CN210912871U - Eight rotor crafts of four-axis - Google Patents

Abstract

The utility model discloses a four-axis eight-rotor aircraft, which is characterized in that a driving motor is connected with a first-level pinion, the first-level pinion is meshed with a first-level face gear, the first-level face gear is fixed on a first-level transmission shaft, two ends of the first-level transmission shaft are respectively provided with a second-level pinion, the second-level pinion is meshed with a second-level face gear, the second-level face gear is fixed on a second-level transmission shaft, two ends of the second-level transmission shaft are respectively provided with a third-level pinion, and the third-level pinion is meshed; 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.

Description

Eight rotor crafts of four-axis

Technical Field

The utility model relates to a multiaxis aircraft field especially relates to an eight rotor crafts of four-axis.

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 the control system of the four-axis aircraft in the prior art is complex, the cruising ability is low and one of the rotors is damaged and can not work, the utility model provides a four-axis eight-rotor aircraft which has simple structure, high reliability, unique configuration and novel principle, can adjust the power output along with the load size, and can close the power output of the rotors of the symmetrical group to continue normal work under the condition that one group of rotors are 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 above-mentioned prior art not enough, the utility model provides an eight rotor crafts of four-axis, this aircraft manipulation principle is unique, breaks through conventional manipulation technical scheme, conceives novelly, and the rotational speed through the rotor under the adjustment realizes flight control, has the characteristics that the reliability is high and simple structure for current method through rotor variable pitch, moreover when under the impaired condition of one of them group rotor, thereby can close symmetrical group rotor power take off and maintain flight and steady landing.

A four-shaft eight-rotor aircraft 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 secondary pinions are arranged at two ends of the primary transmission shaft respectively and are meshed with a secondary face gear, the secondary face gear is fixed on a secondary transmission shaft, two tertiary pinions are arranged at two ends of the secondary transmission shaft respectively and are meshed with an input face gear;

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 beneficial effects of the utility model are as follows: 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 quad-eight rotor aircraft interior architecture (single stack).

Fig. 2 is a quad-quad eight rotor aircraft (single unit).

Fig. 3 is a three-dimensional cross-sectional view of a (single) quad-eight rotor aircraft.

Figure 4 is a quad-quad.

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

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

A four-axis 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 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 primary pinion 29, a primary transmission shaft 30, a secondary face gear 31, a clutch 32, a driving motor 33, a primary face gear 34, a tertiary pinion 35, a secondary face gear clamp spring 36, a secondary pinion 37, a brake spring, 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, only be the preferred embodiment of the utility model discloses a it is not right the utility model discloses do any restriction, all according to the utility model discloses any modification, change and equivalent change to above embodiment are done to the entity all still belong to within the scope of protection of the technique of the utility model.

Claims (1)

1. A four-shaft eight-rotor aircraft 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 secondary pinions are arranged at two ends of the primary transmission shaft respectively and are meshed with a secondary face gear, the secondary face gear is fixed on a secondary transmission shaft, two tertiary pinions are arranged at two ends of the secondary transmission shaft respectively and are meshed with an input face gear;

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.

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