CN206871342U - Gyroplane empennage assembly structure - Google Patents
Gyroplane empennage assembly structure Download PDFInfo
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- CN206871342U CN206871342U CN201720679183.3U CN201720679183U CN206871342U CN 206871342 U CN206871342 U CN 206871342U CN 201720679183 U CN201720679183 U CN 201720679183U CN 206871342 U CN206871342 U CN 206871342U
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- rudder
- gyroplane
- bracing wire
- assembly structure
- pedal
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Abstract
The utility model provides a kind of gyroplane empennage assembly structure, is related to gyroplane technical field, solves that the swing of 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, with pin pushes pedals, 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
Gyroplane technical field is the utility model is related to, more particularly, to a kind of gyroplane empennage assembly structure.
Background technology
Gyroplane is that relative wind when flying before a kind of utilization 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.Have the characteristics that landing apart from it is short, low speed low-latitude flying can be made, it is simple light and handy, be easy to hidden, but can not hang down
Straight landing, it can not hover.Available for take 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 typically is also equipped with less wing and awing provides part lift to provide the power of advance.
The maximum difference of gyroplane and helicopter is that the rotor of gyroplane is not connected with engine driving system, and engine is not to drive
Dynamic rotor provides lift for gyroplane, but during gyroplane flies, rotor wing rotation is blown by front air-flow and produces liter
Power, as a windmill, rotor system is only driven when starting by self power, is referred to as prewhirl (prerotate), after taking off
Driven by air effect power；And the rotor of helicopter is connected with engine driving system, lift can be produced, and can provides flight
Power, as an electric fan.Because rotor is rotation type, the moment of torsion very little being delivered on fuselage, therefore gyroplane is without picture
Tail-rotor as single-rotor helicopter, but empennage is generally equipped with, to control flight.
Awing, gyroplane with helicopter be most significantly respectively 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, and
For keeping the in-flight stability of aircraft and controlling the flight attitude of aircraft.The difference is that vertical tail is to make aircraft on a left side
Right (driftage) direction has certain static stability, and controls motion of the aircraft 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's can is 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.
Utility model content
The purpose of this utility model is to provide a kind of gyroplane empennage assembly structure, to solve existing gyroplane rudder
Swing it is not accurate enough, directly influence gyroplane flight safety and reliability technical problem.
To achieve the above object, the utility model provides following technical scheme：
A kind of gyroplane empennage assembly structure provided by the utility model, including rudder, the rudder are connected with pendulum
Dynamic instrument, the swaying direction of the oscillometer energy control direction rudder；The oscillometer include pedal, bracing wire, pedal gear and
Empennage transmission mechanism, the pedal are connected by the front end of the pedal gear and the bracing wire, the bracing wire
Rear end 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 gyroplane
The turning of fuselage；When needing to turn, with pin pushes pedals, 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 are connected with the bracing wire on the right side of fuselage girder.
Left foot control left-hand tread plate makes gyroplane realize, and right crus of diaphragm control right-hand tread plate makes gyroplane realization turn right, this
Sample meets person's development pattern, is not in case of emergency to step on wrong pedal, and the unsafe condition to turn 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, ensure the stable operation of aircraft, be symmetrical arranged surely in the both sides of rudder
Rudder is determined to realize.
Further, higher than the stable rudder, two stable rudders and a rudder constitute the height of the rudder
Mountain font empennage.
Mountain font empennage, gas flowfield are just more beneficial for the manipulation that rudder turns 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, ensure 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 using square steel.
It is in light weight while proof strength and rigidity using square steel.
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, with pin pushes pedals, 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
, below will be to embodiment in order to illustrate more clearly of the utility model embodiment or technical scheme of the prior art
Or the required accompanying drawing used is briefly described in description of the prior art, it should be apparent that, drawings in the following description are only
It is some embodiments of the utility model, for those of ordinary skill in the art, is not paying the premise of creative work
Under, other accompanying drawings can also be obtained according to these accompanying drawings.
Fig. 1 is the pedal of the utility model gyroplane empennage assembly structure and the attachment structure schematic diagram of bracing wire；
Fig. 2 is that the mountain font empennage of utility model gyroplane empennage assembly structure and the attachment structure of bracing wire look up signal
Figure；
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
, below will be to technology of the present utility model to make the purpose of this utility model, technical scheme and advantage clearer
Scheme is described in detail.Obviously, described embodiment is only the utility model part of the embodiment, rather than all
Embodiment.Based on the embodiment in the utility model, those of ordinary skill in the art are not before creative work is made
Resulting all other embodiment is put, belongs to the scope that the utility model is protected.
As depicted in figs. 1 and 2, the utility model provides a kind of gyroplane empennage assembly structure, including rudder 1, institute
State rudder 1 and be connected with oscillometer, the swaying direction of the oscillometer energy control direction rudder 1；The oscillometer includes pedal, drawn
Line 3, pedal gear and empennage transmission mechanism 5, the pedal pass through the pedal gear and the front end of the bracing wire 3
Drive connection, the rear end of the bracing wire 3 is connected by empennage transmission mechanism 5 and 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, with pin pushes pedals, 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 bracing wire 3 is located at the right side of fuselage girder 6.
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 connects, 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, and right crus of diaphragm control right-hand tread plate 22 makes gyroplane realization turn right
It is curved, so meet person's development pattern, be not in case of emergency to step on wrong pedal, the unsafe condition to turn 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 along the cunning and swing to the left or to the right, 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, ensure the stable operation of aircraft, be symmetrical arranged surely in the both sides of rudder 1
Rudder 9 is determined 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 are just more beneficial for the manipulation that rudder 1 turns 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, ensure 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 using square steel.
It is in light weight while proof strength and rigidity using square steel.
As the improvement of present embodiment, the bracing wire 3 passes through the inner side of fuselage girder 6.
The bracing wire 3 of close 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, with pin pushes pedals, 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.
It is described above, only specific embodiment of the present utility model, but the scope of protection of the utility model is not limited to
In this, any one skilled in the art can readily occur in change in the technical scope that the utility model discloses
Or replace, it should all cover within the scope of protection of the utility model.Therefore, the scope of protection of the utility model should be with the power
The protection domain that profit requires is defined.
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) passes through the empennage transmission mechanism (5) and connected with the rudder (1) transmission
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 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) it is connected with right-hand tread plate (22) composition, the left-hand tread plate (21) 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 are 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 |
|---|---|---|---|
| CN201720679183.3U CN206871342U (en) | 2017-06-12 | 2017-06-12 | Gyroplane empennage assembly structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720679183.3U CN206871342U (en) | 2017-06-12 | 2017-06-12 | Gyroplane empennage assembly structure |
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| Publication Number | Publication Date |
|---|---|
| CN206871342U true CN206871342U (en) | 2018-01-12 |
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ID=61332752
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720679183.3U Active CN206871342U (en) | 2017-06-12 | 2017-06-12 | Gyroplane empennage assembly structure |
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| Country | Link |
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| CN (1) | CN206871342U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107161324A (en) * | 2017-06-12 | 2017-09-15 | 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 CN201720679183.3U patent/CN206871342U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107161324A (en) * | 2017-06-12 | 2017-09-15 | 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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