阅读说明：本技术 螺旋桨链接驱动装置轴系和平流层飞艇 (Propeller-linked driving device shafting and stratospheric airship ) 是由 江京 高鸿启 段洣毅 廉英 陈超群 于 2021-10-19 设计创作，主要内容包括：本发明涉及平流层飞艇技术领域,公开一种螺旋桨链接驱动装置轴系和平流层飞艇。包括：外转子、内定子、第一轴承、第二轴承、外转子轴、外转子轴支撑架、内定子轴和内定子轴支撑架；外转子轴的一端与螺旋桨固定连接,另一端与外转子固定连接；外转子包围内定子,内定子轴的一端与内定子固定连接,另一端与内定子轴支撑架固定连接；第一轴承和第二轴承均设置在外转子轴上,第一轴承和第二轴承相距预定距离；第一轴承和第二轴承的内圈均与外转子轴固定连接,外圈均与外转子轴支撑架固定连接；外转子轴支撑架和内定子轴支撑架固定连接。本发明采用增大两个受力轴承之间的跨距,减小第一轴承承受的扭力,从而延长轴承的使用寿命。(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, the inner stator, the first bearing, the second bearing, the outer rotor shaft support frame, the inner stator shaft and the inner stator shaft support frame; 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 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 rotor shaft support frame is fixedly connected with the inner stator shaft support frame. The invention increases the span between the two stressed bearings and reduces the torsion borne by the first bearing, thereby prolonging the service life of the bearings.)

1. A propeller link drive shafting comprising:

the outer rotor, the inner stator, the first bearing, the second bearing, the outer rotor shaft support frame, the inner stator shaft and the inner stator shaft support frame;

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.

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 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.

4. 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.

5. The multi-propeller linked drive shafting of claim 1, wherein said first bearing is capable of withstanding temperatures of 150 ℃ to 350 ℃ and said second bearing is capable of withstanding temperatures of 150 ℃ to 350 ℃.

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;

one propeller is connected with one shafting.

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; the hub is fixedly connected with the flange plate; and an outer rotor shaft of the shaft system is fixedly connected with the flange plate.

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, 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 axial tension generated by the rotation of the propeller and the axial bending moment generated by the dynamic unbalance force can generate great axial torque force for the pivot with smaller 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 addition, because the laminar layer air is thin and has small convection heat dissipation capability, heat is not easy to dissipate when the bearing is used, so that the temperature of the bearing is increased, and the abrasion of the outer diameter slide way and the inner diameter slide way of the bearing is easily caused, so that the service life of the bearing is reduced.

In order to reduce the influence of the rotation of the propeller on a shafting, the propeller of the stratospheric airship is driven by a motor 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 of the stratospheric airship power system for the battery, which is to be avoided as much as possible in the overall top-level design of the stratospheric airship system, and moreover, the shafting design of the speed reducer also needs to take into account the bearing stress mode.

Therefore, it is necessary to develop a drive shafting capable of reducing the influence of the force generated by the rotation of 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, the inner stator, the first bearing, the second bearing, the outer rotor shaft support frame, the inner stator shaft and the inner stator shaft support frame;

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.

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 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 example embodiment of the present invention, the first bearing comprises a self-aligning bearing or a radial thrust bearing, and 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 ℃. The second bearing is capable of withstanding temperatures of 150 ℃ to 350 ℃.

According to an exemplary embodiment of the invention, the propeller radius is R, 1 meter R < 3.5 meters, the predetermined distance is L, 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;

one propeller is connected with one shafting.

According to an exemplary embodiment of the invention, each propeller comprises a hub with a plurality of blades; the hub is arranged in the center of the propeller, and one end of each blade is fixedly connected with the hub; the hub is fixedly connected with the flange plate; and an outer rotor shaft of the shaft system is fixedly connected with 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 span of the two stressed bearings is prolonged, the torsion borne by the first bearing is reduced, and the service life of the bearings is prolonged. Meanwhile, the radial bearing is changed into a self-aligning bearing or a radial thrust bearing, so that the capability of bearing axial thrust and axial torsion of the bearing is improved, and the service life of a shafting is prolonged.

In addition, the first bearing and the second 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, an outer rotor 8, an outer rotor shaft 9, a power system mounting support 10, a flange plate 11, a propeller radius R and a propeller radius L, wherein the first bearing and the second bearing are at a preset distance.

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 8, an inner stator 5, a first bearing 3, a second bearing 4, an outer rotor shaft 9, an outer rotor shaft supporting frame 2, an inner stator shaft 6, an inner stator shaft supporting frame 7, a power system mounting support 10 and a flange plate 11.

One end of the outer rotor shaft 9 is fixedly connected with the center of the propeller 1 through a flange plate 11, and the other end is fixedly connected with the outer rotor 8.

The outer rotor 8 surrounds the inner stator 5, the outer rotor 8 is driven by the power device to rotate and drives the outer rotor shaft 9 to rotate, and the outer rotor shaft 9 drives the propeller 1 to rotate. The outer rotor 8 is provided with a through hole. The inner stator shaft 6 passes through the through hole, one end of the inner stator shaft 6 extends into the outer rotor 8 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 8.

The first bearing 3 and the second bearing 4 are both arranged on the outer rotor shaft 9, 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 torsion generated by the rotation of the propeller 1 to a power system. The increase in bearing support point span thereby reduces the axial torque of the bearing. The weight of the power driving device can be reduced as much as possible, the efficiency of the power driving device can be increased, and the safety of a shaft system can be ensured. The inner rings of the first bearing 3 and the second bearing 4 are fixedly connected with the outer rotor shaft 9, 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 or the centripetal thrust bearing can improve the capability of bearing axial thrust and axial torsion, and further reduce the pressure of the bearing. 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, and the bearing is easy to wear after the temperature of the bearing exceeds 100 ℃ generally, 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 ℃, the high-temperature bearing capacity formed by the operation of the bearing in the stratosphere environment can be improved, and the service life of the bearing and even the whole 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 10. When the propeller 1 rotates, the outer rotor shaft support frame 2 and the inner stator shaft support frame 7 are both connected with the power system mounting support 10, the power system mounting support 10 is fixedly connected with the hull, the propeller 1 rotates along with the outer rotor shaft 9 under the rotation of the outer rotor 8, and the radial force, the axial force and the axial bending moment of the propeller 1 are reduced due to the existence of the first bearing 3 and the second bearing 4, so that the whole shafting is prolonged in service life, and the safety factor is improved.

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. The hub is fixedly connected with the flange plate 11; an outer rotor shaft 9 of the shaft system is fixedly connected with a flange plate 11.

The power system mounting bracket 10 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 present invention aims to disclose a stratospheric airship, the structure of which is substantially the same as that of the second embodiment, except that the propeller 1 of the airship of the third embodiment does not include a hub, and the flange 11 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.