CN115837991A - Satellite storage and release mechanism and method - Google Patents
Satellite storage and release mechanism and method Download PDFInfo
- Publication number
- CN115837991A CN115837991A CN202310030796.4A CN202310030796A CN115837991A CN 115837991 A CN115837991 A CN 115837991A CN 202310030796 A CN202310030796 A CN 202310030796A CN 115837991 A CN115837991 A CN 115837991A
- Authority
- CN
- China
- Prior art keywords
- satellite
- release
- storage
- magnetic
- connection
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000003860 storage Methods 0.000 title claims abstract description 54
- 230000007246 mechanism Effects 0.000 title claims abstract description 29
- 238000000034 method Methods 0.000 title claims abstract description 21
- 108091092878 Microsatellite Proteins 0.000 claims description 31
- 238000001179 sorption measurement Methods 0.000 claims description 12
- 230000009471 action Effects 0.000 claims description 9
- 238000004891 communication Methods 0.000 claims description 8
- 239000004020 conductor Substances 0.000 claims description 4
- 230000008054 signal transmission Effects 0.000 claims description 3
- 230000005389 magnetism Effects 0.000 abstract description 6
- 238000012546 transfer Methods 0.000 abstract description 4
- 230000008569 process Effects 0.000 description 8
- 108010066057 cabin-1 Proteins 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 3
- 238000011161 development Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000004519 grease Substances 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 238000007726 management method Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 229920001296 polysiloxane Polymers 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
Images
Landscapes
- Casings For Electric Apparatus (AREA)
Abstract
The utility model provides a satellite storage and release mechanism includes the cabin body, transfer assembly and a plurality of magnetism and inhale connecting portion, and the cabin body has the release hatch door, and transfer assembly sets up inside the cabin body, transfer assembly includes driving motor and conveyer belt, and a plurality of magnetism inhale connecting portion and set up on the conveyer belt. Wherein, connecting portion are inhaled to magnetism has the connection interface, the connection interface includes magnetism and inhales the module, is used for realizing the satellite with the releasable connection between the connecting portion is inhaled to magnetism. The driving motor drives the conveyor belt to move, the magnetic suction connecting part is moved to a position corresponding to the release cabin door, and the satellite can be released from the magnetic suction connecting part and pushed out of the release cabin door. A satellite storage and release method is also provided.
Description
Technical Field
The invention relates to the technical field of carrying and launching of a microsatellite, in particular to a satellite storage and release mechanism and a method.
Background
In the aerospace field, the manufacturing cost of satellites increases with the increase of the manufacturing period, and the technical advancement decreases with the increase of the manufacturing period. Therefore, the microsatellite with various advantages of light weight, good performance, short development period, low cost and the like is rapidly developed and becomes one of the important directions of the current aerospace technology development. At present, the microsatellite is mainly applied to the aspects of communication, ground remote sensing, interplanetary detection, scientific research, technical test and the like.
Artificial satellites weighing less than 1000kg are collectively called microsatellites. The cube star is a microsatellite adopting international universal standards, the standardization is a basic characteristic of the cube star, the cube star takes U (Unit) as a basic Unit, the volume of 1U cube star is 10cm multiplied by 10cm, and the weight is less than 1.33kg, and on the basis, 2U, 3U and even 12U cube stars can be expanded. In the field of spacecraft design, the design goals of generalization and modularization enable a cube satellite to become one of the main development directions of microsatellites.
The in-orbit deployment of the microsatellite includes 3 types: 1) Carrying and launching by utilizing the surplus carrying capacity of the rocket, and releasing and separating after the rocket enters the orbit; 2) Releasing the attached microsatellite in the in-orbit operation process of the large satellite by adopting a mother-child satellite mode; 3) The space station is released directly. The microsatellite is usually released by a satellite releasing device, is locked in the device during the carrying process, is unlocked after running to a preset orbit, and is pushed out of the device to be sent into space. Most of existing satellite releasing devices utilize springs to push satellites to release the satellites, the existing satellite releasing devices can only store and release the microsatellites in a queue mode at one time, if a plurality of satellites need to be released, all the satellites can only be released at one time, the launching time and the launching sequence of a single satellite cannot be adjusted, the structure of the releasing device is complex, and the processing cost is high.
