Modular panel stacked satellite mounted facing optical loads

Abstract

The invention provides a modular flat plate stacked satellite installed facing an optical load. The modular flat plate stacked satellite comprises a camera module, a flat satellite platform, a solar wing module and a stacking device module. The camera module comprises a camera module body and a telescopic light shield structure, and the camera module body is of a van type structure and internally comprises optical devices and electronic devices which form the camera module. The telescopic light shield is folded when being launched and extends out after the track, and a light blocking effect is provided for the camera module. The satellite platform is of a hexahedral flat plate structure, the platform mainly provides installation interfaces for the camera module, the solar wing module and the stacking device module, the single machine in the cabin is compactly arranged in the flat plate type satellite platform module, and the solar wing module is folded on the wide side face of the flat plate type satellite platform module when being launched. A plurality of satellites can be stacked together by adopting the stacking device module to form a stacked body, and the stacked body is launched by a carrier rocket.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of optical payload satellites, and in particular, to a modular flat stack satellite for optical payload installation. BACKGROUND

[0002] An optical payload is generally composed of an optical system, electronics, and a main structure, wherein the main structure generally includes a camera module support frame and a light shield, the camera module support frame is in the shape of a cube, and a relatively high light shield needs to be installed on the payload to prevent stray light from entering. The optical payload is high in height and large in volume.

[0003] Multi-satellite stacking launch is a flat and modular design of satellites. The satellites can be compactly stacked in the launch fairing like a flat plate. Through reasonable optimization design of the stacked satellites, compared with traditional van-type satellites, the carrying capacity and envelope can be maximally utilized. The stacked satellites are more suitable for flat antenna type payload installation, and the optical payload with large volume is difficult to apply to the stacked satellite platform.

[0004] The invention patent with publication number CN114692307A proposes a multi-satellite stacking mode, each layer containing four release units, each release unit including two single satellites of positive and negative satellites. A stacked structure and separation mode of a single-layer 8-satellite stack are proposed, which focuses on the connection and separation between satellites, and does not propose the configuration of optical stacking satellites.

[0005] The utility model patent with publication number CN213677217U proposes a satellite platform configuration of one rocket and two or more satellites, which overlaps two or more satellites on the launch docking base to enable the satellites to be stacked for launch. The proposed stacked satellite configuration focuses on satellite stacking launch and its device, which is not suitable for optical satellites and does not solve the problem of difficult accommodation and stacking of optical satellites.

[0006] The invention patent with publication number CN108137172A proposes a stacked spacecraft, which is mainly composed of a device carrying module, three columns, a locking device, and a reinforcing structure. It mainly solves the problem of communication satellite stacking and does not design for optical remote sensing satellite stacking and modularization.

[0007] The invention patent with publication number CN115196055A improves the adaptability of the fairing, but the stacking stability is insufficient, lacks applicability in complex space tasks, and does not involve the field of optical payload satellites.

[0008] In addition, the invention patent with publication number CN112558041A provides a spaceborne flat plate relay optical system, mainly including an optical assembly, a structural flat plate, a flexible support leg and an outer cover. It mainly compactly arranges the internal optical path and realizes flat plate, which is a flat plate design for an optical load, not a whole star flattening and modular design.

[0009] Although the invention patent with publication number CN119239991A proposes a stacked optical remote sensing satellite platform, mainly including a satellite main structure, two folding satellite solar wing modules and a stacked compression release device, its feature is to take the optical load as the center, the satellite structure surrounds the optical load to form a star body and adopts a circular flexible solar wing module, which does not modularize and flatten the satellite platform and the load, and does not have the scanning capability of the camera module. Only one layer of stacking can be performed, which cannot adapt to the installation of traditional square solar wing modules.

[0010] The traditional stacked satellite needs to flatten the overall configuration of the satellite, which is more suitable for installing flat plate antennas and other loads, while the optical load is generally composed of a sunshade and a body, which occupies a large volume, especially in the thickness direction, which is difficult to reduce, resulting in that the optical load is difficult to apply to the stacked satellite platform.

[0011] Therefore, it has important practical significance and application value to develop a modular flat stacked satellite for optical load installation which can effectively overcome the above-mentioned defects. SUMMARY

[0012] In view of the defects in the prior art, the purpose of the present application is to provide a modular flat stacked satellite for optical load installation.

