CN204223177U - A kind of vertically taking off and landing flyer - Google Patents
A kind of vertically taking off and landing flyer Download PDFInfo
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- CN204223177U CN204223177U CN201420601917.2U CN201420601917U CN204223177U CN 204223177 U CN204223177 U CN 204223177U CN 201420601917 U CN201420601917 U CN 201420601917U CN 204223177 U CN204223177 U CN 204223177U
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Abstract
The utility model relates to a kind of vertically taking off and landing flyer, comprise fuselage (1), main wing, the main thrust device (2) verted can be carried out between level attitude and upright position, the reclining device that main thrust device is verted, for controlling the attitude-control device of flight attitude; Wing comprises left half wing and right half wing, and main thrust device uses heat engine as engine installation; It is characterized in that: attitude-control device is made up of at least two posture adjusting devices (4), power module (5), governor module (9), flight control system (6); Posture adjusting device is made up of motor (4a), the screw propeller be connected with power of motor or ducted fan (4b); Have at least a posture adjusting device to be arranged on left half wing, and have at least a posture adjusting device to be arranged on right half wing.Make the physical construction of aircraft be simplified like this, react more rapidly sensitive and be more easy to operation, thus make the gesture stability of aircraft more stable.
Description
Technical field
The utility model relates to a kind of vertically taking off and landing flyer aircraft, particularly relates to a kind of vertically taking off and landing flyer that can switch thrust direction.
Background technology
The jet plane of tilt rotor aircraft, tilting duct fan (Tilt Ducted Fan) aircraft, vertical takeoff and landing is the common vertically taking off and landing flyer that can switch thrust direction, this aircraft is provided with wing, thrust direction can also be switched in the vertical direction and between horizontal direction.When thrust direction is arranged on vertical direction, aircraft can vertically landing as helicopter, and when thrust direction is arranged on horizontal direction, aircraft can fly again as fixed wing aircraft, has had both the advantage of helicopter and fixed-wing.The vertically taking off and landing flyer that the jet plane etc. of tilt rotor aircraft, tilting duct fan (Tilt Ducted Fan) aircraft, vertical takeoff and landing can switch thrust direction needs when realizing vertical takeoff and landing to rely on attitude-control device to keep the balance of aircraft, need to rely on the device of gesture stability to realize the control of flight attitude of the rolling of aircraft vertical landing process, pitching, driftage, and realize longitudinal direction and horizontal flight.
Traditional helicopter is provided with auto-bank unit, and auto-bank unit is made up of two vital partss: a non rotating ring and a swivel eye.Non rotating ring is installed in rotor shaft, and is connected apart from operating control with total with feathering by a series of pull bar.It can tilt to any direction, also can vertically movement.Swivel eye is installed on non rotating ring by bearing, can rotate together with rotor shaft.Toggle is for ensureing swivel eye synchronous rotary together with blade.Anti-torque arm is then for stoping non rotating ring to rotate.These two rings to tilt and up and down as a cell cube simultaneously.Swivel eye is connected with distance-variable rocker arm by pull bar.Helicopter handles auto-bank unit by cyclic pitch control device to make rotor blade feathering realize the control of pitch attitude and roll attitude, also can control longitudinal velocity and cross velocity; Auto-bank unit synchronous change rotor blade pitch is handled for controlling the vertical speed of helicopter apart from operating control by total.Traditional helicopter is also provided with tail-rotor for balancing rotor reaction torque, total apart from controlling helicopter yawing velocity by changing tail-rotor.
Respectively be connected with a machinery space by the V-22 osprey formula tilt rotor aircraft of American Bell Incorporated and Boeing's collaborated design manufacture at the both ends of wing, machinery space can vert between level attitude and upright position, and machinery space is connected with rotor.The flight attitude of V-22 tilt rotor aircraft controls with helicopter similar, is also to make rotor blade feathering and synchronous change rotor blade pitch for controlling aircraft flight attitude by cyclic pitch control device and total distance operating control.V-22 tilt rotor aircraft by least one machinery space that verts, thus produces longitudinal thrust differential between rotor, for controlling the yawing velocity of aircraft.Because the device for the gesture stability of helicopter or tilt rotor aircraft is all adopt complicated machinery parts, thus high to making material requirements, production difficulty large, it is complicated to install, maintenance cost is high; And the device of this type of gesture stability is only applicable to have employed the rotor that is connected with the engine power aircraft as thruster, such aircraft adopts turboaxle motor or piston engine mostly.
