CN113911311A - Propeller-linked driving device shafting and stratospheric airship - Google Patents
Propeller-linked driving device shafting and stratospheric airship Download PDFInfo
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- CN113911311A CN113911311A CN202111217954.4A CN202111217954A CN113911311A CN 113911311 A CN113911311 A CN 113911311A CN 202111217954 A CN202111217954 A CN 202111217954A CN 113911311 A CN113911311 A CN 113911311A
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- bearing
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- propeller
- inner stator
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
- B64B1/24—Arrangement of propulsion plant
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
- B64B1/24—Arrangement of propulsion plant
- B64B1/30—Arrangement of propellers
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Rolling Contact Bearings (AREA)
Abstract
The invention relates to the technical field of stratospheric airships, and discloses a propeller link driving device shafting and a stratospheric airship. The method comprises the following steps: the outer rotor shaft support frame is connected with the inner stator shaft; one end of the outer rotor shaft is fixedly connected with the propeller, and the other end of the outer rotor shaft is fixedly connected with the outer rotor; the outer rotor surrounds the inner stator, one end of the inner stator shaft is fixedly connected with the inner stator, and the other end of the inner stator shaft is fixedly connected with the inner stator shaft support frame; the first bearing and the second bearing are both arranged on the outer rotor shaft and are separated by a preset distance; inner rings of the first bearing and the second bearing are connected with the outer rotor shaft, and outer rings of the first bearing and the second bearing are connected with the outer rotor shaft support frame; and the outer ring of the third bearing is connected with the hole wall of the through hole of the outer rotor, and the inner ring of the third bearing is connected with the inner stator shaft. The invention adopts three stressed bearings, reduces the torsion borne by the first bearing, thereby prolonging the service life of the bearing.
Description
Technical Field
The invention relates to the technical field of stratospheric airships, in particular to a propeller link driving device shafting and a stratospheric airship.
Background
The stratospheric airship has very wide military and civil values, and has great application values in aspects such as missile defense, communication, remote sensing, space observation, atmospheric measurement and the like.
The stratospheric airship power system which is researched and designed at present generally adopts a mode of directly driving a propeller by a shafting in order to save weight. However, because the radius of the propeller of the power system of the stratospheric airship is large, the thrust or the pull generated when the propeller rotates generates alternating radial force, alternating axial force and alternating axial bending moment on a shaft system of the power driving device.
The conventional stratospheric airship power driving device adopts a radial bearing supporting mode, and the mode cannot play a thrust role in axial thrust or axial tension generated by a propeller. Meanwhile, the axial thrust or the axial tension generated by the propeller can generate a large axial torque force for a pivot with a small span, so that the bearing outer diameter slide way, the bearing inner diameter slide way and the bearing ball support frame are damaged, and the service life of the bearing is shortened.
In order to reduce the influence of the propeller on a shafting, the propeller of the stratospheric airship is driven by adopting a click and reducer mode in the prior art. This type of arrangement, with the addition of a speed reducer, adds weight to the airship drive and reduces its mechanical efficiency. The reduction in mechanical efficiency increases the energy requirements for the battery, which is avoided in the overall topsides design of the stratospheric airship system, and the shafting design of the speed reducer also needs to take into account the manner in which its bearings are stressed.
Therefore, it is necessary to develop a drive shafting capable of reducing the influence of the force generated by the propeller and extending the service life of the shafting.
The above information disclosed in this background section is only for enhancement of understanding of the background of the invention and therefore it may contain information that does not constitute prior art that is already known to a person of ordinary skill in the art.
Disclosure of Invention
The present invention is directed to a propeller linked drive shafting and stratospheric airship that overcomes, at least to some extent, one or more of the problems due to the limitations and disadvantages of the related art.
Additional features and advantages of the invention will be set forth in the detailed description which follows, or may be learned by practice of the invention.
According to a first aspect of the present invention, there is disclosed a propeller linked drive shafting comprising:
the outer rotor shaft support frame is connected with the inner stator shaft;
one end of the outer rotor shaft is fixedly connected with the propeller, and the other end of the outer rotor shaft is fixedly connected with the outer rotor;
the outer rotor surrounds the inner stator, a through hole is formed in the outer rotor, the inner stator shaft penetrates through the through hole, one end of the inner stator shaft is fixedly connected with the inner stator, and the other end of the inner stator shaft is fixedly connected with the inner stator shaft supporting frame;
the first bearing and the second bearing are both arranged on the outer rotor shaft and are separated by a preset distance; inner rings of the first bearing and the second bearing are fixedly connected with the outer rotor shaft, and outer rings of the first bearing and the second bearing are fixedly connected with the outer rotor shaft support frame;
the outer ring of the third bearing is connected with the hole wall of the through hole of the outer rotor, and the inner ring of the third bearing is fixedly connected with the inner stator shaft.
According to an exemplary embodiment of the invention, the propeller linked drive shafting further comprises a drive train mounting bracket connecting the outer rotor shaft support frame and the inner stator shaft support frame. The outer rotor shaft support frame and the inner stator shaft support frame are fixedly connected through a power system mounting support.
According to an example embodiment of the invention, the first bearing comprises a self-aligning bearing or a radial thrust bearing; the second bearing comprises a self-aligning bearing or a radial thrust bearing. The centripetal thrust bearing comprises an angle bearing and a tapered roller bearing.
According to an exemplary embodiment of the invention, the first bearing is capable of withstanding temperatures of 150 ℃ to 350 ℃ and the second bearing is capable of withstanding temperatures of 150 ℃ to 350 ℃.
According to an example embodiment of the invention, the third bearing comprises a self-aligning bearing or a radial bearing.
According to an exemplary embodiment of the invention, the third bearing is capable of withstanding temperatures of 150 ℃ to 350 ℃.
According to an exemplary embodiment of the invention, the propeller linkage driving device shafting further comprises a flange plate, and the outer rotor shaft is connected with the propeller through the flange plate.
According to an exemplary embodiment of the invention, the propeller radius is R meters, 1 ≦ R ≦ 3.5, the predetermined distance is L meters, 0.05 XR ≦ L ≦ 0.5 XR.
According to a second aspect of the invention, the invention discloses a stratospheric airship comprising one or more propellers, one or more power plants, one or more propellers linking a driving device shafting and a hull;
the power devices are arranged on the submarine body, and each power device provides power for the rotation of the outer rotor for one shafting;
a propeller is connected with a shafting, and an inner stator shaft support frame of the shafting is fixedly connected with the submarine body.
According to an exemplary embodiment of the invention, each propeller comprises a plurality of blades and a hub; the hub is arranged in the center of the propeller, and one end of each blade is fixedly connected with the hub; the shaft system further comprises a flange plate, and the outer rotor shaft is fixedly connected with the hub through the flange plate.
The invention has the beneficial effects that:
according to the invention, the first bearing and the second bearing are arranged on the outer rotor shaft, so that the quality inspection span of the two stressed bearings is increased, the torsion borne by the first bearing is reduced, and the service life of the bearing is prolonged. The addition of the third bearing correspondingly reduces the forces to which the first bearing is subjected. Meanwhile, the radial bearing is changed into the self-aligning bearing or the centripetal thrust bearing, so that the capability of bearing axial thrust and axial torque of the bearing is improved, the service life of the bearing is further prolonged, and the service life of a shafting is prolonged.
The invention sets a third bearing on the inner stator shaft which is not coaxial with the outer rotor shaft for limiting and controlling the air gap change between the outer rotor and the inner stator. The air gap of the motor in the operation process cannot exceed the allowable value range, so that the output power of the motor is guaranteed to be kept within the allowable value range.
