CN206871340U - Gyroplane empennage mechanism - Google Patents
Gyroplane empennage mechanism Download PDFInfo
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- CN206871340U CN206871340U CN201720671683.2U CN201720671683U CN206871340U CN 206871340 U CN206871340 U CN 206871340U CN 201720671683 U CN201720671683 U CN 201720671683U CN 206871340 U CN206871340 U CN 206871340U
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- gyroplane
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- stabilizer
- steering
- cunning
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Abstract
The utility model provides a kind of gyroplane empennage mechanism, is related to gyroplane technical field, solves the big technical problem of gyroplane empennage aerodynamic loss.Gyroplane empennage mechanism includes turning to the wing, stabilizer and tailplane, and the stabilizer is arranged at around the steering wing, and the steering wing and the stabilizer may be contained within the tailplane；The horizontal cross-section of the stabilizer is half drops, and the close side for turning to the wing of the stabilizer is curved surface, and the remote side for turning to the wing of the stabilizer is plane.The side of the close steering wing of stabilizer is curved surface, the side of the steering wing of the remote gyroplane of stabilizer 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 gyroplane empennage mechanism.
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.
The steering wing is responsible for the steering of gyroplane, is also called the steering wing.The key mechanism turned to as gyroplane, its is right
Security during gyroplane flight plays very big effect, therefore, turns to being reliably connected between the wing and fuselage girder and spirit
Rotation living is very important.
Applicants have discovered that at least there is following technical problem in prior art：
(1) tail structure is influenceed by the flying quality of aircraft, and aeroperformance efficiency is relatively low, and in some flight attitudes
Under (such as ramp-up period), the air-flow streamline of tail structure easily dissipates, and forms turbulent flow, causes the pneumatic effect of aircraft tail structure
Rate reduces, or even can make tail structure stall.
(2) connecting-piece structure between some steering wings of prior art and fuselage girder is complicated, and Maintenance and Repair difficulty is big, takes
When it is laborious.
(3) awing, gyroplane with helicopter be most significantly respectively helicopter rotor towards top rake, and rotor
The rotor of machine is then sweptback.Gyroplane high afterbody in head in takeoff and landing is low, and it is improper such as to drive, its metal empennage
Bottom often directly contact, collide with ground, shake aircraft, when serious even afterbody is rebounded, influence flight safety.
Utility model content
The purpose of this utility model is to provide a kind of gyroplane empennage mechanism, to solve rotor present in prior art
The big technical problem of tail wing aerodynamic loss.
To achieve the above object, the utility model provides following technical scheme：
A kind of gyroplane empennage mechanism provided by the utility model, including the wing, stabilizer and tailplane are turned to, it is described steady
Determine the wing to be arranged at around the steering wing, and the steering wing and the stabilizer may be contained within the tailplane；
The horizontal cross-section of the stabilizer is half drops, and the close side for turning to the wing of the stabilizer is song
Face, the remote side for turning to the wing of the stabilizer is plane.
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, and therefore, stabilizer uses half drops, reduces
Aerodynamic loss.
The side of the close steering wing of stabilizer is curved surface, and the side of the steering wing of the remote gyroplane of stabilizer 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 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 quantity of the stabilizer is two, and two stabilizers are respectively positioned at a left side for the steering wing
Side and right side, and the steering wing and two stabilizers constitute the empennage of mountain font.
Further, two stabilizers are symmetricly set in using the center vertical separation face of the steering wing as the plane of symmetry
The both sides for turning to the wing.
The both sides for turning to the wing respectively set a stabilizer, and are symmetrical arranged, and can ensure the equilibrium of the sidewind of stabilizer two.
Further, the steering wing and the stabilizer are vertically installed on the tailplane.
Further, the width of the horizontal cross-section of two stabilizers is equal sized.
Further, the length direction of the horizontal cross-section of two stabilizers is equal sized.
The size of two stabilizers is identical, and gyroplane is had a smooth flight.
Further, two stabilizers are arranged on the tailplane of gyroplane.
Further, two stabilizers are vertically installed on the tailplane of gyroplane.
Stabilizer 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.
Further, in addition to cunning is lifted up, and the bottom for turning to the wing is lifted up by the cunning can be with the fuselage master of gyroplane
Beam is rotatablely connected.
The bottom of the steering wing is lifted up by the cunning to be rotatablely connected with the fuselage girder of gyroplane, the sliding setting lifted up, is avoided
The empennage of gyroplane directly contacts with ground, reduces the vibrations of empennage and fuselage, makes flight more safe and reliable.
Further, the cunning lift up including it is sliding lift up main body and it is sliding lifts up projection, the cunning, which lifts up projection and is arranged at the cunning, lifts up master
The bottom side of body, the cunning are lifted up projection and can contacted when gyroplane takes off or lands with ground.
Further, the steering wing includes vertically stable portion and turns to rudder, and the vertically stable portion is fixed in fuselage master
Liang Shang, the steering rudder and vertical stable portion's rotation connection.
Further, trim tab is fixed with the steering rudder, the trim tab can be used in counterweight.
Further, the trim tab is fixed on the aerofoil in the left side of the steering rudder.
The side of the close steering wing of stabilizer is curved surface, and the side of the steering wing of the remote gyroplane of stabilizer 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 structural representation of gyroplane empennage portion of the present utility model；
Fig. 2 is the annexation figure of stabilizer and tailplane of the present utility model；
Fig. 3 is to turn to the wing and the sliding connection diagram lifted up；
Fig. 4 is the schematic diagram of the horizontal cross-section of the left stabilizer wing；
Fig. 5 is the schematic diagram of the horizontal cross-section of the right stabilizer wing；
Fig. 6 is the structural representation of trim tab.
1- turns to the wing in figure；11- vertically stabilizes portion；12- turns to rudder；2- stabilizers；3-, which is slided, to lift up；31-, which is slided, lifts up main body；32-
Cunning lifts up projection；4- fuselage girders；5- trim tabs；6- 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 gyroplane empennage mechanism, including turns to the wing 1, stabilizer 2
With tailplane 6, stabilizer 2, which is arranged at, to be turned to around the wing 1, and the steering wing 1 and stabilizer 2 may be contained within tailplane 6；
As shown in Figure 4 and Figure 5, the horizontal cross-section of stabilizer 2 is half drops, the side of the close steering wing 1 of stabilizer 2
For curved surface, the side of the remote steering wing 1 of stabilizer 2 is plane.
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, and therefore, stabilizer 2 uses half drops, subtracts
Few aerodynamic loss.
The side of the close steering wing 1 of stabilizer 2 is curved surface, and the side of the steering wing 1 of the remote gyroplane of stabilizer 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.
Optionally embodiment, half drops section are by being laterally away from gyroplane close to the one of the head of gyroplane
Head 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.
Optionally embodiment, the quantity of stabilizer 2 is two, and two stabilizers 2 are respectively positioned at the left side for turning to the wing 1
Side and right side, and the steering wing 1 and two stabilizers 2 constitute the empennage of mountain font.
Optionally embodiment, two stabilizers 2 are symmetrically set using the center vertical separation face for turning to the wing 1 as the plane of symmetry
It is placed in the both sides for turning to the wing 1.
The both sides for turning to the wing 1 respectively set a stabilizer 2, and are symmetrical arranged, and can ensure the equal of 2 liang of sidewinds of stabilizer
Weighing apparatus.
Optionally embodiment, turns to the wing 1 and stabilizer 2 is vertically installed on tailplane 6.
Optionally embodiment, the width of the horizontal cross-section of two stabilizers 2 it is equal sized.
Optionally embodiment, the length direction of the horizontal cross-section of two stabilizers 2 it is equal sized.
The size of two stabilizers 2 is identical, and gyroplane is had a smooth flight.
Optionally embodiment, two stabilizers 2 are arranged on the tailplane 6 of gyroplane.
Optionally embodiment, two stabilizers 2 are vertically installed on the tailplane 6 of gyroplane.
Stabilizer 2 is vertically installed on the tailplane 6 of gyroplane, is ensured that the course of gyroplane balances, stably, is rotor
Machine provides yawing, gyroplane is corrected the course line of flight.
As shown in figure 3, optionally embodiment, in addition to it is sliding lift up 3, turn to the bottom of the wing 1 by it is sliding lift up 3 can be with
The fuselage girder 4 of gyroplane is rotatablely connected.
Turn to the bottom of the wing 1 to lift up 3 by sliding and be rotatablely connected with the fuselage girder 4 of gyroplane, cunning lifts up 3 setting, avoids
The empennage of gyroplane directly contacts with ground, reduces the vibrations of empennage and fuselage, makes flight more safe and reliable.
