CN103863577A - Frame panel type satellite configuration and modular satellite - Google Patents
Frame panel type satellite configuration and modular satellite Download PDFInfo
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- CN103863577A CN103863577A CN201410063030.7A CN201410063030A CN103863577A CN 103863577 A CN103863577 A CN 103863577A CN 201410063030 A CN201410063030 A CN 201410063030A CN 103863577 A CN103863577 A CN 103863577A
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Abstract
The invention provides a frame panel type satellite configuration and a modular satellite adopting the same. The frame panel type satellite configuration comprises a four-edge-column frame and honeycomb structure plates; the four-edge-column frame is used for bearing axial load when being connected with four connecting interfaces for carrying, wherein the four-edge-column frame comprises rod pieces and rod-piece joints; each rod piece is provided with a plurality of bosses; the bosses are provided with installing holes for connection with the honeycomb structure plates by first fasteners; a plurality of through holes are arranged in the extending surfaces of the end parts of the rod pieces and are used for connection with the rod-piece joints by second fasteners; the honeycomb structure plates provide installing surfaces for single satellite equipment and simultaneously provide in-plane shearing rigidity for the four-edge-column frame.
Description
Technical field
The present invention relates to space technology Satellite technical field, relate in particular to a kind of framework panel type satellite configuration of adapt to directly to enter the orbit transmitting, 4 connection modes and adopt the modularization satellite of this configuration.
Background technology
China is a spacefaring nation, country is a lot of to the input of space flight, our satellite cause is in flourish period at present, New Satellite adopts 4 interfaces that are connected with delivery, adopt and directly enter the orbit, do not use traditional band to connect, the quality of satellite is about 1000Kg, need to determine the node configuration of satellite according to these constraint conditions.This New Satellite power is large simultaneously, and density of heat flow rate is high, needs larger heat delivery surface.And owing to adopting the launch mode of directly entering the orbit, when satellite separates with delivery, impact load is larger, needs the structure of satellite to have good impact resistance.
More typical satellite platform has both at home and abroad at present: the U.S. MMS platform based on truss, the east three of the French SPOT satellite platform based on loaded cylinder, domestic Aerospace Science and Technology Corporation, Dong Sipingtai, the CAST968 series platform based on pure plate type structure etc.
The MMS platform of the U.S. is the modularization satellite platform of the U.S. in the seventies development in last century, the triangular prism structure that platform main structure is made up of truss, satellite each several part is all attached in main structure with the form of standardized module, because triangular prism structure can be at axial arbitrary extension, therefore the extendability of this platform and comformability are very strong.The major defect of truss structure is: triangular prism structure in most cases space availability ratio is relatively low, and this configuration also brings certain difficulty to satellite overall configuration layout simultaneously.
" east three ", " east four " platform of the SPOT series satellite platform of France, domestic Aerospace Science and Technology Corporation are the board-like platforms of typical loaded cylinder, its principal feature is using central loaded cylinder as main load-bearing part, utilizes the dashboard that relies on loaded cylinder as apparatus installation plate.By a large amount of employing honeycomb structure composite materials, loaded cylinder plank frame has the design feature that rigidity is high, quality is light, load-carrying capacity is large, and lot of domestic and international Large-scale satellite all selects loaded cylinder plank frame as main structure at present.Loaded cylinder structure is not suitable for total weight 1000kg with interior middle small satellite, due to less demanding to load-carrying capacity, satellite size is relatively little simultaneously, the existence of central cylindrical shape loaded cylinder has often increased layout difficulty in this case, because small satellite does not need large tank conventionally, in the situation that having opening character requirement, loaded cylinder inner space cannot make full use of simultaneously.Therefore for middle-size and small-size satellite and less satellite, generally do not adopt loaded cylinder structure.
CAST968 series platform be Aerospace Science and Technology Corporation since the pure plate type small satellite platform that last century, the nineties was released successively, be full honeycomb structure plate structure.Platform is made up of common platform part and payload module, and common platform structure is made up of base plate, two block length dividing plates, two breviseptums and butt joint ring.In platform inside, four dividing plates, both as apparatus installation plate, form again the main force support structure of satellite together with butt joint ring, platform floor, load ceiling board.Capacity weight cabin structure comprises 4 exterior panels of load ceiling board, load ceiling board and surrounding, and 4 exterior panels seal into common platform and load cabin structure the whole star structure of approximate square.This flat surface is to the middle-size and small-size satellite that does not need large propellant tank, its compact conformation, and opening character is good, and space availability ratio is high, and low cost of manufacture has the incomparable advantage of satellite platform in the past in small satellite field.But pure plate type structural limitations the load-carrying capacity of satellite, existing several satellite total masss are many in 500kg.