Disclosure of Invention
An object of the present invention is to provide a satellite storage and release mechanism, which can fix a microsatellite during transportation, release the microsatellite after the microsatellite is moved to a predetermined orbit, and adjust the launching time and sequence of a single satellite as required during release, and has simple structure and low processing cost.
The satellite storage and release mechanism comprises: a cabin body having a release cabin door; the conveying assembly is arranged inside the cabin body and comprises a driving motor and a conveying belt; the magnetic suction connecting parts are arranged on the conveyor belt; the magnetic suction connecting part is provided with a connecting interface, and the connecting interface comprises a magnetic suction module and is used for realizing the releasable connection between the satellite and the magnetic suction connecting part; the driving motor drives the conveyor belt to move, the magnetic suction connecting part is moved to a position corresponding to the release cabin door, and the satellite can be released from the magnetic suction connecting part and pushed out of the release cabin door.
In one or more embodiments, the connection interface further comprises: the power supply module is used for supplying power to the satellite; and the communication module is used for realizing data and signal transmission.
In one or more embodiments, a plurality of spring contacts are disposed on the connection interface, and the connection interface is in physical contact with corresponding contacts of the satellite through the spring contacts.
In one or more embodiments, the spring contact is disposed at a center of the connection interface.
In one or more embodiments, a surface of the connection interface is attached with a heat conductive material, and the connection interface further includes a thermal control module, through which temperature control of the satellite is achieved.
In one or more embodiments, the magnetic attraction connecting portion includes a supporting portion and a connecting portion, the connecting portion protrudes from the surface of the conveyor belt through the supporting portion, and the connecting interface is disposed on the connecting portion.
In one or more embodiments, the satellite is a cube star.
Another object of the present invention is to provide a satellite storage and release method, which can fix a microsatellite during transportation, release the microsatellite after traveling to a predetermined orbit, and adjust the transmission time and sequence of the individual satellites as needed during the release.
The satellite storage and release method adopts the satellite storage and release mechanism to realize the in-orbit storage and release of the microsatellite; the satellite storage and release method comprises the following steps: when the satellite is stored, the interface of the satellite for magnetic attraction connection is correspondingly placed with the connection interface of the magnetic attraction connection part; the satellite is connected with the magnetic suction connecting part in an adsorption manner under the action of magnetic adsorption force by introducing forward current to the magnetic suction module; when the satellite is released, the driving motor drives the conveyor belt to move, and the satellite to be released is moved to a position corresponding to the release cabin door; and the magnetic attraction module is charged with reverse current, the satellite is far away from the magnetic attraction connecting part under the action of magnetic repulsion force and moves towards the release cabin door to be released to the outside of the cabin body.
Compared with the prior art, the invention at least has the following beneficial effects:
the magnetic suction connecting part in the satellite storage and release mechanism adopts a magnetic suction locking mode to realize the fixed storage and the on-orbit release of a plurality of cuboids, has a simple structure, can realize two functions of adsorption fixation and pushing release of the satellite by adjusting the current direction of the magnetic suction module, and is convenient and flexible to control. The conveying assembly can guarantee that the delivery launches the mechanical environment to can carry out nimble conveying when the main part device is in the rail, can adjust single cube star's release time and order according to the transmission demand, simultaneously through laying a plurality of magnetism on the conveyer belt and inhale connecting portion, the storage space utilization ratio of cabin internal portion is high, and the deployment size is more intensive, can realize the high intensive storage of cube star.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 is a perspective view of a satellite storage and release mechanism according to one embodiment.
FIG. 2 is a top schematic view of a satellite storage and release mechanism according to one embodiment.
