CN207129132U - The stable Duo Ban drops mechanism of gyroplane - Google Patents
The stable Duo Ban drops mechanism of gyroplane Download PDFInfo
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- CN207129132U CN207129132U CN201720666622.7U CN201720666622U CN207129132U CN 207129132 U CN207129132 U CN 207129132U CN 201720666622 U CN201720666622 U CN 201720666622U CN 207129132 U CN207129132 U CN 207129132U
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- gyroplane
- stable
- rudder
- drops
- rudders
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Abstract
The utility model provides a kind of stable Duo Ban drops mechanism of gyroplane, is related to gyroplane technical field, solves that the aerodynamic loss of gyroplane tail structure present in prior art is big, the low technical problem of pneumatic efficiency.The side of the steering rudder of the close gyroplane of the stable rudder is curved surface, the side of the steering rudder of the remote gyroplane of the stable rudder is plane, so as to reduce the diverging of the air-flow streamline of the empennage portion of gyroplane, form current stabilization, reduce impact of the air-flow to gyroplane empennage, the aerodynamic loss of gyroplane empennage is small, and pneumatic efficiency improves, and the security of gyroplane flight is also improved.
Description
Technical field
Gyroplane technical field is the utility model is related to, more particularly, to a kind of stable Duo Ban drops mechanism of gyroplane.
Background technology
At present, the tail structure of aircraft, is roughly divided into following sections：
(1) tailplane
Abbreviation horizontal tail, longitudinal balance, stable and manipulation rudder face are provided for aircraft.It is general it is left and right be arranged symmetrically in it is winged
The afterbody of row device, pitching moment is provided for aircraft, aircraft is realized the action such as climb, land.
(2) vertical tail
It is referred to as critically ill, play the course balance of holding aircraft, stable and manipulation.It is typically located at aircraft afterbody axle
The top of line, yawing is provided for aircraft, aircraft is corrected the course line of flight.
(3) " V " type tail
It is made up of left and right two aerofoils, seems the horizontal tail for being fixed on the big upper counterangle of afterbody band." V " type tail has concurrently
The function of vertical fin and horizontal tail.Aerofoil can be divided into fixed stabilization and be hinged rudder face two parts, may be alternatively configured full ejector half formula.
Two V-shaped tail surfaces have certain projected area in vertical view and side-looking direction, (are bowed so longitudinal direction can be played simultaneously
Face upward) and course-stability effect.When rudder face makees equidirectional deflection when both sides, lifting rudder action is played；It is inclined to make different directions respectively
When turning (differential), then direction rudder action is played.
Gyroplane field, there are following a few classes substantially in afterbody design aspect：
(1) inverted " t " type afterbody
The tailplane of aircraft is connected with the bottom of vertical tail, forms inverted " t " shape.It is this to belong to most conventional tail
Portion is laid out, and is simple to manufacture, but tailplane is easier to be influenceed (especially in High Angle of Attack ramp-up period) by main wing.
(2) T-shape afterbody
The tailplane of aircraft is connected with the top of vertical tail, forms T-shape.This stern layout, tailplane
Height put the airflow influence for being not easily susceptible to main wing, therefore, the afterbody aeroperformance of this aircraft is relatively good, but manufacture it is complicated,
Weight is larger.
(3) inverted " V " type tail
This tail fin design, the design principle of " V " type tail is based primarily upon, its pneumatic principle is identical with " V " type tail.It is logical
Cross the linkage of two empennage rudder faces, the pitch control and driftage for realizing aircraft are corrected, and this design, more general T-shape or
Inverted " t " type designs, and resistance is smaller.
However, the design of this afterbody, once there is single empennage rudder face failure, the tail structure of whole aircraft is just almost
Function is lost, so as to cause the crash out of control of aircraft.
Applicants have discovered that at least there is following technical problem in prior art：
Tail structure is influenceed by the flying quality of aircraft, and aeroperformance efficiency is relatively low, and under some flight attitudes
(such as ramp-up period), the air-flow streamline of tail structure easily dissipate, and form turbulent flow, cause the pneumatic efficiency of aircraft tail structure
Reduce, or even tail structure stall can be made.
Utility model content
The purpose of this utility model is to provide a kind of gyroplane stable Duo Ban drops mechanism, to solve in the prior art
The aerodynamic loss of existing gyroplane tail structure is big, the low technical problem of pneumatic efficiency.
To achieve the above object, the utility model provides following technical scheme：
The stable Duo Ban drops mechanism of a kind of gyroplane provided by the utility model, the close gyroplane of the stable rudder
The side for turning to rudder is curved surface, and the side of the steering rudder of the remote gyroplane of the stable rudder is plane.
The side of the close steering rudder of stable rudder is curved surface, and the side of the steering rudder of the remote gyroplane of stable rudder is flat
Face, so as to reduce the diverging of the air-flow streamline of the empennage portion of gyroplane, current stabilization is formed, reduce air-flow and gyroplane empennage is rushed
Hit, the aerodynamic loss of gyroplane empennage is small, and pneumatic efficiency improves, and the security of gyroplane flight is also improved.
Further, the horizontal cross-section of the stable rudder is half drops.
Water droplet forms drops in freely falling body, and its drops formed is formed to overcome air drag
, or can be described as to adapt to the shape of air drag and self-assembling formation, it is clear that water droplet is to air-flow streamline during drops
Influence minimum, air drag suffered by water droplet is also minimum, air-flow by when can form current stabilization.
It can be seen that the curved surface of drops is small by air drag, aerodynamic loss is small, it is therefore preferred that stable rudder uses half water droplet
Shape, reduce aerodynamic loss.
Further, the half drops section is the head by being laterally away from gyroplane close to the one of the head of gyroplane
Side it is tapered.
Side close to the head of gyroplane is curved surface, and the side away from rotor chain-drive section is cusped edge, and air drag is small, gas
Dynamic loss is small.
Further, the size of half drops of the root of the stable rudder is more than half water droplet on the top of the stable rudder
The size of shape, and it is tapered from the bottom to top.
The root of stable rudder is thick, can ensure to stablize the intensity of rudder.
Further, the quantity of the stable rudder is two, and the steering rudder of the close gyroplane of two stable rudders
Side be curved surface, the side of the steering rudders of the remote gyroplane of two stable rudders is plane.
Further, two stable rudders turn to the both sides of rudder positioned at gyroplane respectively.
The both sides for turning to rudder respectively set a stable rudder, and are symmetrical arranged, and can ensure to stablize the equilibrium of the sidewind of rudder two.
Further, the width of the horizontal cross-section of two stable rudders is equal sized.
Further, the length direction of the horizontal cross-section of two stable rudders is equal sized.
The size of two stable rudders is identical, and gyroplane is had a smooth flight.
Further, two stable rudders are arranged on the tailplane of gyroplane.
Further, two stable rudders are vertically installed on the tailplane of gyroplane.
Stable rudder is vertically installed on the tailplane of gyroplane, is ensured that the course of gyroplane balances, stably, is gyroplane
Yawing is provided, gyroplane is corrected the course line of flight.
The side of the close steering rudder of stable rudder is curved surface, and the side of the steering rudder of the remote gyroplane of stable rudder is flat
Face, so as to reduce the diverging of the air-flow streamline of the empennage portion of gyroplane, current stabilization is formed, reduce air-flow and gyroplane empennage is rushed
Hit, the aerodynamic loss of gyroplane empennage is small, and pneumatic efficiency improves, and the security of gyroplane flight is also improved.
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 overlooking the structure diagram of gyroplane empennage portion；
Fig. 2 is the connection diagram of two stable rudders；
Fig. 3 is the horizontal cross-section schematic diagram of the A-A sectional views in Fig. 2, i.e. left stabilizer rudder；
Fig. 4 is the horizontal cross-section schematic diagram of the B-B sectional views in Fig. 2, i.e. right stabilizer rudder.
1- turns to rudder in figure；The stable rudders of 2-；3- tailplanes.
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 stable drops mechanism of rudder 2 half of gyroplane, the stabilization
The side of the steering rudder 1 of the close gyroplane of rudder 2 is curved surface, and the side of the steering rudder 1 of the remote gyroplane of the stable rudder 2 is
Plane.
The side of the close steering rudder 1 of stable rudder 2 is curved surface, and the side of the steering rudder 1 of the remote gyroplane of stable rudder 2 is
Plane, so as to reduce the diverging of the air-flow streamline of the empennage portion of gyroplane, current stabilization is formed, reduce air-flow to gyroplane empennage
Impact, the aerodynamic loss of gyroplane empennage is small, and pneumatic efficiency improves, and the security of gyroplane flight is also improved.
As shown in Figure 3 and Figure 4, optionally embodiment, the horizontal cross-section of the stable rudder 2 is half drops.
Water droplet forms drops in freely falling body, and its drops formed is formed to overcome air drag
, or can be described as to adapt to the shape of air drag and self-assembling formation, it is clear that water droplet is to air-flow streamline during drops
Influence minimum, air drag suffered by water droplet is also minimum, air-flow by when can form current stabilization.
It can be seen that the curved surface of drops is small by air drag, aerodynamic loss is small, it is therefore preferred that stable rudder 2 uses half water
Drop-wise, reduce aerodynamic loss.
