CN109703744A - A kind of unmanned plane aileron rudder face fast assembly and disassembly mechanism and assembly and disassembly methods - Google Patents
A kind of unmanned plane aileron rudder face fast assembly and disassembly mechanism and assembly and disassembly methods Download PDFInfo
- Publication number
- CN109703744A CN109703744A CN201910124887.8A CN201910124887A CN109703744A CN 109703744 A CN109703744 A CN 109703744A CN 201910124887 A CN201910124887 A CN 201910124887A CN 109703744 A CN109703744 A CN 109703744A
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- China
- Prior art keywords
- rudder face
- wing
- aileron
- fixing rib
- mounting blocks
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- 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.)
- Pending
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Abstract
The present invention relates to a kind of unmanned plane aileron rudder face fast assembly and disassembly mechanism and assembly and disassembly methods, since the mechanism that the coaxiality error of rudder face shaft in device and wing shaft has oscillating bearing to compensate designs, so that overcoming the insecure defect of control surface deflection precision, the effect that aileron rudder face accurately deflects is achieved；Since aileron rudder face both ends mounting blocks, fixture nut and self-locking nut are mounted on the design of the mechanism on wing in device, so that overcoming cumbersome dismounting defect, achieve aileron rudder face and dismount easier effect.
Description
Technical field
The invention belongs to unmanned plane fields, are related to a kind of using rib fluting modular construction aileron rudder face fast assembling-disassembling machine
Structure, in particular to a kind of unmanned plane rudder face fast assembly and disassembly mechanism and assembly and disassembly methods.
Background technique
Unmanned plane is used widely because having the characteristics that low in cost, response is rapid, task is various.Especially military
Field, unmanned plane has been applied to situation of battlefield perception, ground/air fire is guided, cannon correction shooting and damage effectiveness are commented
Estimate etc.；In civil field, unmanned plane is had been achieved in Electric Power Patrol inspection, rescue and relief work, resource exploration, environmental monitoring etc.
Industry successful application.
Design has aileron rudder face on the wing of unmanned plane, and unmanned plane relies on aileron control surface deflection in flight course, generates
Roll guidance torque, so that controlling unmanned plane realizes rolling maneuver.Existing low speed small and medium size unmanned aerial vehicles mostly use greatly a pair of of pair
Wing rudder face, there are two types of the positions that aileron rudder face is arranged on wing: the first is proximate to wing location of root, the position wing one
End opens, and installation aileron rudder face is easily achieved；The arrangement form in order to guarantee enough operating torques, the rudder face length needed compared with
It is long, meanwhile, required control surface deflection angle is also larger during rolling.It is arranged on the middle position of wing for second, such one
Come, wing at aileron rudder face installation site both ends be all it is closed, aileron rudder face is installed without operable space.Original
Design in, need to design the installation of adapter or flexible connector to realize rudder face at one end.The installation of the former aileron rudder face
If position rudder face is too small cannot to reach required rolling moment, the too big pneumatic efficiency for affecting aerofoil again of rudder face.The latter's pair
The installation site of wing rudder face, the positioning and dismounting all relatively time-consuming, manufacturing cycle and higher cost of rudder face shaft, rudder face replacement
It is time-consuming and laborious.
Summary of the invention
Technical problem solved by the present invention is reducing aileron rudder face dress in order to obtain the maximal efficiency of aileron rudder face
With positioning process workload, reduce base level maintenance time.The present invention provides a kind of easy to operate, high reliablity, Neng Goushi
The mechanism and assembly and disassembly methods of existing fast assembling-disassembling aileron rudder face.
