CN112340066A - Formula of can throwing solar sail spacecraft - Google Patents
Formula of can throwing solar sail spacecraft Download PDFInfo
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- CN112340066A CN112340066A CN202011320249.2A CN202011320249A CN112340066A CN 112340066 A CN112340066 A CN 112340066A CN 202011320249 A CN202011320249 A CN 202011320249A CN 112340066 A CN112340066 A CN 112340066A
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- 238000000926 separation method Methods 0.000 claims abstract description 20
- 239000002184 metal Substances 0.000 claims description 16
- 238000004804 winding Methods 0.000 claims description 16
- 239000012528 membrane Substances 0.000 claims description 8
- 238000004064 recycling Methods 0.000 claims description 6
- 238000003491 array Methods 0.000 claims description 4
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 238000013461 design Methods 0.000 abstract description 4
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 239000010408 film Substances 0.000 description 25
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- 238000007689 inspection Methods 0.000 description 3
- 238000012544 monitoring process Methods 0.000 description 3
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
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- 108010066114 cabin-2 Proteins 0.000 description 1
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- 230000007613 environmental effect Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
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Abstract
The invention discloses a jettisonable solar sail spacecraft, and relates to the technical field of spacecraft design. The solar sail spacecraft comprises a main spacecraft and a plurality of separated sub-spacecrafts which can be separated from the main spacecraft, wherein the plurality of separated sub-spacecrafts are arranged around the main spacecraft; each separated sub-spacecraft is connected with the main spacecraft through a support rod; one end of the supporting rod is fixedly connected to the main spacecraft, and the other end of the supporting rod is collected in the interior of the separation sub spacecraft in a coiling manner; film sail collecting reels are arranged on two sides of each of the separated sub-spacecrafts; and a folding and unfolding mechanism for realizing the storage and unfolding of the supporting rods is further installed in the separation sub-spacecraft. By adopting the technical scheme of '1 main spacecraft + a plurality of separated sub-spacecrafts', the invention can greatly reduce the overall structural quality of the solar sail spacecraft and is beneficial to improving the effective load ratio and the mission flight efficiency of the solar sail spacecraft.
Description
Technical Field
The invention belongs to the technical field of spacecraft design, and particularly relates to a jettisonable solar sail spacecraft.
Background
The solar sail spacecraft, called solar sail for short, is a novel spacecraft which uses the reflected light pressure of the sun on a film to provide power, does not need to consume extra chemical fuel and working medium in the process of sailing, and has the characteristics of small mass, large folding-unfolding ratio, low cost, low power consumption and long range, so that the solar sail spacecraft is considered by broad scholars and experts to have wide application prospect in deep space exploration and active off-orbit technologies.
However, the solar pressure is a very slight environmental force in space, and for example, in a solar sail spacecraft with an area of 100 square meters, the theoretical calculation of the light pressure generated by the surface of the film sail is less than 1 millinewton at a position 1AU from the center of the day (AU is an astronomical unit, and 1AU means the average distance between the earth and the sun, which is about 1.496 hundred million meters) under ideal full reflection conditions. Therefore, in the structural design of the solar sail spacecraft, on one hand, the larger and smaller the area of the membrane sail are desired to obtain larger light pressure; on the other hand, the structural mass of the spacecraft is expected to be as small as possible, so that the spacecraft has higher acceleration, and the time consumed by flight is greatly shortened. It follows that structural mass is an important constraint in the design of solar sail spacecraft.
However, the flexible film sail itself cannot be stretched to a desired plane, but rather, relies on the stretching of the outer support bar structure to form a tensioned planar structure. Because the structural sizes of the film sail and the supporting rod are large, a set of proper unfolding mechanism must be designed, so that the solar sail spacecraft is transited from a compact and small launching state to an on-orbit unfolding state with a large area. Currently, in the research of the solar sail deployment mechanism, there are three main representative configurations: independent blade type, integral tension type and spin tension type, see the literature "Liu jin Guo, Zhao Peng Yuan, Wucheng morning, Qin, Chen Keli, SIASAIL-I solar sail deployment mechanism [ J ]. Mechanical engineering newspaper, 2019,55(21): 1-10". However, after the task of unfolding the film sail is completed, the unfolding mechanisms still remain on the spacecraft body and become redundant mass carried by the solar sail spacecraft in the flying process, so that the structural mass of the solar sail spacecraft cannot be further reduced, and the flying efficiency of the solar sail spacecraft is seriously affected.
Disclosure of Invention
The invention mainly aims to provide a jettisonable solar sail spacecraft, and aims to solve the problem that the structural mass of the solar sail spacecraft cannot be further effectively reduced due to the existing film sail unfolding mode.
In order to achieve the above object, the present invention provides a jettisonable solar sail spacecraft, comprising a main spacecraft and a plurality of separate sub-spacecrafts separable from the main spacecraft, the plurality of separate sub-spacecrafts being arranged around the main spacecraft;
each separated sub-spacecraft is connected with the main spacecraft through a support rod; one end of the supporting rod is fixedly connected to the main spacecraft, and the other end of the supporting rod is collected in the interior of the separation sub spacecraft in a coiling manner;
film sail collecting reels are arranged on two sides of each of the separated sub-spacecrafts; a film sail with a triangular structure is arranged between the separation sub-spacecraft and the main spacecraft, the top end of the film sail is fixedly connected to the main spacecraft, and the other two ends of the film sail are respectively rolled on a film sail collecting reel;
and a folding and unfolding mechanism for realizing the storage and unfolding of the supporting rods is further installed in the separation sub-spacecraft.
Preferably, the separation sub-spacecraft comprises a folding and unfolding mechanism cabin and a body cabin; the folding and unfolding mechanism is arranged inside the cabin of the folding and unfolding mechanism and comprises a supporting rod collecting reel, a flatting sub-mechanism, a guiding sub-mechanism, a metal traction belt and a belt winding and recycling sub-mechanism, and the metal traction belt is driven to be recycled by the belt winding and recycling sub-mechanism so as to realize the unfolding of the supporting rod;
the support rod collecting reel is rotatably erected in the folding and unfolding mechanism and used for winding and collecting the support rod and fixing and winding the metal traction belt;
the flattening sub mechanism is arranged on the outer peripheral side of the support rod collecting reel and is used for flattening the support rod to be wound back onto the collecting reel;
the guide sub mechanism is arranged between the flatting sub mechanism and the support rod unfolding outlet and is used for guiding the unfolding direction of the support rod and ensuring that the support rod is unfolded in the horizontal direction;
the metal traction belt can be wound on the support rod storage reel along with the support rod and is used for drawing the support rod to be unfolded;
the belt winding and recovering sub-mechanism is arranged above the supporting rod collecting reel in an inclined mode and is used for recovering the metal traction belt;
the support rod can be coiled and stored on the support rod storage drum; the tail end of the supporting rod is detachably connected with the supporting rod collecting reel, and the whole supporting rod can be completely horizontally unfolded outwards from the inside of the folding and unfolding mechanism cabin.
Preferably, a connection fixing ring is further arranged at an unfolding outlet of the support rod of the folding and unfolding mechanism cabin, and the connection fixing ring can be separated from the folding and unfolding mechanism cabin when the film sail is completely unfolded in place, stably clamp the support rod and simultaneously realize connection with an end point of the film sail.
Preferably, the bottom of the main spacecraft is also provided with a floor tray.
Preferably, the soliton spacecraft further comprises deployable solar cell arrays, and the solar cell arrays are arranged on two sides of the body cabin.
Preferably, the number of the split sub-spacecraft is six, the structure of the main spacecraft is in a regular hexagonal prism shape, and the configuration of the whole disposable solar sail spacecraft is in a regular hexagon shape.
