CN205098474U - Duct formula aircraft that verts with VTOL function - Google Patents

Duct formula aircraft that verts with VTOL function Download PDF

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Publication number
CN205098474U
CN205098474U CN201520925229.6U CN201520925229U CN205098474U CN 205098474 U CN205098474 U CN 205098474U CN 201520925229 U CN201520925229 U CN 201520925229U CN 205098474 U CN205098474 U CN 205098474U
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CN
China
Prior art keywords
wing
hatchcover
aircraft
rotor
drive link
Prior art date
Application number
CN201520925229.6U
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Chinese (zh)
Inventor
陈佳伟
Original Assignee
陈佳伟
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Publication date
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Priority to CN201520925229.6U priority Critical patent/CN205098474U/en
Application granted granted Critical
Publication of CN205098474U publication Critical patent/CN205098474U/en

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Abstract

The utility model provides a duct formula aircraft that verts with VTOL function, include: fuselage, preceding wing, back wing, rotary machine pterygoid lamina, rotor and rotor adjustment mechanism vert, rotary machine pterygoid lamina hinge dress is at the opening part of back wing, and the rotor that verts is adorned admittedly on blade axis, and blade axis is rotatory for the drive of rotor adjustment mechanism, and the waist is equipped with the duct of installation duct screw, installs cabin cover under with in the upper and lower wind gap department of duct. The wing tip screw is at the in -process that verts, and the rotational speed through the duct screw increases the lift supply, makes the controllability of aircraft gesture in the conversion process. Be convenient for carry out quick adjustment to the flight gesture of aircraft through adjusting the ducted fan rotational speed to the different flight environment of adaptation. Upper and lower cabin cover is closed cabin cover under the aircraft mode of cruising, reduces the flat resistance that flies, improves the flying speed. Rotor adjustment mechanism operation in -process motor does not produce diastema and vibrations, and overall stability can effectual promotion.

Description

The culvert type with vertical takeoff and landing function verts aircraft
Technical field
The utility model belongs to aviation aircraft field, specifically relates to a kind of culvert type with vertical takeoff and landing function and to vert aircraft.
Background technology
The birth of vertical takeoff and landing technology is mainly because the deficiency of aircraft rolling start mode, and the performance particularly in all previous war, allows the vertical takeoff and landing of aircraft enter the sight line of people.The war such as World War II and Mideast Asian war has directly allowed people experience to the attack on enemy airport needs the weak point of the sliding race formula aircraft of runway, and cold war is then the catalyst of vertical takeoff and landing technology.In five sixties after World War II, under the shade very likely breaking out nuclear war, fears are entertained that there is the situation that general nuclear warfare damages airport, conventional airplane cannot be set out, so expedited the emergence of the vertical takeoff and landing technology of fixed wing aircraft.The dependence that vertical take-off and landing aircraft (VTOL aircraft) reduces or substantially broken away from runway, only need very little level land just can rise sheer from level ground and vertical landing, so aircraft can decentralized configuration in war, be convenient to launch an attack flexibly, shift and pretend hidden, not easily found by enemy, the attendance rate also significantly improves, and has very high emergentness to the strike of enemy, substantially increases the battlefield survival rate of aircraft.
The fixed wing aircraft of vertical takeoff and landing ability is had not need special airport and runway, eliminate expensive airport construction expense, bird need not be driven, also can in landing under bad weather condition, reduce use cost, but also it is far away to have voyage, the advantage that the conventional helicopters such as capacity weight is high do not have.So vertical takeoff and landing Fixed Wing AirVehicle becomes a popular direction of aviation aircraft development.
Such as: the patent No. be 201210282360.6 utility model patent disclose and a kind ofly fly to control plate based on three axles and realize the aircraft of fixed-wing and vertical takeoff and landing, it can realize vertical takeoff and landing and the dual offline mode of fixed-wing, it drives steering wheel running by steering wheel, and then driven by motor screw propeller is rotated at 0-90 degree, but, adopt said structure mode, there is following defect is, steering wheel carrying screws verts, but screw propeller can pass to steering wheel antagonistic force by steering wheel arm conversely, steering wheel can be made so stressed too large, easy damage, and steering wheel has diastema, local vibrations can be caused, affect flight safety, in addition, this type of aircraft does not also design duct, particularly in helicopter mode and the mutual switching process of cruise mode, easily occurs rising hypodynamic phenomenon, causes its resistance to overturning poor, easily cause aircraft accident.
Utility model content
The purpose of this utility model is to provide a kind of novel culvert type with vertical takeoff and landing function to vert aircraft, adopts the unreasonable of steering wheel carrying screws structure, easily cause the technical matterss such as potential safety hazard in order to improve the existing aircraft that verts.
In order to solve the problems of the technologies described above, the utility model provides a kind of culvert type with vertical takeoff and landing function and to vert aircraft, comprise: fuselage, front wing, rear wing, whirler wing plate, tilting rotor and rotor regulating mechanism, described front wing symmetry is arranged on forebody, and described rear wing symmetry is arranged on fuselage afterbody;
Described rear wing is provided with opening, described whirler wing plate fills the opening part of wing in the rear by wing axle hinge, described tilting rotor passes whirler wing plate and is packed on wing axle, described rotor regulating mechanism drives wing axle to rotate, and then driven rotary wing plate and tilting rotor rotate;
Described waist is provided with duct, is provided with shrouded propeller in described duct.
Further, described rotor regulating mechanism comprises base and is arranged on the motor on described base, reductor, leading screw, drive link one and drive link two, described motor via reducer drives screw turns, described drive link one is vertically screwed onto on leading screw, described drive link two is contained on base by pitman shaft hinge, and the end of drive link two is connected with drive link one, described pitman shaft is connected with wing axle, motor is by driving leading screw, drive link one, the running of drive link two and pitman shaft, and then wing axle driven rotary wing plate and tilting rotor are rotated in certain angle,
Further, described opening is arranged on the middle part of rear wing, and described opening shape is matched with the shape of whirler wing plate.
Further, described tilting rotor comprises motor and wing tip screw propeller, and described motor is packed on wing axle, drives wing tip screw propeller to operate by motor.
Further, under the driving of described rotor regulating mechanism, described wing axle driven rotary wing plate and tilting rotor rotate at 0-105 degree.
Further, the leading screw pivot center of described rotor regulating mechanism and front wing and rear wingpiston are 45 degree and install, to ensure that described whirler wing plate and tilting rotor rotate at 0-105 degree.
Further, described shrouded propeller is divided into the screw propeller of upper and lower two secondary contrarotations.
Further, also comprise the upper hatchcover for opening or close duct uptake, described upper hatchcover is cut with scissors by axle and fuselage and is fitted together, and is controlled unlatching or the closedown of described upper hatchcover by hatchcover regulating mechanism.
Further, also comprise the lower hatchcover for opening or close air port under duct, described lower hatchcover is cut with scissors by axle and fuselage and is fitted together, unlatching or the closedown of described lower hatchcover is controlled by hatchcover regulating mechanism, described lower hatchcover is provided with two fans, the lower hatchcovers of described two fan be contained in by rotational symmetry hinge be positioned at both sides, air port under duct fuselage on.
Further, described hatchcover regulating mechanism comprises motor, connecting rod one and connecting rod two, described connecting rod one two ends respectively with fuselage and connecting rod two hinged, the other end of described connecting rod two and upper hatchcover or lower hatchcover hinged by axle, by the rotation of motor drive link one, and then drive link two drives upper hatchcover or lower hatchcover to carry out opening or closing, described connecting rod one top is provided with limiting stopper, for carrying out spacing to the anglec of rotation of connecting rod two.
Adopt technique scheme, the culvert type of vertical takeoff and landing function that what the utility model provided have verts aircraft, has following technique effect:
The beneficial effect that technical solutions of the utility model possess has:
(1), wing tip screw propeller of the present utility model is in the process of verting, the lift supply of aircraft is increased by the rotating speed of fuselage interior shrouded propeller, make the controllability (safety, stability and reliability) of aircraft attitude in translative mode process, effectively reduce aircraft accident rate; Meanwhile, by regulating ducted fan rotating speed to be convenient to carry out quick adjustment to the flight attitude of aircraft, to adapt to different flight environment of vehicle;
(2), by rotor regulating mechanism, rotation is carried out to whirler wing plate and tilting rotor and can realize aircraft and turn to aircraft cruise mode by helicopter in hover pattern, expand the field of application of aircraft;
(3), shrouded propeller adopts upper and lower two secondary contrarotating propellers, can realize different power supplies, improving the safety and stability of aircraft in offline mode switching process further by adjusting the two secondary altogether rotating speeds that screw propellers are different;
(4), on the port of duct activity install hatchcover and lower hatchcover, closed duct under aircraft cruise mode, can reduce flatly flying resistance, improve flying speed and efficiency;
(5), the utility model no longer adopts steering wheel carrying screws to carry out the frame mode verted, but adopt motor to drive the running of leading screw, drive link one, drive link two and pitman shaft, and then wing axle driven rotary wing plate and tilting rotor are rotated in certain angle; In operation process, it is less that motor is subject to antagonistic force, can not produce diastema and vibrations, and overall stability obtains actv. and promotes.
Accompanying drawing explanation
In order to be illustrated more clearly in the utility model detailed description of the invention or technical scheme of the prior art, be briefly described to the accompanying drawing used required in detailed description of the invention or description of the prior art below, apparently, accompanying drawing in the following describes is embodiments more of the present utility model, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
Fig. 1 is structural representation of the present utility model;
Fig. 2 is bottom surface structure schematic diagram of the present utility model;
Fig. 3 is tilting rotor and wing structural representation in vertical state;
Fig. 4 is the structural representation of rotor regulating mechanism;
Fig. 5 is the structural representation of hatchcover regulating mechanism;
Fig. 6 is the lateral plan of Fig. 5.
Wherein:
1-fuselage; Wing before 2-; Wing after 3-;
4-whirler wing plate; 5-tilting rotor; 6-rotor regulating mechanism;
The upper hatchcover of 7-; 8-hatchcover regulating mechanism; Hatchcover under 9-;
11-duct; 12-shrouded propeller; 31-opening;
41-wing axle; 51-wing tip screw propeller; 61-base;
62-reductor; 63-leading screw; 64-drive link one;
65-drive link two; 66-pitman shaft;
81-connecting rod one; 82-connecting rod two; 811-limiting stopper.
Detailed description of the invention
Be clearly and completely described the technical solution of the utility model below in conjunction with accompanying drawing, obviously, described embodiment is the utility model part embodiment, instead of whole embodiments.Based on the embodiment in the utility model, those of ordinary skill in the art are not making the every other embodiment obtained under creative work prerequisite, all belong to the scope of the utility model protection.
In description of the present utility model, it should be noted that, orientation or the position relationship of the instruction such as term " " center ", " on ", D score, "left", "right", " vertically ", " level ", " interior ", " outward " they be based on orientation shown in the drawings or position relationship; be only the utility model and simplified characterization for convenience of description; instead of instruction or imply the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as restriction of the present utility model.In addition, term " first ", " second ", " the 3rd " only for describing object, and can not be interpreted as instruction or hint relative importance.
As shown in Figure 1-Figure 3, structural representation of the present utility model;
The culvert type with vertical takeoff and landing function verts an aircraft, comprising: fuselage 1, front wing 2, rear wing 3, whirler wing plate 4, tilting rotor 5 and rotor regulating mechanism 6;
Front wing 2 is provided with a pair, and symmetry is arranged on fuselage 1 front portion respectively, and rear wing 3 is provided with a pair equally, and symmetry is arranged on fuselage 1 rear portion respectively; Front wing 2, rear wing 3 form the aircraft of tandem fixed-wing with fuselage 1 entirety.
After two fans, wing 3 is respectively equipped with opening 31.
As a preferred embodiment, opening 31 is arranged on the middle part of rear wing 3, and the uniform force of wing 3 after ensureing, solves the monolateral stressed problem of wing preferably;
The shape of opening 31 is set to arc-shaped, and the size of opening 31 is equal to or less than the propeller radius size of tilting rotor 5, object be tilting rotor 5 when rotated, opening can promote the lift of screw propeller.Especially in the stage of taking off vertically, screw propeller can not be blocked by wing, hoisting force school.
The form fit of whirler wing plate 4 is in the shape of described opening 31, whirler wing plate 4 inside is run through wing axle 41, whirler wing plate 4 fills opening 31 place of wing 3 in the rear by wing axle 41 hinge, and whirler wing plate 4 can rotate around opening 31 place of wing axle 41 at wing.
Tilting rotor 5 comprises motor and wing tip screw propeller 51, and by the running being driven wing tip screw propeller 51 by motor, motor passes whirler wing plate 4 inside and is packed on wing axle 41; By the rotation of wing axle 41, driven rotary wing plate 4 and tilting rotor 5 rotate simultaneously.
Drive wing axle 41 to rotate by rotor regulating mechanism 6, and then driven rotary wing plate 4 and tilting rotor 5 rotate.
As shown in Figure 4, the structural representation of rotor regulating mechanism;
Rotor regulating mechanism 6 comprises base 61 and is arranged on motor, reductor 62, leading screw 63, drive link 1 and the drive link 2 65 on described base 61;
Motor is connected with reductor 62 by transmission shaft, and increase output torque, reductor 62 output shaft is connected with leading screw 63, and drive leading screw 63 to rotate, the two ends of leading screw 63 are arranged on base 61 by bearing;
The body of rod of drive link 1 is provided with tapped bore, and drive link 1 is vertically screwed onto on leading screw 63 by the tapped bore on it, and drive link 1 makes the circular movement of leading screw 63 be converted to horizontal motion.
Drive link 2 65 is contained on base 61 by pitman shaft 66 hinge, and the end of drive link 2 65 is connected with drive link 1, as a preferred embodiment, the end of drive link 2 65 is designed the breach of a U-shaped, is installed on by this breach on drive link 1; When drive link 1 does straight-line motion, drive link 2 65 swings centered by pitman shaft 66, and meanwhile, pitman shaft 66 rotates in certain angular range.
Described pitman shaft 66 is connected with wing axle 41, and motor by driving the running of leading screw 63, drive link 1, drive link 2 65 and pitman shaft 66, and then makes wing axle 41 driven rotary wing plate 4 and tilting rotor 5 rotate in certain angle;
Wing axle 41 is provided with angular position transducer, for detecting the angle changing condition of wing axle 41.
As a preferred embodiment, under the driving of rotor regulating mechanism 6, wing axle 41 driven rotary wing plate 4 and tilting rotor 5 rotate at 0-105 degree.
Simultaneously, leading screw 63 pivot center of rotor regulating mechanism 6 and front wing 2 and rear wing 3 plane are 45 degree install, to ensure that described whirler wing plate 4 and tilting rotor 5 rotate at 0-105 degree, ensure that tilting rotor 5 can carry out the switching of level or plumbness.
Be provided with duct 11 at the middle part of fuselage 1, shrouded propeller 12 is installed in duct 11.
As a preferred embodiment, shrouded propeller 12 is divided into the screw propeller of upper and lower two secondary contrarotations, contrarotation can be offset anti-twisted, different power supplies can be realized by the rotating speed adjusting two secondary screw propellers (difference) altogether, improve the safety and stability of aircraft in offline mode switching process further.
The utility model also comprises the upper hatchcover 7 for opening or close duct 11 uptake, and upper hatchcover 7 is cut with scissors by axle and fuselage 1 and is fitted together, and is controlled unlatching or the closedown of described upper hatchcover 7 by hatchcover regulating mechanism 8.
The utility model also comprises the lower hatchcover 9 for opening or close duct 11 times air ports, and described lower hatchcover 9 is cut with scissors by axle and fuselage 1 and is fitted together, and is controlled unlatching or the closedown of described lower hatchcover 9 by hatchcover regulating mechanism 8.
As a preferred embodiment, lower hatchcover 9 is provided with two fans, the lower hatchcover 9 of described two fan be contained in by rotational symmetry hinge be positioned at both sides, duct 11 times air ports fuselage 1 on, jointly open by the lower hatchcover 9 of two fans or close the lower air port of duct 11.
As shown in Figure 5, Figure 6, the structural representation (above hatchcover is example, and lower hatch cover structure in like manner) of hatchcover regulating mechanism;
The hatchcover regulating mechanism 8 that upper hatchcover 7 and lower hatchcover 9 adopt comprises motor, connecting rod 1 and connecting rod 2 82;
When being connected with upper hatchcover 7, the two ends of connecting rod 1 respectively with fuselage 1 and connecting rod 2 82 hinged, the other end and the upper hatchcover 7 of connecting rod 2 82 are hinged by axle, and by the rotation of motor drive link 1, and then drive link 2 82 drives upper hatchcover 7 to carry out opening or closing;
When being connected with lower hatchcover 9, the two ends of connecting rod 1 respectively with fuselage 1 and connecting rod 2 82 hinged, the other end and the lower hatchcover 9 of connecting rod 2 82 are hinged by axle, and by the rotation of motor drive link 1, and then drive link 2 82 drives lower hatchcover 9 to carry out opening or closing.
Connecting rod 1 top is provided with limiting stopper 811, for carrying out spacing to the anglec of rotation of connecting rod 2 82.
The culvert type with vertical takeoff and landing function of the present utility model verts aircraft when taking off, it is 90 degree that whirler wing plate in the middle part of rear wing and tilting rotor upwards overturn, perpendicular to the ground, on fuselage, the upper hatchcover of duct and lower hatchcover are opened simultaneously, operated by the screw propeller in driven by motor duct and wing tip screw propeller, when reaching certain rotating speed, the lift of generation is greater than aircraft own wt, and aircraft vertical takes off.
After aircraft arrives predetermined altitude, when turning to cruise mode by helicopter mode, tilted forward by rotor regulating mechanism driven rotary wing plate and tilting rotor simultaneously, improved the rotating speed of fuselage main duct screw propeller by electronic transmission in the process of verting, add lift, to make up the loss of lift in the process of verting, guarantee the stability and security of aircraft in the process of verting.
When whirler wing plate and tilting rotor tilt forward to (state parallel to the ground) when 0 degree, aircraft flies before starting, after arriving certain forward flight speed, front wing and rear wing produce enough lift can trimmed flight device own wt, screw propeller in fuselage main duct quits work, upper hatchcover and lower hatchcover are closed, and to reduce resistance, and then realize the better manoevreability of aircraft.
The beneficial effect that technical solutions of the utility model possess has:
(1), wing tip screw propeller of the present utility model is in the process of verting, the lift supply of aircraft is increased by the rotating speed of fuselage interior shrouded propeller, make the controllability (safety, stability and reliability) of aircraft attitude in translative mode process, effectively reduce aircraft accident rate; Meanwhile, by regulating ducted fan rotating speed to be convenient to carry out quick adjustment to the flight attitude of aircraft, to adapt to different flight environment of vehicle
(2), by rotor regulating mechanism, rotation is carried out to whirler wing plate and tilting rotor and can realize aircraft and turn to aircraft cruise mode by helicopter in hover pattern, expand the field of application of aircraft;
(3), shrouded propeller adopts upper and lower two secondary contrarotating propellers, can realize different power supplies, improving the safety and stability of aircraft in offline mode switching process further by adjusting two secondary propeller speed altogether;
(4), on the port of duct activity install hatchcover and lower hatchcover, closed duct under aircraft cruise mode, can reduce flatly flying resistance, improve flying speed and efficiency;
(5), the utility model no longer adopts steering wheel carrying screws to carry out the frame mode verted, but adopt motor to drive the running of leading screw, drive link one, drive link two and pitman shaft, and then wing axle driven rotary wing plate and tilting rotor are rotated in certain angle; In operation process, it is less that motor is subject to antagonistic force, can not produce diastema and vibrations, and overall stability obtains actv. and promotes.
In description of the present utility model, it should be noted that, unless otherwise clearly defined and limited, term " installation ", " being connected ", " connection " should be interpreted broadly, and such as, can be fixedly connected with, also can be removably connect, or connect integratedly; Can be mechanical connection, also can be electrical connection; Can be directly be connected, also indirectly can be connected by intermediary, can be the connection of two element internals.For the ordinary skill in the art, particular case the concrete meaning of above-mentioned term in the utility model can be understood.
Last it is noted that above each embodiment is only in order to illustrate the technical solution of the utility model, be not intended to limit; Although be described in detail the utility model with reference to foregoing embodiments, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein some or all of technical characteristic; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the scope of each embodiment technical scheme of the utility model.

Claims (10)

1. a culvert type with vertical takeoff and landing function verts aircraft, comprise: fuselage, front wing, rear wing, whirler wing plate, tilting rotor and rotor regulating mechanism, described front wing symmetry is arranged on forebody, and described rear wing symmetry is arranged on fuselage afterbody; It is characterized in that:
Described rear wing is provided with opening, described whirler wing plate fills the opening part of wing in the rear by wing axle hinge, described tilting rotor passes whirler wing plate and is packed on wing axle, described rotor regulating mechanism drives wing axle to rotate, and then driven rotary wing plate and tilting rotor rotate;
Described waist is provided with duct, is provided with shrouded propeller in described duct.
2. the culvert type with vertical takeoff and landing function according to claim 1 verts aircraft, it is characterized in that: described rotor regulating mechanism comprises base and is arranged on the motor on described base, reductor, leading screw, drive link one and drive link two, described motor via reducer drives screw turns, described drive link one is vertically screwed onto on leading screw, described drive link two is contained on base by pitman shaft hinge, and the end of drive link two is connected with drive link one, described pitman shaft is connected with wing axle, motor is by driving leading screw, drive link one, the running of drive link two and pitman shaft, and then wing axle driven rotary wing plate and tilting rotor are rotated in certain angle.
3. the culvert type with vertical takeoff and landing function according to claim 1 verts aircraft, and it is characterized in that: described opening is arranged on the middle part of rear wing, described opening shape is matched with the shape of whirler wing plate.
4. the culvert type with vertical takeoff and landing function according to claim 1 verts aircraft, and it is characterized in that: described tilting rotor comprises motor and wing tip screw propeller, described motor is packed on wing axle, drives wing tip screw propeller to operate by motor.
5. the culvert type with vertical takeoff and landing function according to claim 1 verts aircraft, and it is characterized in that: under the driving of described rotor regulating mechanism, described wing axle driven rotary wing plate and tilting rotor rotate at 0-105 degree.
6. the culvert type with vertical takeoff and landing function according to claim 5 verts aircraft, it is characterized in that: the leading screw pivot center of described rotor regulating mechanism and rear wingpiston are 45 degree and install, to ensure that described whirler wing plate and tilting rotor rotate at 0-105 degree.
7. the culvert type with vertical takeoff and landing function according to claim 1 verts aircraft, it is characterized in that: described shrouded propeller is divided into the screw propeller of upper and lower two secondary contrarotations.
8. the culvert type with vertical takeoff and landing function according to any one of claim 1-7 verts aircraft, it is characterized in that: also comprise the upper hatchcover for opening or close duct uptake, described upper hatchcover is cut with scissors by axle and fuselage and is fitted together, and is controlled unlatching or the closedown of described upper hatchcover by hatchcover regulating mechanism.
9. the culvert type with vertical takeoff and landing function according to claim 8 verts aircraft, it is characterized in that: also comprise the lower hatchcover for opening or close air port under duct, described lower hatchcover is cut with scissors by axle and fuselage and is fitted together, unlatching or the closedown of described lower hatchcover is controlled by hatchcover regulating mechanism, described lower hatchcover is provided with two fans, the lower hatchcovers of described two fan be contained in by rotational symmetry hinge be positioned at both sides, air port under duct fuselage on.
10. the culvert type with vertical takeoff and landing function according to claim 9 verts aircraft, it is characterized in that: described hatchcover regulating mechanism comprises motor, connecting rod one and connecting rod two, described connecting rod one two ends respectively with fuselage and connecting rod two hinged, the other end of described connecting rod two and upper hatchcover or lower hatchcover hinged by axle, by the rotation of motor drive link one, and then drive link two drives upper hatchcover or lower hatchcover to carry out opening or closing, described connecting rod one top is provided with limiting stopper, for carrying out spacing to the anglec of rotation of connecting rod two.
CN201520925229.6U 2015-11-18 2015-11-18 Duct formula aircraft that verts with VTOL function CN205098474U (en)

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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105711831A (en) * 2016-04-25 2016-06-29 长江大学 Vertical take-off and landing type fixed-wing unmanned aerial vehicle
CN106143897A (en) * 2016-07-26 2016-11-23 芜湖万户航空航天科技有限公司 Can be verted tail-rotor
CN106275415A (en) * 2016-08-19 2017-01-04 广东容祺智能科技有限公司 The aircraft that a kind of fixed-wing and many rotors can automatically switch
CN106314789A (en) * 2016-08-31 2017-01-11 张峣 Wing, fixed-wing aircraft and fixed-wing aircraft lifting method
CN106585976A (en) * 2016-11-30 2017-04-26 北京航空航天大学 Aircraft layout of tilt rotors/lift fan during high-speed long endurance
CN107028549A (en) * 2017-05-18 2017-08-11 烟台工程职业技术学院 A kind of glass-cleaning robot
EP3656669A1 (en) 2018-11-26 2020-05-27 AIRBUS HELICOPTERS DEUTSCHLAND GmbH A vertical take-off and landing multirotor aircraft with at least eight thrust producing units
EP3702277A1 (en) 2019-02-27 2020-09-02 AIRBUS HELICOPTERS DEUTSCHLAND GmbH A multirotor aircraft that is adapted for vertical take-off and landing (vtol)
EP3702276A1 (en) 2019-02-27 2020-09-02 AIRBUS HELICOPTERS DEUTSCHLAND GmbH A multirotor joined-wing aircraft with vtol capabilities

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105711831A (en) * 2016-04-25 2016-06-29 长江大学 Vertical take-off and landing type fixed-wing unmanned aerial vehicle
CN106143897A (en) * 2016-07-26 2016-11-23 芜湖万户航空航天科技有限公司 Can be verted tail-rotor
CN106275415A (en) * 2016-08-19 2017-01-04 广东容祺智能科技有限公司 The aircraft that a kind of fixed-wing and many rotors can automatically switch
CN106275415B (en) * 2016-08-19 2018-06-05 广东容祺智能科技有限公司 The aircraft that a kind of fixed-wing and more rotors can automatically switch
CN106314789A (en) * 2016-08-31 2017-01-11 张峣 Wing, fixed-wing aircraft and fixed-wing aircraft lifting method
CN106585976A (en) * 2016-11-30 2017-04-26 北京航空航天大学 Aircraft layout of tilt rotors/lift fan during high-speed long endurance
CN106585976B (en) * 2016-11-30 2019-05-24 北京航空航天大学 A kind of long endurance aircraft layout of tilting rotor/lift fan high speed
CN107028549A (en) * 2017-05-18 2017-08-11 烟台工程职业技术学院 A kind of glass-cleaning robot
EP3656669A1 (en) 2018-11-26 2020-05-27 AIRBUS HELICOPTERS DEUTSCHLAND GmbH A vertical take-off and landing multirotor aircraft with at least eight thrust producing units
EP3702277A1 (en) 2019-02-27 2020-09-02 AIRBUS HELICOPTERS DEUTSCHLAND GmbH A multirotor aircraft that is adapted for vertical take-off and landing (vtol)
EP3702276A1 (en) 2019-02-27 2020-09-02 AIRBUS HELICOPTERS DEUTSCHLAND GmbH A multirotor joined-wing aircraft with vtol capabilities
US10981650B2 (en) 2019-02-27 2021-04-20 Airbus Helicopters Deutschland GmbH Multirotor joined-wing aircraft with VTOL capabilities

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