CN213566465U

CN213566465U - Combined back-propelled variable-pitch autorotation four-rotor aircraft

Info

Publication number: CN213566465U
Application number: CN201920715154.7U
Authority: CN
Inventors: 范磊
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-05-19
Filing date: 2019-05-19
Publication date: 2021-06-29
Anticipated expiration: 2029-05-19

Abstract

The utility model relates to a four rotor crafts of combined type back propulsion displacement rotation, characterized by, fixed wing (2) have been arranged at fuselage (1) middle part, and fuselage (1) back has been arranged and has been arranged back of the body driving force system (6), perpendicular fin (4), horizontal fin (3), has arranged aileron (11) on fixed wing (2), and two sets of main lift rotor group (5) have respectively been arranged in vertical row in fixed wing (2) both ends, but the aircraft configuration slippage undercarriage (9). Through compound flight, the power distribution of four rotor crafts, fixed wing crafts, rotation, the aircraft flight quality is synthesized and is promoted, realizes that the aircraft VTOL, hover, high-speed fly ahead.

Description

Combined back-propelled variable-pitch autorotation four-rotor aircraft

Technical Field

The invention relates to a vertical take-off and landing (VTOL) high-efficiency and high-speed aircraft.

Background

Along with the progress of the related technology, the multi-rotor aircraft has new vitality in recent years, and the existing multi-rotor aircraft is combined with motors, electric regulators and propellers to form the multi-rotor aircraft with different numbers of lift modules. There are also composite multi-rotor aircrafts combining a multi-rotor aircraft and a fixed-wing aircraft.

No matter be many rotor crafts or many rotors of combined type, though current design has the simplicity, lift efficiency has all been sacrificed in its lift module design. The universal characteristics of large load of a paddle disk, large induced power, low lift efficiency, large forward flight resistance, low flight speed, low overload capacity and low disturbance resistance exist. Limited by the control authority of the speed of the blade tip, the blade can only be transported to a micro-miniature machine.

Generally, a plurality of rotor wing machine types can only be driven by electric power and are limited by the existing battery power density, energy density, load, time of flight and the like, which can not meet the requirements of users.

The combined type multi-rotor wing is also limited by the factors, and although fuel power is introduced, the overall efficiency of the aircraft can not be improved and the safety can not be guaranteed due to the problems of efficiency and vibration coupling of the multi-rotor wing lift module.

Disclosure of Invention

The utility model provides a fixed wing 2 is arranged at 1 middle part of combined type rotation four-rotor aircraft, and 1 back of the body has arranged back driving force system 6, vertical tail 4, horizontal tail 3, has arranged aileron 11 on the fixed wing 2, and two sets of main lift rotor group 5 have respectively been arranged to the vertical column in fixed wing 2 both ends, and the undercarriage 9 can be slided away in the aircraft configuration.

The fixed wing 2 arranged in the middle of the fuselage bears the forward flight compensation lift force.

The back of the fuselage 1 is provided with a back propulsion system 6.

The tail part of the machine body is provided with a horizontal tail wing 3 and a vertical tail wing 4.

The main lift rotor set 5 arranged on the fixed wing 2 can be connected with the fixed wing 2 through a folding mechanism 7, and blades 10 are installed on the main lift rotor set 5.

The four pairs of main lift rotor wing groups 5 arranged on the fuselage 1 increase the flying speed along with the application of forward flying power by the back thrust system 6, and the rotor wing driving power comes from the driving force of the main lift rotor wing groups 5 own driving system and the driving force of forward flying incoming flow acting on the rotor wings; on the premise of maintaining the lift force, the fixed wing lift force 2 is increased, the incoming flow driving force is increased, the self driving force is reduced, and the aircraft is in a combined flight mode of a helicopter, a self-rotating rotor aircraft and a fixed wing aircraft; finally, the incoming flow driving force completely replaces the self driving force of the main lifting rotor set 5; the self-driving force is cut off, the rotor wing is in a self-rotating state under the driving of incoming flow, and the aircraft flies forward in a composite mode of the self-rotating rotor wing aircraft and the fixed wing aircraft under the driving of the back propulsion force system 6.

The blades 10 mounted on the main lift rotor set 5 have a variable collective pitch.

The fixed wing 2 can be directly connected with the fuselage 1 or can be connected with the fuselage 1 by installing a fixed wing steering wheel 8.

The main lift rotor set 5 can be fixedly connected to the fixed wing 2, or the main lift rotor set 5 can be folded inwards by 90 degrees after the blades 10 are folded by the folding mechanism 7, and then the fixed wing steering wheel 8 is locked above the airplane body by rotating by 90 degrees.

The aircraft adopts a distributed power design, and the main lift rotor wing group 5 and the back thrust system 6 are driven independently; the device can be driven by full electric power or hybrid power; the full-power drive is powered by the energy storage system, or the power generation system and the energy storage system are powered in a mixed mode; the hybrid power drive is that the main lift rotor set 5 is driven by electric power, the back driving force system 6 is driven by the power of traditional fuel and drives the power generation system to supplement the electric energy to the energy storage system, so as to supplement the electric energy consumption of the main lift rotor set 5 during vertical take-off and landing, hovering and multi-rotor mode cruise; the energy storage system can also adopt a driving system of the main lift rotor set 5 to be designed into a driving and power generation integrated system, and when the aircraft flies in a rotation rotor mode, power is generated to supplement electric energy to the energy storage system.

The invention has the beneficial effects that: the invention adopts a multi-rotor mode, combines the flight principle of an autorotation rotor craft with the flight principle of a fixed wing craft and the flight principle of a multi-rotor craft, adopts a plurality of sets of autorotation rotor systems, designs to optimize the lift force and the forward flight autorotation to be converted into a pneumatic priority, and has the advantages of small blade disc load, small induced power, high lift force efficiency, small forward flight resistance, high overload capacity and strong disturbance resistance. Because the forward flight flies in a composite mode of the autorotation gyroplane and the fixed-wing aircraft, the forward shock waves of the blades and the backward stall are delayed, the high-speed flight can be realized, and simultaneously, because the forward flight of the rotor leads into the autorotation mode, the passive driving rotation is realized, the efficiency of the aircraft is greatly improved, and the noise and the vibration are greatly reduced.

The aircraft combines the special characteristics of flight envelope, adopts distributed power arrangement, and the vertical lift system adopts electric drive, thus realizing the simplicity of the lift module after adopting a plurality of rotors, and being convenient for the switching between the driving rotation and the self-rotation of the rotor system. Because the propulsion system adopts the traditional power drive to get rid of the constraint of the multi-rotor aircraft on the energy density and the power density of the battery.

The aircraft adopts the design of four rotor lift modules in structural design, makes the lift module effectively avoid the fuselage to washing sheltering from of flowing down, effectively improves lift efficiency.

Because the rotor rotation is introduced in the prior flight, the backward stall of the forward and backward shocking waves is overcome, and the aerodynamic characteristics of the aircraft are superior to those of helicopters and multi-rotor aircrafts.

Due to the adoption of the distributed power design, the combination effectively solves the problem that the power requirements of the vertical take-off and landing type and the fixed wing type are not matched under the same load after the two types are combined. The power system can work in a more reasonable and economic power range, and the flying efficiency is greatly improved.

The front flying of the aircraft adopts a composite mode of a self-rotating rotor wing and a fixed wing, so that the aircraft can take off and land by means of the landing gear. The mode of the autorotation gyroplane is unpowered, downslide and short-distance landing can be adopted in flight. Compared with other models, the safety is greatly improved.

The aircraft can be folded and folded, and a smaller space occupation space is realized.

Drawings

FIG. 1 is a side view of a compound back-propelled pitch-variable autorotation quad-rotor aircraft.

Figure 2 composite back-propelled variable pitch autorotation quad-rotor aircraft blade folding view.

FIG. 3 is a folding view of a main lift rotor set of a composite back-propelled variable-pitch autorotation quad-rotor aircraft.

Fig. 4 is a drawing of the composite back-propelled variable-pitch autorotation four-rotor aircraft in a retracted mode for fixing wings and a main lift rotor set.

As shown in fig. 1-4:

1-a fuselage; 2-fixed wings; 3-horizontal tail wing; 4-vertical tail; 5-a main lift rotor set; 6-back driving force system; 7-a folding mechanism; 8-fixed wing steering wheel; 9-a running undercarriage; 10-a blade; 11-aileron.

Detailed Description

The specific implementation is as follows: the combined type flight mode of the fixed wing aircraft and the autorotation four-rotor aircraft is adopted in the embodiment, the fixed wing 2 is arranged on the aircraft body 1, the main lift rotor groups 5 of two sets of longitudinal columns are fixedly arranged on the fixed wing 2, the main lift rotor groups 5 are installed, the blades are installed at intervals of 10, the back propulsion system 6 is installed on the back of the aircraft body, the horizontal tail wing 3 and the vertical tail wing 4 are arranged on the tail of the aircraft body, and the ailerons 11 are arranged on the fixed wing. A slidable undercarriage 9 is arranged on the fuselage 1.

The aircraft power system adopts independent distributed arrangement, and has four sets of main lift rotor group 5 power systems and a back driving force system 6, and the whole aircraft power system can be driven by a full power system or a separate hybrid power. The full electric system can be driven by the energy storage system of the aircraft, or by the direct power supply of the power generation system, or by the mixed power supply of the power generation system and the energy storage system. The hybrid drive adopts a distributed mode: the back driving force system 6 is driven by a traditional fuel oil power system, and the main lifting force rotor set 5 is driven by electric power. The power generation system can be driven by a back driving force system, and the main lifting force rotor wing set 5 can also be designed into a driving and power generation system, wherein the driving motor is used for driving when the main lifting force rotor wing set vertically rises and falls, and the power generation system is used for charging and storing energy to the energy storage system when the main lifting force rotor wing set flies forward and rotates automatically.

When the aircraft vertically takes off, lands and hovers, a multi-rotor aircraft flight and control mode is adopted, and the main lift rotor set 5 bears main lift and main control force. When the aircraft enters into the front flight cruise, the back driving force system 6 starts to start the front thrust, the front flying speed is continuously increased along with the front flying speed, the lift force of the fixed wing 2 is increased, the rotor lift force is gradually unloaded, when the flying speed is higher than the non-speed of the aircraft, the power of the main lift rotor set 5 is cut off, the main lift rotor set 5 is driven to rotate by incoming current, the self-rotating state is achieved, and the aircraft enters into a composite flight mode of the fixed wing aircraft and the autorotation rotor aircraft. The flight main control force is changed into a fixed wing aircraft control mode, and the control of the fixed wing aircraft control mode is controlled by combining the ailerons 11, the vertical tail 4 and the fixed tail 3.

But this aircraft fuselage installs the landing gear 9 that runs additional, when possessing the condition of taking off and landing of running, can take off and land running, and the aircraft is taken off and land running with fixed wing aircraft and the four rotor wing combined type modes of spin this moment. The load efficiency of the mode take-off and landing is larger than that of a vertical take-off and landing mode, and the load efficiency is superior to that of the existing tilting type helicopter type, helicopter type and multi-rotor aircraft type.

Because aircraft main lift rotor group 5 has the ability of rotating under the incoming current, this aircraft still can the spin smooth fall after losing power, has high security performance.

The second concrete implementation: in this embodiment, when the ground space of the machine body is required to be small in occupied ratio for performing a task, a folding mechanism 7 and a fixed wing steering wheel 8 can be additionally arranged.

In this embodiment, the power system, flight mode, and control mode are the same as those of the first embodiment.

The fixed wing 2 of the aircraft is connected with the fuselage through a fixed wing steering wheel 8, two ends of the fixed wing 2 are connected with the main lift rotor wing groups 5 through folding mechanisms 7, and each main lift rotor wing group 5 can be selectively provided with two or three blades 10. When the fixed wing needs to be folded, the blades 10 fold the main lift rotor set 5 inwards for 90 degrees after being folded inwards, the main lift rotor set is folded on one side of the fixed wing 2 to be locked, and the steering wheel 8 of the fixed wing rotates for 90 degrees to meet the requirement of reducing the space occupation ratio for performing tasks.

Claims

1. The utility model provides a four rotor crafts of combined type back of body propulsion displacement rotation, characterized by, fixed wing (2) have been arranged at fuselage (1) middle part, and fuselage (1) back has been arranged back driving force system (6), vertical tail (4), horizontal tail (3), has arranged aileron (11) on fixed wing (2), and two sets of main lift rotor group (5) have respectively been arranged in the vertical column in fixed wing (2) both ends, but the aircraft configuration glides landing gear (9).

2. The aircraft according to claim 1, characterized in that the fixed wings (2) arranged in the middle of the fuselage carry the forward flight compensation lift.

3. The aircraft according to claim 1, characterized in that the fuselage (1) thereof is backed by a back thrust system (6).

4. The aircraft according to claim 1, characterized in that the tail of the fuselage is provided with a horizontal tail (3) and a vertical tail (4).

5. The aircraft according to claim 1, characterized in that the main lift rotor group (5) arranged on the fixed wing (2) is connectable to the fixed wing (2) by means of a folding mechanism (7), the main lift rotor group (5) being provided with blades (10).

6. The aircraft according to claim 1, characterized in that the fuselage (1) of the aircraft is provided with four pairs of main lift rotor sets (5), the flying speed increases with the application of forward flying power by the back thrust system (6), and the rotor driving power comes from the driving force of the main lift rotor sets (5) with driving system and the driving force of forward flying current acting on the rotors; on the premise of maintaining the lift force, the lift force of the fixed wing (2) is increased, the incoming flow driving force is increased, the self-driving force is reduced, and the aircraft is in a combined flight mode of a helicopter, a self-rotating rotor aircraft and a fixed wing aircraft; finally, the incoming flow driving force completely replaces the self driving force of the main lifting rotor set (5); the self-driving force is cut off, the rotor wing is in a self-rotating state under the driving of incoming flow, and the aircraft flies forward in a composite mode of a self-rotating rotor aircraft and a fixed wing aircraft under the driving of a back propulsion force system (6).

7. The aircraft according to claim 1, characterized in that the blades (10) mounted on the main lift rotor group (5) have a variable collective pitch.

8. The aircraft according to claim 1, characterized in that the fixed wing (2) can be connected directly to the fuselage (1) or can be connected to the fuselage (1) by mounting a fixed wing steering wheel (8).

9. The aircraft according to claim 1, characterized in that the main lift rotor set (5) can be fixedly connected to the fixed wing (2) or can be folded by 90 degrees inwards after the blades (10) are folded by the folding mechanism (7), and then the fixed wing steering wheel (8) is locked above the fuselage by rotating 90 degrees.

10. The aircraft of claim 1, characterized in that the aircraft adopts a distributed power design, and the main lift rotor set (5) and the back thrust system (6) are driven independently; the device can be driven by full electric power or hybrid power; the full-power drive is powered by the energy storage system, or the power generation system and the energy storage system are powered in a mixed mode; the hybrid power drive is that the main lift rotor set (5) is driven by electric power, the back driving force system (6) is driven by the power of traditional fuel and drives the power generation system to supplement the electric energy to the energy storage system, so as to supplement the electric energy consumption of the main lift rotor set (5) during vertical take-off and landing, hovering and multi-rotor mode cruise; the energy storage system can also adopt a driving system of the main lift rotor set (5) to be designed into a driving and power generation integrated system, and when the aircraft flies in a self-rotation rotor mode, power is generated to supplement the energy storage system with electric energy.