FIG. 3 is a side view schematic diagram of a satellite storage and release mechanism according to one embodiment.
FIG. 4 is a schematic view of a magnetically attractive connection according to one embodiment.
Detailed Description
The present invention is further described in the following description with reference to specific embodiments and the accompanying drawings, wherein the details are set forth in order to provide a thorough understanding of the present invention, but it is apparent that the present invention can be embodied in many other forms different from those described herein, and it will be readily appreciated by those skilled in the art that the present invention can be implemented in many different forms without departing from the spirit and scope of the invention. It is noted that these and other figures which follow are merely exemplary and not drawn to scale and should not be considered as limiting the scope of the invention as it is actually claimed.
The in-orbit deployment of the microsatellite is generally carried by other large devices, such as carrying and launching with a rocket, or operating as a child satellite with a mother satellite, and releasing the microsatellite after the large devices enter the orbit. In the carrying process, an additional storage fixing device is needed for storing and fixing the microsatellite, the moving freedom degree of the satellite in the storage device is limited, and the damage caused by the movement of the microsatellite in the launching device in the launching or running process of a large device is avoided; after the large-scale device runs to a preset orbit position, the fixing of the storage fixing device to the micro satellite needs to be released, and the satellite is released and sent into the space through the release device.
In the prior art, patent CN104527996B discloses an integral rail type cubic satellite launching device, which can be used for carrying and launching single or multiple standard cubic satellites, but the launching device can only store the cubic satellites in a queue manner, and launches all the cubic satellites at one time through springs at the tail of the device, so that single launching cannot be realized, and the launching time and sequence of the cubic satellites cannot be changed. Patent CN106516172B discloses a device for in-orbit release of a micro/nano satellite, wherein a spring and a rope are adopted by the release device to fix a cube star, the release mode of the cube star is realized by cutting the rope through a hot knife, and the release device does not have single emission capability. Patent CN110963090B discloses a release mechanism for redundant unlocking and time sequence control of small satellite transmission, which uses an electromagnet to control a cabin door to indirectly release a cube star, instead of directly controlling the cube star, contains a large number of complex mechanical linkage mechanisms, and cannot realize the release of the cube star in a specified sequence. In addition, if the release mechanism is used for storing a plurality of 3U or 6U cuboids, the whole device is too long and narrow, the storage utilization rate is low, and the rocket carrying is not facilitated. Patent CN104816842B discloses a little satellite multi-star adaptation deployment device and application, and this deployment device utilizes telescopic baffle and spring to realize the locking to the cube star, and every cube star all needs to be equipped with telescopic baffle and spring assembly, and mechanical complexity is higher, and device overall structure is also comparatively complicated.
In order to solve one or more of the problems, the application provides a satellite storage and release mechanism, which can fix a microsatellite in a carrying process, release the microsatellite after the microsatellite runs to a preset orbit, and adjust the launching time and sequence of a single satellite according to requirements when the microsatellite is released, and has the advantages of simple structure and low processing cost.
Fig. 1-3 illustrate a satellite storage and release mechanism that may be used with a 3U cube star 4. The satellite storage and release mechanism comprises a cabin body 1, a conveying assembly 2 and a plurality of magnetic suction connecting portions 3, wherein the cabin body 1 is provided with a release cabin door 11, the conveying assembly 2 is arranged inside the cabin body 1, the conveying assembly 2 comprises a driving motor 21 and a conveying belt 22, and the magnetic suction connecting portions 3 are arranged on the conveying belt 22. Wherein, the magnetic connecting part 3 has a connecting interface 310, the connecting interface 310 includes a magnetic module for realizing the releasable connection between the satellite and the magnetic connecting part 3, the driving motor 21 drives the conveyor belt 22 to move, the magnetic connecting part 3 is moved to the position corresponding to the release hatch door 11, and the satellite can be released from the magnetic connecting part 3 and pushed out of the release hatch door 11.