[0013] The modular flat stacked satellite for optical load installation provided by the present application comprises a camera module 1, a flat plate satellite platform module 2, a solar wing module 3 and a stacking device module 4. The camera module 1 is the main load of optical remote sensing, which needs a long sunshade to ensure that the camera module 1 is not affected by stray light during on-orbit operation. The flat plate satellite platform module 2 is in a hexahedral flat plate configuration, which can provide installation interfaces for the camera module 1, the solar wing module 3 and the stacking device module 4, and the single machine in the cabin is compactly arranged in the flat plate satellite platform module 2. The solar wing module 3 is arranged in the flat plate satellite platform module 2. The stacking device module 4 is arranged in the flat plate satellite platform module 2, which provides an inter-satellite stacking interface.

[0014] Preferably, the camera module 1 comprises a camera module body 5 and a retractable sunshade 6. The camera module body 5 is a compartmental structure, containing optical devices and electronic devices that constitute the camera module; The telescopic sunshade 6 is retracted during launching and extended after being in orbit, providing light shielding for the camera module 1.

[0015] Preferably, multiple satellites can be stacked together by the stacking device module 4 to form a stack 7, which is launched together.

[0016] Preferably, when the flat satellite platform module 2 is equipped with the solar wing module 3, the height of the camera module body 5 is the same as the height of the flat satellite platform module 2.

[0017] Preferably, the thickness of the camera module body 5 satisfies the optical path arrangement, and the height of the camera module body 5 is the highest part of the whole satellite, which determines the total height of a single satellite.

[0018] Preferably, the stacking device module 4 can also provide a ground parking connection interface.

[0019] Preferably, the solar wing module 3 is retracted on the wider side of the flat satellite platform module 2 during launching and is expanded to the narrower side after being in orbit, ensuring that the solar wing module 3 does not block the field of view of the optical camera module and maximizing the reception of light.

[0020] Preferably, in addition to fixed connection, the camera module 1 and the flat satellite platform module 2 can also be connected by a rotatable mechanism 8, enabling the camera module 1 to have a large range of scanning capabilities in orbit.

[0021] Preferably, the telescopic sunshade 6 is expanded in orbit in a telescopic, foldable, or rotatable manner.

[0022] Preferably, the solar wing module 3 is a rigid solar cell array or a folding flexible solar array.

[0023] Compared with the prior art, the present application has the following beneficial effects: 1. The present application innovatively adopts a new flat stacking method, and the optical load adopts a telescopic sunshade, reducing the volume of the satellite during launching. At the same time, the size of the satellite platform is adaptively reduced to provide space for the installation of the camera module body and the solar wing module. The satellite has a flat appearance and a small volume during launching, and the telescopic sunshade and the solar wing module can be expanded after being in orbit to work normally. The camera module and the platform can also be equipped with a rotating device, enabling the camera module to have an in-orbit scanning function, solving the problem of the difficulty of applying optical load to a flat stacked satellite.

[0024] 2、The configuration of the present application combines telescopic sunshade, flat plate satellite platform module and stacked satellite technology, designs the total thickness of the stacked satellite as the height of the camera module body, performs telescopic design on the sunshade, reasonably arranges the positions of the satellite platform and the solar wing module, and stacks and launches after being folded into a flat plate, so that the problem of large volume of the optical remote sensing satellite load and difficult stacking and launching is solved. 3、Compared with the traditional optical satellite, the volume of the satellite when being folded is reduced, the remote sensing satellite is flattened, the satellite can be compactly stacked in the launch fairing like a flat plate, efficient stacking and launching of multiple satellites is facilitated, the carrying capacity and envelope can be maximally utilized. After being launched into the orbit, the sunshade is extended and the solar wing module is unfolded, so that the function of the satellite in the orbit is not affected.

[0025] 4、The present application solves the problems of large volume of the traditional optical load and large space occupied by the sunshade, reduces the volume of the remote sensing satellite when being folded under the premise of ensuring the same function as the traditional satellite in the orbit, realizes stacking and launching of multiple remote sensing satellites by one rocket, facilitates rapid deployment of multiple satellites on the same orbit, and maximally utilizes the carrying capacity and the fairing envelope. BRIEF DESCRIPTION OF DRAWINGS

[0026] Other features, objects and advantages of the present application will become more apparent from the following detailed description of non-limiting embodiments with reference to the attached drawings: Figure 1 It is a schematic diagram of the unfolded structure of the modular flat stacked satellite for optical load installation of the present application; Figure 2 It is a schematic diagram of the folded structure of the modular flat stacked satellite for optical load installation of the present application; Figure 3 It is a schematic diagram of the camera module scanning of the modular flat stacked satellite for optical load installation of the present application; Figure 4 It is a schematic diagram of the placement structure of two satellites of the modular flat stacked satellite for optical load installation of the present application in the fairing; Figure 5 It is a schematic diagram of the stacked body of the modular flat stacked satellite for optical load installation of the present application.

