CN107161324A - Gyroplane empennage assembly structure - Google Patents
Gyroplane empennage assembly structure Download PDFInfo
- Publication number
- CN107161324A CN107161324A CN201710440641.2A CN201710440641A CN107161324A CN 107161324 A CN107161324 A CN 107161324A CN 201710440641 A CN201710440641 A CN 201710440641A CN 107161324 A CN107161324 A CN 107161324A
- Authority
- CN
- China
- Prior art keywords
- rudder
- gyroplane
- bracing wire
- assembly structure
- pedal
- 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.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/08—Adjustable control surfaces or members, e.g. rudders bodily displaceable
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/02—Initiating means
- B64C13/04—Initiating means actuated personally
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/26—Transmitting means without power amplification or where power amplification is irrelevant
- B64C13/28—Transmitting means without power amplification or where power amplification is irrelevant mechanical
- B64C13/30—Transmitting means without power amplification or where power amplification is irrelevant mechanical using cable, chain, or rod mechanisms
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8263—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like
- B64C2027/8272—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like comprising fins, or movable rudders
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Automation & Control Theory (AREA)
- Toys (AREA)
Abstract
The invention provides a kind of gyroplane empennage assembly structure, it is related to gyroplane technical field, the swing for solving existing gyroplane rudder is not accurate enough, directly influences the technical problem of the safety and reliability of gyroplane flight.Gyroplane empennage assembly structure includes rudder, and the rudder is connected with oscillometer, the swaying direction of the oscillometer energy control direction rudder；The oscillometer includes pedal, bracing wire, pedal gear and empennage transmission mechanism, and the pedal is connected by the front end of the pedal gear and the bracing wire, and the rear end of the bracing wire is connected by empennage transmission mechanism and the rudder.With oscillometer come precisely quickly control direction rudder is swung to the left or to the right, the swing of rudder realizes the turning of gyroplane fuselage；When needing to turn, pin pushes pedals are used, pedal drives bracing wire campaign, and bracing wire can be more convenient directly control direction rudder, be swift in response, and manipulation is flexible.
Description
Technical field
The present invention relates to gyroplane technical field, more particularly, to a kind of gyroplane empennage assembly structure.
Background technology
Gyroplane is that a kind of relative wind using during preceding fly blows autorotation to produce the rotary wing aircraft of lift.It
Thrust directly provided by driven by engine propeller.It is a kind of aircraft between helicopter and aircraft, equipped with rotation
The wing and fixed aerofoil.With landing apart from it is short, can make low speed low-latitude flying, it is simple light and handy, be easy to hidden the features such as, but can not hang down
Straight landing, it can not hover.Available for taking photo in the sky, arm discharge, battlefield scout etc..
Gyroplane and helicopter are simply the same from profile, and substantially gyroplane and helicopter are two kinds complete
Different aircraft.
Gyroplane is actually a kind of aircraft between helicopter and aircraft, and it is removed outside rotor, also with one
The propeller that pair is disposed vertically is also equipped with less wing to provide the power of advance, typically and awing provides part lift.
The maximum difference of gyroplane and helicopter is that the rotor of gyroplane is not connected with engine driving system, and engine is not with drive
Dynamic rotor provides lift for gyroplane, but during gyroplane flies, blows rotor wing rotation by front air-flow and produce liter
Power, as a windmill, rotor system is only driven when starting by self power, is referred to as prewhirl (prerotate), after taking off
By the driving of air effect power；And the rotor of helicopter is connected with engine driving system, lift can be produced, flight can be provided again
Power, as an electric fan.Because rotor is rotation type, the moment of torsion very little on fuselage is delivered to, therefore gyroplane is without picture
Tail-rotor as single-rotor helicopter, but empennage is generally equipped with, to control flight.
Awing, gyroplane be most significantly respectively with helicopter helicopter rotor towards top rake, and gyroplane
Rotor be then sweptback.
Vertical tail abbreviation vertical fin, also referred to as vertical tail, installed in fuselage afterbody, its function is similar with tailplane, is also
For keeping the flight attitude of the in-flight stability of aircraft and control aircraft.The difference is that vertical tail is to make aircraft on a left side
Right (driftage) direction has certain static stability, and controls aircraft in the motion in left and right (driftage) direction.Same level empennage one
Sample, vertical tail by the fixed fin fixed and deflectable rudder unit into.
