CN213566461U

CN213566461U - Combined tail-propelled fixed-distance autorotation four-rotor aircraft

Info

Publication number: CN213566461U
Application number: CN201920715139.2U
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 tail propulsion distance rotation, fixed wing (2) have been arranged at fuselage (1) middle part, tail driving force system (6), perpendicular fin (4), horizontal fin (3) have been arranged to the tail, aileron (11) have been arranged on fixed wing (2), two sets of main lift rotor group (5) have respectively been arranged to fixed wing (2) both ends vertical column, paddle (10) cycle distance that arrange on main lift rotor group (5) is fixed, but the aircraft configuration glides 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 tail-propelled fixed-distance 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 four rotor crafts of combined type tail propulsion distance rotation, fixed wing 2 has been arranged at fuselage 1 middle part, and tail propulsion system 6, vertical tail 4, horizontal tail 3 have been arranged to the tail, have arranged aileron 11 on the fixed wing 2, and two sets of main lift rotor group 5 have respectively been arranged in tandem at fixed wing 2 both ends, and the paddle 10 cycle pitch that arranges on the main lift rotor group 5 is fixed, but the aircraft configuration slumping undercarriage 9.

The aircraft of claim 1, wherein the fixed wing 2 arranged in the middle of the fuselage takes on the forward flight compensation lift.

The aircraft according to claim 1, wherein the main lift rotor set 5 disposed on the fixed wing 2 is fixedly connected to the fixed wing 2, and comprises a folding mechanism 7 connected to the fixed wing 2, and the main lift rotor set 5 is provided with blades 10.

The aircraft of claim 1, when taking off, landing and hovering vertically, the four pairs of main lift rotor groups (5) bear the vertical take-off, landing and hovering lift; when flying forward, the tail driving force system (6) undertakes the power of flying forward; four pairs of main lift rotor groups (5) in the forward flight and the fixed wings (2) jointly keep the lift of the aircraft; the driving, the stopping and the rotating speed change of the power system are utilized to realize the driving and the rotation of the main lift rotor wing set (5) and the conversion of the flight mode.

The aircraft of claim 1, wherein the fixed wing 2 is directly connected to the fuselage 1, including by mounting a fixed wing steering wheel 8 to the fuselage 1.

The aircraft of claim 1 wherein the main lift rotor assembly 5 is fixedly attached to the fixed wing, including folding the main lift rotor assembly 5 inwardly by 90 degrees after the blades 10 are folded by the folding mechanism 7, and then locking the fixed wing steering wheel 8 to rotate by 90 degrees above the fuselage.

According to the claim 1, the aircraft adopts a distributed power design, the main lift rotor group 5 and the tail thrust system 6 are driven independently; driven by full electric power, including 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 wing set 5 is driven by electric power, the tail propulsion 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 wing set 5 during vertical take-off and landing, hovering and multi-rotor wing cruise; the energy consumption compensation of the energy storage system comprises the step of designing a driving system of a main lift rotor set 5 into a driving and power generation integrated system, and generating power to compensate the energy storage system with the power when the aircraft flies in a rotation rotor mode.

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

Figure 1 is a side view of a compound tail-propelled fixed-pitch spinning quad-rotor aircraft.

FIG. 2 is a folded view of a composite aft-propulsion fixed-pitch spinning quad-rotor aircraft blade.

FIG. 3 shows a folding view of a main lift rotor set of a combined type tail-propelled fixed-pitch autorotation quad-rotor aircraft.

FIG. 4 is a diagram of a fixed wing and a main lift rotor set of a combined type tail propulsion fixed-distance autorotation four-rotor aircraft.

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-tail propulsion 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 characterized in that the fixed wing 2 is arranged on the aircraft body 1, two sets of main lift rotor sets 5 in longitudinal rows are fixedly arranged on the fixed wing 2, the rotor sets 5 are installed, blades are installed at intervals of 10, a tail propulsion system 6 is installed at the tail of the aircraft body, a horizontal tail wing 3 and a vertical tail wing 4 are arranged at the tail of the aircraft body, and 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 tail propulsion 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 tail propulsion system 6 is driven by a traditional fuel oil power system, and the main lift rotor set 5 is driven by electric power. The power generation system can be driven by a tail driving force system, and the main lifting 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 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 rotor wing set flies and rotates forwards.

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 gets into and flies to cruise, tail propulsion system 6 begins to start the thrust before, and along with the continuous increase of speed that flies in the front, 2 lift lifts of fixed wing, uninstalls rotor lift gradually, when the speed of flight is greater than the aircraft and loses speed, breaks off main lift rotor group 5 power, and main lift rotor group 5 is driven by the incoming current and rotates, gets into autogyration state, and the aircraft gets into fixed wing aircraft and the compound flight mode of rotation gyroplane. 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 fin 4 and the fixed tail fin 3.

The aircraft body is additionally provided with a running undercarriage 9, and when running take-off and landing conditions are met, the aircraft can run and take-off and landing, and at the moment, the aircraft runs and takes off and landing in a fixed wing aircraft and self-rotating four-rotor combined mode. 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 main lift rotor wing needs to be folded, the blades 10 fold the main lift rotor wing group 5 inwards for 90 degrees and fold the main lift rotor wing group 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 a task.

Claims

1. The utility model provides a four rotor crafts of combined type tail propulsion distance rotation, fuselage (1) middle part has arranged fixed wing (2), tail thrust system (6) have been arranged to the tail, perpendicular fin (4), horizontal fin (3), aileron (11) have been arranged on fixed wing (2), two sets of main lift rotor group (5) have respectively been arranged to fixed wing (2) both ends vertical column, paddle (10) the cycle pitch of arranging on main lift rotor group (5) is fixed, but the aircraft configuration sliding undercarriage (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 main lift rotor group (5) arranged on the fixed wing (2) is fixedly connected to the fixed wing (2), including being connected to the fixed wing (2) by a folding mechanism (7).

4. The aircraft of claim 1, wherein when taking off and landing vertically and hovering, the four pairs of main lift rotor groups (5) bear the lift force of taking off and landing vertically and hovering; when flying forward, the tail driving force system (6) undertakes the power of flying forward; four pairs of main lift rotor groups (5) in the forward flight and the fixed wings (2) jointly keep the lift of the aircraft; the driving, the stopping and the rotating speed change of the power system are utilized to realize the driving and the rotation of the main lift rotor wing set (5) and the conversion of the flight mode. .

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

6. The aircraft of claim 1, characterized in that the main lift rotor set (5) is fixedly connected to the fixed wing, and comprises a folding mechanism (7) which can fold the main lift rotor set (5) inwards for 90 degrees after the blades (10) are folded, and then a fixed wing steering wheel (8) rotates for 90 degrees and is locked above the fuselage.

7. The aircraft of claim 1, wherein the aircraft is of a distributed power design, and the main lift rotor set (5) and the tail thrust system (6) are driven independently; driven by full electric power, including 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 wing set (5) is driven by electric power, the tail propulsion system (6) is driven by the traditional fuel power 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 wing set (5) during vertical take-off and landing, hovering and multi-rotor wing mode cruise; the energy consumption compensation of the energy storage system comprises the steps that a driving system of a main lift rotor set (5) is designed into a driving and power generation integrated system, and power is generated to compensate the energy of the energy storage system when the aircraft flies in a self-rotation rotor mode.