Optionally embodiment, the half drops section are by being laterally away from rotation close to the one of the head of gyroplane
The side on the head of wing machine is tapered.
Side close to the head of gyroplane is curved surface, and the side away from rotor chain-drive section is cusped edge, and air drag is small, gas
Dynamic loss is small.
Optionally embodiment, the size of half drops of the root of the stable rudder 2 are more than the stable rudder 2
The size of half drops on top, and it is tapered from the bottom to top.
The root of stable rudder 2 is thick, can ensure to stablize the intensity of rudder 2.
Optionally embodiment, the quantity of the stable rudder 2 is two, and the close rotation of two stable rudders 2
The side of the steering rudder 1 of wing machine is curved surface, and the side of the steering rudder 1 of the remote gyroplane of two stable rudders 2 is flat
Face.
Optionally embodiment, two stable rudders 2 turn to the both sides of rudder 1 positioned at gyroplane respectively.
The both sides for turning to rudder 1 respectively set a stable rudder 2, and are symmetrical arranged, and can ensure to stablize the equal of 2 liang of sidewinds of rudder
Weighing apparatus.
Optionally embodiment, the width of the horizontal cross-section of two stable rudders 2 it is equal sized.
Optionally embodiment, the length direction of the horizontal cross-section of two stable rudders 2 it is equal sized.
The size of two stable rudders 2 is identical, and gyroplane is had a smooth flight.
Optionally embodiment, two stable rudders 2 are arranged on the tailplane 3 of gyroplane.
Optionally embodiment, two stable rudders 2 are vertically installed on the tailplane 3 of gyroplane.
Stable rudder 2 is vertically installed on the tailplane 3 of gyroplane, is ensured that the course of gyroplane balances, stably, is rotor
Machine provides yawing, gyroplane is corrected the course line of flight.
The side of the close steering rudder 1 of stable rudder 2 is curved surface, and the side of the steering rudder 1 of the remote gyroplane of stable rudder 2 is
Plane, so as to reduce the diverging of the air-flow streamline of the empennage portion of gyroplane, current stabilization is formed, reduce air-flow to gyroplane empennage
Impact, the aerodynamic loss of gyroplane empennage is small, and pneumatic efficiency improves, and the security of gyroplane flight is also improved.
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 (8)
- A kind of 1. stable Duo Ban drops mechanism of gyroplane, it is characterised in that the steering of the close gyroplane of the stable rudder (2) The side of rudder (1) is curved surface, and the side of the steering rudder (1) of the remote gyroplane of the stable rudder (2) is plane, the stable rudder (2) horizontal cross-section is half drops, and the half drops section is by being laterally away from rotor close to the one of the head of gyroplane The side on the head of machine is tapered.
- 2. the stable Duo Ban drops mechanism of gyroplane according to claim 1, it is characterised in that the stable rudder (2) The size of half drops of root is more than the size of half drops on the top of the stable rudder (2), and tapered from the bottom to top.
- 3. the stable Duo Ban drops mechanism of gyroplane according to claim 2, it is characterised in that the stable rudder (2) Quantity is two, and the side of the steering rudder (1) of the close gyroplane of two stable rudders (2) is curved surface, described in two The side of the steering rudder (1) of the remote gyroplane of stable rudder (2) is plane.
- 4. the stable Duo Ban drops mechanism of gyroplane according to claim 3, it is characterised in that two stable rudders (2) it is located at the both sides of the steering rudder (1) of gyroplane respectively.
- 5. the stable Duo Ban drops mechanism of gyroplane according to claim 4, it is characterised in that two stable rudders (2) width of horizontal cross-section it is equal sized.
- 6. the stable Duo Ban drops mechanism of gyroplane according to claim 5, it is characterised in that two stable rudders (2) length direction of horizontal cross-section it is equal sized.
- 7. the stable Duo Ban drops mechanism of gyroplane according to claim 6, it is characterised in that two stable rudders (2) it is arranged on the tailplane (3) of gyroplane.
- 8. the stable Duo Ban drops mechanism of gyroplane according to claim 7, it is characterised in that two stable rudders (2) it is vertically installed on the tailplane (3) of gyroplane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720666622.7U CN207129132U (en) | 2017-06-09 | 2017-06-09 | The stable Duo Ban drops mechanism of gyroplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720666622.7U CN207129132U (en) | 2017-06-09 | 2017-06-09 | The stable Duo Ban drops mechanism of gyroplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207129132U true CN207129132U (en) | 2018-03-23 |
Family
ID=61631573
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720666622.7U Active CN207129132U (en) | 2017-06-09 | 2017-06-09 | The stable Duo Ban drops mechanism of gyroplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207129132U (en) |
-
2017
- 2017-06-09 CN CN201720666622.7U patent/CN207129132U/en active Active
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