1. A highly-generalized and light media micro-nano satellite structure platform is characterized by comprising a satellite adapter (1), a connecting column (2), a lower conical cylinder wall (3), a central force bearing cylinder (4), a lower polygonal ring band (5), a middle cylinder wall (6), a supporting frame (7), a satellite solar wing assembly (8), a comprehensive electronic mounting plate (9), an upper polygonal ring band (10), an angle mounting plate (11), a load control unit (12), a camera load mounting plate (13), an upper conical cylinder wall (14), a communication antenna (15), a circular hoop (16), a light shield (17), an orbit control mounting plate (18), a power supply unit mounting plate (19), a load control unit mounting plate (20) and a camera mounting plate (21);

the bottom of the central bearing cylinder (4) and the lower conical cylinder wall (3) form a satellite attitude and orbit control system, the satellite attitude and orbit control system is arranged above the satellite adapter (1), the lower conical cylinder wall (3) is fixedly sleeved outside the central bearing cylinder (4), the side surface of the bottom of the central bearing cylinder (4) inclines to form a sealed conical structure with the lower conical cylinder wall (3), the bottom of the lower conical cylinder wall (3) is connected with the satellite adapter (1) through a plurality of connecting columns (2), and an attitude and orbit control mounting plate (18) is mounted on a circular ring at the bottom of the central bearing cylinder (4);

the middle section of the central bearing cylinder (4), the middle cylinder wall (6) and the power supply mounting plate (19) form a power supply system, the power supply system is arranged above the satellite attitude and orbit control system, the middle cylinder wall (6) is fixedly sleeved outside the middle section of the central bearing cylinder (4), the power supply mounting plate (19) is mounted at the bottom of the middle cylinder wall (6), the satellite solar wing assemblies (8) are symmetrically mounted in the middle parts of two sides of the middle cylinder wall (6), and the lower end of the middle cylinder wall (6) is fixed on the corresponding side wall of the middle section of the central bearing cylinder (4) through a lower polygonal ring belt (5);

the detachable angle-shaped mounting plates (11) are buckled on the periphery of the middle upper part of the central bearing cylinder (4) to form a closed space, the comprehensive electronic mounting plate (9) is mounted on a plane formed by the bottoms of the angle-shaped mounting plates (11), the comprehensive electronic mounting plate (9) is supported and connected by a plurality of supporting frames (7), and the supporting frames (7) are fixed on the middle cylinder wall (6);

an upper conical cylinder wall (14) is fixedly sleeved on the outer portion of the upper end of the central bearing cylinder (4), a camera load mounting plate (13) is arranged in the upper conical cylinder wall (14), a ring of polygonal ring belt (10) is additionally arranged at the joint of the upper conical cylinder wall (14) and the central bearing cylinder (4) to be fixed, a load control single machine mounting plate (20) is arranged at the bottom of the upper conical cylinder wall (14), a load control single machine (12) is fixed on the load control single machine mounting plate (20), a light shield (17) is arranged above the upper conical cylinder wall (14), and an annular hoop (16) is fixed on the periphery of the light shield (17).

2. The highly generalized, lightweight media micro-nano satellite structure platform according to claim 1, characterized in that: the angle-shaped mounting plate (11) is of an inclined mounting structure, and a solar cell is adhered to the angle-shaped mounting plate (11).

3. The highly generalized, lightweight media micro-nano satellite structure platform according to claim 1, characterized in that: the satellite adapter (1) is an integrally formed structure consisting of conical rod pieces.

4. The highly generalized, lightweight media micro-nano satellite structure platform according to claim 1, characterized in that: the middle section of the central bearing cylinder (4), the middle cylinder wall (6) and the power supply mounting plate (19) form a closed space structure.

5. The highly generalized, lightweight media micro-nano satellite structure platform according to claim 1, characterized in that: a plurality of communication antennas (15) are arranged on the periphery of the load control single machine mounting plate (20) and extend obliquely to the outer part of the upper conical cylinder wall (14).

6. The highly generalized, lightweight media micro-nano satellite structure platform according to claim 1, characterized in that: when communication or non-remote sensing load, the light shield (17) is replaced by a camera load mounting plate (13) and fixed at the top of the upper conical cylinder wall (14), and when a remote sensing camera is designed, a camera mounting plate (21) is fixed in the light shield (17) at the top of the upper conical cylinder wall (14).

Background

Media is an abstract term, which refers to information transmission media (communication, digital media, broadcast, television, movie, publishing, advertisement, news, network, cultural industry, new media, etc.), and with the development of technology, satellite media has become an important part of the information transmission field. The micro-nano satellite structure platform has higher and higher requirements on universalization, standardization and lightweight design, so that the satellite structure platform is required to be designed ingeniously, and how to more widely adapt to various commercial goods shelf subsystem units (COTS) in the market is also considered, such as an effective load, an integrated electronic module, a power supply module and the like. The design of the micro-nano satellite also strengthens the integral design concept of the whole satellite more and more, and the configuration integration design is adopted, so that the compactness of a single machine is improved, for example, the shell of part of instrument equipment is used as one part of a platform structure, the complexity of the main bearing structure design is reduced, the model flattening design is realized, the number of single machine products is reduced, and the universality of a structure platform is ensured. Starting from the whole satellite, the structure integrated design further reduces the structure size and the whole satellite mass of the satellite. The important point for realizing the generalization is to establish a standardized technical system, realize the standardization of the interface and have the space for integrated integration and function improvement.

Cost control needs to be considered in design, production and assembly of the micro-nano satellite, and application requirements of users based on cost are met. This needs to be considered comprehensively from multiple dimensions such as development process, design and manufacture, product assurance, organization and management, and so on, and focuses on a few and mass development process optimization, standardized design, advanced simulation design means, application and reliability guarantee of COTS products, low-cost satellite AIT and test, management mode, and so on.

With increasingly clear requirements of micro-nano satellites on integration, modularization and standardization, common satellite structure platforms are excessively limited by customized requirement design, for example, remote sensing loads and communication loads are incompatible with design requirements of the platforms, and single-machine forms of service systems are various, so that a great obstacle is brought to the generalized design of satellite platform structures. The cube satellite is used as a branch of a small satellite, has small volume and high integration level, and the appearance of the cube satellite is inseparable from the progress of the microelectronic technology, the development of light materials, the appearance of high-power solar cells and the reduction of the cost of satellite core parts, so that the appearance of the cube satellite promotes the process of modularization and standardization of the small satellite industry. However, due to the limitation of the size and scale of the cube star, the cube star is often too single in function, and has poor flexibility in adaptability to some COTS products in the market, such as remote sensing loads and communication loads.

Disclosure of Invention

The invention aims to provide a highly-generalized and light media micro-nano satellite structure platform to solve the problems in the background technology.

In order to achieve the purpose, the invention provides the following technical scheme: a highly-generalized and light media micro-nano satellite structure platform comprises a satellite adapter, a connecting column, a lower conical cylinder wall, a central force bearing cylinder, a lower polygonal ring belt, a middle cylinder wall, a supporting frame, a satellite solar wing assembly, a comprehensive electronic mounting plate, a camera load mounting plate, an upper polygonal ring belt, an angular mounting plate, a load control unit, an upper conical cylinder wall, a communication antenna, a circular hoop, a light shield, a posture and orbit control mounting plate, a power supply unit mounting plate, a load control unit mounting plate and a camera mounting plate;

the bottom of the central bearing cylinder and the wall of the lower conical cylinder form a satellite attitude and orbit control system, the satellite attitude and orbit control system is arranged above the satellite adapter, the wall of the lower conical cylinder is sleeved and fixed outside the central bearing cylinder, the side surface of the bottom of the central bearing cylinder inclines to form a sealed conical structure with the wall of the lower conical cylinder, the bottom of the lower conical cylinder is connected with the satellite adapter through a plurality of connecting columns, and an attitude and orbit control mounting plate is arranged on a circular ring at the bottom of the central bearing cylinder;

the middle section of the central bearing cylinder, the middle cylinder wall and the power supply mounting plate form a power supply system, the power supply system is arranged above the satellite attitude and orbit control system, the middle cylinder wall is sleeved and fixed outside the middle section of the central bearing cylinder, the power supply mounting plate is mounted at the bottom of the middle cylinder wall, the satellite solar wing assemblies are symmetrically mounted in the middle parts of two sides of the middle cylinder wall, and the lower end of the middle cylinder wall is fixed on the corresponding side wall of the middle section of the central bearing cylinder through a lower polygonal ring belt;

the integrated electronic mounting plate is arranged on a plane formed at the bottom of each angular mounting plate and is supported and connected by a plurality of support frames, and the support frames are fixed on the wall of the middle cylinder;

an upper conical cylinder wall is fixedly sleeved outside the upper end of the central bearing cylinder, a camera load mounting plate is arranged in the upper conical cylinder wall, a ring polygonal ring belt is additionally arranged at the joint of the upper conical cylinder wall and the central bearing cylinder and fixed, a load control unit mounting plate is arranged at the bottom of the upper conical cylinder wall, a load control unit is fixedly arranged on the load control unit mounting plate, a light shield is arranged above the upper conical cylinder wall, and an annular clamp is fixedly arranged on the periphery of the light shield.

Preferably, the angle-shaped mounting plate is of an inclined mounting structure, and the solar cell is adhered to the angle-shaped mounting plate.

Preferably, the satellite adapter is an integrally formed structure consisting of conical rod pieces.

Preferably, the middle section of the central force bearing cylinder, the middle cylinder wall and the power supply mounting plate form a closed space structure.

Preferably, a plurality of communication antennas are arranged on the periphery of the load control single machine mounting plate and extend obliquely to the outer part of the upper conical cylinder wall.

Preferably, when communication or non-remote sensing load, the lens hood is replaced by the camera load mounting plate and fixed at the top of the upper conical cylinder wall, and when the remote sensing camera is designed, the camera mounting plate is fixed in the lens hood at the top of the upper conical cylinder wall.

Compared with the prior art, the invention has the beneficial effects that: the satellite structure platform disclosed by the invention can be compatible with the installation of remote sensing loads and communication loads at the same time through ingenious structural design, is advanced in appearance, can flexibly deal with COTS products on the market, and can meet the application of the remote sensing loads and the installation of the communication loads; the satellite structure platform has the characteristics of high universality, modular design and light weight design, meets the integrated design requirements of the micro-nano satellite, and has attractive appearance and excellent pneumatic performance.

Drawings

FIG. 1 is a front elevational view of the final assembly of the present invention;

FIG. 2 is a detail of the present invention in a single piece;

fig. 3 is a cross-sectional view of the plane of symmetry a-a of the present invention.

In the figure: 1. a satellite adapter; 2. connecting columns; 3. a lower conical cylinder wall; 4. a central force bearing cylinder; 5. a lower polygonal annulus; 6. a middle section cylinder wall; 7. a support frame; 8. a satellite solar wing assembly; 9. a composite electronic mounting board; 10. an upper polygonal ring belt; 11. an angular mounting plate; 12. a load control single machine; 13. a camera load mounting plate; 14. an upper conical cylinder wall; 15. a communication antenna; 16. a circular hoop; 17. a light shield; 18. a posture and orbit control mounting plate; 19. a power supply single machine mounting plate; 20. a load control single machine mounting plate; 21. a camera mounting plate.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it should be noted that the terms "vertical", "upper", "lower", "horizontal", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing the present invention 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 invention.

In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

Referring to fig. 1-3, the present invention provides a technical solution: a highly-generalized and light media micro-nano satellite structure platform comprises a satellite adapter 1, a connecting column 2, a lower conical cylinder wall 3, a central force bearing cylinder 4, a lower polygonal ring band 5, a middle cylinder wall 6, a supporting frame 7, a satellite solar wing assembly 8, a comprehensive electronic mounting plate 9, an upper polygonal ring band 10, an angle mounting plate 11, a load control unit 12, a camera load mounting plate 13, an upper conical cylinder wall 14, a communication antenna 15, a circular hoop 16, a light shield 17, a posture and orbit control mounting plate 18, a power supply unit mounting plate 19, a load control unit mounting plate 20 and a camera mounting plate 21;

the bottom of the central bearing cylinder 4 and the lower conical cylinder wall 3 form a satellite attitude and orbit control system, the satellite attitude and orbit control system is arranged above the satellite adapter 1, the lower conical cylinder wall 3 is sleeved and fixed outside the central bearing cylinder 4, the side surface of the bottom of the central bearing cylinder 4 inclines to form a sealed conical structure with the lower conical cylinder wall 3, the bottom of the lower conical cylinder wall 3 is connected with the satellite adapter 1 through a plurality of connecting columns 2, and an attitude and orbit control mounting plate 18 is arranged on a circular ring at the bottom of the central bearing cylinder 4;

the middle section of the central bearing cylinder 4, the middle cylinder wall 6 and the power supply mounting plate 19 form a power supply system, the power supply system is arranged above the satellite attitude and orbit control system, the middle cylinder wall 6 is fixedly sleeved outside the middle section of the central bearing cylinder 4, the power supply mounting plate 19 is arranged at the bottom of the middle cylinder wall 6, the satellite solar wing assemblies 8 are symmetrically arranged in the middle parts of two sides of the middle cylinder wall 6, and the lower end of the middle cylinder wall 6 is fixed on the corresponding side wall of the middle section of the central bearing cylinder 4 through the lower polygonal ring belt 5;

the plurality of detachable angle-shaped mounting plates 11 are buckled on the periphery of the middle upper part of the central bearing cylinder 4 to form a closed space, the comprehensive electronic mounting plate 9 is mounted on a plane formed by the bottom of each angle-shaped mounting plate 11, the comprehensive electronic mounting plate 9 is supported and connected by a plurality of supporting frames 7, and the supporting frames 7 are fixed on the middle cylinder wall 6;

an upper conical cylinder wall 14 is fixedly sleeved on the outer portion of the upper end of the central bearing cylinder 4, a camera load mounting plate 13 is arranged in the upper conical cylinder wall 14, a circle of upper polygonal ring belt 10 is additionally arranged at the joint of the upper conical cylinder wall 14 and the central bearing cylinder 4 for fixing, a load control single machine mounting plate 20 is mounted at the bottom of the upper conical cylinder wall 14, a load control single machine 12 is fixedly arranged on the load control single machine mounting plate 20, a light shield 17 is mounted above the upper conical cylinder wall 14, and an annular clamp 16 is fixedly arranged on the periphery of the light shield 17.

Preferably, the angle mounting plate 11 has an inclined mounting structure, and the solar cell is attached to the angle mounting plate 11.

Preferably, the satellite adapter 1 is an integrally formed structure composed of conical rod members.

Preferably, the middle section of the central force bearing cylinder 4, the middle cylinder wall 6 and the power supply mounting plate 19 form a closed space structure.

Preferably, a plurality of communication antennas 15 are installed on the outer circumference of the load control stand-alone mounting plate 20 and extend obliquely to the outside of the upper conical cylinder wall 14.

Preferably, the light shield 17 is fixed on the top of the upper conical cylinder wall 14 instead of the camera load mounting plate 13 in communication or non-remote sensing load, and the camera mounting plate 21 is fixed in the light shield 17 on the top of the upper conical cylinder wall 14 in remote sensing camera design.

The working principle is as follows: the lower end of the satellite structure platform body is connected with the satellite adapter 1 through the connecting columns 2, the satellite adapter 1 is a conical rod body, the machining integral forming process is adopted, the conical rod structure meets the weight reduction requirement, the rigidity requirement of the adapter is also guaranteed, the disc mounting plate is convenient for explosive separation or random matching of belt separation, the structure force transmission path is direct, the material utilization rate is high, and the structural stability is utilized by conical configuration.

The lower section of the central bearing cylinder 4 and the lower conical cylinder wall 3 form a conical closed structure, the attitude and orbit control mounting plate 18 is directly arranged on the circular ring of the central bearing cylinder 4, the attitude and orbit control mounting plate 18 can be designed according to the pertinence of an attitude and orbit control single machine, a flexible mounting design is set for single machine mounting, and the requirement of universality is met. The middle section of the central bearing cylinder 4, the middle cylinder wall 6 and the power supply mounting plate 19 form a closed structure, and enough arrangement space is reserved for a power supply system and a partial attitude and orbit control system.

The satellite solar wing component 8 is designed in a bilateral symmetrical layout mode, the solar sailboards are arranged on two sides of the middle cylinder wall 6 of the satellite close to the middle position, when the satellite solar wing component 8 is in a folded state, the middle cylinder wall 6 provides a compression point position for the satellite solar wing component, the layout firstly meets the requirement of modular design, a power supply system is arranged in the middle of the satellite, and the cable length and the wiring complexity are reduced.

The lower end of the middle cylinder wall 6 is reinforced and connected to the relative connecting ring of the central bearing cylinder 4 by a lower polygonal ring belt 5, so that the rigidity of the whole structure is enhanced. In order to meet the requirement of remote sensing load, an integrated design concept is adopted, a light shield 17 of a camera is designed on a satellite platform, the light shield is connected by an annular hoop 16, and the annular hoop 16 can play a role in reinforcing the light shield 17 of the camera and can also be used for arranging a satellite communication antenna.

The detachable angle-shaped mounting plate 11 is buckled on the middle upper part of the central bearing cylinder 4 to form a closed space and play a role in supporting and reinforcing a satellite structure, the detachable angle-shaped mounting plate 11 is buckled on the middle upper part of the central bearing cylinder 4 to play a role in maintaining the shape and expand the internal space of a satellite structure platform, a solar battery can be pasted on the angle-shaped mounting plate 11 to provide an effective way for the satellite platform to expand the power supply capacity, and the angle-shaped mounting plate 11 is obliquely installed to contribute to the design of structural stability; synthesize the electron mounting panel 9 and support by a plurality of support frames 7 and connect, support frame 7 is connected to middle part section of thick bamboo wall 6 on, forms stable mounting platform, and angular form mounting panel 11 easy dismounting is convenient for synthesize electron single-machine installation and debugging.

The upper conical cylinder wall 14 is connected with the upper end of the central bearing cylinder 4, a polygonal ring belt 10 is additionally arranged to form a stable conical cylinder structural space, a load control single-machine mounting plate 20 is designed at the bottom, flexible mounting design is achieved, the requirements of various single-machine mounting environments are met, and meanwhile, a mounting space of a certain type of communication antenna 15 is also provided.

In order to meet the requirement of remote sensing load, an integrated design concept is adopted, a light shield 17 of a camera is designed on a satellite platform, the light shield is connected by an annular hoop 16, and the annular hoop 16 can play a role in reinforcing the light shield 17 of the camera and can also be used for arranging a satellite communication antenna 15.

When the satellite structure platform is used for communication or non-remote sensing loads, the light shield 17 can be removed, and the camera load mounting plate 13 can be used for mounting external equipment such as a communication mounting antenna and the like, so that the requirements of special loads such as remote sensing, communication and the like are met in the design of the platform. When the remote sensing camera is designed, the camera mounting plate 21 provides a mounting position for the camera, also meets the integrated design concept, and provides a mounting position for the lens hood 17 of the camera. When there is no camera load, the camera mounting plate 21 becomes the top plate of the satellite platform, so that the satellite structure platform forms a closed structure space, and a mounting space is provided for related external satellite communication.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.