CN207972791U - aircraft aileron control system - Google Patents
aircraft aileron control system Download PDFInfo
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- CN207972791U CN207972791U CN201721369826.0U CN201721369826U CN207972791U CN 207972791 U CN207972791 U CN 207972791U CN 201721369826 U CN201721369826 U CN 201721369826U CN 207972791 U CN207972791 U CN 207972791U
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Abstract
The utility model is related to a kind of aircraft aileron control systems.The aircraft aileron control system includes：Body, the body include fuselage, wing, and the fuselage is connected with wing and the wing is equipped with aileron；Servo motor in body, the servo motor are equipped with sliding block, the link mechanism for driving aileron are socketed on the sliding block；Sliding block on link mechanism one end socket servo motor, is connected with the other end being connected with corresponding to sliding block one end with aileron.Servo motor is arranged in internal body in above-mentioned aircraft aileron control system, and so as to improve the surface structure of aircraft, the link mechanism being connected with by the sliding block on servo motor, the above-mentioned link mechanism other end connects and controls aileron.It is finally reached the rotary motion that the linear motion of steering engine is changed into aileron rudder face by link mechanism, to drive the technique effect of aileron rudder face.
Description
Technical field
This application involves air vehicle technique fields, more particularly to a kind of aircraft aileron control system.
Background technology
With the development of micro electronmechanical (MEMS) technology, aircraft applications are more and more extensive.Aircraft can be used for taking photo by plane, carry
For the smaller article in virtual reality visual angle or shipping mass.Aircraft for taking photo by plane or providing virtual reality visual angle, to shooting
The requirement of quality is higher and higher.
During realizing the prior art, it is found by the applicant that at least there are the following problems in the prior art：
To the control of rudder face mostly by pulling steel wire to pull rudder face holder, this mode not only influences to fly traditional steering engine
The appearance of device causes structure unsightly, also affects the air force of itself.
Invention content
Based on this, it is necessary to not only influence the appearance of aircraft for the prior art, structure is caused unsightly also to affect
The problem of air force of itself, provides a kind of aircraft aileron control system.
A kind of aircraft aileron control system, the aircraft aileron control system include：Body, the body include machine
Body, wing, the fuselage is connected with wing and the wing is equipped with aileron；Servo motor in body, the servo electricity
Machine is equipped with sliding block, and the link mechanism for driving aileron is socketed on the sliding block；Link mechanism one end socket servo electricity
Sliding block on machine is connected with the other end being connected with corresponding to sliding block one end with aileron.
Servo motor is arranged in internal body, so as to improve the appearance knot of aircraft in above-mentioned aircraft aileron control system
Structure, the link mechanism being connected with by the sliding block on servo motor, the above-mentioned link mechanism other end connect and control aileron.Finally reach
To the rotary motion that the linear motion of steering engine is changed into aileron rudder face by link mechanism, to drive the technology of aileron rudder face
Effect.
The link mechanism includes the first drive link and the second drive link in one of the embodiments, and described first passes
The sliding block that lever is equipped with the servo motor socket-connects, and second drive link is connected with the aileron.
First drive link and the second drive link are metallic rod in one of the embodiments,.
The link mechanism is set to the internal body in one of the embodiments,.
First drive link is set to the fuselage in one of the embodiments, and second drive link is set to described
Wing, and first drive link intersects socket with the second drive link by being socketed driving member.
In one of the embodiments, it is characterized in that, the socket driving member is equipped with for being socketed first transmission
Bar and the through-hole of the second drive link handing-over end and square crossing.
The wing is equipped with fixing device for fixing the second drive link in one of the embodiments, and described the
Two drive links are passed through in the fixing device.
The quantity of the fixing device is at least one in one of the embodiments,.
In one of the embodiments, the aileron be equipped with groove, second drive link not with first drive link
One end of socket is equipped with the bending structure perpendicular to the aileron, and the bending structure is placed in the groove to drive the pair
The wing.
The sliding block is equipped with the through-hole for being clamped link mechanism in one of the embodiments,.
Description of the drawings
Fig. 1 is a kind of aircraft unilateral side aileron control system schematic diagram provided by the embodiments of the present application；
Fig. 2 is a kind of aileron control system partial schematic diagram provided by the embodiments of the present application.
