CN218594569U - Distributed power aircraft with combined tilting rotor and lifting rotor - Google Patents

Abstract

The utility model relates to a distributed power aircraft with a combination of a tilting rotor wing and a lifting rotor wing, which comprises an aircraft body, a front wing, a rear wing and a vertical tail; preceding wing front end with preceding vaulting pole and back vaulting pole have been arranged respectively to the back wing rear end, preceding vaulting pole with the power device that verts inboard and the outside is all installed respectively through the axle-moving subassembly to the front end of connecting the vaulting pole and is formed jointly and incline the driving force system, the back vaulting pole with the top of connecting the vaulting pole then is installed respectively back rotor power device and a plurality of side rotor power device and is formed rotor power system jointly. The utility model discloses combined the safe simple and rotor high performance's that verts advantage of compound wing, carried out rational layout to power device and the rotor power device that verts, optimized the configuration, reached weight less relatively, the system complexity is low, the performance is outstanding effect.

Description

Distributed power aircraft with combination of tilting rotor and lifting rotor

Technical Field

The utility model relates to a general aviation field, concretely relates to distributed power aircraft of rotor and lift rotor combination verts.

Background

When super-large urban groups are formed generally, the problems of ground traffic jam and environmental pollution become more and more serious, and the ground traffic infrastructure can not meet the demand of residents for convenient travel. Electric manned vertical take-off and landing aircraft (eVTOL) enables urban travel to be converted from two-dimensional to three-dimensional traffic, also known as urban aircraft.

At present, the urban aircraft mainly adopts a composite wing and a pure tilt rotor aircraft.

(1) Pure composite wing layout (vertical power plus propulsive power): when cruising, the power of the lift rotor wing stops rotating, no longer produces beneficial effect, increases cruising resistance, leads to low cruising lift-drag ratio, and a large amount of weight of the power system of the lift rotor wing forms waste weight at the moment, only can ensure that the airplane flies forward by means of propulsion power, and the cruising speed is low. However, two sets of power of the system are independent, the system structure and control are simple and mature, and a large amount of composite wing vertical take-off and landing aircrafts are developed and used in the field of unmanned aerial vehicles in China.

(2) Pure tilt rotor layout: one set of power both as take-off and land direct lift, as the propulsion power that cruises again, realize multiplexing, so power all is propulsion power, and the big lift-drag ratio of speed of crusing is the advantage, but has brought the system reliability design difficult problem that verts again to and complicated trouble mode is handled, makes the cost too high simultaneously. The tilting rotor aircraft model is not developed or used successfully in China at present, the period and the cost required to be groped are very large, and a plurality of the tilting rotor aircraft in China lose control force when tilting to a power axis to pass through the gravity center, so that the aircraft is easy to crash.

(3) Rotor safety redundancy design: the existing designs only adopt 4 or 6 lifting rotors, and the rotor can not or difficultly respond to 1-2 failed rotors, so that the design defect is fatal.

(4) The existing designs are generally insufficient in wind resistance and too high in use limit requirement.

(5) The rotor plane poses a threat to the ground or passengers. The rotor position is too low when hovering, or in the plane of the driver and passengers when cruising, which is a safety hazard.

SUMMERY OF THE UTILITY MODEL

The utility model provides a technical problem provide a combine composite wing safety simple and tilt rotor high performance advantage, and impel power big, fast, cruise efficiently, and the distributed power aircraft of the rotor that verts that the security performance is high and lift rotor combination.

The utility model provides a technical scheme that its technical problem adopted is:

a distributed power aircraft combining a tilting rotor wing and a lifting rotor wing comprises an aircraft body, a front wing, a rear wing and a vertical tail, wherein the front wing and the rear wing are arranged on the front section and the rear section of the aircraft body in a bilateral symmetry mode respectively, tips on the left side and the right side of the front wing and the rear wing are connected through connecting support rods, and the vertical tail is arranged on the upper side of the tail of the aircraft body; preceding wing front end with preceding vaulting pole and back vaulting pole have been arranged respectively to the back wing rear end, preceding vaulting pole with the front end of connecting the vaulting pole is all installed the inboard power device that verts respectively and is formed the operating system that inclines jointly with the power device that verts in the outside through the axle-moving subassembly, the back vaulting pole with the top of connecting the vaulting pole then installs back rotor power device respectively and constitutes rotor power system jointly with a plurality of side rotor power device, the power system that verts winds through the power device drive the axle-moving subassembly rotates, provides thrust forward, then does after making progress rotor power system's partly.

Further, when the tilting power system is forward, the paddle planes of the inner side tilting power device and the outer side tilting power device are on two different vertical planes.

Preferably, the inboard power device that verts with the oar plane of the power device that verts of outside arranges around respectively, and staggers the key position of fuselage anterior segment driver's cabin.

Further, when power system that verts rotates upwards, inboard vert power device with the equal introversion of back rotor power device, the power device that verts in the outside with the equal extroversion of a plurality of side rotor power device.

Preferably, the angle of said inward inclination and said angle of said outward inclination are between 10 ° and 15 °.

Further, when the tilting power system is upward, the inner side tilting power device and the rear rotor power device are located on a first plane, the outer side tilting power device is located on a second plane, and the plurality of side rotor power devices are located on a third plane.

Preferably, the first plane, the second plane and the third plane are sequentially arranged from top to bottom.

Further, the fuselage front portion is the driver's cabin and installs driver's cabin front windshield and driver's cabin side windshield and driver's cabin emergency exit, the fuselage middle part is the passenger cabin, its side-mounting has passenger cabin windshield and passenger cabin emergency exit.

Furthermore, a control surface and an elevator are arranged on the rear edge of the front wing, an aileron is arranged on the rear edge of the rear wing, and a rudder is arranged on the rear edge of the vertical tail.

Furthermore, a plurality of undercarriages are arranged on the lower belly of the fuselage.

The utility model has the advantages that:

1. the utility model discloses combined the safe simple and rotor high performance's that verts advantage of composite wing, carried out rational layout to verting power device and rotor power device, optimized the configuration, reached that weight is less relatively, the system complexity is low, the performance is outstanding effect.

2. When the aircraft navigates, four tilting power devices are used as propulsion power, the cruising speed is high, the rapid arrival is facilitated, the propulsion propeller is positioned in the free airflow in front of the wing surface, the cruising efficiency is high, an additional lift-increasing effect is generated on the wing surface with the smaller rear part, and the lift-drag ratio of the whole aircraft is improved.

3. When the aircraft rises and falls and hovers, the tilting power device at the front end of the aircraft rotates upwards to be used as a part of a rotor power system, the aircraft has ten lift rotor devices in total to form the rotor power system together, the redundancy of the power system is large, the ten rotors are distributed around the center of gravity, the rotor inclination design is adopted, the rotating torque is maximized, the aircraft nose pointing and wind resistance are excellent, the hovering control effect is optimal, the influence is minimal when any 1-2 powers fail, and the safety is high.

4. When hovering and vertically taking off and landing, all rotor propellers are distributed on three planes with different heights, no control dead point exists in the wind resistance and attitude adjustment of the airplane, the flight transition is stable, and the debugging attitude control capability and the wind resistance capability are optimal.

5. When taking off and landing, all the rotor wings are higher than the top of the head, so that the aircraft is safe to ground personnel; when cruising, all propulsion propeller planes are in front of the passenger position and do not pose a threat.

Drawings

FIG. 1 is a three-dimensional structure of the present invention;

FIG. 2 is a view of the FIG. 1 deformed state;

fig. 3 is a front view of the present invention;

fig. 4 is a side view of the present invention;

fig. 5 is a top view of the present invention;

fig. 6 is a schematic view of the power plant according to an embodiment of the present invention;

labeled in the figure as:

1. the aircraft comprises an aircraft body, 2 parts of a front wing, 3 parts of a rear wing, 4 parts of a vertical tail, 5 parts of a rear supporting rod, 6 parts of a connecting supporting rod, 7 parts of a front supporting rod, 1-1 parts of cab front windshield glass, 1-2 parts of cab side windshield glass, 1-3 parts of cabin windshield glass, 1-4 parts of main landing gear, 1-5 parts of front landing gear, 2-1 parts of control rudder surface, 2-2 parts of lifting rudder, 3-1 parts of auxiliary wing, 4-1 parts of rudder, A part of inner side tilting power device, B part of outer side tilting power device, C part of side rotor power device and D part of rear rotor power device.

Detailed Description

In order to make the aforementioned objects, features and advantages of the present invention more comprehensible, embodiments accompanied with figures are described in detail below. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. The invention may be embodied in many other forms different from those described herein and similar modifications may be made by those skilled in the art without departing from the spirit and scope of the invention and, therefore, the invention is not to be limited to the specific embodiments disclosed below.

It is to be noted that, unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.

As shown in fig. 1, the utility model provides a distributed power aircraft of rotor and lift rotor combination verts, include: the airplane comprises an airplane body 1, a front wing 2, a rear wing 3 and a vertical fin 4, wherein the front wing 2 and the rear wing 3 are arranged on the front portion and the rear portion of the airplane body 1 in a bilateral symmetry mode respectively, the tips of the left side and the tips of the right side of the airplane body are connected through a connecting stay bar 6, and the vertical fin 4 is arranged on the upper side of the tail portion of the airplane body 1. Further, the utility model discloses in, the front end bilateral symmetry of the front wing 2 of the fuselage 1 left and right sides has front stay 7, and the rear end bilateral symmetry of the back wing 3 of the fuselage 1 left and right sides has back stay 5. Connect the front end equipartition of vaulting pole 6 and front stay 7 to have put and vert power device and constitute and incline the rotating force system, connect the top equipartition of vaulting pole 6 and back vaulting pole 5 to have put rotor power device and constitute rotor power system, constitute the utility model discloses a rotor and lift rotor combined's distributed power aircraft verts through verting power system and rotor power system jointly.

As shown in fig. 1, the fuselage 1 is preferably a streamlined fuselage, but not limited to a streamlined fuselage. The front part of the body 1 is a cab, and is provided with a cab front windshield 1-1, a cab side windshield 1-2 and a cab safety door, the middle part of the body 1 is a passenger cabin, and the side surface of the body 1 is provided with a passenger cabin windshield and a passenger cabin safety door. The vertical tail is arranged on the upper side of the tail part of the airplane body 1, and the landing gear is arranged on the lower belly part of the airplane body 1. The utility model discloses in, the undercarriage adopts the three point type undercarriage in front, including the undercarriage 1-4 of the main undercarriage and the undercarriage 1-5 in the place ahead of arranging about, the main undercarriage 1-4 bilateral symmetry arranges the rear at fuselage 1 lower abdomen, and undercarriage 1-5 arranges the place ahead at fuselage 1 lower abdomen, and all undercarriages all adopt the rectification design.

The utility model discloses a front wing 2 and back wing 3 all adopt high lift wing section wing, and vertical fin 4 adopts symmetrical wing section vertical fin, and front wing 2 and the equal bilateral symmetry of back wing 3 arrange respectively in fuselage 1's anterior segment top and back end top. Further, a control surface 2-1 and an elevator 2-2 for pitch control are arranged at the rear edge of the front wing 2. Further, an aileron 3-1 for yaw control is arranged at the rear edge of the rear wing 3. Further, a rudder 4-1 for heading control is arranged at the rear edge of the vertical fin 4.

As shown in fig. 1 and fig. 3, the utility model discloses in, the power device that verts rotates through the axle-driven component and connects the front end at connecting vaulting pole 6 and preceding vaulting pole 7, controls the power device that verts that connects the front end of vaulting pole 6 and forms the outside power device B that verts, and the power device that verts of preceding vaulting pole 7 front end then forms inboard power device a that verts. And an electric or pneumatic power device such as a motor or an air cylinder for driving the tilting power device to rotate is further installed in the shaft-moving assembly, so that the forward and upward rotation of the shaft-moving assembly is controlled by the driving of the respective power device. The rotor power device is arranged above the connecting support rod 6 and the rear support rod 5, and further, a plurality of groups of side rotor power devices C are arranged on the connecting support rod 6, in one embodiment, two groups of side rotor power devices C are uniformly arranged on the left and right connecting support rods 6, and a group of rear rotor power devices D are arranged on the rear support rod 5. Each power device and rotor power device vert all include respective motor, electricity and transfer and the screw the utility model discloses in, power device's that verts screw preferably adopts the variable pitch screw. Meanwhile, the tilting power device and the fixed rotor wing power device both adopt a distributed electric low-rotation-speed propeller design, and the noise in the take-off and landing stage and the cruise stage can be greatly reduced.

As shown in fig. 3, the utility model discloses an inboard power device a that verts and the equal inclination of back rotor power device D (for fuselage 1 inclination), the inclination is 10 ° -15, and the equal camber of power device B and side rotor power device C that verts in the outside (for fuselage 1 camber), camber angle also is 10 ° -15.

The utility model discloses aircraft's flight process as follows:

the tilting power device can rotate around the axial motion assembly, and a propeller rotating shaft of the tilting power device is vertically upwards used as a part of a rotor wing power system in the lifting, standby and hovering stages, as shown in fig. 2, the tilting power device is matched with the rotor wing power device above the connecting support rod 6 and the rear support rod 5 to jointly generate upward pulling force, so that the aircraft vertically takes off; during the level flight stage, the rotating shaft of the propeller of the tilting power device is horizontally forward (as shown in figure 1), so that forward pulling force is generated, and the aircraft flies forward. When the aircraft is in level flight, the propellers of the rotor wing power devices are locked along the heading direction, so that the resistance is reduced.

Fig. 4 and 5 show the positional arrangement of the tilt power unit and the rotor power unit in various states. As shown in fig. 5, in the flat flight state, the paddle rotation plane Aplane of the inside tilt power device a and the paddle rotation plane B plane of the outside tilt power device B are on two different planes, and the paddle rotation plane Aplane and the paddle rotation plane B plane are all staggered from the key position of the driver. As shown in fig. 4, in the vertical take-off and landing state, the propeller mounting planes of the inner-side tilt power device a and the rear rotor power device D are the same plane, and are both 3st planes, the propeller mounting plane of the outer-side tilt power device B is 2st planes, and the propeller mounting planes of the rotor power devices C are both 1st planes.

The utility model discloses an aircraft is hovering and when VTOL, and the power device that verts of aircraft front end is rotatory upwards as rotor power device, constitutes rotor driving system jointly with the rotary power device who connects vaulting pole and back vaulting pole top. Propellers of all rotor wing power devices are distributed at 3 different heights (1 st plane, 2st plane and 3st plane), no control dead point exists in the wind resistance and attitude adjustment of the airplane, the flight transition is stable, and the debugging attitude control capability and the wind resistance capability are optimal.

The utility model provides a power device verts and rotor power device's screw direction of rotation as follows:

when the aircraft is in a flat flight state, the rotation directions of the propellers of the inner tilting power device A and the outer tilting power device B on the left side and the right side of the aircraft body are opposite, and the rotation directions of the inner tilting power device and the outer tilting power device are also opposite, so that a complementary state is formed. As shown in fig. 6, in one embodiment, when viewed from the machine head to the machine tail, the propeller of the right inner tilting power device a rotates in the counterclockwise direction, and the propeller of the right outer tilting power device B rotates in the clockwise direction; the propeller of the left inner tilt power unit a rotates in the clockwise direction and the propeller of the left outer tilt power unit B rotates in the counterclockwise direction. Simultaneously, the screw of each rotor power device above connection vaulting pole and the back vaulting pole is for following the navigation direction locking to reduce the resistance.

When the aircraft goes up and down or hovers, four tilting power devices at the front end of the aircraft all rotate upwards to serve as rotor power devices, the rotor power systems jointly form a rotor power system together with the rotor power devices above the connecting stay bar and the rear stay bar, at the moment, the rotation directions of the propellers of all the rotor power devices in the rotor power system are opposite and complementary, as shown in fig. 6, the propeller of the rear rotor power device D rotates along the anticlockwise direction, the propeller of the rotor power device C-2 at the rear of the connecting stay bar rotates along the clockwise direction, the propeller of the rotor power device C-1 in front of the connecting stay bar rotates along the anticlockwise direction, the propeller of the right-side outer tilting power device B rotates along the clockwise direction, and the propeller of the right-side inner tilting power device A rotates along the anticlockwise direction. The rotation directions of the propellers of the power devices on the left side symmetrically and complementarily rotate.

The utility model discloses combined the safe simple and tiltrotor high performance's of composite wing advantage, carried out rational overall arrangement, optimized structure to it is less relatively to reach weight, and the system complexity is low, the outstanding effect of performance. When cruising, the front end is provided with four tilting power devices as propulsion power, the cruising speed is high, the fast arrival is facilitated, the propulsion propeller is positioned in the free airflow in front of the airfoil, the cruising efficiency is high, an additional lift-increasing effect is generated on the airfoil with a smaller rear part, and the lift-drag ratio of the whole aircraft is improved. When taking off and hovering, four power devices that vert in front rotate upwards, constitute rotor driving system jointly with other six rotor power devices, the aircraft possesses ten lift rotor systems that total, and driving system redundancy is big, and ten rotors distribute around the focus to adopt the rotor slope design, the maximize of rotation torque has outstanding aircraft nose directional and anti-wind ability, and the control effect of hovering is best, and the influence is minimum when any 1-2 power breaks down, has improved the security performance greatly.

The above-mentioned embodiments, further detailed description of the objects, technical solutions and advantages of the present invention, it should be understood that the above-mentioned embodiments are only specific embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the scope of the present invention.

Claims (10)

1. The utility model provides a distributed power aircraft of rotor and lift rotor combination verts, includes fuselage, front wing, back wing and vertical fin, its characterized in that: the front wing and the rear wing are arranged on the front section and the rear section of the fuselage in a bilateral symmetry mode respectively, the tips of the left side and the right side of the front wing and the rear wing are connected through connecting support rods, and the vertical tails are arranged on the upper side of the tail of the fuselage; the front wing front end with fore-stock and back-stay have been arranged respectively to the back wing rear end, the fore-stock with the front end of connecting the stay all installs inboard power device that verts and the power device that verts in the outside respectively through the axle moves the subassembly and constitutes the operating system that verts jointly, the back stay with the top of connecting the stay then installs respectively back rotor power device and a plurality of side rotor power device and constitutes rotor power system jointly, the power system that verts winds through the power device drive the axle moves the subassembly and rotates, provides thrust forward, then does after making progress rotor power system's partly.

2. A tiltrotor rotor and lift rotor combined distributed power aircraft as defined in claim 1, wherein: when the tilting power system is forward, the paddle planes of the inner side tilting power device and the outer side tilting power device are on two different vertical planes.

3. The tiltrotor rotor and lift rotor combination distributed power aircraft of claim 2, wherein: inboard power device that verts with the power device that verts's the oar plane in the outside arranges around respectively, and staggers the key position of fuselage anterior segment driver's cabin.

4. A tiltrotor rotor and lift rotor combined distributed power aircraft as defined in claim 1, wherein: when the tilting power system rotates upwards, the inner side tilts the power device and the rear rotor power device tilts inwards, and the outer side tilts the power device and the plurality of side rotor power devices tilt outwards.

5. A tiltrotor rotor and lift rotor combined distributed power aircraft as defined in claim 4, wherein: the angle of the inward inclination and the angle of the outward inclination are between 10 degrees and 15 degrees.

6. A tiltrotor rotor and lift rotor combined distributed power aircraft as defined in claim 1, wherein: when the tilting power system rotates upwards, the inner side tilting power device and the paddle plane of the rear rotor power device are located on a first plane, the paddle plane of the outer side tilting power device is located on a second plane, and the paddle planes of the plurality of side rotor power devices are located on a third plane.

7. A tiltrotor rotor and lift rotor combined distributed power aircraft as defined in claim 6, wherein: the first plane, the second plane and the third plane are sequentially arranged from top to bottom.

8. A tiltrotor rotor and lift rotor combined distributed power aircraft as claimed in any one of claims 1 to 7, wherein: the fuselage front portion is the driver's cabin and installs front windshield of driver's cabin and driver's cabin side windshield and driver's cabin emergency exit, the fuselage middle part is passenger cabin, its side-mounting has passenger cabin windshield and passenger cabin emergency exit.

9. A tiltrotor rotor and lift rotor combined distributed power aircraft as defined in claim 8, wherein: the rear edge of the front wing is provided with a control surface and an elevator, the rear edge of the rear wing is provided with an aileron, and the rear edge of the vertical tail is provided with a rudder.

10. A tiltrotor rotor and lift rotor combined distributed power aircraft as defined in claim 8, wherein: the lower belly of the fuselage is also provided with a plurality of landing gears.

Images