CN108248809A - Stratosphere powered balloon - Google Patents
Stratosphere powered balloon Download PDFInfo
- Publication number
- CN108248809A CN108248809A CN201810024079.XA CN201810024079A CN108248809A CN 108248809 A CN108248809 A CN 108248809A CN 201810024079 A CN201810024079 A CN 201810024079A CN 108248809 A CN108248809 A CN 108248809A
- Authority
- CN
- China
- Prior art keywords
- stratosphere
- powered balloon
- powered
- type tail
- utricule
- 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.)
- Granted
Links
- 239000005437 stratosphere Substances 0.000 title claims abstract description 35
- 238000009434 installation Methods 0.000 claims abstract description 9
- 230000001681 protective effect Effects 0.000 claims description 11
- 230000008859 change Effects 0.000 claims description 5
- 230000007704 transition Effects 0.000 claims description 2
- 230000006641 stabilisation Effects 0.000 description 5
- 238000011105 stabilization Methods 0.000 description 5
- 230000007246 mechanism Effects 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000004888 barrier function Effects 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 210000001015 abdomen Anatomy 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/40—Balloons
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/40—Balloons
- B64B1/42—Construction or attachment of stabilising surfaces
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
- Wind Motors (AREA)
Abstract
The present invention relates to a kind of stratosphere powered balloon, the stratosphere powered balloon includes utricule, gondola, inflation type tail, propulsion device, power supply and vectored thrust device, wherein, the vectored thrust device is connected to the front end of the utricule.The front end of the stratosphere powered balloon is provided with the semi-flexible installation sheet for installing the vectored thrust device, and the vectored thrust device includes rigid supporting structure, stent and paddle device.Wherein described rigid supporting structure is fixedly connected with the semi-flexible installation sheet, and the stent is connected to the rigid supporting structure in a manner of it can be rotated around X-axis, and the paddle device is connected to the stent in a manner of it can about the z axis be rotated relative to the stent.
Description
Technical field
The present invention relates to lighter-than-air flight device technical field, more particularly to a kind of stratosphere powered balloon.
Background technology
Powered balloon as a kind of lighter-than-air flight device, to overcome flew by the thrust for relying primarily on power propulsion system generation
Air drag in journey.For stratosphere powered balloon in flight course, control powered balloon posture makes it fly according to preset flight path
It is capable or it is motor-driven be very the key link.The application of vectored thrust device is realized wind resistance flight for powered balloon, is stayed for a long time
The tasks such as stay to have great significance.Engine is mounted on the both sides of utricule abdomen gondola by traditional power balloon, is inclined using a set of
Rotation mechanism drives engine rotation to generate thrust.This layout type will appear following situation：Powered balloon is bowed when thrust accelerates
The elevation angle increases, and in the case that inclining rotary mechanism breaks down, is unfavorable for powered balloon safe landing.Another arrangement be
Vectored thrust device is installed in powered balloon tail portion, and the shortcomings that this layout type is：In separation area, influenced by air-flow,
Propeller efficiency can be reduced, thrust output is caused to reduce, alternation pneumatic load may be carried, therefore to propeller and vectored thrust
The intensity of apparatus structure has an impact.Therefore the powered balloon of the prior art is mainly used for that there are following technical problems：Common tail
Wing control course precision is low, and yaw angle is when within ± 20 °, it is difficult to accurate control；Vectored thrust device is mounted on tail portion, control
Low-response, construction weight is big, and control effect is extremely limited；Empennage is mostly rigid structure, is directly installed on hull, and aerofoil installs additional
Steering engine, it is complicated.
Invention content
The purpose of the present invention is one of at least solving the above problems, which is achieved through the following technical solutions：
The present invention proposes a kind of stratosphere powered balloon, and the stratosphere powered balloon includes utricule, gondola, Puffer-type tail
The wing, propulsion device, power supply and vectored thrust device, wherein, the vectored thrust device is connected to the utricule
Front end.
Preferably, the stratosphere powered balloon further includes semi-flexible changeover portion, and the front end of the semi-flexible changeover portion connects
The utricule is connect, the rear end of the semi-flexible changeover portion connects the inflation type tail.
It is further preferred that it is described inflation type tail be variable section structure, it is described inflation type tail front end be with it is described
The approximate circular cross-section that the rear end of air bag matches, and the type tail of inflating is along the central axes direction of hull or X-direction
With gradually flat substantially elliptical structure gradual change, and in the end of the inflation type tail in substantially long and straight type.
A kind of embodiment according to the present invention, the end of the inflation type tail is in the long and straight type extended along Y direction.
Another embodiment according to the present invention, the end of the inflation type tail are straight in the length extended along Z-direction
Type.
Preferably, it is described inflation type tail with the link position of the utricule at be provided with baffling device, the barrier
Device can open so that inflation type tail and the utricule gas connection, and the baffling device can close so that
The inflation type tail is closed in the air bag and is controlled so as to perform independent pressure to the inflation type tail.
According to the present invention to be preferably carried out mode, the front end of the stratosphere powered balloon is provided with described for installing
The semi-flexible installation sheet of vectored thrust device, the vectored thrust device include rigid supporting structure, stent and paddle device,
In
The rigid supporting structure is fixedly connected with the semi-flexible installation sheet,
The stent is connected to the rigid supporting structure in a manner of it can be rotated around X-axis,
The paddle device is connected to the stent in a manner of it can about the z axis be rotated relative to the stent.
Preferably, the paddle device includes blade and rectification safeguard structure, and the rectification safeguard structure is provided with rectification
Protective ring and blade supporting rack, the rectification protective ring are arranged to surround the blade, and the blade supporting rack is fixed on described
It the inside of rectification protective ring and is connect with the wheel hub of the blade.
It is further preferred that the power supply is solar cell.
It is further preferred that the semi-flexible changeover portion is the recessed revolving body in middle part.
The advantage of the invention is that：The present invention by the front end of the utricule in powered balloon set vectored thrust device and
The tail portion of hull has set the type inflatable empennage that stabilization acts on, and can realize control accuracy higher, response quickening, structure weight
Amount reduces and saves steering engine structure.
Description of the drawings
By reading the detailed description of hereafter preferred embodiment, it is various other the advantages of and benefit it is common for this field
Technical staff will become clear.Attached drawing is only used for showing the purpose of preferred embodiment, and is not considered as to the present invention
Limitation.And throughout the drawings, the same reference numbers will be used to refer to the same parts.In the accompanying drawings：
Fig. 1 shows the overall layout chart of the stratosphere powered balloon according to embodiment of the present invention；
Fig. 2 shows a kind of structure diagrams of the stratosphere powered balloon of embodiment according to the present invention；
Fig. 3 shows the structure diagram of the stratosphere powered balloon of another embodiment according to the present invention；
Fig. 4 shows the stereogram of the vectored thrust device of the stratosphere powered balloon according to embodiment of the present invention；
Fig. 5 shows the preceding diagram of the vectored thrust device of the stratosphere powered balloon according to embodiment of the present invention.
Specific embodiment
The illustrative embodiments of the disclosure are more fully described below with reference to accompanying drawings.Although this public affairs is shown in attached drawing
The illustrative embodiments opened, it being understood, however, that may be realized in various forms the disclosure without the reality that should be illustrated here
The mode of applying is limited.It is to be able to be best understood from the disclosure, and can be by this public affairs on the contrary, providing these embodiments
The range opened completely is communicated to those skilled in the art.
According to the embodiment of the present invention, a kind of stratosphere powered balloon is proposed.As shown in Figure 1, the stratosphere of the present invention
Powered balloon includes utricule 1, gondola 5, inflation type tail 2, propulsion device 14, power supply and vectored thrust device 3,
In, vectored thrust device 3 is arranged in the front end of utricule 1, for controlling the pitching of powered balloon and yaw-position.According to the present invention
A kind of embodiment, powered balloon can also include semi-flexible changeover portion 4 so that stratosphere powered balloon of the invention is formed
" three-stage " structure, the i.e. front end of semi-flexible changeover portion 4 are connected to utricule 1, and rear end is connected to inflation type tail 2；Preferably, half
Flexible transition section is arranged to the recessed rotary structure in middle part.Another embodiment according to the present invention, can save semi-flexible
Changeover portion so that inflation type tail 2 is directly connect, such as can be by way of welding or being bonded by Puffer-type tail with utricule 1
The wing 2 is connected to utricule 1.In addition, power supply is preferably by solar cell 13.
The inflation type tail 2 of stratosphere powered balloon according to the present invention plays the role of stabilization, Fig. 2 and Fig. 3 difference
Show two kinds of arrangement forms of inflation type tail.Specifically, inflation type tail of the invention is preferably variable section structure,
Front end is the approximate circular cross-section to match with the shape of air bag rear end, and along the central axes direction of hull or X-direction with
Gradually flat substantially elliptical structure gradual change, and in end in substantially long and straight type.A kind of embodiment according to the present invention,
As shown in Fig. 2, the end of inflation type tail 2 is in the long and straight type extended along Z-direction so that inflation type tail forms single vertical fin peace
Determine face, single vertical fin stabilization can generate restoring moment, realize according to direction of flow motivation of adjustment balloon direction, dynamic so as to control
Strength ball yaw angle.Another embodiment according to the present invention, as shown in figure 3, the end of inflation type tail 2 is in along Y-axis
The long and straight type of direction extension so that inflation type tail forms single horizontal tail stabilization, and single horizontal tail stabilization can generate restoring moment,
So as to control powered balloon pitch angle.As shown in Figure 1, the center of gravity G of powered balloon is located at the underface of centre of buoyancy F, when hull is bowed
When facing upward posture and changing, the pitch attitude of restoring moment control hull is generated with the change in location of hull by position of centre of gravity.
In addition, gondola 5 is installed on the underface of utricule 1, restoring moment is generated when roll attitude variation occurs in hull, controls hull
Roll attitude.
According to a preferred embodiment of the invention, inflation type tail 2 with the link position of utricule 1 at be provided with barrier
Device, such as can be with the valve of remote control.Baffling device can be opened so that inflate type tail 2 and 1 gas connection of utricule, and
And it can close and be controlled so that inflating type tail and being closed in air bag so as to perform independent pressure to inflation type tail.
According to the present invention to be preferably carried out mode, the front end of powered balloon is provided with to install vectored thrust device 3
Semi-flexible installation sheet 6, semi-flexible installation sheet 6 connect with flexible utricule 1.Vectored thrust device 3 includes rigid supporting structure
8th, 11 device of stent and blade, as shown in Figure 4 and Figure 5.Wherein rigid supporting structure 8 is connect with semi-flexible installation sheet 6, such as logical
Cross the connection of the rigid connectors such as bolt, screw；Stent is connected rotating mechanism 10 (such as axis pin) in a manner of it can be rotated around X-axis
It is connected to rigid supporting structure 8 so that stent can carry out 360 ° of rotations with the angular speed rotation of 0-120r/min around X-axis and can
It hovers in arbitrary rotation angle；Paddle device passes through side of the rotating mechanism 9 (such as axis pin) can about the z axis be rotated relative to stent
Formula is connected to stent so that paddle device can carry out 360 ° of rotations with the angular speed of 0-120r/min about the z axis and can be in office
Rotation angle of anticipating hovering.According to a preferred embodiment of the invention, paddle device includes blade 11 and rectification safeguard structure.It is whole
Stream safeguard structure is provided with rectification protective ring 7 and blade supporting rack 12, and rectification protective ring 7 is arranged to surround blade 11, that is, sets
In the outside of blade blade tip, rectification and protection utricule can be played the role of, ensure the thrust that blade rotation generates and
Prevent blade from damaging utricule；Blade supporting rack 12 is fixed on the inside of rectification protective ring 7, preferably with rectification protective ring 7 integrally
Molding, blade 11 is connected to blade supporting rack 12 by its wheel hub so that blade 11 can be relative to blade supporting rack 12 and whole
Stream protective ring 7 rotates.Preferably, paddle device can be rotated with the speed of 0-8000r/min and be pushed away with the vector for providing 0-500N
Power realizes the pitching of stratosphere powered balloon of the present invention and the control of yaw-position.The stratosphere powered balloon of the present invention
Vectored thrust device can be operated in the altitude range of 0-30km.
The foregoing is only a preferred embodiment of the present invention, but protection scope of the present invention be not limited thereto,
Any one skilled in the art in the technical scope disclosed by the present invention, the change or replacement that can be readily occurred in,
It should be covered by the protection scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of the claim
Subject to enclosing.
Claims (10)
1. a kind of stratosphere powered balloon, which is characterized in that the stratosphere powered balloon includes utricule, gondola, Puffer-type tail
The wing, propulsion device, power supply and vectored thrust device, wherein, the vectored thrust device is connected to the utricule
Front end.
2. stratosphere powered balloon according to claim 1, which is characterized in that the stratosphere powered balloon further includes half
Flexible transition section, the front end of the semi-flexible changeover portion connect the utricule, described in the rear end connection of the semi-flexible changeover portion
Inflate type tail.
3. stratosphere powered balloon according to claim 1, which is characterized in that the inflation type tail is variable cross-section knot
Structure, the approximate circular cross-section that the front end for inflating type tail matches for the rear end with the air bag, and the Puffer-type
Empennage along the central axes direction or X-direction of hull with gradually flat substantially elliptical structure gradual change, and in the Puffer-type
The end of empennage is in substantially long and straight type.
4. stratosphere powered balloon according to claim 3, which is characterized in that the end of the inflation type tail is in along Y
The long and straight type of axis direction extension.
5. stratosphere powered balloon according to claim 3, which is characterized in that the end of the inflation type tail is in along Z
The long and straight type of axis direction extension.
6. stratosphere powered balloon according to claim 1, which is characterized in that it is described inflation type tail with the utricule
Link position at be provided with baffling device, the baffling device can open so that the inflation type tail and the utricule gas
Body connects, and the baffling device can close so that the inflation type tail is closed in the air bag so as to described
It inflates type tail and performs independent pressure control.
7. stratosphere powered balloon according to claim 1, which is characterized in that the front end of the stratosphere powered balloon is set
Be equipped with the semi-flexible installation sheet for installing the vectored thrust device, the vectored thrust device include rigid supporting structure,
Stent and paddle device, wherein
The rigid supporting structure is fixedly connected with the semi-flexible installation sheet,
The stent is connected to the rigid supporting structure in a manner of it can be rotated around X-axis,
The paddle device is connected to the stent in a manner of it can about the z axis be rotated relative to the stent.
8. stratosphere powered balloon according to claim 7, which is characterized in that the paddle device includes blade and rectification
Safeguard structure, the rectification safeguard structure are provided with rectification protective ring and blade supporting rack, and the rectification protective ring is arranged to wrap
The blade is enclosed, the blade supporting rack is fixed on the inside of the rectification protective ring and is connect with the wheel hub of the blade.
9. stratosphere powered balloon according to claim 1, which is characterized in that the power supply is solar-electricity
Pond.
10. stratosphere powered balloon according to claim 2, which is characterized in that the semi-flexible changeover portion is under middle part
Recessed revolving body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810024079.XA CN108248809B (en) | 2018-01-10 | 2018-01-10 | Stratosphere dynamic balloon |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810024079.XA CN108248809B (en) | 2018-01-10 | 2018-01-10 | Stratosphere dynamic balloon |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108248809A true CN108248809A (en) | 2018-07-06 |
| CN108248809B CN108248809B (en) | 2024-02-13 |
Family
ID=62724837
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810024079.XA Active CN108248809B (en) | 2018-01-10 | 2018-01-10 | Stratosphere dynamic balloon |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108248809B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111055989A (en) * | 2019-12-13 | 2020-04-24 | 中国特种飞行器研究所 | Small multi-vector airship |
| CN111186552A (en) * | 2018-11-15 | 2020-05-22 | 北京天恒长鹰科技股份有限公司 | Stratospheric airship with fishtail-shaped film-surface type empennage |
| CN112782787A (en) * | 2020-12-28 | 2021-05-11 | 北方大贤风电科技（北京）有限公司 | Method for automatically identifying shear line |
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2018
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111186552A (en) * | 2018-11-15 | 2020-05-22 | 北京天恒长鹰科技股份有限公司 | Stratospheric airship with fishtail-shaped film-surface type empennage |
| CN111055989A (en) * | 2019-12-13 | 2020-04-24 | 中国特种飞行器研究所 | Small multi-vector airship |
| CN112782787A (en) * | 2020-12-28 | 2021-05-11 | 北方大贤风电科技（北京）有限公司 | Method for automatically identifying shear line |
| CN112782787B (en) * | 2020-12-28 | 2022-05-31 | 北方大贤风电科技（北京）有限公司 | Method for automatically identifying shear line |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108248809B (en) | 2024-02-13 |
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