CN110525688A - A kind of in-orbit restructural expansible satellite system - Google Patents
A kind of in-orbit restructural expansible satellite system Download PDFInfo
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- CN110525688A CN110525688A CN201910723209.3A CN201910723209A CN110525688A CN 110525688 A CN110525688 A CN 110525688A CN 201910723209 A CN201910723209 A CN 201910723209A CN 110525688 A CN110525688 A CN 110525688A
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- orbit
- load
- extension
- satellite
- satellite system
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Classifications
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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
-
- 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
-
- 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 present invention provides a kind of in-orbit restructural expansible satellite system, belongs to spacecraft configuation technical field.The satellite system have the characteristics that it is in-orbit it is restructural, it is in-orbit it is expansible, equipment is replaceable, is suitable for polymorphic type load.It include: satellite basic platform, extension truss and Solid rocket engine module bay.Its Satellite basic platform uses subdivision design, including propelling module, equipment compartment and load cabin, is connected between each bay section by bay section mating interface, thus can carry out the replacement and extension of bay section grade.Equipment compartment and load cabin use octoploids structure, wherein four faces installations of equipment compartment can in-orbit more exchange device, the design of four additional face have can in-orbit extension interface, the in-orbit extension for satellite system.Load cabin top surface layout has load generalization to install interface, is suitable for multiple types load.Extension truss and Solid rocket engine module bay are used to meet the in-orbit extension of whole star system of large-scale load application demand, are emitted as needed by transporter aircraft and are entered the orbit.
Description
Technical field
The present invention relates to a kind of satellite configurations, and in particular to a kind of in-orbit restructural expansible satellite system belongs to and defends
Star construction techniques field.
Background technique
In-orbit service, which refers to, to be cooperateed in space by people, robot or both to complete to be related to extend the in-orbit spacecraft longevity
Order or promoted maintenance, Space configuration and the service role of its ability.The application of in-orbit service technology can reduce spacecraft task
Life cycle costing extends spacecraft life cycle, promotes payload reliability, promote spacecraft performance, increase task operating
Freedom degree flexible and that increase spacecraft ground is integrated.But realize in-orbit service premise be space system should have it is in-orbit can group
Dress, restructural, expansible ability, can receive in-orbit service.
Summary of the invention
In view of this, the present invention provides a kind of in-orbit restructural expansible satellite system, satellite system can be adapted to
The technical need for polymorphic type multistage load of uniting meets the in-orbit load extension of space system, on-orbit performance extension, in-orbit reconstruct etc.
Application demand.
The in-orbit restructural expansible satellite system includes: satellite basic platform；The satellite basic platform packet
Three bay sections are included, load cabin, equipment compartment and propelling module are respectively as follows:；
The load cabin, equipment compartment and propelling module are relatively independent, are successively docked by bay section mating interface, are used for bay section grade
In-orbit replacement or extension；
The load cabin has more than two sides, one of them is set-mounted by in-orbit replaceable interface with upper side
Equipment, the in-orbit replacement for device level；In-orbit replaceable interface is reserved in setting on other sides, is existed for device level
Rail extension；The load cabin top surface is provided with load universalized connection, for carrying different types of load；
In-orbit replacement of the equipment compartment side by the set-mounted equipment of in-orbit replaceable interface, for device level；Together
When be disposed on the equipment compartment it is in-orbit arrest mating interface, be used for and provide the spacecraft launching site of in-orbit service, defend this
Star system is provided the spacecraft capture of in-orbit service.
As a kind of preferred embodiment of the invention: further include: extension truss, the extension truss pass through extension truss interface
It is connect with the satellite basic platform, forms load mounting platform.
As a kind of preferred embodiment of the invention: further include: more than two Solid rocket engine module bays, two or more described in push away
Into control module cabin distributing installation on the extension truss；One Solid rocket engine is installed in each Solid rocket engine module bay
Submodule, more than two Solid rocket engine submodules form the Solid rocket engine unit of the satellite system.
As a kind of preferred embodiment of the invention: installing institute by in-orbit replaceable interface on the Solid rocket engine module bay
Equipment is needed, and reserves in-orbit replaceable interface.
As a kind of preferred embodiment of the invention: being provided with solar wing more alias on the equipment compartment, solar wing is logical
It crosses the solar wing more alias to be mounted on the equipment compartment, the solar wing more alias is in-orbit for the solar wing
Replacement.
As a kind of preferred embodiment of the invention: being provided with docking filling on the satellite and the rocket parting surface of the propelling module and connect
Mouthful, the in-orbit filling for propellant.
The utility model has the advantages that
(1) it is connected between the different bay sections of satellite basic platform by bay section mating interface, can be realized the replacement of bay section grade
And Longitudinal Extension；Load cabin side layout have extension truss interface, with its octoploids structure ining conjunction with, it can be achieved that load cabin transverse direction
Multi-direction extension/reconstruct；Equipment compartment and load cabin lateral layout have in-orbit replacement unit interface, can be realized equipment it is in-orbit more
It changes/extends；It can be realized satellite system bay section grade, replaceable, expansible, the restructural characteristic of device level by above structure.
(2) it is replaceable interface that equipment compartment surface, which is used to connect the interface of solar wing, can be realized the replacement of solar wing/liter
Grade；
(3) satellite and the rocket parting surface layout has docking filling interface, can be realized the in-orbit filling of fuel.
(4) satellite system layout has extension truss and propulsion die control cabinet, the load general-purpose interface with load cabin top surface
In conjunction with can be realized the in-orbit extension of load.In conjunction with above-mentioned replaceable, restructural, expansible feature, enable satellite platform
The installation requirements for meeting multitask stage different type, different size scale load, improve the flexibility of task on star, embody
The flexible bearing capacity of satellite platform.Meanwhile above-mentioned characteristic makes satellite have in-orbit assembling ability, is adapted to ultra-large type load
The installation requirements of lotus limit the size and weight that load gets rid of rocket delivery transmitting on star.
(5) the bay section mating interface designed between different bay sections, while it is relatively independent to realize each bay section, makes each bay section can
General assembly and test are individually carried out, so that the general assembly of satellite, test job can be carried out parallel, is realized eventually by bay section mating interface
It is connected between bay section, improves the efficiency and reliability of satellite assembly, test.
Detailed description of the invention
Fig. 1 is the overall structure diagram of the satellite system (equipped with oversize microwave remote sensing load)；
Fig. 2 is the exploded view of satellite basic platform (equipped with microwave remote sensing load)；
The in-orbit status diagram of satellite when Fig. 3 is equipped with optical remote sensing load (for showing satellite and the rocket parting surface)；
Fig. 4 is the emission state schematic diagram of the satellite system equipped with optical remote sensing load；
The in-orbit status diagram of satellite when Fig. 5 is equipped with optical remote sensing load；
Fig. 6 is the emission state schematic diagram of the satellite system equipped with microwave antenna load；
Fig. 7 is the satellite system structural schematic diagram equipped with large scale microwave remote sensing load；
Fig. 8 is the satellite system structural schematic diagram equipped with oversize microwave remote sensing load；
Fig. 9 is the satellite system structural schematic diagram equipped with very big size microwave remote sensing load.
Wherein: 1- docking filling interface, 2- optical remote sensing load, 3- load cabin, 4- equipment compartment, 5- propelling module, 6- bay section
Mating interface, 7- can the in-orbit in-orbit replaceable units B of replacement unit A, 8-, 9- microwave antenna load, 10- are in-orbit replaceable to be connect
Mouthful, 11- solar wing more alias, 12- satellite basic platform is in-orbit to arrest mating interface, 13- microwave remote sensing load, 14- extension
Truss interface, 15- large scale microwave remote sensing load, 16- satellite basic platform, 17- extension truss, 18- Solid rocket engine module bay,
19- solar wing, 20- oversize microwave remote sensing load, the very big size microwave remote sensing load of 21-
Specific embodiment
The present invention will now be described in detail with reference to the accompanying drawings and examples.
Embodiment 1:
The present embodiment provides a kind of in-orbit restructural expansible satellite systems, and it is more can to adapt to spacecraft polymorphic type
The technical need of stage load meets the application demands such as the in-orbit load extension of space system, on-orbit performance extension, in-orbit reconstruct.
As shown in Figure 1, the satellite system includes: satellite basic platform 16, extends truss 17 and Solid rocket engine module bay 18,
Each section by mechanical arm or climbing robot in-orbit assembling formation, robot/mechanical arm by carry out in-orbit service spacecraft
It provides, which is the satellite system of acceptable in-orbit service.Its Satellite basic platform 16 is entire satellite system
The core of system provides most of function of satellite system；Extension truss 17 is used to provide support for ultra-large type load；Solid rocket engine
Module bay 18 plays the role of adjusting ultra-large type load surface accuracy.