The first bearing, the second bearing and the third bearing are high-temperature-resistant bearings, so that the motor shaft system can adapt to the continuous work of the bearings at high temperature in the stratosphere environment, and the service life of the shaft system is prolonged.
Drawings
The above and other objects, features and advantages of the present invention will become more apparent by describing in detail exemplary embodiments thereof with reference to the attached drawings.
Fig. 1 shows a structural view of a propeller-linked drive shafting and a propeller according to the present invention.
The propeller comprises a propeller 1, an outer rotor shaft support frame 2, a first bearing 3, a second bearing 4, an inner stator 5, an inner stator shaft 6, an inner stator shaft support frame 7, a third bearing 8, an outer rotor 9, an outer rotor shaft 10, a power system mounting support 11, a flange 12, a propeller radius R and a preset distance L between the first bearing and the second bearing.
Detailed Description
Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many different forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The drawings are merely schematic illustrations of the invention and are not necessarily drawn to scale.
Furthermore, the described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments. In the following description, numerous specific details are provided to provide a thorough understanding of embodiments of the invention. One skilled in the relevant art will recognize, however, that the invention may be practiced without one or more of the specific details, or with other methods, components, steps, and so forth. In other instances, well-known structures, methods, implementations, or operations are not shown or described in detail to avoid obscuring aspects of the invention.
As a first embodiment of the present invention, an object of the present invention is to disclose a propeller link drive shafting, as shown in fig. 1, comprising: the outer rotor shaft supporting frame comprises an outer rotor 9, an inner stator 5, a first bearing 3, a second bearing 4, a third bearing 8, an outer rotor shaft 10, an outer rotor shaft supporting frame 2, an inner stator shaft 6, an inner stator shaft supporting frame 7, a power system mounting bracket 11 and a flange plate 12.
One end of the outer rotor shaft 10 is fixedly connected with the center of the propeller 1 through a flange 12, and the other end is fixedly connected with the outer rotor 9.
The outer rotor 9 surrounds the inner stator 5, the outer rotor 9 is driven by the power device to rotate and drives the outer rotor shaft 10 to rotate, and the outer rotor shaft 10 drives the propeller 1 to rotate. The outer rotor 9 is provided with a through hole, and the inner wall of the through hole is connected with the outer ring of the third bearing 8. Preferably, the outer ring of the third bearing 8 is attached to the hole wall and fixed on the inner wall of the through hole. The third bearing 8 comprises a self-aligning bearing or a radial bearing. The inner stator shaft 6 passes through the through hole and is fixedly connected with the inner ring of the third bearing 8. One end of the inner stator shaft 6 extends into the outer rotor 9 and is fixedly connected with the central part of the inner stator 5; the other end is fixedly connected with an inner stator shaft support frame 7 outside the outer rotor 9. The third bearing 8 is arranged on the inner stator shaft 6 which is not coaxial with the outer rotor shaft 10 and is used for limiting the change of the air gap between the outer rotor 9 and the inner stator 5, so that the air gap of the motor for controlling the rotation of the outer rotor 9 in the running process cannot exceed the allowable value range, and the output power of the motor is guaranteed to be kept within the allowable value range. In addition, because the motor shaft system is mainly installed on the airship, the working area of the airship is generally a stratosphere, the atmospheric density of the stratosphere is about 1/14 of the atmospheric density of the sea level, and the air flow has poor heat dissipation, heat generated by the high-speed rotation of the motor bearing is not easy to dissipate to form high temperature of the bearing, the bearing is easy to wear after the temperature of the bearing exceeds 100 ℃, and the service life of the bearing is seriously influenced, therefore, the third bearing 8 adopts a high-temperature-resistant bearing, can bear the temperature of 150 ℃ to 350 ℃, and can adapt to the continuous work of the bearing at high temperature under the environment of the stratosphere, thereby prolonging the service life of the shaft system. The high-temperature bearing can be made by continuous high-temperature quenching treatment according to different types and different heat-resistant temperatures.
The first bearing 3 and the second bearing 4 are both arranged on the outer rotor shaft 10, the first bearing 3 and the second bearing 4 being at a predetermined distance. The radius of the propeller 1 is R, R is more than or equal to 1 m and less than or equal to 3.5 m, the preset distance is L, and L is more than or equal to 0.05 multiplied by R and less than or equal to 0.5 multiplied by R. By determining the ratio relationship between the propeller radius R and the span L of the two bearings, the larger the ratio of R to L, the poorer the ability of the bearings to bear axial bending moment. If the predetermined distance is too short, the axial torque on the first bearing 3 is increased due to a large bending moment, which increases the bearing load and shortens the bearing life; if the predetermined distance is too long, the weight of the motor may be increased to the detriment of reducing the overall weight of the stratospheric airship. Two bearings are arranged on the outer rotor shaft 10, the preset distance between the two bearings is increased to be 0.05 to 0.5 times of the length of the blade of the propeller 1 (namely the radius of the propeller 1), the installation span of the stressed bearing is enlarged, and the stressed bearing can correspond to the radial force, the axial force and the axial bending moment generated to a power system by the rotation of the propeller 1. The increase in bearing support point span thus reduces the axial torsion of the bearing 3. The weight of the power driving device is reduced as much as possible, the efficiency of the power driving device can be increased, and the safety of a shaft system is ensured. The inner rings of the first bearing 3 and the second bearing 4 are fixedly connected with the outer rotor shaft 10, and the outer rings are fixedly connected with the outer rotor shaft support frame 2. The first bearing 3 comprises a self-aligning bearing or a radial thrust bearing. Because the first bearing 3 is stressed greatly, the first bearing 3 can be adjusted into a double-row or double-row bearing according to the load, and the rolling bodies in the bearing can also be adjusted into cylindrical rolling bodies according to the load. The second bearing 4 comprises a self-aligning bearing or a radial thrust bearing. The centripetal thrust bearing comprises an angle bearing and a tapered roller bearing. The self-aligning bearing and the centripetal thrust bearing can improve the capability of bearing axial thrust and axial torsion, further reduce the pressure of the bearing and prolong the service life of the bearing and even the whole shafting. In addition, because the motor shaft system is mainly installed on an airship, the working area of the airship is generally a stratosphere, the stratosphere atmospheric density is about 1/14 of the sea level atmospheric density, and the air flow heat dissipation is poor, so heat generated by the high-speed rotation of the motor bearing is not easy to dissipate to form bearing high temperature, the bearing is easy to wear after the temperature of the bearing exceeds 100 ℃, and the service life is seriously influenced, therefore, the first bearing 3 and the second bearing 4 both adopt high temperature resistant bearings, and can bear the temperature of 150 ℃ to 350 ℃, so that the motor shaft system can adapt to the continuous work of the bearing at high temperature in the stratosphere environment, and the service life of the shaft system is prolonged. The high-temperature bearing can be made by continuous high-temperature quenching treatment according to different types and different heat-resistant temperatures.
The outer rotor shaft support frame 2 and the inner stator shaft support frame 7 are fixedly connected through a power system mounting bracket 11. When the propeller 1 is rotated, the power system mounting bracket 11, the outer rotor shaft support bracket 2 and the inner stator shaft support bracket 7 are all fixedly connected with the hull, and specifically, the outer rotor shaft support bracket 2 and the inner stator shaft support bracket 7 are fixedly connected with the hull through the power system mounting bracket 11. Under the rotation of outer rotor 9, along with outer rotor shaft 10 is rotatory, the radial force, the axial force and the axial bending moment of screw 1 have reduced the effect to whole shafting because of first bearing, the existence of second bearing, and then make the life-span extension of whole shafting, factor of safety promotes.