The magnetic suction connecting part 3 in the satellite storage and release mechanism adopts a magnetic suction locking mode to realize the fixed storage and the on-orbit release of a plurality of cuboids 4, has a simple structure, can realize two functions of adsorption fixation and pushing release of a satellite by adjusting the current direction of the magnetic suction module, and is convenient and flexible to control. The conveying assembly 2 can guarantee a carrying and launching mechanical environment, can flexibly convey when a main body device is in orbit, can adjust the release time and the sequence of a single cube star 4 according to launching requirements, and meanwhile, the connecting part 3 is magnetically attracted by arranging a plurality of magnets on the conveying belt 22, so that the storage space inside the cabin body 1 is high in utilization rate, the deployment size is more intensive, and the high-concentration storage of the cube star 4 can be realized.
When the cube star 4 is loaded, the interface for magnetic connection of the cube star 4 is placed corresponding to the connection interface 310 of the magnetic connection part 3, forward current is introduced into the magnetic module, and the cube star 4 can be connected with the magnetic connection part 3 in an adsorption manner under the action of magnetic adsorption force, so that the cube star 4 can be fixed in the cabin in the carrying process, the freedom degree of movement of the cube star 4 is limited, and the damage to the cabin body 1 or the cube star 4 caused by the free movement of the cube star 4 in the cabin body 1 in the emission process of the main body device is avoided.
When the vehicle runs to a preset track and needs to release the cubic star 4, the driving motor 21 drives the conveyor belt 22 to move, the cubic star 4 needing to be released moves to a position corresponding to the release cabin door 11, reverse current is introduced to the magnetic attraction module, the cubic star 4 is released from the fixed connection with the magnetic attraction connecting part 3, is far away from the magnetic attraction connecting part 3 under the action of magnetic repulsion force, is movably released to the outside of the cabin body 1 towards the release cabin door 11, and the release of the single cubic star 4 is completed.
In one embodiment, the connection interface 310 further includes a power module and a communication module, the power module supplies power to the satellite, and the communication module transmits data and signals between the satellite and the magnetic attraction connecting part 3. The satellite storage and release mechanism can have power supply and data communication functions by additionally arranging the power supply and communication module on the connection interface 310, so that the unified power supply and management of a plurality of cubic stars 4 in the cabin 1 can be realized, the on-orbit long-term storage of the cubic stars 4 is facilitated, and the satellite replacement or emergency use is facilitated. The microsatellite has a certain service life, for example, the service life of part of the cubic satellites is 3 months, and the microsatellite needs to be replaced in time before the service life of the microsatellite reaches the service life limit; while unused satellites (standby mode) may be stored for longer than 10 years if they are stored properly. The satellite storage and release mechanism can be used as a long-term storage device, a satellite stored in the cabin 1 is in a standby mode, a plurality of microsatellites can be stored for a long time when the use requirement is not met, and the satellite can be released to work in orbit when the use requirement is met so as to replace the satellite reaching the service life or be used in an emergency when the satellite breaks down.
The connection interface 310 further comprises a thermal control module, temperature control of the satellite is achieved through the thermal control module, the surface of the connection interface 310 is attached with a heat conduction material 313, heat transfer between the satellite and the magnetic attraction connection portion 3 is achieved, accordingly, temperature control can be conducted on the cube star 4 inside the cabin 1 through the thermal control module during carrying of the cube star 4 or in-orbit storage, and damage to the cube star 4 due to overhigh temperature inside the cabin 1 in the emission process of the main body device is avoided. The heat conducting material 313 may be a copper strip, an aluminum film, a heat pipe, a heat conducting silicone grease, or the like.