Satellite basic platform 16 is entered the orbit by carrier rocket transmitting, as shown in Fig. 2, satellite basic platform 16 includes: load
Cabin 3, equipment compartment 4 and propelling module 5, load cabin 3, equipment compartment 4 and propelling module 5 are all made of octoploids structure, and are docked by bay section
Interface successively docks, and after the locking of bay section mating interface is by its two connected bay section, meets the rigidity of the in-orbit connection of setting
And intensity requirement, and the transmitting for the information, energy (electricity), hot-fluid being able to carry out between bay section, while bay section mating interface can be with
Mechanical arm cooperation, realizes bay section grade replacement/Longitudinal Extension.
Load cabin 3 is designed using truss-like main force support structure and octahedral configuration, has preferable opening character, is in-orbit
Replacement and extension provide precondition.Four sides are used to install existing device in eight sides of load cabin 3, and installed
Equipment passes through in-orbit replaceable interface and installs, enable the equipment installed in load cabin 3 by in-orbit replaceable interface be it is in-orbit can
Unit B 8 is replaced, thus, it is possible to realize the in-orbit replacement of device level；In-orbit replaceable interface 10 is provided on four additional side,
Expansion equipment is connected by in-orbit replaceable interface 10 with load cabin 3, is realized the in-orbit extension of device level, is thus provided load cabin
3 in-orbit expansible/replaceable abilities.The expansion equipment locking it after the in-orbit connection of replaceable interface 10 and being connected, locking state
The bonding strength and rigidity requirement for meeting ascent stage (the satellite launch stage) and in-orbit stage apparatus and load cabin 3 have quickly
Swap capabilities can pass for the in-orbit replacement of mechanical arm between satellite basic platform and in-orbit replaceable units B8/ expansion equipment
Pass energy (electricity), information, hot-fluid etc..
The design of 3 top surface of load cabin has load universalized connection, can load the different types such as optical remote sensing, microwave antenna load
Load, as Fig. 4 and Fig. 5 be respectively 3 top surface of load cabin load optical remote sensing load 2 satellite launch and in-orbit status diagram,
Fig. 6 is the satellite launch status diagram that 3 top surface of load cabin loads microwave antenna load 9.
Equipment compartment 4 uses truss-like primary load bearing configuration, has preferable opening character, can the in-orbit spirit for replacing unit with satisfaction
Layout living.Meanwhile equipment compartment 4 is designed using octoploids structure, 4 one end of equipment compartment is right by bay section mating interface 6 and load cabin 3
It connects, the other end is docked by bay section mating interface 6 with propelling module 5.The equipment for being mounted on 4 side of equipment compartment passes through in-orbit replaceable
Interface is installed, and enabling the equipment installed on equipment compartment 4 by in-orbit replaceable interface is in-orbit replaceable units A7, thus, it is possible to
The in-orbit replacement for enough realizing device level on equipment compartment 4, that is, realize the multi-direction in-orbit extension of equipment compartment transverse direction, this characteristic and cabin
Section grade Longitudinal Extension characteristic combine (bay section grade longitudinally refers in future when three cabin structures are unsatisfactory for demand, can load cabin,
Increase equipment compartment between propelling module, become four cabin structures even five cabin structures), further enhance the expansible of equipment compartment 4
Characteristic, i.e. equipment compartment 4 can need to carry out vertical or horizontal extension according to task.
Solar wing 19 is mounted on equipment compartment 4, and the junction of solar wing 19 and equipment compartment 4 is provided with solar wing more changing-over
Mouth 11, i.e. solar wing 19 are connected by solar wing more alias 11 with equipment compartment 4, and solar wing more alias 11 connects solar wing 19
It is locked afterwards, the stiffness and strength requirement of the in-orbit connection of setting is met after locking, and solar wing more alias 11 has fastly
Fast swap capabilities are for the in-orbit replacement solar wing 19 of mechanical arm.Thus the satellite system is made to have the in-orbit replacement of solar wing, performance
The ability of upgrading adapts to demand of the different loads to power by the in-orbit replacement of solar wing.
Be disposed on equipment compartment 4 simultaneously it is in-orbit arrest mating interface 12, so that satellite system is provided in-orbit service
Spacecraft capture implements the operations such as in-orbit replacement, reconstruct or extension to this satellite system in order to provide in-orbit service spacecraft.
