Large-aperture optical satellite configuration suitable for rapid maneuvering

Abstract

The invention provides a satellite configuration suitable for configuring a large-aperture optical camera and needing on-orbit rapid maneuvering. The satellite configuration comprises a service module, a load module, a camera light shield, a two-module locking mechanism and a solar cell array. The service module adopts an outer hexagonal and inner hollow structure, and the outer hexagon fully utilizes the available envelope of the carrying fairing to provide a larger installation space for the whole satellite, so that the height of the service module is reduced, and the overall center of mass of the satellite is reduced; the inner circular hollow part provides an installation space for the camera secondary mirror support cylinder and the camera light shield. The load cabin is located below the service cabin when the satellite is vertically parked, and the camera secondary mirror supporting cylinder penetrates through the service cabin and provides an installation interface for the carrying separation device. The two-cabin locking mechanism provides mechanical support for the service cabin. The solar cell arrays are symmetrically arranged on the two sides of the service module. The problem that the inertia of the whole satellite is too large is solved, the requirement for in-orbit rapid maneuvering of the large-aperture optical satellite is met, and the method has the advantage that the mechanical environment and the space thermal environment of the load active section are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft structure design, and in particular to a large-aperture optical satellite configuration suitable for rapid maneuvering. Background Art

[0002] In today's aerospace field, the performance requirements for satellites are increasing. Large-aperture optical satellites play an important role in fields such as earth observation and astronomical observation. However, the traditional large-aperture optical satellite configuration has many limitations in terms of maneuverability.

[0003] In the past, the design of large-aperture optical satellites often focused on optimizing optical performance while ignoring maneuverability. This makes the satellite react slowly when responding to sudden tasks or when it needs to quickly adjust the observation target. At present, the payload cabin and service cabin of large-aperture optical satellites are mostly connected in parallel, with the payload cabin located above the service cabin and the solar array spread out in a straight line away from the satellite. However, this common configuration has obvious disadvantages: (1) The satellite mass is dispersed and the inertia of the entire satellite is large, resulting in a high cost for rapid maneuvers of the entire satellite. (2) The payload is located above the satellite, and the mechanical environment in the active phase is poor. (3) After the satellite enters orbit, the payload is completely in the space environment, and the thermal environment is poor.

[0004] In summary, in order to meet the requirements of rapid on-orbit maneuverability of large-aperture optical satellites and improve the mechanical environment of the active segment of optical payloads and the on-orbit space environment, there is an urgent need for a satellite configuration that can both ensure large-aperture optical performance and have rapid maneuverability. Summary of the invention

[0005] In view of the defects in the prior art, the purpose of the present invention is to provide a satellite configuration that meets the requirements of rapid on-orbit maneuvers of large-aperture optical satellites, while improving the mechanical environment of the active segment of the optical payload and the on-orbit space environment.

[0006] The present invention provides a large-aperture optical satellite configuration suitable for rapid maneuvering, comprising:

[0007] A service module, a camera sunshade, a two-module locking mechanism, a payload module and multiple solar arrays; the service module is a structure that is hollow inside and open at both ends; the camera sunshade is fixed to the top of the service module to provide an on-orbit space environment for the large-aperture optical camera; the payload module is located below the service module and is fixedly connected to the service module through a two-module locking mechanism, and the payload module is used to load the large-aperture optical camera; the solar array is arranged on the side of the service module.

[0008] Preferably, the outer side of the service module is a hexagonal structure.

[0009] Preferably, the inner side of the service cabin is a circular through hole.

[0010] Preferably, a top plate is provided on the top of the service cabin, and the top plate is provided with a middle hole corresponding to the circular through hole of the service cabin.

[0011] Preferably, the camera hood is a hollow cylindrical structure, the lower end surface of the camera hood is connected to the front surface of the top plate, and the hollow position of the camera hood corresponds to the position of the center hole of the top plate.

[0012] Preferably, a load base plate is provided at the bottom of the load cabin, a two-cabin locking mechanism is mounted on the load base plate, and a large-aperture optical camera is mounted on the load base plate.

[0013] Preferably, a camera secondary mirror support tube is provided on the payload cabin, the lower end of the camera secondary mirror support tube is connected to the payload base plate, and the upper end passes through the circular through hole in the service cabin and extends into the interior of the camera hood.

[0014] Preferably, a portion of the camera secondary mirror support tube is located inside the service cabin, and a portion of the support tube is located inside the camera sunshade.

[0015] Preferably, the diameter of the circular through hole of the service cabin is appropriately larger than the diameter of the camera secondary mirror supporting tube.