In one embodiment, the magnetic suction connecting portion 3 includes a supporting portion 32 and a connecting portion 31, the connecting portion 31 is disposed to protrude from the surface of the conveyor belt 22 through the supporting portion 32, and the connecting interface 310 is disposed on the connecting portion 31. As shown in fig. 4, a connection interface 310 of the magnetic connection portion 3 is provided with a plurality of electromagnets 311 for magnetically connecting with the cubic satellite 4 and a plurality of contacts 312 for electrical connection, and a large area of the rest of the connection interface 310 is attached with a heat conductive material 313 for implementing temperature control of the satellite, and the connection interface 310 physically contacts with corresponding contacts 312 on the satellite through the plurality of contacts 312 to implement electrical connection between the two contacts. As shown in fig. 4, the contacts 312 are disposed at the center of the connection interface 310, and include a positive power contact 3121 and a negative power contact 3123 disposed at both sides for supplying power to the cubesar 4, and a communication contact 3122 disposed in the middle for data signal transmission with the cubesar 4.
In one embodiment, the contact on the connection interface 310 is a spring contact 312, the connection interface 310 physically contacts with a corresponding contact 312 on the satellite through the spring contact 312, when the magnetic attraction connecting portion 3 and the cube star 4 are attracted and connected under the action of the magnetic attraction force, the spring contact 312 on the connection interface 310 abuts against the corresponding contact on the satellite, and a pre-tightening force is applied between the two contacts to ensure the stability of the electrical connection between the connection interface 310 and the satellite.
The application also provides a satellite storage and release method, which adopts the satellite storage and release mechanism in one or more of the above embodiments to realize the in-orbit storage and release of the microsatellite, and the satellite storage and release method comprises the following steps:
when the satellite is stored, the interface of the satellite for magnetic connection is correspondingly arranged with the connection interface 310 of the magnetic connection part 3, forward current is introduced into the magnetic module, and the satellite is connected with the magnetic connection part 3 in an adsorption manner under the action of magnetic adsorption force;
when the satellite is released, the driving motor 21 drives the conveyor belt 22 to move, the satellite to be released is moved to the position corresponding to the release cabin door 11, the reverse current is introduced into the magnetic attraction module, the satellite is far away from the magnetic attraction connecting part 3 under the action of magnetic repulsion force, and the satellite moves towards the release cabin door 11 and is released to the outside of the cabin body 1.
In the above-mentioned satellite storage and release method, the magnetic poles of the magnetic module are switched to push out and release the satellite after the satellite to be released is moved to the position corresponding to the release hatch 11, and the satellite and the magnetic connection part are kept in the adsorption connection state before the satellite is confirmed to be in the releasable position. The judgment of whether the satellite to be released moves to the releasable position (i.e. the position corresponding to the release hatch 11) can be directly judged through motor control, or can be judged through the induction of a sensor arranged at the hatch 11.
According to the satellite storage and release method, the fixed storage and the in-orbit release of a plurality of satellites are realized by adopting a magnetic attraction locking mode, the two functions of adsorption fixing and pushing release of the satellites can be realized by adjusting the current direction of the magnetic attraction module, the control is convenient and flexible, the release time and the release sequence of a single satellite can be adjusted according to the emission requirement through motor control, and meanwhile, the high-concentration storage of the satellites can also be realized.
Although the present invention has been disclosed in terms of the preferred embodiment, it is not intended to limit the invention, and variations and modifications may be made by one skilled in the art without departing from the spirit and scope of the invention. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.
Claims (8)
1. A satellite storage and release mechanism, comprising:
a cabin body having a release cabin door;
the conveying assembly is arranged inside the cabin body and comprises a driving motor and a conveying belt; and
the magnetic suction connecting parts are arranged on the conveying belt;
the magnetic suction connecting part is provided with a connecting interface, and the connecting interface comprises a magnetic suction module and is used for realizing the releasable connection between the satellite and the magnetic suction connecting part;
the driving motor drives the conveyor belt to move, the magnetic suction connecting part is moved to a position corresponding to the release cabin door, and the satellite can be released from the magnetic suction connecting part and pushed out of the release cabin door.
2. The satellite storage and release mechanism of claim 1, wherein the connection interface further comprises:
the power supply module is used for supplying power to the satellite; and
and the communication module is used for realizing data and signal transmission.
