CN220743351U - Fixed wing and tandem rotor wing composite aircraft - Google Patents

Abstract

The utility model belongs to the technical field of aviation aircrafts, and discloses a fixed wing and tandem rotor wing composite aircraft, which consists of an airframe, fixed wings, a flight control system, a power and distribution system, a propeller, task equipment and the like.

Description

Fixed wing and tandem rotor wing composite aircraft

Technical Field

The utility model belongs to the technical field of aviation aircrafts, and particularly relates to a fixed wing and tandem rotor wing complex aircraft.

Background

Aircraft have been widely used for inspection, measurement, fire protection, transportation, marine monitoring, some military applications, and the like. Most of the prior fixed-wing aeroplanes have better cruising flight economy, but do not have a vertical take-off and landing function, and are particularly limited in application in narrow places such as ship deck platforms, mountains, islands and the like; the helicopter has the functions of convenient vertical take-off and landing and hovering, but needs a high-power engine, has short stand-off time, less endurance and poor cruising flight economy, so that the problem is solved by a fixed wing aircraft with good economical performance, most of small aircraft with vertical take-off and landing functions currently adopt a power distribution mode of hybrid oil and electricity, the vertical take-off and landing is solved by an electric rotor, the oil-driven engine finishes flat flight, the motor power is small, the load is low, only the helicopter is suitable for a miniature aircraft, the fuel power and a battery power system cannot be mutually converted in the hybrid oil and electricity system, both power systems must exist, the comprehensive weight of the power system is certainly increased, and the effective load of the aircraft is greatly reduced.

The single rotor aircraft not only increases the body weight, reduces the payload, but also sacrifices a portion of the energy due to the need for tail rotor reversal to counteract the reactive torque.

The diameter of the propeller blades of the horizontal type tiltrotor aircraft is limited, the propeller blades are close to the middle of the aircraft body, the generated vortex seriously affects the aerodynamic performance of the aircraft body, such as a 'hawk' tiltrotor aircraft V-22 aircraft, a flat wing part in a tilting force short wing structure can generate a large attack angle in the tilting process to generate instability, the flying safety is affected, the flying state is extremely unstable especially when the flying posture is changed (such as steering, climbing, landing and the like), the accidents are more, and the practice proves that the horizontal type tiltrotor layout is not as good as the longitudinal type rotor wing stability.

Therefore, the development of a fixed wing and tandem rotor composite aircraft capable of carrying large loads is a problem that needs to be solved by those skilled in the art.

Disclosure of Invention

In order to solve the problems in the background technology, the utility model provides a fixed wing and tandem rotor wing complex aircraft and a flying power conversion method, wherein:

a fixed wing and tandem rotor wing composite aircraft comprises an airframe structure 1, a flight control system 4, a power and distribution system 3, a propeller 5, task equipment 7, an energy storage and electric power distribution system and the like; the machine body structure consists of a machine body 1-1, a machine head 1-2, a machine tail 1-3, a fixed wing 2 and a landing gear 6; the propeller 5 consists of a tandem rotor group 5-1 and a horizontal propeller 5-2, the tandem rotor group 5-1 consists of rotor blades 5-1-1, a rotor shaft 5-1-2 and a rotor group tower seat 5-1-3, the tandem rotor group 5-1 in the direction of a nose 1-2 is called a front tandem rotor group 5-1-A, and the tandem rotor group 5-1 in the direction of a tail 1-3 is called a rear tandem rotor group 5-1-B; at least one column type rotor wing group 5-1 is arranged on the machine body, the column type rotor wing groups 5-1 are arranged in pairs, and each pair of the column type rotor wing groups has the same structure and synchronously rotates but has opposite rotation directions; the fixed wing 2 is arranged in the middle of the fuselage, the fixed wing 2 consists of a fixed wing main body 2-1 and auxiliary equipment, and a fixed wing aileron and elevator 2-1-2 is arranged on a fixed wing main structure 2-1-1 of the fixed wing main body 2-1; a horizontal propeller 5-2 is arranged on the machine body structure 1; the horizontal propeller 5-2 is divided into a horizontal propeller 5-2-1 and a vertical horizontal propeller 5-2-2; the power system of the tandem rotor set 5-1 and the power system of the horizontal propeller 5-2 are the same, and the power conversion of the tandem rotor set 5-1 and the horizontal propeller 5-2 is completed by the flight control system 4 through the power and distribution system 3.

The energy storage part of the energy storage and power distribution system is divided into an engine fuel reserve and a storage battery electric energy reserve, wherein the power distribution system comprises an aircraft whole electric appliance power supply, an engine starting motor 3-2 power supply, a generator 3-5 for charging the storage battery, a power system fuel conveying device power supply, an on-board task device 7 power supply and the like.

Furthermore, the attack angle of the tandem rotor blade paddles 5-1-1 can be adjusted in positive and negative angles through the flapping paddles; the bottom planes of the column type rotor shafts 5-1-2 and the tower seats 5-1-3 of the installation rotor groups can be subjected to inclination adjustment in any direction, and the inclination angle of the inclination adjustment is not larger than the minimum safety distance between the maximum deformation of the whole rotor disk of the rotor in working and non-working states and the machine body 1 and adjacent airborne equipment 7; the arrangement ensures that the tandem rotor group 5-1 can be adjusted to the working state of the rotor in the working state of the transverse horizontal propeller 5-2-1 or the longitudinal horizontal propeller 5-2-2 of the aircraft, and the generated lift force is beneficial to the safety and reliability of the flight and cannot interfere with the adjacent machine body and airborne equipment.

