CN206537480U - Near space aerostatics lets system fly away - Google Patents
Near space aerostatics lets system fly away Download PDFInfo
- Publication number
- CN206537480U CN206537480U CN201720189620.3U CN201720189620U CN206537480U CN 206537480 U CN206537480 U CN 206537480U CN 201720189620 U CN201720189620 U CN 201720189620U CN 206537480 U CN206537480 U CN 206537480U
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- Prior art keywords
- rope
- utricule
- multigroup
- windproof
- hoist engine
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Abstract
System is let fly away the utility model discloses a kind of near space aerostatics.Wherein, the system includes：Utricule；Gondola, is articulated in the lower section of utricule；Multigroup restriction rope, the first end of multigroup restriction rope is fixed on the periphery of utricule, the second end of multigroup restriction rope on multigroup hoist engine, wherein, distance of multigroup hoist engine apart from the center of gondola is identical.It is poor that the utility model solves near space aerostatics stability during letting fly away in the prior art, causes the technical problem for letting failure fly away.
Description
Technical field
The utility model is related near space aerostatics field, in particular to a kind of putting near space aerostatics
Fly system.
Background technology
Near space aerostatics is current global hot research problem, and it is that near space is floated that the stabilization of helium balloon, which is let fly away,
One of key issue of pocket research, helium balloon is in gas replenishment process in the stage of letting fly away, and buoyancy gradually increases, and spheroid is gradually roused
Swollen, spheroid gradually rises, and is influenceed by ground air-flow and air-filled buoyancy gas, and during letting fly away, helium balloon can bear vertical side
To buoyancy and the wind load of horizontal direction.Under the effect of two power, helium balloon shape and position easily occur unstable, it is necessary to right
Helium balloon carries out pose adjustment, it is ensured that shape and position are correct before helium balloon lift-off, steady to rise, and work is let in completion fly away.
One group of constraint can be set in the bottom of the utricule of near space aerostatics or top in the prior art, due to about
Beam is less, it is impossible to effective gesture stability is carried out to spheroid, or without wind resistance, ball position can not during letting fly away
It is effectively fixed, it is easily caused and lets fly away unsuccessfully.
Poor, the problem of the causing to let fly away unsuccessfully near space aerostatics stability during letting fly away in the prior art,
Not yet propose effective solution at present.
Utility model content
The utility model embodiment lets system fly away there is provided a kind of near space aerostatics, at least to solve prior art
Middle near space aerostatics stability during letting fly away is poor, causes the technical problem for letting failure fly away.
According to the one side of the utility model embodiment, there is provided a kind of system of letting fly away of near space aerostatics, bag
Include：Utricule；Gondola, is articulated in the lower section of utricule；Multigroup restriction rope, the first end of multigroup restriction rope is fixed on the periphery of utricule,
Second end of multigroup restriction rope on multigroup hoist engine, wherein, distance of multigroup hoist engine apart from the center of gondola is identical.
Further, restriction rope includes：Windproof force-supporting belt, the first end of windproof force-supporting belt is fixed on the periphery of utricule；Lead
Messenger, pull rope is on hoist engine, and the end of pull rope is connected with the second end of windproof force-supporting belt.
Further, distance of multigroup hoist engine apart from the center of gondola is 25-35m.
Further, system also includes：Multiple rope stretching devices, are fixed on the ground, and pull rope passes through rope stretching device.
Further, rope stretching device is hanger.
Further, system also includes：Multiple to cut rope device, pull rope passes through the second end for cutting rope device and windproof force-supporting belt to connect
Connect.
Further, multiple rope devices of cutting are used for while cutting pull rope.
Further, the first end of windproof force-supporting belt is branch's tab structure, and the second end of windproof force-supporting belt is restricted for sewing
Nested structure.
Further, branch's tab structure includes：Multiple branches, the end connection tab of branch, tab is sewed in utricule
On.
Further, four groups of restriction ropes are fixed on utricule, the first end of four groups of restriction ropes is uniformly fixed to the outer of utricule
In week, the second end of four groups of restriction ropes is on multigroup hoist engine.
