CN205652346U - But vector control's gyroplane - Google Patents
But vector control's gyroplane Download PDFInfo
- Publication number
- CN205652346U CN205652346U CN201620454321.3U CN201620454321U CN205652346U CN 205652346 U CN205652346 U CN 205652346U CN 201620454321 U CN201620454321 U CN 201620454321U CN 205652346 U CN205652346 U CN 205652346U
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- Prior art keywords
- fuselage
- gyroplane
- blade
- winglet
- rotor
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Abstract
The utility creatively provides a but vector control's gyroplane, the reciprocating impact tunnel drilling machine comprises a machine body, the fuselage bottom is provided with the mainmast, the fuselage top is provided with wing structure soon, revolving wing structure and including that gasket and a plurality of evenly connect the rotor blade on the gasket, axis stand one end is continuous with the mainmast, the axis stand other end links to each other with the rotor head that is located the gasket upper end, the rear portion symmetry of fuselage is provided with two winglets, the winglet dead astern is provided with the fin, the connecting rod that sets up through two symmetries between fin and the winglet links to each other, the aircraft nose department of fuselage is provided with the nose -gear, the tip department symmetry of two winglets is provided with two back undercarriages. The utility model discloses create but vector control's gyroplane structural design reasonable, by vectorial resultant control, had better performance in the aspect of position, speed, regulation fuselage pitching stability, lift -over stability and speed stability etc. Improved the navigability of gyroplane and the stability of flight.
Description
Technical field
The invention belongs to gyroplane field, especially relate to a kind of can the gyroplane of vector controlled.
Background technology
Gyroplane belongs to gyroplane, typically using autorotating rotor as lifting surface, adds propelling dress
Putting (such as propeller push/pull power) and realize flight as onward impulse, existing fixed wing airplane is flying
During row is turned, there is the problem turned due to the tilt of horizontal side coupling needs, cause aircraft altitude
Declining, the stability of aircraft reduces.
Summary of the invention
In view of this, the invention be directed to a kind of can the gyroplane of vector controlled, to solve aircraft
The problem that need to roll turning when flight is turned.
For reaching above-mentioned purpose, the technical scheme of the invention is achieved in that
A kind of can the gyroplane of vector controlled, including fuselage, described fuselage bottom is provided with along described fuselage
The mainmast that length direction extends；Described body upper is provided with rotor structure, and described rotor structure includes
Pad is uniformly connected to the rotor blade on pad with several, is provided with installing hole in the middle part of described pad,
Being provided with bearing in described installing hole, axis column one end is connected with mainmast, described axis column another
End is connected with the rotor head being positioned at pad upper end after the bearing in installing hole；The rear portion pair of described fuselage
Claiming to be provided with two winglets, one end of described winglet is connected with fuselage, and the described winglet other end is outside fuselage
Side extends, and described winglet dead astern is provided with empennage, and described empennage includes the level parallel with described winglet
Empennage, described tailplane two ends are symmetrically arranged with two main vertical tails, described main vertical tail set
Being equipped with rudder, described tailplane upper end is evenly arranged with several additional vertical empennages, described level
Empennage upper end is provided with elevator in place between the additional vertical empennage that main vertical tail is adjacent, institute
State and be connected by connecting rod between main vertical tail and the winglet of its homonymy；Arrange at the head of described fuselage
Undercarriage after having nose-gear, the end of described two winglets to be symmetrically arranged with two；Described back body
It is provided with vector motor, described vector motor is provided with propeller.
Further, described pad is with three monolithic constructions connecting blade, each connection blade
Between use arc connect.
Further, the quantity of described rotor blade is three, is connected blade respectively with three and is connected, often
Individual rotor blade is provided with two installing holes with the junction being connected blade, from the installation installed close to the center of circle
Hole is screw and nut fixing hole, is pin hole from installing center of circle installing hole farther out, described pin hole interpolation
There is cork wood latch.
Further, the leading edge of each rotor blade is all embedded with one along the extension of rotor blade length direction
Iron wire.
Further, described fuselage uses square carbon beam as fuselage Os Draconis.
Further, described fore-body is provided with the draw-in groove extended along fuselage length direction, described draw-in groove
Inside it is provided with the battery case that can slide along described draw-in groove, in described battery case, is provided with battery.
Further, the upper surface of described winglet is curved surface.
Relative to prior art, can the gyroplane of vector controlled have following excellent described in the invention
Gesture:
1, due to autorotation, tip speed is less, is therefore not easy advancing blade shock stall occur,
Forward flight speed can improve a lot, and without balancing the tail-rotor of reaction torque, structure is greatly simplified；
2, during rotor relies on flight course, its rotation of driving is flowed in front, and rotor is in autorotation all the time,
For gyroplane provide lift, once engine cut-off, gyroplane can also automatically into the autorotative glide stage,
There is not low speed region of avoidance, the safety in flight course can be ensured well；
3, during regular descent, by rotor control, point type can be realized and land, reduce landing site
Requirement；
4, by Vector modulation control, in orientation, speed, regulation body pitching stability, roll stabilization
The aspect such as property and speed stability is provided with better performance, little particularly by respectively adding one in fuselage both sides
The wing, forms vector controlled with rotor rudder face, improves the navigability of gyroplane and the stability of flight.
Accompanying drawing explanation
The accompanying drawing of the part constituting the invention is used for providing being further appreciated by the invention,
The schematic description and description of the invention is used for explaining the invention, is not intended that this
The improper restriction of bright creation.In the accompanying drawings:
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-fuselage；2-pad；201-connects blade；202-pin hole；203-screw and nut fixing hole；
204-installing hole；3-rotor blade；4-axis column；5-winglet；6-connecting rod；7-empennage；701-
Tailplane；702-elevator；The main vertical tail of 703-；704-rudder；705-additional vertical empennage；
8-nose-gear；Undercarriage after 9-.
Detailed description of the invention
It should be noted that in the case of not conflicting, in embodiment in the invention and embodiment
Feature can be mutually combined.
In the description of the invention, it is to be understood that term " " center ", " longitudinally ", " horizontal stroke
To ", " on ", D score, "front", "rear", "left", "right", " vertically ", " water
Flat ", the orientation that indicates of " top ", " end ", " interior ", " outward " etc. or position relationship be based on attached
Orientation shown in figure or position relationship, be for only for ease of description the invention and simplify description, and not
Be instruction or the hint device of indication or element must have specific orientation, with specific azimuth configuration and
Operation, therefore it is not intended that restriction to the invention.Additionally, term " first ", " second "
Etc. being only used for describing purpose, and it is not intended that instruction or hint relative importance or implicit indicate indication
The quantity of the technical characteristic shown.Thus, the feature defining " first ", " second " etc. can be expressed
Or implicitly include one or more this feature.In the description of the invention, unless otherwise
Illustrating, " multiple " are meant that two or more.
In the description of the invention, it should be noted that unless otherwise clearly defined and limited,
Term " is installed ", " being connected ", " connection " should be interpreted broadly, and connects for example, it may be fixing,
Can also be to removably connect, or be integrally connected；Can be to be mechanically connected, it is also possible to be electrical connection；
Can be to be joined directly together, it is also possible to be indirectly connected to by intermediary, can be the company of two element internals
Logical.For the ordinary skill in the art, can understand that above-mentioned term is at this by concrete condition
Concrete meaning in innovation and creation.
Describe the invention below with reference to the accompanying drawings and in conjunction with the embodiments in detail.
As Figure 1-3, a kind of can the gyroplane of vector controlled, including fuselage 1, described fuselage 1 is adopted
With square carbon beam as fuselage Os Draconis, because fuselage Os Draconis peripheral parts is slab construction, circular carbon beam
It is in contact with it area the least, is susceptible to rotary shifted, and square structure increases carbon beam and each parts
Contact area, improves stability and degree of safety, solves circular configuration and holds and can't stand excessive torque and circle
Shape carbon beam is difficult to install fixing problem, is provided with along described fuselage 1 length direction bottom described fuselage 1
The mainmast extended.
Described fuselage 1 is provided above rotor structure, and described rotor structure includes that pad 2 and several are equal
The even rotor blade 3 being connected on pad 2, the leading edge of each rotor blade 3 is all embedded with one along rotor
The iron wire that blade 3 length direction extends is as the counterweight of rotor blade, it is to avoid because wind-force reason makes rotor leaf
Sheet 3 produces counter-rotary-ing phenomenon, strengthens rotor blade 3 steadiness, is allowed to be unlikely to deform, in described pad 2
Portion is provided with installing hole 204, is provided with bearing, axis column 4 one end and master in described installing hole 204
Mast is connected, described axis column 4 other end through after the bearing in installing hole 204 be positioned at pad 2
The rotor head of upper end is connected,
Rotor head is the main stressed member of rotor structure, is connected with pitching operating shaft and tilting manipulation axle,
The rotor structure plane by rotor head place, rotates around bearing centre, and grasps by controlling pitching
Control axle and inclination operating shaft control the action of rotor, are adjusted flight attitude, at described rotor head
Being provided with pre-cyclone, described pre-cyclone is by gear transmission reducing device and automatically disconnects device two parts
Composition, in standby for takeoff state, rotor blade 3 is by the motor of gear transmission reducing device with gyroplane
Connecting, when motor throttle is gradually increased, gyroplane enters the rolling start stage, and now the power of motor is big
Part is used for driving propeller, fraction to be used for driving pre-cyclone to prewhirl rotor blade, produces
The lift of part and rotor inertia, after aircraft normally takes off, rotor blade rotating speed reaches a certain specific
During value, automatically disconnect device and come into force, the actuating device between rotor and motor is disconnected, now rotor leaf
Sheet only relies on front and flows its rotation of driving, and the power of motor is completely used for driving propeller, pre-cyclone
The ground run distance needed for gyroplane can be greatly shortened, reduce the gyroplane dependence journey for the wind-force that takes off
Degree, reduces the length requirement to runway when gyroplane takes off.
Further, described pad 2 is with three monolithic constructions connecting blade 201, Mei Gelian
Connecing and use arc to connect between blade 201, the quantity of described rotor blade 3 is three, respectively with three
Connecting blade 201 to be connected, the arcuate structure of monoblock type arc spacer 2 is compared circular configuration and is decreased part
Area, alleviates aircraft weight, compares three independent gasket constructions, increases between each rotor blade 3
Interaction, strengthen the structural strength of pad 2, with arc between three pieces of prominent connection blades 201
Shape part connects, and has delayed the structure fatigue damage of pad 2, has improve the monolithic stability degree of rotor, and
Decrease the adverse effect that fuselage is produced by rotor difference,
Each rotor blade 3 is provided with two installing holes with the junction being connected blade 201, from installation
The nearer installing hole in the center of circle is screw and nut fixing hole 203, positions the position of rotor blade 3,
It is pin hole 202 from installing center of circle installing hole farther out, in described pin hole 202, is inserted with cork wood latch,
When rotor blade 3 stress is in certain range of stress, cork wood latch can also play fixation, and two
The fixing position that can determine rotor blade 3 completely of point, when rotor blade 3 subjected to stress exceedes latch
Strength degree time, latch rupture, rotor blade 3 can be carried out in the plane of rotor head around screw
Rotary motion, thus protect rotor blade 3 to be not easy, because being broken off by rigid damage, to increase rotation
The service life of wing blade 3.
The rear portion of described fuselage 1 is symmetrically arranged with two winglets 5, one end of described winglet 5 and fuselage 1
Being connected, described winglet 5 other end extends outside fuselage 1, and the upper surface of described winglet 5 is flexure plane,
According to bernoulli principle, upper surface air-flow velocity is fast, and air is less to the pressure of wing, lower surface air-flow
Flow velocity is slow, and air is relatively big to the pressure of wing, this generates a pressure differential, the most just creates upwards
Lift, when turning, winglet 5 can provide a moment, and balance rotor acts on the power on fuselage
Square, in take-off process, winglet 5 is as high lift device, moreover it is possible to provide a part of lift for gyroplane,
Shorten ground run distance further；During cruise, winglet 5 is similar to the gimbal lever, can play raising and fly
The effect of machine stability,
Described winglet 5 dead astern is provided with empennage 7, and described empennage 7 includes parallel with described winglet 5
Tailplane 701, described tailplane 701 two ends are symmetrically arranged with two main vertical tails 703, institute
Stating and be provided with rudder 704 on main vertical tail 703, described tailplane 701 upper end is evenly arranged with
Several additional vertical empennages 705, described tailplane 701 upper end be positioned at main vertical tail 703 and its
Between adjacent additional vertical empennage 705, place is provided with elevator 702, outermost two main vertical ends
The wing 703 can change control surface deflection angle, makes rudder face shape have a certain degree, and controls the driftage of gyroplane,
The additional vertical empennage 705 of inner side helps aircraft balanced course, it is provided that aircraft Lateral static stability, lifting
Rudder 702 rudder face can have a certain degree with shape, controls the pitching of gyroplane, described main vertical tail 703
And it is connected by connecting rod 6 between the winglet 5 of its homonymy, enhances the integraty of winglet and empennage with steady
Qualitative.
This gyroplane uses tricycle landing gear structure, rises and falls before being provided with at the head of described fuselage 1
Frame 8, the end of described two winglets be symmetrically arranged with two after undercarriage 9.
Described fuselage 1 rear end is provided with vector motor, and described vector motor is provided with propeller, vector
While motor can rotate driving propeller, in certain angle, change motor central axis direction, from
And produce the thrust of different directions.
Described fuselage 1 front portion is arranged in being provided with the draw-in groove extended along fuselage 1 length direction, described draw-in groove
There is the battery case that can slide along described draw-in groove, in described battery case, be provided with battery, battery weight can be relied on
Adjust the position of centre of gravity of gyroplane.
The foregoing is only the preferred embodiment of the invention, not in order to limit present invention wound
Make, within all spirit in the invention and principle, any modification, equivalent substitution and improvement made
Deng, within should be included in the protection domain of the invention.
Claims (7)
1. one kind can the gyroplane of vector controlled, it is characterised in that: include fuselage (1), described fuselage
(1) bottom is provided with the mainmast extended along described fuselage (1) length direction；
Described fuselage (1) is provided above rotor structure, described rotor structure include pad (2) and if
Dry the rotor blade (3) being uniformly connected on pad (2), described pad (2) middle part is provided with
Installing hole (204), is provided with bearing in described installing hole (204), axis column (4) one end with
Mainmast is connected, described axis column (4) other end through after the bearing in installing hole (204) with position
Rotor head in pad (2) upper end is connected；
The rear portion of described fuselage (1) is symmetrically arranged with two winglets (5), the one of described winglet (5)
End is connected with fuselage (1), and described winglet (5) other end extends to fuselage (1) outside, and described two
Individual winglet (5) dead astern is provided with empennage (7), and described empennage (7) includes and described winglet (5)
Parallel tailplane (701), it is vertical that described tailplane (701) two ends are symmetrically arranged with two masters
Empennage (703), described main vertical tail (703) is provided with rudder (704), described level
Empennage (701) upper end is evenly arranged with several additional vertical empennages (705), described tailplane (701)
Upper end is positioned at place between the additional vertical empennage (705) that main vertical tail (703) is adjacent and is provided with
Elevator (702), by even between the winglet (5) of described main vertical tail (703) and its homonymy
Extension bar (6) is connected；
Nose-gear (8), the end pair of described two winglets it is provided with at the head of described fuselage (1)
Undercarriage (9) after claiming to be provided with two；
Described fuselage (1) rear end is provided with vector motor, and described vector motor is provided with propeller.
The most according to claim 1 can the gyroplane of vector controlled, it is characterised in that: described pad
Sheet (2) is with three monolithic constructions connecting blade (201), each connection blade (201)
Between use arc connect.
The most according to claim 2 can the gyroplane of vector controlled, it is characterised in that: described rotation
The quantity of wing blade (3) is three, is connected blade (201) respectively with three and is connected, each rotor leaf
Sheet (3) is provided with two installing holes with the junction being connected blade (201), from installing close to the center of circle
Installing hole be screw and nut fixing hole (203), be pin hole from installing center of circle installing hole farther out
(202), it is inserted with cork wood latch in described pin hole (202).
The most according to claim 1 can the gyroplane of vector controlled, it is characterised in that: Mei Gexuan
The leading edge of wing blade (3) is all embedded with an iron wire extended along rotor blade (3) length direction.
The most according to claim 1 can the gyroplane of vector controlled, it is characterised in that: described machine
Body (1) uses square carbon beam as fuselage Os Draconis.
The most according to claim 1 can the gyroplane of vector controlled, it is characterised in that: described machine
Body (1) front portion is provided with the draw-in groove extended along fuselage (1) length direction, and being provided with in described draw-in groove can
The battery case slided along described draw-in groove, is provided with battery in described battery case.
The most according to claim 1 can the gyroplane of vector controlled, it is characterised in that: described little
The upper surface of the wing (5) is curved surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620454321.3U CN205652346U (en) | 2016-05-17 | 2016-05-17 | But vector control's gyroplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620454321.3U CN205652346U (en) | 2016-05-17 | 2016-05-17 | But vector control's gyroplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205652346U true CN205652346U (en) | 2016-10-19 |
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ID=57403867
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620454321.3U Expired - Fee Related CN205652346U (en) | 2016-05-17 | 2016-05-17 | But vector control's gyroplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205652346U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105775113A (en) * | 2016-05-17 | 2016-07-20 | 中国民航大学 | Rotary-wing aircraft capable of realizing vector control |
| CN109050880A (en) * | 2018-09-27 | 2018-12-21 | 西安爱生技术集团公司 | A kind of full-height foam core unmanned plane rudder face rocker arm mounting structure |
-
2016
- 2016-05-17 CN CN201620454321.3U patent/CN205652346U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105775113A (en) * | 2016-05-17 | 2016-07-20 | 中国民航大学 | Rotary-wing aircraft capable of realizing vector control |
| CN109050880A (en) * | 2018-09-27 | 2018-12-21 | 西安爱生技术集团公司 | A kind of full-height foam core unmanned plane rudder face rocker arm mounting structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161019 Termination date: 20180517 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |