阅读说明：本技术 一种调整飞艇姿态用的螺旋桨电推进装置 (Propeller electric propulsion device for adjusting posture of airship ) 是由 彭桂林 吴玲 李小建 王健 于江 李向阳 李翔 刘鑫磊 于 2021-11-09 设计创作，主要内容包括：本发明公开了一种调整飞艇姿态用的螺旋桨电推进装置,电动机两侧分别具有左输出端和右输出端,左螺旋桨通过左超越离合器与所述左输出端连接,左超越离合器用于控制左螺旋桨单向转动,右螺旋桨通过右超越离合器与所述右输出端连接,右超越离合器用于控制右螺旋桨在与左螺旋桨相反方向上单向转动。本发明针对高空飞行环境设计了一种螺旋桨电推进装置用于调整飞艇高空飞行的姿态,整体结构采用一直线筒状结构,易于安装,且仅采用一套电动机驱动装置即可实现螺旋桨换向工作且换向容易,采用全电推进模式无需氧气动力,能够实现飞艇的偏航推进。(The invention discloses a propeller electric propulsion device for adjusting the posture of an airship, wherein a left output end and a right output end are respectively arranged on two sides of a motor, a left propeller is connected with the left output end through a left overrunning clutch, the left overrunning clutch is used for controlling the left propeller to rotate in a single direction, a right propeller is connected with the right output end through a right overrunning clutch, and the right overrunning clutch is used for controlling the right propeller to rotate in a single direction opposite to the left propeller. The invention designs a propeller electric propulsion device for adjusting the high-altitude flight attitude of an airship aiming at the high-altitude flight environment, the whole structure adopts a linear cylindrical structure, the installation is easy, the propeller reversing work can be realized by only adopting one set of motor driving device, the reversing is easy, the full electric propulsion mode is adopted, no oxygen power is needed, and the yaw propulsion of the airship can be realized.)

1. A propeller electric propulsion device for adjusting the attitude of an airship, comprising: the device comprises a motor (1), a left overrunning clutch (21), a left propeller (31), a right overrunning clutch (22) and a right propeller (32);

motor (1) both sides have left output and right output respectively, left screw (31) through left freewheel clutch (21) with the left output is connected, left freewheel clutch (21) are used for controlling left screw (31) unidirectional rotation, right screw (32) through right freewheel clutch (22) with the right output is connected, right freewheel clutch (22) are used for controlling right screw (32) in with left screw (31) opposite direction upward unidirectional rotation.

2. A propeller electric propulsion device for adjusting the attitude of an airship according to claim 1, characterised by further comprising a left planetary gear reducer (41), the left planetary gear reducer (41) being connected between the left overrunning clutch (21) and the left propeller (31);

and/or the propeller further comprises a right planetary gear reducer (42), and the right planetary gear reducer (42) is installed between the right overrunning clutch (22) and the right propeller (32).

3. A propeller electric propulsion device for adjusting the attitude of an airship according to claim 2, characterised in that a planetary bevel gear reducer is used for the left planetary gear reducer (41) and/or the right planetary gear reducer (42).

4. A propeller electric propulsion device for adjusting the attitude of an airship according to claim 2, characterised by further comprising a left fan (51), the left fan (51) being installed between the left overrunning clutch (21) and the left planetary gear reducer (41);

and/or, further comprising a right fan (52), the right fan (52) being mounted between the right overrunning clutch (22) and the right planetary gear reducer (42).

5. A propeller electric propulsion device for adjusting the attitude of an airship according to claim 4, characterised by further comprising a sleeve (6), the left overrunning clutch (21), the left fan (51), the left planetary gear reducer (41), the motor (1), the right overrunning clutch (22), the right planetary gear reducer (42) and the right fan (52) being arranged in sequence inside the sleeve (6), an annular heat dissipation channel surrounding the motor (1) being formed inside the sleeve (6).

6. Propeller electric propulsion device for adjusting the attitude of an airship according to claim 5, characterised in that the outer walls of the left fan (51) and the right fan (52) support the inner wall of the sleeve (6).