3. The satellite storage and release mechanism of claim 2, wherein the connection interface has a plurality of spring contacts disposed thereon, the connection interface physically contacting corresponding contacts of the satellite through the spring contacts.
4. The satellite storage and release mechanism of claim 3, wherein the spring contact is disposed at a center of the connection interface.
5. The satellite storage and release mechanism according to claim 2, wherein the connection interface has a surface with a thermally conductive material affixed thereto, the connection interface further comprising a thermal control module by which temperature control of the satellite is achieved.
6. The satellite storage and release mechanism of claim 1, wherein the magnetically attractive connection portion comprises a support portion and a connection portion, the connection portion protrudes from the conveyor belt surface through the support portion, and the connection interface is disposed on the connection portion.
7. The satellite storage and release mechanism of claim 1 wherein the satellite is a cube star.
8. A satellite storage and release method, characterized in that the satellite storage and release mechanism according to any one of claims 1 to 7 is adopted to realize the on-orbit storage and release of a microsatellite;
the satellite storage and release method comprises the following steps:
when the satellite is stored, the interface of the satellite for magnetic attraction connection is correspondingly placed with the connection interface of the magnetic attraction connection part;
the satellite is connected with the magnetic suction connecting part in an adsorption manner under the action of magnetic adsorption force by introducing forward current to the magnetic suction module;
when the satellite is released, the driving motor drives the conveyor belt to move, and the satellite to be released is moved to the position corresponding to the release cabin door;
and the magnetic attraction module is charged with reverse current, the satellite is far away from the magnetic attraction connecting part under the action of magnetic repulsion force and moves towards the release cabin door to be released to the outside of the cabin body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310030796.4A CN115837991A (en) | 2023-01-10 | 2023-01-10 | Satellite storage and release mechanism and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310030796.4A CN115837991A (en) | 2023-01-10 | 2023-01-10 | Satellite storage and release mechanism and method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115837991A true CN115837991A (en) | 2023-03-24 |
Family
ID=85579537
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310030796.4A Pending CN115837991A (en) | 2023-01-10 | 2023-01-10 | Satellite storage and release mechanism and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115837991A (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015190527A1 (en) * | 2014-06-13 | 2015-12-17 | 国立研究開発法人宇宙航空研究開発機構 | Method and system for space debris orbit descent, and method and system for changing orbit of artificial satellite |
| CN107089349A (en) * | 2017-04-24 | 2017-08-25 | 上海航天控制技术研究所 | Rotatable micro-nano satellite electromagnetism docking facilities and docking calculation after one kind docking |
| CN107628269A (en) * | 2017-07-31 | 2018-01-26 | 上海宇航系统工程研究所 | A kind of linkage of unlocking declines satellite On-orbit release device |
| CN107933976A (en) * | 2017-12-21 | 2018-04-20 | 星际漫步（北京）航天科技有限公司 | Cube star ejector and its catapult technique |
| CN108438258A (en) * | 2018-02-09 | 2018-08-24 | 焦天龙 | One kind being used for the in-orbit separation release device of satellite |
| CN109263996A (en) * | 2018-10-23 | 2019-01-25 | 西北工业大学 | A kind of bee colony unmanned plane aerial-launcher |
| CN110127087A (en) * | 2019-05-17 | 2019-08-16 | 山东航天电子技术研究所 | A kind of more star orbital road release devices of cube star |
| CN111891390A (en) * | 2020-08-11 | 2020-11-06 | 中国科学院微小卫星创新研究院 | Satellite interface, connection method thereof and satellite system |
