CN105775113B - It is a kind of can vector controlled gyroplane - Google Patents
It is a kind of can vector controlled gyroplane Download PDFInfo
- Publication number
- CN105775113B CN105775113B CN201610330353.7A CN201610330353A CN105775113B CN 105775113 B CN105775113 B CN 105775113B CN 201610330353 A CN201610330353 A CN 201610330353A CN 105775113 B CN105775113 B CN 105775113B
- Authority
- CN
- China
- Prior art keywords
- fuselage
- winglet
- gyroplane
- rotor
- pad
- 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.)
- Active
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/02—Gyroplanes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention provide it is a kind of can vector controlled gyroplane, including fuselage, the fuselage bottom be provided with mainmast；The body upper is provided with rotor structure, and the rotor structure includes pad and several uniform rotor blades being connected on pad, and axis column one end is connected with mainmast, and the axis column other end is connected with the rotor head positioned at pad upper end；The rear portion of the fuselage is symmetrically arranged with two winglets, and the winglet dead astern is provided with empennage, is connected between the empennage and winglet by two symmetrically arranged connecting rods；It is provided with nose-gear at the head of the fuselage, undercarriage after the end of two winglet is symmetrically arranged with two.Described in the invention can vector controlled gyroplane it is reasonable in design, controlled by Vector modulation, better performance is provided with orientation, speed, regulation body pitching stability, roll stability and speed stability etc., improves the navigability of gyroplane and the stability of flight.
Description
Technical field
The invention belongs to gyroplane field, more particularly, to it is a kind of can vector controlled gyroplane.
Background technology
Gyroplane belongs to gyroplane, typically using autorotating rotor as lifting surface, plus propulsion plant (such as spiral
Oar push/pull power) flown as onward impulse to realize, existing fixed wing aircraft exists due to horizontal stroke during flight is turned
Side coupling needs to tilt the problem of turning, and causes aircraft altitude to decline, and the stability of aircraft reduces.
The content of the invention
In view of this, the invention be directed to it is a kind of can vector controlled gyroplane, with solve aircraft flight turn
The problem of turning need to be rolled when curved.
To reach above-mentioned purpose, what the technical scheme of the invention was realized in：
It is a kind of can vector controlled gyroplane, including fuselage, the fuselage bottom be provided with along the fuselage length direction
The mainmast of extension；The body upper is provided with rotor structure, and the rotor structure includes pad and several are uniformly connected
Rotor blade on pad, the pad middle part are provided with mounting hole, bearing, axis column one are provided with the mounting hole
End be connected with mainmast, the axis column other end pass through mounting hole in bearing after be located at pad upper end rotor head phase
Even；The rear portion of the fuselage is symmetrically arranged with two winglets, and one end of the winglet is connected with fuselage, the winglet other end to
Fuselage outer side extends, and the winglet dead astern is provided with empennage, and the empennage includes the tailplane parallel with the winglet, institute
State tailplane both ends and be symmetrically arranged with two main vertical tails, rudder, the level are provided with the main vertical tail
Empennage upper end is evenly arranged with several additional vertical empennages, and it is adjacent thereto that the tailplane upper end is located at main vertical tail
Place is provided with elevator between additional vertical empennage, passes through connecting rod phase between the main vertical tail and the winglet of its homonymy
Even；It is provided with nose-gear at the head of the fuselage, undercarriage after the end of two winglet is symmetrically arranged with two；Institute
State back body and be provided with vector motor, propeller is provided with the vector motor.
Further, the pad is the monolithic construction with three connection blades, is used between each connection blade
Arc connects.
Further, the quantity of the rotor blade is three, is connected blade with three respectively and is connected, each rotor blade
Junction with being connected blade is provided with two mounting holes, and the mounting hole nearer from the installation center of circle is screw and nut fixing hole, from
It is pin hole to install the mounting hole of the center of circle farther out, and cork wood latch is inserted with the pin hole.
Further, the leading edge of each rotor blade is embedded with an iron wire extended along rotor blade length direction.
Further, the fuselage uses square carbon beam as fuselage keel.
Further, the fore-body is provided with the neck extended along fuselage length direction, is provided with the neck
The battery case that can be slided along the neck, is provided with battery in the battery case.
Further, the upper surface of the winglet is curved surface.