Because New Satellite adopts launch mode and 4 connection modes of directly entering the orbit, and existing satellite structure form all adopts butt joint ring to be connected with delivery, inadaptable 4 launch modes that connection is directly entered the orbit.Therefore, need to develop a kind of transmitting that adapts to directly enter the orbit, 4 connection modes, there is good impact property, can adapt to multiple load, be beneficial to several satellite in a rocket transmitting in parallel, there is good heat-sinking capability, can adapt to the new satellite structure of the satellite layout of high heat flux.
Summary of the invention
Technical matters to be solved by this invention is, a kind of framework panel type satellite configuration is provided, and solves prior art Satellite version and all adopts butt joint ring to be connected with delivery, is not suitable with the technical matters of the launch mode that 4 connections directly enter the orbit.
In order to solve the problems of the technologies described above, the invention provides a kind of framework panel type satellite configuration, comprise quadrangular framework and honeycomb panel; Described quadrangular framework is for bearing axial load while joining with 4 connecting interfaces of delivery, wherein said quadrangular framework comprises rod member, rod member joint, described rod member is provided with multiple boss, each boss is provided with mounting hole for being connected with described honeycomb panel by the first fastener, and described Rod end extended surface is provided with multiple through holes for passing through the second fastener connecting rod joint; Described honeycomb panel provides attachment face for satellite stand-alone device, simultaneously for described quadrangular framework provides inplane shear rigidity.
In order to solve the problems of the technologies described above, the present invention also provides a kind of modularization satellite, comprise platform cabin and load cabin, described platform cabin and load cabin all adopt framework panel type satellite configuration of the present invention, on the rod member joint of platform cabin and load cabin abutted surface, be equipped with the connecting bore being connected with cabin section joint, between platform cabin and load cabin, connect by four cabin section joints; The quadrangular framework in described platform cabin adopts the mounting means of 4 connections to adopt satellite-rocket docking joint and delivery to join by rod member, and each satellite-rocket docking joint is provided with a satellite and the rocket disengagement gear; The base plate in described platform cabin has carriage, and carriage is connected with four satellite-rocket docking joints respectively by screw.
The invention has the advantages that: adopt framework panel type satellite configuration be applicable to 4 connections novel delivery connection mode, heat-sinking capability is better, impact resistance is better, load-carrying capacity is better, space availability ratio is high, unit layout is easy, cable louding is convenient, opening character is good, be beneficial to modular design, with low cost.
Accompanying drawing explanation
Fig. 1, the configuration diagram of framework panel type satellite configuration of the present invention;
Fig. 2 A, the rod schematic representation of quadrangular framework of the present invention;
Fig. 2 B, rod member of the present invention and rod member joint connection diagram;
Fig. 3 A-3C, the rod member joint schematic diagram of quadrangular framework described in this specific embodiment;
Fig. 4, modularization satellite schematic diagram of the present invention;
Fig. 5 A, cabin section joint schematic diagram;
Fig. 5 B, the rod member joint schematic diagram being connected with cabin section joint;
Fig. 6 A, satellite-rocket docking face schematic diagram;
Fig. 6 B, satellite-rocket docking joint design schematic diagram
Fig. 7 A, carriage front schematic view;
Fig. 7 B, carriage schematic rear view;
Fig. 7 C, carriage scheme of installation.
The specific embodiment
Below in conjunction with accompanying drawing to framework panel type satellite configuration provided by the invention and adopt the specific embodiment of the modularization satellite that this framework panel type satellite configuration is assembled into elaborate.
First provide by reference to the accompanying drawings the specific embodiment of framework panel type satellite configuration of the present invention.
