阅读说明：本技术 一种可折叠机翼两栖飞行器及其工作方法 (Amphibious aircraft with foldable wings and working method thereof ) 是由 严俊杰 李宜恒 杨超 朱训辉 窦兆起 于 2021-09-26 设计创作，主要内容包括：本发明公开了一种可折叠机翼两栖飞行器,其技术方案要点是包括机身,机身两侧设置有固定翼,固定翼翼端部设置有折叠翼,固定翼上设置有用于控制折叠翼进行翻转折叠的折叠机构,折叠翼上设置有旋翼机构和轮系机构,旋翼机构和轮系机构分设于折叠翼的两侧,折叠翼上还设置有悬架,轮系机构与折叠翼之间通过悬架连接,折叠机构控制所述折叠翼翻转至轮系机构与地面接触或与固定翼水平。本发明一种可折叠机翼两栖飞行器,具有提高整体地面工作的稳定性和安全性,为整体机体提供可靠的地面工作性能。(The invention discloses an amphibious aircraft with foldable wings, which is characterized by comprising an aircraft body, wherein fixed wings are arranged on two sides of the aircraft body, folding wings are arranged at the end parts of the fixed wings, folding mechanisms used for controlling the folding wings to turn and fold are arranged on the fixed wings, a rotor wing mechanism and a wheel train mechanism are arranged on the folding wings, the rotor wing mechanism and the wheel train mechanism are respectively arranged on two sides of the folding wings, a suspension is also arranged on the folding wings, the wheel train mechanism is connected with the folding wings through the suspension, and the folding mechanism controls the folding wings to turn until the wheel train mechanism is in contact with the ground or is horizontal to the fixed wings. The amphibious aircraft with the foldable wings has the advantages that the stability and the safety of the whole ground work are improved, and the reliable ground work performance is provided for the whole aircraft body.)

1. A amphibious aircraft with foldable wings comprises a fuselage (1) and is characterized in that: fuselage (1) both sides are provided with stationary vane (11), the wing tip of stationary vane (11) is provided with folding wing (2), be provided with on stationary vane (11) and be used for controlling folding wing (2) and overturn folding mechanism (3), be provided with rotor mechanism (4) and train mechanism (5) on folding wing (2), rotor mechanism (4) and train mechanism (5) branch are located the both sides of folding wing (2), still be provided with suspension (6) on folding wing (2), be connected through suspension (6) between train mechanism (5) and folding wing (2), train mechanism (5) provide the power when ground runs, folding mechanism (3) control folding wing (2) overturn to train mechanism (5) and ground contact, folding wing (2) set up with stationary vane (11) perpendicularly, rotor mechanism (4) are used for providing the power of VTOL, folding mechanism (3) control folding wing (2) upset to with stationary vane (11) when horizontal, rotor mechanism (4) are used for providing fuselage (1) power when cruising and flying.

2. A foldable wing amphibious aircraft according to claim 1, characterized in that: folding mechanism (3) are including folding steering wheel (31) and folding bent axle (32), folding bent axle (32) are including drive axis body (33) and transmission axis body (34), the wing point department of stationary vane (11) is provided with the cabin, folding steering wheel (31) set up in the cabin, the output shaft of folding steering wheel (31) connects drive axis body (33), the one end that drive axis body (33) deviate from folding steering wheel (31) is articulated with transmission axis body (34), transmission axis body (34) deviate from to be connected with drive axis body (33) and are in folding wing (2) and be connected.

3. A foldable wing amphibious aircraft according to claim 2, characterized in that: the joint of the driving shaft body (33) and the transmission shaft body (34) is subjected to torsion-resistant strengthening treatment.

4. A foldable wing amphibious aircraft according to claim 3, characterized in that: train mechanism (5) are including running wheel (51), universal driving shaft (52), run-up steering wheel (53), transmission shaft (54) and drive member (55), run-up steering wheel (53) sets up on folding wing (2), race groove (21) have been seted up on folding wing (2), run-up wheel (51) set up in race groove (21), arbitrary one side set up two run-up wheels (51) on folding wing (2), connect through universal driving shaft (52) between run-up wheel (51), transmission shaft (54) and run-up steering wheel (53) coaxial coupling, be connected through drive member (55) between transmission shaft (54) and the universal driving shaft (52), be provided with driven bevel gear (56) on run-up wheel (51), universal driving shaft (52) tip is provided with initiative bevel gear (57) with driven bevel gear (56) meshing, so that run-up steering wheel (53) drive through transmission shaft (54) and drive member (55) linkage shaft (55) drive run-up steering wheel (53) 52) The linkage shaft (52) drives the running wheel (51) to rotate to drive the body to run.