The technical scheme is that a kind of unmanned plane aileron rudder face fast assembly and disassembly mechanism, which is characterized in that including machine
The wing, aileron rudder face, rudder face shaft, oscillating bearing, fixing rib and mounting blocks；Perpendicular type is provided at the wing rear spar of the wing to lack
Mouthful, aileron rudder face is installed on the perpendicular type indentation, there；Defining two orthogonal sides is respectively the face X and the face Y, straight in wing
Angle-style notch both ends have fixing rib to be fixed on wing rear spar along the face X, fixing rib lower surface and the cementing fixation of wing, upper surface
It is provided with strip-shaped hole；Mounting blocks are wedge shape, and lower surface is provided with semicircle orifice, and upper surface is provided with tapped through hole, and the axis of threaded hole
It is mutually perpendicular to semi-circular through hole axis；Mounting blocks are fixed in the wedge groove of fixing rib, and semicircle orifice and the face X on mounting blocks
On semicircle orifice docking, formed circular through hole；Aileron rudder face side is equipped with rudder face shaft mounting hole, rudder face shaft one end and aileron
Shaft mounting hole is connected, and the other end is inserted into oscillating bearing, in the wedge groove with mounting blocks indentation fixing rib.
A further technical solution of the present invention is: further including fixing rib locator, for the accurate positioning of fixing rib, guarantee
The concentricity of fixing rib at left and right sides of wing.
A further technical solution of the present invention is: the coaxiality error of the rudder face shaft and fixing rib by oscillating bearing into
Row compensation.
A further technical solution of the present invention is: a kind of assembly and disassembly methods of unmanned plane aileron rudder face fast assembly and disassembly mechanism,
It is characterized in that, comprising the following steps:
Installation steps are as follows:
Step 1: fixing rib, by tooling cooperation requirement, to be fixed on trailing edge always open during wing closes up
Both ends；
Step 2: pass through the cementing both ends for making rudder face shaft and oscillating bearing be fixed on aileron rudder face；
Step 3: aileron rudder face is placed on during trailing edge is directly open, and oscillating bearing is allowed to be caught in the half of fixing rib
In circular hole；
Step 4: being put into mounting blocks in the wedge groove of fixing rib and is fixed by connection bolt and self-locking nut, completes
Installation.
Demounting procedure is as follows:
Step 1: the connection bolt and self-locking nut at aileron both ends are removed using spanner, removes mounting blocks；
Step 2: removing aileron rudder face, completes disassembly.
Invention effect
The technical effects of the invention are that:
1, since the mechanism that the coaxiality error of rudder face shaft in device and wing shaft has oscillating bearing to compensate designs, make
The insecure defect of control surface deflection precision must be overcome, the effect that aileron rudder face accurately deflects is achieved；
2, due in device aileron rudder face both ends mounting blocks, fixture nut and self-locking nut be mounted on the mechanism on wing
Design achieves aileron rudder face and dismounts easier effect so that overcoming cumbersome dismounting defect.
Detailed description of the invention
Fig. 1 is installation effect figure of the invention；
Fig. 2 is disassembly process figure of the invention；
Wherein: 1-wing rear spar, 2-fixing ribs, 3-connection bolts, 4-mounting blocks, 5-aileron rudder faces, 6-self-locking
Nut, 7-wings, 8-rudder face shafts, 9-oscillating bearings.
Specific embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail.
Referring to Fig. 1-Fig. 2, a kind of unmanned plane aileron rudder face fast assembly and disassembly mechanism, including wing, wing rear spar, aileron rudder
Face, rudder face shaft, fixing rib, mounting blocks, connection bolt, self-locking nut and oscillating bearing.Fixing rib and wing rear spar pass through spiral shell
Nail is fixedly connected, and connection is glued between fixing rib lower surface and wing lower aerofoil.There are rudder face shaft mounting hole, rudders for rudder face end
Face shaft one end and the cementing connection of aileron shaft mounting hole, the other end are inserted into oscillating bearing, with the peace of mounting blocks indentation fixing rib
In tankage.Fixing rib and mounting blocks are the critical components of designed, designed, and fixing rib has wedge-shaped mounting groove, are pacified with the wedge shape of mounting blocks
It is firm that dress face is attached by screw bolt and nut.
Unmanned plane wing aileron rudder face position or so is equipped with fixing rib, passes through mounting blocks, connection bolt and self-locking spiral shell
Mother realizes the connection of aileron rudder face and wing.Wing closes up tooling equipped with fixing rib locator, for realizing the essence of fixing rib
It determines position, guarantees the concentricity of fixing rib at left and right sides of wing.The rudder face shaft mounting hole of aileron rudder face end adds essence by machine
Degree control, guarantees the accuracy of manufacture.After the installation of aileron rudder face, the coaxiality error of rudder face shaft and fixing rib by oscillating bearing into
Row compensation.Connection bolt is fixed by self-locking nut, is prevented from loosening in flight course, be fallen off, and guarantees flight safety.
