CN219215388U - Optical remote sensing satellite with side-hanging type configuration - Google Patents
Optical remote sensing satellite with side-hanging type configuration Download PDFInfo
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- CN219215388U CN219215388U CN202223093008.6U CN202223093008U CN219215388U CN 219215388 U CN219215388 U CN 219215388U CN 202223093008 U CN202223093008 U CN 202223093008U CN 219215388 U CN219215388 U CN 219215388U
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Abstract
The utility model relates to an optical remote sensing satellite with a side-hung type structure, which comprises a satellite box body, a satellite sailboard and a remote sensing camera, wherein a left side plate and a right side plate of the satellite box body are of a first right-angle trapezoid structure, the lower ends of a front plate and a rear plate are respectively and vertically fixed on the front side edge and the rear side edge of a bottom plate, right-angle waists of the left side plate and the right side plate are respectively and vertically fixed on the left side edge and the right side edge of the bottom plate, the left side edge and the right side edge of the front plate are respectively and fixedly connected with the left side plate and the right side plate, and the left side edge and the right side edge of the rear plate are respectively and fixedly connected with the left side plate and the right side plate; the front side of the top plate is fixed at the top end of the front plate, the top plate is arranged in parallel with the bottom plate, the rear side of the top plate is fixedly connected with the rear plate, and the left side and the right side of the top plate are respectively fixedly connected with the left side plate and the right side plate; the front side surface of the rear plate is also fixed with a reinforcing plate which is horizontally arranged; the remote sensing camera is fixed on the outer surface of the top plate, and satellite sailboards are respectively hinged on the outer surfaces of the left side plate and the right side plate; the rear side of the rear plate is provided with a plurality of hanging structures.
Description
Technical Field
The utility model relates to the technical field of aerospace, in particular to an optical remote sensing satellite with a side-hung configuration.
Background
The optical remote sensing load needs to be installed on the ground of the satellite, and along with the higher and higher requirements on the observation precision, the scale of the load is larger and larger, the weight is heavier and heavier, and higher adaptability requirements are provided for the configuration of the existing small satellite.
High resolution remote sensing satellites generally need to be equipped with high resolution cameras, high torque Control Moment Gyroscopes (CMGs) or high torque momentum wheels, and the overall volume and weight of the satellite are relatively large. At present, a common small satellite platform mostly adopts a pure plate type structure, a structural plate usually adopts a honeycomb and aluminum skin composite material structure, and platform equipment is generally arranged on a partition plate and a side plate of the satellite.
Under the general condition, the bottom of the remote sensing satellite is in butt joint with the carrier in a standard bag strap and butt joint ring mode, but along with the increasing of the emission quantity of the remote sensing satellite, in order to meet the emission requirement of one arrow with multiple satellites, the installation mode of satellite side hanging is also applied to the optical remote sensing satellite at present, and the optical remote sensing satellite has the advantages of high arrangement density and capability of meeting the arrangement requirement of one arrow with multiple satellites.
Disclosure of Invention
The utility model provides an optical remote sensing satellite with a side-hung configuration for meeting the emission requirement of multiple satellites of one arrow, and has the advantages of light weight, compact structure and strong applicability.
The technical scheme for solving the technical problems is as follows: the utility model provides an optical remote sensing satellite of side-hung type configuration, includes satellite box, satellite sailboard and remote sensing camera, the satellite box includes roof, bottom plate, front bezel, back plate, left side board and right side board all are first right trapezoid structure, the lower extreme of front bezel and back plate is perpendicular to be fixed respectively the front side and the rear side of bottom plate, the right angle waist of left side board and right side board is perpendicular to be fixed the left side and the right side of bottom plate, the left and right sides limit of front bezel respectively with left side board and right side board fixed connection, the left and right sides limit of back plate respectively with left side board and right side board fixed connection, the height of back plate with the lower base length of first right trapezoid structure is the same; the front side edge of the top plate is fixed at the top end of the front plate, the top plate is arranged in parallel with the bottom plate, the rear side edge of the top plate is fixedly connected with the rear plate, and the left side edge and the right side edge of the top plate are respectively and fixedly connected with the left side plate and the right side plate; the front side surface of the rear plate is also fixedly provided with a reinforcing plate which is horizontally arranged; the remote sensing camera is fixed on the outer surface of the top plate, and satellite sailboards are respectively hinged on the outer surfaces of the left side plate and the right side plate; the rear side of the rear plate is also provided with a plurality of hanging structures.
The beneficial effects of the utility model are as follows: the optical remote sensing satellite with the side-hung type structure has the advantages that the whole satellite box body adopts a trapezoid-like structure, the structure has higher structural stability, the volume utilization rate is high, and the integral moment of inertia is smaller. Compared with the traditional configuration, the optical remote sensing satellite with the side-hung configuration can meet the side-hung requirement of the whole satellite, the weight of the satellite is greatly reduced, and the weight ratio of the structural subsystem to the whole satellite is less than 20%.
On the basis of the technical scheme, the utility model can be improved as follows.
Further, a reinforcing frame is fixedly arranged on one side surface of the left side plate and one side surface of the right side plate, which are opposite to each other, the reinforcing frame is located above the top plate, a first edge of the reinforcing frame is fixedly connected with the outer surface of the top plate, a second edge of the reinforcing frame is fixedly connected with the rear plate, and a third edge of the reinforcing frame is flush with the inclined edge of the right trapezoid structure.
The beneficial effects of adopting the further scheme are as follows: through setting up the strengthening frame, be favorable to the structural strength stability of whole satellite box.
Further, the front end of the first side of the reinforcing frame is flush with the front end of the top plate, and the fourth side of the reinforcing frame is parallel to the top plate and fixedly connected with the lower surface of the reinforcing plate.
Further, the reinforcing frame is of a second right-angle trapezoid structure, the upper bottom edge of the second right-angle trapezoid structure is a fourth edge, the lower bottom edge of the second right-angle trapezoid structure is a first edge, the right-angle waist of the second right-angle trapezoid structure is a second edge, and the hypotenuse waist of the second right-angle trapezoid structure is a third edge.
Further, the left side edge and the right side edge of the reinforcing plate are fixedly connected with the left side plate and the right side plate respectively.
Further, the front plate is fixedly connected with the left side plate and the right side plate through first corner frames respectively, the rear plate is fixedly connected with the left side plate and the right side plate through second corner frames respectively, the first corner frames and the second corner frames are L-shaped, and the first corner frames and the second corner frames are fixed at the corners of the inner side walls of the satellite box body.
The beneficial effects of adopting the further scheme are as follows: the setting of angle frame is favorable to the stable connection fixed between front bezel and the curb plate about, back plate and the curb plate about.
Further, a partition plate is arranged in the satellite box body and is arranged in parallel with the front plate, and a structural hole is formed in the partition plate; the thickness of the partition board is 20-30 mm.
The beneficial effects of adopting the further scheme are as follows: the arrangement of the structural holes can meet the electrical connection requirements of the front cabin and the rear cabin of the satellite box body.
Further, each box plate of the satellite box body adopts an aluminum honeycomb plate, and the aluminum honeycomb plate comprises two layers of aluminum alloy skin plates and an aluminum core arranged between the two layers of aluminum alloy skin plates.
The beneficial effects of adopting the further scheme are as follows: the satellite box body adopts a laminate structure, so that the structural weight is reduced and the design and processing cost is reduced on the premise of ensuring the structural strength.
Further, the thicknesses of the top plate and the rear plate are 35-45 mm, and the thicknesses of the bottom plate, the front plate, the left side plate and the right side plate are 25-35 mm.
Further, the number of the hanging structures is four, the four hanging structures are arranged in a square shape, two hanging structures positioned below are arranged adjacent to the bottom plate, and two hanging structures positioned above are arranged at the position where the reinforcing plate is located.
The beneficial effects of adopting the further scheme are as follows: the structure strength of the position where the hanging structure is located is weaker, and the stability of the hanging structure is facilitated by the arrangement of the reinforcing plate.
Drawings
Fig. 1 is a schematic perspective view of a satellite windsurfing board in a folded state of an optical remote sensing satellite with a side-hanging configuration according to the present utility model;
fig. 2 is a schematic diagram of a second perspective structure of a satellite windsurfing board of the optical remote sensing satellite with a side-hanging configuration according to the present utility model;
fig. 3 is a schematic perspective view of a satellite windsurfing board of an optical remote sensing satellite with a side-hanging configuration according to the first embodiment of the present utility model;
fig. 4 is a schematic diagram of a stereoscopic structure of a satellite windsurfing board of the optical remote sensing satellite with a side-hanging configuration in a second unfolding state;
fig. 5 is a schematic view of the internal structure of the satellite box according to the present utility model.
In the drawings, the list of components represented by the various numbers is as follows:
1. a satellite box; 11. a top plate; 12. a bottom plate; 13. a front plate; 14. a rear plate; 15. a left side plate; 16. a right side plate; 17. a partition plate; 18. a structural hole;
2. a satellite windsurfing board; 3. a remote sensing camera; 4. a hitching structure; 5. a first corner frame; 51. a second corner frame; 6. a reinforcing plate; 7. and (5) reinforcing the frame.
Detailed Description
The principles and features of the present utility model are described below with reference to the drawings, the examples are illustrated for the purpose of illustrating the utility model and are not to be construed as limiting the scope of the utility model.
As shown in fig. 1 to 5, an optical remote sensing satellite with a side-hanging configuration in this embodiment includes a satellite box 1, a satellite sailboard 2 and a remote sensing camera 3, where the satellite box 1 includes a top plate 11, a bottom plate 12, a front plate 13, a rear plate 14, a left side plate 15 and a right side plate 16, where the left side plate 15 and the right side plate 16 are all in a first right trapezoid structure, the lower ends of the front plate 13 and the rear plate 14 are respectively and vertically fixed on the front side edge and the rear side edge of the bottom plate 12, the right-angled waists of the left side plate 15 and the right side plate 16 are respectively and vertically fixed on the left side edge and the right side edge of the bottom plate 12, the left side edge and the right side edge of the front plate 13 are respectively and fixedly connected with the left side plate 15 and the right side plate 16, and the left side edge and the right side edge of the rear plate 14 are respectively and the height of the rear plate 14 is the same as the length of the lower side edge of the first right trapezoid structure; the front side of the top plate 11 is fixed at the top end of the front plate 13, the top plate 11 is arranged in parallel with the bottom plate 12, the rear side of the top plate 11 is fixedly connected with the rear plate 14, and the left side and the right side of the top plate 11 are respectively fixedly connected with the left side plate 15 and the right side plate 16; the front side of the rear plate 14 is also fixed with a reinforcing plate 6 which is horizontally arranged; the remote sensing camera 3 is fixed on the outer surface of the top plate 11, and satellite sailboards 2 are respectively hinged on the outer surfaces of the left side plate 15 and the right side plate 16; the rear side of the rear plate 14 is also provided with a plurality of hanging structures 4.
As shown in fig. 1 and 3, the remote sensing camera 3 of the present embodiment is mounted on the top plate 11 of the satellite box 1, the remote sensing camera 3 and the top plate 11 adopt a deformation decoupling mounting mode, and a static kinematic mounting mode is formed by damping supports of three groups of bipos. The decoupling installation mode of the load and the platform is characterized in that on one hand, the camera load and the satellite platform are completely decoupled, and the aspects of mechanics, heat, mechanical structure and the like are relatively independent; on the other hand, the complete decoupling mode can independently develop the camera load and the satellite platform in each stage of design, assembly and system integration, does not need excessive cross coupling, can greatly simplify the complexity of system design, and saves the research and development period and cost.
As shown in fig. 1, 3 and 5, a reinforcing frame 7 is fixedly arranged on one side surface opposite to the left side plate 15 and the right side plate 16 in this embodiment, the reinforcing frame 7 is located above the top plate 11, a first edge of the reinforcing frame 7 is fixedly connected with an outer surface of the top plate 11, a second edge of the reinforcing frame 7 is fixedly connected with the rear plate 14, and a third edge of the reinforcing frame 7 is flush with a hypotenuse of the right trapezoid structure. The reinforcing frame can be made of carbon fiber materials, and is light in weight and high in ratio. Through setting up the strengthening frame, be favorable to the structural strength stability of whole satellite box.
As shown in fig. 1, 3 and 5, the front end of the first edge of the reinforcing frame 7 of the present embodiment is flush with the front end of the top plate 11, and the fourth edge of the reinforcing frame 7 is parallel to the top plate 11 and fixedly connected to the lower surface of the reinforcing plate.
As shown in fig. 1, 3 and 5, the reinforcing frame 7 in this embodiment is a second right trapezoid structure, an upper bottom edge of the second right trapezoid structure is a fourth edge, a lower bottom edge of the second right trapezoid structure is a first edge, a right-angle waist of the second right trapezoid structure is a second edge, and a hypotenuse waist of the second right trapezoid structure is a third edge.
Further, the left side and the right side of the reinforcing plate 6 are fixedly connected with the left side plate 15 and the right side plate 16, respectively. The reinforcing plate 6 can be fixed on the fourth sides of the two reinforcing frames 7, and the reinforcing frames 7 can be used for carrying out certain structural support on the reinforcing plate 6, so that all the box plates, the reinforcing plates and the reinforcing frames are constructed into a whole, and the structures of the box plates, the reinforcing plates and the reinforcing frames are mutually reinforced.
As shown in fig. 5, in order to make the overall configuration more stable and facilitate assembly and debugging, the front plate 13 and the left and right side plates 15 and 16 of the present embodiment are respectively and fixedly connected through a first corner frame 5, the rear plate 14 and the left and right side plates 15 and 16 are respectively and fixedly connected through a second corner frame 51, the first and second corner frames 5 and 51 are all L-shaped, and the first and second corner frames 5 and 51 are all fixed at the corners of the inner side wall of the satellite box 1. The setting of angle frame is favorable to the stable connection fixed between front bezel and the curb plate about, back plate and the curb plate about. The corner frame material is a metal structure of aluminum alloy or titanium alloy, the corner frame is a main bearing component, all adjacent box plates are connected with the corner frame, the corner frame is of an L-shaped reinforcing structure, and the distance between connecting points on each angle steel is not more than 100mm.
As shown in fig. 5, in the satellite box 1 of this embodiment, a partition plate 17 is further disposed, where the partition plate 17 is disposed parallel to the front plate 13, and a structural hole 18 is formed on the partition plate 17; the thickness of the separator 17 is 20 to 30mm, preferably 25mm. The structural holes 18 are round holes, and the number of the structural holes 18 is two. The arrangement of the structural holes can meet the electrical connection requirements of the front cabin and the rear cabin of the satellite box body.
Each box plate of the satellite box 1 in this embodiment adopts an aluminum honeycomb plate, and the aluminum honeycomb plate includes two layers of aluminum alloy skin plates and an aluminum core disposed between the two layers of aluminum alloy skin plates. The aluminum alloy skin plate is an aluminum alloy sheet with the thickness of 0.3 mm. The satellite box body adopts a laminate structure, so that the structural weight is reduced and the design and processing cost is reduced on the premise of ensuring the structural strength.
Specifically, the thicknesses of the top plate 11 and the rear plate 14 are 35-45 mm, and the thicknesses of the bottom plate 12, the front plate 13, the left side plate 15 and the right side plate 16 are 25-35 mm. Further preferably, the thicknesses of the top plate 11 and the rear plate 14 are 40mm, and the thicknesses of the bottom plate 12, the front plate 13, the left side plate 15 and the right side plate 16 are 30mm.
As shown in fig. 2 and 4, the number of the hanging structures 4 in the present embodiment is four, the four hanging structures 4 are arranged in a square shape, the two hanging structures 4 located below are arranged adjacent to the bottom plate 12, and the two hanging structures 4 located above are disposed at the position where the reinforcing plate 6 is located. The structure strength of the position where the hanging structure is located is weaker, and the stability of the hanging structure is facilitated by the arrangement of the reinforcing plate. The hanging structure 4 can be selected from the common hanging structures for aerospace and can be purchased commercially.
All mounting hole embedded parts of the optical remote sensing satellite with the side-hung type structure are aerospace standard embedded parts, the structural weight is reduced, the design and processing cost is reduced, a rear plate is a whole-satellite mounting surface, a top plate is a load mounting surface, thickening treatment is carried out for ensuring the rigidity strength, and in addition, non-standard integral embedded parts are designed for ensuring the connection reliability at key parts for transmitting mechanical loads.
The optical remote sensing satellite with the side-hung type structure has the advantages that the whole satellite box body adopts a trapezoid-like structure, the structure has high structural stability, the volume utilization rate is high, and the integral moment of inertia is small. Compared with the traditional configuration, the optical remote sensing satellite with the side-hung configuration can meet the side-hung requirement of the whole satellite, the weight of the satellite is greatly reduced, and the weight ratio of the structural subsystem to the whole satellite is less than 20%. The optical remote sensing satellite with the side-hung type structure adopts a combined trapezoid box structure of a honeycomb plate and a frame, and the load and the platform are completely decoupled and installed; the side-hung remote sensing satellite configuration is compatible with functionality, practicality and economy, and can greatly improve the economic benefit of the carrier rocket.
In the description of the present utility model, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present utility model and simplifying the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present utility model.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present utility model, the meaning of "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.
In the present utility model, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present utility model can be understood by those of ordinary skill in the art according to the specific circumstances.
In the present utility model, unless expressly stated or limited otherwise, a first feature "up" or "down" a second feature may be the first and second features in direct contact, or the first and second features in indirect contact via an intervening medium. Moreover, a first feature being "above," "over" and "on" a second feature may be a first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is level higher than the second feature. The first feature being "under", "below" and "beneath" the second feature may be the first feature being directly under or obliquely below the second feature, or simply indicating that the first feature is less level than the second feature.
In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present utility model. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.
While embodiments of the present utility model have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the utility model, and that variations, modifications, alternatives and variations may be made to the above embodiments by one of ordinary skill in the art within the scope of the utility model.
Claims (10)
1. The utility model provides an optical remote sensing satellite of side-hung type configuration, its characterized in that includes satellite box, satellite sailboard and remote sensing camera, the satellite box includes roof, bottom plate, front bezel, back plate, left side board and right side board all are first right trapezoid structure, the lower extreme of front bezel and back plate is fixed perpendicularly respectively in the front side and the rear side of bottom plate, the right angle waist of left side board and right side board is fixed perpendicularly in the left side and the right side of bottom plate, the left and right sides limit of front bezel respectively with left side board and right side board fixed connection, the left and right sides limit of back plate respectively with left side board and right side board fixed connection, the height of back plate with the lower base length of first right trapezoid structure is the same; the front side edge of the top plate is fixed at the top end of the front plate, the top plate is arranged in parallel with the bottom plate, the rear side edge of the top plate is fixedly connected with the rear plate, and the left side edge and the right side edge of the top plate are respectively and fixedly connected with the left side plate and the right side plate; the front side surface of the rear plate is also fixedly provided with a reinforcing plate which is horizontally arranged; the remote sensing camera is fixed on the outer surface of the top plate, and satellite sailboards are respectively hinged on the outer surfaces of the left side plate and the right side plate; the rear side of the rear plate is also provided with a plurality of hanging structures.
2. The optical remote sensing satellite with a side-hung configuration according to claim 1, wherein a reinforcing frame is fixedly arranged on one side surface of the left side plate and the right side plate opposite to each other, the reinforcing frame is located above the top plate, a first edge of the reinforcing frame is fixedly connected with the outer surface of the top plate, a second edge of the reinforcing frame is fixedly connected with the rear plate, and a third edge of the reinforcing frame is flush with the inclined edge of the right trapezoid structure.
3. The optical remote sensing satellite in a side-hung configuration according to claim 2, wherein the front end of the first edge of the reinforcing frame is flush with the front end of the top plate, and the fourth edge of the reinforcing frame is parallel to the top plate and fixedly connected to the lower surface of the reinforcing plate.
4. The optical remote sensing satellite with a side-hung configuration according to claim 3, wherein the reinforcing frame is a second right trapezoid structure, an upper bottom edge of the second right trapezoid structure is a fourth edge, a lower bottom edge of the second right trapezoid structure is a first edge, a right-angle waist of the second right trapezoid structure is a second edge, and a hypotenuse waist of the second right trapezoid structure is a third edge.
5. The optical remote sensing satellite of claim 1, wherein the left and right sides of the reinforcing plate are further fixedly connected to the left and right side plates, respectively.
6. The optical remote sensing satellite with a side-hung configuration according to claim 1, wherein the front plate is fixedly connected with the left side plate and the right side plate through first corner frames respectively, the rear plate is fixedly connected with the left side plate and the right side plate through second corner frames respectively, the first corner frames and the second corner frames are all L-shaped, and the first corner frames and the second corner frames are all fixed at corners of the inner side wall of the satellite box body.
7. The optical remote sensing satellite with a side-hung configuration according to claim 1, wherein a partition board is further arranged in the satellite box body, the partition board is arranged in parallel with the front board, and a structural hole is formed in the partition board; the thickness of the partition board is 20-30 mm.
8. The optical remote sensing satellite of claim 1, wherein each of the satellite box panels comprises an aluminum honeycomb panel comprising two aluminum alloy skin panels and an aluminum core disposed between the two aluminum alloy skin panels.
9. The optical remote sensing satellite with a side-hung configuration according to claim 1, wherein the thickness of the top plate and the rear plate is 35-45 mm, and the thickness of the bottom plate, the front plate, the left side plate and the right side plate is 25-35 mm.
10. The optical remote sensing satellite according to claim 1, wherein the number of the hanging structures is four, the four hanging structures are arranged in a square shape, two hanging structures positioned below are arranged adjacent to the bottom plate, and two hanging structures positioned above are arranged at the position of the reinforcing plate.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202223093008.6U CN219215388U (en) | 2022-11-21 | 2022-11-21 | Optical remote sensing satellite with side-hanging type configuration |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223093008.6U CN219215388U (en) | 2022-11-21 | 2022-11-21 | Optical remote sensing satellite with side-hanging type configuration |
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| CN219215388U true CN219215388U (en) | 2023-06-20 |
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| CN202223093008.6U Active CN219215388U (en) | 2022-11-21 | 2022-11-21 | Optical remote sensing satellite with side-hanging type configuration |
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