CN110901890A - High-speed rotor craft with rotor capable of being designed in classification mode - Google Patents
High-speed rotor craft with rotor capable of being designed in classification mode Download PDFInfo
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- CN110901890A CN110901890A CN201911229120.8A CN201911229120A CN110901890A CN 110901890 A CN110901890 A CN 110901890A CN 201911229120 A CN201911229120 A CN 201911229120A CN 110901890 A CN110901890 A CN 110901890A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/385—Variable incidence wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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Abstract
The invention relates to a rotor craft, in particular to a rotor craft which is designed by utilizing a plurality of rotors in a classified mode to achieve efficient vertical take-off and landing and efficient high-speed forward flight. The aircraft comprises a fuselage (1), a front wing (2a), a rear wing (2b), a propeller unit (3) and a lift paddle unit (4). The front wing (2a) and the rear wing (2b) are tiltable mechanisms and are arranged at the front section and the middle and rear sections of the fuselage, the propeller units are symmetrically arranged at the two ends of the front wing (2a) and the rear wing (2b) respectively, and the lift propeller units (4) are symmetrically arranged at the two sides of the front wing (2a) and the rear wing (2 b). The multi-rotor wing tilting aircraft can realize the switching between vertical take-off and landing and high-speed forward flight by wing tilting, and can effectively ensure the flight performance of vertical take-off and landing and high-speed forward flight by adopting the design of various different rotor wings, thereby having greater advantages compared with the existing aircraft.
Description
Technical Field
The invention relates to an aircraft, in particular to a rotor aircraft which is designed by utilizing a plurality of rotors in a classified mode to realize efficient vertical take-off and landing and efficient high-speed forward flight.
Background
In the existing aircraft, the mechanical energy is converted into aerodynamic energy through the rotation of a rotor wing, the efficiency of the helicopter taking the rotor wing as a main aerodynamic source is highest during vertical take-off, landing and hovering flight by utilizing aerodynamic force to overcome gravity, but in the forward flight state of the traditional helicopter, the lift direction of the rotor wing is nearly perpendicular to the forward flight direction, the small component of the lift force of the rotor wing is mainly utilized as the forward flight power to overcome the forward flight resistance, and after the rotor wing is superposed with the incoming flow speed on the outer section of a front side blade in the rotation process along with the increase of the forward flight speed, the linear speed can reach sonic speed to cause great increase of resistance, namely the phenomenon of 'shock wave of the forward blade', and simultaneously, after the inner section of a rear side blade is superposed with the incoming flow, the stall occurs and the lift force cannot be generated, namely the phenomenon of 'stall of the rear blade', the two phenomena comprehensively limit the forward flight speed of the traditional helicopter, and the maximum horizontal flight speed of the traditional helicopter is about 320km/h on average at present.
In order to maintain the capability of VTOL and hover flight, and fly forward at high speed, various types of high-speed rotary-wing aircraft have been developed, most of which are under technical exploration, and the rigid coaxial rotary-wing composite thrust type represented by the S-97 'invader' in the United states and the tilting rotary-wing type represented by the V-22 'osprey' and the V-280 'warrior' are in model application. The rigid coaxial rotor composite thrust type has the advantages that a pair of thrust propellers is added to provide forward flight power, the load of the rotor is reduced, but the defect of resistance caused by forward blade shock waves is not overcome, so that the maximum forward flight speed can only reach about 450 km/h.
The two rotors are respectively arranged at V-22 and V-280 at the wing tips of the wings, when the aircraft vertically takes off, lands and hovers, the two rotors are approximately vertically upward and used as lift propellers to generate lift, when the aircraft flies forward at high speed, the two rotors tilt forward to be horizontal and used as propellers to provide forward flight power, and the wings are used to generate lift, so that the physical limitations of forward blade shock waves and backward blade stall of the rotors are eliminated, the maximum flying speed is increased to about 550km/h, but the high-speed rotor aircraft of the type has the following defects:
(1) the lift propeller and the propeller share one pair of rotors, and the design of the rotors needs to take account of hovering efficiency and propeller efficiency, so that the design compromise that the torsion angle of the blades is not too large, the radius and the rotating speed of the rotors are not too small and the like is caused, the hovering efficiency and the efficiency of the front flying propeller cannot be maximized, and the improvement of the front flying speed is further limited;
(2) the two rotors are respectively arranged at wing tips of the wings, and because the radii of the rotors are large, the structural weight, aerodynamic force, inertia and the like are also large, the structural instability of the wings in the tilting transition stage is easily caused, so that the wings only adopt the strength and rigidity enhancement design, the high-efficiency high-aspect-ratio wings cannot be adopted, and the aerodynamic efficiency of forward flight is not high;
(3) because the two rotors have larger radius, the wings are fixed below the rotors, and the downwash airflow of the rotors is partially blocked by the wings during vertical take-off, landing and hovering flight, so that the hovering efficiency is further reduced;
(4) each rotor wing is driven by an engine, and because the rated rotating speed of the rotor wing is different from the rated rotating speed of the engine greatly, the rotor wing needs to be tilted and reversed, a complex transmission system needs to be added, so that the design limiting conditions of pneumatics, structures, dynamics and the like are more, and the coupling is serious.
