CN210047616U - Fixed posture adjusting device of aircraft - Google Patents
Fixed posture adjusting device of aircraft Download PDFInfo
- Publication number
- CN210047616U CN210047616U CN201920435689.9U CN201920435689U CN210047616U CN 210047616 U CN210047616 U CN 210047616U CN 201920435689 U CN201920435689 U CN 201920435689U CN 210047616 U CN210047616 U CN 210047616U
- Authority
- CN
- China
- Prior art keywords
- push rod
- aircraft
- power push
- gesture
- regulating plate
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Abstract
The utility model discloses a fixed gesture adjusting device of aircraft, including mounting bracket, gesture regulating plate and power push rod, the mounting bracket include the crossbeam and with crossbeam cross arrangement's longeron, the below of crossbeam and longeron all is provided with a plurality of installation pieces and fixing base, the gesture regulating plate is provided with two pivots symmetrically, pivot and the shaft hole normal running fit on the installation piece, the tip of power push rod telescopic link is articulated with the side of gesture regulating plate, and the one end that the telescopic link was kept away from to power push rod is articulated with the fixing base lower extreme. The utility model discloses a design simple structure, the processing and the assembly of being convenient for can realize the control to coaxial two wing aircraft flight gesture through the certain angle of power push rod drive gesture regulating plate swing simultaneously, and control mode is simple, improves controlling of aircraft performance, is favorable to coaxial two wing aircraft's popularization and application.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field, concretely relates to fixed gesture adjusting device of aircraft.
Background
The existing coaxial dual-rotor aircraft has fewer types and relatively low maturity, and compared with other types of aircraft, the structural design and attitude control technology is not mature enough, and the application range is narrow, mainly because the aircraft requires a complicated fuselage mechanism, and the control system has high design difficulty and poor controllability, which are the primary reasons for limiting the development of the coaxial dual-rotor aircraft.
SUMMERY OF THE UTILITY MODEL
The utility model discloses a solve the not enough of prior art, provide a simple structure and control fixed gesture adjusting device of good performance aircraft.
In order to achieve the above purpose, the utility model provides a following technical scheme:
the utility model provides a fixed gesture adjusting device of aircraft, includes mounting bracket, gesture regulating plate and power push rod, the mounting bracket include the crossbeam and with crossbeam cross arrangement's longeron, the below of crossbeam and longeron all is provided with a plurality of installation pieces and fixing base, the gesture regulating plate is provided with two pivots symmetrically, the shaft hole normal running fit on pivot and the installation piece, the tip of power push rod telescopic link is articulated with the side of gesture regulating plate, and the one end that power push rod kept away from the telescopic link is articulated with the fixing base lower extreme.
Furthermore, the included angle between the cross beam and the longitudinal beam is 90 degrees.
Furthermore, the cross beam and the longitudinal beam are integrally formed in an injection molding mode.
Furthermore, through holes used for being assembled with the aircraft frame are formed in two ends of the cross beam.
Furthermore, the fixing base includes first fixed plate and the second fixed plate of parallel arrangement, and the one end that power push rod kept away from the telescopic link sets up between first fixed plate and second fixed plate with articulating.
Compared with the prior art, the utility model discloses a design simple structure, the processing and the assembly of being convenient for can realize the control to coaxial two wing aircraft flight gesture through the certain angle of power push rod drive gesture regulating plate swing simultaneously, and control mode is simple, improves controlling of aircraft performance, is favorable to coaxial two wing aircraft's popularization and application.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a front view of the present invention;
FIG. 2 is an enlarged view of a portion of FIG. 1 at I;
FIG. 3 is an enlarged partial view taken at II in FIG. 1;
fig. 4 is a perspective view of the present invention;
the reference numerals are explained below:
in the figure: 1. a cross beam; 101. a through hole; 2. a stringer; 3. a power push rod; 4. a fixed seat; 401. a first fixing plate; 402. A second fixing plate; 5. a posture adjusting plate; 501. a rotating shaft; 6. and (7) installing the block.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be described in detail below. It is to be understood that the embodiments described are only some embodiments of the invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
Referring to fig. 1-4, the present invention provides a fixed posture adjustment device for an aircraft, which comprises a mounting frame, a posture adjustment plate 5 and a power push rod 3; the mounting frame comprises a cross beam 1 and a longitudinal beam 2 crossed with the cross beam 1, and four mounting blocks 6 and two fixing seats 4 are arranged below the cross beam 1 and the longitudinal beam 2; two rotating shafts 501 are symmetrically arranged at two ends of the posture adjusting plate 5, the rotating shafts 501 are rotatably matched with the mounting block 6, and mounting holes matched with the rotating shafts 501 can be formed in the mounting block 6; power push rod 3 is servo electric putter, and the tip of its telescopic link is articulated with the side of gesture regulating plate 5, and the one end that power push rod 3 kept away from the telescopic link is articulated with fixing base 4 lower extreme, and gesture regulating plate 5 can revolute the swing of rotation 501 under power push rod 3's effect.