It shown in accompanying drawing 1, is the configuration diagram of framework panel type satellite configuration described in this specific embodiment.Described framework panel type satellite configuration comprises quadrangular framework and honeycomb panel 11.Described quadrangular framework is for bearing axial load while joining with 4 connecting interfaces of delivery; Described honeycomb panel 11 joins by the first fastener and described quadrangular framework, for satellite stand-alone device provides attachment face, simultaneously for described quadrangular framework provides inplane shear rigidity.Wherein, described quadrangular framework comprises rod member 12, rod member joint 13.Rod member 12 bears axial load, and honeycomb panel 11 bears shearing load, and rod member 12 is connected by multiple screws with honeycomb panel 11.In present embodiment, adopt M5 screw to connect, screw spacing is 80mm-90mm, and screw spacing determines according to magnitude of load on honeycomb panel 11.Wherein, described honeycomb panel 11 can be made up of lead-covering and aluminium honeycomb core.Honeycomb panel 11 is strengthened mutually with quadrangular framework, implementation structure efficiency optimization.
Described framework panel type satellite configuration cross-sectional plane is the unequal rectangle of the length of side, rather than traditional square.Long side direction is as the main heat delivery surface of satellite, for the satellite stand-alone device of large hear rate is installed.Under the prerequisite that increases fraction satellite volume, greatly increase the heat delivery surface of satellite, thereby improved the heat-sinking capability of satellite, adapted to the feature of satellite high heat flux.Owing to adopting rectangular cross section, the lateral dimension of satellite is less simultaneously, and satellite can in parallelly be placed the transmitting that is beneficial to several satellite in a rocket.
Referring to Fig. 2 A, the rod schematic representation of quadrangular framework described in this specific embodiment.Described rod member 12 is provided with multiple boss 121, and each boss 121 is provided with mounting hole 122, for being connected with described honeycomb panel 11 by the first fastener.As preferred embodiment, the mounting hole 122 on each boss 121 of described rod member 12 is tapped bore, for being connected with honeycomb panel 11 by M5 screw.For the consideration of shortening lead time and reduction development cost, described rod member 12 adopts hollow aluminum bar, and in other embodiments, rod member can be used carbon fibre material processing and manufacturing, to realize higher loss of weight requirement.Hollow aluminum bar wall thickness is generally 2-3mm, and diameter is 30-35mm, and a long rod member quality of 1m is about 1Kg.
Described boss 121 is local small boss design, analyzes design changed the form that traditional rod member one encloses boss by optimization, has greatly alleviated the quality of rod member under the prerequisite that does not affect Mechanics of Bar performance.Owing to adopting local small boss design, improve the long typical rod member quality of a rear 1.2m and become 1.13Kg from 1.36Kg, loss of weight 17%, weight loss effect is obvious.Adopt at present the satellite of this framework panel type satellite configuration to complete development and the test of apperance star and first sample star, apperance star adopts traditional rod member form, first sample star adopts the rod member form of optimizing after improving, first sample star loss of weight simultaneously the Rigidity and strength of whole star without reduction.
Described rod member 12 end extended surfaces 123 are provided with multiple rod member through holes 124, for passing through the second fastener connecting rod joint 13.As preferred embodiment, described extended surface 123 is provided with four through holes 124, and described rod member joint 13 is provided with corresponding tapped bore, and described rod member 12 is connected by four M6 screws with described rod member joint 13, and the mounting means assembling that screw connects is better.As Fig. 2 B, rod member and rod member joint connection diagram described in this specific embodiment.Rod member 12 is connected by screw with rod member joint 13, and junction load is larger, adopt multiple screws to connect.In present embodiment, adopt four M6 screws 21 to connect.
Referring to Fig. 3 A-3C, the rod member joint schematic diagram of quadrangular framework described in this specific embodiment.On described rod member joint 13, be provided with tapped bore 131 and lightening hole 132(as shown in Figure 3A with rod member 12 connecting parts); Rod member joint 13 adopts screw to be connected with rod member 12 by tapped bore 131; On rod member joint 13, be processed with lightening hole 132 to alleviate joint quality.On described rod member joint 13, the one side relative with described lightening hole 132 is provided with lifting eye 133(as shown in Figure 3 B), lifting eye 133 can be for being located at the larger tapped bore on rod member joint 13.When installation, lifting eye 133, towards satellite structure outside, is realized whole star lifting (as shown in Figure 3 C) in order to be connected with suspension rod 31.Described rod member joint 13 can be set to three masks the tapped bore 131 joining with rod member 12, also can be set to four sides and have the tapped bore 131 joining with rod member 12.For the consideration of shortening lead time and reduction development cost, described rod member joint 13 adopts aluminum material to make, and in other embodiments, rod member joint can be used carbon fibre material processing and manufacturing, to realize higher loss of weight requirement.
Framework panel type satellite configuration of the present invention is using quadrangular framework as main supporting structure, can well adapt to deliver the interface of 4 novel connections, each side of quadrangular install instruments plate or instrument container, each dashboard or instrument container are separate, dismounting is flexible, and opening character is good.Emphasize integrated design in platform inside, externally emphasize General design, platform and load mechanical interface are simple, and thermal coupling is little.Adopt framework panel type configuration, satellite main structure does not have brace, and satellite spatial resource utilization is high, and unit layout is easy, good for the comformability of middle small satellite.
Next provide by reference to the accompanying drawings the specific embodiment of modularization satellite of the present invention.
With reference to accompanying drawing 4, modularization satellite of the present invention comprises platform cabin 42 and load cabin 41.Described platform cabin 42 and load cabin 41 all adopt framework panel type satellite configuration of the present invention, on the rod member joint 43 of platform cabin 42 and load cabin 41 abutted surfaces, be equipped with the connecting bore being connected with cabin section joint 44, between platform cabin 42 and load cabin 41, connect by four cabin section joints 44.The quadrangular framework in described platform cabin 42 adopts the mounting means of 4 connections to adopt satellite-rocket docking joint 46 and delivery to join by rod member 45, and each satellite-rocket docking joint 46 is provided with a satellite and the rocket disengagement gear; The base plate 47 in described platform cabin 42 has carriage 48, and carriage 48 is connected with four satellite-rocket docking joints 46 respectively by screw.Framework panel type satellite configuration can need to carry out modularization, subdivisionization design according to satellite task; The extendability of framework panel type satellite configuration is very good, and according to the difference of task, the size in platform cabin 42 and load cabin 41 all can zoom in or out separately.
With reference to figure 5A, cabin section joint schematic diagram.Section joint 44 two ends, described cabin are equipped with multiple through holes 441, and described cabin section joint 44 adopts M10 screw to be connected with the rod member joint 43 on platform cabin 42 and load cabin 41 respectively by through hole 441.Cabin section joint 44 is universal joint, symmetrical up and down, can change its form according to the difference of load.Cabin section joint 44 is larger to whole star stiffness effect, in present embodiment, described cabin section joint 44 can adopt titanium alloy material to make, titanium alloy has higher Rigidity and strength, coefficient of thermal conductivity is less simultaneously, effectively the heat transfer of two cabin sections of isolation, is conducive to two cabin independence thermal designs, analysis, test.Section joint 44 two ends, described cabin can also be provided with lightening hole 442, to realize loss of weight requirement in the situation that meeting rigidity.
With reference to figure 5B, the rod member joint schematic diagram being connected with cabin section joint.Described rod member joint 43 is configured to three connecting rods 45, and one side is connected with cabin section joint 44.On each that rod member joint 43 is connected with rod member 45, be equipped with corresponding tapped bore 431 and corresponding lightening hole 432.The one side that rod member joint 43 is connected with cabin section joint 44 is provided with corresponding connecting bore 433 and corresponding lightening hole 434.Cabin section joint 44 is connected by four M10 screws with the rod member joint 43 of quadrangular framework, adopts M10 screw to connect to guarantee its coupling stiffness.
With reference to figure 6A, satellite-rocket docking face schematic diagram.New Satellite adopts 4 modes that are connected with delivery, rather than traditional band connection mode, and satellite and delivery only have four satellite-rocket docking faces 61, joins by rod member 45 and satellite-rocket docking joint 46.On each satellite-rocket docking face 61, there is a disengagement gear mounting hole 62, for satellite and the rocket disengagement gear is installed.