Relative to prior art, described in the invention can the gyroplane of vector controlled have the advantage that：
1st, due to autorotation, tip speed is smaller, therefore is not easy advancing blade shock stall occur, and forward flight speed can
To improve a lot, and the tail-rotor of reaction torque need not be balanced, structure greatly simplifies；
2nd, rotor relies on front incoming in flight course to drive its rotation, and rotor is in autorotation all the time, is gyroplane
Lift is provided, once engine cut-off, gyroplane can also be automatically into the autorotative glide stage, can in the absence of low speed region of avoidance
To ensure the security in flight course well；
3rd, during regular descent, by rotor control, point type can be achieved and land, reduce the requirement to landing site；
4th, controlled by Vector modulation, in orientation, speed, regulation body pitching stability, roll stability and velocity-stabilization
Property etc. be provided with better performance, particularly by respectively adding a winglet in fuselage both sides, vector control is formed with rotor rudder face
System, improve the navigability of gyroplane and the stability of flight.
Brief description of the drawings
The accompanying drawing for forming the part of the invention is used for providing further understanding the invention, present invention wound
The schematic description and description made is used to explain the invention, does not form the improper restriction to the invention.
In accompanying drawing：
Fig. 1 is the structural representation of the invention；
Fig. 2 is the partial enlarged drawing of the empennage of the invention；
Fig. 3 is the structural representation of the pad of innovation and creation.
Description of reference numerals：
1- fuselages；2- pads；201- connection blades；202- pin holes；203- screw and nut fixing holes；204- mounting holes；
3- rotor blades；4- axis columns；5- winglets；6- connecting rods；7- empennages；701- tailplanes；702- elevators；703- master is hung down
Fin；704- rudders；705- additional vertical empennages；8- nose-gears；Undercarriage after 9-.
Embodiment
It should be noted that in the case where not conflicting, the feature in embodiment and embodiment in the invention can
To be mutually combined.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", " on ", " under ",
The orientation or position relationship of the instruction such as "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " are
Based on orientation shown in the drawings or position relationship, it is for only for ease of description the invention and simplifies description, rather than instruction
Or imply that signified device or element must have specific orientation, with specific azimuth configuration and operation, therefore be not understood that
For the limitation to the invention.In addition, term " first ", " second " etc. are only used for describing purpose, and it is not intended that instruction
Or imply relative importance or the implicit quantity for indicating indicated technical characteristic.Thus, " first ", " second " etc. are defined
Feature can express or implicitly include one or more this feature.In the description of the invention, unless separately
It is described, " multiple " are meant that two or more.
, it is necessary to which explanation, unless otherwise clearly defined and limited, term " are pacified in the description of the invention
Dress ", " connected ", " connection " should be interpreted broadly, for example, it may be fixedly connected or be detachably connected, or integratedly
Connection；Can be mechanical connection or electrical connection；Can be joined directly together, can also be indirectly connected by intermediary,
It can be the connection of two element internals.For the ordinary skill in the art, on being understood by concrete condition
State concrete meaning of the term in the invention.
Describe the invention in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
As Figure 1-3, it is a kind of can vector controlled gyroplane, including fuselage 1, the fuselage 1 made using square carbon beam
For fuselage keel, because fuselage keel peripheral parts are slab construction, it is too small that circular carbon beam is in contact with it area, easily occurs
It is rotary shifted, and the contact area of square structure increase carbon beam and each part, stability and degree of safety are improved, solves circle
Structure holds the problem of can't stand excessive torque and not easy to install fixed circular carbon beam, and the bottom of fuselage 1 is provided with along described
The mainmast of the length direction of fuselage 1 extension.