As a second embodiment of the present invention, an object of the present invention is to disclose a stratospheric airship including: the propellers of the first embodiment link the drive shafting, the propellers 1, the power units and the hull.
The power devices are arranged on the boat body, and each power device provides power for the rotation of the outer rotor of one propeller linkage driving device shafting.
Each propeller 1 comprises a plurality of blades and a hub, preferably 3 blades. The hub is arranged in the centre of the propeller 1 and one end of each blade is fixedly connected to the hub. One end of an outer rotor shaft 10 of the shaft system is fixedly connected with a flange 12. The flange 12 is fixedly connected with the hub.
And a power system mounting bracket 11 of the shafting is fixedly connected with the airship body, so that the airship supports the shafting and the propeller.
The shafting of this scheme of adoption can reduce the atress of shafting, prolongs the life-span of shafting, alleviates airship weight simultaneously.
As a third embodiment of the present invention, the object of the present invention is to disclose an airship of the stratosphere, the structure of which is substantially the same as that of the airship of the second embodiment, except that the propeller 1 of the airship of the third embodiment does not comprise a hub, and the flange 12 is fixedly connected directly to one end of each blade.
Other embodiments of the invention will be apparent to those skilled in the art from consideration of the specification and practice of the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of the invention following, in general, the principles of the invention and including such departures from the present disclosure as come within known or customary practice within the art to which the invention pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the invention being indicated by the following claims.
It will be understood that the invention is not limited to the precise arrangements described above and shown in the drawings and that various modifications and changes may be made without departing from the scope thereof. The scope of the invention is limited only by the appended claims.
Claims (8)
1. A propeller link drive shafting comprising:
the outer rotor shaft support frame is connected with the inner stator shaft;
one end of the outer rotor shaft is fixedly connected with the propeller, and the other end of the outer rotor shaft is fixedly connected with the outer rotor;
the outer rotor surrounds the inner stator, a through hole is formed in the outer rotor, the inner stator shaft penetrates through the through hole, one end of the inner stator shaft is fixedly connected with the inner stator, and the other end of the inner stator shaft is fixedly connected with the inner stator shaft supporting frame;
the first bearing and the second bearing are both arranged on the outer rotor shaft and are separated by a preset distance; inner rings of the first bearing and the second bearing are connected with the outer rotor shaft, and outer rings of the first bearing and the second bearing are connected with the outer rotor shaft support frame;
and the outer ring of the third bearing is connected with the hole wall of the through hole of the outer rotor, and the inner ring of the third bearing is connected with the inner stator shaft.
2. The propeller linked drive shafting of claim 1 further comprising a drive train mounting bracket connecting the outer rotor shaft support frame and the inner stator shaft support frame.
3. The multi-propeller linked drive shafting of claim 1, wherein said first bearing comprises a self-aligning bearing or a radial thrust bearing and said second bearing comprises a self-aligning bearing or a radial thrust bearing.
4. The propeller link drive shafting of claim 1 wherein said third bearing comprises a self-aligning bearing or a radial bearing.
5. The propeller-linked drive unit shafting of claim 1, further comprising a flange, wherein said outer rotor shaft is connected to the propeller via the flange.
6. A propeller linked drive shafting as claimed in claim 1, wherein said propeller radius is R, R is 1 m or less and R is 3.5 m or less, then said predetermined distance is L, 0.05 XR or less and L is 0.5 XR or less.
7. A stratospheric airship comprising one or more propellers, one or more power units, one or more propeller-linked drive shafting and hull according to any one of claims 1 to 6;
the power devices are arranged on the submarine body, and each power device provides rotating power for one shafting;
a propeller is connected with a shafting, and an inner stator shaft support frame of the shafting is fixedly connected with the submarine body.