Rudder is steerable airfoil portion in vertical tail, and it is to carry out yaw control to aircraft that it, which is acted on,.Institute above
Situation about saying assumes that aircraft makees free movement, without pilot guidance.When we need to control the course of aircraft, flight
The rudder that member can be just manipulated in vertical tail reaches the purpose of driftage.The manipulation principle of rudder is similar with elevator, when
When aircraft needs left-hand rotation flight, driver will manipulate rudder and deflect to the left, and now the aerodynamic force suffered by rudder will
The torque for deflecting Nose Left is produced, the course of aircraft also changes therewith.Equally, if pilot control rudder to
Right avertence turns, and the head of aircraft will turn right in the presence of aerodynamic moment.
And the swing of prior art rudder is not accurate enough, the safety and reliability of gyroplane flight is directly influenced.
The content of the invention
It is an object of the invention to provide a kind of gyroplane empennage assembly structure, to solve the pendulum of existing gyroplane rudder
The dynamic technical problem for not enough precisely directly influencing the safety and reliability of gyroplane flight.
To achieve the above object, the invention provides following technical scheme：
A kind of gyroplane empennage assembly structure that the present invention is provided, including rudder, the rudder are connected with oscillometer,
The swaying direction of the oscillometer energy control direction rudder；The oscillometer includes pedal, bracing wire, pedal gear and empennage and passed
Motivation structure, the pedal is connected by the front end of the pedal gear and the bracing wire, and the rear end of the bracing wire leads to
Empennage transmission mechanism is crossed to be connected with the rudder.
With oscillometer come precisely quickly control direction rudder is swung to the left or to the right, the swing of rudder realizes gyroplane
The turning of fuselage；When needing to turn, pin pushes pedals are used, pedal drives bracing wire campaign, and bracing wire can be more convenient directly controlling party
To rudder, it is swift in response, manipulation is flexible.
Further, the quantity of the bracing wire is two, and a bracing wire is located at the left side of fuselage girder, another institute
State the right side that bracing wire is located at fuselage girder.
The left side and right side of fuselage girder respectively set a bracing wire, and control direction rudder swings and swung to the right to the left respectively,
The division of labor is clear and definite.
Further, the pedal is made up of left-hand tread plate and right-hand tread plate, and the left-hand tread plate is with being located on the left of fuselage girder
The bracing wire connection, the right-hand tread plate is connected with the bracing wire on the right side of fuselage girder.
Left foot control left-hand tread plate makes gyroplane realize left-hand bend, and right crus of diaphragm control right-hand tread plate makes gyroplane realize right-hand bend, this
Sample meets person's development pattern, is not in case of emergency to step on wrong pedal, and the unsafe condition turned the wrong way is safe.
Further, cunning is provided between rudder and the gyroplane mast to lift up, the cunning is lifted up being capable of side described in bracketing
To rudder.
It is sliding to lift up support picking-up rudder, rudder is lifted up leftward or rightward swing along the cunning, with direct and mast
Connection is more flexible compared to rotating.
Further, the both sides of the rudder are provided with stable rudder, two stable rudder hanging down with the rudder
Directly divide face equally to be oppositely arranged for the plane of symmetry.
In order to comb the air-flow of rotor drive end unit, it is ensured that the stable operation of aircraft, it is symmetrical arranged surely in the both sides of rudder
Determine rudder to realize.
Further, the height of the rudder is higher than the stable rudder, and two stable rudders and a rudder are constituted
Mountain font empennage.
Mountain font empennage, gas flowfield is just more beneficial for the manipulation that rudder is turned to gyroplane, and Operational Figure Of Merit is high.
Further, trim tab is provided with the rudder, the trim tab is used for counterweight.
In order to ensure the landing of gyroplane, it is ensured that weight balancing, gyroplane needs to carry out counterweight to meet after production is good
Flying condition.
Further, the trim tab is arranged on the left side of the rudder.
Further, the pedal is fabricated by using square steel.
It is lightweight using square steel, it is ensured that while strength and stiffness.
Further, the inner side for being drawstring through fuselage girder.
The cavity that bracing wire close to pedal side is penetrated on the inside of fuselage girder from the hole on fuselage girder, always afterbody extension
Passed to rudder, then from the hole on the fuselage girder away from pedal side.Bracing wire, and outward appearance can be protected well
Neatly.
With oscillometer come precisely quickly control direction rudder is swung to the left or to the right, the swing of rudder realizes gyroplane
The turning of fuselage；When needing to turn, pin pushes pedals are used, pedal drives bracing wire campaign, and bracing wire can be more convenient directly controlling party
To rudder, it is swift in response, manipulation is flexible.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
There is the accompanying drawing used required in technology description to be briefly described, it should be apparent that, drawings in the following description are only this
Some embodiments of invention, for those of ordinary skill in the art, on the premise of not paying creative work, can be with
Other accompanying drawings are obtained according to these accompanying drawings.
Fig. 1 is the pedal of gyroplane empennage assembly structure of the present invention and the attachment structure schematic diagram of bracing wire；
Fig. 2 is the mountain font empennage of invention gyroplane empennage assembly structure and the attachment structure elevational schematic view of bracing wire；
1- rudders in figure；21- left-hand tread plates；22- right-hand tread plates；3- bracing wires；4- pedal gears；5- empennage drivers
Structure；6- fuselage girders；7- masts；8-, which is slided, to lift up；The stable rudders of 9-.
Embodiment
To make the object, technical solutions and advantages of the present invention clearer, technical scheme will be carried out below
Detailed description.Obviously, described embodiment is only a part of embodiment of the invention, rather than whole embodiments.Base
Embodiment in the present invention, those of ordinary skill in the art are resulting on the premise of creative work is not made to be owned
Other embodiment, belongs to the scope that the present invention is protected.
As depicted in figs. 1 and 2, the invention provides a kind of gyroplane empennage assembly structure, including rudder 1, the side
Oscillometer, the swaying direction of the oscillometer energy control direction rudder 1 are connected with to rudder 1；The oscillometer include pedal, bracing wire 3,
Pedal gear and empennage transmission mechanism 5, the pedal are driven by the front end of the pedal gear and the bracing wire 3
Connection, the rear end of the bracing wire 3 is connected by empennage transmission mechanism 5 with the rudder 1.
With oscillometer come precisely quickly control direction rudder 1 is swung to the left or to the right, the swing of rudder 1 realizes rotor
The turning of machine fuselage；When needing to turn, pin pushes pedals are used, pedal drives bracing wire 3 to move, and bracing wire 3 can be more convenient directly to control
Rudder 1 processed, is swift in response, and manipulation is flexible.
As the improvement of present embodiment, the quantity of the bracing wire 3 is two, and a bracing wire 3 is located at fuselage girder 6
Left side, another described bracing wire 3 be located at fuselage girder 6 right side.
The left side and right side of fuselage girder 6 respectively set a bracing wire 3, and control direction rudder 1 swings and put to the right to the left respectively
Dynamic, the division of labor is clear and definite.
As the improvement of present embodiment, the pedal is made up of left-hand tread plate 21 and right-hand tread plate 22, the left-hand tread plate 21 with
The bracing wire 3 positioned at the left side of fuselage girder 6 is connected, and the right-hand tread plate 22 connects with the bracing wire 3 positioned at the right side of fuselage girder 6
Connect.
Left foot control left-hand tread plate 21 makes gyroplane realize left-hand bend, and right crus of diaphragm control right-hand tread plate 22 makes gyroplane realize right-hand rotation
It is curved, so meet person's development pattern, be not in case of emergency to step on wrong pedal, the unsafe condition turned the wrong way, safety
Property it is high.
As the improvement of present embodiment, cunning is provided between the rudder 1 and gyroplane mast 7 and lifts up 8, the cunning is lifted up
8 being capable of rudder 1 described in bracketing.
It is sliding to lift up 8 supports and hold up rudder 1, rudder 1 is lifted up 8 swings to the left or to the right along the cunning, with directly with
The connection of mast 7 is more flexible compared to rotating.
As the improvement of present embodiment, the both sides of the rudder 1 are provided with stable rudder 9, two stable rudders 9 with
The vertical of the rudder 1 is divided face equally and is oppositely arranged for the plane of symmetry.