[0027] The drawings show: DETAILED DESCRIPTION

[0028] The present application will be described in detail below with reference to specific embodiments. The following embodiments will help those skilled in the art to further understand the present application, but do not limit the present application in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present application. These all belong to the protection scope of the present application.

[0029] The embodiment of the present application provides a modular flat stack satellite for optical load installation, as shown in the figure, comprising a camera module 1, a flat satellite platform module 2, a solar wing module 3 and a stacking device module 4. The configuration combines telescopic sunshields, flat satellite platform modules and stacking satellite technologies, and converts optical satellites which are difficult to launch by stacking into satellites which can be launched by stacking. The present application is mainly suitable for the stacking launch of optical load satellites. The carrier mentioned herein refers to a carrier rocket. Figure 1

[0030] Further, the camera module 1 is the main load of optical remote sensing, and is characterized in that a long sunshield is needed to ensure that the camera module 1 is not affected by stray light during on-orbit operation. The camera module 1 mainly comprises a camera module body 5 and telescopic sunshields 6. The camera module body 5 is a van structure and contains optical devices, electronic devices and the like which constitute the camera module.

[0031] As shown in the figure, the telescopic sunshields 6 are retracted during launch and are extended after on-orbit operation, thereby providing light-blocking for the camera module 1. Figure 1 Figure 2 As shown in the figure, the flat satellite platform module 2 is in a hexahedral flat configuration, mainly provides mounting interfaces for the camera module 1, the solar wing module 3 and the stacking device module 4, and the compact layout of single machines in the cabin is in the flat satellite platform module 2.

[0032] As shown in the figure, the flat satellite platform module 2 is in a hexahedral flat configuration, mainly provides mounting interfaces for the camera module 1, the solar wing module 3 and the stacking device module 4, and the compact layout of single machines in the cabin is in the flat satellite platform module 2. Figure 2 Further, the solar wing module 3 is retracted on the wider side of the flat satellite platform module 2 during launch, and is extended to the two narrower sides of the flat satellite platform module 2 after on-orbit operation, thereby ensuring that the solar wing module 3 does not block the field of view of the optical camera module and maximizes the reception of light. The solar wing module 3 is a rigid solar cell array or a folding flexible solar array.

[0033] Further, the stacking device module 4 provides an intersatellite interface, so that the satellites can be stacked together for launch and maximize the use of the carrying capacity of the carrier. The stacking device module 4 can also provide a connection interface with a ground parking.

[0034] As shown in the figure, multiple satellites can be stacked together by the stacking device module 4 to form a stack 7 and be launched together by a carrier. This launch mode can improve the use efficiency of the carrier.

[0035] Figure 5 As shown in the figure, in addition to fixed connection, a rotatable mechanism 8 can also be used to connect the camera module 1 and the flat satellite platform module 2, so that the camera module 1 has the capability of large-range scanning on orbit.

[0036] As shown in the figure, in addition to fixed connection, a rotatable mechanism 8 can also be used to connect the camera module 1 and the flat satellite platform module 2, so that the camera module 1 has the capability of large-range scanning on orbit. Figure 3 As shown in the figure, in addition to fixed connection, a rotatable mechanism 8 can also be used to connect the camera module 1 and the flat satellite platform module 2, so that the camera module 1 has the capability of large-range scanning on orbit.

[0037] As​​​Figure 2 As shown, the thickness of the flat satellite platform module 2 is thin, providing sufficient height for the installation of the solar wing module 3, and after the flat satellite platform module 2 is installed with the solar wing module 3, the height of the flat satellite platform module 2 is the same as the height of the camera module body 5.

[0038] Further, the thickness of the camera module body 5 needs to meet the light path arrangement, and the height of the camera module body 5 is the highest part of the whole satellite, which determines the total height of the single satellite.

