CN112977882A - High orbit satellite platform structure with central force bearing cylinder type storage boxes tiled in parallel - Google Patents
High orbit satellite platform structure with central force bearing cylinder type storage boxes tiled in parallel Download PDFInfo
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- CN112977882A CN112977882A CN202110271633.6A CN202110271633A CN112977882A CN 112977882 A CN112977882 A CN 112977882A CN 202110271633 A CN202110271633 A CN 202110271633A CN 112977882 A CN112977882 A CN 112977882A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/223—Modular spacecraft systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/244—Spacecraft control systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
- B64G1/443—Photovoltaic cell arrays
Abstract
The invention provides a high orbit satellite platform structure with central force bearing cylinder type storage boxes which are tiled in parallel, which comprises a platform structure, a propulsion system and a solar cell array, the solar cell array is arranged outside the platform structure and can be switched between a folded state and an extended state, the electronic cabin and the propulsion cabin are divided into functional areas in the platform structure, the propulsion cabin is provided with a complete independent physical entity, the electronic cabin and the propulsion cabin can be integrated in parallel, on one hand, the propulsion cabin is convenient to weld and integrate the propulsion system and test and maintain a propulsion valve assembly, on the other hand, the support structure on the side of the electronic cabin is good in openness and large in cabin capacity, convenient conditions are created for the electronic cabin to flexibly adapt to assembly, disassembly, test and inspection of onboard instruments and equipment, and application requirements of a high-orbit remote sensing satellite can be met.
Description
Technical Field
The invention relates to a satellite platform configuration, in particular to a high-orbit satellite platform configuration with central force bearing cylinder type storage boxes which are tiled in parallel.
Background
Satellite platforms, also known as satellite service pods, are comprised of satellite service assurance systems that can support a combination of one or more payloads. The satellite platform can be composed of one or more cabin sections such as a service cabin, a propulsion cabin and a return cabin by a satellite service system, and the integration and the test of independent functions are realized.
The satellite platform configuration is a set of composite frames that describe the basic physical dimensions, internal construction, platform service assurance system and the intended area of payload equipment of the satellite platform, similar to a "blank house" of a residential home. The task of the satellite platform configuration design is to determine a basic framework of the satellite platform, and the basic framework comprises platform appearance size design, main structure form and size design, cabin function division and size design, propulsion assembly and other fixed equipment layout design and connection mode design.
High orbit satellite platforms are usually equipped with a two-component unified chemical propulsion system, which needs to carry a large amount of propellant to realize orbit transfer, and more than 2 large-volume propellant tanks need to be equipped. At present, high orbit satellite platforms at home and abroad are mainly manufactured for communication satellites, and the platform configuration generally adopts a cylinder shape with a rectangular cross section, wherein the length direction of the rectangle is the east-west direction, and the width direction is the north-south direction; the internal frame of the platform mainly adopts three main structural forms of a box plate type, a central force bearing cylinder type, a truss type and the like, and a basic platform configuration is formed by connecting 2 propellant storage boxes in series or connecting 3-4 storage boxes in parallel; the platform usually selects the top surface of the platform as the ground; the solar cell has the typical configuration characteristics of large south-north side surface area, large solar cell array area, high-thinness appearance of the size of the platform body and the like. Meanwhile, a communication satellite platform is generally divided into a platform module and a communication module, the two modules are separately and independently inherited and tested, and equipment in the cabin is extremely difficult to maintain and replace after the two modules are combined into a whole.
The effective load of the high-orbit remote sensing satellite, especially the optical remote sensing load, has the characteristics of large size, low power consumption, sensitivity to the force-heat environment and the thermal deformation stability and the like, and has higher requirements on the attitude measurement, the stability precision, the in-orbit thermal deformation and the like of a satellite platform. When the communication platform with the communication transponder and the antenna as main effective loads is applied to the effective loads of the remote sensing satellite, a large amount of platform modification work is required, generally, the modification on aspects of satellite platform configuration, structure, electronic equipment, thermal control design and the like is involved, and the requirement for developing large-scale high-orbit remote sensing satellites is difficult to adapt.
There are also many designs in the prior art, for example, patent document CN104698509A discloses a stationary orbit meteorological satellite configuration and composition, which is designed by using a hexahedral cylinder configuration and a configuration layout of a plurality of large-volume storage tanks. For another example, patent document CN106477072A discloses a multi-type load application satellite configuration, the configuration body of which is a regular hexagonal prism octahedron configuration, including frame, bottom plate, side plate and top plate. For example, patent document CN104260901A discloses a modular two-component propulsion system and a satellite body, which comprises a fuel tank gas bypass module, an oxygen tank gas bypass module, a main gas path module, a fuel agent liquid path module, an oxidant liquid path module, a tank liquid port module, and the like, wherein the modules are arranged on an installation space formed by an upper mounting plate of a + Y-side instrument and a lower mounting plate of the + Y-side instrument and on the side surfaces of the upper/lower mounting plates of the + Y-side instrument, and all the modules are arranged in the + Y-side space in a concentrated manner. For another example, patent document CN107792398A discloses a mounting structure suitable for extension and retraction of a satellite high-pressure gas cylinder, which comprises a gas cylinder mounting plate and a gas cylinder supporting plate, wherein the gas cylinder is fixedly connected with the gas cylinder mounting plate, and the gas cylinder is connected with the gas cylinder supporting plate through a honeycomb plate with a rubber gasket to realize auxiliary support of the gas cylinder. For another example, patent document CN107738761A discloses an adjustable installation structure for a large-sized thin-walled storage tank of a high orbit satellite, which comprises a storage tank installation plate with a reinforcing frame with a hollow structure inside and a storage tank stay bar assembly, wherein the storage tank installation plate and the storage tank stay bar assembly are respectively installed in two opposite directions of the storage tank, and the stay bar is connected with a storage tank sleeve head through a rotatable arrangement. However, the above designs have difficulties in the refitting of satellite platform configurations, structures, electronic devices or thermal control designs, and the like, and cannot adapt to or are difficult to adapt to the requirements of the development of large high-orbit remote sensing satellites.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a high-orbit satellite platform structure with central force bearing cylinder type storage boxes which are tiled in parallel.
The invention provides a high orbit satellite platform structure with central force bearing cylinder type storage boxes which are tiled in parallel, which comprises a platform structure, a propulsion system and a solar cell array;
the propulsion system is mounted on the platform structure, and the solar cell array is mounted outside the platform structure and can be switched between a folded state and an extended state.
Preferably, a central force bearing cylinder is arranged inside the platform structure, and the propulsion system comprises a plurality of storage tanks, a plurality of gas cylinders, an attitude control thruster and a remote engine;
the gas cylinders are arranged inside the central bearing cylinder and are arranged in a central symmetry manner;
the storage boxes and the attitude control thrusters are arranged along the circumferential direction of the central bearing cylinder, the gas cylinders are arranged in a central symmetry manner, and the remote engine is mounted at the end part of the central bearing cylinder and extends to the outside of the central bearing cylinder.
Preferably, the bottom of the storage box is mounted on the platform structure through a mounting flange, and the top of the storage box is connected with the central bearing cylinder in a hinged mode.
Preferably, the platform structure comprises a platform bottom plate, a platform top plate, a side plate assembly, a laminate assembly, a platform lower support frame and a platform upper support frame;
the platform top plate is arranged at the top end of a central force bearing cylinder in the platform structure, the platform bottom plate is arranged at the bottom end of the central force bearing cylinder, an upper platform supporting frame, a layer plate assembly and a lower platform supporting frame are sequentially arranged between the platform top plate and the platform bottom plate, and the upper platform supporting frame, the layer plate assembly and the lower platform supporting frame are all arranged along the circumferential direction of the central force bearing cylinder;
the side plate assembly is arranged along the circumferential direction of the side plate assembly and forms a regular hexahedron structure together with the platform bottom plate and the platform top plate.
Preferably, the side panel assembly comprises an electronic compartment south side panel, an electronic compartment north side panel, a propulsion compartment first east side panel, a propulsion compartment second east side panel, a propulsion compartment first west side panel, and a propulsion compartment second west side panel;
the electronic cabin south side plate, the first east side plate of the propulsion cabin, the second east side plate of the propulsion cabin, the electronic cabin north side plate, the second west side plate of the propulsion cabin and the first west side plate of the propulsion cabin are sequentially connected to form a regular hexahedron structure and are respectively connected with the upper supporting frame and the lower supporting frame of the platform to form 6 containing spaces arranged along the circumferential direction of the central bearing cylinder.