5. A foldable wing amphibious aircraft according to claim 4, characterized in that: the suspension (6) comprises a wheel carrier (61), an axle frame (62) and a lubricating bearing (63), one end of the wheel carrier (61) is connected with the folding wing (2), the other end of the wheel carrier is connected with the sliding wheel (51), one end of the axle frame (62) is connected with the folding wing (2), the other end of the axle frame is connected with the linkage shaft (52), the wheel carrier (61) is connected with the sliding wheel (51) to form a joint, and the lubricating bearing (63) is arranged at the joint of the axle frame (62) and the linkage shaft (52).

6. A foldable wing amphibious aircraft according to claim 5, characterized in that: the transmission member (55) comprises a worm (58) and a worm wheel (59), the worm (58) and one end, far away from the run-up steering engine (53), of the transmission shaft (54) are coaxially and fixedly connected, the worm wheel (59) is coaxially and fixedly connected with the linkage shaft (52), and the worm wheel (59) is meshed with the worm (58).

7. A foldable wing amphibious aircraft according to claim 6, characterized in that: the airplane body (1) comprises an airplane body and an empennage (12), wherein the empennage (12) is arranged at the tail part of the airplane body in a V shape, and a rudder (13) is arranged on the empennage (12).

8. A foldable wing amphibious aircraft according to claim 7, characterized in that: the front end part of the machine body is provided with an airspeed head (14).

9. A working method of an amphibious aircraft with a foldable wing is characterized by comprising the following steps: the amphibious aircraft with the foldable wings, as claimed in claim 8, is provided, and the specific working method is as follows:

when ground work is needed, the rotor wing mechanism (4) stops rotating, the folding wings (2) are kept perpendicular to the fixed wings (11) under the action of the folding mechanism (3), the wheel train mechanism (5) is in contact with the ground, the driving transmission shaft (54) and the transmission component (55) are driven by the run-up steering engine (53) to drive the linkage shaft (52) to rotate, and the linkage shaft (52) drives the running wheels (51) to rotate through the driving bevel gear (57) and the driven bevel gear (56) to provide power for driving the body to run;

when turning is needed, the run-up steering engines (53) positioned on the two sides of the machine body are controlled to rotate in a differential mode, during left turning, the run-up steering engines (53) on the right side of the machine body are controlled to keep the rotating speed, the run-up steering engines (53) on the left side of the machine body are controlled to reduce the speed to form differential rotation, so that the machine body turns left, during right turning, the run-up steering engines (53) on the left side of the machine body are controlled to keep the rotating speed, and the run-up steering engines (53) on the right side of the machine body are controlled to reduce the speed to form differential rotation, so that the machine body turns right;

the rotor wing mechanism (4) provides power for vertical take-off and landing of the machine body when rotating, so that the machine body can vertically take off and land or hover;

when the aircraft body keeps a flying and rotating state, the folding mechanism (3) drives the folding wings (2) to turn over, so that the folding wings (2) turn over to be horizontal to the fixed wings (11), and power for cruising and flying of the aircraft body is provided.

10. A foldable wing amphibious aircraft and a working method thereof according to claim 9, characterized in that: the folding wing (2) is turned over from the position vertical to the fixed wing (11) to the horizontal position with the fixed wing (11) by the specific steps of:

the folding mechanism (3) drives the folding wings (2) to wind around the wing tips of the fixed wings (11) to horizontally turn around the shaft in a direction perpendicular to the axis of the fixed wings (11), and the turning direction is that the wing tips of the folding wings (2) rotate towards the outer side of the machine body and rotate to the horizontal position of the fixed wings (11) to stop rotating;

folding mechanism (3) drive folding wing (2) are around the axis that is on a parallel with stationary vane (11) in the wingtip department of stationary vane (11) and are encircleed the upset, and the upset direction drives for folding wing (2) train mechanism (5) rotate towards the direction at fuselage (1) top to rotate and keep horizontal position stall as to train mechanism (5) and fuselage (1).