Further, the horizontal propellers 5-2-1 are transversely distributed on two sides of the machine body 1-1, and the longitudinal horizontal propellers 5-2-2 are longitudinally distributed on the machine head 1-2 or the machine tail 1-3; the horizontal left propellers 5-2-1-1 and the horizontal right propellers 5-2-1-2 which are transversely distributed on two sides of the machine body 1-1 are beneficial to improving the horizontal flying speed and the practical limit, are symmetrically arranged on two sides of the machine body 1-1 respectively, have the same specification and model, have opposite rotation directions and are used for mutually counteracting the torque generated by each, are distributed in front of the fixed wing and are used for generating tensile force, and the thrust is generated behind the fixed wing, and can also be in a multi-group symmetrical layout;

furthermore, the machine head 1-2 or the machine tail 1-3 is provided with a longitudinal horizontal head propeller 5-2-2-1 and a longitudinal horizontal tail propeller 5-2-2-2, and a single-paddle layout is generally adopted, so that the economic cruising speed is improved, the air-leaving time is improved, the voyage is prolonged, the machine head 1-2 is provided with the longitudinal horizontal head propeller 5-2-2-1 to generate pulling force, and the machine tail 1-3 is provided with the longitudinal horizontal tail propeller 5-2-2-2 to generate pushing force;

the fixed wing main body 2-1 consists of a fixed wing main structure 2-1-1 and a fixed wing aileron and elevator 2-1-2, a fixed wing hanging frame 2-1-3 is arranged below the fixed wing main structure 2-1, a fixed wing tip elevation 2-1-4 is arranged outside the fixed wing main body 2-1, and a fixed wing rudder 2-1-5 is arranged on the fixed wing tip elevation 2-1-4.

The fixed wing tip elevation 2-1-4 can be of various shapes, and the fixed wing rudder 2-1-5 is arranged on the fixed wing tip elevation 2-1-4 to solve the problem of airplane heading maneuvering performance, and the layout is far away from the airplane body, so that the moment is increased, and the influence of the wake flow of the control surface on the aerodynamic performance of the airplane body is reduced; the fixed wing hanging frames 2-1-3 are arranged below the fixed wing main structure 2-1-1 so as to facilitate the external hanging of various task devices 7; the fixed wing tip elevation 2-1-4 can be arranged in an upturned mode or in a turned-down mode, and can penetrate through the wing surface of the fixed wing main structure 2-1-1 to form a cross shape, and the position of the fixed wing tip elevation 2-1-4 can be flexibly distributed at the end part of the fixed wing 2;

furthermore, the outer wing part of the fixed wing 2 is designed into an assembled folding wing main body 2-2, and the folding wing main body 2-2 ensures that the aircraft base occupies small space, and the advantages of the aircraft base can be reflected particularly when the aircraft base is stored; an elevator 2-2-2 is arranged on a folding wing main structure 2-2-1 of a folding wing main body 2-2, a folding wing tip elevation 2-2-3 is arranged on the outer side of the folding wing main body 2-2, and a rudder 2-2-4 is arranged on the folding wing tip elevation 2-2-3; a folding wing hanging frame 2-2-5 is arranged below the folding wing main structure 2-2-1; the elevators 2-2-2 and the rudders 2-2-4 are concentrated on the folding wing main body 2-2, so that the layout of a flight control circuit is facilitated, and the reliability of the maneuvering performance of the aircraft is improved; the combined connection mode and the folding direction of the machine body 1-1, the fixed wing 2 and the folding wing main body 2-2 can be flexibly designed according to actual working conditions, for example, the folding wing main body 2-2 can be turned up or down, and can also be rotated back and forth to narrow;

furthermore, the lift force part of the fixed wing 2 is affected by the air flow generated by the tandem rotor wing group 5-1 to be hollowed out. Because the diameter of the longitudinal rotor wing group 5-1 is larger, the rotor wing blade 5-1-1 rotates to have an overlapping part on the fixed wing 2, so that the air flow generated by the rotor wing blade 5-1-1 can influence the lift force of the fixed wing 2, the difficulty can be solved by carrying out partial hollow processing on the fixed wing 2 of the air flow interference part of the rotor wing blade 5-1-1 and the fixed wing to reduce the lift force loss of the fixed wing 2, and the hydrodynamic performance of the composite wing system caused by mutual interference is improved;

furthermore, the flight control system is provided with a power starting control line 4-1, a power control line 4-2, an electric power input/output control line 4-3, a power clutch control line 4-4 and a power conversion control line 4-5, and the special functional layouts are arranged for effectively controlling the power conversion of the vertical propeller column type rotor wing group 5-1 and the horizontal propeller 5-2;

furthermore, the power and distribution system 3 consists of an engine main body 3-1, an engine starting motor 3-2, an engine power controller 3-3, an engine clutch 3-4, a generator 3-5, a gearbox 3-6 and other related devices, the operation of the devices is controlled by the flight control system 4, and the design of the combination is a necessary condition for realizing the power conversion of the vertical propeller tandem rotor group 5-1 and the horizontal propeller 5-2;

further, the gearbox 3-6 is composed of a speed change gearbox 3-6-1, a power input shaft 3-6-2, a power output shaft 3-6-3 and a gear shifting controller group 3-6-4; the power output shaft 3-6-3 is provided with a combination mode of a rotor output shaft 3-6-3-1 and a transverse horizontal thrust output shaft 3-6-3-2;

further, the gearbox 3-6 is composed of a speed change gearbox 3-6-1, a power input shaft 3-6-2, a power output shaft 3-6-3 and a gear shifting controller 3-6-4; the power output shaft 3-6-3 is provided with a rotor output shaft 3-6-3-1 and a longitudinal head-tail output shaft 3-6-3-3 in a combined mode;

as shown in the figure, the power input of the device can be synchronously supported by multipath collection, the power output of the device can also be multipath output, so that the device is convenient to adapt to the propellers with different rotation speed ratios, and the power output shaft is connected with a propeller shaft through a coupler;

further, the landing gear selects a wheel landing gear 6-1, a sled landing gear 6-2 and a pontoon landing gear 6-3 according to the requirement; the wheel type landing gear 6-1 is suitable for the conditions of an organic runway or short-distance landing, further saves oil consumption and increases endurance; the sled undercarriage 6-2 is more suitable for taking off and landing on carrier-borne, small-platform, narrow zone and field complex terrain; the pontoon landing gear 6-3 is suitable for the surface lifting of oceans, lakes, reservoirs and marshes;

furthermore, the wheel type landing gear 6-1 is composed of a landing gear support 6-1-1, universal wheels 6-1-2 and a landing gear aileron 6-1-3, wherein the upper part of the landing gear support 6-1-1 is arranged on the machine body 1-1, the universal wheels 6-1-2 are arranged at the bottom of the landing gear support, so that the landing gear is convenient for the airplane to take off, land and run, and the landing gear aileron 6-1-3 is arranged in the middle part of the landing gear support 6-1 and can be used for controlling deflection and resetting of a control surface so as to improve the maneuvering performance of the airplane; a brake device is arranged on the universal wheel 6-1-2;

furthermore, the integrated antenna housing 8 is arranged on the machine body, and a multi-band receiving and transmitting antenna is arranged in the integrated antenna housing, so that multi-band measurement can be realized, and the integrated antenna housing can also be used as an electronic countermeasure transmitting platform; the comprehensive radome 8 consists of a radome base 8-1, a radome cabin 8-2 and a radome inspection port 8-3, and is convenient to install and overhaul;

furthermore, the integrated radome 8 is arranged on the plane body, the top of the integrated radome is in a mushroom-shaped circular structure, the bottom of the integrated radome is flat and protrudes, and the integrated radome can generate lifting force when the plane flies flatly, so that the integrated radome is beneficial to the stability of flying and saves oil consumption;

furthermore, the machine head 1-2 or the machine tail 1-3 is of a multi-sphere structure, and the embedded multi-degree-of-freedom task platform 7 is arranged in the machine head, so that the special structures of the machine head 1-2 and the machine tail 1-3 can be fully utilized to realize three-dimensional scanning detection, and meanwhile, the wind resistance of the platform outside the machine body 1 is reduced;

furthermore, the machine body 1-1 is provided with the strip-shaped cabin 1-4 and the barrel cabin 1-5, and the arrangement of the cabin is beneficial to storing task equipment with strip-shaped, round and cylindrical structures, is convenient for flying balance weight and reduces flying operation difficulty caused by unstable gravity center; the large-scale conveyor is also provided with cabin doors 1-6; and the cabin windows 1-7 are convenient for the internal assembly, disassembly and maintenance.

The beneficial effects achieved by the utility model are as follows:

the utility model provides a fixed wing and tandem rotor wing composite aircraft, which fully utilizes the advantage of high load stability of the tandem rotor wing aircraft to carry out scientific and practical improvement, the tandem rotor wings are arranged in pairs, each pair of the tandem rotor wings are identical in structure and synchronously rotate, but the rotation directions are opposite, the counter-torque is naturally counteracted by the counter-rotation of the two paired rotor wings, the diameter of each two adjacent rotor wings can be increased through the arrangement of the height difference of the rotor wing tower seats so as to improve larger lift force, a plurality of groups of rotor wing structure layout can be selected to obtain larger lift force, the effective load and wind resistance level are increased, and the flight actions such as vertical take-off and landing, climbing, hovering, steering, low-speed flight and the like of the aircraft can be completed according to the flight principle characteristics of the rotor wing basic structure;

secondly, the aerodynamic layout of the aircraft is improved by adding the fixed wings on the aircraft body, so that the vertical pulling force of the rotor wing is reduced due to the lifting force generated by the fixed wings in the forward flight process, the rotor wing can finish the flight task with low power, the fuel is saved, and the air retention time and the endurance are greatly improved; after the fixed wings are added in the middle of the engine body, the structural reinforcement is carried out at the weakest part of the engine body (the front end and the rear end of the general tandem rotorcraft structure are both pulled upwards, and the middle part of the general tandem rotorcraft structure sags), so that the overall structural strength of the engine body is improved, particularly the bending resistance and torsion resistance are greatly improved, and the overload capacity of the engine body is greatly improved; the horizontal propeller is arranged on the transverse fixed wing or at the head and the tail of the longitudinal direction, the power conversion between the rotor engine power system and the horizontal propeller is realized by utilizing the flight control system, the aircraft is converted into the flight state of the fixed wing aircraft, and the fixed wing aircraft has higher flight speed and practical limit after conversion because the power of the rotor aircraft is much higher than that of the fixed wing aircraft with equal weight and the oil consumption is naturally much higher, so that the air retention time and the flight range are also increased in the economic navigational speed state, and the flight performance index of the aircraft is also greatly improved; the air flow generated by the rotor wing affects the lift force part of the fixed wing and is compensated, and the integral fluid dynamic performance of the aircraft with the composite wing structure is improved by hollowing out the overlapped part of the fixed wing and the rotor wing.

Thirdly, the rotor power system and the power system of the horizontal propeller use one set of power system, so that the weight of the coexisting multiple power systems can be reduced, and the task load is increased; the flight control system realizes the free conversion of the rotor power and the horizontal propeller power through special control equipment, and the system opens a new way for the multipurpose aviation power in the future.

Fourth, the utility model has fused the quality of the rotor glider, have good low-altitude performance and safe reliability, in the controlled rotary working condition of the power of the tandem rotor, its rotor blade attack angle is positive angle, after the power of the rotor is converted into the power of the horizontal propeller, the tandem rotor is in the free rotary working condition in the neutral gear, adjust the rotor blade attack angle to the negative angle (pitch of the rotor reduces to the minus value), adjust the axial backward tilt of the rotor, then the tandem rotor has become the rotorcraft, the rotor can produce very big lift in the forward flight, have improved the flight security performance and economy performance of the aircraft greatly again, after the aircraft breaks down in the air or the short power disappears, can carry on the short-distance glide again under the dual lift condition of rotorcraft and fixed wing, this is the advantage that neither the mere fixed wing, the helicopter possesses, open up the new aerodynamic layout for the aviation aircraft too, will influence the innovative aircraft and innovated aircraft.

The utility model overcomes the defects that the existing fixed-wing aircraft cannot take off and land vertically, the helicopter has short leaving time and large oil consumption, is uneconomical, has small oil-electricity hybrid power load and the like, and simultaneously meets the advantages that the fixed-wing aircraft can be taken as the helicopter to complete vertical take-off and land and hover, can be taken as the fixed-wing aircraft to take off and land at a short distance and execute long-endurance flight, can be taken as the rotorcraft to take off and land at a low airspace, simultaneously improves the stability and wind resistance of the aircraft flight, is suitable for taking off and land, hovering, flying and the like in various scenes, such as vertical take-off and landing of ships and offshore platforms, short take-off and landing of island runways and the like, greatly improves the loading capacity, comprehensively improves the safety reliability and economic performance of the aircraft, and is more suitable for executing various flight tasks, especially complex military tasks.

Drawings

FIG. 1 is a schematic view of a rotor and tail rotor assembly of the present utility model;

FIG. 2 is a schematic view of a rotor and lateral thrust structure combination of the present utility model;

FIG. 3 is a schematic view of the bottom structural arrangement of the present utility model;

FIG. 4 is a schematic representation of the utility model as applied to a water-based take-off and landing aircraft;

FIG. 5 is a sample plan of the utility model as applied to an early warning aircraft;

FIG. 6 is a schematic diagram of a power distribution system according to the present utility model;

FIG. 7 is a schematic diagram of the power conversion control of the present utility model;

figure 8 is a schematic illustration of tandem dual rotor flight operation;

fig. 9 is a schematic view of the flying operation state of the fixed wing.

Reference numerals in the drawings:

a machine body structure 1; a fuselage 1-1; 1-2 parts of a machine head; tail 1-3; 1-4 of bar-shaped cabins; 1-5 parts of barrel cabin; cabin doors 1-6; cabin windows 1-7;

a fixed wing 2; a fixed wing main body 2-1; a fixed wing main structure 2-1-1; fixed wing aileron and elevator 2-1-2; 2-1-3 of fixed wing hangers; 2-1-4 of wing tip elevation of fixed wing; 2-1-5 of fixed wing rudders; a folding wing main body 2-2; a folding wing main structure 2-2-1; 2-2-2 of folding wing elevators; 2-2-3 of folding wing tip elevation; 2-2-4 of folding wing rudder; 2-2-5 of folding wing hanging frames;

an engine 3; an engine block 3-1; an engine start motor 3-2; an engine power controller 3-3; engine clutches 3-4; 3-5 of a generator; 3-6 parts of a gearbox; a speed change gear box 3-6-1; a power input shaft 3-6-2; 3-6-3 parts of a power output shaft; rotor power take-off 3-6-3-1; the output shaft 3-6-3-2 of the horizontal propeller; the output shaft of the longitudinal head-tail propeller is 3-6-3-3; power conversion shift controller 3-6-4;

a flight control system 4; a power start control line 4-1; a power control line 4-2; a power input/output control line 4-3; a power clutch control line 4-4; power conversion control line 4-5;

a propeller 5; tandem rotor set 5-1; rotor blade 5-1-1, rotor shaft 5-1-2, rotor set tower 5-1-3, front tandem rotor set 5-1-A; rear tandem rotor set 5-1-B; a horizontal propeller 5-2; a horizontal pusher 5-2-1, a horizontal left pusher 5-2-1-1; a transverse horizontal right propeller 5-2-1-2; a longitudinal horizontal propeller 5-2-2; a longitudinal horizontal first propeller 5-2-2-1; a longitudinal horizontal tail propeller 5-2-2-2;

landing gear 6; wheel landing gear 6-1; landing gear supports 6-1-1; 6-1-2 of universal wheels; landing gear ailerons 6-1-3; ski landing gear 6-2; buoy landing gear 6-3;

a task device 7;

a radome 8; a radome base 8-1; radome cabin 8-2; radome inspection port 8-3.

Detailed Description

The embodiments of the present utility model will be described more fully hereinafter with reference to the accompanying drawings, in which the embodiments of the present utility model are shown by way of illustration only, and the utility model is not limited to the embodiments of the present utility model, but other embodiments of the present utility model will be apparent to those skilled in the art without making any inventive effort.

Referring to fig. 1-9, the utility model provides a fixed wing and tandem rotor wing composite aircraft, which comprises an airframe structure 1, a flight control system 4, a power and distribution system 3, a propeller 5, task equipment 7 and the like; the machine body structure consists of a machine body 1-1, a machine head 1-2, a machine tail 1-3, a fixed wing 2 and a landing gear 6; the propeller 5 consists of a tandem rotor group 5-1 and a horizontal propeller 5-2, the tandem rotor group 5-1 consists of rotor blades 5-1-1, a rotor shaft 5-1-2 and a rotor group tower seat 5-1-3, the tandem rotor group 5-1 in the direction of a nose 1-2 is called a front tandem rotor group 5-1-A, and the tandem rotor group 5-1 in the direction of a tail 1-3 is called a rear tandem rotor group 5-1-B; at least one group of tandem rotor wing groups 5-1 are arranged on the machine body, the tandem rotor wing groups 5-1 are arranged in pairs, and each pair of the tandem rotor wing groups has the same structure, synchronously rotates and has opposite rotation directions; the fixed wing 2 is arranged in the middle of the fuselage and is provided with a fixed wing main body 2-1, and the fixed wing main body 2-1 is provided with a fixed wing main structure 2-1-1, a fixed wing aileron and elevator 2-1-2 and a fixed wing hanging frame 2-1-3; the horizontal propeller 5-2 is arranged on the machine body structure 1, and the horizontal propeller 5-2 is divided into a horizontal propeller 5-2-1 and a longitudinal horizontal propeller 5-2-2 according to the layout; the power system of the tandem rotor set 5-1 and the power system of the horizontal propeller 5-2 are the same, and the power conversion of the tandem rotor set 5-1 and the horizontal propeller 5-2 is completed by the flight control system 4 through the power and distribution system 3.

The attack angle of the rotor blade oar 5-1-1 can be adjusted in positive and negative angles through the flapping oar; the rotor shaft 5-1-2 and the bottom plane of the tower seat 5-1-3 for installing the rotor group can be subjected to any direction inclination adjustment, and the inclination angle of the inclination adjustment is not larger than the minimum safety distance between the maximum deformation of the whole rotor disk of the rotor and the machine body 1 and the adjacent airborne equipment 7 in working and non-working states; the arrangement ensures that the tandem rotor group 5-1 can be adjusted to the working state of the rotor in the working state of the horizontal propeller 5-2, the generated lifting force is beneficial to the safety and reliability of the flight, and the lifting force cannot interfere with the adjacent machine body and airborne equipment.

The horizontal propellers 5-2-1 are transversely distributed on two sides of the machine body 1-1, and the longitudinal horizontal propellers 5-2-2 are longitudinally distributed on the machine head 1-2 or the machine tail 1-3; the horizontal left propellers 5-2-1-1 and the horizontal right propellers 5-2-1-2 which are transversely distributed on two sides of the machine body 1-1 are beneficial to improving the flat flight speed and practical rising limit, the two sides of the machine body 1-1 are symmetrically arranged respectively, the specifications and the models are the same, the rotation directions are opposite, the rotation directions are used for mutually canceling the torque generated respectively, the tension force is generated in front of the fixed wing, the thrust force is generated behind the fixed wing, and the multiple groups of symmetrical arrangements are also possible.

In the structure of the fixed wing 2, the lift force part of the fixed wing 2 is hollowed out due to the influence of the air flow generated by the rotor wing, and the rotor wing has a larger diameter, and the rotor wing blade 5-1-1 rotates to have an overlapped part on the fixed wing 2, so that the lift force of the fixed wing 2 can be influenced by the air flow generated by the rotor wing blade 5-1-1.

The machine head 1-2 or the machine tail 1-3 is provided with a longitudinal horizontal head propeller 5-2-2-1 and a longitudinal horizontal tail propeller 5-2-2-2, and a single-paddle layout is generally adopted, so that the economic cruising speed is improved, the air-leaving time is improved, the voyage is prolonged, the machine head 1-2 is provided with the longitudinal horizontal head propeller 5-2-2-1 to generate a pulling force, and the machine tail 1-3 is provided with the longitudinal horizontal tail propeller 5-2-2 to generate a pushing force.

The fixed wing tip elevation 2-1-4 is provided with the fixed wing rudder 2-1-5, so that the heading maneuvering performance of the aircraft is solved, and the influence of the wake flow of the control surface on the aerodynamic performance of the aircraft is reduced due to the fact that the layout is far away from the aircraft body; the fixed wing hanging frame 2-1-3 is arranged below the fixed wing main structure 2-1-1, so that various task devices 7 can be conveniently hung externally.

The outer wing part of the fixed wing 2 is designed into an assembled folding wing main body 2-2, and the folding wing main body 2-2 ensures that the aircraft base occupies small space, and the advantages of the aircraft base can be reflected particularly when the aircraft base is stored; the main structure 2-2-1 of the folding wing is provided with an elevator 2-2-2 and a folding wing tip elevation 2-2-3, and the folding wing tip elevation 2-2-3 is provided with a rudder 2-2-4; a folding wing hanging frame 2-2-5 is arranged below the folding wing main structure 2-2-1; the concentration of the elevators 2-2-2 and the rudders 2-2-4 on the folding wing body 2-2 is also beneficial to the layout of flight control lines and improves the reliability of the maneuvering performance of the aircraft.

The flight control system is provided with a power starting control line 4-1, a power control line 4-2, an electric power input/output control line 4-3, a power clutch control line 4-4 and a power conversion control line 4-5, and the special functional layouts are arranged for effectively controlling the power conversion of the tandem rotor group 5-1, the transverse horizontal propeller 5-2 and the longitudinal horizontal propeller 5-3.

The power and distribution system 3 consists of an engine main body 3-1, an engine starting motor 3-2, an engine power controller 3-3, an engine clutch 3-4, a generator 3-5, a gearbox 3-6 and other related devices, the operation of the devices is controlled by the flight control system 4, and the design of the combination is a necessary condition for realizing the power conversion of the vertical propeller rotor 5-1 and the horizontal propeller 5-2.

The gearbox 3-6 consists of a speed change gearbox 3-6-1, a power input shaft 3-6-2, a power output shaft 3-6-3 and a gear shifting controller group 3-6-4; the power output shaft 3-6-3 is provided with a combination mode of a rotor output shaft 3-6-3-1 and a transverse horizontal thrust output shaft 3-6-3-2.

The gearbox 3-6 consists of a speed change gearbox 3-6-1, a power input shaft 3-6-2, a power output shaft 3-6-3 and a gear shifting controller 3-6-4; the power output shaft 3-6-3 is provided with a rotor output shaft 3-6-3-1 and a longitudinal head-tail output shaft 3-6-3-3 in a combined mode. The power input can be supported by multi-path aggregation synchronization, and the power output can also be multi-path output.

The landing gear selects a wheel landing gear 6-1, a sled landing gear 6-2 and a buoy landing gear 6-3 according to the requirements; the wheel type landing gear 6-1 is suitable for the conditions of an organic runway or short-distance landing, further saves oil consumption and increases endurance; the sled undercarriage 6-2 is more suitable for taking off and landing on carrier-borne, small-platform, narrow zone and field complex terrain; the pontoon landing gear 6-3 is suitable for the surface lifting of oceans, lakes, reservoirs and marshes;

the wheel type landing gear 6-1 is composed of a landing gear support 6-1-1, universal wheels 6-1-2 and landing gear ailerons 6-1-3, the upper part of the landing gear support 6-1-1 is arranged on the machine body 1-1, the universal wheels 6-1-2 are arranged at the bottom of the landing gear support, the landing gear ailerons 6-1-3 are arranged in the middle of the landing gear support 6-1, and the steering surface control deflection and resetting can be performed, so that the maneuvering performance of the aircraft is improved.

The integrated antenna housing 8 is arranged on the machine body, and a multi-band receiving and transmitting antenna is arranged in the integrated antenna housing, so that multi-band measurement can be realized, and an electronic countermeasure transmitting platform can be also realized; the comprehensive radome 8 consists of a radome base 8-1, a radome cabin 8-2 and a radome inspection port 8-3, and is convenient to install and overhaul.

The top of the integrated radome 8 arranged on the aircraft body is of a mushroom-shaped circular structure, the bottom of the integrated radome is flat and convex, and the structure can generate lifting force when the aircraft flies flatly, thereby being beneficial to the stability of the aircraft and saving oil consumption;

the machine head 1-2 and the machine tail 1-3 are of multi-sphere structures, and the embedded multi-degree-of-freedom task platform 7 is arranged in the machine head, so that the special structures of the machine head 1-2 and the machine tail 1-3 can be fully utilized to realize three-dimensional scanning detection, and meanwhile, the wind resistance of the platform outside the machine body 1 is reduced.

The machine body 1-1 is provided with the strip-shaped cabin 1-4 and the barrel cabin 1-5, and the arrangement of the cabin is beneficial to storing task equipment with strip-shaped, round and cylindrical structures, is convenient for flying balance weight, and reduces flying operation difficulty caused by unstable gravity center; the large unmanned conveyor is also provided with cabin doors 1-6; and the cabin windows 1-7 are convenient for the internal assembly, disassembly and maintenance.

The following describes the tandem dual rotor flight operating conditions:

as shown in fig. 2, 3 and 4, in the working state of the tandem double-rotor flight of the aircraft in fig. 8, the attitude and power output coordination of the front and rear rotors 5-1 are controlled by the flight control system 4 to complete the flight function of the aircraft; the tandem double rotor 5-1 not only provides lift force, but also provides thrust force in different directions after the rotor 5-1 slightly tilts for a certain angle, so that more types of air maneuvering actions are completed, and the aircraft can fly along a certain route.

1. Tandem dual rotor system flight preparation: as shown in fig. 6 and 7, (1) check before power system start-up: checking the normal of oil supply, power supply, cooling system and the like, disconnecting the clutch of the input shaft of the gearbox, and ensuring the no-load starting of the engine; (2) and (3) starting an engine: the flight control system sends a command to the starting motor through a 4-1 power starting control line to start the engine, and the output power of the engine is properly adjusted; (3) rotor starts: the method comprises the steps of correcting a rotor shaft 5-1-2 in a front tandem rotor group 5-1-A and a rear tandem rotor group 5-1-B to be perpendicular to a base plane at the bottom of a rotor group tower seat 5-1-3, adjusting an attack angle of a rotor blade 5-1-1 to be a power starting set angle, sending a command to a 3-6-4 power conversion gear shifting controller through a 4-2 power conversion control line by a flight control system, enabling a gearbox to be converted from neutral to be connected with a rotor output shaft, enabling an engine clutch to be actively connected with a gearbox input shaft through a 4-4 power clutch control line by the flight control system, driving a rotor to rotate, and enabling the flight to be shifted to fly after the flight control system is preheated for a certain period to check that the operation of each system is normal.

2. Landing and hovering of rotorcraft: as shown in fig. 8, the rotor disks in the front tandem rotor set 5-1-a and the rear tandem rotor set 5-1-B are corrected to be in a horizontal state, the rotor blades 5-1-1 are adjusted to change the total distance of the front rotor and the rear rotor in the same direction, the flight control system 4 controls the engine power controller 3-3 to gradually increase the output power through the power control line 4-2, the lift force of the front rotor and the rear rotor is simultaneously changed to realize the control of the altitude shaft, the lift force is in an ascending state when the lift force is greater than the total weight of the machine body, the take-off and the climbing of the aircraft can be completed, the lift force is in a hovering state when the lift force is equal to the total weight of the machine body, the lift force is in a descending state when the lift force is less than the total weight of the machine body, and the vertical take-off, the lifting, the hovering and the vertical landing of the aircraft are completed.

3. Forward flight: when the aircraft climbs to a certain safety height, when the rotor disks in the front tandem rotor group 5-1-A and the rear tandem rotor group 5-1-B are adjusted to incline forwards, the rotor disks in the front tandem rotor group 5-1-A and the rear tandem rotor group 5-1-B generate a component force in the horizontal direction forwards when generating upward pulling force, namely pulling force for guiding the aircraft to advance, so that the aircraft can obtain high advancing speed, as shown in fig. 8-c.

4. And (3) backing and flying: when the rotor disks in the front tandem rotor group 5-1-a and the rear tandem rotor group 5-1-B are adjusted to tilt backward, the rotor disks in the front tandem rotor group 5-1-a and the rear tandem rotor group 5-1-B generate a component force in the horizontal direction to the rear of the machine body 1, namely, a pulling force for guiding the aircraft to retreat, and the aircraft can obtain a retreating speed with high loudness, as shown in fig. 8-d.

5. And (3) diving flight: when the front tandem rotor set 5-1-a is tilted forward and the rear rotor 5-1-B is held horizontal, the aircraft is in a nose down condition, as shown in fig. 8-B.

6. Side rolling: when both fore-aft tandem rotor sets 5-1-a, 5-1-B are simultaneously tilted to one side, the aircraft can now be efficiently moved sideways, as in fig. 8-e to the right and fig. 8-f to the left.

7. Turning: when the two front and rear tandem rotor wing groups 5-1-A and 5-1-B are inclined in a crossed mode, the airplane can rotate around the center of the airplane body as an axis, and can rotate in place to turn in a hovering state, as shown in the figure 8-g to the right and the figure 8-h to the left.

Short take-off and landing of the fixed wing flight state is shown in fig. 1, 5, 6 and 7 and 9:

1. fixed wing system flight preparation: as shown in fig. 6 and 7, (1) check before power system start-up: checking the normal of oil supply, power supply, cooling system and the like, disconnecting the clutch of the input shaft of the gearbox, and ensuring the no-load starting of the engine; (2) and (3) starting an engine: the flight control system sends a command to the starting motor through a 4-1 power starting control line to start the engine, and the output power of the engine is properly adjusted; (3) and adjusting the working posture of the column type rotor wing group 5-1: correcting angles of the rotor shafts 5-1-2 in the front tandem rotor group 5-1-A and the rear tandem rotor group 5-1-B and the base reference plane of the bottom of the rotor group tower seat 5-1-3 to the rotorcraft, and adjusting attack angles of the rotor blades 5-1-1 to be a negative value regulated angle; correcting the rudder angle of the folding wing elevator 2-2-2 on the fixed wing aileron combined elevator 2-1-2 or the folding wing main structure 2-2-1 to be zero, and correcting the rudder angle of the folding wing 2-2-4 on the fixed wing rudder 2-1-5 or the folding wing tip elevation 2-2-3 to be zero; the universal wheel 6-1-2 of the control wheel type landing gear 6-1 is in a braking state; then the flight control system 4 sends a command to the power conversion gear shift controller 3-6-4 through the power conversion control line 4-2, so that the gearbox 3-6 is converted from neutral position to a transverse horizontal propeller output shaft 3-6-3-2 or a longitudinal head-tail propeller output shaft 3-6-3-3 which is connected with the power output shaft 3-6-3 of the fixed wing 2; the flight control system 4 actively connects the engine clutch 3-4 with the power input shaft 3-6-2 of the speed change gear box 3-6-1 through the power clutch control line 4-4, thereby driving the transverse horizontal propeller output shaft 3-6-3-2 or the longitudinal head-tail propeller output shaft 3-6-3-3 to rotate, the power system 3 is in an idling state initially, and the flight can be shifted after the system is preheated for a certain time to check that the operation of each system is normal.

2. Takeoff and climb of fixed wing aircraft: as shown in fig. 6, 7 and 8, the fixed wing aircraft is placed at the initial position of a flight runway to prepare for taking off, the braking state of the universal wheels 6-1-2 of the wheel landing gear 6-1 is released, the flight control system 4 controls the engine power controller 3-3 to gradually increase the output power through the power control line 4-2, so that the fixed wing aircraft runs on the runway in an accelerating way, as shown in fig. 9-1, when the running speed is such that the lift force generated by the fixed wing and the rotor wing together is greater than the total weight of the aircraft body, the flight control system 4 sends a climbing instruction to the fixed wing aileron elevator 2-1-2 or the folding wing elevator 2-2, the elevator control surfaces are turned up simultaneously to generate the moment of head lifting of the aircraft 1-2, and the aircraft flies in the air at the climbing angle, as shown in fig. 9-2, so that taking off and climbing of the fixed wing aircraft are completed;

3. plane flight of fixed wing aircraft: when the aircraft climbs to a certain height, the flight control system 4 sends a plane flight command to the fixed wing aileron combined elevator 2-1-2 or the folding wing elevator 2-2-2, and at the moment, the control surface of the fixed wing aileron combined elevator 2-1-2 or the folding wing elevator 2-2-2 is zeroed, so that the aircraft is in a plane flight state, as shown in fig. 9-1;

4. steering of fixed wing aircraft: in the flat flight state, the control system 4 sends a steering instruction to the fixed wing rudder 2-1-5 of the fixed wing tip elevation 2-1-4 or the folding wing rudder 2-2-4 on the folding wing tip elevation 2-2-3, the right steering rudder surface deflects rightwards, the torque generated by the control surface deflects the nose 1-2 rightwards as shown in fig. 9-5, the left steering rudder surface deflects leftwards as shown in fig. 9-4, and the torque generated by the control surface deflects the nose 1-2 leftwards as shown in fig. 9-4; in the flat flight state, the function of correcting the heading can be also achieved by controlling the deflection of the landing gear aileron 6-1-3 on the landing gear support 6-1-1;

5. side roll of fixed wing aircraft: when the flight control system 4 sends out a left rolling instruction, the left fixed wing auxiliary elevator 2-1-2 or the folding wing elevator 2-2-2 control surface of the machine body 1-1 is turned up, and the right fixed wing auxiliary elevator 2-1-2 or the folding wing elevator 2-2 control surface of the machine body 1-1 is turned down, so that a left rotating moment is generated on the machine body, and the machine body 1-1 rolls anticlockwise and left, as shown in fig. 9-6; the reverse operation causes the fuselage 1-1 to roll right as shown in fig. 9-7;

6. when the pilot command is sent by the pilot control system 4, the pilot control system 4 turns down the control surfaces of the fixed wing aileron and elevator 2-1-2 or the folding wing elevator 2-2 simultaneously, then generates downward moment of the nose 1-2, and the aircraft is in a pilot flight attitude, as shown in fig. 9-3;

7. landing of fixed wing aircraft: when the aircraft is in low altitude and is aligned with the runway in a long distance, the lift force is weakened along with the reduction of the speed of the aircraft along with the reduction of the power system, the aircraft naturally descends, the engine is reduced to an idle state after the aircraft lands on the initial point of the runway according to the descending speed, the aircraft runs in a speed-reducing manner on the runway, the aircraft stops finally through point braking, and the aircraft landing process is completed, as shown in fig. 9-1.

The power conversion between the tandem rotor set 5-1 and the horizontal propeller 5-2 is shown in fig. 1, 4, 5, 6 and 7:

(1) checking before starting a power system: checking the normal of oil supply, power supply, cooling systems and the like, disconnecting the engine clutch 3-4 of the gearbox 3-6, and ensuring the no-load starting of the engine 3;

(2) the engine 3 is started: the flight control system 4 sends a command to the engine starting motor 3-2 through the power starting control line 4-1 to start the engine, and the output power of the engine is properly adjusted;

(3) rotor operation: the flight control system 4 sends an instruction to the power conversion gear shift controller 3-6-4 through the power conversion control line 4-2, so that the gearbox 3 is converted from neutral position to be connected with the rotor wing power output shaft 3-6-3-1, the engine clutch 3-4 is actively connected with the power input shaft 3-6-2 on the speed change gearbox 3-6-1 through the power clutch control line 4-4 by the flight control system 4, the tandem rotor wing group 5-1 is driven to rotate, the lift force generated by the rotor wing is greater than the dead weight along with the increase of power, the aircraft is in a take-off and lifting stage, and the working state of the tandem rotor wing group 5-1 is controlled through the flight control system 4, so that the take-off and landing, hovering and low-speed flight tasks of the aircraft are completed;

(4) horizontal thrust 5-2-1 transition: when the rotor wing lifts the aircraft to a safe height and keeps a certain flat flying speed, so that the fixed wing 2 generates enough lifting force to ensure stable flying, the flight control system 4 gives an instruction through the power clutch control line 4-4 to enable the engine clutch 3-4 to be actively and completely separated from the power input shaft 3-6-2 of the gearbox 3-6, the flight control system 4 gives an instruction through the power conversion gear shifting controller 3-6-4 to enable the gear position to be changed from the rotor wing to a neutral position close to the power output shaft 3-6-3, and then the neutral position is changed to the gear position of the output shaft 3-6-3-2 of the horizontal propeller, so that a signal is fed back to the flight control system 4 after the gear shifting is successful, the flight control system 4 can give an instruction to the engine clutch 3-4, the engine clutch 3-4 receives the instruction to be actively connected with the power input shaft 3-6-2 of the gearbox 3-6, the power output is changed to the output shaft 3-6-2 of the horizontal propeller, the output shaft 3-6-2 of the horizontal propeller is immediately driven by the horizontal propeller, the output shaft 3-2 of the horizontal propeller is immediately driven by the horizontal propeller 5-2, or the horizontal propeller is driven by the vertical propeller 5-2, and the horizontal propeller is continuously changed to the horizontal propeller 5-1, or the horizontal propeller is continuously driven by the horizontal propeller 5-5, and the horizontal propeller is continuously changed to the horizontal propeller is driven by the horizontal propeller 1, and the horizontal propeller is driven by the horizontal propeller 5, and the horizontal propeller is continuously driven by the horizontal propeller 1.

Power conversion of tandem rotor set 5-1 with longitudinal horizontal propeller 5-2-2:

(1) checking before starting a power system, (2) starting an engine, and (3) enabling a rotor to work equivalently to power conversion of the tandem rotor set 5-1 and the horizontal propeller, and are not stated;

(4) when the rotor 5-1 lifts the aircraft by a safe height and keeps a certain flat flying speed, the flying control system 4 sends out an instruction to completely separate the engine clutch 3-4 from the power input shaft 3-6-2 of the gearbox 3-6 through the power clutch control line 4-4, the flying control system 4 sends out an instruction to transfer the gear from the longitudinal rotor group 5-1 to a neutral gear close to the output shaft 3-6-3-3 of the longitudinal head-tail propeller, then transfers to the output shaft 3-6-3-3 of the longitudinal head-tail propeller by the neutral gear, ensures that after the gear is shifted successfully, feeds back a signal to the flying control system 4, and can give out an instruction to the engine clutch 3-4, the engine clutch 3-4 instructs to actively abut against the power input shaft 3-6-2 of the gearbox 3-6-1, transfers the power output to the output shaft 3-6-3-3 or the longitudinal head-tail propeller to drive the longitudinal head-3-2 or the longitudinal head-2-2-2 to run continuously (the longitudinal head-3-3 or the longitudinal head-2-2-2) to make the longitudinal head-2-2 drive the aircraft to run horizontally, the power conversion between the tandem rotor group 5-1 and the longitudinal horizontal propeller 5-2-2 is completed, and the power conversion between the longitudinal horizontal propeller 5-2-2 and the tandem rotor group 5-1 is performed in the reverse operation.

The last points to be described are: first, in the description of the present application, it should be noted that, unless otherwise specified and defined, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be mechanical or electrical, or may be a direct connection between two elements, and "upper," "lower," "left," "right," etc. are merely used to indicate relative positional relationships, which may be changed when the absolute position of the object being described is changed; secondly: in the drawings of the disclosed embodiments, only the structures related to the embodiments of the present disclosure are referred to, and other structures can refer to the common design, so that the same embodiment and different embodiments of the present disclosure can be combined with each other under the condition of no conflict; finally: the foregoing description of the preferred embodiments of the utility model is not intended to limit the utility model to the precise form disclosed, and any such modifications, equivalents, and alternatives falling within the spirit and principles of the utility model are intended to be included within the scope of the utility model.

Claims (9)

1. The utility model provides a fixed wing and tandem rotor complex aircraft which characterized in that, it includes organism structure, flight control system, power and distribution system, propeller, mission equipment, energy storage and electric power distribution system, wherein:

the machine body structure comprises a machine body, a machine head, a machine tail, fixed wings and a landing gear;

the fixed wing is arranged in the middle of the machine body, and an aileron with an elevator function is arranged on the fixed wing;

the propeller comprises a vertical propeller and a horizontal propeller;

the vertical propeller comprises at least one column-type rotor wing group arranged on the machine body, wherein each column-type rotor wing group comprises two rotor wings which are identical in structure, synchronously rotate and have opposite rotation directions;

the horizontal propeller is arranged on the machine body structure;

the power conversion between the tandem rotor group and the horizontal propeller is completed by the flight control system through the power and distribution system.

2. The fixed wing and tandem rotor complex aircraft of claim 1, wherein: the rotor is provided with a rotor blade with positive and negative adjustable attack angle and a rotor shaft with adjustable inclination angle according to the flying gesture.

3. The fixed wing and tandem rotor complex aircraft of claim 1, wherein: the horizontal propeller is arranged at one or more of two sides of the machine body, the machine head and the machine tail.

4. The fixed wing and tandem rotor complex aircraft of claim 1, wherein: the wing tip of the fixed wing is provided with a vertical face, and a rudder is arranged on the vertical face.

5. The fixed wing and tandem rotor complex aircraft of claim 1, wherein: the outer wing portions of the fixed wings are designed as combinable folding wings.

6. The fixed wing and tandem rotor complex aircraft of claim 1, wherein: in the structure of the fixed wing, the part of the fixed wing, which is influenced by the air current generated by the rotor wing, is hollowed out.

7. The fixed wing and tandem rotor complex aircraft of claim 1, wherein:

the power distribution system comprises an engine main body, an engine starting motor, an engine power controller, an engine clutch, a generator and a gearbox, wherein the engine main body, the engine starting motor, the engine power controller, the engine clutch, the generator and the gearbox can be controlled to run by the flight control system;

the gearbox comprises a speed change gearbox, a power input shaft, a power output shaft and a gear shifting controller;

the power output shaft comprises a rotor output shaft and a horizontal propeller output shaft.

8. The fixed wing and tandem rotor complex aircraft of claim 1, wherein: the landing gear is a wheel landing gear or a sled landing gear or a pontoon landing gear.

9. The fixed wing and tandem rotor complex aircraft of claim 1, wherein: the integrated antenna housing is arranged on the machine body and consists of an antenna housing base, an antenna housing cabin and an antenna housing inspection port; the radome cabin is of a mushroom-shaped structure with a flat bottom and a convex upper part, and is internally provided with a multi-band transceiver antenna.