Wherein,
Body 100
Fuselage 101
Wing 102
Aileron 200
Servo motor 300
Lead screw 301
Sliding block 302
First drive link 401
Second drive link 402
It is socketed driving member 403
Specific implementation mode
To keep the purpose, technical scheme and advantage of the application clearer, below in conjunction with the application specific embodiment and
Technical scheme is clearly and completely described in corresponding attached drawing.Obviously, described embodiment is only the application one
Section Example, instead of all the embodiments.Based on the embodiment in the application, those of ordinary skill in the art are not doing
Go out the every other embodiment obtained under the premise of creative work, shall fall in the protection scope of this application.
The embodiment of the present invention is described below in detail, examples of the embodiments are shown in the accompanying drawings, wherein from beginning to end
Same or similar label indicates same or similar element or element with the same or similar functions.Below with reference to attached
The embodiment of figure description is exemplary, and is only used for explaining the present invention, and is not considered as limiting the invention.
In the description of the present invention, it is to be understood that, term " longitudinal direction ", " transverse direction ", "upper", "lower", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, and does not indicate or imply the indicated dress
It sets or element must have a particular orientation, with specific azimuth configuration and operation, therefore should not be understood as the limit to the present invention
System.
In the description of the present invention, unless otherwise specified and limited, it should be noted that term " installation ", " connected ",
" connection " shall be understood in a broad sense, for example, it may be mechanical connection or electrical connection, can also be the connection inside two elements, it can
, can also indirectly connected through an intermediary, for the ordinary skill in the art to be to be connected directly, it can basis
Concrete condition understands the concrete meaning of above-mentioned term.
Here aircraft occurs usually in the form of unmanned plane, for taking photo by plane, providing virtual reality visual angle or transport matter
The smaller article of amount.In order to make it easy to understand, illustrating only by taking the aircraft for providing aerial photography function as an example here, it should be pointed out that
It is, as long as can be the implementation of the application concrete application to the aircraft that the image shot in aircraft has certain image quality to require
Example.
Here the specific form of aircraft occurs, still usually in the form of rotor craft, however not excluded that fixed-wing flies
Row device, driven helicopter, or even it is not excluded for the aircraft using heating power lift-off.
It should be understood that be, the specific application function of aircraft here and specifically there is form, is not construed as
Limitation to the substantial protection range of the application.
It please refers to shown in Fig. 1-2, the present invention provides a kind of aircraft aileron control system.
In one embodiment, a kind of aircraft aileron control system is provided, above-mentioned aircraft aileron control system includes：Packet
The body 100 of fuselage 101, wing 102 is included, above-mentioned fuselage 101 is connected with wing 102, and above-mentioned wing 102 is equipped with aileron 200；
Servo motor 300 is equipped in body 100, above-mentioned servo motor 300 is equipped with sliding block 302, and is socketed with and is used on above-mentioned sliding block 302
Drive the link mechanism of aileron 200；Sliding block 302 on above-mentioned link mechanism one end socket servo motor, sliding block is connected with above-mentioned
The other end corresponding to 302 one end is connected with aileron 200.
Above-mentioned aircraft aileron control system is used to drive the aileron 200 on wing 102 in aircraft working condition,
And then control the flight effect of entire aircraft.
In one embodiment, the above-mentioned body 100 being made of fuselage 101, wing 102 is a complete aircraft,
Above-mentioned wing 102 is equipped with 200 rudder face of aileron.Servo motor 300 is equipped in above-mentioned body.
Specifically, above-mentioned servo motor 300 is screw steering engine, and above-mentioned screw steering engine includes at least stake body, above-mentioned holder
It is equipped with lead screw 301 in vivo, above-mentioned sliding block 302 is threaded on above-mentioned lead screw 301, and above-mentioned sliding block 302 can be in above-mentioned holder
It is moved back and forth in guide groove on body.
In a specific embodiment, above-mentioned sliding block 302 is equipped at least one through-hole, and above-mentioned through-hole is for being clamped first
One end of drive link 401.
In one embodiment, above-mentioned for driving the link mechanism of aileron 200 to be driven by the first drive link 401 and second
Bar 402 is formed by connecting.
Specifically, above-mentioned first drive link 401 is connected with the second drive link 402 by being socketed driving member 403, above-mentioned set
It connects driving member 403 to be set in 100 1 groove of body, and above-mentioned socket driving member 403 has at least two through-holes, above-mentioned two is logical
Hole is used for across 401 and second drive link 402 of above-mentioned first drive link, and interaction is vertically installed in above-mentioned socket driving member 403.
In a specific embodiment, 300 top shoe of above-mentioned servo motor is fixed in one end of above-mentioned first drive link 401
One end of 302 through-hole, the other end and the second drive link 402 that above-mentioned first drive link 401 is not passed through sliding block 302 is passed through in upper
State socket driving member 403.At runtime, above-mentioned sliding block 302 is as the movement of above-mentioned lead screw 301 is upper for above-mentioned servo motor 300
It states in guide groove and moves back and forth, and one end of above-mentioned first drive link 401 is due to the sliding block 302 that is connected on above-mentioned screw steering engine
On, when above-mentioned sliding block 302 moves back and forth in above-mentioned guide groove, above-mentioned first drive link 401 moves back and forth therewith, and due to above-mentioned
The other end that first drive link 401 is not connected with sliding block 302 is socketed on above-mentioned socket driving member 403, and above-mentioned first drive link 401 connects
There is one end of sliding block 302 to be transferred on above-mentioned socket driving member 403, drives the reciprocating motion of above-mentioned socket driving member 403, due to
Then the second drive link 402 is also covered on socket driving member 403, to make the second drive link 402 also by above-mentioned first drive link
401 influence, and then be driven to 200 rudder face of aileron.
Further, above-mentioned aileron 200 is equipped with groove, above-mentioned second drive link 402 not with 401 sets of above-mentioned first drive link
The one end connect is equipped with the bending structure perpendicular to above-mentioned aileron 200, and above-mentioned bending structure is placed in above-mentioned groove to drive aileron
200。
In one embodiment, above-mentioned second drive link 402 is fixed in the groove on wing 102, the ruler of above-mentioned groove
Very little size and the size of above-mentioned second drive link 402 match.
Further, in above-mentioned groove, equipped with the fixing device for fixing the second drive link 402, above-mentioned fixed dress
It is set to equipped with the drive link holder for the socket structure across the second drive link.
In a specific embodiment, the geometric dimension for the second drive link 402 and wing 102 considers, in above-mentioned machine
The quantity of set fixing device is 2-3 on the wing 102.
In one embodiment, above-mentioned first drive link 401 and above-mentioned second drive link 402 are metallic rod.
Specifically, above-mentioned first drive link 401 and above-mentioned second drive link 402 are the suitable steel wire of size.
In one embodiment, for the air force being subject to aircraft itself the considerations of, above-mentioned aileron control system
System may be contained in body.The first drive link 401 in above-mentioned link mechanism is set in fuselage 101, with above-mentioned servo motor
300 are connected.The second drive link 402 in above-mentioned link mechanism is set in the groove of wing 102.
Above-mentioned aircraft is in working condition, due to being threaded with sliding block on the lead screw 301 in above-mentioned screw steering engine
302, and the first drive link 401 is connected on above-mentioned sliding block 302, so when screw steering engine works, above-mentioned sliding block 302 is with lead screw
Moved back and forth in 301 guide groove in above-mentioned screw steering engine stake body, above-mentioned first drive link 401 along sliding block 302 movement
Track and move.Above-mentioned first drive link 401 and the second drive link 402 are connect and are driven by being socketed driving member 403, by
After the driving force of first drive link 401, above-mentioned socket driving member 403 is moved also along the movement locus of sliding block 302, due to above-mentioned
Second drive link 402 is also socketed on above-mentioned socket driving member 403, according to the second drive link 402 and above-mentioned first drive link 401
Relative position relation, by the driving force with 401 Relative vertical direction of the first drive link.Not due to above-mentioned second drive link 402
It is equipped with bending structure with the other end of the first drive link 401 handing-over, above-mentioned bending structure is for directly driving 200 rudder of above-mentioned aileron
Face, to which above-mentioned aircraft has reached the technique effect of driving 200 rudder face of aileron.
It is fixed in the groove on above-mentioned wing 200 it should be noted that referring to above-mentioned second drive links of Fig. 2 402, it is above-mentioned
The size of groove and the size of above-mentioned second drive link 402 match.In above-mentioned groove, if there are two for solid
The drive link holder of fixed second drive link 402.
Servo motor 300 is arranged, so as to improve aircraft in above-mentioned aircraft aileron control system inside body 100
Surface structure, the link mechanism being connected with by the sliding block 302 on servo motor 300, the above-mentioned link mechanism other end are connected and are controlled
Aileron 20 processed.It is finally reached the rotary motion that the linear motion of screw steering engine is changed into 200 rudder face of aileron by link mechanism,
To drive the technique effect of 200 rudder face of aileron.
In addition to the above advantage, above-mentioned aircraft aileron control system is also simple in structure, and appearance is compared with traditional technology
The advantageous effects such as improvement, and the link mechanism of above-mentioned aircraft aileron control system may be contained in body 100, to aircraft
Air force does not impact.
Each technical characteristic of embodiment described above can be combined arbitrarily, to keep description succinct, not to above-mentioned reality
It applies all possible combination of each technical characteristic in example to be all described, as long as however, the combination of these technical characteristics is not deposited
In contradiction, it is all considered to be the range of this specification record.
Several embodiments of the invention above described embodiment only expresses, the description thereof is more specific and detailed, but simultaneously
It cannot therefore be construed as limiting the scope of the patent.It should be pointed out that coming for those of ordinary skill in the art
It says, without departing from the inventive concept of the premise, various modifications and improvements can be made, these belong to the protection of the present invention
Range.Therefore, the protection domain of patent of the present invention should be determined by the appended claims.
Claims (10)
1. a kind of aircraft aileron control system, which is characterized in that the aircraft aileron control system includes：
Body, the body include fuselage, wing, and the fuselage is connected with wing and the wing is equipped with aileron；
Servo motor in body, the servo motor are equipped with sliding block, are socketed on the sliding block for driving aileron
Link mechanism；
Sliding block on link mechanism one end socket servo motor, with the other end and aileron phase being connected with corresponding to sliding block one end
Connection.
2. aircraft aileron control system according to claim 1, which is characterized in that the link mechanism includes the first biography
Lever and the second drive link, the sliding block that first drive link is equipped with the servo motor socket-connect, second drive link
It is connected with the aileron.
3. aircraft aileron control system according to claim 2, which is characterized in that first drive link and second passes
Lever is metallic rod.
4. aircraft aileron control system according to claim 2, which is characterized in that the link mechanism is set to described
Internal body.
5. aircraft aileron control system according to claim 4, which is characterized in that first drive link is set to described
Fuselage, second drive link is set to the wing, and first drive link and the second drive link are handed over by being socketed driving member
Fork socket.
6. aircraft aileron control system according to claim 5, which is characterized in that the socket driving member is equipped with and is used for
It is socketed first drive link and the through-hole of the second drive link handing-over end and square crossing.
7. aircraft aileron control system according to claim 2, which is characterized in that the wing is equipped with for fixing
The fixing device of second drive link, second drive link are passed through in the fixing device.
8. aircraft aileron control system according to claim 7, which is characterized in that the quantity of the fixing device is at least
It is one.
9. aircraft aileron control system according to claim 2, which is characterized in that the aileron is equipped with groove, described
Second drive link is not equipped with the bending structure perpendicular to the aileron, the bending knot with one end of first drive link socket
It sets up in the groove to drive the aileron.
10. aircraft aileron control system according to claim 1, which is characterized in that the sliding block is equipped with for being clamped
The through-hole of link mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721369826.0U CN207972791U (en) | 2017-10-23 | 2017-10-23 | aircraft aileron control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721369826.0U CN207972791U (en) | 2017-10-23 | 2017-10-23 | aircraft aileron control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207972791U true CN207972791U (en) | 2018-10-16 |
Family
ID=63771044
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721369826.0U Active CN207972791U (en) | 2017-10-23 | 2017-10-23 | aircraft aileron control system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207972791U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112124562A (en) * | 2020-11-20 | 2020-12-25 | 中国空气动力研究与发展中心高速空气动力研究所 | Aircraft and aircraft control method thereof |
| CN112238932A (en) * | 2020-11-20 | 2021-01-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Aircraft flutter suppression device and aircraft thereof |
-
2017
- 2017-10-23 CN CN201721369826.0U patent/CN207972791U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112124562A (en) * | 2020-11-20 | 2020-12-25 | 中国空气动力研究与发展中心高速空气动力研究所 | Aircraft and aircraft control method thereof |
| CN112238932A (en) * | 2020-11-20 | 2021-01-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Aircraft flutter suppression device and aircraft thereof |
| CN112124562B (en) * | 2020-11-20 | 2021-03-30 | 中国空气动力研究与发展中心高速空气动力研究所 | Aircraft and aircraft control method thereof |
| CN112238932B (en) * | 2020-11-20 | 2021-05-28 | 中国空气动力研究与发展中心高速空气动力研究所 | Aircraft flutter suppression device and aircraft thereof |
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