Preferably, the number of the split sub-spacecrafts is four, the structure of the main spacecraft is in a cuboid shape, and the configuration of the whole disposable solar sail spacecraft is in a square shape.
Preferably, the number of the separated sub-spacecrafts is eight, the structure of the main spacecraft is in a regular octagonal prism shape, and the configuration of the whole disposable solar sail spacecraft is in a regular octagon shape.
Compared with the prior art, the technical scheme of the invention has the following beneficial effects:
according to the invention, by adopting the configuration and the technical scheme of '1 main spacecraft + a plurality of separated sub-spacecrafts', the separated sub-spacecrafts are internally provided with the folding and unfolding mechanisms for accommodating and unfolding the supporting rods, and the separated sub-spacecrafts can be separated from the main spacecraft after executing the task of unfolding the supporting rods, and the folding and unfolding mechanisms are thrown relative to the main spacecraft, so that the overall structural quality of the solar sail spacecrafts is greatly reduced, the effective load ratio and the task flight efficiency of the solar sail spacecrafts are improved, and the completion and the realization of space tasks of the solar sail spacecrafts are facilitated.
Secondly, the separating sub-spacecraft 2 has the function of unfolding the structure, and also has the capability of completing the tasks of monitoring the whole unfolding process of the solar sail spacecraft, space observation and inspection, space exploration and the like.
The solar sail spacecraft designed by the invention has flexible configuration, and different spacecraft configurations, such as square, regular hexagon, regular octagon and the like, can be realized by adopting different numbers of the separated sub-spacecrafts.
The invention has the capability of designing a large-area solar sail spacecraft, and taking the situation of six split sub-spacecraft in the embodiment of the invention as an example, if a solar sail spacecraft with the length of 50 square meters is designed, the length of a single-rod supporting rod is only required to be designed to be 4.4 meters; if the solar sail spacecraft with 100 square meters is designed, the length of the single-rod supporting rod is only required to be designed to be 6.2 meters; and if a solar sail spacecraft with the square meter of 200 is designed, the length of the single-rod supporting rod is only required to be designed to be 8.8 meters.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic view of a jettisonable solar sail spacecraft of the present invention in a collapsed configuration;
FIG. 2 is a schematic view of a jettisonable solar sail spacecraft of the present invention during deployment;
FIG. 3 is a schematic view of a jettisonable solar sail spacecraft of the present invention in a fully deployed, impending separation position;
FIG. 4 is a schematic view of the jettisonable solar sail spacecraft of the present invention in a state just prior to the completion of the separation;
FIG. 5 is a schematic view of the jettisonable solar sail spacecraft of the present invention after separation;
FIG. 6 is a schematic structural view of the segregant spacecraft with the solar array undeployed;
FIG. 7 is a schematic structural view of the segregant spacecraft with the solar array deployed;
fig. 8 is a schematic view of the internal structure of the folding and unfolding mechanism cabin of the split-sub spacecraft.
The invention is illustrated by the reference numerals:
| reference numerals | Name (R) | Reference numerals | Name (R) |
| 1 | |
21 | Folding and unfolding |
| 2 | Split- |
22 | |
| 3 | |
23 | |
| 4 | |
211 | Support |
| 5 | Film |
212 | |
| 6 | Support rod | 213 | Guide sub mechanism |
| 7 | Connecting |
214 | Metal traction belt |
| 8 | Support |
215 | Band winding recycling mechanism |
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In order to further reduce the structural mass of the solar sail spacecraft and improve the flight efficiency of the solar sail spacecraft, the invention provides a disposable solar sail spacecraft. Fig. 1 is a schematic structural diagram of a jettisonable solar sail spacecraft of the present invention in a collapsed state.
As shown in fig. 1, the throwable solar sail spacecraft of the present invention includes a main spacecraft 1, a plurality of separate sub-spacecrafts 2, a plurality of support rods 6, and a plurality of thin film sails 3, wherein the main spacecraft is located at a central position of the solar sail spacecraft, and the number of the separate sub-spacecrafts is six in this embodiment. The separating sub-spacecrafts 2 are uniformly distributed around the main spacecraft 1 in a circumferential array mode, in the embodiment, the structure of the main spacecraft 1 is in a regular hexagonal prism shape, and the included angles between six connecting lines at the centers of the six separating sub-spacecrafts 2 and the main spacecraft 1 are all 60 degrees.
Each of the separated sub-spacecrafts 2 is connected to the main-spacecraft 1 through one support rod 6, and in this embodiment, the number of the separated sub-spacecrafts is 6, so that the number of the support rods 6 is also six. One end (referred to as a starting end herein for convenience of description) of the support rod 6 is fixedly connected to the sidewall of the main spacecraft 1, and the other end (referred to as a tail end) is housed inside the separate sub-spacecraft 2 in a coiled manner.
Specifically, referring to the schematic structural diagrams of the separated sub-spacecraft 2 shown in fig. 6 and 7, the separated sub-spacecraft 2 includes a folding and unfolding mechanism cabin 21 and a body cabin 22; the internal structure of the folding and unfolding mechanism cabin 21 is schematically shown in fig. 8, and a folding and unfolding mechanism for folding and unfolding the support rod 6 is installed inside the folding and unfolding mechanism cabin 21. The folding and unfolding mechanism comprises a support rod collecting reel 211, a flattening sub mechanism 212, a guiding sub mechanism 213, a metal traction belt 214, a belt winding and recycling sub mechanism 215 and the like.
The supporting rod collecting reel 211 is rotatably erected in the folding and unfolding mechanism and used for winding and collecting the supporting rod 6 and fixing and winding the metal traction belt.
The crushing mechanism 212 is provided on the outer peripheral side of the support rod storage roll 211, and crushes the support rod 6 to be wound back on the storage roll.
For convenience of description, a side panel of the folding and unfolding mechanism cabin 21 facing the main spacecraft 1 is referred to as a front panel, a support rod unfolding outlet 8 is arranged on the front panel, and the guide sub mechanism 213 is arranged between the flattening sub mechanism and the support rod unfolding outlet 8 and is used for guiding the unfolding direction of the support rod 6 and ensuring that the support rod 6 is unfolded in the horizontal direction.
The metal traction belt 214 can be wound on the support rod storage reel 211 along with the support rod and is used for drawing the support rod to be unfolded;
the belt winding and recovering mechanism 215 is arranged obliquely above the support rod collecting reel 211 and is used for recovering the metal traction belt;
the tail end of the support rod 6 is stored on the support rod storing reel 211, the tail end of the support rod is detachably connected with the support rod storing reel 211, and the whole support rod 6 can be completely horizontally unfolded outwards from the inside of the folding and unfolding mechanism cabin 21.
In this embodiment, the belt winding and recovering mechanism 215 drives the metal traction belt 214 to recover and further draw the support rod 6 to unfold, so that the support rod 6 can be continuously unfolded from the support rod storage reel 211, and the support rod 6 can be continuously and horizontally unfolded from the inside of the folding and unfolding mechanism cabin 21 along the support rod unfolding outlet 8. Because the starting end of the supporting rod 6 is installed on the main spacecraft 1 in a fixedly connected mode, along with the continuous expansion of the supporting rod 6, the length of the supporting rod 6 is continuously increased, the supporting rod 6 continuously pushes the ion separation spacecraft 2 outwards, namely, the ion separation spacecraft 2 continuously moves outwards along with the expansion of the supporting rod 6 in the direction departing from the main spacecraft 1.
Two sides of each separated sub-spacecraft 2 are respectively provided with a film sail collecting reel 5, the film sail 3 is in a triangular structure, the top end of the film sail 3 is fixedly connected to the side edge of the main spacecraft 1, and the other two ends of the film sail collecting reel are respectively wound on the film sail collecting reels 5. Likewise, since the top end of the membrane sail 3 is fixedly mounted on the main spacecraft 1, the membrane sail collection reel 5 will rotate continuously as the support rods 6 are continuously unwound and the separate sub-spacecraft 2 is continuously moved outwardly away from the main spacecraft 1, thereby continuously unwinding the membrane sail 3 wound thereon.
In summary, the deployment process of the jettisonable solar sail spacecraft of the present invention can be summarized as follows: under the driving of a folding and unfolding mechanism arranged in a folding and unfolding mechanism cabin 21, the supporting rod 6 is continuously horizontally unfolded from the supporting rod unfolding outlet 8, and along with the increase of the length of the supporting rod 6, the separating sub-spacecraft 2 continuously moves outwards in the direction departing from the main spacecraft 1, so that the film sail collecting reel 5 is driven to rotate, and the film sail 3 wound on the film sail collecting reel 5 is continuously unfolded until the whole film sail 3 is completely unfolded. FIG. 2 is a schematic view of a jettisonable solar sail spacecraft of the present invention during deployment; fig. 3 shows a schematic view of the state of the jettisonable solar sail spacecraft of the invention at the moment of just full deployment.
After the film sail 3 is completely unfolded to the proper position, the tail ends of the support rods 6 are not fixedly connected to the support rod storage reel 211 but detachably connected, so that the tail ends of the support rods 6 can also slide out of the support rod unfolding outlets 8 along with the operation of the unfolding and folding mechanism, and at the moment, the separation sub-spacecraft 2 can be separated from the main spacecraft 1. Please refer to fig. 4, which is a schematic diagram of the state of the jettisonable solar sail spacecraft of the present invention just after the separation is completed. As can be seen from fig. 4, the split sub-spacecraft 2 is now no longer connected to the main spacecraft 1 via the support bars 6, leaving only the support bars 6 extending above the main spacecraft 1.
Fig. 5 is a schematic diagram of the state of the jettisonable solar sail spacecraft of the invention after separation. When separation is completed, the separating sub-spacecraft 2 can actively fly off the main spacecraft 1, so that the separating sub-spacecraft 2 is no longer present in fig. 5. As is evident from fig. 5, the structural mass of the main spacecraft 1 is undoubtedly reduced by the approach taken by the invention, since the separate sub-spacecraft 2 with the stowing and unfolding mechanism no longer remains on the main spacecraft 1.
It is worth adding that at the support bar deployment exit 8 on the front panel of the stowing and deployment mechanism compartment 21, a connecting and fixing ring 7 is also provided, which connecting and fixing ring 7 has two functions. When the membrane sail 3 is just fully deployed, the coupling and fixing rings 7 are disengaged from the spacecraft 2, on the one hand firmly gripping the support rods 6 and, on the other hand, effecting the coupling with the ends of the membrane sail 3, as shown in fig. 5.
In addition, a bottom plate tray is further arranged at the bottom of the main spacecraft 1, please refer to fig. 1, in order to enable the solar sail spacecraft designed by the invention to pass the examination of the harsh vibration impact of the rocket launching section, the bottom plate tray can support and connect six separation sub-spacecraft 2 so as to prevent the problem of insufficient connection strength caused by connection of the solar sail spacecraft by the supporting rod 6, and the bottom plate tray and the separation sub-spacecraft 2 are unlocked firstly and then started to separate after the solar sail spacecraft is launched into orbit.
After the task of unfolding the support rod 6 is executed, the separating sub-spacecraft 2 can actively fly away from the main spacecraft 1, and other tasks which can be completed include monitoring the whole unfolding process of the solar sail spacecraft, space observation and inspection, space detection and the like. In order to ensure sufficient energy, the segregant spacecraft 2 further includes a pair of solar cell arrays 23, as shown in fig. 6, which are installed on both sides of the body capsule 22. After performing the task of unfolding, the solar array 23 can also be unfolded to form a plane for capturing sunlight, as shown in fig. 7.
In summary, the present invention has the following features:
according to the technical scheme of the invention, the 1 main spacecraft and the plurality of the separated sub-spacecrafts are adopted, the folding and unfolding mechanisms for accommodating and unfolding the supporting rods are installed in the separated sub-spacecrafts, and the separated sub-spacecrafts can be separated from the main spacecraft after the tasks of unfolding the supporting rods are executed, so that the overall structural quality of the solar sail spacecraft is further effectively reduced, and the improvement of the effective load ratio and the task flight efficiency of the solar sail spacecraft is facilitated.
Secondly, the separating sub-spacecraft 2 has the function of unfolding the structure, and also has the capability of completing the tasks of monitoring the whole unfolding process of the solar sail spacecraft, space observation and inspection, space exploration and the like.
The solar sail spacecraft designed by the invention is flexible in configuration, and if the '1 main spacecraft +4 separated sub-spacecrafts' is adopted, the solar sail spacecraft is square in configuration; if the '1 main spacecraft +6 separated sub-spacecrafts' is adopted, the configuration of the solar sail spacecraft is a regular hexagon; if "1 main spacecraft +8 separate sub-spacecraft" is used, the configuration of the solar sail spacecraft is regular octagon.
The structural size of the solar sail spacecraft designed by the invention can be made very large, namely the solar sail spacecraft has the capacity of designing a large-area solar sail spacecraft, for example, if the solar sail spacecraft with the length of 50 square meters is required to be designed, the length of the single-rod supporting rod is only required to be designed to be 4.4 meters, taking the situation of six split sub-spacecrafts in the embodiment of the invention as an example; if a solar sail spacecraft with 100 square meters is required to be designed, the length of the single-rod supporting rod is only required to be designed to be 6.2 meters; and if the solar sail spacecraft with the square meter of 200 is designed, the length of the single-rod supporting rod is only required to be designed to be 8.8 meters.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (8)
1. A jettisonable solar sail spacecraft, comprising a main spacecraft and a plurality of separate sub-spacecraft separable from the main spacecraft, the plurality of separate sub-spacecraft being arranged around the main spacecraft;
each separated sub-spacecraft is connected with the main spacecraft through a support rod; one end of the supporting rod is fixedly connected to the main spacecraft, and the other end of the supporting rod is collected in the interior of the separation sub spacecraft in a coiling manner;
film sail collecting reels are arranged on two sides of each of the separated sub-spacecrafts; a film sail with a triangular structure is arranged between the separation sub-spacecraft and the main spacecraft, the top end of the film sail is fixedly connected to the main spacecraft, and the other two ends of the film sail are respectively rolled on a film sail collecting reel;
and a folding and unfolding mechanism for realizing the storage and unfolding of the supporting rods is further installed in the separation sub-spacecraft.
2. The jettisonable solar sail spacecraft of claim 1, wherein the splitter spacecraft includes a stowing mechanism bay and a body bay; the folding and unfolding mechanism is arranged inside the cabin of the folding and unfolding mechanism and comprises a supporting rod collecting reel, a flatting sub-mechanism, a guiding sub-mechanism, a metal traction belt and a belt winding and recycling sub-mechanism, and the metal traction belt is driven to be recycled by the belt winding and recycling sub-mechanism so as to realize the unfolding of the supporting rod;
the support rod collecting reel is rotatably erected in the folding and unfolding mechanism and used for winding and collecting the support rod and fixing and winding the metal traction belt;
the flattening sub mechanism is arranged on the outer peripheral side of the support rod collecting reel and is used for flattening the support rod to be wound back onto the collecting reel;
the guide sub mechanism is arranged between the flatting sub mechanism and the support rod unfolding outlet and is used for guiding the unfolding direction of the support rod and ensuring that the support rod is unfolded in the horizontal direction;
the metal traction belt can be wound on the support rod storage reel along with the support rod and is used for drawing the support rod to be unfolded;
the belt winding and recovering sub-mechanism is arranged above the supporting rod collecting reel in an inclined mode and is used for recovering the metal traction belt;
the support rod can be coiled and stored on the support rod storage drum; the tail end of the supporting rod is detachably connected with the supporting rod collecting reel, and the whole supporting rod can be completely horizontally unfolded outwards from the inside of the folding and unfolding mechanism cabin.
3. The jettisonable solar sail spacecraft of claim 2, wherein at the deployment exit of the support rods of the stowing mechanism compartment, there are further provided fastening rings which can disengage from the stowing mechanism compartment when the membrane sail is fully deployed in position and firmly grip the support rods while enabling connection to the membrane sail end points.
4. The disposable solar-sail spacecraft of claim 1, wherein a floor tray is also provided at the bottom of the primary spacecraft.
5. The jettisonable solar sail spacecraft of claim 2, wherein the split sub-spacecraft further comprises deployable arrays of solar cells disposed on opposite sides of the body cavity.
6. The disposable solar-sail spacecraft of any one of claims 1 to 5, wherein the number of the separate sub-spacecraft is six, the structure of the main spacecraft is in the shape of a regular hexagonal prism, and the configuration of the entire disposable solar-sail spacecraft is in the shape of a regular hexagon.
7. The disposable solar-sail spacecraft of any of claims 1 to 5, wherein the number of the separate sub-spacecraft is four, the structure of the main spacecraft is rectangular parallelepiped, and the configuration of the entire disposable solar-sail spacecraft is square.
8. The disposable solar-sail spacecraft of any of claims 1 to 5, wherein the number of the separate sub-spacecraft is eight, the structure of the main spacecraft is in the shape of a regular octagonal prism, and the configuration of the entire disposable solar-sail spacecraft is in the shape of a regular octagon.
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| US20020116877A1 (en) * | 2001-02-28 | 2002-08-29 | Elmar Breitbach | Apparatus including a boom to be compressed and rolled up |
| DE10241618B4 (en) * | 2002-09-04 | 2005-10-27 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Method for stowing and unfolding large-area films |
| WO2004098994A2 (en) * | 2002-12-13 | 2004-11-18 | Arizona Board Of Regents | Attitude determination and control system for a solar sail spacecraft |
| DE102011082497A1 (en) * | 2011-09-12 | 2013-03-14 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Solar sail drive for satellite, has two intersecting poles, where sailing segment is arranged between pole ends and common center |
| CN104058105A (en) * | 2014-06-24 | 2014-09-24 | 中国空间技术研究院 | Deep space solar sail spacecraft driven by utilizing sunlight pressure |
| CN106394933A (en) * | 2016-09-28 | 2017-02-15 | 西北工业大学 | Solar-sail spacecraft structure provided with distributed satellites for traction |
| CN106527499A (en) * | 2016-12-06 | 2017-03-22 | 北京航空航天大学 | Variable stiffness deployable mechanism and measurement and control method thereof |
| CN107628270A (en) * | 2017-07-31 | 2018-01-26 | 上海宇航系统工程研究所 | A kind of bean-pod shaped bracing stick casts development mechanism aside |
| CN108946339A (en) * | 2018-06-05 | 2018-12-07 | 中国人民解放军国防科技大学 | Device for containing and unfolding bean pod rods |
| CN109573101A (en) * | 2018-11-22 | 2019-04-05 | 中国人民解放军国防科技大学 | Truss type full-flexible spacecraft structure platform |
| CN111547273A (en) * | 2020-05-14 | 2020-08-18 | 中国人民解放军国防科技大学 | Thin film spacecraft |
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| CN112340066B (en) | 2022-04-19 |
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