Tilting duct fan (Tilt Ducted Fan) aircraft has the merits and faults the same with tilt rotor aircraft, the X-22 tilting duct fan aircraft of such as Bell Co., screw propeller is placed in duct, constitute ducted fan (Ducted Fan), at first view with conventional propeller not too large difference, but the air-flow inside and outside duct has velocity contrast, make great efforts the effect of principle shellfish under, height air-flow in duct can drag the low speed flow outside duct, can produce the extra-push model than air current flow as many as 50% in duct.Bel X-22 adopts four turboshaft engines, is arranged in vertical fin both sides between two, by crosslinked synchronizing shaft, drives all fourth officer ducted fans.Be provided with pneumatic control as attitude-control device with V-22 osprey formula tilt rotor aircraft unlike each duct outlet of, X-22 tilting duct fan aircraft, be used to provide vertical takeoff and landing (VTOL) peace fly in flight attitude control.But the cost that due to the mechanical part that this pneumatic control is a kind of complexity, this mechanical part is produced, safeguard is high, and easily there was a mechanical failure; In addition, utilize pneumatic control to control the taking off of aircraft, land, aircraft balance when hovering is poor and sensitivity is lower.
" sparrow hawk " formula fighter plane developed by Huo Ke Aircraft Company of Britain and Bristol aero-engine company, the groundwork that its realizes vertical/short take-off and landing (STOL) is that " flying horse " fanjet of employing 4 swivel nozzles provides lift required when rising and falling and transition flight and the thrust needed for normal flight.Two pairs of spouts are symmetrical in the center of gravity of airplane, split fuselage both sides, by joystick and the engine power control arm of spout maneuvering system, realize the size and Orientation of the control break thrust of engine thrust vector.Head, fuselage and wingtip are equipped with the jet counteraction maneuvering system from engine bleed, in order to control flight attitude when vertical, short take-off and landing (STOL) or hovering, and also can in order to improve road-holding property during stall in normal flight.Because the device for the gesture stability of vertical takeoff and landing jet plane is also adopt complicated mechanical part, particularly swivel nozzle, not only high to the material requirements made but also production difficulty large, so improve the cost produced and safeguard; And the device of this type of gesture stability be only applicable to have employed lift fan that vector spout or lifting driving engine be even connected with engine power by driving device as normal thrust device aircraft, this type of aircraft adopts special turbofan or turbojet engine.
The attitude-control device that the flight attitude that the vertically taking off and landing flyer of the above-mentioned type is used as controls is all adopt complicated physical construction, and a large amount of mechanical parts not only increases the difficulty of manufacture, the production also improved and the cost of maintenance; And this type of adopts the aircraft underaction of attitude-control device of complex mechanical structure and not easy to operate.
Summary of the invention
The technical problems to be solved in the utility model is to provide a kind of vertically taking off and landing flyer that do not have the attitude-control device of complex mechanical structure, that can control flight attitude more neatly.
For solving the problems of the technologies described above, vertically taking off and landing flyer of the present utility model comprises fuselage, main wing, can carry out the main thrust device verted between level attitude and upright position, the reclining device that main thrust device is verted, for controlling the attitude-control device of flight attitude; Main wing comprises left half wing and right half wing, and main thrust device uses heat engine as engine installation; Wherein, attitude-control device is made up of power module, at least two posture adjusting devices, governor module, flight control systems; Posture adjusting device is made up of motor, the screw propeller be connected with power of motor or ducted fan (Ducted Fan); Governor module is used for the horsepower output of the motor regulating each posture adjusting device respectively, and governor module accepts the control of flight control system; Power module is used for providing power supply; Have at least a posture adjusting device to be arranged on left half wing, and have at least a posture adjusting device to be arranged on right half wing.
By being respectively arranged with posture adjusting device at the left half wing of main wing and right half wing, flight control system is implemented to control to governor module, governor module regulates the horsepower output often organizing motor respectively, the difference of the thrust produced by regulating each posture adjusting device, realizes the control to aircraft roll attitude; The vector component that it can be made to produce vertical direction thrust and longitudinal thrust by the main thrust device that verts realizes controlling the balance of pitch attitude.Such benefit is, have employed and uses the attitude-control device of electric energy can remove original complicated mechanical part from, the physical construction of aircraft is simplified.The reaction of the attitude-control device using motor as engine installation controlled by flight control system is more rapidly sensitive and be more easy to operation, thus makes the gesture stability of aircraft more stable.
As the further improvement of a kind of vertically taking off and landing flyer of the utility model, posture adjusting device is arranged on the end of main wing.The screw propeller of posture adjusting device or ducted fan are arranged on the left half wing of main wing, the end of right half wing, the screw propeller of posture adjusting device or ducted fan can be made away from the center of gravity of aircraft, can improve the efficiency of posture adjusting device gesture stability like this.
As another improvement of a kind of vertically taking off and landing flyer of the utility model, this aircraft is also provided with head or the afterbody that at least one posture adjusting device is placed at aircraft.Posture adjusting device can be connected to fuselage or be connected to head or the afterbody of aircraft by the mechanism such as wing, adapter shaft.Can be controlled by the pitch attitude of posture adjusting device to aircraft like this; The reaction of the attitude-control device using motor as engine installation controlled by flight control system is more rapidly sensitive and be more easy to operation, thus makes the gesture stability of aircraft more stable.
Further improve, this aircraft is also provided with tailplane, and tailplane comprises port tailplane and starboard tailplane; Each posture adjusting device is separately positioned on the end of port tailplane, starboard tailplane, left half wing, right half wing.Screw propeller or ducted fan that arranging like this can make posture adjusting device, away from the center of gravity of aircraft, can improve the efficiency of posture adjusting device gesture stability like this.
As another improvement of a kind of vertically taking off and landing flyer of the utility model, main wing is bi-wing configuration, and wherein the first main wing is placed in the first half section of aircraft near head side, and the second main wing is placed in the second half section of aircraft near tail side; Each half wing of first main wing and the second main wing is respectively arranged with posture adjusting device.As further improvement, each posture adjusting device is separately positioned on the end of each half wing of the first main wing, the second main wing.As further improving, the first main wing can also be set to buzzard-type wing.By adopting the main wing of bi-wing configuration, stability when can improve aircraft Longitudinal Flight and increase fixed-wing lift; By adopting the aircraft of the main wing of bi-wing configuration, its main thrust device producing normal thrust can concentrate on immediate vicinity with the position of the wing producing fixed-wing lift, main thrust device does not conflict with wing position, and main thrust Plant arrangement can be made convenient; In addition the efficiency that the screw propeller of posture adjusting device or ducted fan are separately positioned on the first main wing, posture adjusting device gesture stability can be improved in the end of each half wing of the second main wing.First main wing is set to buzzard-type wing, and the second main wing is set to maneuvering performance and the 1ift-drag ratio that swept wing can increase aircraft, can also increase the space between the first main wing and the second main wing.
As the further improvement of a kind of vertically taking off and landing flyer of the utility model, can be flexibly connected posture adjusting device, screw propeller or ducted fan are set to vert between level attitude and upright position; Posture adjusting device also comprises reclining device.As further improving, power module comprises electric power storage device, electrical generator, electrical generator and electric power storage device electrical hookup; Screw propeller or the ducted fan of posture adjusting device are connected with generator power; Motor comprises rotor and stator, and the rotor of motor doubles as the rotor of electrical generator.Like this can by the posture adjusting device that verts, the direction of the thrust that posture adjusting device is produced can switch in the vertical direction and between horizontal direction, the utilization ratio of the posture adjusting device of raising; By the posture adjusting device that verts, driftage can also be carried out and controls.Screw propeller or the ducted fan of posture adjusting device are connected with generator power, screw propeller or ducted fan can be utilized like this to generate electricity as the power input device of electrical generator, and charge to power module.
As the further improvement of a kind of vertically taking off and landing flyer of the utility model, have 2 groups of main thrust devices to be separately positioned on the left and right sides of middle fuselage, main thrust device is any one in fanjet, turbojet engine, the rotor of power connecting engine or ducted fan.The top, stage casing of fuselage is provided with protrusion, and main thrust device is connected to protrusion.There are two groups of main thrust devices to be connected to the left and right sides in the stage casing of fuselage, main thrust device can be made more to concentrate on the immediate vicinity of aircraft, the stability of aircraft flight can be improved; Reducing the risk because causing during left and right main thrust device generation thrust differential simultaneously, making aircraft safer.The top, stage casing of fuselage is provided with protrusion, and main thrust device is connected to protrusion, and main thrust device can be made to vert for during horizontality, main thrust device can not touch ground, makes the mode landing that aircraft can run with cunning.
Accompanying drawing explanation
Below in conjunction with the drawings and specific embodiments, the utility model is described in further detail.
Fig. 1 is the attitude-control device fundamental diagram of a kind of vertically taking off and landing flyer of the utility model.
Fig. 2 is the structural representation of a kind of vertically taking off and landing flyer of the utility model.
Fig. 3 is the schematic diagram of the posture adjusting device connection reclining device of a kind of vertically taking off and landing flyer of the utility model.
Fig. 4 is the schematic diagram that the top of the middle fuselage of a kind of vertically taking off and landing flyer of the utility model is provided with protrusion.
Fig. 5 be a kind of vertically taking off and landing flyer of the utility model connect wing and screw propeller schematic diagram by the axis of elongation.
Detailed description of the invention
A kind of vertically taking off and landing flyer of the utility model comprises fuselage 1, main wing, can carry out the main thrust device 2 verted between level attitude and upright position, the reclining device that described main thrust device 2 is verted, for controlling the attitude-control device of flight attitude; Described main wing comprises left half wing and right half wing, and described main thrust device 2 uses heat engine as engine installation; It is characterized in that: described attitude-control device is made up of power module 5, at least two posture adjusting devices 4, governor module 9, flight control systems 6; Described posture adjusting device 4 is made up of motor 4a, the screw propeller be connected with motor 4a power or ducted fan 4b; Described governor module 9 is for regulating the horsepower output of the motor 4a of each posture adjusting device 4 respectively, and described governor module 9 accepts the control of described flight control system 6; Described power module 5 is for providing power supply; Have at least the posture adjusting device 4 described in be arranged on described left half wing, and have at least the posture adjusting device 4 described in be arranged on described right half wing.Posture adjusting device 4 can be arranged on the end of main wing.
Power module 5, for providing power supply for motor 4a, can also provide power supply for power devices such as governor module 9, flight control systems 6.Power module 5 can be electric power storage device, such as rechargeable battery, super capacitor, nuclear battery etc., and rechargeable battery can adopt lithium ion battery, also can be rechargeable battery such as nickel-cadmium cell, Ni-MH battery, the lithium iron battery etc. of other type; Power module 5 can be also power generation assembly, comprises electrical generator is connected electrical generator power input device with power, and power input device can be heat engine or flabellum; Power module 5 also can be the electric power storage device being connected with power generation assembly.Motor 4a adopts brushless motor optimum, but is not limit, and also can be the motor of other type, as brush motor, alternating current dynamo, DC machine, monophase machine, three phase electric machine etc.Governor module 9 can adopt and comprise the device that electronic governor electronic speed controller, DC motor speed-regulating device, speed regualtion of AC motor device etc. can regulate output power of motor; Governor module 9 can for the module combined with motor 4a or miscellaneous equipment, and also can be independently governor, can be that single group exports the governor controlling single motor, also can be that many groups export the governor controlling multiple motor respectively; The type of governor should with the type matching of motor 4a, such as brushless motor adopts brushless electronic governor, brush motor to adopt brush electronic governor etc.Governor module 9 accepts flight control system 6 and controls, and governor module 9 can be connected with flight control system 6 signal or electrically connect; Flight control system 6 is the autonomous cruise speed systems carrying out flight attitude and kinematic parameter enforcement control, and flight control system 6 can adopt electronic flight control system, digital flight control system, fly-by-wire etc. to possess the flight control system of automatic control ability; Flight control system 6 can be utilized to gather flight attitude data, analyzing and processing data, automatically send control signal, controlled the horsepower output of motor 4a by governor module 9, thus realize the gesture stability to aircraft.
