CN214824110U

CN214824110U - Double-rotor power system of aircraft

Info

Publication number: CN214824110U
Application number: CN202121698331.9U
Authority: CN
Inventors: 臧晓晨; 张同任; 魏德宸; 陈永斌; 王子安; 牛群; 高照
Original assignee: Binzhou University
Current assignee: Binzhou University
Priority date: 2021-07-23
Filing date: 2021-07-23
Publication date: 2021-11-23
Anticipated expiration: 2031-07-23

Abstract

The utility model discloses an aircraft dual-rotor power system, which belongs to the technical field of aircraft power devices and comprises a mounting frame, an engine, a transmission main shaft, blades and two differential tilting steering engines, wherein the transmission main shaft is rotatably arranged on the mounting frame in a penetrating way and is in transmission connection with the engine; a hollow shaft in transmission connection with the differential tilting steering engine is respectively rotatably sleeved on the transmission main shafts on the two sides of the mounting rack, and a tilting bracket is arranged at one end of the hollow shaft; the paddle is rotatably installed with the tilting bracket through the paddle shaft; the transmission main shaft is in transmission connection with the propeller shaft through a bevel gear set. The engine drives the transmission main shaft to drive the propeller shaft and the propeller blades to rotate through the bevel gear set, so that the propeller blades are driven; the differential tilting steering engine drives the hollow shaft to drive the tilting support to rotate, so that flexible tilting of the paddle is realized. The power component is integrated on the mounting frame, the structure is compact, the size of the power cabin is reduced, the flying resistance caused by leakage outside the power cabin is reduced, the rotational inertia of the system is concentrated, the flying control is facilitated, and the practicability is good.

Description

Double-rotor power system of aircraft

Technical Field

The utility model belongs to the technical field of aircraft power device, specifically speaking are aircraft bispin wing driving system.

Background

The vertical take-off and landing fixed wing unmanned aerial vehicle has the capabilities of taking off and landing a rotor wing and controlling hovering, has the advantages of high speed, long voyage, low oil consumption and the like of a fixed wing aircraft, can be widely applied to various fields, and has important research value and economic benefit.

The tilt rotor type aircraft has the functions of vertical take-off and landing and fixed-point hovering of a gyroplane, has the advantages of high flying speed and long voyage of a fixed-wing aircraft, and is one of the main development directions of future aircrafts.

In the existing tilt rotor type aircraft, a power system on the aircraft is only the superposition of two or more sets of helicopter rotor systems in principle, so that the aircraft has high failure rate and is difficult to apply to small and medium-sized aircraft platforms; and the power system of the tilt rotor aircraft has a complex structure and the power cabin is large in size, so that the reduction of flight resistance is not facilitated.

SUMMERY OF THE UTILITY MODEL

The problem that a power system on the existing tilt rotor type aircraft is the superposition of two or more sets of helicopter rotor systems is solved, so that the fault rate is high, and the power system is difficult to be applied to small and medium-sized aircraft platforms; and the driving system structure of rotor class aircraft verts is complicated, and the engine compartment is bulky, is unfavorable for reducing the problem of flight resistance, the utility model provides an aircraft bispin wing driving system.

The utility model discloses a realize through following technical scheme:

