阅读说明：本技术 一种共轴双桨八旋翼飞行器 (Coaxial double-oar eight rotor crafts ) 是由 莫帅 李旭 宋文浩 侯茂祥 宋裕玲 杨振宁 岳宗享 党合玉 邹振兴 石丽娟 黄青 于 2019-11-11 设计创作，主要内容包括：本发明公开了一种共轴双桨八旋翼飞行器,其特征在于驱动电机与一级小齿轮相连,一级小齿轮与一级面齿轮相啮合,一级面齿轮固定在一级传动轴上,一级传动轴两端各有一个二级小齿轮,二级小齿轮与二级面齿轮啮合,二级面齿轮固定在二级传动轴上,二级传动轴两端各有一个三级小齿轮,三级小齿轮与输入面齿轮啮合；有益效果是设计原理新颖,结构巧妙独特,可根据负载大小改变旋翼运动数量来切换动力,具有非常广阔的商业前景,即可以填补相关技术空白,又可产生较大的社会效益与经济效益。(The invention discloses a coaxial double-propeller eight-rotor aircraft which is characterized in that a driving motor is connected with a primary pinion, the primary pinion is meshed with a primary face gear, the primary face gear is fixed on a primary transmission shaft, two ends of the primary transmission shaft are respectively provided with a secondary pinion, the secondary pinions are meshed with a secondary face gear, the secondary face gear is fixed on a secondary transmission shaft, two ends of the secondary transmission shaft are respectively provided with a tertiary pinion, and the tertiary pinions are meshed with an input face gear; the novel rotary wing power transmission device has the advantages of novel design principle, ingenious and unique structure, capability of changing the motion quantity of the rotary wings to switch power according to the load, very wide commercial prospect, capability of filling up the blank of the related technology and capability of generating great social benefit and economic benefit.)

1. A coaxial double-propeller eight-rotor aircraft is characterized in that a driving motor is connected with a first-stage pinion, the first-stage pinion is meshed with a first-stage face gear, the first-stage face gear is fixed on a first-stage transmission shaft, two ends of the first-stage transmission shaft are respectively provided with a second-stage pinion, the second-stage pinion is meshed with a second-stage face gear, the second-stage face gear is fixed on a second-stage transmission shaft, two ends of the second-stage transmission shaft are respectively provided with a third-stage pinion, and the third-stage pinions are meshed with an input;

the input face gear is connected with the upper rotor shaft through a spline, the upper rotor shaft is fixedly connected with the upper face gear, the upper rotor shaft is connected with the upper rotor through a spline and a clamp spring, the upper face gear is meshed with a pair of symmetrically arranged input pinions, the lower face gear is also meshed with the input pinions, the input pinions are fixed on the power conversion frame, and a bearing assembly is arranged between the input pinions and the power conversion frame;

a bearing assembly is arranged between the upper rotor shaft and the lower rotor shaft, the lower rotor shaft is connected with a lower gear through a screw, the lower rotor shaft is connected with the lower rotor through a spline and a snap spring, a friction plate is fixedly connected to the lower rotor shaft, a braking platform is fixed between the lower rotor friction plate and the power conversion frame, an upper braking piece is connected with the lower braking piece through a screw, the upper braking piece is connected with the braking platform through a spring and a guide pillar, and an electromagnetic coil is fixed on the braking platform;

braking platform is fixed in on the aircraft shell, two secondary drive axle are placed at spatial symmetry, the one-level pinion is located overall structure central point and puts, six brake spring place around last rotor shaft equidistant, the guide pillar is placed around last rotor shaft equidistant, the one-level transmission shaft passes through the bearing and installs on the aircraft shell, the secondary drive axle passes through the bearing and installs on the shell, four rotor systems are spatial symmetry about the one-level pinion and place, upper and lower rotor turns to oppositely, adjacent two sets of rotor turns to oppositely, relative two sets of rotor turns to the same.

Technical Field

The invention relates to the field of multi-axis aircrafts, in particular to a coaxial double-propeller eight-rotor aircraft.

Background

The quadcopter has the characteristics of small volume, light weight, simple structure, easiness in control, low cost, miniaturization and the like, and is widely applied to military and civil fields based on the characteristics, such as radar positioning, geological exploration, forest monitoring, electric stringing, agricultural plant protection, aerial photography and the like.

The four-axis aircraft is a new aircraft, is developed on the basis of the traditional helicopter, overcomes the defects of complex mechanical structure, poor flying and hovering stability and the like of the helicopter, and has a series of advantages of small volume, light weight, simple structure and the like, so the four-axis aircraft increasingly receives wide attention at home and abroad. However, at present, the problems of large power consumption, low load capacity, short endurance and the like of the multi-axis aircraft still exist.

In order to solve the defects that a four-axis aircraft control system in the prior art is complex, has low cruising ability and can not work when one rotor wing is damaged, the invention provides a coaxial double-propeller eight-rotor aircraft which has simple structure, high reliability, unique configuration and novel principle, can adjust power output along with the load, and can close the power output of the symmetrical rotor wings to continue to work normally under the condition that one rotor wing is damaged; the method can meet the actual requirements of the four-axis aircraft in working environments of various fields, fill up the blank of related technologies, and produce great social and economic benefits.

Disclosure of Invention

In order to overcome the defects of the prior art, the invention provides a coaxial double-propeller eight-rotor aircraft, which has a unique operating principle, breaks through the conventional operating technical scheme, has novel conception, realizes flight control by adjusting the rotating speed of a lower rotor, has the characteristics of high reliability and simple structure compared with the existing method of changing the pitch by rotors, and can close the power output of the rotors of a symmetrical group so as to maintain flight and stably land when one group of rotors are damaged.

A coaxial double-propeller eight-rotor aircraft is characterized in that a driving motor is connected with a first-stage pinion, the first-stage pinion is meshed with a first-stage face gear, the first-stage face gear is fixed on a first-stage transmission shaft, two ends of the first-stage transmission shaft are respectively provided with a second-stage pinion, the second-stage pinion is meshed with a second-stage face gear, the second-stage face gear is fixed on a second-stage transmission shaft, two ends of the second-stage transmission shaft are respectively provided with a third-stage pinion, and the third-stage pinions are meshed with an input;

furthermore, the input face gear is connected with the upper rotor shaft through a spline, the upper rotor shaft is fixedly connected with the upper face gear, the upper rotor shaft is connected with the upper rotor through the spline and a clamp spring, the upper face gear is meshed with a pair of symmetrically-arranged input pinions, the lower face gear is also meshed with the input pinions, the input pinions are fixed on the power conversion frame, and a bearing assembly is arranged between the input pinions and the power conversion frame;

furthermore, a bearing assembly is arranged between the upper rotor shaft and the lower rotor shaft, the lower rotor shaft is connected with a lower gear through a screw, the lower rotor shaft is connected with the lower rotor through a spline and a snap spring, a friction plate is fixedly connected to the lower rotor shaft, a braking platform is fixed between the lower rotor friction plate and the power conversion frame, an upper braking plate is connected with a lower braking plate through a screw, the upper braking plate is connected with the braking platform through a spring and a guide pillar, and an electromagnetic coil is fixed on the braking platform;

furthermore, braking platform is fixed in on the aircraft shell, two secondary drive axle are placed at spatial symmetry, the one-level pinion is located overall structure central point and puts, six brake spring place around last rotor shaft equidistant, the guide pillar is placed around last rotor shaft equidistant, the one-level drive axle passes through the bearing and installs on the aircraft shell, the secondary drive axle passes through the bearing and installs on the shell, four rotor systems are spatial symmetry about the one-level pinion and place, upper and lower rotor turns to oppositely, two sets of adjacent rotors turn to oppositely, two sets of rotor turns to the same relatively.

Compared with the prior art, the invention has the following beneficial effects: the design principle is novel, and the structure is unique, realizes changing aircraft flight state through adjusting rotor speed down, and rotor work together about when the load is big, only goes up the rotor work when the load is little, still can fly and land steadily under the impaired circumstances of a set of rotor among them, has very wide commercial prospect, can fill up relevant technical blank, can produce great social and economic benefits again.

Drawings

Fig. 1 is a (single) set of internal structure of a coaxial twin-oar eight-rotor aircraft.

Figure 2 is a coaxial twin-oar eight rotor craft (single set).

Fig. 3 is a three-dimensional cross-sectional view of a coaxial twin-bladed eight-rotor aircraft (single stack).

Figure 4 is a coaxial twin-bladed eight-rotor aircraft.

In fig. 1:

1. an upper rotor; 2. An inter-shaft bearing snap spring; 3. A lower rotor;

4. a friction plate; 5. Braking the platform; 6. A brake spring;

7. a lower brake pad; 8. A transition frame bearing; 9. lower gear

10. A pinion snap spring; 11. A cylindrical roller bearing; 12. An input pinion gear;

13. an input face gear; 14. An input face gear clamp spring; 15. An upper rotor shaft;

16. an upper gear; 17. A power conversion frame; 18. A cylindrical roller bearing snap spring;

19. screw holes; 20. A conversion frame bearing clamp spring; 21. Countersunk screw holes;

22. a guide post; 23. An electromagnetic coil; 24. An upper brake pad;

25. a lower rotor shaft; 26. A lower rotor clamp spring; 27. An inter-shaft bearing;

28. an upper rotor clamping spring; 29. A primary pinion gear; 30. A primary transmission shaft;

31. a secondary face gear; 32. A clutch; 33. A drive motor;

34. a primary face gear; 35. A tertiary pinion; 36. A secondary face gear snap spring;

37. a secondary pinion gear; 38. A second-level pinion clamp spring; 39. A secondary transmission shaft.

In fig. 2:

I. a rotor system.

Detailed Description

Embodiments of the present invention will be described with reference to the accompanying drawings, and the present invention will be described in detail below with reference to fig. 1 to 2.

A coaxial double-paddle eight-rotor aircraft comprises an upper rotor 1, an inter-axle bearing clamp spring 2, a lower rotor 3, a friction plate 4, a brake platform 5, a brake spring 6, a lower brake block 7, a conversion frame bearing 8, a lower gear 9, a pinion clamp spring 10, a cylindrical roller bearing 11, an input pinion 12, an input face gear 13, an input face gear clamp spring 14, an upper rotor shaft 15, an upper face gear 16, a power conversion frame 17, a cylindrical roller bearing clamp spring 18, a screw hole 19, a conversion frame bearing clamp spring 20, a countersunk screw hole 21, a guide post 22, an electromagnetic coil 23, an upper brake block 24, a lower rotor shaft 25, a lower rotor clamp spring 26, an inter-axle bearing 27, an upper rotor clamp spring 28, a first-level pinion 29, a first-level transmission shaft 30, a second-level face gear 31, a clutch 32, a driving motor 33, a first-level face gear 34, a third-level pinion 35, a second-level face gear clamp spring 36, A secondary pinion clamp spring 38 and a secondary transmission shaft 39.

The driving motor 33 is connected with a primary pinion 29, the primary pinion 29 is meshed with a primary face gear 34, the primary face gear 34 is fixed on a primary transmission shaft 30, two secondary pinions 37 are respectively arranged at two ends of the primary transmission shaft 30, and the secondary pinions 37 are meshed with a secondary face gear 31.

The secondary face gear 31 is fixed on a secondary transmission shaft 39, the secondary transmission shaft 39 is divided into two sections, the two sections are connected through a clutch 32, two three-stage pinions 35 are respectively arranged at two ends of the secondary transmission shaft 39, the three-stage pinions 35 are meshed with the input face gear 13, and the input face gear 13 is connected with the upper rotor shaft 15 through splines.

The upper rotor shaft 15 is fixedly connected with an upper gear 16, the upper rotor shaft 15 is connected with the upper rotor 1 through a spline and an upper rotor clamp spring 28, the upper gear 16 is meshed with a pair of symmetrically-arranged input pinions 12, a lower gear 9 is also meshed with the input pinions 12, the input pinions 12 are fixed on a power conversion frame 17, cylindrical roller bearings 11 are arranged between the input pinions 12 and the power conversion frame 17, and the cylindrical roller bearings are axially positioned through the pinion clamp springs 10 and the cylindrical roller bearings 18.

An inter-shaft bearing 27 is arranged between the upper rotor shaft 15 and the lower rotor shaft 25, the inter-shaft bearing 27 is axially positioned through an inter-shaft bearing snap spring 2, the lower rotor shaft 25 is connected with a lower gear 9 through a screw 19 by a screw, the lower rotor shaft 25 is connected with the lower rotor 3 through a spline and a lower rotor snap spring 26, a friction plate 4 is fixedly connected onto the lower rotor shaft 25, a braking platform 5 is fixed between the lower rotor friction plate 4 and the power conversion frame 17, an upper braking piece 24 is connected with a lower braking piece 7 through a countersunk screw hole 21 by a screw, the upper braking piece 24 is connected with the braking platform 5 through a braking spring 6 and a guide post 22, and an electromagnetic coil 23 is fixed onto the braking platform 5.

The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and all modifications, alterations, and equivalents of the above embodiments according to the principles of the present invention are within the scope of the present invention.