With reference to figure 6B, satellite-rocket docking joint design schematic diagram.Satellite-rocket docking joint 46 one end are provided with connecting bore 461 and lightening hole 462.Satellite-rocket docking joint 46 adopts multiple the 4th fasteners to be connected with the through hole on vertical rod member 45 on quadrangular framework by connecting bore 461, adopt in the present embodiment four M10 screws to connect, adopting M10 screw is in order to obtain larger coupling stiffness, increases the integral rigidity of satellite.Because satellite-rocket docking joint 46 and vertical rod member 45 are connected by screw, increase linkage interface, thus actv. attenuate shock.According to Impulse Test Result, linkage interface can reduce approximately 53% shock response.
Satellite-rocket docking joint 46 1 sides are provided with disengagement gear mounting hole 463 for satellite and the rocket disengagement gear is installed.Satellite adopts four satellite and the rocket disengagement gears to separate with delivery, has a M12 bolt in each satellite and the rocket disengagement gear, is exploded and is separated release by priming system.There is priming system satellite and the rocket disengagement gear inside, and priming system detonates and separates satellite and rocket, now can cause larger impact, in order not destroy the stand-alone device of whole star, needs to reduce the shock response being delivered in stand-alone device.Satellite-rocket docking joint is the pass heavy mail of whole main frame, and the rigidity of joint directly affects the rigidity of whole star.In present embodiment, satellite-rocket docking joint 46 adopts aluminum alloy materials, and the damping force characteristics of aluminum alloy is better than steel and titanium, adopts aluminum alloy materials can under the prerequisite that obtains better damping force characteristics, guarantee the rigidity of whole star.
Described in each, satellite-rocket docking joint 46 all adopts cavity structure, and this version can actv. attenuating shock wave, reduces shock response, slows down the shock response being delivered in stand-alone device.Design and increase linkage interface by cavity structure, while having reduced significantly satellite and the rocket separation, being delivered to the shock response on satellite body.
A side relative with being provided with disengagement gear mounting hole 463 on satellite-rocket docking joint 46 is provided with the through hole 464 joining with carriage 48, and satellite-rocket docking joint 46 adopts screw to be connected with carriage 48 one end by through hole 464.On satellite-rocket docking joint 46, be also provided with the lifting eye 133 of hanger erection hole 465(with Fig. 3 B), realize whole star lifting in order to be connected with suspension rod 31.
With reference to figure 7A-7C, wherein, Fig. 7 A is carriage front schematic view; Fig. 7 B is carriage schematic rear view; Fig. 7 C is carriage scheme of installation.
Because New Satellite adopts 4 mounting meanss that are connected with delivery, satellite base plate 47 does not have butt joint ring to support below, in order to improve the Rigidity and strength of base plate, has designed a carriage 48 below base plate 47.On the framework of carriage 48, be respectively equipped with corresponding mounting hole 481, carriage 48 adopts screw 71 to be connected with base plate 47 by mounting hole 481.Four ends of carriage 48 are respectively equipped with corresponding connecting bore 482, and carriage 48 adopts screw 72 to be connected with the through hole 464 of satellite-rocket docking joint 46 by connecting bore 482, thereby is connected with four satellite-rocket docking joints 46 respectively.And because carriage 48 links together four satellite-rocket docking joints 46, increase lateral stiffness and the intensity of whole star.
Modularization satellite of the present invention adopts framework panel type satellite configuration of the present invention, has the following advantages:
1) the novel delivery connection mode of applicable 4 connections: satellite adopts Novel connection type, adopts framework panel type structure, can shorten Path of Force Transfer, improves structure efficiency.In framework, rod member can bear larger axial load, and the load of satellite is directly delivered on the base of satellite by vertical rod member.---structural slab of unit is installed, and---rod member---satellite base---delivers load trans path: unit load.Satellite adopts four bottom fittings (satellite-rocket docking joint) to be connected with delivery, and four satellite-rocket docking joints of satellite are directly sitting on the support frame of delivery, middle by four independently satellite and the rocket disengagement gear interconnect, connection mode is simple and reliable.
2) heat-sinking capability is good: satellite framework cross-sectional plane adopts square-section, rather than traditional square.Long side direction is as the main heat delivery surface of satellite, the unit of large hear rate is installed on the main heat delivery surface of satellite, under the prerequisite that increases fraction satellite volume, greatly increase the heat delivery surface of satellite, thereby improved the heat-sinking capability of satellite, adapted to the feature of satellite high heat flux.Owing to adopting rectangular cross section, the lateral dimension of satellite is less simultaneously, and satellite can in parallelly be placed the transmitting that is beneficial to several satellite in a rocket.
3) impact resistance is good: satellite-rocket docking joint is cavity structure, and cavity structure is obvious for the attenuation characteristic of shock wave, and this structure can actv. attenuate shock.Because satellite-rocket docking joint and vertical rod member are connected by screw, can obtain larger coupling stiffness simultaneously, increase the integral rigidity of satellite, and increased linkage interface, thus actv. attenuate shock.According to Impulse Test Result, linkage interface can reduce approximately 53% shock response.Design and increase linkage interface by cavity structure, while having reduced significantly satellite and the rocket separation, being delivered to the shock response on satellite body.
4) load-carrying capacity is better: the rod member in framework is used for bearing concentrated force, and rod member is better than bending block at axial pressurized examining tensile behavior, relative and pure plate type structure, and its load-carrying capacity is better.
5) space availability ratio is high: the direction each other of the rod member in framework is orthogonal, there is no brace, and its stability is guaranteed by bending block.Owing to there is no brace, space availability ratio improves greatly.
6) unit mounting arrangement is easy: framework panel type configuration is because inside does not have inclined member, and because of the supporting role of framework, veneer area is larger, flexibly mounting arrangements unit simultaneously.Unit can first be arranged on structural slab, and the cable between unit in plate is connected, and then integral installation is on the main frame of satellite.When unit is installed, structural slab is flat condition, installs very conveniently, and easily operation, has increased safety when installation.And conventional satellite unit while installing structural slab be generally vertical state, unit installation difficulty is large and safety is not high.
7) cable louding facility: framework panel type configuration does not have the framing members such as center loaded cylinder and dividing plate, and satellite center is hollow configuration, is convenient to the trend of cable.In actual applications, cable can move towards along rod member, and can fix along rod member colligation, and with respect to the satellite of other structures, cable louding, colligation are fixed relatively easy.
8) opening character is good: the satellite of framework panel type configuration, structural slab is arranged on the framework of satellite, unit is arranged on the structural slab of satellite, the structural slab of satellite does not connect each other, can be from the outside the structural slab of dismounting satellite and unit thereof easily.
9) be beneficial to modular design: framework panel type configuration is beneficial to the modularization of satellite, from large aspect, satellite can be divided into platform cabin and load cabin, each cabin section is framework panel type configuration, connects each other easy accessibility by cabin section joint.From little aspect, for independent platform cabin or load cabin, each structure plates can be made modularization.Such as the structural slab having is installed power-supply system unit, power system modules that Here it is; Some structural slabs are installed TT&C system unit, TT&C system module that Here it is.
10) with low cost: framework panel type configuration is generally made up of aluminium chassis and lead-covering bending block, aluminium chassis processing is simple, cheap, the satellite total expense of a 1000Kg magnitude is no more than 2,000,000, with respect to load cartridge type satellite six or a seven hundred contingency loaded cylinder easily, framework panel type configuration is with low cost.Meanwhile, framework panel type configuration also has short feature of process-cycle, and the process-cycle is about 20 days, and the composite material load-carrying cylinder process-cycle reached about half a year.The feature that framework panel type configuration is with low cost, the process-cycle is short is beneficial to the mass production of satellite.And framework panel type configuration has been tested and appraised the examination of grade mechanical test.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the premise without departing from the principles of the invention; can also make some improvements and modifications, these improvements and modifications also should be considered as protection scope of the present invention.
Claims (11)
1. a framework panel type satellite configuration, is characterized in that, comprises quadrangular framework and honeycomb panel;
Described quadrangular framework is for bearing axial load while joining with 4 connecting interfaces of delivery, wherein said quadrangular framework comprises rod member, rod member joint, described rod member is provided with multiple boss, each boss is provided with mounting hole for being connected with described honeycomb panel by the first fastener, and described Rod end extended surface is provided with multiple through holes for passing through the second fastener connecting rod joint;
Described honeycomb panel provides attachment face for satellite stand-alone device, simultaneously for described quadrangular framework provides inplane shear rigidity.
2. framework panel type satellite configuration according to claim 1, is characterized in that, the mounting hole on each boss of described rod member is tapped bore, for being connected with honeycomb panel by M5 screw; Described Rod end extended surface is provided with four through holes, and described rod member joint is provided with corresponding tapped bore, and described rod member is connected by four M6 screws with described rod member joint.
3. framework panel type satellite configuration according to claim 2, is characterized in that, on described rod member joint, is provided with lightening hole with rod member connecting part; On described rod member joint, the one side relative with described lightening hole is provided with lifting eye, and when installation, lifting eye, towards satellite structure outside, is realized whole star lifting in order to be connected with suspension rod.
4. framework panel type satellite configuration according to claim 3, is characterized in that, described rod member adopts hollow aluminum bar, and described rod member joint adopts alumina based material to make, or described rod member and rod member joint all adopt carbon fibre material to make.
5. framework panel type satellite configuration according to claim 1, is characterized in that, described honeycomb panel is made up of lead-covering and aluminium honeycomb core.
6. framework panel type satellite configuration according to claim 1, is characterized in that, described framework panel type satellite configuration cross-sectional plane is the unequal rectangle of the length of side, and long side direction is as the main heat delivery surface of satellite, for the satellite stand-alone device of large hear rate is installed.
7. a modularization satellite, comprises platform cabin and load cabin, it is characterized in that,
Described platform cabin and load cabin all adopt the framework panel type satellite configuration described in claim 1-6 any one, on the rod member joint of platform cabin and load cabin abutted surface, be equipped with the connecting bore being connected with cabin section joint, between platform cabin and load cabin, connect by four cabin section joints;
The quadrangular framework in described platform cabin adopts the mounting means of 4 connections to adopt satellite-rocket docking joint and delivery to join by rod member, and each satellite-rocket docking joint is provided with a satellite and the rocket disengagement gear;
The base plate in described platform cabin has carriage, and carriage is connected with four satellite-rocket docking joints respectively by screw.
8. modularization satellite according to claim 7, is characterized in that, described cabin section joint adopts titanium alloy material to make, and its two ends are connected with the rod member joint on platform cabin and load cabin respectively by M10 screw.
9. modularization satellite according to claim 7, is characterized in that, described in each, satellite-rocket docking joint all adopts cavity structure, is connected with the corresponding rod member of described quadrangular framework by multiple the 4th fasteners.
10. modularization satellite according to claim 9, is characterized in that, described in each, satellite-rocket docking joint is connected with corresponding rod member by four M10 screws.
11. framework panel type satellite configurations according to claim 10, is characterized in that, described satellite-rocket docking joint adopts aluminum alloy materials.
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| CN111936389A (en) * | 2018-02-19 | 2020-11-13 | 马扎罗姆进出口有限公司 | Small-sized artificial satellite, CARD-SAT " |
| CN112052540A (en) * | 2020-09-09 | 2020-12-08 | 哈尔滨工业大学 | Architecture of small satellite for supporting ultrahigh power consumption |
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| US10407189B1 (en) | 2016-10-27 | 2019-09-10 | Space Systems/Loral, Llc | Spacecraft exoskeleton truss structure |
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| CN111936389A (en) * | 2018-02-19 | 2020-11-13 | 马扎罗姆进出口有限公司 | Small-sized artificial satellite, CARD-SAT " |
| CN111936389B (en) * | 2018-02-19 | 2024-02-20 | 马扎罗姆进出口有限公司 | Small-sized artificial satellite- "CARD-SAT" |
| US11242161B1 (en) * | 2018-05-24 | 2022-02-08 | David Michael White | Cube-shaped primary structure module |
| CN108791953A (en) * | 2018-06-15 | 2018-11-13 | 上海卫星工程研究所 | A kind of trapezoidal moonlet structure for adapting to carry |
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| CN112052540A (en) * | 2020-09-09 | 2020-12-08 | 哈尔滨工业大学 | Architecture of small satellite for supporting ultrahigh power consumption |
| CN112124627A (en) * | 2020-09-28 | 2020-12-25 | 中国科学院微小卫星创新研究院 | Flexible satellite platform structure |
| CN112124606A (en) * | 2020-09-30 | 2020-12-25 | 中航(成都)无人机系统股份有限公司 | But modularization equipment's airborne nacelle |
| CN112319867A (en) * | 2020-10-29 | 2021-02-05 | 上海宇航系统工程研究所 | Ejection type connecting and separating integrated device |
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