CN108657412B - Damping device for aerostat and aerostat - Google Patents
Damping device for aerostat and aerostat Download PDFInfo
- Publication number
- CN108657412B CN108657412B CN201710208811.4A CN201710208811A CN108657412B CN 108657412 B CN108657412 B CN 108657412B CN 201710208811 A CN201710208811 A CN 201710208811A CN 108657412 B CN108657412 B CN 108657412B
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- CN
- China
- Prior art keywords
- aerostat
- main rod
- damping device
- capsule
- bag body
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- 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.)
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Links
- 238000013016 damping Methods 0.000 title claims abstract description 24
- 239000002775 capsule Substances 0.000 claims abstract description 32
- 239000000463 material Substances 0.000 claims description 4
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 238000007789 sealing Methods 0.000 claims 1
- 230000005484 gravity Effects 0.000 abstract description 8
- 238000005516 engineering process Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
In one aspect, the invention provides a damping device for an aerostat, comprising a main rod, wherein a first end of the main rod is movably connected with a capsule of the aerostat, and a second end of the main rod extends to the outside of the capsule and is connected with a weight. The invention also relates to an aerostat. The invention aims to provide a damping device for an aerostat and the aerostat, wherein the damping device is used for guaranteeing the flight attitude of an aircraft through self gravity center deviation.
Description
Technical Field
The invention relates to the technical field of aerostats, in particular to a damping device for an aerostats and the aerostats.
Background
Super high-rise buildings in the world today bloom throughout the world. The construction of super high-rise buildings is a comprehensive representation of high-rise and new technologies in a plurality of fields, wherein the design of building structures is the most important. To ensure safety, firstly, super-strong earthquake resistance is required. In addition, comfort in living is also considered, and shaking of the building can be reduced when the wind power is high. Therefore, wind dampers known as 'building-calming magic balls' are widely used. The basic operation principle is that when the disturbance wind is coming, the gravity center of the machine body is shifted to the opposite direction of shaking so as to achieve the purpose of counteracting shaking. The wind-resistant damper is divided into an active damper and a passive damper, and the active damper drives devices such as a hydraulic rod spring and the like through computer calculation to realize the shift of the gravity center. The passive device has good economic benefit, does not need an additional device, but has high regulation performance limitation, so that the application range of the passive device is smaller.
The damper with the wind resistance function is mainly applied to the building industry and the aviation field, and the design of a general fixed-wing aircraft generally does not take wind resistance as a main design problem, because the lateral wind resistance of the fixed-wing aircraft has a mature technology. However, considering the particularity of the aerostat, the weight and the mechanism of the aerostat and other factors of the aerostat need to be designed into a damping device for the aerostat.
Disclosure of Invention
In view of the problems in the related art, an object of the present invention is to provide a damping device for an aerostat and an aerostat.
In order to achieve the above object, according to an aspect of the present invention, there is provided a damping device for an aerostat, comprising a main rod, wherein a first end of the main rod is movably connected with a capsule inside the capsule of the aerostat, and a second end of the main rod extends to the outside of the capsule and is connected with a weight member.
According to one embodiment of the invention, the first end of the main rod is connected to the capsule by at least one damper.
According to one implementation of the invention, the damper includes one or more of a hydraulic device, a pneumatic device, and a spring assembly.
According to one embodiment of the invention, the first end of the main rod is connected to the bladder by a universal adjustment mechanism.
According to one embodiment of the invention, the first end of the main rod is connected to the capsule by a plurality of springs, which are equally spaced from each other around the first end of the main rod.
According to one embodiment of the invention, the bladder is internally provided with a mounting seat at the central position of the top end, to which the spring is connected.
According to one embodiment of the invention, a through hole is provided in the central position of the bottom end of the capsule for the second end of the main rod to pass through, wherein a seal is provided between the through hole and the rod section of the main rod.
According to one implementation of the invention, the seal is made of a flexible material.
According to another aspect of the invention there is also provided an aerostat having provided therein a damping device according to any of the embodiments described above.
According to one implementation of the invention, the weight is configured as an on-board mechanical and/or electronic device of the aerostat.
The beneficial technical effects of the invention are as follows:
the invention relates to a damping device for an aerostat and the aerostat, wherein the first end of a main rod of the damping device is movably connected with a bag body of the aerostat, the second end of the main rod extends to the outside of the bag body and is provided with a counterweight, and the gravity center of the counterweight is offset to passively partially offset the swinging mode caused by interference wind to ensure the flight attitude of an aircraft and prevent the aircraft from generating an unrecoverable flight attitude.
Drawings
FIG. 1 is a schematic diagram of one embodiment of the present invention;
FIG. 2 is a schematic view of a mount of the present invention;
figure 3 is a schematic view of an aerostat according to one embodiment of the present invention.
Detailed Description
Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
As shown in fig. 1, one embodiment of the present invention provides a damping device for an aerostat, comprising a main rod 10, the main rod 10 being vertically disposed inside a capsule of the aerostat, wherein a first end of the main rod 10 is movably connected with the capsule inside the capsule of the aerostat, and a second end of the main rod 10 extends to the outside of the capsule and is connected with a weight 12.
In the above embodiment, the first end of the main rod 10 is swingably connected with the capsule body inside the capsule body of the aerostat, and the second end of the main rod extends to the outside of the capsule body and is provided with the weight 12, so that the flying attitude of the aircraft is ensured by passively partially counteracting the swing mode caused by the interference wind through the gravity center deviation of the weight 12, and the unrecoverable flying attitude of the aircraft is prevented.
When the aerostat is disturbed by natural flow, the weight of the counterweight 12 itself passively counteracts the swing amplitude by its inertia. The airworthiness and the task performance of the aerostat in windy conditions are enhanced.
As shown in fig. 2, according to one implementation of the invention, a first end of the boom 10 is connected to the bladder by at least one damper 14.
It should be appreciated that the damper 14 flexibly connects the main rod 10 to the capsule in order to ensure the flying attitude of the aerostat when disturbed by external forces. For example, according to one implementation of the present invention, the damper 14 includes one or more of a hydraulic device, a pneumatic device, and a spring assembly. Of course, the damper 14 may be constructed in other structures as the case may be, and the invention is not limited thereto.
Alternatively, according to an embodiment of the invention, the first end of the boom 10 may be coupled to the bladder via a universal adjustment mechanism. Thus, when the aerostat is interfered by external force, the weight piece 12 swings due to self gravity, and one end of the main rod 10 connected with the bag body can rotate relative to the bag body through the universal adjusting mechanism, so that the bag body is prevented from being damaged due to overlarge swinging of the weight piece 12.
Or according to an implementation of the invention, the first end of the main rod 10 is connected to the capsule by means of springs 18 arranged equidistant from each other around the first end. For example, in the embodiment shown in fig. 2, the first end of the boom 10 is connected to the bladder by four springs 18 disposed equidistant from each other about the first end. It should be understood that the springs 18 may be disposed in the same plane around the main rod 10, or may be disposed in different planes perpendicular to the axial direction of the main rod 10 along the axial direction of the main rod 10, as the case may be, and the present invention is not limited thereto.
As shown in fig. 1 and 2, according to one implementation of the present invention, a mount 16 is provided at a top central position inside the capsule, and a spring 18 is connected to the mount 16. In this way, it is avoided that the weight 12 swings too much to pull the spring 18 to damage the capsule when the wind force is too great.
According to one embodiment of the invention, a through hole is provided in the central position of the bottom end of the capsule for the second end of the main rod 10 to pass through, wherein a seal is provided between the through hole and the rod section of the main rod 10 to prevent gas in the capsule from escaping through the gap between the through hole and the main rod 10.
Further, according to one implementation of the invention, the seal is configured as a seal made of a flexible material. That is, there is a certain swing space between the second end of the main lever 10 and the capsule, and when the weight 12 swings due to its own weight, the main lever 10 does not damage the capsule due to collision with the capsule.
According to another aspect of the invention there is also provided an aerostat having provided therein a damping device according to any of the embodiments described above.
In the above embodiment, the first end of the main rod 10 is swingably connected with the capsule body inside the capsule body of the aerostat, and the second end of the main rod extends to the outside of the capsule body and is provided with the weight 12, so that the flying attitude of the aircraft is ensured by passively partially counteracting the swing mode caused by the interference wind through the gravity center deviation of the weight 12, and the unrecoverable flying attitude of the aircraft is prevented.
According to one implementation of the invention, the weight 12 is configured as an on-board mechanical and/or electronic device of an aerostat. Therefore, the aerostat can ensure the flying attitude of the aircraft by passively partially counteracting the swinging mode brought by the interference wind through the gravity center offset of the airborne mechanical and/or electronic equipment of the aerostat without adding extra weight, and the unrecoverable flying attitude of the aircraft is prevented.
Of course, other materials or devices may be added as the weight 12 when the weight of the mechanical and/or electronic equipment onboard the aerostat is insufficient.
As shown in fig. 3, according to another embodiment of the present invention, a channel 20 penetrating the capsule is further provided at the center of the capsule of the aerostat, and the damping device according to any of the above embodiments is provided in the channel 20. That is, the entire damping device is disposed outside the outer surface of the aerostat, so that the aerostat bladder is not easily torn or damaged due to collision or pulling of the damping device.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. A damping device for an aerostat, characterized by comprising a main rod (10),
Wherein the first end of the main rod (10) is movably connected with the bag body in the bag body of the aerostat, a through hole for the second end of the main rod (10) to pass through is arranged at the central position of the bottom end of the bag body, a channel (20) penetrating through the bag body is also arranged at the central position of the bag body, the second end of the main rod (10) extends to the outside of the bag body and is connected with a weight part (12),
Wherein a first end of the main rod (10) is connected with the capsule through a universal adjusting mechanism, the main rod (10) is arranged in the channel (20), and wherein the first end of the main rod (10) is connected with the capsule through at least one damper (14).
2. The damping device of claim 1, wherein the damper comprises one or more of a hydraulic device, a pneumatic device, and a spring assembly.
3. Damping device according to claim 1, characterized in that the damper comprises a plurality of springs (18), the first end of the main rod (10) being connected to the bladder by means of a plurality of springs (18), the plurality of springs (18) being arranged equidistant from each other around the first end of the main rod.
4. A damping device according to claim 3, characterized in that a mounting seat (16) is provided at a top central position inside the capsule, the spring (18) being connected to the mounting seat (16).
5. A damping device according to claim 1, wherein,
A sealing element is arranged between the through hole and the rod section of the main rod (10).
6. The damping device of claim 5, wherein the seal is made of a flexible material.
7. An aerostat, characterized in that it is provided with a damping device according to any one of claims 1-6.
8. Aerostat according to claim 7, wherein the counterweight (12) is configured as an on-board mechanical and/or electronic device of the aerostat.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710208811.4A CN108657412B (en) | 2017-03-31 | 2017-03-31 | Damping device for aerostat and aerostat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710208811.4A CN108657412B (en) | 2017-03-31 | 2017-03-31 | Damping device for aerostat and aerostat |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108657412A CN108657412A (en) | 2018-10-16 |
| CN108657412B true CN108657412B (en) | 2024-09-03 |
Family
ID=63783925
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710208811.4A Active CN108657412B (en) | 2017-03-31 | 2017-03-31 | Damping device for aerostat and aerostat |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108657412B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101028863A (en) * | 2007-03-22 | 2007-09-05 | 王旭东 | High-altitude float platform |
| CN102425244A (en) * | 2011-10-19 | 2012-04-25 | 沈阳建筑大学 | Multidirectional multi-frequency tuned mass damper |
| CN104763070A (en) * | 2015-04-14 | 2015-07-08 | 山东大学 | Suspension type multidimensional impact vibration reduction damper |
| CN206679242U (en) * | 2017-03-31 | 2017-11-28 | 成都天府新区光启未来技术研究院 | Damping unit and aerostatics for aerostatics |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| BR9807052A (en) * | 1997-06-11 | 2000-05-16 | Prospective Concepts Ag | Cable car for an aerostatic lift body |
| RU2325303C2 (en) * | 2006-06-27 | 2008-05-27 | Григорий Геннадьевич Попов | Airship |
| CN201465508U (en) * | 2009-06-01 | 2010-05-12 | 潘志 | Air cloth slogan balloon device |
| CN101734366A (en) * | 2010-01-05 | 2010-06-16 | 严学文 | Airship attitude adjusting method and related airship |
| CN102336253A (en) * | 2011-07-05 | 2012-02-01 | 赵凤银 | Ship or naval ship or submarine with outside embedded and hung or outside suspended and hung counterweight iron device system |
| US9039334B2 (en) * | 2011-11-18 | 2015-05-26 | Sergey Nikolayevich Ermilov | Methods and apparatuses for moving objects based on a buoyancy force |
| US20150203184A1 (en) * | 2014-01-17 | 2015-07-23 | Joseph Nilo Sarmiento | Sail-equipped amphibious aerostat or dirigible |
| CN204341387U (en) * | 2014-10-27 | 2015-05-20 | 深圳光启空间技术有限公司 | Aerostatics |
| CN205010464U (en) * | 2015-09-28 | 2016-02-03 | 东莞前沿技术研究院 | Aerostatics and utricule structure thereof |
| CN105220791B (en) * | 2015-11-18 | 2017-07-28 | 山东大学 | Multidimensional dual adjustable formula damping control device |
| CN205387191U (en) * | 2015-12-29 | 2016-07-20 | 中国特种飞行器研究所 | Empty aircraft annular ballonet floats |
-
2017
- 2017-03-31 CN CN201710208811.4A patent/CN108657412B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101028863A (en) * | 2007-03-22 | 2007-09-05 | 王旭东 | High-altitude float platform |
| CN102425244A (en) * | 2011-10-19 | 2012-04-25 | 沈阳建筑大学 | Multidirectional multi-frequency tuned mass damper |
| CN104763070A (en) * | 2015-04-14 | 2015-07-08 | 山东大学 | Suspension type multidimensional impact vibration reduction damper |
| CN206679242U (en) * | 2017-03-31 | 2017-11-28 | 成都天府新区光启未来技术研究院 | Damping unit and aerostatics for aerostatics |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108657412A (en) | 2018-10-16 |
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