CN209553485U - A kind of aircraft rudder surface operating mechanism and the aircraft with it - Google Patents
A kind of aircraft rudder surface operating mechanism and the aircraft with it Download PDFInfo
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- CN209553485U CN209553485U CN201822004217.6U CN201822004217U CN209553485U CN 209553485 U CN209553485 U CN 209553485U CN 201822004217 U CN201822004217 U CN 201822004217U CN 209553485 U CN209553485 U CN 209553485U
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Abstract
The application belongs to aircraft rudder surface manipulation technology field, more particularly to a kind of aircraft rudder surface operating mechanism and with its aircraft, it drives the rotation of the first driving bevel gear, the second driving device to drive the rotation of the second driving bevel gear by first driving device, and the first deflection state, the second deflection state, the third deflection state for generating operating mechanism are combined in the rotation of the first driving bevel gear with the rotation of the second driving bevel gear；Furthermore, additionally provide a kind of aircraft with above-mentioned operating mechanism, operating mechanism is able to drive rudder face in the first deflection state and rotates around active axis, operating mechanism is able to drive rudder face in the second deflection state and rotates around driven axis, operating mechanism is able to drive rudder face in third deflection state and rotates around active axis and driven axis, and the angle of aircraft rudder surface is adjusted within the scope of two freedom degrees to realize.
Description
Technical field
The application belongs to aircraft rudder surface manipulation technology field, and in particular to a kind of aircraft rudder surface operating mechanism and with its
Aircraft.
Background technique
Aircraft rudder surface is designed to adjust aircraft flight direction and its flight attitude, and currently, an aircraft rudder surface only has
A standby deflection freedom degree, only can in one direction be adjusted its angle, provide the manipulation in a direction for aircraft
Torque, manipulation and regulation performance are limited.The operating torque of multiple directions is provided to aircraft to realize, the manipulation for meeting aircraft is wanted
It asks, currently, the technological means that designer generallys use is to cause aircaft configuration complicated for the multiple primary control surfaces of airplane design,
And there is biggish quality, limit the raising of In-Flight Performance.
Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one drawbacks described above of the prior art.
Summary of the invention
The purpose of the application is to provide a kind of aircraft rudder surface operating mechanism and the aircraft with it, above-mentioned to overcome or alleviated by
The defect of at least one aspect.
The technical solution of the application is:
On the one hand a kind of aircraft rudder surface operating mechanism is provided, comprising:
First driving bevel gear；
Second driving bevel gear is oppositely arranged with the first driving bevel gear, and the axis of the first driving bevel gear and second
The axis of driving bevel gear is overlapped with active axis；
First driven bevel pinion is arranged between the first driving bevel gear and the second driving bevel gear, and actively with first
Bevel gear is engaged with the second driving bevel gear；
Second driven bevel pinion is arranged between the first driving bevel gear and the second driving bevel gear, and actively with first
Bevel gear is engaged with the second driving bevel gear；The axis of the axis of first driven bevel pinion and the second driven bevel pinion with it is driven
Axis is overlapped；Active axis intersects with driven axis line；
Driven shaft is arranged between the first driven bevel pinion and the second driven bevel pinion, and one end is and the first driven umbrella
Gear connection, the other end is connect with the second driven bevel pinion, and the axis of driven shaft is overlapped with driven axis, and driven shaft being capable of phase
Second driven bevel pinion is rotated around driven axis；
First driving device is connect with the first driving bevel gear, for driving the first driving bevel gear；
Second driving device is connect with the second driving bevel gear, for driving the second driving bevel gear to turn around active axis
It is dynamic；
Wherein,
First driving bevel gear and the second driving bevel gear, in the same direction to rotation, generate the of operating mechanism with identical speed
One deflection state；
First driving bevel gear and the second driving bevel gear are rotated with identical velocity reversal, generate the second of operating mechanism
Deflection state；
First driving bevel gear rotates at different rates with the second driving bevel gear, generates the third deflection of operating mechanism
State；
Operating mechanism is in:
First deflection state, the first driven bevel pinion, the second driven bevel pinion wheel, driven shaft are rotated around active axis；
Second deflection state, the first driven bevel pinion and the second driven bevel pinion around driven axis rotate, and first from
Dynamic bevel gear is opposite with the second driven bevel pinion rotation direction；
Third deflection state, the first driven bevel pinion, the second driven bevel pinion, driven shaft are rotated around active axis, and the
One driven bevel pinion and the second driven bevel pinion are rotated around driven axis, and the first driven bevel pinion and the second driven bevel pinion turn
It moves contrary.
In some alternative embodiments, first driving device includes first motor, shaft and the first driving bevel gear
Spline fitted connection；
Second driving device includes the second motor, and shaft is connect with the second driving bevel gear spline fitted.
In some alternative embodiments, one end of driven shaft is fixedly connected with the first driven bevel pinion；
Second driven bevel pinion is socketed in the other end of driven shaft.
In some alternative embodiments, above-mentioned operating mechanism further includes connection bearing, is arranged in the second driven bevel pinion
Between driven shaft, outer ring and the second driven bevel pinion interference fit are connected, and inner ring and driven shaft interference fit connect.
In some alternative embodiments, connect bearing, inner ring close to the first driven bevel pinion side wall surface with it is driven
Axis outer wall abuts；
Above-mentioned operating mechanism further includes self-locking nut, is threadedly engaged one end of setting driven shaft, and be located at the second driven umbrella
Side of the gear far from the first driven bevel pinion.
On the other hand a kind of aircraft is provided, comprising: any above-mentioned operating mechanism, wherein
First motor and the second motor are fixed on the body of aircraft；
The rudder face of aircraft is connect with the first driven bevel pinion；
Operating mechanism is in:
First deflection state, rudder face are rotated around active axis；
Second deflection state, rudder face are rotated around driven axis；
Third deflection state, rudder face are rotated around active axis and driven axis.
At least there are following advantageous effects in the application: providing a kind of aircraft rudder surface operating mechanism, pass through first
Driving device drives the rotation of the first driving bevel gear, the second driving device to drive the rotation of the second driving bevel gear, the first active umbrella
The rotation of gear combined with the rotation of the second driving bevel gear generate the first deflection state of operating mechanism, the second deflection state,
Third deflection state；Further it is provided that a kind of aircraft with above-mentioned operating mechanism, operating mechanism energy in the first deflection state
Enough rudder face is driven to rotate around active axis, operating mechanism is able to drive rudder face in the second deflection state and rotates around driven axis,
Operating mechanism is able to drive rudder face in third deflection state and rotates around active axis and driven axis, to realize at two certainly
By the angle of aircraft rudder surface is adjusted within the scope of degree.
Detailed description of the invention
Fig. 1 is the structural scheme of mechanism of aircraft rudder surface operating mechanism provided by the embodiments of the present application；
Fig. 2 is the schematic diagram that aircraft rudder surface operating mechanism is in the first deflection state in Fig. 1；
Fig. 3 is the schematic diagram that aircraft rudder surface operating mechanism is in the second deflection state in Fig. 1；
Fig. 4 is the schematic diagram that aircraft rudder surface operating mechanism is in third deflection state in Fig. 1；
Fig. 5 is the partial structurtes signal provided by the embodiments of the present application with the aircraft of aircraft rudder surface operating mechanism in Fig. 1
Figure；
Fig. 6 is the schematic diagram that aircraft rudder surface operating mechanism drives aircraft rudder surface to rotate in its first deflection state in Fig. 5；
Fig. 7 is the schematic diagram that aircraft rudder surface operating mechanism drives aircraft rudder surface to rotate in its second deflection state in Fig. 5；
Fig. 8 is the schematic diagram that aircraft rudder surface operating mechanism drives aircraft rudder surface to rotate in its third deflection state in Fig. 5.
Specific embodiment
The application is described in further detail with reference to the accompanying drawings and examples.It is understood that this place is retouched
The specific embodiment stated is used only for explaining related application, rather than the restriction to this application.It also should be noted that in order to
Convenient for description, part relevant to the application is illustrated only in attached drawing.
It should be noted that in the absence of conflict, the features in the embodiments and the embodiments of the present application can phase
Mutually combination.The application is described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
It should be noted that in the description of the present application, term " center ", "upper", "lower", "left", "right", "vertical",
The direction of the instructions such as "horizontal", "inner", "outside" or the term of positional relationship are direction based on the figure or positional relationship, this
It is intended merely to facilitate description, rather than indication or suggestion described device or element must have a particular orientation, with specific
Orientation construction and operation, therefore should not be understood as the limitation to the application.In addition, term " first ", " second ", " third " are only used
In description purpose, it is not understood to indicate or imply relative importance.
In addition it is also necessary to explanation, in the description of the present application unless specifically defined or limited otherwise, term " peace
Dress ", " connected ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integrally
Connection；It can be mechanical connection, be also possible to be electrically connected；Can be directly connected, can also indirectly connected through an intermediary,
It can be the connection inside two elements.To those skilled in the art, it can understand that above-mentioned term exists as the case may be
Concrete meaning in the application.
1 to Fig. 6 the application is described in further details with reference to the accompanying drawing.
On the one hand a kind of aircraft rudder surface operating mechanism is provided, comprising:
First driving bevel gear 1；
Second driving bevel gear 2 is oppositely arranged with the first driving bevel gear 1, and the axis of the first driving bevel gear 1 and
The axis of two driving bevel gears 2 is overlapped with active axis；
First driven bevel pinion 3 is arranged between the first driving bevel gear 1 and the second driving bevel gear 2, and leads with first
Dynamic bevel gear 1 is engaged with the second driving bevel gear 2；
Second driven bevel pinion 4 is arranged between the first driving bevel gear 1 and the second driving bevel gear 2, and leads with first
Dynamic bevel gear 1 is engaged with the second driving bevel gear 2；The axis of first driven bevel pinion 3 and the axis of the second driven bevel pinion 4 are equal
It is overlapped with driven axis；Active axis intersects with driven axis line；
Driven shaft 5 is arranged between the first driven bevel pinion 3 and the second driven bevel pinion 4, one end be with it is first driven
Bevel gear 3 connects, and the other end is connect with the second driven bevel pinion 4, and the axis of driven shaft 5 is overlapped with driven axis, driven shaft 5
It can be rotated relative to the second driven bevel pinion 4 around driven axis；
First driving device 6 is connect with the first driving bevel gear 1, for driving the first driving bevel gear 1；
Second driving device 7 is connect with the second driving bevel gear 2, for driving the second driving bevel gear 2 around active axis
Rotation；
Wherein,
First driving bevel gear 1 and the second driving bevel gear 2, in the same direction to rotation, generate operating mechanism with identical speed
First deflection state；
First driving bevel gear 1 and the second driving bevel gear 2 generate the of operating mechanism with identical velocity reversal rotation
Two deflection states；
First driving bevel gear 1 rotates at different rates with the second driving bevel gear 2, and the third for generating operating mechanism is inclined
Turn state；
Operating mechanism is in:
First deflection state, the first driven bevel pinion 3, the second driven bevel pinion 4, driven shaft 5 are rotated around active axis；
Second deflection state, the first driven bevel pinion 3 and the second driven bevel pinion 4 are rotated around driven axis, and first
Driven bevel pinion 3 is opposite with 4 rotation direction of the second driven bevel pinion；
Third deflection state, the first driven bevel pinion 3, the second driven bevel pinion 4, driven shaft 5 are rotated around active axis, and
First driven bevel pinion 3 and the second driven bevel pinion 4 are rotated around driven axis, the first driven bevel pinion 3 and the second driven umbrella
4 rotation direction of gear is opposite.
In some alternative embodiments, first driving device 6 includes first motor, shaft and the first driving bevel gear
The connection of 1 spline fitted；
Second driving device 7 includes the second motor, and shaft is connect with 2 spline fitted of the second driving bevel gear.
In some alternative embodiments, one end of driven shaft 5 is fixedly connected with the first driven bevel pinion 3；
Second driven bevel pinion 4 is socketed in the other end of driven shaft 5.
In some alternative embodiments, above-mentioned rudder face operating mechanism further includes connection bearing 8, is arranged driven second
Between bevel gear 4 and driven shaft 5, outer ring and the second driven bevel pinion 4 interference fit are connected, inner ring and 5 interference of driven shaft
It is cooperatively connected.
In some alternative embodiments, connection 8 inner ring of bearing close to 3 side of the first driven bevel pinion wall surface with from
5 outer wall of moving axis abuts；
Above-mentioned operating mechanism further includes self-locking nut 9, is threadedly engaged one end of setting driven shaft 5, and above-mentioned rudder face manipulates machine
Structure, and it is located at side of second driven bevel pinion 4 far from the first driven bevel pinion 3.
On the other hand a kind of aircraft is provided, comprising: any above-mentioned aircraft rudder surface operating mechanism, wherein
First motor and the second motor are fixed on the body of aircraft；
The rudder face 10 of aircraft is connect with the first driven bevel pinion 3；
Operating mechanism is in:
First deflection state, rudder face 10 are rotated around active axis；
Second deflection state, rudder face 10 are rotated around driven axis；
Third deflection state, rudder face 10 are rotated around active axis and driven axis.
Aircraft rudder surface operating mechanism disclosed in the embodiment of the present application is based on differential gear train principle, passes through the first electricity
Machine, second motor control the first driving bevel gear 1 and the second driving bevel gear 2 are rotated in a predetermined direction with pre-set velocity, from
And the first driven bevel pinion 3 and driven bevel pinion 4 is driven to rotate around active axis and/or driven axis.
Aircraft disclosed in the present embodiment has above-mentioned aircraft rudder surface operating mechanism, the rudder face 10 and operating mechanism on aircraft
The connection of first driven bevel pinion 3 can rotate under the drive of the first driven bevel pinion 3 around active axis and/or driven axis, from
And it easily realizes control rudder face and quickly rotates to being arbitrarily designated posture.
By disclosed operating mechanism described in the embodiment of the present application, can easily realize to aircraft rudder surface in two freedom degrees
The manipulation in direction, it, which manipulates a rudder face by a set of operating mechanism, compared with prior art to provide both direction for aircraft
On operating torque, application aboard can greatly reduce the quantity of rudder face operating mechanism and aircraft rudder surface, so as to
Mitigate the quality that aircraft is, improves the maneuvering performance of aircraft.
So far, it has been combined preferred embodiment shown in the drawings and describes the technical solution of the application, still, this field
Technical staff is it is easily understood that the protection scope of the application is expressly not limited to these specific embodiments.Without departing from this
Under the premise of the principle of application, those skilled in the art can make equivalent change or replacement to the relevant technologies feature, these
Technical solution after change or replacement is fallen within the protection scope of the application.
Claims (6)
1. a kind of aircraft rudder surface operating mechanism characterized by comprising
First driving bevel gear (1)；
Second driving bevel gear (2) is oppositely arranged with first driving bevel gear (1), and first driving bevel gear (1)
Axis be overlapped with active axis with the axis of second driving bevel gear (2)；
First driven bevel pinion (3) is arranged between first driving bevel gear (1) and second driving bevel gear (2),
And it is engaged with first driving bevel gear (1) with second driving bevel gear (2)；
Second driven bevel pinion (4) is arranged between first driving bevel gear (1) and second driving bevel gear (2),
And it is engaged with first driving bevel gear (1) with second driving bevel gear (2)；First driven bevel pinion (3)
Axis is overlapped with driven axis with the axis of second driven bevel pinion (4)；The active axis and the driven axis
Line intersection；
Driven shaft (5) is arranged between first driven bevel pinion (3) and second driven bevel pinion (4), and one end is
It is connect with first driven bevel pinion (3), the other end is connect with second driven bevel pinion (4), and the driven shaft (5)
Axis be overlapped with the driven axis, the driven shaft (5) can relative to second driven bevel pinion (4) around it is described from
Shaft line rotation；
First driving device (6) is connect, for driving first driving bevel gear with first driving bevel gear (1)
(1)；
Second driving device (7) is connect with second driving bevel gear (2), for driving second driving bevel gear (2)
It is rotated around the active axis；
Wherein,
First driving bevel gear (1) is with second driving bevel gear (2) with identical speed in the same direction to rotation, generation behaviour
First deflection state of vertical mechanism；
First driving bevel gear (1) and second driving bevel gear (2) generate manipulation with identical velocity reversal rotation
Second deflection state of mechanism；
First driving bevel gear (1) rotates at different rates with second driving bevel gear (2), generates operating mechanism
Third deflection state；
The operating mechanism is in:
First deflection state, first driven bevel pinion (3), second driven bevel pinion (4), the driven shaft
(5) it is rotated around the active axis；
Second deflection state, first driven bevel pinion (3) and the second driven bevel pinion (4) are around the driven axis
Rotation, and first driven bevel pinion (3) is opposite with the second driven bevel pinion (4) rotation direction；
The third deflection state, first driven bevel pinion (3), second driven bevel pinion (4), the driven shaft
(5) it is rotated around the active axis, and first driven bevel pinion (3) and the second driven bevel pinion (4) are around described driven
Axis rotation, first driven bevel pinion (3) are opposite with the second driven bevel pinion (4) rotation direction.
2. aircraft rudder surface operating mechanism according to claim 1, which is characterized in that
The first driving device (6) includes first motor, and shaft and the first driving bevel gear (1) spline fitted connect
It connects；
Second driving device (7) includes the second motor, and shaft and the second driving bevel gear (2) spline fitted connect
It connects.
3. with according to aircraft rudder surface operating mechanism as claimed in claim 2, which is characterized in that
One end of the driven shaft (5) is fixedly connected with first driven bevel pinion (3)；
Second driven bevel pinion (4) is socketed in the other end of the driven shaft (5).
4. aircraft rudder surface operating mechanism according to claim 3, which is characterized in that further include connection bearing (8), setting exists
Between second driven bevel pinion (4) and the driven shaft (5), outer ring is matched with the second driven bevel pinion (4) interference
Connection is closed, inner ring and the driven shaft (5) interference fit connect.
5. aircraft rudder surface operating mechanism according to claim 4, which is characterized in that
Wall surface and the driven shaft (5) outer wall of connection bearing (8) inner ring close to the first driven bevel pinion (3) side
It abuts；
Further include self-locking nut (9), is threadedly engaged one end that the driven shaft (5) is set, and be located at the described second driven umbrella tooth
Take turns the side of (4) far from first driven bevel pinion (3).
6. a kind of aircraft characterized by comprising aircraft rudder surface operating mechanism described in claim 5, wherein
The first motor and second motor are fixed on the body of aircraft；
The rudder face (10) of the aircraft is connect with first driven bevel pinion (3)；
The operating mechanism is in:
First deflection state, the rudder face (10) rotate around the active axis；
Second deflection state, the rudder face (10) rotate around the driven axis；
The third deflection state, the rudder face (10) rotate around the active axis and the driven axis.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822004217.6U CN209553485U (en) | 2018-12-01 | 2018-12-01 | A kind of aircraft rudder surface operating mechanism and the aircraft with it |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822004217.6U CN209553485U (en) | 2018-12-01 | 2018-12-01 | A kind of aircraft rudder surface operating mechanism and the aircraft with it |
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| Publication Number | Publication Date |
|---|---|
| CN209553485U true CN209553485U (en) | 2019-10-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201822004217.6U Active CN209553485U (en) | 2018-12-01 | 2018-12-01 | A kind of aircraft rudder surface operating mechanism and the aircraft with it |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111268099A (en) * | 2019-12-27 | 2020-06-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Folding wing flap driving transmission mechanism |
| CN111891336A (en) * | 2020-09-02 | 2020-11-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Variable-configuration control surface for realizing composite control of airplane |
| CN112389638A (en) * | 2020-11-06 | 2021-02-23 | 西安远超航空科技有限公司 | Crank transmission type flying patrol device folding mechanism |
-
2018
- 2018-12-01 CN CN201822004217.6U patent/CN209553485U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111268099A (en) * | 2019-12-27 | 2020-06-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Folding wing flap driving transmission mechanism |
| CN111268099B (en) * | 2019-12-27 | 2022-02-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Folding wing flap driving transmission mechanism |
| CN111891336A (en) * | 2020-09-02 | 2020-11-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Variable-configuration control surface for realizing composite control of airplane |
| CN112389638A (en) * | 2020-11-06 | 2021-02-23 | 西安远超航空科技有限公司 | Crank transmission type flying patrol device folding mechanism |
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