CN108263595A - A kind of small drone wing installing mechanism - Google Patents
A kind of small drone wing installing mechanism Download PDFInfo
- Publication number
- CN108263595A CN108263595A CN201711445394.1A CN201711445394A CN108263595A CN 108263595 A CN108263595 A CN 108263595A CN 201711445394 A CN201711445394 A CN 201711445394A CN 108263595 A CN108263595 A CN 108263595A
- Authority
- CN
- China
- Prior art keywords
- wing
- guide rail
- sliding block
- installing plate
- small drone
- 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.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
Abstract
A kind of small drone wing installing mechanism, including installing plate, wing mounting base, guide rail and screw slider driving mechanism, the installing plate is the square plate with strip groove, and it is parallel with unmanned aerial vehicle body axis by the central axes of groove and in same vertical plane in a manner of be mounted on airframe top, two guide rails are parallelly mounted on strip groove both sides along groove length direction, screw slider driving mechanism is mounted on the installing plate, and coordinate with the guide rail and assemble, the wing mounting base is mounted on the screw slider, it can be under the action of the screw slider driving mechanism, wing mounted thereto is driven to move along a straight line on guide rail with sliding block.The configuration of the present invention is simple is reliable, control is simple and efficient, is rationally distributed, occupying little space, precision is high.
Description
Technical field
The invention belongs to vehicle technology fields, and in particular to one kind is suitable for the displacement of small drone wing, limiting, lock
The structure design of dead installing mechanism.
Background technology
With the development of the new and high technologies such as microelectronics, computer, automatic Pilot, artificial intelligence.So that small drone obtains
Quick comprehensive development is arrived.Small drone field is quickly grown at present, can be carried out with mission requirements and designed, complete various
Business.
With the multifarious development of unmanned plane task, demand is proposed to the aerial variant of small drone.Common position
It moves drive form and elastic potential energy is mainly converted into the side of mechanical energy using using energy storing structure (such as spring, elastic rubber)
Formula, and then drive the movement of the positions such as unmanned plane wing, body.Major defect in this way is：The drive of elastic material
Power is related with material deformation, more apparent for the variation of power during big travel displacement, moving end driving force reduce and
There are larger impacts in place.Simultaneously because end elastic force reduces, it is therefore desirable to additional designs locking mechanism.Increase mechanism
Complexity.
Invention content
Present invention solves the technical problem that it is：A kind of wing of small drone is overcome the deficiencies of the prior art and provide
Displacement mechanism can steadily realize the displacement, limiting and locked function for carrying out wing automatically in the air in unmanned plane.
The present invention technical solution be：A kind of small drone wing installing mechanism is installed including installing plate, wing
Seat, guide rail and screw slider driving mechanism, the installing plate are the square plates with strip groove, and with the central axes of groove with
Unmanned aerial vehicle body axis is parallel and mode in same vertical plane is mounted on the top of airframe, two guide rails along
Groove length direction is parallelly mounted on strip groove both sides, and screw slider driving mechanism is mounted on the installing plate, and with
The guide rail cooperation assembling, the wing mounting base is mounted on the screw slider, in the screw slider driving mechanism
Under effect, wing mounted thereto is driven to move along a straight line on guide rail with sliding block.
It is preferred that the screw slider driving mechanism includes steering engine, leading screw and sliding block, the steering engine is the one of the guide rail
End is mounted on the installing plate, between the leading screw is assemblied in two guide rails along the central axes of two guide rails, screw thread installation
Sliding block on the leading screw is fitted on two guide rails.
It is preferred that the end set limit switches of the separate steering engine in the guide rail, when the sliding block slides into the limiting
When at switch, by touching the limit switch, the steering engine power-off is made to stop operating, and pass through the leading screw lock slider,
So as to reach position-limiting action.
It is preferred that the installing plate is directly replaced using fuselage, the groove is directly opened in the top of fuselage.
It is preferred that the steering engine turns servo driving using 360 ° of companies of PWM pulsewidth modulations square wave control, output torque is
0.2N·m。
It is preferred that the stroke of the sliding block is 90mm.
