CN117465666A

CN117465666A - Four-power-source tilting aircraft

Info

Publication number: CN117465666A
Application number: CN202311391329.0A
Authority: CN
Inventors: 路精保; 申鑫民; 石宇昊
Original assignee: Zhejiang University Ningbo Five In One Campus Education Development Center
Current assignee: Zhejiang University Ningbo Five In One Campus Education Development Center
Priority date: 2023-10-25
Filing date: 2023-10-25
Publication date: 2024-01-30
Also published as: CN118124801A

Abstract

The invention discloses a four-power-source tilting aircraft, which comprises a fuselage, wherein the fuselage is provided with a wing system and a tilting propulsion device, and the tilting propulsion device comprises two pairs of upper rotors and lower rotors which are positioned at two ends of the wing; the aircraft has the advantages of high flying speed and long endurance time by arranging the tilting mechanism; the design of four rotor power sources enables the aircraft to eliminate a traditional system power transmission shaft and a universal joint; meanwhile, by arranging the tilting rotor wing structure, the weight minimization of the tilting propulsion device is realized, the weight of the aircraft is reduced, and the thrust-weight ratio efficiency is improved; in addition, the rotor wing ensures the safe sliding under the condition of failure of the whole engine, and has reliability more than the traditional four-rotor aircraft; the aircraft can realize short-distance running and take-off and vertical take-off and landing flight by being matched with four power sources in a tilting mode, so that the effective load of the aircraft has a higher lifting space.

Description

Four-power-source tilting aircraft

Technical Field

The invention relates to the technical field of aircrafts, in particular to a four-power-source tilting aircraft.

Background

The utility model provides an aircraft that power supply can tilt is a novel aircraft that fuses fixed wing aircraft and other power supplies, and with rotor tilting and duct tilting are numerous, not only have traditional fixed wing aircraft to run the ability of taking off and cruising in the sky, have the ability of hovering in the sky of vertical take off and land again, and the tilting power supply makes the aircraft have not to have dead weight in addition, has improved thrust-weight ratio greatly. The four rotor power source design eliminates the traditional system power transmission shaft and universal joint for the aircraft. The tilting mechanism comprises a power source tilting system capable of rotating alternately between a horizontal position and a vertical position and a power system for providing power, and when the aircraft vertically takes off and lands, the supporting beam is parallel to the ground; when the aircraft is in cruising condition, the backbar is perpendicular to the ground.

The existing tiltrotor aircraft mainly comprises the following two types:

tilt rotor layout: taking a V-22 model aircraft of Bell company as an example, after the U.S. V-22 is successfully in service, the vertical take-off and landing/short take-off and landing of the fixed wing aircraft are realized by a unique pneumatic layout, and the high speed, long endurance and vertical take-off and landing of the helicopter of the fixed wing aircraft are perfectly combined. However, the V-22 uses a complex system power transmission shaft and a universal joint, so that the control difficulty is high, particularly, in the process of converting a helicopter state into a fixed wing state, the control difficulty is very high, and the helicopter is very easy to crash.

Duct tilting layout: taking the model of the aircraft of model Nexus 4EX of Bell corporation as an example, bell corporation publishes an all-electric vertical take-off and landing (eVTOL) validator, bell Nexus 4EX. The maximum take-off quality is 3200kg, the cruising speed is 240km/h, and the vehicle can fly 97km when carrying 4-5 passengers and 1 pilot. Nexus 4EX has only 4 ducted fans to reduce drag and increase cruise efficiency compared to the 6 ducted fans of Nexus shown on CES in 2019.

The existing power source tilting aircraft has the problems of unreasonable layout, more invalid weight and larger control difficulty.

Disclosure of Invention

Aiming at the defects of the prior art, the invention provides the tilting aircraft with four power sources, which has reasonable layout, realizes the minimization of the weight ratio of a power system and a tilting system, reduces the weight and the resistance of the aircraft and increases the thrust-weight ratio.