7. A propeller electric propulsion device for the adjustment of the attitude of an airship according to claim 1, characterised by further comprising a multi-stage resolver (7), the multi-stage resolver (7) being installed between the electric motor (1) and the left overrunning clutch (21).

8. Propeller electric propulsion device for the adjustment of the attitude of an airship according to claim 7, characterised in that a multi-stage rotary transformer (7) is used as a brushless rotary transformer.

9. A propeller electric propulsion device for the adjustment of the attitude of an airship according to claim 1, characterised in that the left overrunning clutch (21) and/or the right overrunning clutch (22) is a wedge overrunning clutch.

10. Propeller electric propulsion device for adjusting the attitude of an airship according to claim 1, characterised in that the left propeller (31) and/or the right propeller (32) are fixed-distance tension propellers.

Technical Field

The invention relates to the technical field of airship attitude adjustment, in particular to a propeller electric propulsion device for adjusting the attitude of an airship.

Background

The high-altitude airship platform requires hovering at a fixed point and maneuvering flying at a high altitude above a stratosphere for a long time, the maximum wind resistance of the high-altitude airship platform exceeds 20m/s, and in order to realize that the airship platform continuously executes tasks in a specified area, a high-altitude power system which is suitable for a high-altitude environment and meets the requirements of airship hovering at a fixed point and maneuvering flying power propulsion needs to be developed.

Since the air at the upper air above the stratosphere is thin and the air temperature is low, and the airship flies at high air, the air input of the fuel engine is reduced due to the low air density, and the effectiveness of the traditional power system needing oxygen is reduced, so that the most effective high-altitude power source is a power device (such as a solar power device) needing no oxygen, and the low-altitude power propelling devices such as turboprop, piston engine and the like which are mature at present are not completely suitable for high-altitude propelling of the airship. Due to the technical requirements on the propulsion efficiency and the working stability, a set of propeller electric propulsion mode with a brand-new system, such as light weight, high efficiency, long service life, strong adaptability and high stability, needs to be developed for the high-altitude airship to verify the feasibility of power propulsion and yaw in the high-altitude environment above the stratosphere.

Disclosure of Invention

In order to solve the technical problems in the background art, the invention provides a propeller electric propulsion device for adjusting the posture of an airship.

The invention provides a propeller electric propulsion device for adjusting the posture of an airship, which comprises: the motor, the left overrunning clutch, the left propeller, the right overrunning clutch and the right propeller;

the left screw propeller is connected with the left output end through a left overrunning clutch, the left overrunning clutch is used for controlling the one-way rotation of the left screw propeller, the right screw propeller is connected with the right output end through a right overrunning clutch, and the right overrunning clutch is used for controlling the one-way rotation of the right screw propeller in the direction opposite to that of the left screw propeller.

Preferably, the left planetary gear reducer is further included and is connected between the left overrunning clutch and the left propeller;

and/or the right planetary gear reducer is arranged between the right overrunning clutch and the right screw propeller.

Preferably, the left planetary gear reducer and/or the right planetary gear reducer adopt a planetary bevel gear reducer.

Preferably, the left fan is installed between the left overrunning clutch and the left planetary gear reducer;

and/or, a right fan is further included and is mounted between the right overrunning clutch and the right planetary gear reducer.

Preferably, the fan cooling device further comprises a sleeve, wherein the left overrunning clutch, the left fan, the left planetary gear reducer, the motor, the right overrunning clutch, the right planetary gear reducer and the right fan are sequentially arranged in the sleeve, and an annular heat dissipation channel surrounding the motor is formed in the sleeve.

Preferably, the outer walls of the left and right fans support the inner wall of the sleeve.

Preferably, a multi-stage resolver is further included, the multi-stage resolver being mounted between the motor and the left overrunning clutch.

Preferably, the multi-stage resolver is a brushless resolver.

Preferably, the left overrunning clutch and/or the right overrunning clutch adopt wedge overrunning clutches.

Preferably, the left propeller and/or the right propeller adopt a fixed-distance tension propeller.

According to the propeller electric propulsion device for adjusting the posture of the airship, the two sides of the motor are respectively provided with the left output end and the right output end, the left propeller is connected with the left output end through the left overrunning clutch, the left overrunning clutch is used for controlling the left propeller to rotate in a single direction, the right propeller is connected with the right output end through the right overrunning clutch, and the right overrunning clutch is used for controlling the right propeller to rotate in a single direction opposite to the left propeller. The invention designs a propeller electric propulsion device for adjusting the high-altitude flight attitude of an airship aiming at the high-altitude flight environment, the whole structure adopts a linear cylindrical structure, the installation is easy, the propeller reversing work can be realized by only adopting one set of motor driving device, the reversing is easy, the full electric propulsion mode is adopted, no oxygen power is needed, and the yaw propulsion of the airship can be realized.

Drawings

Fig. 1 is a schematic structural diagram of a propeller electric propulsion device for adjusting the posture of an airship according to the present invention.

Fig. 2 is a schematic structural view of the planetary gear reducer of the present embodiment.

Fig. 3 is a schematic structural diagram of the overrunning clutch of the present embodiment.

Detailed Description

As shown in fig. 1 to 3, fig. 1 is a schematic structural diagram of a propeller electric propulsion device for adjusting an attitude of an airship according to the present invention, fig. 2 is a schematic structural diagram of a planetary gear reducer according to the present embodiment, and fig. 3 is a schematic structural diagram of an overrunning clutch according to the present embodiment.

Referring to fig. 1, the present invention provides a propeller electric propulsion device for adjusting the posture of an airship, including: the motor 1, the left overrunning clutch 21, the left propeller 31, the right overrunning clutch 22 and the right propeller 32;

the two sides of the motor 1 are respectively provided with a left output end and a right output end, the left propeller 31 is connected with the left output end through a left overrunning clutch 21, the left overrunning clutch 21 is used for controlling the left propeller 31 to rotate in one direction, the right propeller 32 is connected with the right output end through a right overrunning clutch 22, and the right overrunning clutch 22 is used for controlling the right propeller 32 to rotate in one direction opposite to the left propeller 31.

In the specific working process of the propeller electric propulsion device for adjusting the posture of the airship, when the motor rotates forwards, the right overrunning clutch is disengaged, the right propeller does not work, the left overrunning clutch is connected with the left screw shaft, and at the moment, the left propeller rotates to work to realize the right yaw of the airship; on the contrary, when the motor rotates reversely, the left overrunning clutch is disengaged, the left propeller does not work, the right overrunning clutch is connected with the right screw shaft, and the right screw shaft rotates to work to realize the left yaw of the airship.

In this embodiment, the proposed propeller electric propulsion device for adjusting the posture of an airship has a left output end and a right output end on two sides of a motor respectively, the left propeller is connected with the left output end through a left overrunning clutch, the left overrunning clutch is used for controlling the left propeller to rotate in a single direction, the right propeller is connected with the right output end through a right overrunning clutch, and the right overrunning clutch is used for controlling the right propeller to rotate in a single direction opposite to that of the left propeller. The invention designs a propeller electric propulsion device for adjusting the high-altitude flight attitude of an airship aiming at the high-altitude flight environment, the whole structure adopts a linear cylindrical structure, the installation is easy, the propeller reversing work can be realized by only adopting one set of motor driving device, the reversing is easy, the full electric propulsion mode is adopted, no oxygen power is needed, and the yaw propulsion of the airship can be realized.

In the specific embodiment, a left planetary gear reducer 41 is further included, and the left planetary gear reducer 41 is connected between the left overrunning clutch 21 and the left propeller 31; a right planetary gear reducer 42 is also included, the right planetary gear reducer 42 being mounted between the right overrunning clutch 22 and the right propeller 32.

Specifically, the left planetary gear reducer 41 and/or the right planetary gear reducer 42 employ a large-torque, low-weight planetary helical gear reducer. The reduction ratio is more than 5, the cooling device has the characteristics of stable operation, low impact, vibration and noise and the like, and the cooling mode adopts natural air cooling and radiation heat dissipation. The stretching dynamic seal of the speed reducer shaft adopts a double-lip rubber dynamic seal ring for water proofing and lubricating oil sealing, and can meet the requirements of high linear speed and long service life. Specifically, referring to fig. 2, the planetary gear reducer includes a reducer shaft extension seal 111, and a double-lip rubber dynamic seal ring is used for waterproof and lubricating oil sealing, so that the requirements of high linear speed and long service life can be met; the planet carrier 112 adopts an integral two-end supporting structure, so that the planet carrier has high torsional rigidity and high and stable supporting performance for a large-diameter propeller; the first reducer bearing 113 is an angular contact ball bearing, and can bear the axial force increased by the planetary helical gear reducer; the second reducer bearing 117 is an angular contact ball bearing; the lubricating oil 118 is gear lubricating oil. In a specific design mode, the planet wheels 114 and the sun wheel 116 are processed by gear hobbing and gear grinding so as to improve the high bearing capacity and the running stability of the planet wheels. In addition, in order to ensure the compact structure of the reducer and the motor 1, the internal gear 115 of the reducer and the front bearing chamber of the motor 1 are designed into a whole, and the axial length dimension is reduced to effectively reduce the weight.

In order to ensure the heat dissipation of the motor and the planetary gear reducer, the present embodiment further includes a left fan 51, the left fan 51 being installed between the left overrunning clutch 21 and the left planetary gear reducer 41, and a right fan 52, the right fan 52 being installed between the right overrunning clutch 22 and the right planetary gear reducer 42.

Further, the device also comprises a sleeve 6, wherein the left overrunning clutch 21, the left fan 51, the left planetary gear reducer 41, the motor 1, the right overrunning clutch 22, the right planetary gear reducer 42 and the right fan 52 are sequentially arranged in the sleeve 6, and an annular heat dissipation channel surrounding the motor 1 is formed in the sleeve 6; the sleeve externally protects the overrunning clutch, the left fan, the left planetary gear reducer, the motor, the right overrunning clutch, the right planetary gear reducer and the right fan, and meanwhile, an annular ventilation channel is formed outside the motor and the planetary gear reducer through the design of the sleeve and the fan, so that the heat dissipation of the motor and the planetary gear reducer is guaranteed. The two ends of the sleeve are matched with the propeller shaft through rotary dynamic seals, and the rotary dynamic seals can adopt double-lip rubber dynamic seal rings, are used for water proofing and sealing lubricating oil, and can meet the requirements of high linear speed and long service life.

In a specific installation of the jacket body, the outer walls of the left fan 51 and the right fan 52 support the inner wall of the sleeve 6.

In addition, the present embodiment further includes a multi-stage resolver 7, the multi-stage resolver 7 being installed between the motor 1 and the left overrunning clutch 21; as the position sensor, a brushless rotary transformer with high precision, high reliability and strong anti-interference capability is adopted, the precision reaches 10 minutes, the position sensor is used for detecting the position of the rotation of a motor, and the position sensor is particularly suitable for occasions where a rotary encoder cannot normally work, such as high temperature, severe cold, humidity, high speed, high vibration and the like.

Referring to fig. 3, in a specific selection mode of the overrunning clutch, the left overrunning clutch 21 and/or the right overrunning clutch 22 adopt a wedge overrunning clutch, and the reverse unlocking is light, the structure is compact, and the operation is convenient. As shown in fig. 3, the overrunning clutch has a self-clutch function by changing the rotation direction of the driving part and the driven part. A certain number of wedge elements, namely wedges 222, are arranged between the raceways of the inner ring 221 and the outer ring 223, and due to the eccentric action of the working arc of the wedges 222, when the inner ring 221 rotates in the forward direction, torque can be transmitted to the outer ring 223 to drive the propeller to rotate, and when the inner ring 221 rotates in the reverse direction, torque cannot be transmitted to the outer ring 223, so that the large end cover 224 has relative idling performance, and is connected with the planetary gear reducer through a pin 225.

In the specific design mode of the propeller, the left propeller 31 and/or the right propeller 32 adopt fixed-distance tension propellers, the main components comprise blades, a propeller hub and fasteners, in order to reduce the weight, the two-blade propeller hub and the blades are integrally designed, and the maximum wind-resistant wind speed reaches 20 m/s.

The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.