In order to comb the air-flow of rotor drive end unit, it is ensured that the stable operation of aircraft, it is symmetrical arranged surely in the both sides of rudder 1
Determine rudder 9 to realize.
As the improvement of present embodiment, the height of the rudder 1 is higher than the stable rudder 9, two stable rudders 9 and one
Individual rudder 1 constitutes mountain font empennage.
Mountain font empennage, gas flowfield is just more beneficial for the manipulation that rudder 1 is turned to gyroplane, and Operational Figure Of Merit is high.
As the improvement of present embodiment, trim tab is provided with the rudder 1, the trim tab is used for counterweight.
In order to ensure the landing of gyroplane, it is ensured that weight balancing, gyroplane needs to carry out counterweight to meet after production is good
Flying condition.
As the improvement of present embodiment, the trim tab is arranged on the left side of the rudder 1.
As the improvement of present embodiment, the pedal is fabricated by using square steel.
It is lightweight using square steel, it is ensured that while strength and stiffness.
As the improvement of present embodiment, the bracing wire 3 passes through the inner side of fuselage girder 6.
Bracing wire 3 close to pedal side penetrates the cavity of the inner side of fuselage girder 6 from the hole on fuselage girder 6, always afterbody
Extend near rudder 1, then passed from the hole on the fuselage girder 6 away from pedal side.Bracing wire 3 can be protected well,
And outward appearance is clean and tidy.
With oscillometer come precisely quickly control direction rudder 1 is swung to the left or to the right, the swing of rudder 1 realizes rotor
The turning of machine fuselage；When needing to turn, pin pushes pedals are used, pedal drives bracing wire 3 to move, and bracing wire 3 can be more convenient directly to control
Rudder 1 processed, is swift in response, and manipulation is flexible.
The foregoing is only a specific embodiment of the invention, but protection scope of the present invention is not limited thereto, any
Those familiar with the art the invention discloses technical scope in, change or replacement can be readily occurred in, should all be contained
Cover within protection scope of the present invention.Therefore, protection scope of the present invention should be based on the protection scope of the described claims.
Claims (10)
1. a kind of gyroplane empennage assembly structure, it is characterised in that including rudder (1), the rudder (1) is connected with swing
Instrument, the oscillometer can control the swaying direction of the rudder (1)；The oscillometer includes pedal (2), bracing wire (3), pedal
Transmission mechanism (4) and empennage transmission mechanism (5), the pedal (2) pass through the pedal gear (4) and the bracing wire (3)
Front end drive connection, the rear end of the bracing wire (3), which passes through the empennage transmission mechanism (5) and is driven with the rudder (1), to be connected
Connect.
2. gyroplane empennage assembly structure according to claim 1, it is characterised in that the quantity of the bracing wire (3) is two
Individual, a bracing wire (3) is located at the left side of fuselage girder (6), and another described bracing wire (3) is located at the right side of fuselage girder (6)
Side.
3. gyroplane empennage assembly structure according to claim 1, it is characterised in that the pedal (2) is by left-hand tread plate
(21) constituted with right-hand tread plate (22), the left-hand tread plate (21) is connected with the bracing wire (3) on the left of fuselage girder (6), institute
Right-hand tread plate (22) is stated to be connected with the bracing wire (3) on the right side of fuselage girder (6).
4. gyroplane empennage assembly structure according to claim 1, it is characterised in that the rudder (1) and gyroplane
It is provided with cunning between mast (7) to lift up (8), the cunning lifts up (8) being capable of rudder (1) described in bracketing.
5. gyroplane empennage assembly structure according to claim 1, it is characterised in that the both sides of the rudder (1) are set
It is equipped with stable rudder (9), two stable rudders (9) are divided equally face and be oppositely arranged as the plane of symmetry using the vertical of the rudder (1).
6. gyroplane empennage assembly structure according to claim 5, it is characterised in that the height of the rudder (1) is high
In the stable rudder (9), two stable rudders (9) and a rudder (1) constitute mountain font empennage.
7. gyroplane empennage assembly structure according to claim 1, it is characterised in that be provided with the rudder (1)
Trim tab, the trim tab is used for counterweight.