The utility model discloses in, contained angle between crossbeam 1 and the longeron 2 is 90, crossbeam 1 and 2 integrative injection moulding of longeron, installation piece 6 and fixing base 4 also can adopt with crossbeam 1 and 2 integrated into one piece's of longeron processing mode, and crossbeam 1's both ends are provided with the through-hole 101 that is used for with the assembly of aircraft frame, and the project organization is simple reasonable, is convenient for process and assembly.
The utility model discloses in, fixing base 4 includes parallel arrangement's first fixed plate 401 and second fixed plate 402, and the one end that power push rod 3 kept away from the telescopic link on it sets up between first fixed plate 401 and second fixed plate 402 with articulating.
The utility model discloses when concrete implementation, locate to be connected with the frame of aircraft through the bolt at through-hole 101, four power push rod 3 all with the flight control system electric connection of aircraft, through the flexible volume of flight control system control power push rod 3, make 5 revolute shaft 501 swing corresponding angles of gesture regulation version, the air current that the aircraft rotor produced acts on gesture regulating plate 5, and then makes the flight gesture of aircraft change.
The above description is only for the specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art can easily think of the changes or substitutions within the technical scope of the present invention, and all should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (5)
1. The fixed posture adjusting device of the aircraft is characterized by comprising a mounting frame, a posture adjusting plate (5) and a power push rod (3), wherein the mounting frame comprises a cross beam (1) and a longitudinal beam (2) which is arranged in a cross mode with the cross beam (1), a plurality of mounting blocks (6) and a fixing seat (4) are arranged below the cross beam (1) and the longitudinal beam (2), two rotating shafts (501) are symmetrically arranged at two ends of the posture adjusting plate (5), the rotating shafts (501) are in rotating fit with the mounting blocks (6), the end portion of a telescopic rod of the power push rod (3) is hinged to the side face of the posture adjusting plate (5), and one end, far away from the telescopic rod, of the power push rod (3) is hinged to the lower end of the fixing seat (4.
2. The fixed attitude adjustment device of an aircraft according to claim 1, characterized in that: the included angle between the cross beam (1) and the longitudinal beam (2) is 90 degrees.
3. The fixed attitude adjustment device of an aircraft according to claim 2, characterized in that: the transverse beam (1) and the longitudinal beam (2) are integrally formed by injection molding.
4. The fixed attitude adjustment device of an aircraft according to claim 3, characterized in that: both ends of the cross beam (1) are provided with through holes (101) used for being assembled with an aircraft frame.
5. The fixed attitude adjustment device of an aircraft according to claim 1, characterized in that: the fixing seat (4) comprises a first fixing plate (401) and a second fixing plate (402) which are arranged in parallel, and one end, far away from the telescopic rod, of the power push rod (3) is hinged between the first fixing plate (401) and the second fixing plate (402).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920435689.9U CN210047616U (en) | 2019-04-02 | 2019-04-02 | Fixed posture adjusting device of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920435689.9U CN210047616U (en) | 2019-04-02 | 2019-04-02 | Fixed posture adjusting device of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210047616U true CN210047616U (en) | 2020-02-11 |
Family
ID=69380069
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920435689.9U Expired - Fee Related CN210047616U (en) | 2019-04-02 | 2019-04-02 | Fixed posture adjusting device of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210047616U (en) |
-
2019
- 2019-04-02 CN CN201920435689.9U patent/CN210047616U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200211 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |