body through a side plate;

and step 9: a non-contact control console (2) is arranged on the top plate;

step 10: a space debris monitoring camera (3) is arranged on the non-contact control console (2);

step 11: solar wings are arranged on two outer sides of the agile maneuvering cabin body.

Compared with the prior art, the invention has the following beneficial effects:

the non-contact force is used for controlling the high-precision detection imaging load of the space debris, eliminating the interference on the monitoring of the space debris by a satellite platform, innovatively solving the problems of capturing, tracking and high-quality imaging monitoring of the space tiny debris and the micro-fluidic star, and being applicable to the technical fields of future space debris monitoring, protection of on-orbit satellites on the space debris and the like;

the method is suitable for quick capture tracking and imaging monitoring tasks of space debris by using technical methods such as small-inertia large-torque maneuvering, non-contact force control, camera integrated design and assembly and the like, can keep good interference isolation performance and maneuvering stability under the driving of non-contact force control force, and is superior to the traditional contact type driving device. Therefore, the invention fully solves the technical problems of high-resolution imaging, stable tracking and application of the space dim and weak target facing a large dynamic range.

The non-contact force control method is adopted, and the satellite large-torque output equipment and the high-precision continuous sampling angular displacement and linear displacement sensor are combined, so that the system has the advantages of strong maneuvering capability, high interference isolation degree, strong maneuvering stability, reliable system and the like. The method has important social and economic values for future space debris monitoring satellite systems, applications, protection of scientific satellites on space debris and the like.

Drawings

Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:

FIG. 1 is a block diagram of the design components of the platform configuration of the present invention;

FIG. 2 is an exploded schematic view of an agile maneuvering pod;

FIG. 3 is an exploded schematic view of a non-contact precision console;

FIG. 4 is an exploded schematic view of a space debris monitoring camera;

FIG. 5 is a schematic view of a flight profile of the platform configuration of the present invention;

FIG. 6 is a schematic view of a launch profile of the platform configuration of the present invention;

FIG. 7 is a flow chart of the assembly of the platform configuration of the present invention.

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 invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.

As shown in fig. 1 to 4, a non-contact scanning satellite platform for space debris monitoring according to the present invention includes: the device comprises an agile maneuvering cabin (1), a non-contact control console (2) and a space debris monitoring camera (3).

The agile maneuvering cabin (1) is characterized in that a lower skirt, a bottom plate and a central bearing cylinder are integrally assembled, the central bearing cylinder is a column-cone assembly, the central bearing cylinder, the bottom plate, a middle plate, a partition frame and a top plate are enclosed by a plurality of side plates to form the agile maneuvering cabin (1), and two sides of the agile maneuvering cabin are provided with double-wing solar wings (118). The agile maneuvering cabin (1) is divided into two layers by a middle plate, a flywheel (101), a measurement and control transponder (102), a two-dimensional solar cell array driving mechanism (103), an onboard computer (104), a high-precision fiber-optic gyroscope (105), a data storage device (305) and other devices are arranged on the upper layer, and a storage battery (106), a magnetic rod (107), a power supply controller (108), a propelling storage box (109), a pressure sensor (110), a thruster (111), a pentagonal pyramid moment gyroscope combination (112) and other devices are arranged on the lower layer. The system comprises a flywheel (101), a measurement and control transponder (102), a two-dimensional solar cell array driving mechanism (103), an on-board computer (104) and a high-precision fiber-optic gyroscope (105), wherein the flywheel (101), the measurement and control transponder, the on-board computer and the high-precision fiber-optic gyroscope (105) are arranged on the upper surface of a middle plate; a pentagonal pyramid moment gyro combination (112) is arranged in the center of the back surface of the bottom plate, a horizon sensor (116), a data transmission antenna (117), a measurement and control antenna (113) and the like are arranged on the periphery of the bottom plate; the front side of the bottom plate is provided with a storage battery (106), a magnetic rod (107) and a power controller (108), the inverted cone section of the central bearing cylinder is provided with a propelling storage box (109), a lower partition frame is arranged between the bottom plate and the middle plate, an upper partition frame is arranged between the middle plate and the top plate, and the upper partition frame and the lower partition frame are assembled by adopting high-strength carbon fiber rods and multidirectional glue joints; a non-contact control console (2) is arranged in the center above the top plate, and a measurement and control antenna (113), a GNSS antenna (114), a star sensor (115), a pan-tilt controller (210), an electric cabinet (304) and the like are arranged on the periphery above the top plate.