| CN114044142A (en) * | 2021-11-17 | 2022-02-15 | 南京航空航天大学 | Unmanned aerial vehicle air basis storage and delivery integrated device |
| CN115477021A (en) * | 2022-10-21 | 2022-12-16 | 湖北航天技术研究院总体设计所 | Rotary transmitting device and method capable of continuously transmitting satellite |
-
2023
- 2023-01-10 CN CN202310030796.4A patent/CN115837991A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015190527A1 (en) * | 2014-06-13 | 2015-12-17 | 国立研究開発法人宇宙航空研究開発機構 | Method and system for space debris orbit descent, and method and system for changing orbit of artificial satellite |
| CN107089349A (en) * | 2017-04-24 | 2017-08-25 | 上海航天控制技术研究所 | Rotatable micro-nano satellite electromagnetism docking facilities and docking calculation after one kind docking |
| CN107628269A (en) * | 2017-07-31 | 2018-01-26 | 上海宇航系统工程研究所 | A kind of linkage of unlocking declines satellite On-orbit release device |
| CN107933976A (en) * | 2017-12-21 | 2018-04-20 | 星际漫步（北京）航天科技有限公司 | Cube star ejector and its catapult technique |
| CN108438258A (en) * | 2018-02-09 | 2018-08-24 | 焦天龙 | One kind being used for the in-orbit separation release device of satellite |
| CN109263996A (en) * | 2018-10-23 | 2019-01-25 | 西北工业大学 | A kind of bee colony unmanned plane aerial-launcher |
| CN110127087A (en) * | 2019-05-17 | 2019-08-16 | 山东航天电子技术研究所 | A kind of more star orbital road release devices of cube star |
| CN111891390A (en) * | 2020-08-11 | 2020-11-06 | 中国科学院微小卫星创新研究院 | Satellite interface, connection method thereof and satellite system |
| CN114044142A (en) * | 2021-11-17 | 2022-02-15 | 南京航空航天大学 | Unmanned aerial vehicle air basis storage and delivery integrated device |
| CN115477021A (en) * | 2022-10-21 | 2022-12-16 | 湖北航天技术研究院总体设计所 | Rotary transmitting device and method capable of continuously transmitting satellite |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| IL301521A (en) | Spacecraft servicing devices and related assemblies, systems, and methods | |
| EP3564135B1 (en) | Tank support assembly for a vehicle | |
| WO2006068884A1 (en) | Geometrically encoded magnetic latch intercontact face | |
| JP2010524780A (en) | Usage and usage of optimized collaborative spacecraft | |
| JP2017515739A (en) | Payload injection system | |
| CN115837991A (en) | Satellite storage and release mechanism and method | |
| EP0780302A1 (en) | Device and method for equalizing heat dissipation between multiple radiators on a spacecraft | |
| Arnold et al. | QbX-the CubeSat experiment | |
| CN116513491B (en) | Superior and space replenishment system | |
| CN111717424B (en) | On-orbit installation system | |
| CN112373727A (en) | Separable satellite propulsion system configuration | |
| Fredrickson et al. | Application of the mini AERCam free flyer for orbital inspection | |
| CN111417575B (en) | Method for the secure release of satellites in earth orbit | |
| CN115258195B (en) | Deployable mechanism suitable for separation of a plurality of minisatellite in finite space | |
| CN113815904B (en) | Modularized energy system capable of being maintained and replaced on orbit | |
| CN111891390B (en) | Satellite interface, connection method thereof and satellite system | |
| CN109774986B (en) | Magnetic suspension cubic floating aircraft | |
| CN214084796U (en) | Unmanned aerial vehicle accumulate system | |
| JPH10101000A (en) | Orbit-separated space platform assembly | |
| CN113788163B (en) | On-orbit multidimensional expansion evolution method of modularized satellite | |
| CN108910086A (en) | A kind of reentrant formula cube star system based on moonlet cluster | |
| Barde | 1989–2019: Three decades of power systems evolution through the prism of ESPC | |
| US20230227179A1 (en) | System and method of energy and mass transfer in low-gravity environments | |
| Swartwout | Bandit: A platform for responsive educational and research activities | |
| HADDOCK et al. | An optimized Space Station tethered elevator design |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |