CN108248809B - Stratosphere dynamic balloon - Google Patents
Stratosphere dynamic balloon Download PDFInfo
- Publication number
- CN108248809B CN108248809B CN201810024079.XA CN201810024079A CN108248809B CN 108248809 B CN108248809 B CN 108248809B CN 201810024079 A CN201810024079 A CN 201810024079A CN 108248809 B CN108248809 B CN 108248809B
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- China
- Prior art keywords
- balloon
- stratospheric
- blade
- tail
- inflatable tail
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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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- 239000005437 stratosphere Substances 0.000 title description 2
- 230000007704 transition Effects 0.000 claims description 12
- 230000000903 blocking effect Effects 0.000 claims description 8
- 230000007246 mechanism Effects 0.000 description 4
- 239000003381 stabilizer Substances 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 239000002775 capsule Substances 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 210000001015 abdomen Anatomy 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000006467 substitution reaction 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
Abstract
The invention relates to a stratospheric power balloon, which comprises a balloon body, a nacelle, an inflatable tail wing, a propulsion device, an energy supply device and a vector thrust device, wherein the vector thrust device is connected to the front end of the balloon body. The front end of the stratospheric power balloon is provided with a semi-flexible mounting piece for mounting the vector thrust device, and the vector thrust device comprises a rigid supporting structure, a bracket and a blade device. Wherein the rigid support structure is fixedly connected to the semi-flexible mounting sheet, the bracket is rotatably connected to the rigid support structure about an X-axis, and the paddle device is rotatably connected to the bracket about a Z-axis relative to the bracket.
Description
Technical Field
The invention relates to the technical field of floating aircrafts, in particular to a stratospheric dynamic balloon.
Background
The dynamic balloon is used as a floating aircraft, and mainly overcomes air resistance in the flying process by virtue of thrust generated by a dynamic propulsion system. In the flight process of the stratospheric dynamic balloon, the control of the gesture of the dynamic balloon to fly or maneuver according to a preset track is a very key link. The application of the vector thrust device has great significance for the tasks of wind-resistant flight, long-time residence and the like of the dynamic balloon. The traditional power balloon is characterized in that an engine is arranged on two sides of a capsule body belly nacelle, and a set of tilting mechanism is adopted to drive the engine to rotate to generate thrust. This layout may be subject to the following conditions: the pitch angle of the power balloon is increased when the thrust is accelerated, and the power balloon is not beneficial to safely landing under the condition that the tilting mechanism fails. Another arrangement is to install a vector thrust device at the tail of the dynamic balloon, and the disadvantage of this arrangement is that: in the air flow separation zone, the influence of the air flow can reduce the efficiency of the propeller, reduce the thrust output and possibly bear alternating aerodynamic load, thus influencing the strength of the propeller and the structure of the vector thrust device. Therefore, the power balloon in the prior art is mainly used for solving the following technical problems: the ordinary tail wing has low control course precision, and the yaw angle is difficult to control accurately when the yaw angle is within +/-20 degrees; the vector thrust device is arranged at the tail part, so that the control response is slow, the structure weight is large, and the control effect is very limited; the fin is mostly a rigid structure, is directly installed on the hull, and the steering engine is installed to the airfoil additional, and the structure is complicated.
Disclosure of Invention
The invention aims to at least solve one of the problems, and the aim is achieved by the following technical scheme:
the invention provides a stratospheric power balloon, which comprises a balloon body, a nacelle, an inflatable tail wing, a propulsion device, an energy supply device and a vector thrust device, wherein the vector thrust device is connected to the front end of the balloon body.
Preferably, the stratospheric power balloon further comprises a semi-flexible transition section, the front end of the semi-flexible transition section is connected with the bag body, and the rear end of the semi-flexible transition section is connected with the inflatable tail wing.
Further preferably, the inflatable tail fin has a variable cross-section structure, the front end of the inflatable tail fin has a substantially circular cross-section matched with the rear end of the air bag, and the inflatable tail fin is gradually changed in a gradually flattened substantially elliptical structure along the central axis direction or the X-axis direction of the hull, and is substantially long and straight at the end of the inflatable tail fin.
According to one embodiment of the invention, the tail end of the inflatable tail fin is long and straight and extends along the Y-axis direction.
According to another embodiment of the present invention, the tail end of the inflatable tail fin is in a long straight shape extending along the Z-axis direction.
Preferably, the inflatable tail is provided with a blocking device at a connection position with the balloon, the blocking device being openable so that the inflatable tail is in gaseous communication with the balloon, and the blocking device being closable so that the inflatable tail is enclosed in the balloon so that independent pressure control can be performed on the inflatable tail.
According to a preferred embodiment of the invention, the forward end of the stratospheric power balloon is provided with a semi-flexible mounting tab for mounting the vector thrust apparatus, the vector thrust apparatus comprising a rigid support structure, a bracket and a paddle apparatus, wherein
The rigid support structure is fixedly connected with the semi-flexible mounting sheet,
the carriage is rotatably connected to the rigid support structure about an X-axis,
the paddle device is rotatably connected to the bracket about a Z-axis relative to the bracket.
Preferably, the blade device comprises a blade and a rectifying guard structure, the rectifying guard structure is provided with a rectifying guard ring and a blade support frame, the rectifying guard ring is arranged to surround the blade, and the blade support frame is fixed on the inner side of the rectifying guard ring and is connected with a hub of the blade.
Further preferably, the energy supply device is a solar cell.
Still further preferably, the semi-compliant transition section is a concave-centered solid of revolution.
The invention has the advantages that: according to the invention, the vector thrust device is arranged at the front end of the bag body of the power balloon, and the inflatable tail wing which plays a role of a stabilizer is arranged at the tail part of the boat body, so that the control precision is higher, the response is accelerated, the structure weight is reduced, and the steering engine structure is omitted.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to designate like parts throughout the figures. In the drawings:
figure 1 shows an overall layout of a stratospheric powered balloon according to an embodiment of the invention;
FIG. 2 shows a schematic structural view of a stratospheric powered balloon according to one embodiment of the invention;
fig. 3 shows a schematic structural view of a stratospheric powered balloon according to another embodiment of the present invention;
FIG. 4 illustrates a perspective view of a vector thrust device of a stratospheric powered balloon according to an embodiment of the invention;
fig. 5 shows a front view of a vector thrust device of a stratospheric powered balloon according to an embodiment of the invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
According to an embodiment of the present invention, a stratospheric powered balloon is presented. As shown in fig. 1, the stratospheric power balloon of the present invention comprises a balloon body 1, a nacelle 5, an inflatable tail 2, a propulsion device 14, an energy supply device and a vector thrust device 3, wherein the vector thrust device 3 is arranged at the front end of the balloon body 1 for controlling the pitch and yaw attitude of the power balloon. According to one embodiment of the invention, the powered balloon may also comprise a semi-flexible transition section 4, so that the stratospheric powered balloon of the invention forms a "three-section" structure, i.e. the semi-flexible transition section 4 has a front end connected to the balloon body 1 and a rear end connected to the inflatable tail 2; preferably, the semi-compliant transition section is provided as a hollow-centered, concave solid of revolution. According to a further embodiment of the invention, the semi-flexible transition section may be omitted, so that the inflatable tail 2 is directly connected to the balloon 1, for example by welding or adhesive bonding the inflatable tail 2 to the balloon 1. In addition, the energy supply means preferably employs a solar cell 13.
The inflatable tail 2 of the stratospheric power balloon according to the present invention functions as a stabilizer, and two arrangements of the inflatable tail are shown in fig. 2 and 3, respectively. In particular, the inflatable tail wing of the present invention is preferably of a variable cross-section structure having a generally circular cross-section at its front end that matches the shape of the rear end of the air bag and gradually tapers in a gradually flattened generally oval configuration along the central axis or X-axis of the hull and is generally elongate at its distal end. According to one embodiment of the present invention, as shown in fig. 2, the tail end of the inflatable tail fin 2 is in a long straight shape extending along the Z-axis direction, so that the inflatable tail fin forms a single vertical fin, and the single vertical fin can generate a restoring moment to adjust the direction of the power balloon according to the incoming flow direction, thereby controlling the yaw angle of the power balloon. According to another embodiment of the present invention, as shown in fig. 3, the tail end of the inflatable tail 2 is in a long straight shape extending along the Y-axis direction, so that the inflatable tail forms a single horizontal tail stabilizer, and the single horizontal tail stabilizer can generate a restoring moment, thereby controlling the pitch angle of the power balloon. As shown in fig. 1, the gravity center G of the power balloon is located right below the floating center F, and when the pitching attitude of the hull changes, the pitching attitude of the hull is controlled by generating a restoring moment according to the change of the gravity center position along with the position change of the hull. In addition, the nacelle 5 is installed right under the hull 1, and generates a restoring moment when the hull changes in rolling posture, thereby controlling the rolling posture of the hull.
According to a preferred embodiment of the invention, the inflatable tail 2 is provided with a blocking device, such as a valve which can be controlled remotely, at the connection to the balloon 1. The blocking means can be opened so that the inflatable tail 2 is in gas communication with the balloon 1 and can be closed so that the inflatable tail is enclosed in the balloon so that independent pressure control can be performed on the inflatable tail.
According to a preferred embodiment of the invention, the front end of the powered balloon is provided with a semi-flexible mounting tab 6 for mounting the vector thrust apparatus 3, the semi-flexible mounting tab 6 being connected to the flexible bladder 1. The vector thrust apparatus 3 comprises a rigid support structure 8, a bracket and a blade 11 arrangement as shown in figures 4 and 5. Wherein the rigid support structure 8 is connected to the semi-flexible mounting sheet 6, for example by means of a rigid connection such as a bolt, screw or the like; the support is rotatably connected to the rigid support structure 8 about the X-axis by a rotation mechanism 10 (for example a pin) such that the support can rotate about the X-axis at an angular speed of 0-120r/min for 360 ° rotation and hover at any rotation angle; the blade device is connected to the support in a rotatable manner about the Z-axis relative to the support by means of a rotation mechanism 9, such as a pin, so that the blade device can be rotated 360 ° about the Z-axis at an angular speed of 0-120r/min and can hover at any rotation angle. According to a preferred embodiment of the invention, the blade arrangement comprises a blade 11 and a rectifying guard structure. The rectification protection structure is provided with the rectification protection ring 7 and the blade support frame 12, and the rectification protection ring 7 is arranged to surround the blade 11, namely is arranged on the outer side of the blade tip, so that the rectification protection structure can play roles in rectifying and protecting the capsule, ensure the thrust effect generated by the rotation of the blade and prevent the blade from damaging the capsule; the blade support frame 12 is fixed to the inner side of the fairing ring 7, preferably integrally formed with the fairing ring 7, and the blade 11 is connected to the blade support frame 12 by its hub so that the blade 11 can rotate relative to the blade support frame 12 and the fairing ring 7. Preferably, the blade means is capable of rotating at a speed of 0-8000r/min to provide a vector thrust of 0-500N, enabling control of pitch and yaw attitude of the stratospheric powered balloon of the invention. The vector thrust apparatus of the stratospheric power balloon of the present invention can operate in a height range of 0-30 km.
The present invention is not limited to the above-mentioned embodiments, and any changes or substitutions that can be easily understood by those skilled in the art within the technical scope of the present invention are intended to be included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (7)
1. A stratospheric power balloon, characterized in that the stratospheric power balloon comprises a balloon body, a nacelle, an inflatable tail, a propulsion device, an energy supply device and a vector thrust device, wherein the vector thrust device is connected to the front end of the balloon body;
the inflatable tail is provided with a blocking device at a connecting position with the bag body, the blocking device can be opened to enable the inflatable tail to be in gas communication with the bag body, and the blocking device can be closed to enable the inflatable tail to be sealed in the bag body, so that independent pressure control can be performed on the inflatable tail;
the front end of the stratospheric power balloon is provided with a semi-flexible mounting piece for mounting the vector thrust device, the vector thrust device comprises a rigid supporting structure, a bracket and a blade device, wherein,
the rigid support structure is fixedly connected with the semi-flexible mounting sheet,
the carriage is rotatably connected to the rigid support structure about an X-axis,
the paddle device is rotatably connected to the bracket around a Z axis relative to the bracket;
the blade device comprises a blade and a rectification protection structure, wherein the rectification protection structure is provided with a rectification protection ring and a blade support frame, the rectification protection ring is arranged to surround the blade, and the blade support frame is fixed on the inner side of the rectification protection ring and is connected with a hub of the blade.
2. The stratospheric power balloon of claim 1, further comprising a semi-flexible transition section, a front end of the semi-flexible transition section being connected to the bladder, a rear end of the semi-flexible transition section being connected to the inflatable tail.
3. The stratospheric power balloon according to claim 1, wherein the inflatable tail has a variable cross-section structure, a front end of the inflatable tail has a substantially circular cross-section that matches a rear end of the balloon body, and the inflatable tail tapers in a gradually flattened substantially elliptical structure along a central axis direction or an X-axis direction of the balloon body and has a substantially elongated straight shape at a distal end of the inflatable tail.
4. A stratospheric power balloon according to claim 3, characterized in that the tip of the inflatable tail is elongate and straight extending in the Y-axis direction.
5. A stratospheric power balloon according to claim 3, characterized in that the tip of the inflatable tail is elongate and straight extending in the Z-axis direction.
6. The stratospheric power balloon of claim 1, wherein the energy supply means is a solar cell.
7. The stratospheric power balloon of claim 2, wherein the semi-flexible transition section is a concave-centered revolution 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 CN108248809A (en) | 2018-07-06 |
| CN108248809B true 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) |
Families Citing this family (2)
| 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 |
| 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 |
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Also Published As
| Publication number | Publication date |
|---|---|
| CN108248809A (en) | 2018-07-06 |
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