a double-rotor power system of an aircraft comprises a mounting frame, an engine, a transmission main shaft, a paddle and two differential tilting steering engines, wherein the engine and the differential tilting steering engines are respectively connected and mounted with the mounting frame; the transmission main shaft is rotatably arranged on the mounting frame in a penetrating manner and is in transmission connection with the engine; a hollow shaft in transmission connection with the differential tilting steering engine is respectively rotatably sleeved on the transmission main shafts on the two sides of the mounting frame, and a tilting support is arranged at one end, far away from the mounting frame, of the hollow shaft; the paddle is rotatably mounted with the tilting bracket through a paddle shaft; the transmission main shaft is in transmission connection with the paddle shaft through a bevel gear set. The engine drives the transmission main shaft to rotate, and the bevel gear set drives the propeller shaft and the propeller blades to rotate, so that the propeller blades are driven by power; the two differential tilting steering engines drive the two hollow shafts respectively, and the hollow shafts drive the tilting supports to rotate, so that the propeller shafts and the blades rotate along the annular meshing positions of the bevel gear sets, the bevel gear sets are guaranteed to be meshed all the time, and the blades can be tilted flexibly. The differential tilting steering engine and the engine are integrated on the mounting frame together, the structural design is compact, the size of the power cabin is effectively reduced, the flight resistance caused by leakage outside the power cabin is reduced, the left power part and the right power part are symmetrically and intensively arranged, the rotational inertia of the system is centralized, and the flying control is facilitated; the differential tilting steering engine drives the blades to tilt, so that the aircraft can tilt forwards and accelerate, and meanwhile, the yaw and the roll of the aircraft can be controlled in a vertical mode and a horizontal mode; the whole structure is simple, the control is flexible, and the practicability is good.

The utility model is further improved in that a one-way clutch belt wheel is arranged on the transmission main shaft, and an engine belt wheel is arranged on the engine output shaft; the engine belt wheel is in transmission connection with the one-way clutch belt wheel through a belt. The transmission is accurate and stable, and the reliability is good; the unidirectional clutch belt wheel can ensure that the blades can automatically rotate by inertia after the engine loses power, and the blades are prevented from being crashed due to sudden power loss.

The utility model is further improved in that two differential tilting steering engines are symmetrically arranged on two sides of the mounting frame, and a first synchronous belt pulley is arranged on an output shaft of the differential tilting steering engine; a second synchronous belt wheel is mounted on the hollow shaft; the second synchronous belt wheel is in transmission connection with the first synchronous belt wheel through a belt. The mounting frames of the differential tilting steering engine, the first synchronous belt pulley and the second synchronous belt pulley, which are close to the middle part, are integrally arranged, so that the structure is compact, and the volume of the power cabin is effectively reduced; two differential tilting steering engines drive two hollow shafts to rotate respectively through belt transmission, thereby realizing independent tilting of paddles on two sides, realizing various operation states of the aircraft, being convenient to control and good in flexibility.

The utility model is further improved by that the bevel gear group comprises a first bevel gear arranged on the transmission main shaft and a second bevel gear arranged on the propeller shaft; the first bevel gear is meshed with the second bevel gear at right angle. When the differential tilting steering engine drives the tilting bracket and the paddle to tilt, the second bevel gear on the paddle shaft rotates around the first bevel gear, and the first bevel gear and the second bevel gear can be always meshed, so that the use reliability of the whole power system is ensured; the paddle shaft is perpendicular to the transmission main shaft, so that the partial thrust in the left and right opposite directions cannot occur after the paddles tilt, and the output conversion efficiency of the engine is improved.

The utility model is further improved in that a variable-pitch steering engine is arranged on the hollow shaft, a variable-pitch disc is sleeved on the propeller shaft in a sliding manner, and the variable-pitch disc is connected with the propeller hub of the propeller blade through a rocker arm of the propeller hub; the variable-pitch steering engine is connected with the variable-pitch disc through a variable-pitch operating lever. The variable-pitch steering engine drives the variable-pitch disc to slide up and down along the propeller shaft through the variable-pitch control rod, so that the propeller hub rocker is driven to perform variable-pitch adjustment on the propeller blades, and flexible and periodic variable pitch of the propeller blades is realized.

The utility model discloses a further improvement still, the displacement dish through hollow slider structure with the leg joint that verts. The hollow slide block structure can ensure the up-and-down movement stability of the variable-pitch disc, avoid the interference to the rotation of the propeller shaft and ensure the operation reliability.