Propelling module 5 uses truss-like main force support structure, realizes integrated power transmission, passes through bay section mating interface 6 and equipment compartment 4
It is connected, to adapt to the replaceable demand of bay section.Another visual angle of satellite basic platform 16 is as shown in figure 3, the satellite and the rocket in propelling module 5 divide
From be provided on face docking filling interface 1, so that satellite basic platform 16 is had on-board propulsion agent filled function, realize fuel
Rail filling, docking filling interface 1 are used to be connected with external propellant filing provision, and propellant loading equipment is locked after connection, and
Locking state meets in-orbit Status satellite platform and implements the coupling stiffness and intensity requirement of filling satellite, can carry out the biography of fuel
It passs.
Extension truss interface 14 is additionally provided in load cabin 3, extension truss interface 14 (expands for connecting extension truss 17
Exhibition truss 17 is connect by extending truss interface 14 with satellite basic platform 16), load mounting platform is formed, in-orbit truss is passed through
It extends to adapt to the assembly demand of ultra-large load.The extension design of truss 17 has reusable interface, meets satellite platform
In-orbit multi-direction extension demand.
Embodiment 2:
On the basis of above-described embodiment 1, when the load installed is larger, when so that the satellite system is larger, to protect
The Solid rocket engine module that original is mounted in satellite basic platform 16 is divided into two by the dynamic stability for demonstrate,proving the satellite platform
The above Solid rocket engine submodule, each Solid rocket engine submodule are mounted in a Solid rocket engine module bay 18, Solid rocket engine mould
Block cabin 18 is standard small cabin, and distributing installation is on extension truss 17, and the satellite system is steady when guaranteeing carrying large size load
It is qualitative.Equipment needed for being installed on Solid rocket engine module bay 18 by in-orbit replaceable interface, and in-orbit replaceable interface is reserved, make
It has the in-orbit replacement of certain equipment and propagation energy.
Ultra-large type load installation satellite is collectively formed in extension truss 17 and satellite basic platform 16, Solid rocket engine module bay 18
Platform.
The satellite platform can carry various sizes of microwave antenna load it can be seen from Fig. 7 to Fig. 9, further,
Extending the continuous extension of truss and Solid rocket engine module, it is ensured that satellite platform adapts to the matching requirements of ultra-large load,
It realizes the in-orbit application of ultra-large load, solves traditional rocket delivery transmitting and the limitation of Space Vehicle System size and scale is asked
Topic.
Related extension truss 17 and Solid rocket engine module bay 18 are carried transmitting and are entered the orbit by world aircraft of round transporting,
And it is sent by orbit transfer vehicle to task track.
To sum up, the above is merely preferred embodiments of the present invention, it is not intended to limit the scope of the present invention.It is all
Within the spirit and principles in the present invention, any modification, equivalent replacement, improvement and so on should be included in protection of the invention
Within the scope of.
Claims (7)
1. a kind of in-orbit restructural expansible satellite system characterized by comprising satellite basic platform (16)；It is described to defend
Star basic platform (16) includes three bay sections, is respectively as follows: load cabin (3), equipment compartment (4) and propelling module (5)；
The load cabin (3), equipment compartment (4) and propelling module (5) are relatively independent, are successively docked, are used for by bay section mating interface
The in-orbit replacement or extension of bay section grade；
The load cabin (3) has more than two sides, one of them is set-mounted by in-orbit replaceable interface with upper side
Equipment, the in-orbit replacement for device level；In-orbit replaceable interface (10) are reserved in setting on other sides, are used for device level
In-orbit extension；Load cabin (3) top surface is provided with load universalized connection, for carrying different types of load；
In-orbit replacement of equipment compartment (4) side by the set-mounted equipment of in-orbit replaceable interface, for device level；Simultaneously
Be disposed on the equipment compartment (4) it is in-orbit arrest mating interface (12), be used for and provide the spacecraft launching site of in-orbit service, make
The satellite system is provided the spacecraft capture of in-orbit service.
2. in-orbit restructural expansible satellite system as described in claim 1, it is characterised in that: further include: extension truss
(17), the extension truss (17) is connect by extending truss interface (14) with the satellite basic platform (16), forms load
Mounting platform.
3. in-orbit restructural expansible satellite system as claimed in claim 2, it is characterised in that: further include: it is more than two
Solid rocket engine module bay (18), more than two Solid rocket engine module bay (18) distributing installations are in the extension truss (17)
On；One Solid rocket engine submodule, more than two Solid rocket engine are installed in each Solid rocket engine module bay (18)
Module forms the Solid rocket engine unit of the satellite system.
4. in-orbit restructural expansible satellite system as claimed in claim 3, it is characterised in that: the Solid rocket engine module
Equipment needed for being installed on cabin (18) by in-orbit replaceable interface, and reserve in-orbit replaceable interface.
5. in-orbit restructural expansible satellite system as claimed in claim 1,2 or 3, it is characterised in that: in the equipment
Solar wing more alias (11) is provided on cabin (4), solar wing (19) is mounted on institute by the solar wing more alias (11)
It states on equipment compartment (4), the solar wing more alias (11) is used for the in-orbit replacement of the solar wing (19).
6. in-orbit restructural expansible satellite system as claimed in claim 1,2 or 3, it is characterised in that: in the propulsion
Docking filling interface (1), the in-orbit filling for propellant are provided on the satellite and the rocket parting surface in cabin (5).
7. in-orbit restructural expansible satellite system as claimed in claim 1,2 or 3, it is characterised in that: the load cabin
(3), equipment compartment (4) and propelling module (5) are all made of octoploids structure.
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| CN201910723209.3A CN110525688B (en) | 2019-08-06 | 2019-08-06 | On-orbit reconfigurable extensible satellite system |
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| CN201910723209.3A CN110525688B (en) | 2019-08-06 | 2019-08-06 | On-orbit reconfigurable extensible satellite system |
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| CN110525688A true CN110525688A (en) | 2019-12-03 |
| CN110525688B CN110525688B (en) | 2020-09-25 |
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| CN111409871A (en) * | 2020-03-19 | 2020-07-14 | 上海卫星工程研究所 | Satellite platform configuration with extendable truss node pods |
| CN111409878A (en) * | 2020-03-19 | 2020-07-14 | 上海卫星工程研究所 | Open type assembled module platform cabin structure |
| CN111422378A (en) * | 2020-03-10 | 2020-07-17 | 上海卫星工程研究所 | Static orbit ultra-large type assembled satellite platform configuration and in-orbit assembly method |
| CN112093081A (en) * | 2020-09-27 | 2020-12-18 | 中国科学院微小卫星创新研究院 | Solar wing microwave remote sensing integrated load and control method thereof |
| CN112265656A (en) * | 2020-09-23 | 2021-01-26 | 北京空间飞行器总体设计部 | Packaging and containing type on-orbit assembly device and method for long-length antenna |
| CN112404984A (en) * | 2020-12-01 | 2021-02-26 | 哈尔滨工业大学 | Ultra-large space telescope on-orbit assembly system based on multi-space robot |
| CN113135301A (en) * | 2021-05-28 | 2021-07-20 | 中国科学院微小卫星创新研究院 | Integrated system of satellite |
| CN113428326A (en) * | 2021-07-06 | 2021-09-24 | 中国人民解放军国防科技大学 | Standard load cabin underwater replacing device for modular underwater intelligent equipment platform |
| CN113788163A (en) * | 2021-09-06 | 2021-12-14 | 中国科学院微小卫星创新研究院 | On-orbit multidimensional extension evolution method of modular satellite |
| CN113879568A (en) * | 2021-09-06 | 2022-01-04 | 中国科学院微小卫星创新研究院 | Pluggable satellite thermal control system and method |
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| CN113135301A (en) * | 2021-05-28 | 2021-07-20 | 中国科学院微小卫星创新研究院 | Integrated system of satellite |
| CN113135301B (en) * | 2021-05-28 | 2024-03-22 | 中国科学院微小卫星创新研究院 | Integrated system of satellite |
| CN113428326A (en) * | 2021-07-06 | 2021-09-24 | 中国人民解放军国防科技大学 | Standard load cabin underwater replacing device for modular underwater intelligent equipment platform |
| CN113879568A (en) * | 2021-09-06 | 2022-01-04 | 中国科学院微小卫星创新研究院 | Pluggable satellite thermal control system and method |
| CN113879568B (en) * | 2021-09-06 | 2022-07-12 | 中国科学院微小卫星创新研究院 | Pluggable satellite thermal control system and method |
| CN113788163B (en) * | 2021-09-06 | 2023-10-17 | 中国科学院微小卫星创新研究院 | On-orbit multidimensional expansion evolution method of modularized satellite |
| CN113788163A (en) * | 2021-09-06 | 2021-12-14 | 中国科学院微小卫星创新研究院 | On-orbit multidimensional extension evolution method of modular satellite |
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