The aim of the invention is realized by the following technical scheme: a four-power source tilting aircraft comprises a fuselage, wherein a wing system and a tilting propulsion device are arranged on the fuselage;

the wing system comprises a main wing and a tail wing, wherein the main wing and the tail wing are symmetrically distributed on two sides of the fuselage, the tail wing is arranged at the rear end of the fuselage, and a pair of supporting beams are rotatably connected to two ends of the main wing and are respectively and vertically installed with the main wing;

the tilting propulsion device comprises two configurations, wherein the two configurations are provided with two upper rotary wings and two lower rotary wings, one configuration is that the upper rotary wings are respectively fixed at the front end of a supporting beam and symmetrically distributed at the upper part of a machine body, and the lower rotary wings are respectively fixed at the rear end of the supporting beam and symmetrically distributed at the lower part of the machine body; the other configuration is that the upper rotor wings are respectively fixed at the rear ends of the supporting beams and symmetrically distributed at the upper part of the machine body, the lower rotor wings are respectively fixed at the front ends of the supporting beams and symmetrically distributed at the lower part of the machine body;

the tilting propulsion device realizes tilting relative to the fuselage based on the supporting beam, is matched with four rotor power sources, and is coordinated with the rotating speeds and the pneumatic surfaces of the four rotors to realize short-distance running take-off, hovering and vertical take-off and landing of the aircraft.

Further, the main wing comprises an aileron and a flap, and the tail wing comprises an elevator and a rudder for controlling the attitude of the aircraft.

Further, when the aircraft switches flight states, the upper rotor wing and the lower rotor wing change the inclination angle of the power source.

Further, the tail fin is H-shaped and comprises a vertical tail fin and a horizontal tail fin, and the vertical tail fin comprises a rudder and a vertical stabilizer; the horizontal tail comprises a horizontal stabilizer and an elevator, the yaw of the aircraft is controlled by operating the elevator, and the pitch of the aircraft is controlled by operating the elevator.

Further, the rotation directions of a group of upper and lower rotors positioned on the same side wing are opposite, and the rotation directions of the upper rotor and the lower rotor positioned on the diagonal position are the same, so that the counter torque is counteracted.

Further, the tiltable propulsion apparatus further includes a power system having an engine compartment with a motor/engine, a speed reducer, and an angle sensor, the motor/engine being connected to the upper rotor and the lower rotor through the speed reducer and an output shaft.

Further, the power system further comprises a lithium battery arranged on the lower side of the rotor wing, and heat is dissipated by means of the downwash air flow of the rotor wing.

Further, the bottom of the machine body is provided with a landing gear.

The invention has the beneficial effects that: the aircraft has the advantages of high flying speed and long endurance time by arranging the tilting rotor system, the weight minimization of the power system and the tilting rotor system is realized, the weight of the aircraft is lightened, the resistance of the aircraft is reduced, and the traditional thrust-weight ratio efficiency is improved. In addition, the fixed wing ensures the safe sliding under the condition of failure of the whole engine, and has more reliability than the traditional four-rotor aircraft. More importantly, when the rotor is in a suspension state, four power sources can replace universal joints which are necessary in the traditional two-tilting rotor structure, so that the complexity of the mechanism is simplified. The tilting and matching four power source rotors can enable the airplane to realize short-distance running and take-off and vertical take-off and landing flight, so that the effective load of the airplane has a higher lifting space. It should be noted that, for the power system portion of this patent, the rotor may also be used with other power systems, and the power system is widely adapted, including: turbojet, jet, propeller, and the like.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

Fig. 1 is an overall structural view of configuration 1 of the present invention in a vertical take-off and landing or levitation state.

Fig. 2 is an overall structural view of configuration 1 of the present invention patent at cruising (rotated 90 deg. counterclockwise).

Fig. 3 is a side view of configuration 1 of the present invention in vertical lift or levitation (rotated 90 deg. counterclockwise).

Fig. 4 is a side view of configuration 1 of the present patent at cruising (rotated 90 deg. counterclockwise).

Fig. 5 is an overall structural view of configuration 2 of the present invention patent at vertical take-off and landing.