It is related to a kind of unmanned plane rudder face fast assembly and disassembly mechanism, more particularly, to a kind of using rib fluting modular construction
Unmanned plane aileron rudder face fast assembly and disassembly mechanism.As shown in Fig. 2, structure of the invention includes wing rear spar 1, fixing rib 2, connection bolt
3, mounting blocks 4, aileron rudder face 5, self-locking nut 6, wing 7, rudder face shaft 8, oscillating bearing 9.There are bolts for 2 end face of fixing rib
4 card slot of hole, 9 mounting groove of oscillating bearing and mounting blocks, screw hole realize that fixing rib 2 is connected with the screw of wing rear spar 1.Aileron
Rudder face shaft mounting hole is arranged in the end face of rudder face 5, for realizing the connection of aileron rudder face 5 Yu rudder face shaft 8.Outside rudder face shaft 8
There is step on surface, for installing oscillating bearing 9.Mounting blocks 4 are used to fix aileron rudder face 5 and the connection of wing 7 is integral, and
It is fixed by connection bolt 3 and self-locking nut 6.
The installation process of aileron rudder face fast assembly and disassembly mechanism is as follows: oscillating bearing 9 being inserted in the two of rudder face upper shaft 8 first
End, is placed on oscillating bearing 8 and rudder face 5 in 2 card slot of fixing rib, and mounting blocks 4 are finally passed through connection bolt 3 and self-locking
Nut 6 is connected and fixed, and completes installation.
The disassembly process of aileron rudder face fast assembly and disassembly mechanism is as follows: first with 3 He of connection bolt for removing aileron both ends
Then self-locking nut 6 removes mounting blocks 4, finally take out aileron rudder face 5, completes disassembly.
Above embodiment of the invention is not construed as to limitation made by the claims in the present invention, if this field
The inspiration of technical staff through the invention does not need creative labor and makes corresponding variation, shall fall within right of the present invention
It is required that protection scope in.
Claims (4)
1. a kind of unmanned plane aileron rudder face fast assembly and disassembly mechanism, which is characterized in that including wing (7), aileron rudder face (5), rudder face
Shaft (8), oscillating bearing (9), fixing rib (2) and mounting blocks (4)；Perpendicular type is provided at the wing rear spar of the wing (7) to lack
Mouthful, aileron rudder face (5) is installed on the perpendicular type indentation, there；Defining two orthogonal sides is respectively the face X and the face Y, in machine
Wing perpendicular type notch both ends have fixing rib (2) to be fixed on wing rear spar (1) along the face X, fixing rib (2) lower surface and wing
(7) cementing fixation, upper surface are provided with strip-shaped hole；Mounting blocks (4) are wedge shape, and lower surface is provided with semicircle orifice, and upper surface is provided with spiral shell
Line through-hole, and the axis of threaded hole is mutually perpendicular to semi-circular through hole axis；Mounting blocks are fixed on the wedge groove of fixing rib (2)
In, and the semicircle orifice docking on the semicircle orifice and the face X on mounting blocks, form circular through hole；Aileron rudder face (5) side is equipped with rudder face
Shaft mounting hole, rudder face shaft one end and aileron shaft mounting hole are connected, and the other end is inserted into oscillating bearing (9), with mounting blocks (4)
It is pressed into the wedge groove of fixing rib (2).
2. a kind of unmanned plane aileron rudder face fast assembly and disassembly mechanism as described in claim 1, which is characterized in that further include fixing rib
Locator guarantees the concentricity of fixing rib at left and right sides of wing for the accurate positioning of fixing rib.
3. a kind of unmanned plane aileron rudder face fast assembly and disassembly mechanism as described in claim 1, which is characterized in that the rudder face shaft
(8) it is compensated with the coaxiality error of fixing rib (2) by oscillating bearing (9).