Optionally embodiment, it is sliding lift up 3 include it is sliding lift up 3 main bodys and it is sliding lift up it is 3 raised, it is sliding lift up 3 projections and be arranged at cunning lift up 3
The bottom side of main body, cunning, which lifts up 3 projections, to be contacted when gyroplane takes off or lands with ground.
Optionally embodiment, turning to the wing 1 includes vertically stable portion 11 and turns to rudder 12, and vertically stable portion 11 is affixed
It is rotatablely connected on fuselage girder 4, turning to rudder 12 with vertical stable portion 11.
Optionally embodiment, turn to and be fixed with trim tab 5 on rudder 12, the structure of trim tab 5 is as shown in fig. 6, repair
Positive 5 can be used in counterweight.
Optionally embodiment, trim tab 5 are fixed on the aerofoil in the left side for turning to rudder 12.
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 mechanism, it is characterised in that described including turning to the wing (1), stabilizer (2) and tailplane (6)
Stabilizer (2) is arranged at around the steering wing (1), and the steering wing (1) and the stabilizer (2) may be contained within it is described
On tailplane (6)；
The horizontal cross-section of the stabilizer (2) is half drops, the close side for turning to the wing (1) of the stabilizer (2)
For curved surface, the remote side for turning to the wing (1) of the stabilizer (2) is plane.
2. gyroplane empennage mechanism according to claim 1, it is characterised in that the half drops section is by close to rotation
The side that the one of the head of wing machine is laterally away from the head of gyroplane is tapered.
3. gyroplane empennage mechanism according to claim 2, it is characterised in that the quantity of the stabilizer (2) is two,
Two stabilizers (2) are located at the left side and right side of the steering wing, and the steering wing (1) and two stabilizations respectively
The wing (2) constitutes the empennage of mountain font.
4. gyroplane empennage mechanism according to claim 3, it is characterised in that two stabilizers (2) are with described turn
The center vertical separation face of guide vane (1) is the both sides that the plane of symmetry is symmetricly set in the steering wing (1).
5. gyroplane empennage mechanism according to claim 4, it is characterised in that the steering wing (1) and the stabilizer
(2) it is vertically installed on the tailplane (6).
6. the gyroplane empennage mechanism according to any one of claim 1 to 5, it is characterised in that also include cunning and lift up (3), institute
State and turn to the bottom of the wing (1) and (3) are lifted up by the cunning can be rotatablely connected with the fuselage girder (4) of gyroplane.
7. gyroplane empennage mechanism according to claim 6, it is characterised in that the cunning lifts up (3) and lifts up main body including cunning
(31) lifted up raised (32) with cunning, the cunning lifts up raised (32) and is arranged at the bottom side that the cunning lifts up main body (31), and the cunning lifts up projection
(32) can be contacted when gyroplane takes off or lands with ground.
8. gyroplane empennage mechanism according to claim 1, it is characterised in that the steering wing (1) includes vertical stable
Portion (11) and turn to rudder (12), vertically stable portion (11) are fixed on fuselage girder (4), the steering rudder (12) with it is described
Vertically stable portion (11) rotation connection.
9. gyroplane empennage mechanism according to claim 8, it is characterised in that be fixed with amendment on the steering rudder (12)
Piece (5), the trim tab (5) can be used in counterweight.
10. gyroplane empennage mechanism according to claim 9, it is characterised in that the trim tab (5) is fixed on described turn
To on the aerofoil in the left side of rudder (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720671683.2U CN206871340U (en) | 2017-06-09 | 2017-06-09 | Gyroplane empennage mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720671683.2U CN206871340U (en) | 2017-06-09 | 2017-06-09 | Gyroplane empennage mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206871340U true CN206871340U (en) | 2018-01-12 |
Family
ID=61332864
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720671683.2U Active CN206871340U (en) | 2017-06-09 | 2017-06-09 | Gyroplane empennage mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206871340U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109466745A (en) * | 2018-12-29 | 2019-03-15 | 河北天启通宇航空器材科技发展有限公司 | A kind of gyroplane tail structure |
-
2017
- 2017-06-09 CN CN201720671683.2U patent/CN206871340U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109466745A (en) * | 2018-12-29 | 2019-03-15 | 河北天启通宇航空器材科技发展有限公司 | A kind of gyroplane tail structure |
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