[0016] Preferably, the solar cell array includes three substrates, the number of the solar cell arrays is 2, and the two solar cell arrays are symmetrically arranged on both sides of the service module.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] 1. The outer side of the service module of the present invention adopts a hexagonal structure, which fully utilizes the effective envelope of the carrier fairing and meets the layout requirements of the service module while a large-aperture optical camera passes through the service module.

[0019] 2. The payload module of the present invention is located below the service module, the camera secondary mirror support tube passes through the circular through hole of the service module, and the solar cell array installed on the side of the service module is spread out in a line along the optical axis direction of the large-aperture optical camera in orbit, so as to achieve the purpose of centralized satellite mass distribution and reduce the center of mass and inertia of the entire satellite, thereby realizing rapid maneuvering in orbit.

[0020] 3. The payload cabin of the present invention is located at the lower side of the service cabin, providing a good mechanical environment for the active section of the large-aperture optical camera.

[0021] 4. The camera secondary mirror support tube of the present invention passes through the service module, and the camera light shield is arranged on the front of the top plate of the service module, which provides a good on-orbit thermal environment for the large-aperture optical camera. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0023] Figure 1 An exploded diagram of a large-aperture optical satellite configuration suitable for rapid maneuvering in an embodiment of the present invention;

[0024] Figure 2 This is a schematic diagram of the structure of a large-aperture optical satellite suitable for rapid maneuvering in an embodiment of the present invention;

[0025] Figure 3 The diagram is a schematic diagram of the in-orbit flight appearance of a large-aperture optical satellite suitable for rapid maneuvers in an embodiment of the present invention. DETAILED DESCRIPTION

[0026] The present invention provides a satellite configuration suitable for configuring a large-aperture optical camera and requiring rapid on-orbit maneuvers, including a service module, a payload module, a camera sunshade, a two-module locking mechanism, and a solar cell array. The service module adopts an outer hexagonal and inner hollow configuration. The outer hexagon fully utilizes the available envelope of the carrier fairing to provide a larger installation space for the entire satellite, thereby reducing the height of the service module and the overall center of mass of the satellite; the inner circular hollow provides installation space for the camera secondary mirror support tube and the camera sunshade. The payload module is located below the service module when the satellite is parked vertically. The camera secondary mirror support tube runs through the service module and provides an installation interface with the carrier separation device. The two-module locking mechanism is arranged between the service module and the payload module to provide mechanical support for the service module. The solar cell array is symmetrically arranged on both sides of the service module. The present invention solves the problem of excessive inertia of the entire satellite, meets the needs of rapid on-orbit maneuvers of large-aperture optical satellites, and has the characteristics of improving the mechanical environment of the active section of the payload and the thermal environment of space.

[0027] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0028] Figure 1 This is an exploded diagram of a large-aperture optical satellite configuration suitable for rapid maneuvering in an embodiment of the present invention. Figure 2 The figure is a schematic diagram of the structure of a large-aperture optical satellite suitable for rapid maneuvering in an embodiment of the present invention.

[0029] like Figure 1 , 2 As shown, an embodiment of the present invention provides a large-aperture optical satellite configuration suitable for rapid maneuvers, including a service module 10 , a camera sunshade 20 , a two-module locking mechanism 30 , a payload module 40 and a plurality of solar cell arrays 50 .

[0030] The service cabin 10 is a structure with a hollow interior and openings at both ends.

[0031] In this embodiment, the outer side of the service module 10 is a hexagonal structure, which fully utilizes the space of the carrier fairing. The inner side of the service module 10 is a circular through hole. The top of the service module 10 is provided with a top plate 11, and the top plate 11 is provided with a middle hole corresponding to the circular through hole of the service module 10.

[0032] The camera sunshade 20 is fixed on the top of the service module 10 to provide an on-orbit space environment for the large-aperture optical camera 60 .

[0033] In this embodiment, the camera hood 20 is a hollow cylindrical structure, the lower end surface of the camera hood 20 is connected to the front surface of the top plate 11, and the hollow position of the camera hood 20 corresponds to the position of the center hole of the top plate 11.

[0034] Preferably, the diameter of the hollow of the camera lens hood 20 is greater than the diameter of the central hole of the top plate 11 .

[0035] The payload cabin 40 is located below the service cabin 10 and is fixedly connected to the service cabin 10 via a two-cabin locking mechanism 30 . The payload cabin 40 is used to load a large-aperture optical camera 60 .

[0036] In this embodiment, a load base plate 41 is provided at the bottom of the load cabin 40, the two-cabin locking mechanism 30 is installed on the load base plate 41, and the large-caliber optical camera 60 is installed on the load base plate 41. A camera secondary mirror support tube 42 is provided on the load cabin 40, the lower end of the camera secondary mirror support tube 42 is connected to the load base plate 41, and the upper end of the camera secondary mirror support tube 42 passes through the circular through hole in the service cabin 10 and extends into the interior of the camera light shield 20. A portion of the camera secondary mirror support tube 42 is located inside the service cabin 10, and a portion is located inside the camera light shield 20. The diameter of the circular through hole of the service cabin 10 is appropriately larger than the diameter of the camera secondary mirror support tube 42.

[0037] The solar cell array 50 includes three substrates and is disposed on the side of the service module 10 .

[0038] In this embodiment, the number of the solar cell arrays 50 is two, and the two solar cell arrays 50 are symmetrically arranged on both sides of the service module 10, and the solar cell arrays 50 are spread out in a line along the optical axis direction of the large-aperture optical camera 60 on the track.

[0039] Figure 3 The diagram is a schematic diagram of the in-orbit flight appearance of a large-aperture optical satellite suitable for rapid maneuvers in an embodiment of the present invention.

[0040] like Figure 3As shown, the working principle characteristics of the present invention are as follows: the large-aperture optical satellite of the present invention is configured in a hexagonal configuration, the large-aperture optical camera 60 and the camera secondary mirror support tube 42 are installed on the payload cabin 40, the service cabin 10 passes through the camera secondary mirror support tube 42, and is reliably connected to the payload cabin 40 through the two-cabin locking mechanism 30; after the two cabins are assembled, the camera sunshade 20 is installed on the front of the top plate of the service cabin 10, and after entering orbit, the solar cell array 50 is unfolded in a straight line along the optical axis direction of the large-aperture optical camera 60, further reducing the inertia of the entire satellite.

[0041] This embodiment solves the problem of rapid maneuvering of large-aperture optical satellites, and has the characteristics of low center of mass of the whole satellite, small moment of inertia, excellent mechanical environment of the active segment, and good on-orbit space environment, thereby meeting the needs of rapid on-orbit maneuvering of large-aperture optical imaging satellites.

[0042] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0043] The above describes the specific embodiments of the present invention. It should be understood that the present invention 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 essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A large-aperture optical satellite configuration suitable for rapid maneuvering, characterized in that: It includes a service module, a camera sunshade, a two-module locking mechanism, a payload module, and multiple solar arrays; The service cabin is a structure that is hollow inside and open at both ends; The camera sunshade is fixed on the top of the service module and is used to provide an on-orbit space environment for the large-aperture optical camera; The payload cabin is located below the service cabin and is fixedly connected to the service cabin through the two-cabin locking mechanism. The payload cabin is used to load the large-aperture optical camera. The solar cell array is arranged on the side of the service module.

2. The large-aperture optical satellite configuration suitable for rapid maneuvering according to claim 1, characterized in that: The outer side of the service module is a hexagonal structure.

3. The large-aperture optical satellite configuration suitable for rapid maneuvering according to claim 1, characterized in that: The inner side of the service cabin is a circular through hole.

4. The large-aperture optical satellite configuration suitable for rapid maneuvering according to claim 3 is characterized in that: A top plate is provided on the top of the service cabin, and a middle hole corresponding to the circular through hole of the service cabin is provided on the top plate.

5. The large-aperture optical satellite configuration suitable for rapid maneuvering according to claim 4, characterized in that: The camera hood is a hollow cylindrical structure, the lower end surface of the camera hood is connected to the front surface of the top plate, and the hollow position of the camera hood corresponds to the position of the center hole of the top plate.

6. The large-aperture optical satellite configuration suitable for rapid maneuvering according to claim 5, characterized in that: A load base plate is provided at the bottom of the load cabin, the two-cabin locking mechanism is mounted on the load base plate, and the large-aperture optical camera is mounted on the load base plate.

7. The large-aperture optical satellite configuration suitable for rapid maneuvering according to claim 6, characterized in that: A camera secondary mirror support tube is provided on the load cabin, the lower end of the camera secondary mirror support tube is connected to the load base plate, and the upper end passes through the circular through hole in the service cabin and extends into the interior of the camera sunshade.

8. The large-aperture optical satellite configuration suitable for rapid maneuvering according to claim 7, characterized in that: A portion of the camera secondary mirror support tube is located inside the service cabin, and a portion of the camera secondary mirror support tube is located inside the camera light shield.

9. The large-aperture optical satellite configuration suitable for rapid maneuvering according to claim 7, characterized in that: The diameter of the circular through hole of the service cabin is appropriately larger than the diameter of the camera secondary mirror support tube.

10. The large-aperture optical satellite configuration suitable for rapid maneuvering according to claim 1, characterized in that: The solar cell array includes three substrates. The number of the solar cell arrays is 2, and the two solar cell arrays are symmetrically arranged on both sides of the service module.

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