The advantages of the present invention over the prior art are that：
1st, the present invention is based on the aerial variant demands of unmanned plane, it is proposed that the wing tail mechanism based on screw slide, profit
With the principle of lead screw transmission, by controlling the rotation angle of steering engine, rotational motion is converted into the linear motion of sliding block, with routine
Spring does flowing mode and compares, and screw slide has good kinetic stability, simple in structure and have latching characteristics.
2nd, the present invention uses miniature screw slider mechanism, has the characteristics of large transmission ratio is laborsaving, reduces to driving steering engine
Torque requirement.Simultaneously because the latching characteristics of leading screw, does not need to add additional locking mechanism, simplifies the complexity of structure
Property, it improves reliability and ensures enough positioning accuracy.
3rd, the axial extension layout of screw slider of the present invention and the longitudinal direction of small-sized steering machine and limit switch are laid out, can
It is preferable to save space, and velocity of displacement can design as needed with shift length, can control in the ideal range.
Description of the drawings
Fig. 1 is wing displacement mechanism internal structure chart
Fig. 2 is the external structure of wing displacement mechanism
In attached drawing：1-movable wings, 2-positive coupling, 3-fuselage, 4-steering engine, 5-sliding block, 6-guide rail, 7-
Leading screw, 8-limit switch, 9-wing mounting base.
Specific embodiment
Fig. 1 is wing installing mechanism internal structure chart, is come about machine 4, positive coupling including the company in wing displacement mechanism
2nd, leading screw 7, guide rail 6, limit switch 8, fuselage mounting surface 3, sliding block 5 and wing 1.It can be seen from the figure that leading screw 7 and rudder
Machine 4 is connected by positive coupling 2, and passes through sliding block 5.Sliding block 5 can move in guide rail 6, while sliding block 5 is installed with wing
Seat 9 is connected.Rotary motion is passed when steering engine 4 rotates and is changed to linear motion, so as to which wing 1 be driven to be moved axially along fuselage 3.Machine
The wing 1 is mounted on by wing mounting base 9 on sliding block 5.
Fig. 2 locks figure in place for displacement mechanism, and rotation driving sliding block 5 reaches design position after steering engine 4 receives pwm signal
It postpones, sliding block 5 contacts limit switch 8, is closed limit switch 8, and cut-out steering engine 4, which is powered, reaches the mesh of command displacement mechanism stopping
's.
The steering engine of the present invention is that small-sized 360 ° of companies of a PWM pulsewidth modulations square wave control turn servo driving.Steering engine weight
9g, output torque 0.2Nm.Leading screw top is supported by a miniature deep groove ball bearing, and the other end is fixed on by shaft coupling
On steering engine output shaft.Steering engine drives leading screw to rotate by a positive coupling, then is turned the rotational motion of leading screw by slide unit
The linear motion along lead screw guide rails is turned to, achievees the purpose that mobile wing position.Wing mounting base, which is through on leading screw, plays sliding block work
With, and pass through leading screw guide groove and be axially moved along fuselage.Meanwhile there is guide rail to be used for limiting wing mounting base week on screw slide pedestal
Fuselage is passed to movement, and by aerodynamic force suffered by wing.Slider stroke is 90mm.When reaching design position, sliding block touches
Limit switch, driving steering engine power-off stalling.
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.
Claims (6)
1. a kind of small drone wing installing mechanism, it is characterised in that：Including installing plate, wing mounting base, guide rail and leading screw
Slider-actuated mechanism, the installing plate are the square plates with strip groove, and with the central axes of groove and unmanned aerial vehicle body axis
Line is parallel and mode in same vertical plane is mounted on the top of airframe, and two guide rails are along groove length direction
Strip groove both sides are parallelly mounted on, screw slider driving mechanism is mounted on the installing plate, and is coordinated with the guide rail
Assembling, the wing mounting base is mounted on the screw slider, under the action of the screw slider driving mechanism, drives peace
Mounted in wing thereon as sliding block moves along a straight line on guide rail.
2. a kind of small drone wing installing mechanism according to claim 1, it is characterised in that：The screw slider
Driving mechanism includes steering engine, leading screw and sliding block, and the steering engine is mounted in one end of the guide rail on the installing plate, the silk
Between thick stick is assemblied in two guide rails along the central axes of two guide rails, the sliding block being threadably mounted on the leading screw is fitted to
On two guide rails.
3. a kind of small drone wing installing mechanism according to claim 2, it is characterised in that：In the remote of the guide rail
End set limit switches from steering engine, when the sliding block is slided at the limit switch, by touching the limiting
Switch makes the steering engine power-off stop operating, and pass through the leading screw lock slider, so as to reach position-limiting action.
4. a kind of small drone wing installing mechanism according to any one of claim 1-3, it is characterised in that：It is described
Installing plate directly replaced using fuselage, the groove is directly opened in the top of fuselage.
5. a kind of small drone wing installing mechanism according to claim 1, it is characterised in that：The steering engine uses
360 ° of companies of PWM pulsewidth modulations square wave control turn servo driving, output torque 0.2Nm.
6. a kind of small drone wing installing mechanism according to claim 1, it is characterised in that：The stroke of the sliding block
For 90mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711445394.1A CN108263595A (en) | 2017-12-27 | 2017-12-27 | A kind of small drone wing installing mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711445394.1A CN108263595A (en) | 2017-12-27 | 2017-12-27 | A kind of small drone wing installing mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108263595A true CN108263595A (en) | 2018-07-10 |
Family
ID=62772818
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711445394.1A Pending CN108263595A (en) | 2017-12-27 | 2017-12-27 | A kind of small drone wing installing mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108263595A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108919674A (en) * | 2018-08-14 | 2018-11-30 | 正德职业技术学院 | UAV Flight Control analogue system |
| CN109263858A (en) * | 2018-10-30 | 2019-01-25 | 彩虹无人机科技有限公司 | A kind of coaxial wingfold mechanism |
| CN111003142A (en) * | 2019-12-25 | 2020-04-14 | 中国航空工业集团公司西安飞机设计研究所 | Flexible connecting device for wing body |
Citations (6)
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|---|---|---|---|---|
| JPH02161300A (en) * | 1988-12-15 | 1990-06-21 | Mitsubishi Electric Corp | Guided missile |
| JPH02219996A (en) * | 1989-02-22 | 1990-09-03 | Mitsubishi Electric Corp | Steering device for guided missiles |
| CN202213714U (en) * | 2011-09-02 | 2012-05-09 | 北京航空航天大学 | Supporting mechanism for trailing edge flap high lift device |
| CN105620720A (en) * | 2016-03-17 | 2016-06-01 | 舒丹丹 | Aerial photography folding wing unmanned aerial vehicle |
| CN105923158A (en) * | 2016-04-23 | 2016-09-07 | 董昕武 | Folding wing unmanned plane for municipal landscaping |
| CN206634198U (en) * | 2017-03-09 | 2017-11-14 | 北京天宇新超航空科技有限公司 | A kind of inclining rotary mechanism for tiltrotor |
-
2017
- 2017-12-27 CN CN201711445394.1A patent/CN108263595A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH02161300A (en) * | 1988-12-15 | 1990-06-21 | Mitsubishi Electric Corp | Guided missile |
| JPH02219996A (en) * | 1989-02-22 | 1990-09-03 | Mitsubishi Electric Corp | Steering device for guided missiles |
| CN202213714U (en) * | 2011-09-02 | 2012-05-09 | 北京航空航天大学 | Supporting mechanism for trailing edge flap high lift device |
| CN105620720A (en) * | 2016-03-17 | 2016-06-01 | 舒丹丹 | Aerial photography folding wing unmanned aerial vehicle |
| CN105923158A (en) * | 2016-04-23 | 2016-09-07 | 董昕武 | Folding wing unmanned plane for municipal landscaping |
| CN206634198U (en) * | 2017-03-09 | 2017-11-14 | 北京天宇新超航空科技有限公司 | A kind of inclining rotary mechanism for tiltrotor |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108919674A (en) * | 2018-08-14 | 2018-11-30 | 正德职业技术学院 | UAV Flight Control analogue system |
| CN109263858A (en) * | 2018-10-30 | 2019-01-25 | 彩虹无人机科技有限公司 | A kind of coaxial wingfold mechanism |
| CN111003142A (en) * | 2019-12-25 | 2020-04-14 | 中国航空工业集团公司西安飞机设计研究所 | Flexible connecting device for wing body |
| CN111003142B (en) * | 2019-12-25 | 2022-08-19 | 中国航空工业集团公司西安飞机设计研究所 | Flexible connecting device for wing body |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180710 |