Disclosure of Invention
The purpose of the invention is as follows: the rotor craft can take off and land vertically and fly forwards at high speed efficiently.
The technical scheme of the invention is as follows: the utility model provides a many rotors tilt aircraft, its includes fuselage 1, front wing 2a, back wing 2b, screw unit 3, lift oar unit 4, undercarriage 5, wherein, front wing 2a, back wing 2b are tilting mechanism, set up at fuselage anterior segment and well back-end, the undercarriage is installed in fuselage below or on the wing, the screw unit symmetry respectively sets up the both ends at front wing 2a, back wing 2b, lift oar unit 4 symmetry sets up in front wing 2a, back wing 2b both sides to be located screw unit 3 inboardly, and lift oar unit 4 and screw unit 3 all move towards unanimously.
The lift paddle unit 4 comprises a lift paddle 41 and a lift paddle driving motor 42, the lift paddle driving motor 42 directly drives the lift paddle 41 to rotate, the lift paddle unit 4 is controlled by changing the rotating speed, and the lift force is adjusted by changing the rotating speed.
The root of the lifting paddle 41 is connected with a motor shaft through a hinge, the motor shaft rotates when the lifting paddle vertically takes off and lands, the paddle is driven to rotate through the hinge, the paddle stretches around the hinge under the action of a rotating centrifugal force, the driving motor 42 brakes and stops rotating when the lifting paddle flies at present, and the paddle is folded under the action of front flying resistance.
The lift paddle 41 adopts a small torsion angle, the torsion angle range is-6 degrees to-12 degrees, and the pneumatic efficiency is improved during vertical lifting.
The lift paddle 41 is designed to be a high lift wing type, has a small front edge radius and is a flat convex wing type, and is used for improving the lift coefficient.
The propeller unit 3 includes a propeller 31 and a propeller driving motor 32, and the propeller driving motor 32 directly drives the propeller 31 to rotate.
The propeller 31 adopts a variable-pitch design, the propeller driving motor 32 adopts constant rotating speed control, the lift force is adjusted by changing the pitch, and two different rotating speeds are adopted in a vertical take-off and landing and hovering low-speed flight state and a forward flight state; in the vertical take-off and landing and hovering low-speed flight states, large rotating speed is adopted to match with small propeller pitch; in the forward flight state, the small rotating speed is matched with the large pitch.
The front wing 2a and the rear wing 2b are designed in a large aspect ratio, and the aspect ratio ranges from 10 to 20.
In the multi-rotor tilting aircraft, under a high-speed forward flight state, the rotating directions of the adjacent propeller units 3 and the adjacent lift paddle units 4 are opposite, so that the front wing tip vortex 8a and the front wing propeller detached vortex 9a are opposite at the front wing 2 a.
The multi-rotor tilting aircraft is characterized in that wingtip winglets 7 are symmetrically arranged at the wingtips of the rear wings 2b, the wingtip winglets 7 can separate wingtip small wingtip vortexes 8b and rear wing propeller detached vortexes 9b in the same direction by a certain distance in the front flying state of the fixed wings,
the multi-rotor-wing tilting aircraft is characterized in that the front wing 2a and the rear wing 2b are located in an approximately vertical direction in a vertical take-off and landing and hovering low-speed flight state, vertical operation of the multi-rotor-wing tilting aircraft is achieved by simultaneously changing the lift force of the lift force paddle unit 4 and the lift force of the propeller unit 3, the front wing 2a lift force paddle unit 4 and the propeller unit 3 are differentially changed, the rear wing 2b lift force paddle unit 4 and the propeller unit 3 are differentially changed, the lift force of the front wing 2a left side lift force paddle unit 4 and the propeller unit 3, the front wing 2a right side lift force paddle unit 4 and the propeller unit 3 are differentially changed, and course operation is achieved by differentially changing the lift force of the lift force paddle unit 4 and the propeller unit 3 which are in the same direction.
The multi-rotor tilting aircraft is characterized in that a front wing 2a and a rear wing 2b are located in an approximately horizontal direction under the condition that a fixed wing flies forwards, a lift paddle 41 is folded in a stalling way, the pitching operation of the multi-rotor tilting aircraft is realized through differential deflection of a front wing flaperon 201a and a rear wing flaperon 201b, the rolling operation of the multi-rotor tilting aircraft is realized through synchronous deflection of a left front wing flaperon 201a and a right rear wing flaperon 201b, and the course operation is realized through differential regulation of the tension of a left side screw unit 3 and the pull of a right side screw unit 3 and coordinated turning.
Many rotors tilt aircraft, its transition flight state includes 2 states: the state of transition from vertical take-off and landing and hovering low-speed flight to fixed wing forward flight and the state of transition from fixed wing forward flight to hovering low-speed flight;
in a conversion state, the front wing 2a and the rear wing 2b synchronously tilt to an approximately horizontal direction, and the control in the state is realized by mixing a vertical take-off and landing and hovering low-speed flight control mode and a fixed wing forward flight control mode;
in a transition state, the blades of the lift paddle 41 rotate and expand, the front wing 2a and the rear wing 2b synchronously tilt in an approximately vertical direction, and the control in the state is realized by mixing a vertical take-off and landing and hovering low-speed flight control mode and a fixed wing forward flight control mode.
A flight control method of a high-speed rotor aircraft with a rotor wing capable of being designed in a classified mode drives rotor wing units on front and rear wings to tilt by controlling the tilting of the front and rear wings, then respectively controls working states of a lift paddle unit and a propeller unit in the rotor wing units, and respectively realizes vertical take-off and landing, high-speed forward flight and mutual switching.
The invention has the beneficial effects that:
(1) high-efficiency vertical take-off and landing and high-efficiency high-speed forward flight. The rotor wing is divided into two types of lifting propellers and propellers, the lifting propellers are used for vertical take-off and landing and hovering low-speed flight, the propellers are mainly used for forward flight, the lifting propellers can be designed according to the highest hovering and vertical take-off and landing pneumatic efficiency, the hovering efficiency can be designed to be more than 0.75, the propellers can be designed according to the highest forward flight efficiency, and the propeller unit adopts two different rotating speeds in the two states of vertical take-off and landing and forward flight, so that the propeller efficiency can be further improved; the lifting propellers stop rotating and fold during forward flight, and the results of computational fluid mechanics comparative analysis show that the resistance of the lifting rotor wing is reduced by 48.9 percent in the same state after being folded compared with that under the condition of not being folded, so that the rotor wing aircraft has the forward flight speed capability of more than 600 km/h;
(2) the lift-drag ratio of the wing is large. The two wings are distributed in a high aspect ratio, so that the lift-drag ratio is high; the direction of the tail stream vortex separated from the propeller unit at the wing tip of the front wing during forward flying is opposite to that of the wing tip vortex of the wing, so that the wing tip vortex is broken, and the test proves that the lift-drag ratio can be improved by about 10%;
(3) the lift paddle unit and the propeller unit are arranged on the front edge of the wing and tilt along with the wing, so that the wing has small interference on the downwash airflow of the wing;
(3) the lift oar unit and the propeller unit are arranged at the front edge of the wing, the wake flow of the lift oar unit and the propeller unit blows over the wing, and the lift force of the wing can be increased in a tilting transition state, so that the tilting transition can be completed at a small forward flying speed, and a flight speed 'transition corridor' is expanded;
(4) the plurality of small lifting propellers and the propellers are adopted, the rated rotating speed range of the small lifting propellers and the propeller is equivalent to the rated rotating speed range of the motor, the motors can be adopted for direct drive, a transmission system is omitted, the lifting propeller unit and the propeller unit can rotate along with the random wings at the same time, a reversing system is omitted, and the degree of freedom and flexibility of aerodynamics, structure, dynamics and overall arrangement design are increased;
(5) the dual-wing aircraft with the tandem layout enables the rotor aircraft to be equivalent to a four-rotor aircraft during vertical take-off and landing and low-speed hovering flight, has larger longitudinal and transverse gravity center range, and is beneficial to hanging and transporting operation;
(6) by adopting the double wings, the lift paddle unit and the propeller unit with the same parameters, the economical efficiency of manufacturing and the interchangeability during maintenance can be improved, the manufacturing cost is reduced, and the logistics maintenance is facilitated.
Drawings
FIG. 1 is an isometric view of a high-speed rotorcraft of a rotor-sortable design according to an embodiment of the present invention in a low-speed vertical takeoff and landing and hovering flight state;
FIG. 2 is a side view of a high-speed rotorcraft of a rotor-sortable design in a low-speed vertical takeoff and landing and hovering flight state, according to an embodiment of the present invention;
FIG. 3 is a top view of a high-speed rotorcraft with classifiable rotor designs, according to an embodiment of the present invention, in a low-speed vertical takeoff and landing and hovering flight state;
FIG. 4 is an isometric view of a high-speed rotorcraft of a rotor-sortable design according to an embodiment of the present invention in a forward flight condition;
fig. 5 is an isometric view of a high-speed rotorcraft of rotor-sortable design according to an embodiment of the present invention in a transitional state.
FIG. 6 is a schematic view of a high-speed rotorcraft rotor-lift unit and propeller unit with sortable rotors according to an embodiment of the present invention;
fig. 7 is a schematic diagram illustrating forward wing rotor wash-down and forward wing tip vortex interference of a high-speed rotorcraft with a rotor of a sortable design according to an embodiment of the present invention in a forward flight state;
fig. 8 is a schematic diagram illustrating interference between the wing-rotor wash-down and winglet tip vortex of a high-speed rotorcraft with a rotor of a classifiable design according to an embodiment of the present invention, when the high-speed rotorcraft is in a forward flight state.
The labels in the figures are:
a body 1; a wing 2; a front wing 2 a; a rear wing 2 b; front wing flaperon 201 a; rear wing flaperon 201 b; a propeller unit 3; a propeller 31; a propeller drive motor 32; a lift paddle unit 4; a lifting paddle 41; a lift paddle drive motor 42; a landing gear 5; a vertical tail 6; wingtip winglets 7; the front wing tip vortex 8 a; a wing tip small wing tip vortex 8 b; a front wing propeller detached vortex 9 a; the rear wing propeller sheds the body vortex 9 b.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1, an embodiment of the present invention provides a multi-rotor tilting aircraft, including a fuselage 1, a front wing 2a, a rear wing 2b, a propeller unit 3, a lift paddle unit 4, and a landing gear 5. The front wing 2a and the rear wing 2b are tiltable mechanisms and are arranged at the front section and the middle and rear sections of the fuselage, the undercarriage is arranged below the fuselage or on the wings, the propeller units are respectively symmetrically arranged at two ends of the front wing 2a and the rear wing 2b, the lift propeller units 4 are symmetrically arranged at two sides of the front wing 2a and the rear wing 2b and are located on the inner sides of the propeller units 3, and the orientations of the lift propeller units 4 and the propeller units 3 are consistent. Because the two types of propeller units 3 and the lifting propeller units 4 are arranged on the front wing 2a and the rear wing 2b respectively, the quantity of propeller units is large, the control consistency is high, the propeller units are driven to tilt by directly controlling the tilting of the wings, the structure can be effectively simplified, the control efficiency is improved, and the operation performance of the airplane is ensured.
The body 1 of the rotor craft provided by the embodiment of the invention is a streamline approximate spindle body, the front flying resistance can be reduced, the interior of the body comprises structures and equipment such as an engine, a generator, a converter, an oil tank, a controller, a cabin and the like, the details are not shown in the figure, and the body can be designed by adopting a conventional scheme according to actual conditions to realize the basic functions.
The undercarriage 5 of the rotor craft provided by the embodiment of the invention adopts a front three-point retractable undercarriage form and is arranged at the lower part of the fuselage 1, and the undercarriage 5 is retracted in the fuselage 1 during forward flight, so that the forward flight resistance is reduced. In addition, in a modified embodiment, the landing gear may be disposed below the front wing 2a and the rear wing 2 b.
The wings 2 of the rotorcraft in the embodiment of the invention are in a tandem layout and comprise a front wing 2a and a rear wing 2b, and the front wing 2a and the rear wing 2b are in a large aspect ratio layout, so that a wide layout space can be provided for the propeller unit 3 and the lift propeller unit 4, and the lift-drag ratio during forward flight can be improved. In addition, the length of the rear wing 2b is not less than the size of the front wing 2a, so that the aerodynamic interference of the front wing 2a is reduced as much as possible, and the aerodynamic performance is ensured.
Preceding wing 2a and back wing 2b and fuselage combination department all are provided with and combine the department assorted notch with the fuselage to directly being provided with the fuselage and verting and actuating the mechanism, realizing the control of verting, actuating the mechanism drive down should verting, all can verting to the fuselage relatively, do the motion of verting between two directions of approximate level and approximate perpendicular promptly, just preceding wing 2a and back wing 2b vert in step. Wherein, the tilting actuating mechanism can adopt a hydraulic or electric actuating mechanism. In addition, the front wing 2a and the rear wing 2b adopt the same design parameters such as pneumatics, structures and the like, so that the economical efficiency of manufacturing and the interchangeability during maintenance are increased, the manufacturing cost is reduced, and the logistics maintenance is facilitated; the front wing 2a is symmetrically connected to the rear part of the fuselage 1 along the longitudinal symmetrical plane of the fuselage 1 through a hydraulic or electric actuating mechanism; the rear wings 2b are symmetrically connected to the front part of the fuselage 1 along the longitudinal symmetrical plane of the fuselage 1 through a hydraulic or electric actuating mechanism; the front wing 2a and the rear wing 2b are spaced at a certain interval in the longitudinal direction and the vertical direction of the fuselage 1, so that aerodynamic interference between the two wings in a forward flying state is reduced.
The same positions of the trailing edges of the front wing 2a and the rear wing 2b are respectively provided with a front wing flaperon 201a and a rear wing flaperon 201b, and the front wing flaperon 201a and the rear wing flaperon 201b are arranged along the longitudinal symmetrical plane of the fuselage 1 in a bilateral symmetry manner so as to carry out further pneumatic adjustment.
The rotor craft provided by the embodiment of the invention adopts 4 pairs of lift paddle units 4, wherein 2 pairs of lift paddle units 4 are symmetrically and fixedly arranged at the front edge of the front wing 2a along the longitudinal symmetry plane of the fuselage 1, and the other 2 pairs of lift paddle units 4 are symmetrically and fixedly arranged at the front edge of the rear wing 2b along the longitudinal symmetry plane of the fuselage 1.
The lift paddle unit 4 comprises a lift paddle 41 and a lift paddle driving motor 42, the lift paddle driving motor 42 directly drives the lift paddle 41 to rotate, the lift paddle unit 4 is controlled by changing the rotating speed, and the lift force is adjusted by changing the rotating speed. The root of the lifting paddle 41 is connected with a motor shaft through a hinge, the motor shaft rotates when the lifting paddle vertically takes off and lands, the paddle is driven to rotate through the hinge, the paddle expands around the hinge under the action of a rotating centrifugal force, the driving motor 42 brakes and stops rotating when the lifting paddle flies currently, and the paddle is folded under the action of front flying resistance.
Because the lifting paddle 41 only effectively works in the low-speed flight state of vertical take-off and landing and hovering, and the front-flying axial flow state is not considered, the pneumatic layout of the paddle adopts the design of a small torsion angle, a high-lift wing profile and the like, and the hovering efficiency of the lifting paddle 41 is improved.
The lift paddle 41 adopts a small torsion angle, the torsion angle range is-6 degrees to-12 degrees, and the pneumatic efficiency is improved during vertical lifting.
The lift paddle 41 is designed to be a high lift wing type, has a small front edge radius and is a flat convex wing type, and is used for improving the lift coefficient.
The lift oar 41 of the embodiment of the invention adopts 2 blades, the number of the blades can be changed according to the actual application condition, the blades of the lift oar 41 can be stopped to rotate, folded and rotated to be unfolded, and particularly, the blades of the lift oar 41 are unfolded and rotated to generate lift force under the vertical take-off and landing and hovering low-speed flight states of a rotor craft; under the state that the rotor craft flies forward, the lift oar 41 paddle stall folding to reduce the resistance that flies forward, improve the speed that flies forward.
Specifically, under the low-speed flight state of vertical take-off and landing and hovering of the rotorcraft, the lift paddle 41 is vertically upward, the lift paddle driving motor 42 drives the blades to rotate, and the blades are unfolded upward under the action of centrifugal force and lift force along with the increase of the rotating speed to generate upward lift force; under the forward flight state of the rotorcraft, the lift paddle drive motor 42 gradually brakes and stops rotating, and the blades of the lift paddle 41 are folded backwards under the action of centrifugal force and forward flight resistance which are gradually unloaded so as to reduce the forward flight resistance.
The rotor craft provided by the embodiment of the invention adopts 2 pairs of propeller units 3, wherein 1 pair of propeller units 3 are symmetrically and fixedly arranged at the front edge of the wingtip of the front wing 2a along the longitudinal symmetry plane of the fuselage 1, and the other 1 pair of propeller units 3 are symmetrically and fixedly arranged at the front edge of the wingtip of the rear wing 2b along the longitudinal symmetry plane of the fuselage 1.
The propeller unit 3 comprises a propeller 31 and a propeller driving motor 32, the propeller driving motor 32 directly drives the propeller 31 to rotate, the propeller 31 adopts a variable-pitch design, the propeller driving motor 32 realizes constant rotating speed control through an electronic speed regulator, the lift force is adjusted by changing the size of the pitch, and two different rotating speeds are adopted in a vertical take-off and landing and hovering low-speed flight state and a forward flight state. In the vertical take-off and landing and hovering low-speed flight states, the high rotating speed is adopted to be matched with the small propeller pitch, so that the efficiency of the propeller in the state is improved; in the forward flight state, because the propeller 31 is in the axial flow state, the effective attack angle of the blades of the propeller 31 is reduced by a larger forward flight speed, so that the propeller 31 is in an inefficient state, and the efficiency of the propeller 31 can be optimized by matching a small rotating speed with a large pitch. The propeller 31 of the embodiment of the invention adopts 3 blades, and the number of the blades can be changed according to the actual application condition.
The arrangement and direction of rotation of the rotor unit 3 and the lift paddle unit 4 of a rotorcraft according to an embodiment of the present invention is shown in fig. 3. When the aircraft vertically takes off and lands, the directions of rotation between two adjacent propeller units 3 and 4 or between the two adjacent propeller units 4 and 4 are opposite, and the aim of the aircraft is to effectively offset the torque difference on the wings and realize the balance between the torque and the reactive torque on a single wing.
In the high-speed forward flight state of the rotorcraft, the directions of the front wing tip vortex 8a and the front wing propeller detached vortex 9a are opposite at the front wing 2a, as shown in fig. 7, favorable aerodynamic interference can be generated, and the test proves that the lift-drag ratio can be improved by about 10%.
According to the embodiment of the invention, the wingtip winglets 7 are symmetrically arranged at the wingtips of the rear wings 2b of the rotorcraft, and in the front flying state of the fixed wings, the wingtip winglets 7 can separate wingtip small wingtip vortexes 8b and rear wing propeller detached vortexes 9b in the same direction by a certain distance, so that as shown in fig. 8, vortex interference resistance is reduced, the span length of the rear wings 2b is increased, and the lift-drag ratio is further improved.
The vertical tail 6 is arranged at the rear part of the aircraft body 1 of the rotor aircraft, is mainly used for keeping course and transverse stability in a fixed wing forward flying state, and can be selected and cancelled according to practical application.
The rotor craft of the embodiment of the invention adopts oil-electricity hybrid power, namely, the mechanical energy of the engine is converted into electric energy through the generator, and the propeller driving motor 32 and the lifting propeller driving motor 42 are adopted through the rectification conversion and power distribution system, so that the flight time of the rotor craft of the embodiment of the invention can be increased, and meanwhile, the electric energy transmitted by adopting the cable has the advantages of light weight and flexible arrangement.
The rotor craft provided by the embodiment of the invention has three flight states: vertical take-off and landing, hovering low-speed flight, transition flight and fixed wing forward flight.