According to the technical scheme provided by the utility model, the beneficial effects are that: the engine drives the transmission main shaft to rotate, and the bevel gear set drives the propeller shaft and the propeller blades to rotate, so that the propeller blades are driven by power; the two differential tilting steering engines drive the two hollow shafts respectively, and the hollow shafts drive the tilting supports to rotate, so that the propeller shafts and the blades rotate along the annular meshing positions of the bevel gear sets, the bevel gear sets are guaranteed to be meshed all the time, and the blades can be tilted flexibly. The differential tilting steering engine and the engine are integrated on the mounting frame together, the structural design is compact, the size of the power cabin is effectively reduced, the flight resistance caused by leakage outside the power cabin is reduced, the left power part and the right power part are symmetrically and intensively arranged, the rotational inertia of the system is centralized, and the flying control is facilitated; the differential tilting steering engine drives the blades to tilt, so that the aircraft can tilt forwards and accelerate, and meanwhile, the yaw and the roll of the aircraft can be controlled in a vertical mode and a horizontal mode; the whole structure is simple, the control is flexible, and the practicability is good.

Drawings

In order to more clearly illustrate the technical solution of the present invention, the drawings used in the description will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without creative efforts.

Fig. 1 is a schematic structural diagram of an embodiment of the present invention.

Fig. 2 is a schematic sectional structure diagram of an embodiment of the present invention.

Fig. 3 is a schematic view of a tilting bracket mounting structure according to an embodiment of the present invention.

In the drawings: 1. the variable-pitch steering engine comprises blades, 2, a hollow shaft, 3, an engine, 4, a differential tilting steering engine, 5, a hub rocker arm, 6, a tilting support, 7, a variable-pitch steering engine, 8, a transmission main shaft, 9, a propeller shaft, 10, a second synchronous belt wheel, 11, a first synchronous belt wheel, 12, a one-way clutch belt wheel, 13, a second bevel gear, 14, a first bevel gear, 15, a variable-pitch control lever, 16 and a variable-pitch disc.

Detailed Description

In order to make the objects, features and advantages of the present invention more obvious and understandable, the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments, and obviously, the embodiments described below are only some embodiments of the present invention, not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the scope of protection of this patent.

As shown in fig. 1-3, the utility model discloses an aircraft dual-rotor power system, which comprises a mounting frame, an engine 3, a transmission main shaft 8 and two differential tilting steering engines 4, wherein the engine 3 and the two differential tilting steering engines 4 are respectively and fixedly mounted with the mounting frame; the transmission main shaft 8 penetrates through the mounting frame from left to right, the middle part of the transmission main shaft is rotatably mounted with the mounting frame through a bearing, and the transmission main shaft 8 is in transmission connection with the engine 3; the transmission main shafts 8 on the two sides of the mounting rack are respectively rotatably sleeved with a hollow shaft 2 in transmission connection with the differential tilting steering engine 4, namely the hollow shaft 2 is rotatably sleeved with the transmission main shafts 8 through bearings; the outer end of the hollow shaft 2 is provided with a tilting bracket 6; a paddle shaft 9 is rotatably arranged in the tilting bracket 6 through a bearing, and two oppositely arranged paddles 1 are arranged at the upper end of the paddle shaft 9; the transmission main shaft 8 is in transmission connection with the paddle shaft 9 through a bevel gear set.

The engine 3 drives the transmission main shaft 8 to rotate, and drives the propeller shaft 9 and the propeller blades 1 to rotate through the bevel gear set, so that the propeller blades 1 are driven by power; two differential steering engine 4 that verts drive respectively two hollow shafts 2, and hollow shaft 2 drives the support 6 rotation that verts to make oar axle 9, paddle 1 rotate along bevel gear's annular meshing position, and guarantee bevel gear and mesh all the time, thereby realize that paddle 1's flexibility verts. The differential tilting steering engine 4 and the engine 3 are integrated on the mounting frame together, the structural design is compact, the size of the power cabin is effectively reduced, the flight resistance caused by leakage outside the power cabin is reduced, the left power part and the right power part are symmetrically and intensively arranged, the rotational inertia of the system is centralized, and the flying control is facilitated; the differential tilting steering engine 4 drives the blades 1 to tilt, so that the aircraft can tilt forwards and accelerate, and meanwhile, the yaw and the roll of the aircraft can be controlled in a vertical mode and a horizontal mode; the whole structure is simple, the control is flexible, and the practicability is good.