Preferably, the layer assembly comprises a first propulsion compartment east layer plate, a second propulsion compartment east layer plate, a first propulsion compartment west layer plate, a second propulsion compartment west layer plate, an electronic compartment south lower layer plate and an electronic compartment north lower layer plate;
the first propulsion cabin east plate, the second propulsion cabin east plate, the electronic cabin north lower plate, the first propulsion cabin west plate, the second propulsion cabin west plate and the electronic cabin south lower plate are arranged around the central bearing cylinder in a coplanar manner in the circumferential direction and are all perpendicular to the axis of the central bearing cylinder.
Preferably, the lower platform supporting frame and the upper platform supporting frame both adopt rod type frames.
Preferably, 2 accommodating spaces respectively corresponding to the south side plate and the north side plate of the electronic cabin are the electronic cabin, the platform cabin is used for bearing satellite electronic instrument equipment, and structural members used for bearing in the platform cabin are detachably connected;
the other 4 accommodating spaces are propulsion cabins and are used for bearing the storage boxes, and structural members used for bearing in the propulsion cabins are welded.
Preferably, the laminate subassembly still includes electronics cabin south top plate and electronics cabin north top plate, electronics cabin south top plate parallel mount is between electronics cabin south bottom plate and platform roof and both sides are connected respectively braced frame on the platform, electronics cabin north top plate parallel mount is between electronics cabin north bottom plate and platform roof and both sides are connected respectively braced frame on the platform.
Preferably, the solar cell array adopts a single-wing configuration or a double-wing configuration, wherein the number of folding plates on each wing of the solar cell array is greater than or equal to 2.
Compared with the prior art, the invention has the following beneficial effects:
1. the electronic cabin and the propulsion cabin are divided into functional areas in the platform structure, the propulsion cabin is provided with a complete independent physical entity, and the electronic cabin and the propulsion cabin can be integrated in parallel, so that on one hand, the propulsion cabin is convenient to weld and integrate the propulsion system and test and maintain the propulsion valve assembly, on the other hand, the support structure at the side of the electronic cabin is good in smoothness and large in cabin capacity, convenient conditions are created for the electronic cabin to flexibly adapt to assembly, disassembly, test, inspection and the like of instruments and equipment on the satellite, and the application requirements of a high-orbit remote sensing satellite can be met.
2. The invention adopts the prism platform shape with the hexagonal cross section, 4 storage boxes are connected in parallel and tiled, the top plate has large area, a short and fat structure is formed, the appearance of the fairing of the carrier rocket can be fully utilized, and the practicability is strong.
3. The platform has the advantages of large fixed ground area, low platform mass center and large rotary inertia, and can provide favorable conditions for loading a plurality of large remote sensing instruments, low mechanical environment conditions and high-stability attitude control.
4. The propulsion system in the propulsion cabin is welded and fixed through the pipeline, the propulsion system is arranged in a non-detachable structure, the electronic cabin is a main cabin section of the platform for bearing satellite electronic instrument equipment, the arrangement mode of being detachable and changeable in internal structure is adopted, the structural members can be disassembled, assembled and replaced according to the satellite task requirement, flexible configuration is achieved, and the universality is high.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a schematic configuration outline of a platform in a folded state of a solar cell array according to an embodiment of the present invention;
fig. 2 is a schematic configuration outline diagram of a platform in an unfolded state of a solar cell array according to an embodiment of the present invention;
fig. 3 is an exploded view of the internal components of the platform configuration in a folded state of the solar cell array according to the embodiment of the present invention;
FIG. 4 is an exploded view of a platform structure according to an embodiment of the present invention;
fig. 5 is a schematic structural outline of a lower support frame according to an embodiment of the present invention;
FIG. 6 is a schematic view of another lower support frame structure according to an embodiment of the present invention;
FIG. 7 is a schematic view of the outer shape of a propulsion platform provided by an embodiment of the present invention;
FIG. 8 is a schematic illustration of a flat configuration and connections of a storage tank provided by an embodiment of the present invention;
FIG. 9 is a schematic illustration of a gas cylinder and remote site engine connection provided by an embodiment of the present invention;
fig. 10 is a schematic structural outline of an upper support frame according to an embodiment of the present invention;
fig. 11 is a schematic view of another upper supporting frame structure according to an embodiment of the present invention.
The figures show that:
platform structure 1 electronics cabin south side panel 112
Under platform support frame 103 propulsion bay second east side plate 117
First propulsion compartment east deck 104 propulsion compartment first west deck 118
The electronics bay southern lower deck 105 pushes into the bay second west side 119
First propulsion compartment west deck 106 storage tank 201
Electronic cabin north lower plate 107 gas cylinder 202
Electronics compartment north upper plate 110 valve assembly 205
Platform top plate 111 conical support 206
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
Example 1:
the invention provides a high orbit satellite platform structure with central bearing cylinder type storage boxes tiled in parallel, which comprises a platform structure 1 with a central bearing cylinder type regular hexagon column, a two-component chemical unified propulsion system 2 with storage boxes tiled in parallel and a solar cell array 3, wherein the propulsion system 2 is arranged on the platform structure 1, the solar cell array 3 is arranged outside the platform structure 1 and can be switched between a folded state and an extended state, the solar cell array 3 can adopt a single-wing configuration or a double-wing configuration according to the requirements of practical application scenes, the number and the area of folded plates on the solar cell array 3 can be adjusted according to the requirements of platform output power, and the number of the folded plates on each wing of the solar cell array 3 is more than or equal to 2, as shown in figures 1-4.
Specifically, a central bearing cylinder 101 is arranged inside the platform structure 1, the central bearing cylinder 101 serves as a main bearing structure of the platform, the bottom end portion of the central bearing cylinder 101 serves as a mechanical reference of a satellite and a satellite-rocket docking interface, and meets a standard 1666 satellite-rocket belting separation type mechanical interface, the propulsion system 2 comprises a plurality of storage tanks 201, a plurality of gas cylinders 202, attitude control thrusters 203 and a remote engine 204, the plurality of gas cylinders 202 are flatly laid inside the central bearing cylinder 101 and are arranged in a central symmetry manner, the plurality of storage tanks 201 and the attitude control thrusters 203 are all arranged along the circumferential direction of the central bearing cylinder 101, the plurality of gas cylinders 202 are arranged in a central symmetry manner relative to the central bearing cylinder 101, and the plurality of storage tanks 201 are used for filling propellants of two working media with different densities, namely, an oxidant and a fuel. The remote engine 204 is installed at the end of the central force bearing cylinder 101 and extends to the outside of the central force bearing cylinder 101, the central force bearing cylinder 101 is preferably connected with the end of the central force bearing cylinder 101 through a conical support 206, the remote engine 204 is arranged at the central position of the end of the central force bearing cylinder 101, the body of the remote engine 204 exceeds the bottom end of the central force bearing cylinder 101, and the installation surface of the remote engine 204 is flush with the satellite-rocket butt joint surface of the central force bearing cylinder 101.
Further, the bottom of the storage tank 201 is mounted on the platform structure 1 through a mounting flange, and the top of the storage tank 201 is connected with the central bearing cylinder 101 in a hinged manner.
Specifically, the platform structure 1 includes a platform bottom plate 102, a platform top plate 111, a side plate assembly, a deck plate assembly, a platform lower support frame 103, and a platform upper support frame 108, the platform top plate 111 is installed at the top end of a central force bearing cylinder 101 provided in the platform structure 1, the platform bottom plate 102 is installed at the bottom end of the central force bearing cylinder 101, the platform upper support frame 108, the deck plate assembly, and the platform lower support frame 103 are sequentially installed between the platform top plate 111 and the platform bottom plate 102, and the platform upper support frame 108, the deck plate assembly, and the platform lower support frame 103 are all arranged along the circumferential direction of the central force bearing cylinder 101; the side plate assembly is arranged along the circumferential direction of the side plate assembly and forms a regular hexahedron structure together with the platform bottom plate 102 and the platform top plate 111, wherein the platform lower supporting frame 103 and the platform upper supporting frame 108 both preferably adopt rod type frames.
Further, the side plate assembly comprises an electronic cabin south side plate 112, an electronic cabin north side plate 114, a first propulsion cabin east side plate 116, a second propulsion cabin east side plate 117, a first propulsion cabin west side plate 118 and a second propulsion cabin west side plate 119, wherein the electronic cabin south side plate 112, the first propulsion cabin east side plate 116, the second propulsion cabin east side plate 117, the electronic cabin north side plate 114, the second propulsion cabin west side plate 119 and the first propulsion cabin west side plate 118 are sequentially connected to form a regular hexahedron structure and are respectively connected with the platform upper supporting frame 108 and the platform lower supporting frame 103 to form 6 accommodating spaces arranged along the circumferential direction of the central bearing cylinder 101. 2 accommodation spaces that electron cabin south curb plate 112, electron cabin north curb plate 114 correspond respectively are the electron cabin, the platform cabin is used for bearing satellite electronic instrument equipment, the structure that is used for bearing in the platform cabin is for dismantling the connection, and remaining 4 accommodation spaces are for advancing the cabin, are used for bearing storage tank 201, the structure that is used for bearing in the propulsion cabin adopts the welding, for can not dismantle.