FIG. 6 is an overall structural view of configuration 2 of the present invention at cruising (90 rotated counterclockwise)

Fig. 7 is a side view of configuration 2 of the present invention at a stage of vertical take-off and landing.

Fig. 8 is a side view of configuration 2 of the present patent at cruising (rotated 90 deg. counterclockwise).

In the figure, 1, a fuselage; 2. a main wing; 3. a flap; 4. aileron; 5. landing gear; 6. an upper rotor; 7. a vertical stabilizer; 8. a rudder; 9. a horizontal stabilizer; 10. an elevator; 11. a lower rotor nacelle; 12. an upper rotor nacelle; 13. a lower rotor; 14. a support beam.

Detailed Description

The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

As shown in fig. 1 and 2, the four-power-source tiltable aircraft provided by the invention comprises a fuselage 1, wherein the fuselage 1 is provided with a wing system and a tiltable propulsion device; the bottom of the machine body is provided with a landing gear 5.

The wing system comprises a wing 2 and an H-shaped tail wing, wherein the main wing 2 and the H-shaped tail wing are symmetrically distributed on two sides of the fuselage 1, the main wing comprises an aileron 4 and a flap 3, the H-shaped tail wing is arranged at the rear end of the fuselage 1 and is connected with the fuselage, and an elevator and a rudder are used as an actuating mechanism by a steering engine arranged at the tail of the lower single-wing fuselage to deflect at a certain angle. As an improvement, the tail fin can be of a T shape, a V shape, an inverted V shape or an inverted T shape. A pair of support beams 14 rotatably connected to both ends of the main wing 2 and installed perpendicular to the main wing 2, respectively;

the tilting propulsion device comprises an upper rotor 6 and a lower rotor 13, wherein the upper rotor and the lower rotor are arranged in two ways, one is that the upper rotor is positioned in front of the supporting beam and the lower rotor is positioned behind the supporting beam, and the other is that the upper rotor is positioned behind the supporting beam and the lower rotor is positioned in front of the supporting beam; the upper rotor wing 6 is provided with two rotor wings which are symmetrically distributed on the upper part of the machine body 1 and are respectively fixed on the front end or the rear end of the supporting beam 14, the lower rotor wing 7 is also provided with two rotor wings which are symmetrically distributed on the lower part of the machine body 1 and are respectively fixed on the rear end or the front end of the supporting beam 13;

the upper rotor 6 and the lower rotor 13 can change the inclination angle of the power source when the aircraft switches the flight state, for example, when the aircraft changes from a vertical take-off state to a cruising state, the power source of the aircraft can rotate anticlockwise by 90 degrees from the vertical state to reach the cruising state parallel to the horizontal plane under the drive of the tilting mechanism.

Further, the rotation directions of a group of upper and lower rotors positioned on the same side wing are opposite, and the rotation directions of an upper rotor 6 and a lower rotor 13 positioned on the diagonal positions are the same, so as to counteract the anti-torque moment;

the tilting propulsion device further comprises a power system for driving the rotor wings to independently and alternately move in the horizontal direction and the vertical direction, the power system is provided with a lower rotor wing engine room 11 and an upper rotor wing engine room 12, a motor/engine, a speed reducer and an angle sensor are arranged in the two engine rooms, and the motor/engine is connected to the upper rotor wing and the lower rotor wing through the speed reducer and an output shaft; the two sets of rotors are respectively symmetrical to the center of gravity of the aircraft, and each set of rotors is connected with the supporting beam 14 through the engine room.

The power system further comprises a lithium battery, and the lithium battery is arranged at the lower side of the rotor wing as a preferable embodiment and can dissipate heat by means of the downward washing airflow of the rotor wing;

the H-shaped tail wing comprises a vertical tail wing and a horizontal tail wing, and the vertical tail wing comprises a rudder 8 and a vertical stabilizer 7; the horizontal tail comprises a horizontal stabilizer 9 and an elevator 10 for providing the course static stability of the aircraft, the yaw of the aircraft is controlled by operating the rudder 8, the horizontal stabilizer 7 provides the longitudinal stability of the aircraft, and the pitch of the aircraft is controlled by operating the elevator 10.

The four-rotor type aircraft adopts the four-rotor type layout, and when the aircraft is in a suspended or hovering configuration, the control logic of the aircraft is similar to that of a simple four-rotor type aircraft to a certain extent, so that universal joints are not required when hovering or vertical landing is realized, only the rotating speeds and the pneumatic surfaces of the four rotors are required to be coordinated and matched, meanwhile, a power transmission shaft is omitted, the structural complexity is reduced to a great extent, and the difficulty of a control system is simplified; the aircraft designed by the invention has the advantages of the vertical take-off and landing characteristics of the four rotors and simple structure, the fixed wings and the tilting rotors solve the characteristics of short endurance, small carrying capacity and the like of the four rotors, and the endurance time and the flying speed of the four rotors of the same type are improved;

as shown in fig. 1 and 3, the aircraft is in a schematic view under a vertical take-off and landing state, when taking off and landing vertically, the tilting rotor wing is adjusted to be parallel to the ground by the supporting beam, and the aircraft provides lift force for taking off vertically by means of 4 tilting rotor wings; after the flying speed is increased to the cruising speed, the four rotary wings rotate anticlockwise by 90 degrees to adjust the supporting beams to be vertical to the ground, so that the effects of reducing resistance and increasing thrust are achieved;

as shown in fig. 2 and fig. 4, the aircraft is in a cruising or running and taking off state, when the aircraft is cruising, the tilting rotor rotates 90 degrees anticlockwise from a vertical taking off and hovering state to adjust the supporting beam to be vertical to the ground, the aircraft provides forward thrust by means of 4 tilting rotors, the rotors provide upward pulling force, cruising efficiency is ensured, the configuration has a very high thrust-weight ratio when cruising, dead weight does not exist, and the rotors fully provide power for forward flight of the aircraft;

meanwhile, the invention has a take-off mode of vertical take-off and landing and running, when the load is smaller, the vertical take-off and landing can be directly adopted for take-off and landing; when the load quantity is large, the take-off and landing modes of running can enable the aircraft to take off when the load quantity is large, and therefore the effective load of the aircraft has a higher lifting space.

The above-described embodiments are intended to illustrate the present invention, not to limit it, and any modifications and variations made thereto are within the spirit of the invention and the scope of the appended claims.

Claims

1. A four-power source tilting aircraft comprises a fuselage, and is characterized in that a wing system and a tilting propulsion device are arranged on the fuselage;

2. The four-power-source tiltable aircraft of claim 1, wherein the main wings include ailerons and flaps, and the tail wings include elevators and rudders for controlling the attitude of the aircraft.

3. The four-power-source tiltable aircraft of claim 1, wherein the upper rotor and the lower rotor change the tilt angle of the power source when the aircraft switches flight conditions.

4. The four-power-source tiltable aircraft of claim 2, wherein the tail is H-shaped, including a vertical tail and a horizontal tail, the vertical tail including a rudder and a vertical stabilizer; the horizontal tail comprises a horizontal stabilizer and an elevator, the yaw of the aircraft is controlled by operating the elevator, and the pitch of the aircraft is controlled by operating the elevator.

5. The four-power-source tiltable aircraft as in claim 1, wherein the upper and lower rotors of the four rotors on the same side are rotated in opposite directions, and the upper and lower rotors on diagonal positions are rotated in the same direction to counteract the counter torque.

6. The four-power-source tiltable aircraft of claim 1, further comprising a power system having an engine compartment, the engine compartment further having a motor/engine, a speed reducer, and an angle sensor, the motor/engine being coupled to the upper rotor and the lower rotor via the speed reducer and the output shaft.

7. The four-power-source tiltable aircraft of claim 6, wherein the power system further comprises a lithium battery disposed on the underside of the rotor that dissipates heat via the downwash of the rotor.

8. The four-power-source tiltable aircraft of claim 1, wherein the bottom of the fuselage is provided with landing gear.