Wherein the tilting angle of the blade 1 is 0-90; one end of the hollow shaft 2, which is close to the mounting rack, is provided with a connecting rod, and the mounting rack is provided with a stop block for limiting the forward and reverse rotation angle of the connecting rod; the positive and negative rotation angle of the connecting rod can be limited through the stop block, and the limitation of 0-90-degree tilting angle is effectively realized.

As shown in fig. 1 and 2, a one-way clutch pulley 12 is fixedly sleeved on the transmission main shaft 8, and an engine pulley is arranged on an output shaft of the engine 3; the engine belt wheel is in transmission connection with the one-way clutch belt wheel 12 through a belt. The transmission is accurate and stable, and the reliability is good; the one-way clutch belt wheel 12 can ensure that the blades 1 can automatically rotate by inertia after the engine 3 loses power, and the blades are prevented from being crashed due to sudden power loss.

As shown in fig. 1 and 2, the two differential tilting steering engines 4 are symmetrically installed on two sides of the mounting frame, and first synchronous pulleys 11 are arranged on output shafts of the differential tilting steering engines 4; a second synchronous belt pulley 10 is fixedly sleeved at one end of the hollow shaft 2 close to the mounting rack; the second synchronous pulley 10 is in transmission connection with the first synchronous pulley 11 through a belt. The differential tilting steering engine 4, the first synchronous belt pulley 11 and the second synchronous belt pulley 10 are integrally arranged on the mounting rack close to the middle part, so that the structure is compact, and the size of the power cabin is effectively reduced; two differential tilting steering engines 4 drive two hollow shafts 2 respectively through belt transmission and rotate to realize independent tilting of paddle 1 on both sides, thereby can realize various running states of aircraft, it is convenient to control, and the flexibility is good.

As shown in fig. 2 and 3, the bevel gear set comprises a first bevel gear 14 mounted on the transmission main shaft 8 and a second bevel gear 13 mounted on the paddle shaft 9; the first bevel gear 14 is engaged with the second bevel gear 13 at right angle, i.e. the paddle shaft 9 is arranged perpendicular to the transmission main shaft 8. When the differential tilting steering engine 4 drives the tilting support 6 and the paddle 1 to tilt, the second bevel gear 13 on the paddle shaft 9 rotates around the first bevel gear 14, so that the two are always meshed, and the use reliability of the whole power system is ensured. The propeller shaft 9 is perpendicular to the transmission main shaft 8, so that the partial thrust in the left and right opposite directions cannot occur after the propeller blades 1 tilt, and the output conversion efficiency of the engine 3 is improved.

As shown in fig. 3, a variable-pitch steering engine 7 is mounted at the outer end of the hollow shaft 2 through a variable-pitch steering engine bracket, a variable-pitch disc 16 is slidably sleeved on the propeller shaft 9, and the variable-pitch disc 16 is connected with the hub of the blade 1 through a hub rocker arm 5; the variable-pitch steering engine 7 is connected with the variable-pitch disc 16 through a variable-pitch control lever 15. The variable-pitch steering engine 7 drives the variable-pitch disc 16 to slide up and down along the propeller shaft 9 through the variable-pitch control lever 15, so that the propeller hub rocker arm 5 is driven to perform variable-pitch adjustment on the propeller blades 1, and flexible and periodic variable pitch of the propeller blades 1 is realized.

The pitch disc 16 is connected to the tilt bracket 6 by a hollow slider structure. When the variable-pitch steering engine 7 adjusts the variable-pitch disc 16 up and down through the variable-pitch control lever 15, the up-and-down movement stability of the variable-pitch disc 16 can be ensured through the hollow slide block structure, the interference on the rotation of the propeller shaft 9 is avoided, and the operation reliability is ensured.

The double-rotor power system of the aircraft has the advantages of simple overall structure, flexible control and good practicability; the engine drives the transmission main shaft to rotate, and the bevel gear set drives the propeller shaft and the propeller blades to rotate, so that the propeller blades are driven by power; the two differential tilting steering engines respectively drive the two hollow shafts, and the hollow shafts drive the tilting supports to rotate, so that the propeller shafts and the blades rotate along the annular meshing position of the bevel gear set, the bevel gear set is guaranteed to be meshed all the time, and the blades can be tilted flexibly; the variable-pitch steering engine drives the variable-pitch disc to slide up and down along the propeller shaft through the variable-pitch control rod, so that the propeller hub rocker is driven to perform variable-pitch adjustment on the propeller blades, and flexible and periodic variable pitch of the propeller blades is realized. The differential tilting steering engine and the engine are integrated on the mounting frame together, the structural design is compact, the size of the power cabin is effectively reduced, the flight resistance caused by leakage outside the power cabin is reduced, the left power part and the right power part are symmetrically and intensively arranged, the rotational inertia of the system is centralized, and the flying control is facilitated; the differential tilting steering engine drives the blades to tilt, so that the aircraft can not only tilt forwards and accelerate, but also control yaw and roll in a horizontal mode under a vertical mode of the aircraft.

The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.

The terms "upper", "lower", "outside", "inside" and the like in the description and claims of the present invention and the above drawings are used for distinguishing relative relationships in positions, if any, and are not necessarily given qualitatively. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the invention described herein are capable of operation in sequences other than those illustrated or otherwise described herein. Furthermore, the terms "comprising" and "having," as well as any variations thereof, are intended to cover non-exclusive inclusions.

The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. The double-rotor power system of the aircraft is characterized by comprising a mounting rack, an engine (3), a transmission main shaft (8), a blade (1) and two differential tilting steering engines (4), wherein the engine (3) and the differential tilting steering engines (4) are respectively connected and mounted with the mounting rack; the transmission main shaft (8) is rotatably arranged on the mounting frame in a penetrating manner and is in transmission connection with the engine (3); a hollow shaft (2) in transmission connection with the differential tilting steering engine (4) is respectively rotatably sleeved on the transmission main shafts (8) on the two sides of the mounting rack, and a tilting support (6) is arranged at one end, far away from the mounting rack, of the hollow shaft (2); the paddle (1) is rotatably mounted with the tilting bracket (6) through a paddle shaft (9); the transmission main shaft (8) is in transmission connection with the paddle shaft (9) through a bevel gear set.

2. The dual-rotor power system of the aircraft according to claim 1, wherein a one-way clutch pulley (12) is provided on the transmission main shaft (8), and an engine pulley is provided on the output shaft of the engine (3); the engine belt wheel is in transmission connection with the one-way clutch belt wheel (12) through a belt.

3. The double-rotor power system of the aircraft according to claim 1, wherein the two differential tilting steering engines (4) are symmetrically arranged on two sides of the mounting rack, and output shafts of the differential tilting steering engines (4) are provided with first synchronous belt wheels (11); a second synchronous belt wheel (10) is arranged on the hollow shaft (2); the second synchronous pulley (10) is in transmission connection with the first synchronous pulley (11) through a belt.

4. The aircraft dual rotor power system according to claim 1, wherein the bevel gear set comprises a first bevel gear (14) mounted on the drive shaft (8) and a second bevel gear (13) mounted on the propeller shaft (9); the first bevel gear (14) is meshed with the second bevel gear (13) at right angles.

5. The dual-rotor power system of the aircraft according to claim 1, wherein a variable-pitch steering engine (7) is mounted on the hollow shaft (2), a variable-pitch disc (16) is slidably sleeved on the propeller shaft (9), and the variable-pitch disc (16) is connected with a hub of the blade (1) through a hub rocker arm (5); the variable-pitch steering engine (7) is connected with the variable-pitch disc (16) through a variable-pitch operating rod (15).

6. The aircraft dual-rotor power system according to claim 5, characterized in that the pitch disc (16) is connected to the tilt bracket (6) by means of a hollow slider structure.