CN109263901A - A kind of suspension type folding rotor craft - Google Patents
A kind of suspension type folding rotor craft Download PDFInfo
- Publication number
- CN109263901A CN109263901A CN201811274762.5A CN201811274762A CN109263901A CN 109263901 A CN109263901 A CN 109263901A CN 201811274762 A CN201811274762 A CN 201811274762A CN 109263901 A CN109263901 A CN 109263901A
- Authority
- CN
- China
- Prior art keywords
- wing
- suspension
- fuselage
- suspension type
- fixed
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- 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
-
- 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
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/36—Structures adapted to reduce effects of aerodynamic or other external heating
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
- B64U50/14—Propulsion using external fans or propellers ducted or shrouded
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Wind Motors (AREA)
Abstract
The invention discloses a kind of suspension type folding rotor craft, including fuselage and tail, the fuselage two sides are symmetrically arranged with dalta wing, and the tail end lines and the fuselage of the dalta wing are perpendicular, and are located at the tail front end；The front end of the dalta wing, which is uniformly hung, is provided with several suspension rotors, and the suspension rotor is positioned horizontally in the bottom front of the dalta wing；The dalta wing includes the wing that is connected to a fixed with the fuselage, and the folding wings being connected by fold mechanism with the fixed-wing.The present invention can effectively adjust the installation site of rotor, to according to the real-time change of flight device wing form of different flight environment of vehicle, to influence the peripheral gas flow form during aircraft flight, increase the operating condition scope of application of aircraft, effectively enhances the anti-prominent wind energy power of rotor craft.
Description
Technical field
The present invention relates to aviation aircraft technical field, more particularly to a kind of suspension type folding rotor flying
Device.
Background technique
Aircraft especially rotor craft is continuous recently as scientific and technological fast development and all kinds of specific demands
Increase, starts to be widely used.And aircraft is broadly divided into two classes: fixed wing aircraft and multi-rotor aerocraft.Both
All have inevitable defect: fixed wing aircraft flight efficiency is high, but landing mode is complicated, is unable to VTOL, and fly
Speed cannot be too small；Multi-rotor aerocraft can be with VTOL, and speed is controllable, but flying speed is slow, and the flight time is short, flight effect
Rate is low.The rotor of current existing aircraft is fixed on fuselage more, so that cannot achieve the position tune of rotor in flight course
It is whole, and realize stronger anti-prominent wind energy power.It is confirmed through research, reducing prominent wind bending moment has pole to the flight stability of aircraft
It is big to help.
Therefore, how to provide a kind of suspension type folding rotor craft with stronger anti-prominent wind energy power is this field skill
The problem of art personnel's urgent need to resolve.
Summary of the invention
In view of this, can effectively adjust the installation of rotor the present invention provides a kind of suspension type folding rotor craft
Position, thus according to the real-time change of flight device wing form of different flight environment of vehicle, thus the week during influencing aircraft flight
Side airflow shape increases the operating condition scope of application of aircraft, effectively enhances the anti-prominent wind energy power of rotor craft.
To achieve the goals above, the present invention adopts the following technical scheme:
A kind of suspension type folding rotor craft, including fuselage and tail, the fuselage two sides are symmetrically arranged with dalta wing, and described three
The tail end lines and the fuselage of angle blade are perpendicular, and are located at the tail front end；The front end of the dalta wing uniformly hangs and sets
Several suspension rotors are equipped with, the suspension rotor is positioned horizontally in the bottom front of the dalta wing；
The dalta wing includes the wing that is connected to a fixed with the fuselage, and be connected by fold mechanism with the fixed-wing
Folding wings.
The present invention passes through the suspension rotor that dalta wing front bottom end is arranged in, and greatly strengthens the air stream of dalta wing bottom
Dynamic property improves the power performance of aircraft so that aircraft obtains stronger lift, weakens mutation high wind to triangle
The disturbance of the wing；The folding structure of folding wings and fixed-wing enhances dalta wing integrally to the adaptivity of prominent wind bending moment power, and
And drive partial suspension rotor to rise while bending, it can effectively weaken the gas-flow resistance of dalta wing two sides.
Preferably, it is provided with spar in the fixed-wing, controller is installed on the spar, the controller connects institute
State fold mechanism.
Preferably, the fold mechanism includes spindle nose, hydraulic stem, transmission shaft, drive rod, pilot pin and fixing axle；
The spindle nose transmission connection is on the controller, and the spindle nose is also connected with one end of the hydraulic stem；
The other end of the hydraulic stem is flexibly connected with the drive rod by transmission shaft；
The drive rod is fixed on the end of the fixed-wing by the pilot pin, and the drive rod is branch with the pilot pin
Point rotation；The other end of the locating rod connects the fixing axle；
The fixing axle is mounted in the folding wings.
It preferably, further include control loop positioned at cockpit, the control loop and the controller wired connection, to
The controller sends control signal, and the controller controls the contraction of hydraulic pressure bar and elongation.
Preferably, the fixing axle is mounted on one end that the folding wings are docked with the fixed-wing.
Preferably, there are two the suspension rotors for suspension in the folding wings.
Preferably, duct is respectively arranged on the dalta wing of the fuselage two sides, and the duct is with respect to fuselage
It is symmetrical.
Preferably, propeller is provided in the duct.
Preferably, the suspension rotor is fixedly connected by suspension assembly with the dalta wing.
Preferably, the suspension assembly includes the overarm for being vertically fixed on the dalta wing bottom, and is hung down with the overarm
The direct-connected installation frame connect, the suspension rotor are fixedly mounted on the installation frame.
It can be seen via above technical scheme that compared with prior art, the present disclosure provides a kind of suspension type foldings
Rotor craft has the advantages that
1, by the way that the suspension rotor of dalta wing front bottom end is arranged in, the air flow property of dalta wing bottom is greatly strengthened, from
And aircraft is made to obtain stronger lift, the power performance of aircraft is improved, mutation high wind is weakened and dalta wing is disturbed
It is dynamic；
2, the folding structure of folding wings and fixed-wing enhances dalta wing integrally to the adaptivity of prominent wind bending moment power, and
It drives partial suspension rotor to rise while bending, can effectively weaken the gas-flow resistance of dalta wing two sides；
3, the hydraulicdriven structure design of fold mechanism, not only saves space, but also stable structure, and manufacturing cost is low, operation
Simply, the adjusting by the flexible realization of control hydraulic stem to the bending angle of folding wings, flexibility with higher；
4, double ducts design on dalta wing, the forward power that cooperation suspension rotor generates, further increases in dalta wing
The airflow in portion improves the climbing power of fuselage.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
The embodiment of invention for those of ordinary skill in the art without creative efforts, can also basis
The attached drawing of offer obtains other attached drawings.
Fig. 1 attached drawing is suspension type folding rotor craft overall structure top view provided by the invention；
Fig. 2 attached drawing is suspension type folding rotor craft overall structure front view provided by the invention；
Fig. 3 attached drawing is the partial enlarged view of dalta wing provided by the invention；
Fig. 4 attached drawing is the folding principle schematic diagram one of dalta wing provided by the invention；
Fig. 5 attached drawing is the folding principle schematic diagram two of dalta wing provided by the invention.
In Fig. 1: 1 being fuselage, 2 be tail, 3 be dalta wing, 4 be suspension rotor, 5 be duct, 6 be propeller, 42 be
Installation frame.
In Fig. 2: 31 being fixed-wing, 32 be folding wings, 41 be overarm.
In Fig. 3: 31 being fixed-wing, 32 be folding wings.
In Fig. 4: 311 being spar, 312 be controller, 331 be spindle nose, 332 be hydraulic stem, 333 be transmission shaft, 334 be
Drive rod, 335 be pilot pin, 336 be fixing axle.
In Fig. 5: 311 being spar, 312 be controller, 331 be spindle nose, 332 be hydraulic stem, 333 be transmission shaft, 334 be
Drive rod, 335 be pilot pin, 336 be fixing axle.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
The embodiment of the invention discloses a kind of suspension type folding rotor crafts, referring to Figure of description 1-3, including fuselage
1 and tail 2,1 two sides of fuselage be symmetrically arranged with dalta wing 3, the tail end lines and fuselage 1 of dalta wing 3 are perpendicular, and be located at tail 2
Front end；The front end of dalta wing 3, which is uniformly hung, is provided with several suspension rotors 4, and suspension rotor 4 is positioned horizontally in the bottom of dalta wing 3
Portion front end；Dalta wing 3 includes the wing 31 that is connected to a fixed with fuselage 1, and the folding being connected by fold mechanism with fixed-wing 31
The folded wing 32.
In a specific embodiment, dalta wing is symmetricly set on fuselage two sides, and has the design of independent tail, and three
Angle blade facilitates balance and stability of the fuselage under high wind, and independent tail makes speed air flow when increasing fuselage flight,
The air pressure difference before and after fuselage is balanced, the stability of aircraft flight is further increased.
In a specific embodiment, aircraft is if prominent meet high wind in flight course, and folding wings are folded upward at, energy
It realizes that wind resistance increases steady effect, and can smoothly pass through in narrow space.Suspension rotor is capable of increasing the throughput of triangle underwing,
Weaken the influence from different angle high wind for aircraft flight track, under folding wings bending state, before being located at folding wings
The suspension rotor at end is promoted therewith, can be stablized the air-flow sinuous flow that high wind acts on lower wing tip two sides, be further enhanced anti-prominent wind
Ability.
In order to further optimize the above technical scheme, it is provided with spar 311 in fixed-wing 31, control is installed on spar 311
Device 312 processed, controller 312 connect fold mechanism.
In order to further optimize the above technical scheme, fold mechanism includes spindle nose 331, hydraulic stem 332, transmission shaft 333, passes
Lever 334, pilot pin 335 and fixing axle 336；
Spindle nose 331 is sequentially connected on controller 312, and spindle nose 331 is also connected with one end of hydraulic stem 332；
The other end of hydraulic stem 332 is flexibly connected with drive rod 334 by transmission shaft 333；
Drive rod 334 is fixed on the end of fixed-wing 31 by pilot pin 335, and drive rod 334 is turned with pilot pin 335 for fulcrum
It is dynamic；The other end of locating rod is connected and fixed axis 336；
Fixing axle 336 is mounted in folding wings 32.
The bottom of controller 312 and 331 joint face of spindle nose is provided with snap-gauge perpendicular to joint face, for stretching in folding wings 32
Under exhibition state, Horizontal load-bearing power is provided for fold mechanism, increases stability of the fold mechanism in fixed-wing 31, and reduce control
Control load of the device 312 to spindle nose 331.
It in order to further optimize the above technical scheme, further include the control loop for being located at cockpit, control loop and control
312 wired connection of device sends control signal to controller 312, and controller 312 controls hydraulic stem 332 and shrinks and extend.
In order to further optimize the above technical scheme, fixed-wing end top portion is equipped with limited block, for folding wings and admittedly
Determine position-limiting action when wing docking, prevents the case where position occurred in folding wings stretching process.
In a specific embodiment, referring to Figure of description 4, under regular flight condition, hydraulic stem, which is in, to be shunk
State, hydraulic stem, drive rod are located on same level axis at this time, and folding wings realize that level is docked with fixed-wing.
Referring to Figure of description 5, when prominent chance high wind, driver sends control signal to controller by control loop,
Controller controls hydraulic stem elongation, at this point, drive rod can be rotated by dot of pilot pin by the length position-limiting action of drive rod,
The angle of rotation is determined by the extended length of hydraulic stem, if the length value of hydraulic stem elongation is shorter, the angle of drive rod rotation
Small, if the length value of hydraulic stem elongation is longer, the angle of drive rod rotation is big.At this time it should be noted that by snap-gauge limit
Position effect, hydraulic stem is not in the case where tilting down.The angle of drive rod rotation is equal to the bending angle of folding wings.It folds
The setting of mechanism increases the controllability of folding wings bending action, and adjustable folding wings meet not to any bending angle
Adaptability requirement with flight environment of vehicle to aircraft wing.
In order to further optimize the above technical scheme, fixing axle 336 is mounted on one that folding wings 32 are docked with fixed-wing 31
End.
In order to further optimize the above technical scheme, there are two hang rotor 4 for suspension in folding wings 32.
In order to further optimize the above technical scheme, it is respectively arranged with duct 5 on the dalta wing 3 of 1 two sides of fuselage, and contained
Road 5 is symmetrical with respect to fuselage 1.
In order to further optimize the above technical scheme, propeller 6 is provided in duct 5.
In a specific embodiment, using the layout of double ducts among aircraft, the air-flow for generating propeller is complete
Portion is flowed through from centre, increases power, reduces gas-flow resistance.
In order to further optimize the above technical scheme, suspension rotor 4 is fixedly connected by suspension assembly with dalta wing 3.
In order to further optimize the above technical scheme, suspension assembly includes the overarm 41 for being vertically fixed on 3 bottom of dalta wing,
With with overarm 41 installation frames 42 connected vertically, suspension rotor be fixedly mounted on installation frame 42.
Each embodiment in this specification is described in a progressive manner, the highlights of each of the examples are with other
The difference of embodiment, the same or similar parts in each embodiment may refer to each other.For device disclosed in embodiment
For, since it is corresponded to the methods disclosed in the examples, so being described relatively simple, related place is said referring to method part
It is bright.
The foregoing description of the disclosed embodiments enables those skilled in the art to implement or use the present invention.
Various modifications to these embodiments will be readily apparent to those skilled in the art, as defined herein
General Principle can be realized in other embodiments without departing from the spirit or scope of the present invention.Therefore, of the invention
It is not intended to be limited to the embodiments shown herein, and is to fit to and the principles and novel features disclosed herein phase one
The widest scope of cause.
Claims (10)
1. a kind of suspension type folding rotor craft, including fuselage (1) and tail (2), it is characterised in that: the fuselage (1) two
Side is symmetrically arranged with dalta wing (3), and the tail end lines and the fuselage (1) of the dalta wing (3) are perpendicular, and is located at the tail
(2) front end；The front end of the dalta wing (3), which is uniformly hung, is provided with several suspensions rotor (4), suspension rotor (4) water
Prosposition is in the bottom front of the dalta wing (3)；The dalta wing (3) includes that the wing (31) are connected to a fixed with the fuselage (1),
And the folding wings (32) being connected by fold mechanism with the fixed-wing (31).
2. a kind of suspension type folding rotor craft according to claim 1, which is characterized in that in the fixed-wing (31)
It is provided with spar (311), is equipped with controller (312) on the spar (311), the controller (312) connects the folding
Mechanism.
3. a kind of suspension type folding rotor craft according to claim 2, which is characterized in that the fold mechanism includes
Spindle nose (331), hydraulic stem (332), transmission shaft (333), drive rod (334), pilot pin (335) and fixing axle (336)；The axis
Head (331) transmission connection is on the controller (312), and the spindle nose (331) is also solid with one end of the hydraulic stem (332)
Even；The other end of the hydraulic stem (332) is flexibly connected with the drive rod (334) by transmission shaft (333)；The drive rod
(334) end of the fixed-wing (31) is fixed on by the pilot pin (335), the drive rod (334) is with the positioning
Bolt (335) is fulcrum rotation；The other end of the locating rod connects the fixing axle (336)；The fixing axle (336) is mounted on
On the folding wings (32).
4. a kind of suspension type folding rotor craft according to claim 1, which is characterized in that further include being located at cockpit
Control loop, the control loop and the controller (312) wired connection send control letter to the controller (312)
Number, the controller (312) controls the hydraulic stem (332) and shrinks and extend.
5. a kind of suspension type folding rotor craft according to claim 4, which is characterized in that the fixing axle (336)
It is mounted on one end that the folding wings (32) are docked with the fixed-wing (31).
6. a kind of suspension type folding rotor craft according to claim 1, which is characterized in that on the folding wings (32)
There are two the suspension rotors (4) for suspension.
7. a kind of suspension type folding rotor craft according to claim 1, which is characterized in that fuselage (1) two sides
The dalta wing (3) on be respectively arranged with duct (5), and the duct (5) with respect to fuselage (1) it is symmetrical.
8. a kind of suspension type folding rotor craft according to claim 7, which is characterized in that set in the duct (5)
It is equipped with propeller (6).
9. a kind of suspension type folding rotor craft according to claim 1, which is characterized in that the suspension rotor (4)
It is fixedly connected by suspension assembly with the dalta wing (3).
10. a kind of suspension type folding rotor craft according to claim 9, which is characterized in that the suspension assembly packet
Include the overarm (41) for being vertically fixed on the dalta wing (3) bottom, and with described overarm (41) installation frame connected vertically
(42), the suspension rotor is fixedly mounted on the installation frame (42).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274762.5A CN109263901A (en) | 2018-10-30 | 2018-10-30 | A kind of suspension type folding rotor craft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274762.5A CN109263901A (en) | 2018-10-30 | 2018-10-30 | A kind of suspension type folding rotor craft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109263901A true CN109263901A (en) | 2019-01-25 |
Family
ID=65194531
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811274762.5A Withdrawn CN109263901A (en) | 2018-10-30 | 2018-10-30 | A kind of suspension type folding rotor craft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109263901A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2021154759A (en) * | 2020-03-25 | 2021-10-07 | 三菱重工業株式会社 | Wing and aircraft |
-
2018
- 2018-10-30 CN CN201811274762.5A patent/CN109263901A/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2021154759A (en) * | 2020-03-25 | 2021-10-07 | 三菱重工業株式会社 | Wing and aircraft |
| JP7346347B2 (en) | 2020-03-25 | 2023-09-19 | 三菱重工業株式会社 | wings and aircraft |
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| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20190125 |
|
| WW01 | Invention patent application withdrawn after publication |