CN218806627U - Expandable and modular platform and load structure integrated satellite device - Google Patents

Abstract

The utility model discloses an extensible and modularized platform and load structure integrated satellite device, which integrates the satellite structure and the camera load, effectively improving the compactness of the satellite structure; the satellite structure load integrated design is adopted, so that the satellite emission envelope size is reduced, the overall weight of the satellite is reduced, and the emission cost of the satellite is saved; the satellite bottom and the top are respectively provided with a satellite-rocket separation point and an inter-satellite separation point, so that stacked launching can be performed, and one-rocket multi-satellite stacked launching is facilitated under the condition of limited carrying space; the solar cell array and the phased array antenna structure are in modular design, so that the solar cell array and the phased array module can be increased or decreased according to satellite power and user requirements; the module units of the solar cell array can be connected through the hinges, and module expansion splicing which meets various application requirements and configuration requirements is achieved.

Description

Expandable and modular platform and load structure integrated satellite device

Technical Field

The utility model relates to a space flight vehicle technical field specifically is an it is expanded, modularization platform and load structure integration satellite device.

Background

In recent years, with the increasing competition of space resources, companies such as OneWeb, amazon, telesat, spaceX, boeing and the like have proposed low-orbit communication satellite constellation plans. Research on small satellites and application technologies thereof is actively carried out in China, and particularly, national internet satellite constellations can be rapidly deployed in the coming years. With the continuous improvement of satellite manufacturing technology, the demand of satellites with high precision, high agility and low cost is increasingly strong. The platform and load integrated design is one of important directions for the development of satellites with high precision, high agility and low cost in the future, and the platform and load integrated configuration design is an important direction and a key technology for the development of satellites.

At present, the development of a satellite is vigorously transformed towards a direction with higher use efficiency, the requirements of the satellite for improving performance indexes and increasing load scale are more and more urgent, in a traditional development mode, a platform and a load are designed on the basis of an interface in a configuration layout, the coupling degree of professional in-situ analysis such as severe mechanical environment resistance, in-orbit slight vibration resistance, in-orbit photothermal analysis and the like of an emission section is not deep, but with the increase of the whole satellite and the load scale, a more refined and simplified design method must be sought for supporting the satellite, and particularly the overall development of a remote sensing satellite.

Therefore, it is desirable to design an integrated satellite device with a scalable, modular platform and load structure that is highly practical.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an it can expand, modularization platform and load structure integration satellite device to solve the problem that provides among the above-mentioned background art.

In order to solve the technical problem, the utility model provides a following technical scheme:

the utility model provides an expanded, modularization platform and load structure integration satellite device, includes satellite main structure, camera load and solar cell array, satellite main structure Z axle direction is equipped with the camera load, solar cell array fixed mounting is in the four corners of one of them mesa of satellite main structure, the solar cell array is extending structure, fixed mounting has integrated form to synthesize automatically controlled board and lithium cell array in the satellite main structure, another mesa of satellite main structure and the equal fixed mounting in non-light-facing side of solar cell array have phased array antenna.

According to the technical scheme, the two ends of the camera load are respectively and fixedly provided with the inter-satellite separation ring and the satellite-arrow separation ring.

According to the technical scheme, the camera load is located in the middle of the satellite main structure, the camera load is of a two-part combined structure, and the front two parts are integrally formed through two deck plates of the satellite main structure respectively.

According to the technical scheme, the solar cell array is of a rotary folding structure.

According to the technical scheme, the camera load on the side of the solar cell array protrudes out of the surface of the satellite main structure, and the protruding height of the camera load is higher than the folding height of the solar cell array in a folding mode.

According to the technical scheme, the camera load on the phased array antenna side protrudes out of the surface of the satellite main structure, and the protruding height of the camera load is higher than the thickness of the phased array antenna.

According to the technical scheme, the area of the single piece of the solar cell array is one ninth of the area of the table top of the satellite main structure, and the shape of the single piece of the solar cell array is similar to the shape of the table top of the satellite main structure in an equal ratio.

Compared with the prior art, the utility model discloses the beneficial effect who reaches is:

1. the satellite device is designed to integrally design the satellite structure and the camera load, so that the compactness of the satellite structure is effectively improved;

2. the device adopts the integrated design of the satellite structure load, reduces the size of the satellite emission envelope, reduces the total weight of the satellite and saves the emission cost of the satellite;

3. the satellite device is designed to be provided with a satellite-rocket separation point and an inter-satellite separation point at the bottom and the top of the satellite respectively, so that stacked launching can be carried out, and one-rocket multi-satellite stacked launching is facilitated under the condition of a limited carrying space;

4. the solar cell array and the phased array antenna structure are designed in a modular mode, and the number of solar cell arrays and phased array modules can be increased or decreased according to satellite power and user requirements;

5. the module units of the solar cell array designed in the device can be connected through the hinge, and the module expansion splicing which meets various application requirements and configuration requirements is realized.

Drawings

The accompanying drawings are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention, and together with the description serve to explain the invention and not to limit the invention. In the drawings:

fig. 1 is a schematic perspective view of the first state of the present invention;

fig. 2 is a schematic diagram of a first-view perspective structure of the on-orbit state of the present invention;

fig. 3 is a schematic diagram of a second perspective three-dimensional structure in an on-orbit state of the present invention;

fig. 4 is a schematic view of the solar cell array of the present invention in the direction of expansion.

In the figure: 1. the system comprises a satellite main structure, 2 camera loads, 3 solar cell arrays, 4 integrated comprehensive electric control boards, 5 lithium batteries, 6 inter-satellite separation rings, 7 satellite and rocket separation rings and 8 phased array antennas.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-4, the present invention provides a technical solution: the utility model provides an expanded, modularization platform and load structure integration satellite device, includes satellite main structure 1, camera load 2 and solar cell array 3, satellite main structure 1Z axle direction is equipped with camera load 2, solar cell array 3 fixed mounting is in the four corners of one of the mesa of satellite main structure 1, solar cell array 3 is extending structure, fixed mounting has integrated form to synthesize automatically controlled board 4 and lithium cell 5 array in satellite main structure 1, the equal fixed mounting in non-light-facing side of another mesa of satellite main structure 1 and solar cell array 3 has phased array antenna 8.

Satellite main structure 1 adopts many aviation aluminum alloy preparation, constructs the space framework, makes things convenient for the installation of inside lithium cell 5 and the automatically controlled board 4 of integrated form synthesis, and camera load 2 provides the basis for the installation of camera, and solar cell array 3 is through the functional of self, for lithium cell 5 charges and for whole star work provides the electric energy, automatically controlled board 4 is synthesized to the integrated form and is integrated the preparation according to the functional requirement, lithium cell 5 stores the surplus electric energy that solar cell array 3 produced, realizes stand-by power supply.

Specifically, an inter-satellite separation ring 6 and a satellite and rocket separation ring 7 are fixedly mounted at two ends of the camera load 2 respectively.

Through the intersatellite separating rings 6 fixedly installed at the two ends of the camera load 2, satellites launched by a plurality of stacked satellites can be separated, and the satellite and rocket separating rings 7 can effectively separate the satellites from the rockets.

Specifically, the camera load 2 is located in the middle of the satellite main structure 1, the camera load 2 is a two-part combined structure, and the two front parts are integrally formed through two deck plates of the satellite main structure 1 respectively.

Lie in the middle part of satellite main structure 1 through camera load 2 for holistic gravity balance is more stable, and through integrated configuration, makes things convenient for holistic equipment more, and integrated into one piece structure has increased stability.

Specifically, the solar cell array 3 has a rotary folding structure.

Through gyration structure of buckling, can be better spread whole light-facing side.

Specifically, the camera load 2 on the solar cell array 3 side protrudes out of the surface of the satellite main structure 1, and the protruding height is higher than the folding height of the solar cell array 3.

The solar cell array 3 can be protected when the satellites are stacked by the projection of the camera load 2.

Specifically, the camera load 2 on the phased array antenna 8 side protrudes from the surface of the satellite main structure 1, and the protruding height is higher than the thickness of the phased array antenna 8.

The spatial distance control when the phased array antenna 8 is installed is achieved by the protrusion of the camera load 2, and then protection is achieved.

Specifically, the single-chip area of the solar cell array 3 is one ninth of the mesa area of the satellite main structure 1, and the single-chip shape of the solar cell array 3 is similar to the mesa shape of the satellite main structure 1 in an equal ratio.

Through the arrangement similar to the equal ratio, the satellite main structure 1 can be better matched in the folding and unfolding processes.

The working principle is as follows: when the solar energy satellite main structure is used, a satellite body is connected with a rocket through the satellite and rocket separating ring 7, the satellite body is connected through the inter-satellite separating ring 6, when the satellite enters a preset orbit, the satellite body is separated independently through the satellite and rocket separating ring 7 and the inter-satellite separating ring 6, after the satellite enters the orbit, the satellite main structure 1 is subjected to posture adjustment, the solar cell array 3 is unfolded until the light-facing surface of the solar cell array 3 faces the sun, and the phased array antenna 8 is located at a proper signal receiving position.

It should be noted that, in this document, relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described above, or equivalents may be substituted for elements thereof. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (7)

1. The utility model provides an expanded, modularization platform and load structure integration satellite device, includes satellite main structure (1), camera load (2) and solar cell array (3), its characterized in that: the solar energy satellite main structure comprises a satellite main structure (1) and is characterized in that a camera load (2) is arranged in the Z-axis direction of the satellite main structure (1), a solar cell array (3) is fixedly arranged at four corners of one table-board of the satellite main structure (1), the solar cell array (3) is of an extensible structure, an integrated electric control board (4) and a lithium battery (5) array are fixedly arranged in the satellite main structure (1), and a phased array antenna (8) is fixedly arranged on the other table-board of the satellite main structure (1) and a non-light-facing surface of the solar cell array (3) array.

2. The integrated expandable, modular platform and payload structure satellite device of claim 1, wherein: and an inter-satellite separation ring (6) and a satellite-rocket separation ring (7) are respectively and fixedly mounted at two ends of the camera load (2).

3. The integrated expandable, modular platform and payload structure satellite device of claim 1, wherein: the camera load (2) is located in the middle of the satellite main structure (1), the camera load (2) is of a two-part combined structure, and the front two parts are integrally formed through two deck plates of the satellite main structure (1) respectively.

4. An expandable, modular platform and load structure integrated satellite device according to claim 1, wherein: the solar cell array (3) is of a rotary folding structure.

5. The integrated expandable, modular platform and payload structure satellite device of claim 1, wherein: the camera load (2) on the side of the solar cell array (3) protrudes out of the surface of the satellite main structure (1), and the protruding height is higher than the folding height of the solar cell array (3) in a folding mode.

6. The integrated expandable, modular platform and payload structure satellite device of claim 1, wherein: the camera load (2) on the phased array antenna (8) side protrudes out of the surface of the satellite main structure (1), and the protruding height is higher than the thickness of the phased array antenna (8).

7. The integrated expandable, modular platform and payload structure satellite device of claim 1, wherein: the single-chip area of the solar cell array (3) is one ninth of the table-board area of the satellite main structure (1), and the single-chip shape of the solar cell array (3) is similar to the table-board shape of the satellite main structure (1) in an equal ratio.

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