8. gyroplane empennage assembly structure according to claim 7, it is characterised in that the trim tab is arranged on the side
To the left side of rudder (1).
9. gyroplane empennage assembly structure according to claim 1, it is characterised in that the pedal (2) uses square steel system
Make and form.
10. gyroplane empennage assembly structure according to claim 1, it is characterised in that the bracing wire (3) passes through fuselage master
The inner side of beam (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710440641.2A CN107161324A (en) | 2017-06-12 | 2017-06-12 | Gyroplane empennage assembly structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710440641.2A CN107161324A (en) | 2017-06-12 | 2017-06-12 | Gyroplane empennage assembly structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107161324A true CN107161324A (en) | 2017-09-15 |
Family
ID=59825156
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710440641.2A Pending CN107161324A (en) | 2017-06-12 | 2017-06-12 | Gyroplane empennage assembly structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107161324A (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080179450A1 (en) * | 2004-11-19 | 2008-07-31 | Stepan Grigoryevich Jamgarov | Lifting-Type Aeroplane Fuselage |
| CN102285452A (en) * | 2010-06-21 | 2011-12-21 | 聂国安 | Annular fixed wing aircraft |
| RU119324U1 (en) * | 2012-04-27 | 2012-08-20 | Валерий Александрович Белов | AUTO FAT AMPHIBIA |
| US20130126666A1 (en) * | 2008-07-28 | 2013-05-23 | MARTIN CHRIST GEFRIERTROCKNUGSANLAGEN GmbH | Combined air, water and road vehicle |
| CN203916079U (en) * | 2014-05-20 | 2014-11-05 | 汕头市博迪科技有限公司 | Have the fixed wing aircraft toy of helicopter function concurrently |
| CN204166725U (en) * | 2014-10-10 | 2015-02-18 | 西京学院 | A kind of analogue means of simple and easy aircraft drive system |
| CN105438466A (en) * | 2015-12-07 | 2016-03-30 | 上海奥科赛飞机有限公司 | Human-powered fixed-wing aeroplane |
| CN105775110A (en) * | 2014-12-16 | 2016-07-20 | 常州市华奥泡塑新材料有限公司 | Unmanned aerial vehicle with flight stability |
| CN206155773U (en) * | 2016-10-25 | 2017-05-10 | 深圳创壹通航科技有限公司 | Rudder operating mechanism and gyroplane |
| CN206871342U (en) * | 2017-06-12 | 2018-01-12 | 河北天启通宇航空器材科技发展有限公司 | Gyroplane empennage assembly structure |
-
2017
- 2017-06-12 CN CN201710440641.2A patent/CN107161324A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080179450A1 (en) * | 2004-11-19 | 2008-07-31 | Stepan Grigoryevich Jamgarov | Lifting-Type Aeroplane Fuselage |
| US20130126666A1 (en) * | 2008-07-28 | 2013-05-23 | MARTIN CHRIST GEFRIERTROCKNUGSANLAGEN GmbH | Combined air, water and road vehicle |
| CN102285452A (en) * | 2010-06-21 | 2011-12-21 | 聂国安 | Annular fixed wing aircraft |
| RU119324U1 (en) * | 2012-04-27 | 2012-08-20 | Валерий Александрович Белов | AUTO FAT AMPHIBIA |
| CN203916079U (en) * | 2014-05-20 | 2014-11-05 | 汕头市博迪科技有限公司 | Have the fixed wing aircraft toy of helicopter function concurrently |
| CN204166725U (en) * | 2014-10-10 | 2015-02-18 | 西京学院 | A kind of analogue means of simple and easy aircraft drive system |
| CN105775110A (en) * | 2014-12-16 | 2016-07-20 | 常州市华奥泡塑新材料有限公司 | Unmanned aerial vehicle with flight stability |
| CN105438466A (en) * | 2015-12-07 | 2016-03-30 | 上海奥科赛飞机有限公司 | Human-powered fixed-wing aeroplane |
| CN206155773U (en) * | 2016-10-25 | 2017-05-10 | 深圳创壹通航科技有限公司 | Rudder operating mechanism and gyroplane |
| CN206871342U (en) * | 2017-06-12 | 2018-01-12 | 河北天启通宇航空器材科技发展有限公司 | Gyroplane empennage assembly structure |
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