4. based on a kind of assembly and disassembly methods of unmanned plane aileron rudder face fast assembly and disassembly mechanism described in claim 1, which is characterized in that
The following steps are included:
Installation steps are as follows:
Step 1: fixing rib (2) is fixed on wing (7) rear right angle by tooling cooperation requirement during wing closes up and is opened
The both ends of mouth；
Step 2: rudder face shaft (8) and oscillating bearing (9) is made to be fixed on the both ends of aileron rudder face (5) by cementing；
Step 3: aileron rudder face (5) is placed on during wing (7) rear is directly open, and oscillating bearing (9) is allowed to be caught in fixing rib
(2) in semicircle orifice；
Step 4: being put into mounting blocks (4) in the wedge groove of fixing rib (2) and solid by connection bolt (3) and self-locking nut (6)
It is fixed, complete installation.
Demounting procedure is as follows:
Step 1: the connection bolt (3) and self-locking nut (6) at aileron both ends are removed using spanner, removes mounting blocks (4)；
Step 2: removing aileron rudder face (5), completes disassembly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910124887.8A CN109703744A (en) | 2019-02-20 | 2019-02-20 | A kind of unmanned plane aileron rudder face fast assembly and disassembly mechanism and assembly and disassembly methods |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910124887.8A CN109703744A (en) | 2019-02-20 | 2019-02-20 | A kind of unmanned plane aileron rudder face fast assembly and disassembly mechanism and assembly and disassembly methods |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109703744A true CN109703744A (en) | 2019-05-03 |
Family
ID=66264643
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910124887.8A Pending CN109703744A (en) | 2019-02-20 | 2019-02-20 | A kind of unmanned plane aileron rudder face fast assembly and disassembly mechanism and assembly and disassembly methods |
Country Status (1)
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| CN (1) | CN109703744A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112520010A (en) * | 2020-12-14 | 2021-03-19 | 中宇航通(北京)航空集团有限公司 | Unmanned aerial vehicle body tail connection locking device and method |
| CN113492967A (en) * | 2021-07-23 | 2021-10-12 | 航天时代飞鹏有限公司 | Device and method for quickly disassembling steering engine of freight unmanned aerial vehicle |
| CN114750931A (en) * | 2022-04-14 | 2022-07-15 | 中国空气动力研究与发展中心空天技术研究所 | Front flap rudder surface structure of unmanned aerial vehicle |
| CN114942000A (en) * | 2022-07-13 | 2022-08-26 | 成都国营锦江机器厂 | Detection and calibration method for tail transmission shaft of helicopter |
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| CN108082449A (en) * | 2018-03-06 | 2018-05-29 | 中航通飞研究院有限公司 | A kind of large aircraft control surface suspension structure |
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| CN109080814A (en) * | 2018-09-30 | 2018-12-25 | 西安爱生技术集团公司 | A kind of full-height foam core unmanned plane lifting rudder face shaft installing mechanism |
| CN208429234U (en) * | 2018-06-25 | 2019-01-25 | 深圳市大疆创新科技有限公司 | Fixed-wing unmanned plane and its empennage |
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| US20090127406A1 (en) * | 2007-11-15 | 2009-05-21 | Airbus Uk Limited | Aileron actuator bracket |
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| CN108082449A (en) * | 2018-03-06 | 2018-05-29 | 中航通飞研究院有限公司 | A kind of large aircraft control surface suspension structure |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112520010A (en) * | 2020-12-14 | 2021-03-19 | 中宇航通(北京)航空集团有限公司 | Unmanned aerial vehicle body tail connection locking device and method |
| CN113492967A (en) * | 2021-07-23 | 2021-10-12 | 航天时代飞鹏有限公司 | Device and method for quickly disassembling steering engine of freight unmanned aerial vehicle |
| CN113492967B (en) * | 2021-07-23 | 2023-02-17 | 航天时代飞鹏有限公司 | Freight unmanned aerial vehicle steering engine quick-release device and method |
| CN114750931A (en) * | 2022-04-14 | 2022-07-15 | 中国空气动力研究与发展中心空天技术研究所 | Front flap rudder surface structure of unmanned aerial vehicle |
| CN114942000A (en) * | 2022-07-13 | 2022-08-26 | 成都国营锦江机器厂 | Detection and calibration method for tail transmission shaft of helicopter |
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Application publication date: 20190503 |