The non-contact control console (2) comprises a multi-rib circular truncated cone (201), a U-shaped outer frame (202), an O-shaped inner frame (203), a high-precision synchronous ultrasonic motor (204), a coaxial angular displacement sensor (205), a SiCp/Al substrate (206), a plurality of non-contact force driving mechanisms (207), a plurality of linear displacement sensors (208), an electric control locking bolt (209) and a tripod head controller (210); the multi-rib circular truncated cone (201) and the holder controller (210) are arranged on the top plate of the agile motor cabin (1), the U-shaped outer frame (202) is connected with the multi-rib circular truncated cone (201) through a plurality of connecting holes, the high-precision synchronous ultrasonic motor (204) and the coaxial angular displacement sensor (205) are respectively arranged at two ends of the U-shaped outer frame (202), the O-shaped inner frame (203) is connected with a group of high-precision synchronous ultrasonic motors (204) and the coaxial angular displacement sensor (205) through a pair of rotating shafts, meanwhile, the other pair of rotating shafts of the inner frame orthogonal to the rotating shaft of the O-shaped inner frame (203) is provided with another group of high-precision synchronous ultrasonic motors (204) and the coaxial angular displacement sensor (205), the pair of rotating shafts of the SiCp/Al substrate (206) are connected with the group of high-precision synchronous ultrasonic motors (204) and the coaxial angular displacement sensor (205), and the SiCp/Al substrate (206, A plurality of linear displacement sensors (208) and a plurality of electric control locking bolts (209); the motion control of the non-contact control console (2) is accurately controlled through a pan-tilt controller (210).

Space debris monitoring camera (3) is including lens hood (301), ray apparatus (302), camera base (303), electric cabinet (304), data memory (305). The camera base (303) is connected with a plurality of non-contact force driving mechanisms (207) and a plurality of electric control locking bolts (209) of the non-contact precise control console (2), repeated contact and non-contact state switching can be achieved, a light shield (301) and an optical machine (302) which are arranged on the camera base (303) are key parts for imaging space debris, an electric cabinet (304) is arranged on a top plate of the agile maneuvering cabin (1), and a data memory (305) is arranged on a middle layer plate of the agile maneuvering cabin (1) and used for storing observation data generated by the space debris monitoring camera (3) and carrying out data transmission with the onboard computer (104).

In the embodiment of the invention, the diameter of the satellite lower skirt is the same as that of the bottom ring of the central bearing cylinder, and the lower skirt, the bottom plate and the central bearing cylinder are integrally assembled in the agile maneuvering cabin. The central bearing cylinder is a column-cone combination body, the minimum diameter is 540mm, and the maximum diameter of the bottom is 960 mm. The bottom plate is an embedded reinforced aluminum honeycomb plate with the thickness of 25mm and square central holes with the diameter of 960 mm. The middle plate and the top plate are both aluminum honeycomb plates with embedded reinforcing ribs, the thickness of each of which is 25mm, and the diameter of each of which is 540 mm. The bulkhead is a jointless lightweight bulkhead wound by high-strength carbon fibers, and the size of the bulkhead is 450mm multiplied by 550 mm. The lower bulkhead is a jointless lightweight bulkhead wound by high-strength carbon fibers, and the size of the lower bulkhead is 449mm multiplied by 424 mm. Each side plate is an embedded reinforced aluminum honeycomb plate with the thickness of 15mm, and the size is 1500mm multiplied by 1100 mm.

The multi-rib circular truncated cone of the non-contact control console and the agile service cabin are integrally assembled and are composed of a multi-rib skin and a reinforcing plate, and the size of the multi-rib skin is 760mm in upper circle diameter, 900mm in lower circle diameter and 360mm in circular truncated cone height. The U-shaped outer frame is an integrally formed aluminum alloy reinforcement structure, the size of a U-shaped opening is 732mm, and the outer envelope size of the U-shaped outer frame is 933mm multiplied by 566mm multiplied by 265 mm. The O-shaped inner frame is of an integrally formed aluminum alloy octagonal annular structure, the outer envelope of the O-shaped frame is 650mm long, 612mm wide and 257mm thick, the O-shaped inner frame is high in coaxial precision, the length direction of the O-shaped inner frame is connected with the U-shaped outer frame through the high-precision synchronous ultrasonic motor and the coaxial angular displacement sensor, and the width direction of the O-shaped inner frame is connected with the SiCp/Al substrate through the high-precision synchronous ultrasonic motor and the coaxial angular displacement sensor. The high-precision synchronous ultrasonic motor is a servo control motor with excellent time step consistency, and the motor adopts a stepless reducer to output continuously controllable torque to realize posture adjustment in a large dynamic range. The coaxial angular displacement sensor is a photoelectric structure and outputs an angular displacement value of a rotating angle of the frame rotating shaft relative to a reference zero position to the holder controller. The SiCp/Al substrate is an aluminum-based silicon carbide carbon-carbon composite material structure, has the characteristics of high thermal stability and high modulus, and is used for mounting the space debris monitoring camera on a non-contact accurate control console through a non-contact force driving mechanism and an electric control locking bolt. The non-contact force driving mechanism is a permanent magnet electric control driving mechanism, one end of the permanent magnet is connected with the SiCp/Al substrate, one end of the electric control winding is connected with the space debris monitoring camera, the electric control winding is not in direct contact with the permanent magnet, the driving force output precision and stability of the electric control winding are higher than those of the electric control winding in a conventional electromagnetic driving mode, and the influence of the power interference of the movement of the non-contact accurate control platform on the space debris monitoring camera is blocked under the driving and controlling of the holder controller. The linear displacement sensor is a high-precision laser distance measuring device. The electronic control locking bolt is a titanium alloy bolt driven by a stepping motor, and the SiCp/Al substrate is connected with or released from the space debris monitoring camera. The holder controller is a drive control unit of the non-contact force control holder, and integrates the measurement parameter information of the linear displacement sensor and the coaxial displacement sensor to control the non-contact force control mechanism and the high-precision synchronous ultrasonic motor.

In the space debris monitoring camera, the light shield is of a high-thermal-stability structure and is integrally formed by adopting a carbon fiber reinforced resin-based material. The optical machine is the internal optical path hardware of the camera and adopts a coaxial three-reflector structure. The camera base is made of carbon-carbon composite materials, has a high-plane precision structure and has high thermal stability and heat conductivity. The electric cabinet is a camera detector, an optical-mechanical control unit and a thermal management unit thereof, and is integrally installed with the camera.

Fig. 5 is a schematic view of a flight profile of the platform configuration of the invention, as shown in fig. 2, when the non-contact fast scanning satellite platform for space debris monitoring of the invention flies in orbit, a solar wing (118) is unfolded, a non-contact console (2) controls a plurality of electric control locking bolts (209) to unlock a space debris monitoring camera (3), and a high-precision synchronous ultrasonic motor (204), a coaxial angular displacement sensor (205), a plurality of non-contact force driving mechanisms (207) and a linear displacement sensor (208) control the camera to accurately image space debris under the instruction of a pan-tilt controller (210).

Fig. 6 is a schematic view of the launching profile of the platform configuration of the invention, as shown in fig. 3, when the non-contact fast scanning satellite platform for space debris monitoring launches, the solar wings are folded at two sides of the agile maneuvering chamber (1), and the space debris monitoring camera (3) is locked on the non-contact control console (2).

Fig. 7 is a schematic view illustrating an assembly process of the platform configuration of the present invention, and as shown in fig. 4, the installation method of the space debris monitoring non-contact fast scanning satellite platform launching state of the present invention is as follows:

step 01-agile engine compartment bottom plate, lower skirt and central bearing cylinder are integrally assembled;

step 02-quick maneuvering cabin middle plate, spacer frame and central bearing cylinder are connected;

step03, connecting the top plate of the agile motor cabin with the central force bearing cylinder and the partition frame;

step04, installing, connecting and fixing a storage tank and a propelling pipeline in the central bearing cylinder;

a storage battery, a magnetic rod, a power supply controller, a pentagonal pyramid moment gyro combination, a horizon sensor, a data transmission antenna, a measurement and control antenna and other equipment are arranged on a Step 05-bottom plate;

step06, mounting equipment such as a flywheel, a measurement and control transponder, a two-dimensional solar cell array driving mechanism, an on-satellite computer, a high-precision fiber-optic gyroscope and the like on the middle plate;

step07, mounting a measurement and control antenna, a GNSS antenna, a star sensor, a holder controller, an electric cabinet and other equipment on the top plate;

step 08-a plurality of side plates enclose the assembly body from Step 01-07 into a closed agile maneuvering cabin body;

step 09-installing a non-contact console on the top plate;

step10, mounting a space debris monitoring camera on a non-contact accurate control console;

step 11-two wings of the sun wing are arranged on two sides outside the agile maneuvering cabin and locked and fixed, so that the assembly and the forming of the non-contact rapid scanning satellite platform for space debris monitoring are completed.

In the description of the present application, it is to 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 those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.

The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.