The top of fuselage 1 is provided with rotor structure, and the rotor structure includes pad 2 and several are uniformly connected to pad
Rotor blade 3 on piece 2, the leading edge of each rotor blade 3 are made embedded with an iron wire along the extension of the length direction of rotor blade 3
For the counterweight of rotor blade, avoid, because wind-force reason makes rotor blade 3 produce counter-rotary-ing phenomenon, strengthening the steadiness of rotor blade 3, making
Be unlikely to deform, the middle part of the pad 2 is provided with mounting hole 204, and bearing, axis column 4 one are provided with the mounting hole 204
End be connected with mainmast, the other end of axis column 4 pass through mounting hole 204 in bearing after be located at the upper end of pad 2 rotation
Wing head is connected,
Rotor head is the main stressed member of rotor structure, is connected with pitching operating shaft and tilting manipulation axle, rotor structure
By the plane where rotor head, rotated around bearing centre, and controlled by controlling pitching operating shaft and rolling operating shaft
The action of rotor processed, is adjusted to flight attitude, pre- cyclone is provided with the rotor head, the pre- cyclone is by gear
Transmission decelerating device and the automatic device two parts that disconnect form, and in standby for takeoff state, rotor blade 3 passes through gear transmission reducing
The motor connection of device and gyroplane, when motor throttle gradually increases, gyroplane enters the work(in takeoff stage, now motor
Rate is mostly used in driving propeller, and fraction is used to drive pre- cyclone to prewhirl rotor blade, produces the liter of part
Power and rotor inertia, it is automatic to disconnect device life when rotor blade rotating speed reaches a certain particular value after aircraft normally takes off
Effect, the transmission device between rotor and motor is disconnected, now rotor blade only relies on front incoming and drives its rotation, motor
Power is completely used for driving propeller, and pre- cyclone can greatly shorten the ground run distance needed for gyroplane, reduce gyroplane pair
In the degree of dependence for the wind-force that takes off, reduce when gyroplane takes off to the length requirement of runway.
Further, the pad 2 is the monolithic constructions with three connection blades 201, it is each connect blade 201 it
Between connected using arc, the quantity of the rotor blade 3 is three, and it is connected be connected blade 201 with three respectively, monoblock type arc
The arcuate structure of pad 2 reduces area compared to circular configuration, mitigates aircraft weight, the pad knot independent compared to three
Structure, the interaction between each rotor blade 3 is increased, strengthen the structural strength of pad 2, three pieces of prominent connection blades
Connected between 201 with arch section, delayed the structure fatigue damage of pad 2, improve the monolithic stability degree of rotor, and reduced
Rotor difference to adverse effect caused by fuselage,
Each rotor blade 3 is provided with two mounting holes with being connected the junction of blade 201, nearer from the installation center of circle
Mounting hole is screw and nut fixing hole 203, and the position of rotor blade 3 is positioned, and is from the mounting hole of the installation center of circle farther out
Pin hole 202, cork wood latch is inserted with the pin hole 202, when the stress of rotor blade 3 is in certain range of stress, cork wood
Latch can also play fixation, and two point fixations can determine the position of rotor blade 3 completely, be subject to when rotor blade 3
When stress exceedes the strength degree of latch, latch fracture, rotor blade 3 can be revolved around screw in the plane of rotor head
Transhipment is dynamic, and so as to protect rotor blade 3 to be not easy to be broken off because being damaged by hardness, increase rotor blade 3 uses the longevity
Life.
The rear portion of the fuselage 1 is symmetrically arranged with two winglets 5, and one end of the winglet 5 is connected with fuselage 1, described small
The other end of the wing 5 extends to the outside of fuselage 1, and the upper surface of the winglet 5 is flexure plane, according to bernoulli principle, upper surface air-flow
Flow velocity is fast, and air is smaller to the pressure of wing, and lower surface air-flow velocity is slow, and air is larger to the pressure of wing, this generates
One pressure differential, also just generates upward lift, and when turning, winglet 5 can provide a torque, and balance rotor acts on
Torque on fuselage, in take-off process, winglet 5 is used as high lift device, moreover it is possible to provides a part of lift for gyroplane, further
Shorten ground run distance；During cruise, winglet 5 is similar to balancing pole, can play a part of improving aircraft stability,
The dead astern of winglet 5 is provided with empennage 7, and the empennage 7 includes the tailplane 701 parallel with the winglet 5,
The both ends of tailplane 701 are symmetrically arranged with two main vertical tails 703, and direction is provided with the main vertical tail 703
Rudder 704, the upper end of tailplane 701 are evenly arranged with several additional vertical empennages 705, the upper end of tailplane 701
Place is provided with elevator 702 between the additional vertical empennage 705 adjacent thereto positioned at main vertical tail 703, outermost two
Main vertical tail 703 can change control surface deflection angle, rudder face shape is had a certain degree, and control the driftage of gyroplane, inner side
Additional vertical empennage 705 helps aircraft balanced course, there is provided aircraft Lateral static stability, the rudder face of elevator 702 can form one
Fixed angle, the pitching of gyroplane is controlled, passes through the phase of connecting rod 6 between the main vertical tail 703 and the winglet 5 of its homonymy
Even, the integraty and stability of winglet and empennage are enhanced.
The gyroplane uses tricycle landing gear structure, and nose-gear 8 is provided with the head of the fuselage 1, described
Undercarriage 9 after the end of two winglets is symmetrically arranged with two.
The rear end of fuselage 1 is provided with vector motor, and propeller is provided with the vector motor, and vector motor can drive
While dynamic propeller is rotated, change motor central axis direction in certain angle, so as to produce the thrust of different directions.
The front portion of fuselage 1 is provided with the neck extended along the length direction of fuselage 1, and being provided with the neck can be along described
The battery case that neck slides, battery is provided with the battery case, battery weight can be relied on to adjust the position of centre of gravity of gyroplane.
The preferred embodiment of the invention is the foregoing is only, is not intended to limit the invention creation, it is all at this
Within the spirit and principle of innovation and creation, any modification, equivalent substitution and improvements made etc., the invention should be included in
Protection domain within.
Claims (4)
1. it is a kind of can vector controlled gyroplane, it is characterised in that：Including fuselage (1), fuselage (1) bottom is provided with along institute
State the mainmast of fuselage (1) length direction extension；
Rotor structure is provided with above the fuselage (1), the rotor structure includes pad (2) and several are uniformly connected to pad
Rotor blade (3) on piece (2), pad (2) middle part are provided with mounting hole (204), are provided with the mounting hole (204)
Bearing, axis column (4) one end are connected with mainmast, and axis column (4) other end passes through the bearing in mounting hole (204)
It is connected afterwards with the rotor head positioned at pad (2) upper end；
The rear portion of the fuselage (1) is symmetrically arranged with two winglets (5), and one end of the winglet (5) is connected with fuselage (1), institute
Winglet (5) other end is stated to extension on the outside of fuselage (1), described two winglet (5) dead asterns are provided with empennage (7), the empennage
(7) tailplane (701) parallel with the winglet (5) is included, tailplane (701) both ends are symmetrically arranged with two masters
Vertical tail (703), rudder (704) is provided with the main vertical tail (703), tailplane (701) upper end is equal
Even to be provided with several additional vertical empennages (705), tailplane (701) upper end is located at main vertical tail (703) and its
Place is provided with elevator (702), the main vertical tail (703) and its homonymy between adjacent additional vertical empennage (705)
It is connected between winglet (5) by connecting rod (6)；
It is provided with nose-gear (8) at the head of the fuselage (1), the end of two winglet is risen after being symmetrically arranged with two
Fall frame (9)；
Fuselage (1) rear end is provided with vector motor, and propeller is provided with the vector motor；
The pad (2) is the monolithic construction with three connection blades (201), is each used between connection blade (201)
Arc connects；
The quantity of the rotor blade (3) be three, be connected respectively with three blade (201) be connected, each rotor blade (3) and
The junction of connection blade (201) is provided with two mounting holes, and the mounting hole nearer from the installation center of circle is fixed for screw and nut
Hole (203), it is pin hole (202) from the mounting hole of the installation center of circle farther out, cork wood latch is inserted with the pin hole (202)；
The leading edge of each rotor blade (3) is embedded with an iron wire extended along rotor blade (3) length direction.
2. it is according to claim 1 can vector controlled gyroplane, it is characterised in that：The fuselage (1) uses square carbon
Bar is as fuselage keel.
3. it is according to claim 1 can vector controlled gyroplane, it is characterised in that：Fuselage (1) front portion is provided with
Along the neck of fuselage (1) length direction extension, the battery case that can be slided along the neck, the battery are provided with the neck
Battery is provided with groove.
4. it is according to claim 1 can vector controlled gyroplane, it is characterised in that：The upper surface of the winglet (5) is
Curved surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610330353.7A CN105775113B (en) | 2016-05-17 | 2016-05-17 | It is a kind of can vector controlled gyroplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610330353.7A CN105775113B (en) | 2016-05-17 | 2016-05-17 | It is a kind of can vector controlled gyroplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105775113A CN105775113A (en) | 2016-07-20 |
| CN105775113B true CN105775113B (en) | 2018-01-16 |
Family
ID=56378953
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610330353.7A Active CN105775113B (en) | 2016-05-17 | 2016-05-17 | It is a kind of can vector controlled gyroplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105775113B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108594839B (en) * | 2018-05-22 | 2019-06-28 | 深圳智航无人机有限公司 | Control method, aircraft and storage medium based on more vectoring technologies |
| CN109279006A (en) * | 2018-11-16 | 2019-01-29 | 苏州神龙航空科技有限公司 | A kind of gyroplane of variable power |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5301900A (en) * | 1990-12-12 | 1994-04-12 | Groen Henry J | Autogyro aircraft |
| CN200988577Y (en) * | 2005-11-07 | 2007-12-12 | 邵厚洪 | Double airframe triphibian aircraft |
| GB2446589A (en) * | 2007-02-17 | 2008-08-20 | Univ Sheffield | Thrust vectoring in aerial vehicles |
| CN201633921U (en) * | 2010-03-04 | 2010-11-17 | 陈明军 | Helicopter with empennage |
| AU2013360005B2 (en) * | 2012-12-13 | 2015-08-13 | Stoprotor Technology Pty Ltd | Aircraft and methods for operating an aircraft |
| CN103395492B (en) * | 2013-07-10 | 2016-03-02 | 中国航天空气动力技术研究院 | A kind of unpowered short take-off and landing (STOL) unmanned plane turning rotor |
| CN205652346U (en) * | 2016-05-17 | 2016-10-19 | 中国民航大学 | But vector control's gyroplane |
-
2016
- 2016-05-17 CN CN201610330353.7A patent/CN105775113B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN105775113A (en) | 2016-07-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103863563B (en) | A kind of can vertical/STOL canard configuration airplane | |
| CN106043696A (en) | Flying system for unmanned aerial vehicle | |
| CN203946273U (en) | The little minute vehicle of a kind of coaxial double-rotary wing formula | |
| WO2017000156A1 (en) | Double-blade tandem helicopter | |
| CN101274666A (en) | Split type wing | |
| CN102673780A (en) | Double-configuration aircraft | |
| CN205998126U (en) | A kind of unmanned plane during flying system | |
| CN109319110A (en) | A kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure | |
| CN104417750A (en) | Tandem tilt rotor aircraft | |
| CN105775113B (en) | It is a kind of can vector controlled gyroplane | |
| CN109263931A (en) | A kind of VTOL aircraft | |
| CN204507261U (en) | A kind of coaxial many in the same way helighros | |
| CN108622402A (en) | A kind of combined type VTOL long endurance unmanned aircraft | |
| CN115214881A (en) | Electric tilt rotor aircraft | |
| CN107878747A (en) | A kind of Fixed Wing AirVehicle of VTOL | |
| CN205652346U (en) | But vector control's gyroplane | |
| WO2018103458A1 (en) | Tandem-wing unmanned aerial vehicle | |
| CN206664931U (en) | A kind of tilted propeller can VTOL high-speed aircraft | |
| CN105217026A (en) | A kind of compound type aircraft | |
| CN104943859A (en) | Unmanned helicopter | |
| CN207917144U (en) | One kind is verted wing helicopter | |
| CN105197234A (en) | Combined aircraft provided with empennage | |
| CN110282127A (en) | A kind of tailstock formula unmanned plane | |
| CN202481307U (en) | Four-propeller aircraft taking off and landing vertically | |
| CN205131655U (en) | Compound aircraft of tape trailer wing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20221012 Address after: AVIC Science Park, No. 9, Guangxuan Road, Dongli District, Tianjin 300300 Patentee after: Ma Chao Patentee after: Tianjin Zero One Intelligent Technology Co.,Ltd. Address before: 300000 Tianjin Dongli Binhai International Airport Patentee before: CIVIL AVIATION University OF CHINA |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20221212 Address after: AVIC Science Park, No. 9, Guangxuan Road, Dongli District, Tianjin 300300 Patentee after: Tianjin Weite Aviation Technology Co.,Ltd. Address before: AVIC Science Park, No. 9, Guangxuan Road, Dongli District, Tianjin 300300 Patentee before: Ma Chao Patentee before: Tianjin Zero One Intelligent Technology Co.,Ltd. |