8. The stratospheric airship of claim 7, wherein each propeller comprises a plurality of blades and a hub; the hub is arranged in the center of the propeller, and one end of each blade is fixedly connected with the hub; an outer rotor shaft of the shaft system is connected with the flange plate; the flange plate is connected with the hub.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111217954.4A CN113911311A (en) | 2021-10-19 | 2021-10-19 | Propeller-linked driving device shafting and stratospheric airship |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111217954.4A CN113911311A (en) | 2021-10-19 | 2021-10-19 | Propeller-linked driving device shafting and stratospheric airship |
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| Publication Number | Publication Date |
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| CN113911311A true CN113911311A (en) | 2022-01-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111217954.4A Pending CN113911311A (en) | 2021-10-19 | 2021-10-19 | Propeller-linked driving device shafting and stratospheric airship |
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Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11278389A (en) * | 1998-03-31 | 1999-10-12 | Ishikawajima Harima Heavy Ind Co Ltd | Airship |
| CN107985586A (en) * | 2017-12-29 | 2018-05-04 | 江苏方阔航空科技有限公司 | A kind of life-cycle pulp hub structure |
| CN110435869A (en) * | 2019-08-12 | 2019-11-12 | 北京航空航天大学 | A kind of energy storage type stratospheric airship motor and control system |
| CN110752689A (en) * | 2019-11-28 | 2020-02-04 | 北京空天高科技有限公司 | Radiating fin type outer rotor motor and stratospheric airship |
| CN111301662A (en) * | 2020-04-09 | 2020-06-19 | 西安九天飞艇制造有限公司 | Vector power structure of large manned airship |
| CN111301671A (en) * | 2020-03-19 | 2020-06-19 | 常州华创航空科技有限公司 | Helicopter tail propeller |
| CN212458149U (en) * | 2020-09-18 | 2021-02-02 | 北京空天高科技有限公司 | Initiating explosive device detonation circuit and stratospheric airship |
| CN112572754A (en) * | 2020-12-11 | 2021-03-30 | 中国特种飞行器研究所 | Airship power device, airship and steering control method of airship |
| CN113060269A (en) * | 2021-04-08 | 2021-07-02 | 西北工业大学 | Pneumatic layout of tandem tilting canal type boat wing airship |
| CN215752978U (en) * | 2021-10-19 | 2022-02-08 | 北京空天高科技有限公司 | Propeller-linked driving device shafting and stratospheric airship |
-
2021
- 2021-10-19 CN CN202111217954.4A patent/CN113911311A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11278389A (en) * | 1998-03-31 | 1999-10-12 | Ishikawajima Harima Heavy Ind Co Ltd | Airship |
| CN107985586A (en) * | 2017-12-29 | 2018-05-04 | 江苏方阔航空科技有限公司 | A kind of life-cycle pulp hub structure |
| CN110435869A (en) * | 2019-08-12 | 2019-11-12 | 北京航空航天大学 | A kind of energy storage type stratospheric airship motor and control system |
| CN110752689A (en) * | 2019-11-28 | 2020-02-04 | 北京空天高科技有限公司 | Radiating fin type outer rotor motor and stratospheric airship |
| CN111301671A (en) * | 2020-03-19 | 2020-06-19 | 常州华创航空科技有限公司 | Helicopter tail propeller |
| CN111301662A (en) * | 2020-04-09 | 2020-06-19 | 西安九天飞艇制造有限公司 | Vector power structure of large manned airship |
| CN212458149U (en) * | 2020-09-18 | 2021-02-02 | 北京空天高科技有限公司 | Initiating explosive device detonation circuit and stratospheric airship |
| CN112572754A (en) * | 2020-12-11 | 2021-03-30 | 中国特种飞行器研究所 | Airship power device, airship and steering control method of airship |
| CN113060269A (en) * | 2021-04-08 | 2021-07-02 | 西北工业大学 | Pneumatic layout of tandem tilting canal type boat wing airship |
| CN215752978U (en) * | 2021-10-19 | 2022-02-08 | 北京空天高科技有限公司 | Propeller-linked driving device shafting and stratospheric airship |
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