The screw propeller of posture adjusting device 4 or ducted fan can form reaction torque when rotated, can take balance the setting of reaction torque or arrange the device of balance reaction torque.Can adopt the screw propeller of each posture adjusting device 4 or the hand of rotation of ducted fan be set to forward and oppositely arrange in pairs or groups between two, setting that the coaxial positive and negative pair of oar, inclination posture adjusting device 4 etc. that adopt reaction torque to offset can balance reaction torque.The device of balance reaction torque can be tail-rotor, be arranged on the rudder face of wind underside, also can be the device of other type, the NOTAR tail-rotor that such as Boeing MD600N helicopter adopts, namely forms the device of anti-twisted power by the favourable interaction of jet injection and rotor downwash; The device of balance reaction torque is optional.The method to set up of balance reaction torque can also be utilized or the device balancing reaction torque is set and realize driftage control.Screw propeller mentioned by the utility model refers to that rotating turn of engine power conversion is in atmosphere the device of propulsive force, and fan, flabellum, rotor etc. also belong to the scope of screw propeller described in the utility model.
So-called thruster refers to device engine power being converted to thrust, and main thrust device 2 can be utilized to provide main thrust for aircraft.Main thrust device 2 can be rotor, the ducted fan of power connecting engine, and also can be other thruster, such as vector engine, fanjet etc. can provide the thruster of normal thrust; When employing rotor or ducted fan, driving engine can adopt turboaxle motor or piston engine; Main thrust device 2 quantity is not limit, and can be one group, two groups or many groups.Main thrust device 2 adopts when the rotor of power connecting engine or ducted fan can balance the method for reaction torque to balance reaction torque with reference to above-mentioned posture adjusting device 4, can also the reaction torque of comprehensive posture adjusting device 4 utilize said method to balance reaction torque, not remake repeat specification at this; Equally, when main thrust device 2 is rotor or the ducted fan of employing power connecting engine, the device of balance reaction torque is optional.The method to set up of balance reaction torque can also be utilized or the device balancing reaction torque is set and realize driftage control.Although main thrust device 2 produce vertical lift make a concerted effort to depart from aircraft center of gravity place time attitude-control device can be relied on to realize the balance of aircraft, but the burden of attitude-control device can be increased like this, so the position that can act on aircraft cardinal principle center of gravity place with joint efforts of the lift that the preferred connection location of main thrust device 2 can be all main thrust devices 2 to be produced, the position that namely main thrust device 2 is arranged can make aircraft balance substantially; Certainly, this is one of them is preferably and not limit.
Above mentioned " posture adjusting device 4 can be arranged on the end of main wing ", mainly refers to that the screw propeller of posture adjusting device 4 or ducted fan 4b are arranged on the end of main wing.Can be that motor 4a is connected with screw propeller or ducted fan 4b by output shaft or driving device, motor 4a and screw propeller or ducted fan 4b be arranged on the end of main wing simultaneously; Or motor 4a is connected with screw propeller or ducted fan 4b by drivings device such as transmission shafts, motor 4a is arranged on other position of aircraft, and only screw propeller or ducted fan 4b are connected to the end of main wing; " part of posture adjusting device 4 " or " posture adjusting device 4 whole " is arranged on the end of main wing, and these two kinds of simple conversion all belong within the spirit and scope of the utility model " posture adjusting device 4 is arranged on the end of main wing " scheme.The position that main wing is connected with fuselage is root, and the end of above mentioned main wing refers to the outermost end of the main wing away from root, and the statement such as " taper of main wing, tip " all belongs within the spirit and scope of the utility model " end of main wing ".
Posture adjusting device 4 can be embedded in main wing, also can be connected with main wing outside main wing, but is embedded in main wing the restriction receiving main wing size due to posture adjusting device 4, so be connected for preferred scheme outside main wing with main wing with posture adjusting device 4; Certainly, this just preferably and and unrestricted.A kind of vertically taking off and landing flyer of the utility model shown in Fig. 5 connect wing and screw propeller schematic diagram by the axis of elongation, when posture adjusting device 4 adopts screw propeller to be connected with motor 4a, the axis of elongation 14 can be adopted to connect wing and screw propeller, the downwash flow that object makes screw propeller produce not stop by wing; The axis of elongation 14 can for meeting the shapes such as aerodynamic cylindrical, rhombus.
As the further improvement of a kind of vertically taking off and landing flyer of the utility model, this aircraft is also provided with head or the afterbody that at least one posture adjusting device 4 is placed at aircraft.Posture adjusting device 4 can be connected directly between fuselage 1, or is connected with the head of aircraft or the fuselage 1 of afterbody by mechanisms such as empennage, canard, the axis of elongation 14.As further improvement, this aircraft is also provided with tailplane, and tailplane comprises port tailplane and starboard tailplane; Each posture adjusting device 4 is separately positioned on the end of port tailplane, starboard tailplane, left half wing, right half wing.
The structural representation of a kind of vertically taking off and landing flyer of the utility model shown in Fig. 2, main wing can be bi-wing configuration, and wherein the first main wing 3a is placed in the first half section of aircraft near head side, and the second main wing 3b is placed in the second half section of aircraft near tail side; Each half wing of first main wing 3a and the second main wing 3b is respectively arranged with posture adjusting device 4.As further improvement, each posture adjusting device 4 can be separately positioned on the end of each half wing of the first main wing 3a, the second main wing 3b.First main wing 3a can also be set to buzzard-type wing.Each half wing refers to each left half wing, right half wing.
As the further improvement of a kind of vertically taking off and landing flyer of the utility model, can be flexibly connected posture adjusting device 4, screw propeller or ducted fan 4b are set to vert between level attitude and upright position; Posture adjusting device 4 also comprises reclining device.Servoactuator 11 can be adopted as reclining device, and servoactuator 11 can be connected with flight control system 6 signal or electrically connect; Servoactuator refers to a kind of actuating unit of flight control system, also known as steering wheel; It can carry out directly (as duplicated control actuator type) or indirectly (as auxiliary elevator type) control according to each controlsurface of the output command of flight control computer to aircraft; Servoactuator has polytype, can adopt electro-hydraulic servo actuator, also can adopt the servoactuator of other type, such as electrodynamic type servoactuator or pneumatic type servoactuator etc.Also motor can be adopted to connect the devices such as gear cluster as reclining device.Posture adjusting device 4 can be flexibly connected by the device such as barring gear 13 or hinge.
The posture adjusting device of a kind of vertically taking off and landing flyer of the utility model shown in Fig. 3 connects the schematic diagram of reclining device, nacelle 10 can be provided with, nacelle 10 is for loading motor 4a or driving device, and motor 4a is connected with screw propeller by motor output shaft or is connected with screw propeller by driving device; Nacelle 10 is flexibly connected with wing by barring gear 13, certainly, can also realize being flexibly connected of nacelle and wing by devices such as hinges; Nacelle 10 is operably connected with servoactuator 11, and servoactuator 11 can directly be connected with nacelle 10, also can be connected with nacelle 10 by bent axle 12, thus realize verting of posture adjusting device 4.Certainly, also can not arrange nacelle 10, can directly be flexibly connected motor 4a and wing, motor 4a is connected with screw propeller or ducted fan 4b by motor output shaft; Be operatively connected by motor 4a and servoactuator 11, thus realize verting of screw propeller or ducted fan 4b.When posture adjusting device 4 adopts ducted fan to be connected with motor 4a power, duct can be connected by barring gear 13 or articulate, duct be operatively connected with servoactuator 11, thus realize verting of ducted fan.
When screw propeller or ducted fan 4b vert, motor 4a not necessarily will vert with screw propeller or ducted fan 4b.Such as motor 4a is connected with screw propeller or ducted fan 4b by drivings device such as transmission shafts, and motor 4a is arranged on different positions from screw propeller or ducted fan 4b, like this can only tilted propeller or ducted fan 4b; When motor 4a is connected with screw propeller or ducted fan 4b by motor output shaft, motor 4a can vert with screw propeller or ducted fan 4b simultaneously; This simple conversion still belongs within the spirit and scope of the utility model scheme.
As the further improvement of a kind of vertically taking off and landing flyer of the utility model, power module 5 comprises electric power storage device, electrical generator, electrical generator and electric power storage device electrical hookup; Screw propeller or the ducted fan 4b of posture adjusting device 4 are connected with generator power; Motor 4a comprises rotor and stator, and the rotor of motor 4a doubles as the rotor of electrical generator.
As the further improvement of a kind of vertically taking off and landing flyer of the utility model, have two groups of main thrust devices 2 to be separately positioned on the left and right sides in fuselage 1 stage casing, main thrust device 2 is any one in fanjet, turbojet engine, the rotor of power connecting engine or ducted fan.Fig. 4 is the schematic diagram that the top of the middle fuselage of a kind of vertically taking off and landing flyer of the utility model is provided with protrusion, and the top, stage casing of fuselage 1 can be provided with protrusion 7, and main thrust device 2 is connected to protrusion 7.Protrusion 7 is raised in fuselage 1 top, for promoting the height of main thrust device 2; Protrusion 7 can be arranged to meet aerodynamic stream line pattern.
When main thrust device 2 is any one in the ducted fan of fanjet, turbojet engine, power connecting engine, main thrust device 2 can be directly connected with fuselage 1 by driving engine or duct.When main thrust device 2 is the rotor of power connecting engine, main thrust device 2 can be connected with fuselage 1 by mechanisms such as short limb 8 or adapter shafts.Main thrust device 2 can also be provided with nacelle, nacelle is for loading driving engine or transmission device; Can by barring gear 13 or hinged flexible connection driving engine or duct or nacelle, then being operatively connected by servoactuator and driving engine or nacelle or duct, thus realize verting of main thrust device 2.
The position that wing is connected with fuselage is root, the utility model mention main wing the end of end or tailplane refer to the outermost end of the wing away from root, the statement such as " taper, the tip " of main wing or tailplane all belongs within the spirit and scope of " end " of the utility model main wing or tailplane.The statement of the position about posture adjusting device 4 setting mentioned by the utility model " being placed in " or " being arranged on " includes the scope of " being embedded within it " and " being connected to outside it "; The position not changing in fact aircraft at posture adjusting device 4 described in the utility model by directly or indirectly connecting posture adjusting device 4 all still belongs in the scope of technical solutions of the utility model.
As the further improvement of the utility model vertically taking off and landing flyer, main wing, tailplane can be provided with aileron or wing flap, or aileron and wing flap are all arranged simultaneously; The aileron of the second main wing can also double as elevating rudder.Further, aircraft also can also be provided with vertical tail, and vertical tail can also be provided with yaw rudder; Damper can also be housed in rudder control system, phenomenon is waved in the driftage occurred in high speed flight at high altitude to prevent aircraft, and yaw rudder and damper are all optional.Aircraft is also provided with landing gear, and landing gear can also comprise load pillar, bumper, jack, front-wheel shimmy-damper and wheel steering system.
It should be noted last that, above embodiment is only in order to illustrate the technical solution of the utility model and unrestricted, although be described in detail the utility model with reference to preferred embodiment, those of ordinary skill in the art is to be understood that, can modify to the technical solution of the utility model or equivalent replacement, and not depart from the spirit and scope of technical solutions of the utility model; Any simple modification done above embodiment according to technical spirit of the present utility model, equivalent variations and modification, all still belong in the scope of technical solutions of the utility model.
Claims (10)
1. a vertically taking off and landing flyer, comprise fuselage (1), main wing, the main thrust device (2) verted can be carried out between level attitude and upright position, the reclining device that described main thrust device (2) is verted, for controlling the attitude-control device of flight attitude; Described main wing comprises left half wing and right half wing, and described main thrust device (2) uses heat engine as engine installation; It is characterized in that: described attitude-control device is made up of power module (5), at least two posture adjusting devices (4), governor module (9), flight control systems (6); Described posture adjusting device (4) is made up of motor (4a), the screw propeller be connected with motor (4a) power or ducted fan (4b); Described governor module (9) is for regulating the horsepower output of the motor (4a) of each posture adjusting device (4) respectively, and described governor module (9) accepts the control of described flight control system (6); Described power module (5) is for providing power supply; Have at least the posture adjusting device described in (4) to be arranged on described left half wing, and have at least the posture adjusting device described in (4) to be arranged on described right half wing.
2. vertically taking off and landing flyer according to claim 1, is characterized in that: described posture adjusting device (4) is arranged on the end of described main wing.
3. vertically taking off and landing flyer according to claim 1, is characterized in that: this aircraft posture adjusting device (4) be also provided with described at least one is placed at head or the afterbody of described aircraft.
4. vertically taking off and landing flyer according to claim 3, is characterized in that: this aircraft is also provided with tailplane, and described tailplane comprises port tailplane and starboard tailplane; Described each posture adjusting device (4) is separately positioned on the end of described port tailplane, starboard tailplane, left half wing, right half wing.
5. vertically taking off and landing flyer according to claim 1, it is characterized in that: described main wing is bi-wing configuration, wherein the first main wing (3a) is placed in the first half section of aircraft near head side, and the second main wing (3b) is placed in the second half section of aircraft near tail side; Each half wing of described first main wing (3a) and described second main wing (3b) is respectively arranged with described posture adjusting device (4).
6. vertically taking off and landing flyer according to claim 5, is characterized in that: described each posture adjusting device (4) is separately positioned on the end of each half wing of described first main wing (3a), the second main wing (3b).
7. according to the arbitrary vertically taking off and landing flyer described in claim 1 to 6, it is characterized in that: the posture adjusting device (4) described in flexible connection, described screw propeller or ducted fan (4b) are set to vert between level attitude and upright position; Described posture adjusting device (4) also comprises reclining device.
8. vertically taking off and landing flyer according to claim 7, is characterized in that: described power module (5) comprises electric power storage device, electrical generator, described electrical generator and described electric power storage device electrical hookup; Screw propeller or the ducted fan (4b) of described posture adjusting device (4) are connected with described generator power; Described motor (4a) comprises rotor and stator, and the rotor of described motor (4a) doubles as the rotor of described electrical generator.
9. vertically taking off and landing flyer according to claim 7, it is characterized in that: have 2 groups of main thrust devices (2) to be separately positioned on the left and right sides in fuselage (1) stage casing, described main thrust device (2) is fanjet, any one in the rotor of turbojet engine, power connecting engine or ducted fan.
10. according to the arbitrary vertically taking off and landing flyer described in claim 1 to 6, it is characterized in that: have 2 groups of main thrust devices (2) to be separately positioned on the left and right sides in fuselage (1) stage casing, described main thrust device (2) is fanjet, any one in the rotor of turbojet engine, power connecting engine or ducted fan.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201420601917.2U CN204223177U (en) | 2014-10-19 | 2014-10-19 | A kind of vertically taking off and landing flyer |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201420601917.2U CN204223177U (en) | 2014-10-19 | 2014-10-19 | A kind of vertically taking off and landing flyer |
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| CN204223177U true CN204223177U (en) | 2015-03-25 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104908928A (en) * | 2015-06-23 | 2015-09-16 | 白立安 | Ground effect aircraft |
| CN106965928A (en) * | 2017-03-08 | 2017-07-21 | 贾杰 | The rotatable wing vertically taking off and landing flyer of multistage |
| CN110162079A (en) * | 2019-07-16 | 2019-08-23 | 江苏集萃智能制造技术研究所有限公司 | A kind of Self-balance Control System of manned whirlpool spray aircraft |
-
2014
- 2014-10-19 CN CN201420601917.2U patent/CN204223177U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104908928A (en) * | 2015-06-23 | 2015-09-16 | 白立安 | Ground effect aircraft |
| CN106965928A (en) * | 2017-03-08 | 2017-07-21 | 贾杰 | The rotatable wing vertically taking off and landing flyer of multistage |
| CN110162079A (en) * | 2019-07-16 | 2019-08-23 | 江苏集萃智能制造技术研究所有限公司 | A kind of Self-balance Control System of manned whirlpool spray aircraft |
| CN110162079B (en) * | 2019-07-16 | 2019-10-29 | 江苏集萃智能制造技术研究所有限公司 | A kind of Self-balance Control System of manned whirlpool spray aircraft |
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