CN113844647B

CN113844647B - Three-flight-mode electric general aircraft capable of taking off and landing vertically

Info

Publication number: CN113844647B
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: 2023-05-16
Anticipated expiration: 2041-09-21
Also published as: CN113844647A

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 a fuselage, wings, a power system, a tail wing, 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 a propeller for propulsion, the propeller blades in the working state of the propeller are unfolded to rotate around the shaft, and the blades in the non-working state are retracted to the fairing; the wings on two sides are connected into a whole through the switching mechanism, and are connected in a rotating way 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 above the fuselage through the wing support, and the wing support is rotationally connected with the switching mechanism through a second rotating shaft, so that the switching mechanism drives the wings on two sides to rotate around the second rotating shaft, and the switching of the fixed wing posture and the rotor wing posture is realized. 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 aviation craft in China is rapidly developed, the total flying amount is increased by more than 10%, the industry scale is increasingly enlarged, the application field is continuously expanded, the flying types are increasingly increased, and the flying demand is gradually vigorous. The development of general aviation is promoted, and the method has important significance for building civil aviation. The general aviation aircraft has the advantages of simple operation, low requirements on the landing sites and the like.

Electric aircraft use electric propulsion systems instead of internal combustion engine power, thus achieving many advantages and unique qualities. The most outstanding advantages are energy saving, environment 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 (explosion and fuel leakage are not generated), simple structure, convenient 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; aircraft with supernormal performance can be designed, special purpose requirements can be met, and the like.

Rotorcraft is a rotorcraft that uses the relative airflow of a forward flight to blow the rotor to spin to generate lift, with the forward force being provided directly by the engine driving the propeller. The rotor can make approximately vertical descent, and the descent technique is an aviation technique developed at the end of the 50 s. The aircraft using the drop technology is flexible and has incomparable advantages to the conventional aircraft. First, aircraft with droop capability do not require specialized airports and runways, and can reduce use costs. In addition, the vertical-landing aircraft can land on a small site, so that the battlefield survival rate of the aircraft is greatly improved.

V-22 tiltrotor aircraft (nickname: hawk) is a type of tiltrotor aircraft with vertical take-off and landing (short take-off and landing capability), V-22 tiltrotor aircraft is similar to a fixed wing aircraft in appearance, but two rotatable engines at wing tips drive two rotors, in a fixed wing state, V-22 is like an aircraft with two oversized propellers at wing tips at two sides, and in a helicopter state, the helicopter is a helicopter with two smaller propellers, so that the helicopter has the advantages of vertical lifting capability of the helicopter, but has the advantages of high speed, long range and lower oil consumption of the fixed wing helicopter, and the maximum flying speed reaches 509 km, and is the fastest helicopter in the world.

The general aircraft has good application prospect due to the advantages of simple operation, strong flexibility and the like, but has high dependence on the flight field and environment due to the need of running in the take-off and landing stage; the common aviation general aircraft has short endurance time and low reliability due to the adoption of the driving of an internal combustion engine, which is the technical problem to be solved by the invention.

The aircraft design scheme provided by the invention can quickly cruise in a fixed wing posture, can take off and land vertically like a V-22 aircraft, and can safely land in a rotor wing type flight mode in a state that an engine is stopped. The aircraft can rely on solar energy storage to provide power for the aircraft in the cruising state, and the range of the aircraft is prolonged.

Disclosure of Invention

The technical problems to be solved are 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, which enables the aircraft to have the characteristic of taking off and landing vertically and reduces the environmental dependence; the problem of short endurance of the flight can be solved by solar energy storage under the flight attitude of the fixed wing; the rotor wing mode can ensure the safe landing of the aircraft in an emergency state that the aircraft loses power; thereby improving the flexibility, cruising ability and safety performance of the aircraft.

The technical scheme of the invention is as follows: the utility model provides a but three flight mode electric general aircraft of vertical take off and land, includes fuselage 1, wing 2, driving system 3, fin 5, undercarriage 8, cabin 9, and wing 2 is located the both sides of fuselage 1, and driving system 3 sets up on wing 2, and fin 5 is located fuselage 1 afterbody, and undercarriage 8 is located fuselage 1 belly, and cabin 9 is located fuselage 1 top front end; the method is characterized in that: the wind turbine also comprises a fairing 4, a first rotating shaft 6, a second rotating shaft 7, a wing brace 10 and a switching mechanism 11;

the two power systems 3 are symmetrically arranged at the front edges of the wings 2 at two sides respectively through two fairings 4, the power systems 3 adopt propellers for propulsion, the propellers are of a retractable structure, the working state blades are unfolded to rotate around the shaft, and the non-working state blades are retracted to the fairings 4;

the two wings 2 are connected into a whole through the switching mechanism 11, the two sides of the wings 2 are respectively and rotatably connected with the two ends of the switching mechanism 11 through the first rotating shaft 6, 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;

the switching mechanism 11 is fixed right above the machine body 1 through the wing support 10, the root of the wing support 10 is fixedly connected with the machine body 1, the top of the wing support 10 is rotationally connected with the switching mechanism 11 through the second rotating shaft 7, the switching mechanism 11 drives the wings 2 on two sides to rotate around the second rotating shaft 7, and the switching of the fixed wing posture and the rotor wing posture is realized.

The invention further adopts the technical scheme that: the system also comprises an onboard power supply, wherein the onboard power supply comprises 3 groups of batteries and an emergency power supply, 2 groups of batteries are respectively used for supplying power to the power system 3, and the other 1 group of batteries are used for supplying power to onboard equipment.

The invention further adopts the technical scheme that: the skin is a flexible solar panel skin 22, which can absorb solar energy to store energy for an airborne power supply and prolong the flight time.

The invention further adopts the technical scheme that: the machine body 1 is in streamline shape design; 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 2/3 of a circle, and the lower arc line 13 takes 1/4 of the circle; the radial cross-section along the axial direction is scaled equally.

The invention further adopts the technical scheme that: the plane shape of the wing 2 adopts a trapezoid design, the wing profile adopts an elliptic wing profile, and the range of rotation of the wing profile around the first rotating shaft 6 is 0-100 degrees.

The invention further adopts the technical scheme that: the cross section of the wing brace 10 in the symmetrical plane of the machine body 1 is trapezoid, the radial cross section is elliptical, and the wing brace is formed by bridging two elliptical end surfaces.

The invention further adopts the technical scheme that: the switching mechanism 11 is composed of a local cake-shaped outer cover 20 and a transition section 19, the cake-shaped outer cover 20 is circular in horizontal projection shape, the vertical section 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 part is an elliptical section 21.

The invention further adopts the technical scheme that: the fairing 4 comprises a fairing 14 and a groove 15, the groove 15 is symmetrically arranged on the peripheral wall surface of the fairing 14 and is used as a storage bin for propeller blades, the blades are recycled into the groove 15, and the fairing 4 is of a circular section; the propeller comprises two blades, the blades are connected with the front end of the fairing 4 through a steering engine, and the expansion and the retraction of the blades are controlled by the steering engine.

The invention further adopts the technical scheme that: the fairing 4 has an axial cross-section that is equally contracted.

The invention further adopts the technical scheme that: the root of the fairing 14 is in streamline fusion design with the wing skin.

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 panel skin, and the solar flexible panel skin can store energy for the battery pack of the power system when the fixed wing flies, so that the flight endurance of the aircraft is prolonged.

The wings on two sides of the aircraft are connected with the switching mechanism through the first rotating shaft, so that vertical take-off and landing can be realized when the propellers on two sides are rotated to face upwards, external hardware facilities such as airports are not needed, and the dependence on the take-off and landing environments is small;

when faults such as air engine stopping and the like occur to the aircraft, the wing rotates around the second rotating shaft of the aircraft, the propeller is retracted into the rectifying outer cover of the power system to reduce resistance when the wing rotates, and the flight mode is switched to the safest rotorcraft mode in the current flight field to conduct autorotation and downslide, 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 propellers are retracted into the rectification outer cover of the power system, so that the required ground parking space is smaller, and the parking is more convenient.

The aircraft can fly at a high speed in a fixed wing posture in a cruising state, and has higher cruising speed compared with a common rotor wing type aircraft and a helicopter; when the engine fails and stops, the rotary wing type flying attitude can be converted, and the rotary wing type flying attitude can safely fall; the propeller can be lifted upwards and vertically during take-off and landing, so that the environmental requirement of take-off and landing is 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-sided view;

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

FIG. 3 is a plan view of the solution in detail;

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

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

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

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

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

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

reference numerals illustrate: 1. fuselage, 2, wings, 3, power system, 4, fairing, 5, wings, 6, first shaft, 7, second shaft, 8, landing gear, 9, cabin, 10, wing stay, 11, adaptor mechanism, 12, upper camber, 13, lower camber, 14, fairing, 15, groove, 16, cross section, 17, movable control surface, 18, stabilizer, 19, transition section, 20, pie-shaped fairing, 21, elliptical cross section, 22, flexible solar panel skin.

Detailed Description

The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.

In the description of the present invention, it should 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", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.

Referring to fig. 1-3, the electric aircraft with three flight modes capable of taking off and landing vertically comprises a fuselage 1, wings 2, a power system 3, a fairing 4, a tail wing 5, a first rotating shaft 6, a second rotating shaft 7, a landing gear 8, a cabin 9, a wing brace 10, an adapter mechanism 11 and a flexible solar panel skin 22; the wings 2 are positioned on two sides of the fuselage 1, the power system 3 is arranged on the wings 2, the tail wing 5 is positioned at the tail of the fuselage 1, the landing gear 8 is positioned at the abdomen of the fuselage 1, and the cabin 9 is positioned at the front end above the fuselage 1; the system also comprises an onboard power supply, wherein the onboard power supply comprises 3 groups of batteries and an emergency power supply, 2 groups of batteries are respectively used for supplying power to the power system 3, and the other 1 group of batteries are used for supplying power to onboard equipment. The skin is a flexible solar panel skin 22, which can absorb solar energy to store energy for an airborne power supply and prolong the flight time.

Referring to fig. 1 and 4, the fuselage 1 is of streamlined profile design; 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 2/3 of a circle, and the lower arc line 13 takes 1/4 of the circle; the radial cross-section along the axial direction is scaled equally.

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

referring to fig. 1 and 2, the landing gear 8 is of a front three-point retractable landing gear design; the canopy adopts an integrated all-glass structural design, and has no reinforcing rib in the middle;

referring to fig. 5, two power systems 3 are symmetrically installed at the front edges of wings 2 at two sides through two fairings 4 respectively, the power systems 3 adopt propellers for propulsion, the propellers are of a retractable structure, the working state blades are unfolded to rotate around a shaft, and the non-working state blades are retracted to the fairings 4;

the fairing 4 comprises a fairing 14 and a groove 15, the groove 15 is symmetrically arranged on the peripheral wall surface of the fairing 14 and is used as a storage bin for propeller blades, the blades are recycled into the groove 15, and the fairing 4 is of a circular section; the propeller comprises two blades, the blades are connected with the front end of the fairing 4 through a steering engine, and the expansion and the retraction of the blades are controlled by the steering engine. The fairing 4 has an axial section which is contracted in an equal ratio, and the root of the fairing 14 and the wing skin are in streamline fusion design.

Referring to fig. 3, 6 and 7, the plane shape of the wing 2 adopts a trapezoid design, and the wing profile adopts an elliptic wing profile. The two wings 2 are connected into a whole through the switching mechanism 11, the two sides of the wings 2 are respectively and rotatably connected with the two ends of the switching mechanism 11 through the first rotating shaft 6, the axial direction of the first rotating shaft 6 is perpendicular to the symmetrical plane of the machine 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 lifting posture and the fixed wing posture is realized;

the switching mechanism 11 is composed of a local cake-shaped outer cover 20 and a transition section 19, the cake-shaped outer cover 20 is circular in horizontal projection shape, the vertical section 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 part is an elliptical section 21.

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

When the aircraft takes off and lands, the wings tilt upwards around the first rotating shaft 6 to enable the propellers of the power system 3 to face upwards, even if the power output of the power system 3 is converted from horizontal output to longitudinal output, the aircraft generates upward lifting force through the pulling force generated by the rotation of the propellers, and therefore vertical take off and lands are achieved; when the aircraft flies to a designated take-off and landing altitude, 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 mode is switched to a fixed wing mode with better speed characteristics and cruising characteristics, the fixed wing flying is realized, and meanwhile, the landing gear is retracted; the normal landing process is opposite to the take-off process;

when the aircraft takes off and land, the pitching and attitude control of the aircraft is realized mainly by adjusting the inclination angle of the wing and the rotating speeds of the left and right engine propellers in a differential control way; when the fixed wing cruises to fly or the autorotation rotor flies, the gesture control is realized mainly by an inverted V-shaped tail wing arranged at the tail part of the fuselage;

when the aircraft flies in the air, the left power system 3 and the right power system 3 adopt a mode of separately and independently supplying power, 2 groups of battery packs respectively supply power for the left engine and the right engine, and the other 1 group of battery packs supply power for airborne equipment, an emergency power supply does not work, and in the process of flying in the air, the flexible solar panel skin 22 arranged on the surface of the wing skin stores energy for the 3 groups of battery packs by utilizing solar energy so as to prolong the flying time of the aircraft; when the battery pack power supply system fails in the air, the emergency power supply starts to work, and the solar panel flexible skin 22 stores energy for the emergency battery by utilizing solar energy for the functions of the airborne equipment;

the gyroplane is taken as the safest aircraft in the world at present, is deeply favored by flight lovers in the navigation field, and the scheme of the aircraft can be directly switched into a gyroplane mode when an air power system fails, and comprises the following specific steps: the propeller blades of the power system are retracted into the power system outer cover so as to reduce the resistance of the rotor wing during flying, and meanwhile, the switching mechanism drives the wing to rotate around the rotating shaft 6, so that the mode of the rotorcraft is switched;

when the ground is parked, the switching mechanism is locked after the wing is connected with the switching mechanism to rotate clockwise to a position parallel to the fuselage, and the propeller blades of the power system are locked after being retracted into the rectification outer cover of the power system, so that the ground parking space is reduced, and the damage to the aircraft caused by the collision of foreign matters on the ground is prevented.

Although embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives, and variations may be made in the above embodiments by those skilled in the art without departing from the spirit and principles of the invention.

Claims

1. The utility model provides a but three flight mode electric general aircraft of vertical take off and land, includes fuselage (1), wing (2), driving system (3), fin (5), undercarriage (8), cabin (9), and wing (2) are located the both sides of fuselage (1), and driving system (3) set up on wing (2), and fin (5) are located the afterbody of fuselage (1), and undercarriage (8) are located the belly of fuselage (1), and cabin (9) are located the front end above fuselage (1); the method is characterized in that: the wind turbine also comprises a fairing (4), a first rotating shaft (6), a second rotating shaft (7), a wing brace (10) and a switching mechanism (11);

the two power systems (3) are symmetrically arranged at the front edges of wings (2) at two sides through two fairings (4), the power systems (3) adopt propellers for propulsion, the propellers are of a retractable structure, the working state blades are unfolded to rotate around a shaft, and the non-working state blades are retracted to the fairings (4);

the two side wings (2) are connected into a whole through the switching mechanism (11), the two side wings (2) are respectively connected with the two ends of the switching mechanism (11) in a rotating way through the first rotating shaft (6), the axial direction of the first rotating shaft (6) is perpendicular to the symmetrical plane of the machine 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), and the switching between the vertical lifting gesture and the fixed wing gesture is realized;

the switching mechanism (11) is fixed above the machine body (1) through the wing support (10), the root of the wing support (10) is fixedly connected with the machine body (1), the top of the wing support (10) is rotationally connected with the switching mechanism (11) through the second rotating shaft (7), and the switching mechanism (11) drives the wings (2) on two sides to rotate around the second rotating shaft (7), so that the switching of the fixed wing posture and the rotor wing posture is realized.

2. The electric three-flight-mode general-purpose aircraft capable of taking off and landing vertically according to claim 1, wherein: the system also comprises an onboard power supply, wherein the onboard power supply comprises 3 groups of batteries and an emergency power supply, 2 groups of batteries are respectively used for supplying power to a power system (3), and the other 1 group of batteries are used for supplying power to onboard equipment.

3. The electric three-flight-mode general-purpose aircraft capable of taking off and landing vertically according to claim 2, wherein: the skin is a flexible solar panel skin (22) which can absorb solar energy to store energy for an airborne power supply and prolong flight time.

4. The electric three-flight-mode general-purpose aircraft capable of taking off and landing vertically according to claim 1, wherein: the machine body (1) is of streamline shape design; 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 2/3 of a circle, and the lower arc line (13) takes 1/4 of the circle; the radial cross-section along the axial direction is scaled equally.

5. The electric three-flight-mode general-purpose aircraft capable of taking off and landing vertically according to claim 1, wherein: the plane shape of the wing (2) adopts a trapezoid design, the wing profile adopts an elliptic wing profile, and the range of rotation of the wing profile around the first rotating shaft (6) is 0-100 degrees.

6. The electric three-flight-mode general-purpose aircraft capable of taking off and landing vertically according to claim 1, wherein: the cross section of the wing brace (10) positioned in the symmetrical plane of the machine body (1) is trapezoid, the radial cross section is elliptical, and the wing brace is formed by bridging two elliptical end surfaces.

7. The electric three-flight-mode general-purpose aircraft capable of taking off and landing vertically according to claim 1, wherein: the switching 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 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 connecting part is an elliptical section (21).

8. The electric three-flight-mode general-purpose aircraft capable of taking off and landing vertically according to claim 1, wherein: the fairing (4) comprises a fairing housing (14) and a groove (15), the groove (15) is symmetrically arranged on the peripheral wall surface of the fairing housing (14) and is used as a storage bin for propeller blades, the blades are recycled into the groove (15), and the fairing (4) is of a circular section; the propeller comprises two blades, the blades are connected with the front end of the fairing (4) through a steering engine, and the expansion and the retraction of the blades are controlled by the steering engine.

9. The electric three-flight-mode general-purpose aircraft capable of taking off and landing vertically according to claim 1, wherein: the fairing (4) is contracted in an equal ratio in the axial section.

10. The electric three-flight-mode general-purpose aircraft capable of taking off and landing vertically according to claim 1, wherein: the root of the rectifying outer cover (14) and the wing skin are in streamline fusion design.