[0039] Further, the telescopic light shield 6 can be deployed on orbit in various ways such as telescopic, folding, rotating, etc.

[0040] The modular flat stacking satellite provided by the application is for the installation of an optical load, the platform and the camera module of the flat satellite are designed to be flat and modular, the volume occupied by the satellite platform is reduced, and space is left for the installation of the camera module body and the solar wing module. Meanwhile, the telescopic light shield design is adopted, and the camera module has a small volume during launching. Compared with the traditional optical satellite, the volume of the satellite is reduced when the satellite is retracted, the remote sensing satellite is flat, and the satellite can be stacked in the launch fairing like a flat plate, which facilitates the efficient stacking and launching of multiple satellites, and the carrying capacity and the fairing envelope are maximized. After the satellite is on orbit, the light shield is extended, and the solar wing module is unfolded, which does not affect the on-orbit working function of the satellite. The rotating device can be installed between the camera module and the platform, so that the camera module has an on-orbit scanning function.

[0041] The application solves the problems of large volume of the traditional optical load and large space occupied by the light shield, reduces the volume of the remote sensing satellite when the satellite is retracted, realizes the stacking and launching of multiple satellites in the same batch, facilitates the rapid deployment of multiple satellites on the same orbit, and maximizes the utilization of the carrying capacity and the fairing envelope.

[0042] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0043] The specific embodiments of the present application are described above. It should be understood that the present application is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be arbitrarily combined without conflict.

Claims

1. A modular flat panel stacked satellite oriented towards optical payload installation, characterized by, The application relates to a satellite system, which comprises a camera module (1), a flat satellite platform module (2), a solar wing module (3) and a stacking device module (4). The camera module (1) is the main load of optical remote sensing, and a long light shield is required during on-orbit operation to ensure that the camera module (1) is not affected by stray light. The flat satellite platform module (2) is in a hexahedral flat plate configuration, can provide mounting interfaces of the camera module (1), the solar wing module (3) and the stacking device module (4), and can compactly arrange single machines in the flat satellite platform module (2). The solar wing module (3) is arranged on the flat satellite platform module (2). The stacking device module (4) is arranged on the flat satellite platform module (2) and provides an intersatellite stacking interface. The camera module (1) comprises a camera module body (5) and a retractable light shield (6).

2. The modularized platform stacking satellite facing optical payload installation according to claim 1, characterized in that, The camera module body (5) is in a compartment structure and contains optical devices and electronic devices of the camera module. The retractable light shield (6) is retracted during launching and is extended after on-orbit operation, thereby providing a light blocking effect for the camera module (1). Multiple satellites can be stacked together by the stacking device module (4) to form a stack (7) and are launched together.

3. The modularized planar stack satellite facing optical payload installation according to claim 1, characterized in that, After the flat satellite platform module (2) is arranged with the solar wing module (3), the height of the camera module body (5) is the same as that of the flat satellite platform module (2).

4. The modularized planar stack satellite facing optical payload installation according to claim 2, characterized in that, The thickness of the camera module body (5) satisfies the light path arrangement, the height of the camera module body (5) is the highest part of the whole satellite, and determines the total height of the single satellite.

5. The modularized planar stack satellite facing optical payload installation according to claim 2, characterized by, The stacking device module (4) can also provide a ground parking connection interface.

6. The optical payload-mtstalled modular piaie stack satellite of claim 1, wherein, The solar wing module (3) is retracted on the wider side of the flat satellite platform module (2) during launching and is unfolded on the narrower side after on-orbit operation, thereby ensuring that the solar wing module (3) does not block the field of view of the optical camera module and maximizes the reception of light.

7. The modularized planar stack satellite facing optical payload installation according to claim 1, characterized by, In addition to the fixed connection between the camera module (1) and the flat satellite platform module (2), a rotatable mechanism (8) can also be used to connect the camera module (1), so that the camera module (1) has the capability of large-range scanning on orbit.

8. The modularized planar stack satellite facing optical payload installation according to claim 1, characterized by, The retractable light shield (6) is unfolded on orbit in the way of stretching, folding or rotating.

9. The optical payload-mtstalled modular piaie stack satellite of claim 2, wherein, The solar wing module (3) is a rigid solar cell array or a folding flexible solar array.

10. The modularized planar stack satellite facing optical payload installation according to claim 1, characterized by, ​

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