Technical Field

The invention relates to the technical field of aircrafts, in particular to an amphibious aircraft with foldable wings and a working method thereof.

Background

With the vigorous development in the aviation field, a plurality of novel aircrafts are proposed and put into use, so that the types and functions of the aircrafts are continuously innovated, and a plurality of different types of aircrafts are derived, but the aircrafts are mostly in single forms, wherein the fixed wings, the propeller wings and the tilt rotors have more types, the short plates of the fixed wings and the propeller wings are obvious, the single fixed wing aircrafts cannot hover in the air, have higher requirements on the terrain for taking off, have higher occupation positions and the like, while the tilt rotor aircrafts have low utilization efficiency of flight energy and slower flight speed, have poorer or no working capacity on the ground, need to use an undercarriage to realize support when taking off by the ground, but the current undercarriage supporting sliding running needs to realize sliding by means of thrust, and does not have the effect of assisting the whole body to run and land, and when the landing gear works on the ground, the whole stability is poor, the situation that the landing gear slides away unstably is easy to occur, and therefore the safety of the whole body is affected.

Disclosure of Invention

Aiming at the defects in the prior art, the invention aims to provide the amphibious aircraft with the foldable wings, which has the advantages of improving the stability and the safety of the integral ground work and providing reliable ground work performance for an integral body.

In order to achieve the purpose, the invention provides the following technical scheme:

an amphibious aircraft with foldable wings comprises an aircraft body, wherein fixed wings are arranged on two sides of the aircraft body, the end part of the fixed wing is provided with a folding wing, the fixed wing is provided with a folding mechanism for controlling the folding wing to turn and fold, the folding wings are provided with a rotor wing mechanism and a wheel train mechanism which are respectively arranged at the two sides of the folding wings, the folding wings are also provided with a suspension, the wheel train mechanism is connected with the folding wings through the suspension, the wheel train mechanism provides power for ground running, the folding mechanism controls the folding wings to overturn until the wheel train mechanism is contacted with the ground, the folding wings and the fixed wings are vertically arranged, the rotor wing mechanism is used for providing power for vertical take-off and landing, when the folding mechanism controls the folding wings to overturn to the level of the fixed wings, the rotor wing mechanism is used for providing power for the aircraft body during cruising flight.

As a further improvement of the invention, the folding mechanism comprises a folding steering engine and a folding crankshaft, the folding crankshaft comprises a driving shaft body and a transmission shaft body, the wing tip of the fixed wing is provided with an engine room, the folding steering engine is arranged in the engine room, an output shaft of the folding steering engine is connected with the driving shaft body, one end of the driving shaft body, which deviates from the folding steering engine, is hinged with the transmission shaft body, and the transmission shaft body deviates from the connection with the driving shaft body and is connected with the folding wing.

As a further improvement of the invention, the joint of the driving shaft body and the transmission shaft body is subjected to torsion-resistant strengthening treatment.

As a further improvement of the invention, the gear train mechanism comprises running wheels, a linkage shaft, a running steering engine, a transmission shaft and a transmission member, wherein the running steering engine is arranged on a folding wing, a wheel groove is formed in the folding wing, the running wheels are arranged in the wheel groove, two running wheels are arranged on one side of the folding wing, the running wheels are connected through the linkage shaft, the transmission shaft is coaxially connected with the running steering engine, the transmission shaft is connected with the linkage shaft through the transmission member, driven bevel gears are arranged on the running wheels, and driving bevel gears meshed with the driven bevel gears are arranged at the end parts of the linkage shaft, so that the running steering engine drives the linkage shaft to rotate through the transmission shaft and the transmission member, and the linkage shaft drives the running wheels to drive the engine body to run.

As a further improvement of the invention, the suspension comprises a wheel carrier, a shaft carrier and a lubricating bearing, wherein one end of the wheel carrier is connected with the folding wing, the other end of the wheel carrier is connected with the running wheel, one end of the shaft carrier is connected with the folding wing, the other end of the shaft carrier is connected with the linkage shaft, and the lubricating bearing is arranged at the connection part of the wheel carrier and the running wheel and the connection part of the shaft carrier and the linkage shaft.

As a further improvement of the invention, the transmission component comprises a worm and a worm wheel, the worm is coaxially and fixedly connected with one end of the transmission shaft, which is far away from the run-up steering engine, the worm wheel is coaxially and fixedly connected with the linkage shaft, and the worm wheel is meshed with the worm.

As a further improvement of the invention, the fuselage comprises a fuselage and an empennage, wherein the empennage is arranged at the tail part of the fuselage in a V shape, and a rudder is arranged on the empennage.

As a further improvement of the invention, the front end part of the machine body is provided with a pitot tube.

A working method of an amphibious aircraft with foldable wings comprises the following specific working methods:

when ground work is needed, the rotor wing mechanism stops rotating, the folding wings are kept perpendicular to the fixed wings under the action of the folding mechanism, the gear train mechanism is in contact with the ground, the run-up steering engine drives the transmission shaft and the transmission member to drive the linkage shaft to rotate, the linkage shaft drives the run wheels to rotate through the driving bevel gear and the driven bevel gear, and power for driving the body to run is provided;

when turning is needed, the run-up steering engines positioned on the two sides of the machine body are controlled to rotate in a differential mode, the run-up steering engines on the right side of the machine body are controlled to keep rotating speed during left turning, the run-up steering engines on the left side of the machine body are controlled to reduce the speed to form differential rotation, so that the machine body turns left, and the run-up steering engines on the left side of the machine body are controlled to keep rotating speed during right turning, so that the run-up steering engines on the right side of the machine body are controlled to reduce the speed to form differential rotation, so that the machine body turns right;

when the rotor wing mechanism rotates, power for vertical taking off and landing of the machine body is provided, so that the machine body can vertically take off and land or hover;

when the aircraft body keeps a flying and rotating state, the folding mechanism drives the folding wings to turn over, so that the folding wings turn over to be in the horizontal position of the fixed wings, and power for cruising and flying of the aircraft body is provided.

As a further improvement of the invention, the specific steps of turning the folding wing from the position vertical to the fixed wing to the horizontal position with the fixed wing are as follows:

the folding mechanism drives the folding wings to wind the wing tips of the fixed wings to be vertical to the axis of the fixed wings to horizontally turn around the shaft, and the turning direction is that the wing tips of the folding wings rotate towards the outer side of the machine body and rotate to the horizontal position of the fixed wings to stop rotating;

folding mechanism drives folding wing is around the axis that is on a parallel with the stationary vane in the wingtip department of stationary vane to carry out the upset around the axle, and the upset direction drives for folding wing train mechanism rotates towards the direction at fuselage top to rotate and keep horizontal position stall as far as train mechanism and fuselage.

The invention has the beneficial effects that: through set up folding mechanism in the stationary vane, folding mechanism connects stationary vane and folding wing, realize the folding upset of control folding wing under folding mechanism's effect, be provided with rotor mechanism and train mechanism on the folding wing, make after folding the upset to folding wing, make the contact that can control train mechanism and ground, so that when train mechanism functions, realize wholly can carry out ground work, rotor mechanism can provide power for whole VTOL simultaneously, when control folding wing sets up with the stationary vane level, realize holistic flight of cruising, and rotor mechanism provides the power that whole flight of cruising this moment, the stability and the security that improve whole ground work have been realized, provide reliable ground working property for whole organism, and provide stable power for flight of cruising.

Drawings

FIG. 1 is a schematic perspective view showing a flight state;

FIG. 2 is a schematic perspective view of a ground operation;

FIG. 3 is a schematic structural view of a folding mechanism;

fig. 4 is a schematic configuration diagram showing a train wheel mechanism and a suspension.

