CN113844647A

CN113844647A - Three-flight-mode electric general aircraft capable of taking off and landing vertically

Info

Publication number: CN113844647A
Application number: CN202111102650.3A
Authority: CN
Inventors: 田耘彰; 屈崑
Original assignee: Northwestern Polytechnical University
Current assignee: Northwestern Polytechnical University
Priority date: 2021-09-21
Filing date: 2021-09-21
Publication date: 2021-12-28
Anticipated expiration: 2041-09-21
Also published as: CN113844647B

Abstract

The invention relates to a three-flight mode electric general aircraft capable of taking off and landing vertically, belonging to the field of aircrafts; the aircraft comprises an aircraft body, wings, a power system, an empennage, an undercarriage, a cabin, a fairing, a first rotating shaft, a second rotating shaft, a wing support and a switching mechanism; the power system adopts propeller propulsion, the blades of the propeller rotate around the shaft in the working state, and the blades of the propeller retract to the fairing in the non-working state; the wings on the two sides are connected into a whole through the switching mechanism and are rotationally connected through the first rotating shaft, so that the wings can rotate around the axial direction of the first rotating shaft relative to the switching mechanism, and the switching between the vertical take-off and landing posture and the fixed wing posture is realized; the switching mechanism is fixed right above the fuselage through the wing brace, and the wing brace is connected with the switching mechanism through the rotation of second pivot for the wing that switching mechanism drove both sides is rotatory around the second pivot, realizes the switching of stationary vane gesture and rotor wing gesture. The aircraft has the advantages of three different flight modes and can avoid the defects caused by a single flight mode.

Description

Three-flight-mode electric general aircraft capable of taking off and landing vertically

Technical Field

The invention belongs to the field of aircrafts, and particularly relates to a three-flight-mode electric general aircraft capable of taking off and landing vertically.

Background

In recent years, the general aircrafts in China are rapidly developed, the total flying amount is increased by more than 10% every year, the industry scale is gradually enlarged, the application field is continuously expanded, the flying types are gradually increased, and the flying requirement is gradually vigorous. The development of general aviation is promoted, and the method has important significance for building civil aviation strong countries. The general aviation aircraft has the advantages of simple and convenient operation, low requirement on take-off and landing sites and the like.

Electric aircraft use electric propulsion systems instead of internal combustion engine power, thereby achieving many advantages and unique qualities. The most outstanding advantages are energy saving, environmental protection, high efficiency, low energy consumption, near zero emission, low noise and vibration level, good riding comfort and being a real environment-friendly airplane. In addition, the device has the characteristics of safety, reliability (no explosion and fuel leakage), simple structure, convenience in operation and use, good maintainability, low cost, good economy and the like. There are also many advantages in design: the overall layout is flexible, and the optimal layout and the unconventional/innovative layout can be adopted; the airplane with extraordinary performance can be designed to meet the requirements of special purposes, and the like.

Rotor flight is a rotorcraft that generates lift by blowing the rotor to spin with relative airflow during forward flight, and the forward force is directly provided by an engine driving a propeller. Approximately vertical descent can be performed by means of a rotor, and the vertical descent technology is an aviation technology developed in the late 50 s. The airplane using the vertical landing technology is flexible in maneuvering and has the advantages that the conventional airplane cannot compare with the airplane. First, aircraft with vertical descent capability do not require specialized airports and runways, which can reduce use costs. In addition, the vertical landing aircraft can land only in a small field, and the battlefield survival rate of the aircraft is greatly improved.

The V-22 tilting rotor aircraft (nickname: osprey) is a U.S. A-type tilting rotor aircraft with vertical take-off and landing (short take-off and landing capability), the V-22 tilting rotor aircraft is similar to a fixed wing aircraft in appearance, but two rotatable engines at the wing tips drive two rotors, in the state of the fixed wing, the V-22 is like an aircraft with two oversized propellers at the wing tips at two sides, in the state of the helicopter, the helicopter is provided with two small rotors, so that the helicopter has the vertical lifting capability of the helicopter, but has the advantages of high speed, long voyage and low oil consumption of the fixed wing propeller aircraft, the maximum flight speed reaches 509 kilometers, and the helicopter flies fastest in the world.

The general aircraft has a good application prospect due to the advantages of simple and convenient operation, strong flexibility and the like, but has high dependence on a flight field and the environment due to the fact that the general aircraft needs to run in the take-off and landing stages; the common aviation general aircraft is driven by the internal combustion engine, so that the endurance time is short, and the reliability is low, which is the technical problem to be solved by the invention.

The design scheme of the aircraft provided by the invention not only can quickly cruise in a fixed wing attitude, but also can vertically take off and land like a V-22 aircraft, and can safely land in a rotor wing type flight mode under the state that an engine is stopped. Under the cruising state, the aircraft can provide power for the aircraft by means of solar energy storage, and the voyage of the aircraft is prolonged.

Disclosure of Invention

The technical problem to be solved is as follows:

in order to avoid the defects of the prior art, the invention provides the three-flight mode electric general aircraft capable of taking off and landing vertically, so that the aircraft has the characteristic of taking off and landing vertically and the environmental dependence is reduced; the problem of short endurance of flight can be solved by solar energy storage in the flight attitude of the fixed wing; the rotor mode can ensure the safe landing of the aircraft in the emergency state that the aircraft loses power; thereby improving the flexibility, the endurance and the safety performance of the aircraft.

The technical scheme of the invention is as follows: a three-flight mode electric general aircraft capable of vertically taking off and landing comprises an aircraft body 1, wings 2, a power system 3, an empennage 5, an undercarriage 8 and a cabin 9, wherein the wings 2 are positioned on two sides of the aircraft body 1, the power system 3 is arranged on the wings 2, the empennage 5 is positioned at the tail of the aircraft body 1, the undercarriage 8 is positioned at the belly of the aircraft body 1, and the cabin 9 is positioned at the front end above the aircraft body 1; the method is characterized in that: the wing support is characterized by further comprising a fairing 4, a first rotating shaft 6, a second rotating shaft 7, a wing support 10 and a switching mechanism 11;

the two power systems 3 are symmetrically arranged on the front edges of the wings 2 on the two sides through two fairing covers 4 respectively, the power systems 3 are propelled by propellers, the propellers are of retractable structures, blades rotate around a shaft in a working state, and the blades are retracted to the fairing covers 4 in a non-working state;

the wings 2 on the two sides are connected into a whole through the switching mechanism 11, the wings 2 on the two sides and the two ends of the switching mechanism 11 are respectively connected in a rotating manner through the first rotating shaft 6, and the axial direction of the first rotating shaft 6 is vertical to the symmetrical plane of the fuselage 1, so that the wings 2 can rotate around the axial direction of the first rotating shaft 6 relative to the switching mechanism 11, and the switching between the vertical take-off and landing postures and the fixed wing postures is realized;

changeover mechanism 11 props 10 through the wing and is fixed in directly over the fuselage 1, and the wing props 10 roots and links to each other with the fuselage 1 is fixed, and the top that the wing propped 10 is passed through second pivot 7 and is connected with changeover mechanism 11 rotates for changeover mechanism 11 drives the wing 2 of both sides and rotates around second pivot 7, realizes the switching of stationary vane gesture and rotor wing gesture.

The further technical scheme of the invention is as follows: still include the airborne power supply, the airborne power supply includes 3 group batteries and emergency power source, and wherein 2 group batteries are used for 3 powers of driving system respectively, and 1 group is used for the airborne equipment power supply in addition.

The further technical scheme of the invention is as follows: the skin is a flexible solar panel skin 22, and can absorb solar energy to store energy for an airborne power supply, so that the flight time is prolonged.

The further technical scheme of the invention is as follows: the machine body 1 is designed in a streamline shape; the radial section adopts a double-arc design and comprises an upper arc line 12 and a lower arc line 13, wherein the upper arc line 12 takes the 2/3 part of the circle, and the lower arc line 13 takes the 1/4 part of the circle; the radial cross-sections along the axial direction are scaled in equal proportion.

The further technical scheme of the invention is as follows: the planar shape of the wing 2 adopts a trapezoidal design, the wing adopts an elliptical wing, and the range of the wing capable of rotating around the first rotating shaft 6 is 0-100 degrees.

The further technical scheme of the invention is as follows: the cross section of the wing support 10 in the symmetrical plane of the fuselage 1 is trapezoidal, and the radial cross section is oval, and is formed by bridging two oval end faces.

The further technical scheme of the invention is as follows: the changeover mechanism 11 is composed of a local pie-shaped outer cover 20 and a transition section 19, the pie-shaped outer cover 20 is circular in horizontal projection shape, the vertical section of the pie-shaped outer cover is elliptical, the pie-shaped outer cover 20 is smoothly connected with the wing root of the wing 2 through the transition section 19, and the section of the connection position is an elliptical section 21.

The further technical scheme of the invention is as follows: the fairing 4 comprises a fairing outer cover 14 and grooves 15, the grooves 15 are symmetrically arranged on the peripheral wall surface of the fairing outer cover 14 and used as storage bins for propeller blades, the propeller blades are recovered into the grooves 15, and the fairing 4 is circular in section; the propeller comprises two blades, the blades are connected with the front end of the fairing 4 through a steering engine, and the steering engine controls the blades to be unfolded and retracted.

The further technical scheme of the invention is as follows: the fairing 4 shrinks proportionally in the axial section.

The further technical scheme of the invention is as follows: the root of the fairing 14 and the wing skin are in streamline fusion design.

Advantageous effects

The invention has the beneficial effects that:

the power mode of the aircraft scheme adopts a pure electric mode, the surface of the wing is provided with the solar flexible battery panel skin, and the solar flexible battery panel skin can store energy for the power system battery pack when the fixed wing flies, so that the flying time of the fixed wing is prolonged.

According to the aircraft, the wings on the two sides are connected with the switching mechanism through the first rotating shaft, so that the vertical takeoff and landing can be realized when the propellers face upwards after the wings on the two sides rotate, external hardware facilities such as airports and the like are not needed, and the dependence on the flying and taking-off environment is small;

when faults such as air engine parking and the like occur in the aircraft, the wings rotate around a second rotating shaft of the aircraft, the propellers are collected into a rectification housing of the power system to reduce resistance when the wings rotate, and the flight mode is switched to the safest gyroplane mode in the current flight field to rotate and slide down, so that safe landing is realized;

in the ground parking state of the aircraft, the wings rotate to the direction parallel to the axial direction of the aircraft body, and meanwhile, the propeller is collected into the rectifying outer cover of the power system, so that the required ground parking space is smaller, and the aircraft is more convenient to park.

The aircraft can fly at a high speed in a fixed wing attitude in a cruising state, and has higher cruising speed than a common rotor wing type aircraft and a helicopter; when the engine is in failure and stops, the aircraft can be converted into a rotor wing type flight attitude, and can land safely; during taking off and landing, the propeller can be vertically lifted upwards, and the environmental requirements of lifting are reduced. The aircraft has the advantages of three different flight modes and can avoid the defects caused by a single flight mode.

Drawings

FIG. 1 is a schematic three-side view;

FIG. 2 is a detailed side view of the protocol;

FIG. 3 is a detailed plan view of the protocol;

FIG. 4 is a cross-sectional view of the fuselage;

FIG. 5 is a detailed view of a powertrain fairing;

FIG. 6 is a detailed view of the transfer mechanism;

FIG. 7 is a schematic view of vertical take-off and landing;

FIG. 8 is a schematic view of a rotor mode;

FIG. 9 is a schematic view of a ground parking;

description of reference numerals: 1. the flexible solar cell panel comprises a fuselage, 2. wings, 3. a power system, 4. a fairing, 5. the wings, 6. a first rotating shaft, 7. a second rotating shaft, 8. a landing gear, 9. a cabin, 10. a wing support, 11. a switching mechanism, 12. an upper arc line, 13. a lower arc line, 14. a fairing cover, 15. a groove, 16. a cross section, 17. a movable control surface, 18. a stabilizing surface, 19. a transition section, 20. a cake-shaped outer cover, 21. an oval cross section and 22. a flexible solar cell panel cover.

Detailed Description

The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.

Referring to fig. 1-3, the three-flight mode electric aircraft capable of vertically taking off and landing according to the present invention includes a fuselage 1, wings 2, a power system 3, a fairing 4, a tail fin 5, a first rotating shaft 6, a second rotating shaft 7, a landing gear 8, a cabin 9, a wing brace 10, an adapter 11, and a flexible solar panel skin 22; the wings 2 are positioned at two sides of the fuselage 1, the power system 3 is arranged on the wings 2, the empennage 5 is positioned at the tail part of the fuselage 1, the undercarriage 8 is positioned at the belly part of the fuselage 1, and the cabin 9 is positioned at the front end above the fuselage 1; still include the airborne power supply, the airborne power supply includes 3 group batteries and emergency power source, and wherein 2 group batteries are used for 3 powers of driving system respectively, and 1 group is used for the airborne equipment power supply in addition. The skin is a flexible solar panel skin 22, and can absorb solar energy to store energy for an airborne power supply, so that the flight time is prolonged.

Referring to fig. 1 and 4, the fuselage 1 is designed in a streamline shape; the radial section adopts a double-arc design and comprises an upper arc line 12 and a lower arc line 13, wherein the upper arc line 12 takes the 2/3 part of the circle, and the lower arc line 13 takes the 1/4 part of the circle; the radial cross-sections along the axial direction are scaled in equal proportion.

Referring to fig. 3, the tail 5 adopts an inverted V-shaped tail design, the wing is a symmetrical wing, and the tail 5 is composed of a stabilizing surface 18 and a movable control surface 17;

referring to fig. 1 and 2, the landing gear 8 is of a three-point forward retractable landing gear design; the canopy is designed by adopting an integrated all-glass structure, and no reinforcing rib is arranged in the middle;

referring to fig. 5, two power systems 3 are symmetrically installed on the front edges of two wings 2 through two fairings 4 respectively, the power systems 3 are propelled by propellers, the propellers are of retractable structures, blades are unfolded to rotate around a shaft in a working state, and the blades are retracted to the fairings 4 in a non-working state;

the fairing 4 comprises a fairing outer cover 14 and grooves 15, the grooves 15 are symmetrically arranged on the peripheral wall surface of the fairing outer cover 14 and used as storage bins for propeller blades, the propeller blades are recovered into the grooves 15, and the fairing 4 is circular in section; the propeller comprises two blades, the blades are connected with the front end of the fairing 4 through a steering engine, and the steering engine controls the blades to be unfolded and retracted. The fairing 4 shrinks in equal proportion along the axial section, and the root of the fairing 14 and the wing skin are in streamline fusion design.

Referring to fig. 3, 6 and 7, the planar shape of the wing 2 is trapezoidal, and the wing is elliptical. The wings 2 on the two sides are connected into a whole through the switching mechanism 11, the wings 2 on the two sides and the two ends of the switching mechanism 11 are respectively connected in a rotating mode through the first rotating shaft 6, the axial direction of the first rotating shaft 6 is perpendicular to the symmetrical plane of the airplane body 1, so that the wings 2 can rotate around the axial direction of the first rotating shaft 6 relative to the switching mechanism 11, the rotating range is 0-100 degrees, and the switching between the vertical take-off and landing posture and the fixed wing posture is achieved;

the changeover mechanism 11 is composed of a local pie-shaped outer cover 20 and a transition section 19, the pie-shaped outer cover 20 is circular in horizontal projection shape, the vertical section of the pie-shaped outer cover is elliptical, the pie-shaped outer cover 20 is smoothly connected with the wing root of the wing 2 through the transition section 19, and the section of the connection position is an elliptical section 21.

Referring to fig. 2, 3, 7, 8 and 9, the changeover mechanism 11 is fixed right above the fuselage 1 through the wing support 10, the root of the wing support 10 is fixedly connected with the fuselage 1, and the top of the wing support 10 is rotatably connected with the changeover mechanism 11 through the second rotating shaft 7, so that the changeover mechanism 11 drives the wings 2 on two sides to rotate around the second rotating shaft 7, and the switching between the fixed wing attitude and the rotor wing attitude is realized. The cross section of the wing support 10 in the symmetrical plane of the fuselage 1 is trapezoidal, and the radial cross section is elliptical and is formed by bridging two elliptical end faces.

When the aircraft takes off and lands, the wings tilt upwards around the first rotating shaft 6, so that the propeller of the power system 3 faces upwards, even if the power output of the power system 3 is converted from horizontal output to longitudinal output, the aircraft generates upward lift force through the pulling force generated by the rotation of the propeller, and thus the vertical taking off and landing are realized; when the airplane flies to a designated take-off and landing height, the wings tilt forwards around the first rotating shaft 6, so that the power output of the power system is converted from longitudinal output to horizontal output, namely, the power output is switched to a fixed wing mode with better speed characteristic and cruise characteristic, the fixed wing flying is realized, and the landing gear is retracted simultaneously; the normal landing process is just opposite to the taking-off process;

when the aircraft takes off and lands, the pitching and attitude control of the aircraft is mainly realized by adjusting the size of the wing tilting angle and differentially controlling the rotating speed of left and right engine propellers; when the fixed wing flies in cruising or the self-rotating rotor wings, the attitude control is mainly realized by an inverted V-shaped tail wing arranged at the tail part of the aircraft body;

when the aircraft takes off and lands and flies in the normal air, the left and right power systems 3 adopt a separate and independent power supply mode, 2 groups of battery packs respectively supply power to a left engine and a right engine, the other 1 group of battery packs supply power to airborne equipment, an emergency power supply does not work, and in the air cruising flight process, the flexible solar cell panel skin 22 arranged on the surface of the wing skin stores energy for the 3 groups of battery packs by using solar energy so as to prolong the flight time; when the battery pack power supply system has a fault in the air, the emergency power supply starts to work and serves as an airborne device, and the solar panel flexible skin 22 stores energy for the emergency battery by using solar energy;

the gyroplane is taken as the safest aircraft in the world at present, is deeply favored by flight enthusiasts in the field of navigation, and the aircraft scheme related in the invention can be directly switched into a self-rotation gyroplane mode when an air power system fails, and the specific steps are as follows: the propeller blades of the power system are collected into the power system housing to reduce the resistance of the rotor wing during flight, and meanwhile, the switching mechanism drives the wing to rotate around the rotating shaft 6, so that the mode is switched into a gyroplane mode;

when the aircraft is parked on the ground, the switching mechanism and the wings rotate clockwise to the position parallel to the aircraft body and then are locked, and the propeller blades of the power system are locked after being collected into the rectification outer cover of the power system, so that the parking space on the ground is reduced, and the aircraft is prevented from being damaged by the collision of foreign matters on the ground.

Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.

Claims

1. A three-flight mode electric general aircraft capable of vertically taking off and landing comprises an aircraft body (1), wings (2), a power system (3), an empennage (5), an undercarriage (8) and a cabin (9), wherein the wings (2) are positioned on two sides of the aircraft body (1), the power system (3) is arranged on the wings (2), the empennage (5) is positioned at the tail part of the aircraft body (1), the undercarriage (8) is positioned at the belly part of the aircraft body (1), and the cabin (9) is positioned at the front end above the aircraft body (1); the method is characterized in that: the wing support is characterized by also comprising a fairing (4), a first rotating shaft (6), a second rotating shaft (7), a wing support (10) and a switching mechanism (11);

the two power systems (3) are symmetrically arranged on the front edges of the wings (2) on the two sides through two fairing covers (4) respectively, the power systems (3) are propelled by propellers, the propellers are of retractable structures, blades rotate around a shaft in a working state, and the blades are retracted to the fairing covers (4) in a non-working state;

the wings (2) on the two sides are connected into a whole through the switching mechanism (11), the wings (2) on the two sides are rotatably connected with the two ends of the switching mechanism (11) through the first rotating shaft (6), and the axial direction of the first rotating shaft (6) is perpendicular to the symmetrical plane of the fuselage (1), so that the wings (2) can rotate around the axial direction of the first rotating shaft (6) relative to the switching mechanism (11), and the switching between the vertical take-off and landing posture and the fixed wing posture is realized;

changeover mechanism (11) are fixed in directly over fuselage (1) through wing props (10), and the wing props (10) root and fuselage (1) fixed linking to each other, and the top that the wing propped (10) is rotated with changeover mechanism (11) through second pivot (7) and is connected for changeover mechanism (11) drive wing (2) of both sides around second pivot (7) rotatory, realize the switching of stationary vane gesture and rotor wing gesture.

2. The triple-flight mode electric utility vehicle of claim 1, wherein: still include the airborne power supply, the airborne power supply includes 3 group's batteries and emergency power source, and wherein 2 group's batteries are used for driving system (3) power supply respectively, and 1 group is used for the airborne equipment power supply in addition.

3. The triple-flight mode electric utility vehicle of claim 2, wherein: the skin is flexible solar cell panel skin (22), can absorb solar energy and be the airborne power energy storage, prolongs flight time.

4. The triple-flight mode electric utility vehicle of claim 1, wherein: the machine body (1) is designed in a streamline shape; the radial section adopts a double-arc design and comprises an upper arc line (12) and a lower arc line (13), wherein the upper arc line (12) takes the 2/3 part of a circle, and the lower arc line (13) takes the 1/4 part of the circle; the radial cross-sections along the axial direction are scaled in equal proportion.

5. The triple-flight mode electric utility vehicle of claim 1, wherein: the plane shape of the wing (2) adopts a trapezoidal design, the wing adopts an elliptical wing shape, and the range of rotation around the first rotating shaft (6) is 0-100 degrees.

6. The triple-flight mode electric utility vehicle of claim 1, wherein: the cross section of the wing support (10) in the symmetrical plane of the fuselage (1) is trapezoidal, the radial cross section is oval, and the wing support is formed by bridging two oval end faces.

7. The triple-flight mode electric utility vehicle of claim 1, wherein: the changeover mechanism (11) is composed of a local cake-shaped outer cover (20) and a transition section (19), the horizontal projection shape of the cake-shaped outer cover (20) is circular, the vertical section of the cake-shaped outer cover is elliptical, the cake-shaped outer cover (20) is smoothly connected with the wing root of the wing (2) through the transition section (19), and the section of the connection position is an elliptical section (21).

8. The triple-flight mode electric utility vehicle of claim 1, wherein: the fairing (4) comprises a fairing outer cover (14) and grooves (15), the grooves (15) are symmetrically arranged on the peripheral wall surface of the fairing outer cover (14) and used as storage bins for propeller blades, the propeller blades are recovered into the grooves (15), and the fairing (4) is circular in section; the propeller comprises two blades, the blades are connected with the front end of the fairing (4) through a steering engine, and the steering engine controls the blades to be unfolded and retracted.

9. The triple-flight mode electric utility vehicle of claim 1, wherein: the fairing (4) shrinks proportionally along the axial section.

10. The triple-flight mode electric utility vehicle of claim 1, wherein: the root of the fairing (14) and the wing skin are in streamline fusion design.