CN206544597U - One kind is used for the double inclining rotary mechanisms of fixed-wing wing - Google Patents
One kind is used for the double inclining rotary mechanisms of fixed-wing wing Download PDFInfo
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- CN206544597U CN206544597U CN201720255451.9U CN201720255451U CN206544597U CN 206544597 U CN206544597 U CN 206544597U CN 201720255451 U CN201720255451 U CN 201720255451U CN 206544597 U CN206544597 U CN 206544597U
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Abstract
It is used for the double inclining rotary mechanisms of fixed-wing wing the utility model discloses one kind, belongs to aircraft mechanical technical field.Described double inclining rotary mechanisms are verted process by controlling outside wing and inboard wing to rotate adjustment respectively, described axle sleeve axle construction is located at the junction of outside wing and inboard wing, two sets of described four-bar linkage structures are arranged symmetrically on fuselage, described Lead screw transmission structure is located on fuselage to be connected with interior axle, it is reasonable in design, pass through axle sleeve axle construction, three primary structures of four-bar linkage structure and Lead screw transmission structure realize the inner side of aircraft, double functions of verting of outside wing, the axle sleeve axle construction being installed in inside and outside wing realizes the connection of interior outer shaft, the quadric chain being connected in waist with inboard wing realizes the accurate control verted to inboard wing；By accurately controlling to realize the manipulation of internally outside wing, the distribution of medial lateral wing is verted for adjustment aircraft airflight posture, and accurate control aircraft landing is significant.
Description
Technical field：
The utility model, which is related to one kind, is used for the double inclining rotary mechanisms of fixed-wing wing, belongs to aircraft mechanical designing technique neck
Domain.
Background technology：
Nowadays, the research of tiltrotor aircraft belongs to the popular problem of aircraft mechanical design, and it can pass through wing
Vert and realize the adjustment of airflight posture, aircraft multi-modes are realized, to realize VTOL, high-performance cruise, fixed
Point hovering etc. function, it is civilian or military domain all have bright prospects.And the machinery of tiltrotor aircraft
In design, inclining rotary mechanism design is design core.
In existing tiltrotor aircraft, for example, having put into the V22 osprey aircrafts in the military U.S. in inclining rotary mechanism
Aspect is used can cycle pulp distance varying mechanism.This mechanism not only substantially increases the weight of aircraft, is not easy to maintenance, and
Because the air channel of propeller and wing have greater overlap part, weaken the power of propeller offer, thus in maximum speed and
Very big influence is also result on cruising time.
Utility model content：
Verted in view of the above-mentioned problems, the technical problems to be solved in the utility model is to provide a kind of fixed-wing wing pair that is used for
Mechanism, is realized after the rise of two axle aircraft verticals or before landing, the conversion between helicopter mode and fixed-wing pattern, and increase
Plus the stability in helicopter mode and fixed-wing mode transition procedure.
Of the present utility model to be used for the double inclining rotary mechanisms of fixed-wing wing, it includes three parts：Axle sleeve axle construction A, double leval jib
Structure B and Lead screw transmission structure C, axle sleeve axle construction A are arranged in inboard wing 4 and outside wing 17, and quadric chain B is installed
It is connected in waist with inboard wing 4 and outside wing 17, Lead screw transmission structure C is arranged on fuselage and is connected with interior axle 2, institute
The axle sleeve axle construction A stated is included and outer shaft 3 is provided with outside bearing 1, interior axle 2 and outer shaft 3, bearing 1, and bearing 1 is internally provided with interior
Axle 2, interior axle 2 and outer shaft 3 are connected by bearing 1, and the connection inboard wing 4 of outer shaft 3, interior axle 2 is embedded in outer bar by bearing 1, worn
Fuselage is crossed, and is connected with outside wing 17, steering wheel 7 is connected with screw thread and pad 16, described four-bar linkage structure B includes inner side machine
The wing 4, connecting rod 5, rocking bar 6, steering wheel 7 and transverse axis 18, rocking bar 6 are connected by steering wheel 7 with transverse axis 18, transverse axis 18 by outer shaft 3 with
Inboard wing 4 is connected, and inboard wing 4, connecting rod 5, rocking bar 6 and transverse axis 18 are mutually sequentially connected, described Lead screw transmission structure C
Include motor 15, reducing gear 14, ball bearing 13, sensor 10, sliding block 12, leading screw 11, slide block connecting rod 9 and connecting shaft 8, motor 15
Upper end is provided with reducing gear 14, and the one end of leading screw 11 is connected with reducing gear 14, and the other end is connected with connecting shaft 8, the upper end of leading screw 11
Ball bearing 13 is provided with, leading screw 11 is provided at both ends with sensor 10, and sliding block 12 is enclosed on leading screw 11, and sliding block is passed through with interior axle 2
Connecting rod 9 is connected.
Preferably, described double inclining rotary mechanisms are inclined by controlling outside wing 17 and inboard wing 4 to rotate adjustment respectively
Turn over journey.
Preferably, described axle sleeve axle construction A is located at the junction of outside wing 17 and inboard wing 4.
Preferably, two sets of described four-bar linkage structure B are arranged symmetrically on fuselage.
It is connected preferably, described Lead screw transmission structure C is located on fuselage with interior axle 2.
The beneficial effects of the utility model：It simple in construction, it is reasonable in design, pass through axle sleeve axle construction, four-bar linkage structure
With three primary structures of Lead screw transmission structure realize the inner side of aircraft, outside wing double functions of verting, be installed on internal-external machine
Axle sleeve axle construction in the wing realizes the connection of interior outer shaft, and the quadric chain being connected in waist with inboard wing is realized internal
The accurate control that side wing verts；The lead screw transmission mechanism being connected on fuselage with interior axle realizes the control verted to outside wing
System, inboard wing is connected with quadric chain, and outside wing is connected with interior bar, by accurately controlling to realize wing on the outside of internally
Manipulation, the distribution of medial lateral wing is verted for adjustment aircraft airflight posture, and accurate control aircraft landing has
Significance.
Brief description of the drawings：
For ease of explanation, the utility model is described in detail by following specific implementations and accompanying drawing.
Fig. 1 is structural representation of the present utility model；
Fig. 2 is axle sleeve axle construction schematic diagram；
Fig. 3 is four-bar linkage structure schematic diagram；
Fig. 4 is lead screw transmission schematic diagram.
Reference：A- axle sleeve axle construction；B- four-bar linkage structures；C- Lead screw transmission structures；1- bearings；2- interior axles；Outside 3-
Axle；4- inboard wings；5- connecting rods；6- rocking bars；7- steering wheels；8- connecting shafts；9- slide block connecting rods；10- sensors；11- screw mandrels；12- is slided
Block；13- ball bearings；14- reducing gears；15- motors；16- pads；Wing on the outside of 17-.
Embodiment：
As Figure 1-Figure 4, present embodiment uses following technical scheme：It includes three parts：Axle sleeve axle construction
A, four-bar linkage structure B and Lead screw transmission structure C, axle sleeve axle construction A are arranged in inboard wing 4 and outside wing 17, double leval jib
Mechanism B is connected installed in waist with inboard wing 4 and outside wing 17, Lead screw transmission structure C be arranged on fuselage on it is interior
Axle 2 is connected, and described axle sleeve axle construction A is included to be provided with outer shaft 3, bearing 1 outside bearing 1, interior axle 2 and outer shaft 3, bearing 1
Portion is provided with interior axle 2, and interior axle 2 and outer shaft 3 are connected by bearing 1, and the connection inboard wing 4 of outer shaft 3, interior axle 2 is embedded in by bearing 1
In outer bar, it is connected through fuselage, and with outside wing 17, steering wheel 7, described four-bar linkage structure B is connected with screw thread and pad 16
Comprising inboard wing 4, connecting rod 5, rocking bar 6, steering wheel 7 and transverse axis 18, rocking bar 6 is connected by steering wheel 7 with transverse axis 18, and transverse axis 18 leads to
Cross outer shaft 3 with inboard wing 4 to be connected, inboard wing 4, connecting rod 5, rocking bar 6 and transverse axis 18 are mutually sequentially connected, described leading screw
Drive mechanism C is comprising motor 15, reducing gear 14, ball bearing 13, sensor 10, sliding block 12, leading screw 11, slide block connecting rod 9 and connects
Axle 8, the upper end of motor 15 is provided with reducing gear 14, and the one end of leading screw 11 is connected with reducing gear 14, and the other end is connected with connecting shaft 8,
The upper end of leading screw 11 is provided with ball bearing 13, and leading screw 11 is provided at both ends with sensor 10, and sliding block 12 is enclosed on leading screw 11, with interior axle
2 are connected by slide block connecting rod 9.
Preferably, described double inclining rotary mechanisms are inclined by controlling outside wing 17 and inboard wing 4 to rotate adjustment respectively
Turn over journey.
Preferably, described axle sleeve axle construction A is located at the junction of outside wing 17 and inboard wing 4.
Preferably, two sets of described four-bar linkage structure B are arranged symmetrically on fuselage.
It is connected preferably, described Lead screw transmission structure C is located on fuselage with interior axle 2.
The course of work of inclining rotary mechanism in present embodiment take-off process is divided into following several stages：
First stage, wing and propeller are perpendicular to ground, the sliding block 12 in helicopter attitude, Lead screw transmission structure C
Positioned at the left end of leading screw 11, contacted with sensor 10, outside wing 17 does not vert, rocking bar 6 is vertical, the horizontal engine of connecting rod 5
Propeller rotational is driven, aircraft vertical rises, reached after certain altitude hovering, the driving reducing gear 14 of motor 15 drives leading screw
11 are rotated, and the sliding block 12 being nested on leading screw 11 is moved, and the interior bar of the other end of slide block connecting rod 9 is rotated, and control is outer
Side wing 17 verts.After slide block connecting rod 9 is rotated by 90 °, stopped the rotation under the effect of the right-hand member sensor 10 of leading screw 11, make outside wing
17 perpendicular to ground by switching to level in ground and fixed position.