In the utility model embodiment, the system of letting fly away of near space aerostatics includes：Utricule；Gondola, is articulated in capsule
The lower section of body；Multigroup restriction rope, the first end of multigroup restriction rope is fixed on the periphery of utricule, the second end winding of multigroup restriction rope
On multigroup hoist engine, wherein, distance of multigroup hoist engine apart from the center of gondola is identical.It is easily noted that, due to capsule
Body is fixed on the ground by multigroup restriction rope and multigroup hoist engine, and multigroup constraint is carried out to utricule, increases the wind resistance energy of utricule
Power, so as to efficiently control posture, the position of spheroid in the inflation of utricule and the stage of letting fly away, enables the process of letting fly away to bear necessarily
Wind load, resists the buoyancy of itself before letting fly away, it is ensured that utricule inflation lets that process is steady, be smoothed out fly away, so as to solve existing
Have in technology that near space aerostatics stability during letting fly away is poor, cause the technical problem for letting failure fly away, reach that raising is faced
The stability of near space aerostatics, lifting near space aerostatics lets the technique effect of success rate fly away.
Brief description of the drawings
Accompanying drawing described herein is used for providing further understanding to of the present utility model, constitutes the part of the application,
Schematic description and description of the present utility model is used to explain the utility model, does not constitute to of the present utility model improper
Limit.In the accompanying drawings：
Fig. 1 is the schematic diagram for letting system fly away of the near space aerostatics according to the utility model embodiment；
Fig. 2 is the structural representation of hoist engine according to the utility model embodiment and rope stretching device；
Fig. 3 is the structural representation of the windproof force-supporting belt according to the utility model embodiment；And
Fig. 4 is the schematic diagram for letting system fly away of the optional near space aerostatics according to the utility model embodiment.
Wherein, above-mentioned accompanying drawing is marked including the following drawings：
10th, utricule；20th, gondola；30th, restriction rope；40th, hoist engine；31st, windproof force-supporting belt；32nd, pull rope；50th, rope stretching
Device；60th, rope device is cut；70th, clump；80th, hanger；311st, branch's tab structure；312nd, sewing rope sling structure；313rd, branch；
314th, tab；90th, cyclone separator；100th, helium car.
Embodiment
In order that those skilled in the art more fully understand the utility model scheme, it is real below in conjunction with the utility model
The accompanying drawing in example is applied, the technical scheme in the utility model embodiment is clearly and completely described, it is clear that described
Embodiment is only the embodiment of the utility model part, rather than whole embodiments.Based on the reality in the utility model
Example is applied, the every other embodiment that those of ordinary skill in the art are obtained under the premise of creative work is not made all should
When the scope for belonging to the utility model protection.
It should be noted that term " first " in specification and claims of the present utility model and above-mentioned accompanying drawing,
" second " etc. is for distinguishing similar object, without for describing specific order or precedence.It should be appreciated that so
The data used can be exchanged in the appropriate case, so that embodiment of the present utility model described herein can be with except at this
In diagram or description those beyond order implement.In addition, term " comprising " and " having " and their any deformation, meaning
Figure is that covering is non-exclusive and included, and is not necessarily limited to clearly arrange for example, containing a series of system of units, product or equipment
Those units gone out, but may include not list clearly or for these products or the intrinsic other units of equipment.
According to the utility model embodiment, there is provided a kind of embodiment for letting system fly away of near space aerostatics.
Fig. 1 is the schematic diagram for letting system fly away of the near space aerostatics according to the utility model embodiment, such as Fig. 1 institutes
Show, the system includes：Utricule 10；Gondola 20 and multigroup restriction rope 30 (only show 4 groups, can carried out according to actual needs in figure
Setting).Wherein, gondola 20 is articulated in the lower section of utricule 10.The first end of multigroup restriction rope 30 is fixed on the periphery of utricule 10, many
Second end of group restriction rope 30 is on multigroup hoist engine 40, the distance phase at center of multigroup hoist engine 40 apart from gondola 20
Together.
Specifically, utricule 10 is in gas replenishment process, and utricule 10 understands gradually bulging, gradually rises, by ground air-flow and inflation
The influence of buoyant gas, the shape of utricule 10 and position occur unstable, are adjusted in order to the posture to utricule 10,
On the equidistant concentric circles ground in the center of gondola 20, four groups of hoist engines 40, the first end of restriction rope 30 seam can be being fixed
The spherome surface of utricule 10 is formed on, the second end is on hoist engine 40.Multigroup hoist engine 40 can be controlled in gas replenishment process
The rope lengths of the restriction rope 30 wound on work, regulation hoist engine 40, so as to adjust the height of utricule 10, posture and position
Put, complete the constraint to utricule 10.In a kind of optional embodiment, the distance at center of multigroup hoist engine 40 apart from gondola 20
For 25-35m, it is preferable that multigroup hoist engine 40 can be arranged on to the concentric circles that the distance apart from the center of gondola 20 is 30m
On.In an alternative embodiment, Fig. 2 is the structural representation of the hoist engine and rope stretching device according to the utility model embodiment
Figure, as shown in Fig. 2 hoist engine 40 is fixed on clump 70 by the installation stud being arranged on clump 70, clump 70
Ground is embedded to, clump 70 is reinforced concrete construction.
In the utility model above-described embodiment, the system of letting fly away of near space aerostatics includes：Utricule 10；Gondola 20,
It is articulated in the lower section of utricule 10；Multigroup restriction rope 30, the first end of multigroup restriction rope 30 is fixed on the periphery of utricule 10, Duo Zuyue
Second end of binding yarn 30 on multigroup hoist engine 40, wherein, distance of multigroup hoist engine 40 apart from the center of gondola is identical.
It is easily noted that, because utricule 10 is fixed on the ground by multigroup restriction rope 30 and multigroup hoist engine 40, to utricule 10
Multigroup constraint is carried out, increases the wind loading rating of utricule 10, so as to efficiently control ball in the inflation of utricule 10 and the stage of letting fly away
The posture of body, position, enable the process of letting fly away to bear certain wind load, and the buoyancy of itself is resisted before letting fly away, it is ensured that utricule 10 fills
Gas lets that process is steady, be smoothed out, so as to solve near space aerostatics stability during letting fly away in the prior art fly away
Difference, causes the technical problem for letting failure fly away, reaches the stability for improving near space aerostatics, and lifting near space aerostatics is put
Fly the technique effect of success rate.
Alternatively, as shown in figure 1, restriction rope 30 includes：Windproof force-supporting belt 31 and pull rope 32.Wherein, windproof force-supporting belt
31 first end is fixed on the periphery of utricule 10.Pull rope 32 is on hoist engine 40, and the end of pull rope 32 is held with windproof
The second end connection of power band 30.
Specifically, above-mentioned windproof force-supporting belt 31 can be high-strength polyethylene band, and above-mentioned pull rope 32 can be brocade
Cord.In gas replenishment process, control hoist engine 40 works, and the length of pull rope 32 is can adjust, so as to adjust the height of utricule 10, appearance
State and position；After the completion of inflation, it can complete to let fly away by the way that pull rope 32 is separated with windproof force-supporting belt 31.
Alternatively, as shown in figure 1, system also includes：Multiple rope stretching devices 50.Wherein, rope stretching device 50 is fixed on the ground, is led
Messenger 32 passes through rope stretching device 50.
Specifically, in order to ensure pull rope 32 in whole gas replenishment process can smoothly folding and unfolding, can fix on the ground
Multiple rope stretching devices 50, each rope stretching device 50 is before every group of hoist engine 40, and the pull rope 32 wound on every group of hoist engine 40 can be with
Through rope stretching device 50, then the second end with windproof force-supporting belt 31 is connected.
Alternatively, as shown in Fig. 2 rope stretching device 50 is hanger.
Specifically, as shown in Fig. 2 rope stretching device 50 can be that hanger 80 is set on clump 70, it will be rolled up on hoist engine 40
Around pull rope 32 pass through hanger 80, it is ensured that the overhanging cable 32 of hoist engine 40 in whole gas replenishment process can smoothly folding and unfolding.
Alternatively, as shown in figure 1, system also includes：It is multiple to cut rope device 60.Wherein, pull rope 32 through cut rope device 60 with
The second end connection of windproof force-supporting belt 31.
Alternatively, multiple rope devices 60 of cutting are used for while cutting pull rope 32.
Specifically, above-mentioned rope device 60 of cutting can be approved product, after inflation is completed, can be cut by the way that remote control is multiple
Device 60 of restricting cuts pull rope 32, completes the separation of the pull rope 32 and windproof force-supporting belt 31 on hoist engine 40, completes restraint release,
And then complete letting fly away for utricule 10.Further, in order to ensure stabilization of the near space vehicle during letting fly away, it is necessary to logical
Cross the multiple rope devices 60 of cutting of remote control remote control simultaneously and carry out cutting operation, it is ensured that pull rope 32 and windproof load on multigroup hoist engine 40
Band 31 is separated simultaneously.
Alternatively, Fig. 3 is the structural representation of the windproof force-supporting belt according to the utility model embodiment, as shown in figure 3, anti-
The first end of wind force-supporting belt 31 is branch's tab structure 311, and the second end of windproof force-supporting belt 31 is sewing rope sling structure 312.
Alternatively, as shown in figure 3, branch's tab structure 311 includes：Multiple branches 313.Wherein, the end of branch 313 connects
Tab 314 is connect, tab 314 is sewed on utricule 10.
Specifically, as shown in figure 3, the first end of windproof force-supporting belt 31 is branch's tab structure 311, the second end is restricted for sewing
Nested structure 312.A circular running-on can be formed by the rope at the second end of windproof force-supporting belt 31 is sewn together, through cutting rope
The pull rope 32 of device 60 passes through running-on, so that pull rope 32 be connected with the second end of windproof force-supporting belt 31.In order to further prevent
Only strong wind causes windproof force-supporting belt 31 to be separated with utricule 10, influences the stability of utricule 10, can be by the of windproof force-supporting belt 31
One end is divided into multiple branches 313 (3 only being shown in figure, can need to be set according to actual wind resistance), and at the end of branch 313
End connection tab 314, tab 314 is sewed on utricule 10, passes through multiple tabs of being sewed in the same position of utricule 10
314, it is ensured that windproof force-supporting belt 31 can be securely fixed on the surface of utricule 10, so as to further increase the wind resistance of utricule 10
Ability.
Alternatively, Fig. 4 is to let showing for system fly away according to the optional near space aerostatics of the utility model embodiment
It is intended to, as shown in figure 4, fixing four groups of restriction ropes 30 on utricule 10, the first end of four groups of restriction ropes 30 is uniformly fixed to utricule
10 periphery, the second end of four groups of restriction ropes 30 is fixed on the ground.
Specifically, as shown in figure 4, near space vehicle can be made up of utricule 10, gondola 20 and cyclone separator 90, gondola
20 are articulated in the lower section of utricule 10 by cyclone separator 90, are ensured by cyclone separator 90 during utricule 10 rotates, gondola 20
Do not rotate.The whole system of letting fly away can be by 4 groups of windproof force-supporting belts 31,4 groups of hoist engines 40 and on hoist engine 40
Pull rope 32,4 rope stretching devices 50 and 4 cut rope device 60 and constituted.The surrounding of near space vehicle utricule 10 equably fixes 4 groups
Windproof force-supporting belt 31；4 groups of hoist engines 40 are arranged in 4 directions of utricule 10, are fixed on ground cement pier, on hoist engine volume 40
Around four pull ropes 32, pull rope 32 is passed through after rope stretching device 50, and top after cutting rope device 60 with four groups of windproof force-supporting belts 31 by connecting
Connect.Utricule 10 can be inflated by helium car 100, be wound in gas replenishment process by adjusting on 4 groups of hoist engines 40
The height of the rope lengths of pull rope 32 regulation utricule 10 and position, completion are constrained utricule 10；After the completion of inflation, by 4
Group cuts the remote control simultaneously of rope device 60 and cuts pull rope 32, completes separation of the pull rope 32 with windproof force-supporting belt 31, completes restraint release,
And then complete to let fly away.
By above-described embodiment, it is combined using hoist engine 40 by rope stretching device 50, realizes the control to utricule 10, it is ensured that
Multigroup restriction rope 30 effectively can apply active force to utricule 10.With advantages below：Effectively realize near space aerostatics
The regulation of spheroid posture and position control during letting fly away, it is ensured that aerostatics steadily rises during letting fly away, and can resist
Certain wind-force, it is ensured that let fly away it is steady, be smoothed out.
Above-mentioned the utility model embodiment sequence number is for illustration only, and the quality of embodiment is not represented.
In above-described embodiment of the present utility model, the description to each embodiment all emphasizes particularly on different fields, in some embodiment
The part not being described in detail, may refer to the associated description of other embodiment.
Described above is only preferred embodiment of the present utility model, it is noted that for the common skill of the art
For art personnel, on the premise of the utility model principle is not departed from, some improvements and modifications can also be made, these improve and
Retouching also should be regarded as protection domain of the present utility model.
Claims (10)
1. a kind of near space aerostatics lets system fly away, it is characterised in that including：
Utricule (10)；
Gondola (20), is articulated in the lower section of the utricule (10)；
Multigroup restriction rope (30), the first end of multigroup restriction rope (30) is fixed on the periphery of the utricule (10), Duo Zusuo
The second end of restriction rope (30) is stated on multigroup hoist engine (40), wherein, hung described in multigroup hoist engine (40) distance
The distance at the center in cabin (20) is identical.
2. system according to claim 1, it is characterised in that the restriction rope (30) includes：
Windproof force-supporting belt (31), the first end of the windproof force-supporting belt (31) is fixed on the periphery of the utricule (10)；
Pull rope (32), the pull rope (32) is on the hoist engine (40), the end of the pull rope (32) and institute
State the second end connection of windproof force-supporting belt (31).
3. system according to claim 2, it is characterised in that multigroup hoist engine (40) is apart from the gondola (20)
The distance at center is 25-35m.
4. system according to claim 2, it is characterised in that the system also includes：
Multiple rope stretching devices (50), fix on the ground, and the pull rope (32) passes through the rope stretching device (50).
5. system according to claim 4, it is characterised in that the rope stretching device (50) is hanger.
6. system according to claim 2, it is characterised in that the system also includes：
Multiple to cut rope device (60), the pull rope (32) cuts the second of rope device (60) and the windproof force-supporting belt (31) through described
End connection.
7. system according to claim 6, it is characterised in that multiple rope devices (60) of cutting are used to lead described in while cutting
Messenger (32).
8. system according to claim 2, it is characterised in that the first end of the windproof force-supporting belt (31) is branch's tab
Structure (311), the second end of the windproof force-supporting belt (31) is sewing rope sling structure (312).
9. system according to claim 8, it is characterised in that branch's tab structure (311) includes：
Multiple branches (313), the end connection tab (314) of the branch (313), tab (314) sewing is in the capsule
On body (10).
10. system as claimed in any of claims 1 to 9, it is characterised in that fix four groups on the utricule (10)
The restriction rope (30), the first end of restriction rope (30) is uniformly fixed to the periphery of the utricule (10), four groups described in four groups
Second end of the restriction rope (30) is on multigroup hoist engine (40).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720189620.3U CN206537480U (en) | 2017-02-28 | 2017-02-28 | Near space aerostatics lets system fly away |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720189620.3U CN206537480U (en) | 2017-02-28 | 2017-02-28 | Near space aerostatics lets system fly away |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206537480U true CN206537480U (en) | 2017-10-03 |
Family
ID=59949407
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|---|---|---|---|
| CN201720189620.3U Expired - Fee Related CN206537480U (en) | 2017-02-28 | 2017-02-28 | Near space aerostatics lets system fly away |
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| Country | Link |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108163179A (en) * | 2017-12-06 | 2018-06-15 | 湖南航天远望科技有限公司 | A kind of near space aerostatics distribution method and dispensing apparatus |
| CN108238229A (en) * | 2017-12-14 | 2018-07-03 | 北京天恒长鹰科技股份有限公司 | Reduction dirigible lets the system of windage fly away and dirigible lets method fly away |
| CN109866911A (en) * | 2017-12-04 | 2019-06-11 | 中国特种飞行器研究所 | A kind of aerostatics butterfly junction structure |
-
2017
- 2017-02-28 CN CN201720189620.3U patent/CN206537480U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109866911A (en) * | 2017-12-04 | 2019-06-11 | 中国特种飞行器研究所 | A kind of aerostatics butterfly junction structure |
| CN108163179A (en) * | 2017-12-06 | 2018-06-15 | 湖南航天远望科技有限公司 | A kind of near space aerostatics distribution method and dispensing apparatus |
| CN108163179B (en) * | 2017-12-06 | 2021-07-27 | 湖南航天远望科技有限公司 | Near space aerostat issuing method and apparatus |
| CN108238229A (en) * | 2017-12-14 | 2018-07-03 | 北京天恒长鹰科技股份有限公司 | Reduction dirigible lets the system of windage fly away and dirigible lets method fly away |
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| CF01 | Termination of patent right due to non-payment of annual fee |