The platform structure of the invention is divided into 15 internal cabin section spaces by a laminate component, a platform upper and lower support frame and a central bearing cylinder 101, the space between the central bearing cylinder 101 and a side plate is an ' electronic cabin ' and a ' propulsion cabin ', the propulsion cabin ' is used for loading a propulsion storage tank 201, an air bottle 202, an attitude control thruster 203, a remote engine 204 and a valve component 205, and the ' electronic cabin ' is used for loading the platform and instrument equipment related to a payload.
The propulsion cabin is a cabin section formed by minimum complete solid structures required by the general assembly and integration of the propulsion system, and after the propulsion system is welded by pipelines, all structural components are preferably not detachable, so that the working stability of the propulsion system 2 is ensured. The electronic cabin is a main cabin section for bearing satellite electronic instrument equipment by the platform, and internal structural parts can be disassembled, assembled and replaced according to the satellite task requirement, so that flexible configuration is realized, and the structural parts comprise laminates and other auxiliary fixed parts.
Furthermore, the electronic cabin and the propulsion cabin are divided into independent functional areas in space, and form an organic unified high-orbit satellite common platform structure which is customized for the remote sensing payload in physics, and the platform has the distinct characteristics of large loading cross section area of the payload, large payload bearing capacity, large size span in the north-south direction, large cabin capacity in the platform, large platform rotational inertia, short and fat body size, convenient satellite final assembly and test and the like.
Specifically, the tier assembly includes a first propulsion bay east tier floor 104, a second propulsion bay east floor 113, a first propulsion bay west floor 106, a second propulsion bay west floor 115, an electronics bay south lower floor 105, an electronics bay north lower floor 107, an electronics bay south upper floor 109, and an electronics bay north upper floor 110, the first propulsion cabin east plate 104, the second propulsion cabin east plate 113, the electronic cabin north lower plate 107, the first propulsion cabin west plate 106, the second propulsion cabin west plate 115 and the electronic cabin south lower plate 105 are sequentially arranged around the circumference of the central bearing cylinder 101 in a coplanar manner and are all vertical to the axis of the central bearing cylinder 101, the south upper plate 109 of the electronic cabin is arranged between the south lower plate 105 of the electronic cabin and the top plate 111 of the platform in parallel, and both sides of the south upper plate are respectively connected with the upper supporting frame 108 of the platform, the north upper plate 110 of the electronic cabin is installed in parallel between the north lower plate 107 of the electronic cabin and the top plate 111 of the platform, and both sides of the north upper plate are respectively connected with the upper supporting frame 108 of the platform.
Example 2:
this embodiment is a preferred embodiment of embodiment 1.
In the embodiment, the high orbit satellite platform with the central bearing barrel type storage boxes tiled in parallel adopts a prism platform shape with a hexagonal cross section, the envelope size of the platform structure 1 is phi 3650mm multiplied by 2205mm, the height size of a column section is 2095mm, a dwarf configuration characteristic is formed, the high orbit satellite platform can be matched with a 4000F fairing of a carrier rocket of CZ-3B series in China, the maximum filling amount of a propellant is 3100kg, and a main structure form of the central bearing barrel and a tiled configuration with 4 storage boxes 201 connected in parallel are selected. Fig. 4 is a schematic diagram of the structural composition of the platform of this embodiment, which is a hexagonal column structure, the side length of the hexagon is 1680mm, the central bearing cylinder 101 is used as a main bearing structure of the platform, and the outer diameter of the column section is 1020 mm.
The remote sensing payload is installed on a platform top plate 111, a propulsion system 2 comprises 4 propellant storage tanks 201, 3 gas cylinders 202, 1 set of attitude control thruster 203, 1 remote location engine 204, 1 set of pipeline and valve component, the 4 propellant storage tanks are symmetrically distributed on a first propulsion cabin east plate 104, a second propulsion cabin east plate 113, a first propulsion cabin west plate 106 and a second propulsion cabin west plate 115 in parallel, the 3 gas cylinders are symmetrically distributed inside a central bearing cylinder 101 in parallel, and the remote location engine 204 is installed on the central bearing cylinder 101 and close to the bottom of the platform; the foldable solar cell arrays 3 are two and are respectively folded and pressed on the electronic cabin south side plate 112 and the electronic cabin north side plate 114.
The platform top plate 111 can be expanded in the east-west direction according to payload loading requirements and rocket fairing enveloping limitation, the shape of the minimum size is a regular hexagon, and the side length of the regular hexagon is the same as that of the platform bottom plate 102.
The electronic cabin south lower layer plate 105 and the electronic cabin north lower layer plate 107 are arranged in a coplanar manner, and the electronic cabin south upper layer plate 109 and the electronic cabin north upper layer plate 110 are arranged in a coplanar manner.
The central bearing cylinder 101 comprises a conical section and a cylindrical section, and the end part of the conical section far away from the cylindrical section is a standard 1666 star-arrow belt-separated mechanical interface.
The lower platform supporting frame 103 and the upper platform supporting frame 108 have 12 frames in total, and the space is divided into 6 equal parts around the central force bearing cylinder 101. The supporting frames are rod-type frames, wherein the platform lower supporting frame 103 is divided into two specifications of 8 rod pieces and 9 rod pieces, as shown in fig. 5, 6, 10 and 11, the platform upper supporting frame 108 is divided into two specifications of 12 rod pieces and 14 rod pieces; 9 rods and 14 rods are located above and below the propulsion bay east/west deck.
The propellant storage tank 201 is of a spherical cylinder structure, as shown in fig. 7 and 8, an installation flange is arranged near the junction of a lower hemisphere and a column section, a cylinder section is arranged at the top of an upper hemisphere, the storage tank installation flange is connected with a side plate assembly, the upper hemisphere cylinder section of the storage tank is connected to the column section of the central bearing cylinder 101 in a hinged mode through a support consisting of 2 rod pieces, and a certain movable gap is formed for responding to the change of the volume of the storage tank. The 4 propellant storage tanks 201 have the same external dimension, are flatly arranged on the laminate assembly and have symmetry.
The 3 gas cylinders 202 have the same external dimension, and are flatly and symmetrically arranged inside the column section of the central bearing cylinder 101 as shown in fig. 9.
The platform lower supporting frame 103 and the platform upper supporting frame 108 form a bulkhead assembly, a supporting truss structure is adopted, the attitude control thruster 203 is arranged on the platform bottom plate 102 and the bulkhead assembly, wherein the platform bottom plate 102 is divided into 4 areas, and the bulkhead assembly is divided into 2 areas.
The remote engine 204 is arranged at the center of the end part of the central bearing cylinder 101, and the engine body exceeds the bottom end of the central bearing cylinder 101 and is connected with the central bearing cylinder 101 through a conical support 206.
The valve component assemblies 205 are all arranged on the laminate component, and the storage tank 201, the gas cylinder 202, the valve component assemblies 205, the attitude control thruster 203 and the remote engine 204 are connected into a whole propulsion system through pipelines; the pipeline passes through the partition frame assembly, the central bearing cylinder 101 and other structural components.
The foldable and unfoldable solar cell array 3 is a general foldable and unfoldable solar cell array, the foldable and unfoldable solar cell array 3 is of a double-wing structure and can be changed into a single-wing structure according to needs, the number of folding plates of a single solar cell array 3 is 2, and the number of folding plates can be adjusted according to needs.
Example 3:
this embodiment is another preferable embodiment of embodiment 1.
Fig. 5 and 6 show two specific configurations of the lower platform support frame 103 in this embodiment, fig. 10 and 11 show two specific configurations of the upper platform support frame 108, wherein the total number of the support frames with fewer rods is 4, that is, two structures in fig. 6, and two structures in fig. 11 are connected to the corresponding side plate assemblies of the electronic compartment, so as to provide a larger operation space for the dismounting and inspection of the instruments and equipment loaded on the electronic compartment.
Fig. 7 is an outline view of the propulsion bay of the present embodiment, where the distance between the lower surface of the east/west deck and the upper surface of the platform floor 102 is 645mm, and the distance between the upper surface of the east/west deck and the lower surface of the platform ceiling 111 is 1340 mm. A propulsion cabin structure entity is formed by the central force bearing cylinder 101, the platform bottom plate 102, the platform supporting truss, the propulsion cabin east/west layer plate and the electronic cabin north/south layer plate, and after the storage tank 201, the gas cylinder 202, the attitude control thruster 203, the remote engine 204 and the valve component 205 are assembled, a complete independent entity of the platform propulsion cabin is formed by welding through a propulsion pipeline, so that the welding, testing and valve component maintenance work of the propulsion system can be independently realized. The 4 propellant storage tanks are distributed and filled with working media with two different densities of oxidant and fuel, wherein 1 storage tank 201 filled with the oxidant or the fuel is respectively arranged on the east plate of the propulsion cabin and the east plate of the propulsion cabin, and the storage tanks 201 filled with the oxidant or the fuel are arranged in a central symmetry mode relative to the longitudinal axis of the platform. The valve assembly is disposed at the propulsion pod east/west deck.
Fig. 8 is a schematic diagram of the flat laying configuration and connection of the storage tanks in the embodiment, 4 storage tanks 201 are distributed on a pitch circle with a diameter of 1920mm in a central symmetry manner, the bottoms of the storage tanks 201 are connected with the east/west layer plate of the propulsion cabin through storage tank flanges, and the tops of the storage tanks are connected with the central bearing cylinder 101 through a support consisting of 2 rod pieces. The storage tank 201 is of a spherical-column structure, a mounting flange is arranged near the junction of the lower hemisphere and the column section, the top of the upper hemisphere is provided with a column section, the sphere diameter of the hemisphere is 402mm, the height of the column section is 870mm, and the effective volume is 704L. Two ends of the 2 rod pieces are of hinge structures, and the two ends of the 2 rod pieces can adapt to deformation caused by pressurization and expansion of the storage tank 201.
Fig. 9 is a schematic view of the connection of the gas cylinder of the present embodiment to a remote location engine. The gas cylinders are tiled and symmetrically arranged inside the bearing cylinder column section. The remote engine 204 is arranged at the center of the end part of the central bearing cylinder 101, the engine body exceeds the bottom end of the central bearing cylinder and is connected with the bearing cylinder through a conical support 206, and the engine mounting surface is flush with the satellite-rocket butt joint surface of the central bearing cylinder.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A high orbit satellite platform structure with a central force bearing cylinder type storage box which is connected in parallel and tiled is characterized by comprising a platform structure (1), a propulsion system (2) and a solar cell array (3);
the propulsion system (2) is arranged on the platform structure (1), and the solar cell array (3) is arranged outside the platform structure (1) and can be switched between a folded state and an extended state.
2. The high-orbit satellite platform configuration with the parallelly-tiled central bearing-drum type storage boxes according to claim 1, characterized in that the platform structure (1) is internally provided with a central bearing drum (101), and the propulsion system (2) comprises a plurality of storage boxes (201), a plurality of gas cylinders (202), an attitude control thruster (203) and a remote engine (204);
the gas cylinders (202) are arranged inside the central bearing cylinder (101) and are arranged in a central symmetry manner;
the storage boxes (201) and the attitude control thrusters (203) are arranged along the circumferential direction of the central force bearing cylinder (101), the air cylinders (202) are arranged in a central symmetry manner, and the remote engine (204) is installed at the end part of the central force bearing cylinder (101) and extends to the outside of the central force bearing cylinder (101).
3. The high-orbit satellite platform configuration with the central force-bearing cylinder type storage boxes tiled in parallel according to claim 2 is characterized in that the bottom of the storage box (201) is installed on the platform structure (1) through a mounting flange, and the top of the storage box (201) is connected with the central force-bearing cylinder (101) in a hinged mode.
4. The high orbit satellite platform configuration with parallel tiling of central messenger canisters tanks of claim 1 or claim 2, characterized by the platform structure (1) comprising a platform floor (102), a platform roof (111), side plate assemblies, deck assemblies, a platform lower support frame (103) and a platform upper support frame (108);
the platform top plate (111) is mounted at the top end of a central force bearing cylinder (101) in the platform structure (1), the platform bottom plate (102) is mounted at the bottom end of the central force bearing cylinder (101), an upper platform supporting frame (108), a laminate assembly and a lower platform supporting frame (103) are sequentially mounted between the platform top plate (111) and the platform bottom plate (102), and the upper platform supporting frame (108), the laminate assembly and the lower platform supporting frame (103) are all arranged along the circumferential direction of the central force bearing cylinder (101);
the side plate assembly is arranged along the circumferential direction of the side plate assembly and forms a regular hexahedron structure together with the platform bottom plate (102) and the platform top plate (111).
5. The high orbit satellite platform configuration with parallel tiling of central messenger drums or tanks of claim 4, wherein the side plate assembly comprises an electronics bay south side plate (112), an electronics bay north side plate (114), a propulsion bay first east side plate (116), a propulsion bay second east side plate (117), a propulsion bay first west side plate (118), and a propulsion bay second west side plate (119);
the electronic cabin south side plate (112), the first east side plate (116) of the propulsion cabin, the second east side plate (117) of the propulsion cabin, the north side plate (114) of the electronic cabin, the second west side plate (119) of the propulsion cabin and the first west side plate (118) of the propulsion cabin are sequentially connected to form a regular hexahedron structure and are respectively connected with the supporting frame (108) and the lower supporting frame (103) on the platform to form 6 containing spaces arranged along the circumferential direction of the central bearing cylinder (101).
6. The high orbit satellite platform configuration with parallel tiling of central messenger pods according to claim 5, wherein the deck assembly includes a first propulsion pod east deck (104), a second propulsion pod east deck (113), a first propulsion pod west deck (106), a second propulsion pod west deck (115), an electronics pod south lower deck (105), and an electronics pod north lower deck (107);
the first propulsion cabin east plate (104), the second propulsion cabin east plate (113), the electronic cabin north lower plate (107), the first propulsion cabin west plate (106), the second propulsion cabin west plate (115) and the electronic cabin south lower plate (105) are sequentially arranged around the circumference of the central bearing cylinder (101) in a coplanar manner and are all perpendicular to the axis of the central bearing cylinder (101).
7. The high-orbit satellite platform configuration with the central force-bearing cylinder type storage boxes tiled in parallel according to claim 4, wherein the platform lower supporting frame (103) and the platform upper supporting frame (108) are rod type frames.
8. The high-orbit satellite platform configuration with the central force-bearing barrel type storage boxes tiled in parallel according to claim 5, wherein 2 accommodating spaces corresponding to the south side plate (112) and the north side plate (114) of the electronic cabin are electronic cabins, the platform cabins are used for bearing satellite electronic instrument equipment, and structural members used for bearing in the platform cabins are detachably connected;
the other 4 accommodating spaces are propulsion cabins for bearing the storage box (201), and structural members for bearing in the propulsion cabins are welded.
9. The high-orbit satellite platform configuration with the parallel tiling of the central messenger trunk according to claim 6, wherein the laminate assembly further comprises an electronics bay south upper laminate (109) and an electronics bay north upper laminate (110), the electronics bay south upper laminate (109) being mounted in parallel between the electronics bay south lower laminate (105) and the platform top plate (111) and connected on both sides to the platform upper support frames (108), and the electronics bay north upper laminate (110) being mounted in parallel between the electronics bay north lower laminate (107) and the platform top plate (111) and connected on both sides to the platform upper support frames (108).
10. The high-orbit satellite platform configuration with the central force-bearing cylinder type storage boxes tiled in parallel according to claim 1, wherein the solar cell array (3) adopts a single-wing configuration or a double-wing configuration, wherein the number of folding plates on each wing of the solar cell array (3) is greater than or equal to 2.
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| CN202110271633.6A CN112977882A (en) | 2021-03-12 | 2021-03-12 | High orbit satellite platform structure with central force bearing cylinder type storage boxes tiled in parallel |
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| CN202110271633.6A CN112977882A (en) | 2021-03-12 | 2021-03-12 | High orbit satellite platform structure with central force bearing cylinder type storage boxes tiled in parallel |
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| CN113665843A (en) * | 2021-08-30 | 2021-11-19 | 上海卫星工程研究所 | Surround configuration for deep space exploration |
| CN114212277A (en) * | 2021-12-06 | 2022-03-22 | 航天东方红卫星有限公司 | Satellite structure with high maneuvering and low structural weight |
| CN114229040A (en) * | 2021-12-17 | 2022-03-25 | 中国长城工业集团有限公司 | Separable independent propulsion cabin system |
| CN114295678A (en) * | 2021-12-07 | 2022-04-08 | 北京卫星制造厂有限公司 | Detection equipment for satellite bearing cylinder |
| CN114435627A (en) * | 2022-02-23 | 2022-05-06 | 航天科工空间工程发展有限公司 | Satellite structure and satellite assembly method |
| CN116062362A (en) * | 2023-01-10 | 2023-05-05 | 中国科学院微小卫星创新研究院 | Space storage device |
| CN116513487A (en) * | 2023-07-05 | 2023-08-01 | 北京未来宇航空间科技研究院有限公司 | Multifunctional upper-level configuration and space carrier |
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Application publication date: 20210618 |