The drive rocker 6 of second stage motor 15, drivening rod 5 makes inboard wing 4 be verted together with propeller, inboard wing 4
Verted together with propeller and be divided into two processes, rocking bar 6 verts 45 ° first, inboard wing 4 is in 45 ° of heeling conditions, stress is steady
After fixed, rocking bar 6 continues to vert 45 °, inboard wing 4 is verted together with propeller to horizontal level.
Final carriage：The level of rocking bar 6, connecting rod 5 is vertical, and sliding block 12 is located at the right-hand member of leading screw 11, wing and propeller level in
Ground, is converted into speed soon, the strong fixed wing aircraft posture of controllability.
General principle of the present utility model and principal character and advantage of the present utility model has been shown and described above.One's own profession
The technical staff of industry is it should be appreciated that the utility model is not restricted to the described embodiments, described in above-described embodiment and specification
Simply illustrate principle of the present utility model, on the premise of the utility model spirit and scope are not departed from, the utility model is also
Various changes and modifications are had, these changes and improvements are both fallen within the range of claimed the utility model.The utility model
Claimed scope is by appended claims and its equivalent thereof.
Claims (4)
1. one kind is used for the double inclining rotary mechanisms of fixed-wing wing, it is characterised in that：It includes three parts：Axle sleeve axle construction (A), four connect
Bar structure (B) and Lead screw transmission structure (C), axle sleeve axle construction (A) are arranged in inboard wing (4) and outside wing (17), and four
Linkage (B) is connected installed in waist with inboard wing (4) and outside wing (17), and Lead screw transmission structure (C) is installed
It is connected on fuselage with interior axle (2), described axle sleeve axle construction (A) includes bearing (1), interior axle (2) and outer shaft (3), bearing (1)
Outside is provided with outer shaft (3), and bearing (1) is internally provided with interior axle (2), and interior axle (2) and outer shaft (3) are connected by bearing (1), outside
Axle (3) connection inboard wing (4), interior axle (2) is embedded in outer bar by bearing (1), through fuselage, and with outside wing (17) phase
Even, steering wheel (7) is connected with screw thread and pad (16), described four-bar linkage structure (B) includes inboard wing (4), connecting rod (5), shaken
Bar (6), steering wheel (7) and transverse axis (18), rocking bar (6) are connected by steering wheel (7) with transverse axis (18), and transverse axis (18) passes through outer shaft
(3) it is connected with inboard wing (4), inboard wing (4), connecting rod (5), rocking bar (6) and transverse axis (18) are mutually sequentially connected, described
Lead screw transmission structure (C) include motor (15), reducing gear (14), ball bearing (13), sensor (10), sliding block (12), silk
Thick stick (11), slide block connecting rod (9) and connecting shaft (8), motor (15) upper end are provided with reducing gear (14), leading screw (11) one end and reducing gear
(14) it is connected, the other end is connected with connecting shaft (8), leading screw (11) upper end is provided with ball bearing (13), leading screw (11) two ends
Sensor (10) is provided with, sliding block (12) is enclosed on leading screw (11), is connected with interior axle (2) by slide block connecting rod (9).
2. it is according to claim 1 a kind of for the double inclining rotary mechanisms of fixed-wing wing, it is characterised in that：Described axle sleeve axle
Structure (A) is located at the junction of outside wing (17) and inboard wing (4).
3. it is according to claim 1 a kind of for the double inclining rotary mechanisms of fixed-wing wing, it is characterised in that：Described two set four
Bar linkage structure (B) is arranged symmetrically on fuselage.
4. it is according to claim 1 a kind of for the double inclining rotary mechanisms of fixed-wing wing, it is characterised in that：Described leading screw is passed
Dynamic structure (C) is located on fuselage to be connected with interior axle (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720255451.9U CN206544597U (en) | 2017-03-16 | 2017-03-16 | One kind is used for the double inclining rotary mechanisms of fixed-wing wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720255451.9U CN206544597U (en) | 2017-03-16 | 2017-03-16 | One kind is used for the double inclining rotary mechanisms of fixed-wing wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206544597U true CN206544597U (en) | 2017-10-10 |
Family
ID=59996156
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720255451.9U Expired - Fee Related CN206544597U (en) | 2017-03-16 | 2017-03-16 | One kind is used for the double inclining rotary mechanisms of fixed-wing wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206544597U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111516866A (en) * | 2020-04-29 | 2020-08-11 | 燕山大学 | Single-drive tilting dual-rotor aircraft |
-
2017
- 2017-03-16 CN CN201720255451.9U patent/CN206544597U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111516866A (en) * | 2020-04-29 | 2020-08-11 | 燕山大学 | Single-drive tilting dual-rotor aircraft |
| CN111516866B (en) * | 2020-04-29 | 2022-08-19 | 燕山大学 | Single-drive tilting dual-rotor aircraft |
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|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171010 Termination date: 20180316 |
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| CF01 | Termination of patent right due to non-payment of annual fee |