阅读说明：本技术 一种基于混合电推进系统的垂直起降倾转动力翼飞机 (Vertical take-off and landing tilting power wing aircraft based on hybrid electric propulsion system ) 是由 兰旭东 王财政 卜建国 冯光烁 夏爱国 于 2020-12-08 设计创作，主要内容包括：本申请实施例涉及一种基于混合电推进系统的垂直起降倾转动力翼飞机,包括：机身、前动力翼、后动力翼和混合电推进系统,前动力翼有两个,分别设置在机身两侧的前端,前动力翼可相对于机身转动,后动力翼有两个,分别设置在机身两侧的后端,后动力翼可相对于机身转动,混合电推进系统与前动力翼和后动力翼连接,机身两侧分别设置有前动力翼和后动力翼,前动力翼和后动力翼均可相对于机身转动,以便能够根据实际情况进行前动力翼和后动力翼的调节,以完成飞机的垂直起降,以及降低飞机的飞行阻力,以提高飞机的航程,采用混合电推进系统驱动前动力翼和后动力翼,能够使功率分配更加合理,以降低油耗,提高飞机的航程。(The embodiment of the application relates to a VTOL power wing aircraft that verts based on mix electric propulsion system includes: the hybrid electric propulsion system is connected with the front power wing and the rear power wing, the front power wing and the rear power wing are arranged on two sides of the airplane body respectively, the front power wing and the rear power wing can rotate relative to the airplane body, so that the front power wing and the rear power wing can be adjusted according to actual conditions, the vertical take-off and landing of the airplane can be completed, the flight resistance of the airplane can be reduced, the flight range of the airplane can be improved, the front power wing and the rear power wing are driven by the hybrid electric propulsion system, the power distribution can be more reasonable, the oil consumption can be reduced, and the flight range of the airplane can be improved.)

1. A vertical take-off and landing tilt-wing aircraft based on a hybrid electric propulsion system, comprising: the hybrid electric propulsion system comprises a fuselage (1), a front power wing (2), a rear power wing (3) and a hybrid electric propulsion system (9);

the two front power wings (2) are respectively arranged at the front ends of the two sides of the machine body (1), and the front power wings (2) can rotate relative to the machine body (1);

the two rear power wings (3) are respectively arranged at the rear ends of the two sides of the machine body (1), and the rear power wings (3) can rotate relative to the machine body (1);

the hybrid electric propulsion system (9) is connected with the front power wing (2) and the rear power wing (3) and is used for driving the front power wing (2) and the rear power wing (3).

2. The VTOL tiltrotor aircraft based on a hybrid electric propulsion system according to claim 1,

the hybrid electric propulsion system (9) comprises at least a tilting mechanism;

the tilting mechanism is arranged in the machine body (1) and can rotate around the machine body (1);

the tilting mechanism is four in number, and each tilting mechanism is connected with the front power wing (2) and each rear power wing (3) respectively.

3. The VTOL tiltrotor aircraft based on a hybrid electric propulsion system according to claim 2,

the front power wing (2) and the rear power wing (3) both comprise: the propeller (4), the supporting transverse wing (5) and the lower semi-ring wing (6);

one side of the lower semi-ring wing (6) is connected with the tilting mechanism;

the supporting transverse wing (5) is connected to the upper part of the lower semi-ring wing (6);

the propeller (4) is connected to the front end of the support wing (5).

4. A VTOL tiltrotor aircraft based on a hybrid electric propulsion system according to claim 3,

the hybrid electric propulsion system (9) further comprising an engine propulsion system (91), an electric motor propulsion system (92) and a power module (93);

the engine propulsion system (91) and the motor propulsion system (92) are both connected with the power module (93).

5. The VTOL tiltrotor aircraft based on a hybrid electric propulsion system according to claim 4,

the engine propulsion system (91) comprises an engine (911), a starting and power generation integrated motor (912), an input shaft (913), a transmission shaft (914) and an output shaft (915);

the number of the engines (911) and the starting and power generating integrated motors (912) is two, each engine (911) is connected with one starting and power generating integrated motor (912), and each starting and power generating integrated motor (912) is connected with the power module (93);

two input shafts (913), one input shaft (913) being connected to each of the engines (911);

two transmission shafts (914) are provided, and each input shaft (913) is in transmission connection with each transmission shaft (914);

two output shafts (915) are provided, the two output shafts (915) are respectively arranged in the supporting transverse wings (5) of the front power wing (2), and each transmission shaft (914) is respectively in transmission connection with one output shaft (915);

the output shaft (915) is connected with the propeller (4) of the front power wing (2).

6. The VTOL tiltrotor aircraft based on a hybrid electric propulsion system according to claim 4,

the motor propulsion system (92) comprises a storage battery (921) and a motor (922), the motor (922) is electrically connected with the storage battery (921), and the storage battery (921) is connected with the power module (93);

the number of the motors (922) is two, the two motors (922) are respectively arranged inside the supporting transverse wing (5) of the rear power wing (3), and the motors (922) are connected with the propellers (4) of the rear power wing (3).

7. The VTOL tiltrotor aircraft based on a hybrid electric propulsion system according to claim 5,

the tilting mechanism comprises a tilting torsion tube, a bearing, a tilting actuating cylinder and a tilting rocker arm;

the bearing is arranged on one side of the machine body (1);

the tilting torsion tube penetrates through the bearing and the machine body (1) and is connected with the lower semi-ring wing (6);

one end of the tilting rocker arm is connected with the tilting actuating cylinder, and the other end of the tilting rocker arm is connected to the outer side of the tilting torsion tube;

the tilting cylinder is electrically connected with the power module (93);

the transmission shaft (914) is arranged in the tilting torsion tube, and one end of the transmission shaft (914) extends out of the machine body (1) and is in transmission connection with the output shaft (915).

8. The VTOL tiltrotor aircraft based on a hybrid electric propulsion system according to claim 1,

the rear ends of the two sides of the machine body (1) are provided with folded horizontal tails (10);

one side of folding back parallel tail (10) with fuselage (1) rotates and is connected, keeping away from of folding back parallel tail (10) fuselage (1) one side with back power wing (3) are connected.

9. A hybrid electric propulsion system based vtol-tilt-wing aircraft according to any of claims 1-7, characterized in that the fuselage (1) is provided at its bottom with a landing gear mechanism (8).

10. The VTOL tiltrotor aircraft based on a hybrid electric propulsion system according to any of claims 1 to 7, characterized in that the top of the rear end of the fuselage (1) is symmetrically provided with vertical fins (7), and the vertical fins (7) are obliquely arranged with the fuselage (1).

Technical Field

The application relates to the technical field of aircraft manufacturing, in particular to a vertical take-off and landing tilting power wing aircraft based on a hybrid electric propulsion system.

Background

The vertical take-off and landing aircraft is almost not limited by the field, can take off and land on any flat ground, can be deployed at a position closer to a battlefield, is much convenient and quick for transporting personnel and materials, and greatly improves the efficiency of combined delivery; and the probability of hitting by enemy army is greatly reduced because the device is not limited by the field.

At present, vertical take-off and landing aircrafts are mainly divided into two main categories: rotorcraft and fixed-wing aircraft. Among them, rotorcraft are typically represented by helicopters owned by the major military forces of the world. Such as the apache helicopters, the kmann helicopters, the konu dry transport helicopters, the new generation high speed helicopters S-97, etc., the russian card series helicopters, etc., the chinese helicopter in the straight line, etc.

However, the maximum takeoff weight of the helicopter is directly limited by the power of the engine, and after the helicopter vertically flies, rotates and flies horizontally, the power requirement is further improved and the oil consumption is increased due to the increase of resistance, so that the range of the helicopter is greatly influenced, and the hitting capability of the helicopter on a deep target is weak.

Disclosure of Invention

The embodiment of the application provides a VTOL power wing aircraft that verts based on mix electric propulsion system, aims at solving the less problem of current gyroplane range.

The embodiment of the application provides a VTOL power wing aircraft that verts based on mix electric propulsion system includes: the hybrid electric propulsion system comprises a fuselage, a front power wing, a rear power wing and a hybrid electric propulsion system;

the two front power wings are respectively arranged at the front ends of the two sides of the machine body and can rotate relative to the machine body;

the two rear power wings are respectively arranged at the rear ends of the two sides of the machine body and can rotate relative to the machine body;

the hybrid electric propulsion system is connected with the front power wing and the rear power wing and used for driving the front power wing and the rear power wing.

Optionally, the hybrid electric propulsion system comprises at least a tilting mechanism;

the tilting mechanism is arranged in the machine body and can rotate around the machine body;

the tilting mechanism is four, and each of the front power wing and the rear power wing is connected with one tilting mechanism respectively.

Optionally, the front power wing and the rear power wing each comprise: the propeller, the supporting transverse wing and the lower semi-ring wing;

one side of the lower semi-ring wing is connected with the tilting mechanism;

the supporting transverse wings are connected to the upper parts of the lower semi-ring wings;

the propeller is connected to the front end of the support wing.

Optionally, the hybrid electric propulsion system further comprises an engine propulsion system, an electric motor propulsion system, and a power module;

the engine propulsion system and the motor propulsion system are both connected to the power module.

Optionally, the engine propulsion system comprises an engine, a starting and power generation integrated motor, an input shaft, a transmission shaft and an output shaft;

the number of the engines and the starting and power generation integrated motors is two, each engine is connected with one starting and power generation integrated motor, and each starting and power generation integrated motor is connected with the power module;

the number of the input shafts is two, and each engine is connected with one input shaft;

the number of the transmission shafts is two, and each input shaft is in transmission connection with each transmission shaft;

the two output shafts are respectively arranged in the supporting transverse wings of the front power wing, and each transmission shaft is respectively connected with one output shaft in a transmission manner;

the output shaft is connected with the propeller of the front power wing.

Optionally, the electric motor propulsion system comprises a battery and an electric motor, the electric motor being electrically connected to the battery, the battery being connected to the power module;

the two motors are respectively arranged inside the supporting transverse wing of the rear power wing, and the motors are connected with the propeller of the rear power wing.

Optionally, the tilting mechanism comprises a tilting torsion tube, a bearing, a tilting cylinder and a tilting rocker arm;

the bearing is arranged on one side of the machine body;

the tilting torsion tube penetrates through the bearing and the machine body and is connected with the lower semi-ring wing;

one end of the tilting rocker arm is connected with the tilting actuating cylinder, and the other end of the tilting rocker arm is connected to the outer side of the tilting torsion tube;

the tilting actuating cylinder is electrically connected with the power module;

the transmission shaft is arranged in the tilting torsion tube, one end of the transmission shaft extends out of the machine body and is in transmission connection with the output shaft.

Optionally, the rear ends of the two sides of the machine body are provided with folded horizontal tails;

one side of the folded horizontal tail is connected with the machine body in a rotating mode, and one side of the machine body is connected with the rear power wing in a keeping away from the folded horizontal tail.

Optionally, a landing gear mechanism is provided at the bottom of the fuselage.

Optionally, the top of the rear end of the fuselage is symmetrically provided with vertical tails, and the vertical tails and the fuselage are arranged in an inclined manner.

Adopt this application provide based on mixed electric propulsion system's VTOL power wing aircraft that verts, first aspect, the fuselage both sides are provided with preceding power wing and back power wing respectively, and preceding power wing and back power wing all can rotate for the fuselage to can carry out the regulation of preceding power wing and back power wing according to actual conditions, with the VTOL of accomplishing the aircraft, and reduce the flight resistance of aircraft, with the range that improves the aircraft.

In the second aspect, the hybrid electric propulsion system is connected with the front power wing and the rear power wing, and the hybrid electric propulsion system is adopted to drive the front power wing and the rear power wing, so that the power distribution is more reasonable, the oil consumption is reduced, and the range of the airplane is improved.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the description of the embodiments of the present application will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without inventive exercise.

Fig. 1 is a schematic top view of a hybrid electric propulsion system based vtol tilt-wing aircraft according to an embodiment of the present application;

FIG. 2 is a schematic side view of a hybrid electric propulsion system based VTOL tiltrotor aircraft according to an embodiment of the present application;

fig. 3 is a schematic tilted perspective view of a hybrid electric propulsion system-based vtol tilt-wing aircraft according to an embodiment of the present application;

FIG. 4 is a schematic front view of a hybrid electric propulsion system based VTOL tilt-rotor aircraft according to an embodiment of the present application;

FIG. 5 is a schematic illustration of a hybrid electric propulsion system for a VTOL tiltrotor aircraft based on the hybrid electric propulsion system, according to an embodiment of the present application;

fig. 6 is a schematic side view of a hybrid electric propulsion system based vtol tilt-wing aircraft according to an embodiment of the present application.

Description of reference numerals:

1-fuselage, 2-front power wing, 3-rear power wing, 4-propeller, 5-support horizontal wing, 6-lower semi-ring wing, 7-vertical tail, 8-lifting frame mechanism, 9-hybrid electric propulsion system, 10-folded horizontal tail, 91-engine propulsion system, 92-motor propulsion system, 93-power module, 911-engine, 912-starting power generation integrated motor, 914-input shaft, 913-transmission shaft, 915-output shaft, 921-storage battery and 922-motor.

Detailed Description

The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some, but not all, embodiments of the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

In the related art, vertical take-off and landing aircrafts are mainly classified into two categories: rotorcraft and fixed-wing aircraft. Among them, rotorcraft are typically represented by helicopters owned by the major military forces of the world. Such as the apache helicopters, the kmann helicopters, the konu dry transport helicopters, the new generation high speed helicopters S-97, etc., the russian card series helicopters, etc., the chinese helicopter in the straight line, etc.

However, the maximum takeoff weight of the helicopter is directly limited by the power of the engine, and after the helicopter vertically flies, rotates and flies horizontally, the power requirement is further improved and the oil consumption is increased due to the increase of resistance, so that the range of the helicopter is greatly influenced, and the hitting capability of the helicopter on a deep target is weak.

In view of the above, the application creatively provides a solution of a vertical take-off and landing tilting power wing aircraft based on a hybrid electric propulsion system, and a new configuration (tilting power wing) and a new hybrid power system (hybrid electric propulsion system) are comprehensively adopted, so that the unmanned aircraft has the characteristics of vertical take-off and landing, long endurance and fixed wing carrier-based aircraft, can be used for verifying and developing a vertical take-off and landing high-speed flying fixed wing unmanned aerial vehicle, and meets the urgent requirements of various military varieties on tonnage-level carrier-based unmanned aerial vehicles.

Referring to fig. 1 and 2, fig. 1 is a schematic top view and fig. 2 is a schematic side view of a hybrid electric propulsion system-based vtol tiltrotor aircraft according to an embodiment of the present application. As shown in fig. 1 and 2, the hybrid electric propulsion system-based vtol tilt-wing aircraft includes: the hybrid electric propulsion system comprises a fuselage 1, a front power wing 2, a rear power wing 3 and a hybrid electric propulsion system 9;

the two front power wings 2 are respectively arranged at the front ends of the two sides of the machine body 1, and the front power wings 2 can rotate relative to the machine body 1;

two rear power wings 3 are respectively arranged at the rear ends of two sides of the machine body 1, and the rear power wings 3 can rotate relative to the machine body 1;

the hybrid electric propulsion system 9 is connected to the front power wing 2 and the rear power wing 3, and is configured to drive the front power wing 2 and the rear power wing 3.

In this embodiment, there are two front power wings 2, which are respectively disposed at the front ends of both sides of the fuselage 1 to bear the main propulsion, specifically, the two front power wings 2 are symmetrically disposed at both ends of the fuselage 1 to ensure the force balance of the fuselage 1, so that the aircraft can fly stably, and the front power wings 2 can rotate relative to the fuselage 1 to form tilt power wings, so that the direction of the power provided by the front power wings 2 can be adjusted, when the aircraft needs to take off and land vertically, the direction of the power provided by the front power wings 2 is adjusted to be a vertical direction, so that vertical take-off and landing are completed, when the aircraft needs to take off and land horizontally, the direction of the power provided by the front power wings 2 is adjusted to be a horizontal direction, so that the power is provided for the plane flight of the aircraft, and the resistance of the front power wings 2 can be reduced to reduce the energy consumption and improve the range of the aircraft.

The rear power wings 3 are respectively arranged at the rear ends of two sides of the airplane body 1 to bear auxiliary propulsion, specifically, the two rear power wings 3 are symmetrically arranged at two ends of the airplane body 1 to ensure the stress balance of the airplane body 1 so as to enable the airplane to fly stably, and the rear power wings 3 can rotate relative to the airplane body 1 to form tilting power wings so as to adjust the direction of power provided by the rear power wings 3.

The hybrid electric propulsion system 9 is connected with the front power wing 2 and the rear power wing 3 so as to be able to drive the front power wing 2 and the rear power wing 3, and the hybrid electric propulsion system 9 is able to save energy to improve the range of the aircraft.

Adopt the VTOL power wing aircraft that verts that this application provided based on mix electric propulsion system, first aspect, 1 both sides of fuselage are provided with preceding power wing 2 and back power wing 3 respectively, and preceding power wing 2 and back power wing 3 all can rotate for fuselage 1 to can carry out the regulation of preceding power wing 2 and back power wing 3 according to actual conditions, in order to accomplish the VTOL of aircraft, and reduce the flight resistance of aircraft, in order to improve the voyage of aircraft.

In the second aspect, the hybrid electric propulsion system 9 is connected with the front power wing 2 and the rear power wing 3, and the hybrid electric propulsion system 9 is adopted to drive the front power wing 2 and the rear power wing 3, so that the power distribution is more reasonable, the oil consumption is reduced, and the range of the airplane is improved.

Based on the vertical take-off and landing tilt power wing aircraft of the hybrid electric propulsion system, the application provides the following specific examples, and on the premise of no conflict, the examples can be combined at will to form a new vertical take-off and landing tilt power wing aircraft of the hybrid electric propulsion system. It should be understood that the new hybrid electric propulsion system vtol tilt-wing aircraft, formed by any combination of examples, is intended to fall within the scope of the present application.

With reference to fig. 1 to 3, fig. 3 is a schematic tilted perspective view of a hybrid electric propulsion system-based vtol tilt-wing aircraft according to an embodiment of the present application, in a possible implementation, the hybrid electric propulsion system 9 includes at least a tilting mechanism;

the tilting mechanism is arranged in the machine body 1 and can rotate around the machine body 1;

the tilting mechanism is four, and each tilting mechanism is connected with the front power wing 2 and each rear power wing 3 respectively.

In this embodiment, the hybrid electric propulsion system 9 includes at least the tilting mechanism, the tilting mechanism is disposed inside the fuselage 1, and can rotate around the fuselage 1, and the tilting mechanism has four, and a tilting mechanism is disposed at each of the front power wings 2 and each of the rear power wings 3, and the front power wings 2 and the rear power wings 3 are both connected with the tilting mechanism, so that the tilting mechanism can drive the front power wings 2 and the rear power wings 3 to rotate, and the front power wings 2 and the rear power wings 3 are made to rotate relative to the fuselage 1.

With reference to fig. 1 to 4, fig. 4 is a schematic front view of a vertical take-off and landing tilt-rotor aircraft based on a hybrid electric propulsion system according to an embodiment of the present application, and in a possible implementation, the front power wing 2 and the rear power wing 3 each include: a propeller 4, a support cross wing 5 and a lower semi-ring wing 6;

one side of the lower semi-ring wing 6 is connected with the tilting mechanism;

the supporting transverse wings 5 are connected to the upper parts of the lower semi-ring wings 6;

the propeller 4 is connected to the front end of the support wing 5.

In the present embodiment, each of the front power wing 2 and the rear power wing 3 includes: a propeller 4, a support wing 5 and a lower semi-ring wing 6, wherein the power direction provided by the front power wing 2 and the rear power wing 3 is horizontal direction in the conventional case, and the following structure is oriented in the conventional case, wherein one side of the lower semi-ring wing 6 is connected with a tilting mechanism so that the tilting mechanism can drive the lower semi-ring wing 6 to rotate, the support wing 5 is connected with the upper part of the lower semi-ring wing 6, the propeller 4 is connected with the front end of the support wing 5 so that the support wing 5 can support the propeller 4, specifically, the propeller 4 is connected with the middle part of the support wing 5, the lower semi-ring wing 6 is located at the lower part of the propeller 4, wherein the lower semi-ring wing 6 is a semi-ring wing protruding downwards, when the aircraft is in level flight, the airflow velocity at the upper part of the lower semi-ring wing 6 is much greater than the airflow velocity at the lower part of the lower semi-ring wing 6 due to the uninterrupted rotation of the propeller 4, so that the pressure at the upper part of, the lower half-ring wing 6 is subjected to an upward lift force, so that the load of the aircraft can be increased.

Referring to fig. 1 to 5, fig. 5 is a schematic diagram of a hybrid electric propulsion system of a vertical take-off and landing tilt-rotor aircraft based on a hybrid electric propulsion system according to an embodiment of the present application, in a possible implementation, the hybrid electric propulsion system 9 further includes an engine propulsion system 91, an electric motor propulsion system 92 and a power module 93;

the engine propulsion system 91 and the motor propulsion system 92 are both connected to the power module 93.

In this embodiment, the hybrid electric propulsion system 9 further includes an engine propulsion system 91, a motor propulsion system 92, and a power module 93, wherein the engine propulsion system 91 and the motor propulsion system 92 are connected to the power module 93, and the power module 93 can reasonably distribute the power of the engine propulsion system 91 and the motor propulsion system 92 to save energy.

In one possible embodiment, the engine propulsion system 91 includes an engine 911, a start-and-power-generation-integrated motor 912, an input shaft 913, a transmission shaft 914, and an output shaft 915;

two engines 911 and two starting and power generating integrated motors 912 are provided, each engine 911 is connected with one starting and power generating integrated motor 912, and each starting and power generating integrated motor 912 is connected with the power module 93;

two input shafts 913 are provided, and each of the engines 911 is connected to one of the input shafts 913;

two transmission shafts 914 are provided, and each input shaft 913 is in transmission connection with each transmission shaft 914;

two output shafts 915 are provided, the two output shafts 915 are respectively arranged in the supporting transverse wings 5 of the front power wing 2, and each transmission shaft 914 is respectively in transmission connection with one output shaft 915;

the output shaft 915 is connected to the propeller 4 of the front power wing 2.

In the present embodiment, the engine propulsion system 91 includes an engine 911, a start/power generation integrated motor 912, an input shaft 913, a transmission shaft 914 and an output shaft 915, wherein there are two start/power generation integrated motors 911 and 912, each engine 911 is connected to one start/power generation integrated motor 912, each start/power generation integrated motor 912 is connected to the power module 93, and the power of the engine propulsion system 91 and the motor propulsion system 92 is adjusted by controlling the start/power generation integrated motors 912 through the power module 93.

The input shaft 913 is connected with engine 911, the input shaft 913 stretches out from engine 911 inside, engine 911 drives input shaft 913 to rotate, then drive transmission shaft 914 through input shaft 913 and rotate, and then drive output shaft 915 through transmission shaft 914 and rotate, wherein, each input shaft 913 all is connected with two transmission shaft 914 through the bevel gear transmission, output shaft 915 sets up in the support horizontal wing 5 of preceding power wing 2, the one end of transmission shaft 914 stretches out fuselage 1, stretch into in the support horizontal wing 5, be connected through the bevel gear transmission with output shaft 915, then drive the screw propeller 4 rotation of preceding power wing 2 by output shaft 915.

In a possible embodiment, the starting and generating integrated motor 912 is divided into a plurality of permanent magnet rotors and a plurality of coil stators, the permanent magnet rotors are uniformly distributed on an impeller of a compressor of the engine, the coil stators are uniformly distributed on a diffuser of the engine to form equal-diameter rotors and stators, and the equal-diameter rotors and stators are opposite to each other in the axial direction to form the form of an axial permanent magnet brushless dc motor.

The application relates to switching of multiple working modes, in particular to a ground mode, namely power generation, wherein in the ground mode, an aircraft stays on the ground, and a power generation integrated motor 912 is started to generate power to charge a storage battery 921; a ground mode-sleep mode, in which the aircraft stays on the ground and the integrated power generation motor 912 is started to be in a sleep state; a vertical take-off and landing mode-dormancy mode, in which the full power of the engine 911 is output to the main propeller 4, the storage battery 921 drives the motor of the auxiliary propeller 4 to run at full power, and the starting and power generation integrated motor 912 is in dormancy; cruise mode, in which the thrust of the aircraft is completely provided by the engine 911 and the engine 911 generates electricity to charge the battery 921 by starting the electricity generation integrated motor 912; in the vertical take-off and landing mode, power generation is carried out, in the mode, the engine 911 drives the main propeller 4, the power is generated through the generator, and the generator and the storage battery 921 jointly drive the motor of the auxiliary propeller 4; sixthly, a cruise mode-a dormant mode, wherein the thrust of the aircraft is completely provided by the engine 911, and the power generation integrated motor 912 is started to be in a dormant state; a maneuvering mode-dormancy, in which the engine 911 drives the main propeller 4 by full-power operation, and the storage battery 921 drives the auxiliary propeller 4 to drive the motor to run by full power, so as to provide thrust for the aircraft; eighthly, in the maneuvering mode, the motor 911 runs most of power at full power to drive the main propeller 4, and partial power drives the motor of the auxiliary propeller 4 together with the storage battery 921 through starting the power generation integrated motor 912 to generate power, so that the thrust is provided for the aircraft together; ninthly, in a shutdown mode, the engine 911, the starting and power generation integrated motor 912 and the storage battery 921 do not work at the moment, wherein the main propeller 4 is the propeller 4 of the front power wing 2, and the auxiliary propeller 4 is the propeller 4 of the rear power wing 3. Through the power module, different components are controlled to work under different conditions, so that the power of the engine propulsion system and the power of the motor propulsion system can be reasonably distributed, energy is saved, and the range of the airplane is improved.

In one possible embodiment, the electric motor propulsion system 92 includes a battery 921 and an electric motor 922, the electric motor 922 is electrically connected to the battery 921, and the battery 921 is connected to the power module 93;

the number of the motors 922 is two, the two motors 922 are respectively arranged inside the supporting wings 5 of the rear power wing 3, and the motors 922 are connected with the propellers 4 of the rear power wing 3.

In the present embodiment, the motor propulsion system 92 includes a motor 922 and a battery 921, the motor 922 is electrically connected to the battery 921, the battery 921 is electrically connected to the power module 93, the motor 922 is disposed inside the support lateral wings 5 of the rear power wing 3, the motor 922 is connected to the propeller 4 of the rear power wing 3, and the power module 93 can control the battery 921 to energize the motor 922 so that the motor 922 rotates the propeller 4 of the rear power wing 3.

In one possible embodiment, the tilt mechanism includes a tilt torsion tube, a bearing, a tilt cylinder, and a tilt rocker arm;

the bearing is arranged on one side of the machine body 1;

the tilting torsion tube penetrates through the bearing and the fuselage 1 and is connected with the lower semi-ring wing 6;

one end of the tilting rocker arm is connected with the tilting actuating cylinder, and the other end of the tilting rocker arm is connected to the outer side of the tilting torsion tube;

the tilt cylinder is electrically connected to the power module 93;

the transmission shaft 914 is arranged in the tilting torsion tube, and one end of the transmission shaft 914 extends out of the machine body 1 and is in transmission connection with the output shaft 915.

In the present embodiment, the tilting mechanism includes a tilting torque tube, a bearing, a tilting cylinder and a tilting rocker arm, the tilting torque tube is mounted inside the fuselage 1 through the bearing, specifically, the bearing is mounted on one side of the fuselage 1, and the tilting torque tube passes through the bearing and the fuselage 1 and is connected to the lower half-ring wing 6 so as to be able to drive the entire front power wing 2 or the entire rear power wing 3 to rotate. One end of the tilting rocker arm is connected with the tilting actuating cylinder, the other end of the tilting rocker arm is connected to the outer side of the tilting torque tube, the tilting actuating cylinder is electrically connected with the power module 93, specifically, the tilting rocker arm is hinged with the tilting actuating cylinder, during the vertical take-off and landing, the power module 93 can control the tilting actuating cylinder to work, so that the tilting actuating cylinder is extended to drive the tilting rocker arm to rotate, and further, the tilting torque tube can drive the tilting torque tube to rotate, the tilting torque tube drives the lower semi-ring wing 6 to rotate, the lower semi-ring wing 6 drives the supporting cross wing 5 connected with the lower semi-ring wing 6 to rotate together with the propeller 4, so that the rotating plane of the propeller 4 is superposed with the horizontal plane, so that the propeller 4 can provide the lifting force in the vertical direction, thereby completing the vertical take-off and landing, during the horizontal flight, the power module 93 can control the tilting actuating cylinder to work, so that the tilting actuating cylinder retracts to the original position, thereby, the lower semi-ring, so that the rotation plane of the propeller 4 is perpendicular to the central axis of the fuselage 1, and the propeller 4 provides power in the horizontal direction.

Referring to fig. 6, fig. 6 is another schematic side view of a vertical take-off and landing tilt-rotor aircraft based on a hybrid electric propulsion system according to an embodiment of the present application, in a possible embodiment, the rear ends of two sides of the fuselage 1 are provided with folded horizontal tails 10;

one side of folding back horizontal tail 10 with fuselage 1 rotates and is connected, keeping away from of folding back horizontal tail 10 fuselage 1 one side with back power wing 3 is connected.

In this embodiment, the rear end of fuselage 1 both sides is provided with folding back tail 10, one side of folding back tail 10 rotates with fuselage 1 to be connected, the fuselage 1 one side of keeping away from of folding back tail 10 is connected with back power wing 3, folding back tail can make the focus position of aircraft move backward, thereby make the total resistance of aircraft descend, when the aircraft does not use, can rotate folding back tail 10, make folding back tail 10 upwards fold with back power wing 3 together, thereby can reduce the space occupation of aircraft on the horizontal plane.

In a possible embodiment, the bottom of the fuselage 1 is provided with a landing gear mechanism 8 to facilitate the support of the fuselage 1 during the landing of the aircraft, avoiding damage to the fuselage 1 when it contacts the ground.

In a possible embodiment, the top of the rear end of the fuselage 1 is symmetrically provided with vertical fins 7, and the vertical fins 7 are obliquely arranged with the fuselage 1.

In the embodiment, the vertical tails 7 are symmetrically arranged at the top of the rear end of the fuselage 1, the vertical tails 7 are obliquely arranged with the fuselage 1 and used for keeping the stability of the aircraft in flight and controlling the flight attitude of the aircraft, and two rudders on the double vertical tails 7 bear yawing moment respectively, so that the stress of each rudder is reduced.

In a feasible implementation mode, the aircraft further comprises a scanning imaging and communication radar system, a fire control system and a flight control system, wherein the scanning imaging and communication radar system, the fire control system and the flight control system are all arranged in the aircraft body 1, so that the practical performance of the aircraft is improved.

The vertical take-off and landing tilting power wing aircraft based on the hybrid electric propulsion system has the advantages that the maximum take-off weight is 1200kg, the maximum effective load is 500kg, the maximum dead time is 20 hours, the maximum flying speed is 400km/h, the cruising speed is 350km/h and the maximum range is 3000km, the aircraft can be flexibly switched between a vertical take-off and landing mode and a high-speed level flight mode, and the ratio of the lowest level flight speed to the maximum flying speed reaches 1: 10; the ship has the characteristics of high efficiency, low oil consumption, large load, flexibility, changeability, wide adaptability, convenience in maintenance and the like, can be equipped with various naval vessels, and greatly enriches the use scene.

It should be understood that while the present specification has described preferred embodiments of the present application, additional variations and modifications of those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including the preferred embodiment and all such alterations and modifications as fall within the true scope of the embodiments of the application.

Finally, it should also be noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or terminal that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or terminal. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other like elements in a process, method, article, or terminal that comprises the element.

The vertical take-off and landing tilt-rotor power wing aircraft based on the hybrid electric propulsion system, which is provided by the application, is described in detail above, and specific examples are applied in the description to explain the principle and the implementation manner of the application, and the description of the above embodiments is only used to help understand the method and the core idea of the application; meanwhile, for a person skilled in the art, according to the idea of the present application, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present application.