Reference numerals: 1. a body; 11. a fixed wing; 12. a tail wing; 13. a rudder; 14. a pitot tube; 2. folding the wings; 21. a wheel groove; 3. a folding mechanism; 31. folding the steering engine; 32. folding the crankshaft; 33. a drive shaft body; 34. a transmission shaft body; 4. a rotor mechanism; 5. a gear train mechanism; 51. a running wheel; 52. a linkage shaft; 53. a run-up steering engine; 54. a drive shaft; 55. a transmission member; 56. a driven bevel gear; 57. a drive bevel gear; 58. a worm; 59. a worm gear; 6. a suspension; 61. a wheel carrier; 62. a pedestal; 63. and (5) lubricating the bearing.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings and examples. In which like parts are designated by like reference numerals. It should be noted that the terms "front," "back," "left," "right," "upper" and "lower" used in the following description refer to directions in the drawings, and the terms "bottom" and "top," "inner" and "outer" refer to directions toward and away from, respectively, the geometric center of a particular component.

Referring to fig. 1 to 4, a specific embodiment of the amphibious aircraft with foldable wings and the working method thereof according to the present invention includes an airframe 1, fixed wings 11 are disposed on two sides of the airframe 1, folding wings 2 are disposed at wing ends of the fixed wings 11, folding mechanisms 3 for controlling the folding wings 2 to turn and fold are disposed on the fixed wings 11, rotor mechanisms 4 and wheel train mechanisms 5 are disposed on the folding wings 2, the rotor mechanisms 4 and the wheel train mechanisms 5 are disposed on two sides of the folding wings 2, the rotor mechanisms 4 are the prior art, the working method and working principle thereof are not described herein, the folding wings 2 are further provided with suspensions 6, the wheel train mechanisms 5 and the folding wings 2 are connected by the suspensions 6, so that when the folding wings 2 are controlled by the folding mechanisms 3 to turn and fold until the wheel train mechanisms 5 contact the ground, the wheel train mechanisms 5 provide power for ground running, so as to enable the entire amphibious aircraft to stably run, efficiency that the rolloff starts is improved, folding mechanism 3 control folding wing 2 overturns to train mechanism 5 when contacting with ground, folding wing 2 sets up with stationary vane 11 is perpendicular, and folding wing 2 keeps away from the afterbody direction of stationary vane 11 wing tip department towards fuselage 1, rotor mechanism 4 is used for providing the power of VTOL, folding mechanism 3 control folding wing 2 overturns to when 11 levels with the stationary vane, rotor mechanism 4 is used for providing the power when fuselage 1 cruises and flies, fuselage 1 includes organism and fin 12, fin 12 is the V type and sets up in the afterbody of organism, be provided with rudder 13 on fin 12, make turning to and the upset that can the regulation and control organism, fin 12 is the V type and sets up in the organism afterbody, thereby play the effect of maintaining the stable flight of organism, tip is provided with airspeed tube 14 before the organism.

Referring to fig. 1 to 3, the folding mechanism 3 includes a folding steering engine 31 and a folding crankshaft 32, the folding crankshaft 32 includes a driving shaft body 33 and a transmission shaft body 34, a cabin is disposed at a wing tip of the fixed wing 11, the folding steering engine 31 is disposed in the cabin, an output shaft of the folding steering engine 31 is connected with the driving shaft body 33, one end of the driving shaft body 33, which is far away from the folding steering engine 31, is hinged to the transmission shaft body 34, which is far away from the driving shaft body 33, is connected to the folding wing 2, a joint between the driving shaft body 33 and the transmission shaft body 34 is subjected to torsional reinforcement, specifically, firstly, the thickness of a material is increased at the joint between the driving shaft body 33 and the transmission shaft body 34, and the salt bath nitridation treatment is performed on the whole driving shaft body 33 and the transmission shaft body 34, so as to improve the whole hardness, the wear resistance, the torsional strength and the corrosion resistance, and polish the stressed part, and improve the service life of the whole body, finally, the drive shaft body 33 and the transmission shaft body 34 are quenched.

Referring to fig. 1 to 4, the gear train mechanism 5 includes running wheels 51, a linkage shaft 52, running steering gears 53, transmission shafts 54 and transmission members 55, the running steering gears 53 are disposed on the folding wings 2, wheel grooves 21 are disposed on the folding wings 2, the running wheels 51 are disposed in the wheel grooves 21, two running wheels 51 are disposed on the folding wing 2 on any side, the running wheels 51 are connected through the linkage shaft 52, the transmission shafts 54 are coaxially connected with the running steering gears 53, the transmission shafts 54 are connected with the linkage shaft 52 through the transmission members 55, the transmission members 55 include worms 58 and worm wheels 59, the worms 58 are coaxially and fixedly connected with one ends of the transmission shafts 54 far away from the running steering gears 53, the worm wheels 59 are coaxially and fixedly connected with the linkage shaft 52, the worm wheels 59 are engaged with the worms 58, driven bevel gears 56 are disposed on the running wheels 51, driving bevel gears 57 engaged with the driven bevel gears 56 are disposed at the end portions of the linkage shaft 52, so that the transmission shafts 54 are driven to rotate by the action of the running steering gears 53, thereby driving the worm 58 to rotate, driving the linkage shaft 52 to rotate through the worm wheel 59 meshed with the worm 58, further driving the running wheel 51 to rotate, realizing active running without the action of the body thrust when running is needed, and realizing ground movement;

the suspension 6 comprises a wheel frame 61, an axle frame 62 and a lubricating bearing 63, one end of the wheel frame 61 is connected with the folding wing 2, the other end of the wheel frame is connected with the running wheel 51, one end of the axle frame 62 is connected with the folding wing 2, the other end of the axle frame is connected with the linkage shaft 52, the lubricating bearing 63 is arranged at the joint of the wheel frame 61 and the running wheel 51 and the joint of the axle frame 62 and the linkage shaft 52, under the action of the lubricating bearing 63, the rotation of the linkage shaft 52 and the rotation of the running wheel 51 are difficult to be blocked, the rotation resistance of the linkage shaft 52 and the running wheel 51 is reduced, and under the action of the wheel frame 61 and the axle frame 62, the wheel train mechanism 5 can be stably connected with the folding wing 2.

The working mode of the amphibious aircraft is as follows:

when ground work is needed, the rotor wing mechanism 4 stops rotating, the folding wings 2 are kept perpendicular to the fixed wings 11 under the action of the folding mechanism 3, so that the running wheels 51 in the wheel train mechanism 5 are in contact with the ground, the running steering engine 53 drives the transmission shaft 54 and the transmission member 55 to drive the linkage shaft 52 to rotate, and the linkage shaft 52 drives the running wheels 51 to rotate through the driving bevel gear 57 and the driven bevel gear 56, so that power for driving the body to run is provided;

when turning is needed, the run-up steering engines 53 positioned on the two sides of the machine body are controlled to rotate in a differential mode, during left turning, the run-up steering engines 53 on the right side of the machine body are controlled to keep rotating speed, the run-up steering engines 53 on the left side of the machine body are controlled to reduce the speed to form differential rotation, so that the machine body turns left, during right turning, the run-up steering engines 53 on the left side of the machine body are controlled to keep rotating speed, and the run-up steering engines 53 on the right side of the machine body are controlled to reduce the speed to form differential rotation, so that the machine body turns right;

the rotor wing mechanism 4 provides power for vertical taking off and landing of the machine body when rotating, so that the machine body can vertically take off and land or hover;

when the aircraft body keeps a flying state, the folding mechanism 3 drives the folding wings 2 to turn over, so that the folding wings 2 turn over to be in the horizontal position of the fixed wings 11, and power for cruising and flying of the aircraft body is provided;

the specific steps of turning the folding wing 2 from the position vertical to the fixed wing 11 to the horizontal position with the fixed wing 11 are as follows:

the folding mechanism 3 drives the folding wings 2 to wind around the wing tips of the fixed wings 11 to be vertical to the axis of the fixed wings 11 to horizontally turn around the shaft, and the turning direction is that the wing tips of the folding wings 2 rotate towards the outer side of the machine body and rotate to the horizontal position of the fixed wings 11 to stop rotating;

the folding mechanism 3 drives the folding wing 2 to rotate around the wing tip of the fixed wing 11 in a direction parallel to the axis of the fixed wing 11, and the folding wing 2 drives the gear train mechanism 5 to rotate towards the top of the machine body 1 in the rotating direction, and the gear train mechanism 5 and the machine body 1 are rotated to keep horizontal position and stop rotating.

The above description is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above embodiments, and all technical solutions belonging to the idea of the present invention belong to the protection scope of the present invention. It should be noted that modifications and embellishments within the scope of the invention may occur to those skilled in the art without departing from the principle of the invention, and are considered to be within the scope of the invention.