Under the low-speed flight state of vertical take-off and landing and hovering, the front wing 2a and the rear wing 2b are located in the approximate vertical direction, vertical operation of the rotorcraft is achieved by simultaneously changing the lift force of the lift paddle units 4 and the propeller units 3, the pitching operation of the rotorcraft is achieved by differentially changing the lift force of the lift paddle units 4 and the propeller units 3 of the front wing 2a and the rear wing 2b, the lift force of the lift paddle units 4 and the propeller units 3 on the left side of the front wing 2a and the rear wing 2b, the lift force of the lift paddle units 4 and the propeller units 3 on the right side of the front wing 2a and the rear wing 2b, and the lift force of the lift paddle units 4 and the propeller units 3 on the right side of the front wing 2a and the rear wing 2b are differentially changed, and course operation is achieved by. Meanwhile, the fine adjustment of the attitude of the rotorcraft can be realized by deflecting the front wing flaperon 201a and the rear wing flaperon 201b by utilizing the downward wash flow of the propeller unit 3 and the lift paddle unit 4.
Under the fixed wing forward flight state, the front wing 2a and the rear wing 2b are located in the approximately horizontal direction, the lift propellers 41 are stopped and folded, the pitching control of the rotor craft is realized by differentially deflecting the front wing flaperon 201a and the rear wing flaperon 201b, the rolling control of the rotor craft is realized by synchronously deflecting the left and right front wing flaperon 201a and the rear wing flaperon 201b, and the course control is realized by differentially adjusting the tension of the left and right side propeller units 3 and coordinately turning.
The transitional transition flight state includes 2 states: the state of transition from vertical take-off and landing and low-speed hovering flight to fixed-wing forward flight, and the state of transition from fixed-wing forward flight to low-speed hovering flight.
In a conversion state, the front wing 2a and the rear wing 2b synchronously tilt to an approximately horizontal direction, and the control in the state is realized by mixing a vertical take-off and landing and hovering low-speed flight control mode and a fixed wing forward flight control mode.
In a transition state, the blades of the lift paddle 41 rotate and expand, the front wing 2a and the rear wing 2b synchronously tilt in an approximately vertical direction, and the control in the state is realized by mixing a vertical take-off and landing and hovering low-speed flight control mode and a fixed wing forward flight control mode.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (13)
1. The utility model provides a high-speed rotor craft of rotor sortable design, its characterized in that, includes fuselage (1), preceding wing (2a), back wing (2b), screw unit (3), lift oar unit (4), undercarriage (5), wherein, preceding wing (2a), back wing (2b) are tilting mechanism, set up at fuselage anterior segment and middle and back end, the undercarriage is installed in fuselage below or on the wing, the screw unit symmetry respectively sets up the both ends at preceding wing (2a), back wing (2b), lift oar unit (4) symmetry sets up in preceding wing (2a), back wing (2b) both sides to be located screw unit (3) inboard, and lift oar unit (4) and screw unit (3) all move towards unanimously.
2. The high-speed rotorcraft with sortable rotors according to claim 1, wherein the lift paddle unit (4) comprises a lift paddle (41) and a lift paddle drive motor (42), the lift paddle drive motor (42) directly drives the lift paddle (41) to rotate, and the lift paddle unit (4) is controlled by changing the rotating speed to adjust the lift force.
3. The high-speed rotorcraft with sortable rotor as claimed in claim 2, wherein the roots of said lifting paddles (41) are connected to the motor shaft by hinges, and the motor shaft rotates to rotate the blades via the hinges during vertical takeoff and landing, and the blades are unfolded around the hinges by centrifugal force of rotation, and the driving motor (42) stops when the blades fly forward, and the blades are folded by resistance of forward flight.
4. High-speed rotorcraft, with rotor-classifiable design, according to claim 3, characterized in that the lift blades (41) are of low-twist-angle, high-lift airfoil design.
5. High-speed rotorcraft, with sortable rotors according to claim 3, wherein the propeller unit (3) comprises a propeller (31) and a propeller drive motor (32), the propeller drive motor (32) directly driving the propeller (31) in rotation.
6. The rotorcraft, with rotor-sortable design, as recited in claim 5, wherein said propellers (31) are of variable pitch design, propeller drive motors (32) are controlled with constant rotational speed, the amount of lift is adjusted by varying the pitch, and two different rotational speeds are used in the vertical takeoff and hover low speed flight condition and in the forward flight condition; in the vertical take-off and landing and hovering low-speed flight states, large rotating speed is adopted to match with small propeller pitch; in the forward flight state, the small rotating speed is matched with the large pitch.
7. The high-speed rotorcraft with classifiable rotor wing design according to claim 3, characterized in that the front wing (2a) and the rear wing (2b) are designed with a high aspect ratio, which is in the range of 10-20.
8. High-speed rotorcraft, with sortable rotor design, according to claim 3, wherein, in the high-speed forward flight condition, the directions of rotation of adjacent rotor units (3), lift paddle units (4) are opposite, so that at the front wing (2a), the front wing tip vortex (8a) and the front wing propeller deswirler vortex (9a) are opposite.
9. The high-speed rotorcraft with sortable rotor design according to claim 3, wherein wingtip winglets (7) are symmetrically disposed at the wingtips of the rear wings (2b), and the wingtip winglets (7) can separate the wingtip vortex (8b) and the rear wing propeller detached vortex (9b) in the same direction by a certain distance in the fixed-wing forward flight state.
10. The high-speed rotorcraft with sortable rotors according to any one of claims 1 to 9, wherein the control of the tilting of the front and rear wings causes the tilting of the rotor units on the front and rear wings, and then the control of the operating states of the lift paddle unit and the propeller unit in the rotor units, respectively, enables vertical take-off and landing and high-speed forward flight and switching between them.
11. The high-speed rotorcraft with sortable rotor design according to claim 10, wherein the front wing (2a) and the rear wing (2b) are in an approximately vertical orientation during the vertical takeoff and landing and hover low-speed flight conditions, vertical maneuvering of the rotorcraft is achieved by simultaneously changing the lift magnitudes of the lift paddle units (4) and the propeller units (3), pitch maneuvering of the rotorcraft is achieved by differentially changing the lift magnitudes of the lift paddle units (4, 3) of the front wing (2a) and the propeller units (3) of the rear wing (2b) and the lift paddle units (4, 3) of the rear wing (2b), roll maneuvering is achieved by differentially changing the lift magnitudes of the lift paddle units (4, 3) of the left side of the front wing (2a) and the rear wing (2b) and the lift paddle units (4, 3) of the right side of the front wing (2a) and the rear wing (2b), the course control is realized by differentially changing the lift force of the lift paddle unit 4 and the propeller unit (3) which are in the same direction of rotation.
12. The high-speed rotorcraft with sortable rotor design according to claim 10, wherein, in the fixed-wing forward flight state, the front wing (2a) and the rear wing (2b) are positioned in an approximately horizontal direction, the lift rotor (41) blades are stall folded, the rotorcraft (0) pitch control is achieved by differentially deflecting the front wing flap (201a) and the rear wing flap (201b), the rotorcraft (0) roll control is achieved by synchronously deflecting the left and right front wing flap (201a) and the rear wing flap (201b), and the course control is achieved by differentially adjusting the tension of the left and right propeller units (3) and coordinating the turning.
13. A high-speed rotary-wing aircraft with rotor-type design according to claim 10, wherein the transitional transition flight state comprises 2 states: the state of transition from vertical take-off and landing and hovering low-speed flight to fixed wing forward flight and the state of transition from fixed wing forward flight to hovering low-speed flight;
in a conversion state, the front wing (2a) and the rear wing (2b) synchronously tilt to an approximately horizontal direction, and the control in the state is realized by mixing a vertical take-off and landing and hovering low-speed flight control mode and a fixed wing forward flight control mode;
in a transition state, the blades of the lifting propeller (41) are rotated and unfolded, the front wing (2a) and the rear wing (2b) synchronously tilt to the approximate vertical direction, and the control in the state is realized by mixing a vertical take-off and landing and hovering low-speed flight control mode and a fixed wing forward flight control mode.
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| CN201911229120.8A CN110901890A (en) | 2019-12-04 | 2019-12-04 | High-speed rotor craft with rotor capable of being designed in classification mode |
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| CN201911229120.8A CN110901890A (en) | 2019-12-04 | 2019-12-04 | High-speed rotor craft with rotor capable of being designed in classification mode |
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| CN112678149A (en) * | 2021-01-12 | 2021-04-20 | 西北工业大学太仓长三角研究院 | Multi-body active variable configuration distributed propeller aircraft |
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