CN204173159U - A kind of direction-variable power device realizing the vertical landing of existing unmanned aerial vehicle - Google Patents
A kind of direction-variable power device realizing the vertical landing of existing unmanned aerial vehicle Download PDFInfo
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- CN204173159U CN204173159U CN201420339903.8U CN201420339903U CN204173159U CN 204173159 U CN204173159 U CN 204173159U CN 201420339903 U CN201420339903 U CN 201420339903U CN 204173159 U CN204173159 U CN 204173159U
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Abstract
A kind of direction-variable power device realizing the vertical landing of existing unmanned aerial vehicle: for existing unmanned aerial vehicle, need booster rocket, runway, tailstock realizes taking off, parachute, barrier, runway, the deficiency of tailstock landing, the utility model proposes direction-variable power device, overcome existing unmanned aerial vehicle to take off above shortcomings in descent, it is by steering base, pitman arm forms, after driving engine installs direction-variable power device additional, driving engine is made to be provided with vector Power output function, existing unmanned aerial vehicle is made to take off except landing modes except traditional, also there is being pulled up to head by horizontality of unmanned aerial vehicle body, realize vertical takeoff, vertical drop, break away from and needed airport, rocket, tailstock, take off, parachute, barrier, traditional landing mode of tailstock landing, it is made to expand range of use, enhance practicality and comformability.
Description
Technical field:
The utility model relates to the unmanned aerial vehicle in aviation field, and what be specifically related to is a kind of direction-variable power device realizing the vertical landing of existing unmanned aerial vehicle.
Background technology:
When the unmanned aerial vehicle of current use takes off, the unmanned aerial vehicle of micro volume adopts hand throwing type takeoff method, the unmanned aerial vehicle of larger volume, adopt track to add rocket assist to realize and take off, large-scale unmanned aerial vehicle needs runway to realize to take off, and adopts hurdle to cut net during landing, parachute, runway realizes landing, and this landing method that takes off brings much inconvenience to the use of unmanned plane, also limit the range of use of unmanned aerial vehicle.
These taking off that landing exists for unmanned aerial vehicle are not enough, vd200 tailstock formula unmanned plane, (Air China's industry Chengdu developed) it is the tailstock utilizing afterbody, make body be in nose-high and become vertical state, propeller pull-up body realizes vertical takeoff, after reaching certain speed, level off body utilizing the deflection of aileron and realize flat flying, by propeller pull-up head during landing, then at its pulling force of minimizing, body is slowly the declined landing until its tailstock has landed, to control the direction controlling that two-engined speed discrepancy and wing rudder realize in vertical landing process.
Unmanned plane before A seating unmanned plane really can overcome takes off the some shortcomings of landing aspect, but it is weak also to there is maneuverability in vertical landing process, by geographical conditions, wind-force is to vertical state lower body stability influence, tailstock structure volume, weight, the deficiency that empty resistance is larger.
Utility model content:
Object
The purpose of this utility model, be to provide a kind of direction-variable power device realizing the vertical landing of existing unmanned aerial vehicle, solve maneuverability in tailstock formula unmanned aerial vehicle vertical landing process weak, tailstock structure volume, weight, empty resistance is larger, with the needs of existing unmanned aerial vehicle by external force, runway realizes taking off, and needs barrier, parachute, the problem of runway landing.
The solution of problem is achieved through the following technical solutions:
A kind of direction-variable power device realizing the vertical landing of existing unmanned aerial vehicle, composition comprises: steering base, pitman arm, described engine power axle connects steering base, described steering base connects common axis, described common axis closure arm, described steering base connects steering gear worm, described steering gear worm connecting worm and motor, described worm screw and motor connecting engine, described pitman arm connects the worm gear that verts, described vert worm gear connecting worm and motor, and described worm screw and motor connect steering base.
Described a kind of direction-variable power device realizing the vertical landing of existing unmanned aerial vehicle, described common axis connects the excessive elevating arc of power, the excessive elevating arc of described power is while connect power input elevating arc, described power input elevating arc connecting engine dynamical axis, the excessive elevating arc another side of described power connects Power output elevating arc, described Power output elevating arc connects power take-off shaft, described power take-off shaft closure arm, and described power take-off shaft mouth connects propeller.
Utility model principle of work:
1, direction-variable power device is contained on engine power axle, by steering base rotating centered by its axle, connection can relatively steering base vert pitman arm composition, engine power is through fan gear cluster, power take-off shaft passes to propeller, pitman arm interlock propeller is verted and can be produced unidirectional vector power, again due to the rotation of steering base interlock pitman arm, the existing unidirectional vector power that propeller is produced, vector pulling force or the thrust of different azimuth is produced in 360 degree of relative spaces, thus realize doing process by directed Power output to the work of vector Power output.
Beneficial effect:
1, the utility model proposes, install direction-variable power device structure on the engine additional, make existing unmanned aerial vehicle, do not need tailstock structure, by external force, runway takes off.Barrier, parachute, tailstock, runway lands.
2, the utility model proposes, install direction-variable power device structure on the engine additional, do not need to make body become vertical state, therefore be not subject to geographical wind-force on the impact of holding up organism stability, there is aerial vertically hovering, can to any direction vertically movement, accommodative ability of environment is strong, range of use is large, can realize vertical landing on narrow and small place and the middle-size and small-size warship in moving.
3, the utility model proposes, the composite entity of driving engine and direction-variable power device, the commercial production of practicable standardised series.
Accompanying drawing illustrates:
Accompanying drawing 1 is direction-variable power device structural representation.
Detailed description of the invention:
Implementation column 1:
A kind of direction-variable power device realizing the vertical landing of existing unmanned aerial vehicle, composition comprises: steering base 2, pitman arm 3, described driving engine 10 dynamical axis 9 connects steering base 2, described steering base 2 connects common axis 4, described common axis 4 closure arm 3, described steering base 2 connects steering gear worm 11, described steering gear worm 11 connecting worm 12 and the worm screw 12 described in motor 13 and motor 13 connecting engine 10, described pitman arm 3 connects the worm gear 14 that verts, described vert worm gear 14 connecting worm 15 and motor 16, described worm screw 15 and motor 16 connect steering base 2.
Implementation column 2:
A kind of direction-variable power device realizing the vertical landing of existing unmanned aerial vehicle described in implementation column 1, described common axis 4, connect the excessive elevating arc 5 of power, the excessive elevating arc 5 of described power, while connect power input elevating arc 6, described power input elevating arc 6 connecting engine dynamical axis 9, described power excessive elevating arc 5 another side connects Power output elevating arc 7, described Power output elevating arc 7 connects power take-off shaft 8, described power take-off shaft 8 closure arm 3, described power take-off shaft 8 mouth connects propeller 17.
Utility model principle of work:
1, direction-variable power device 1 is contained on engine power axle 9, by steering base 2 rotary centered by its axle, connection can steering base 2 verts relatively pitman arm 3 form, driving engine 10 power is through fan gear 5, 6, 7 power take-off shafts 8 pass to propeller 17, verting of pitman arm 3 interlock propeller 17 can produce unidirectional vector power, again due to the rotation of steering base 2 interlock pitman arm 3, the existing unidirectional vector power that propeller 17 is produced, vector pulling force or the thrust of different azimuth is produced at the spaces of 360 degree, thus realize doing process by directed Power output to the work of vector Power output.
Claims (2)
1. one kind realizes the direction-variable power device of the vertical landing of existing unmanned aerial vehicle, composition comprises: steering base, pitman arm, it is characterized in that: engine power axle connects steering base, described steering base connects common axis, described common axis connects pitman arm, described steering base connects steering gear worm connecting worm described in steering gear worm and motor, described worm screw and motor connecting engine, described pitman arm connects the worm gear that verts, described vert worm gear connecting worm and motor, described endless screw electric motor connects steering base.
2. a kind of direction-variable power device realizing the vertical landing of existing unmanned aerial vehicle according to claim 1, it is characterized in that: described common axis, described common axis connects the excessive elevating arc of power, the excessive elevating arc of described power is while connect power input elevating arc, described power input elevating arc connecting engine dynamical axis, the excessive elevating arc another side of described power connects Power output elevating arc, described Power output elevating arc connects power take-off shaft, described power take-off shaft closure arm, described power take-off shaft mouth connects propeller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420339903.8U CN204173159U (en) | 2014-06-24 | 2014-06-24 | A kind of direction-variable power device realizing the vertical landing of existing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420339903.8U CN204173159U (en) | 2014-06-24 | 2014-06-24 | A kind of direction-variable power device realizing the vertical landing of existing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204173159U true CN204173159U (en) | 2015-02-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420339903.8U Expired - Fee Related CN204173159U (en) | 2014-06-24 | 2014-06-24 | A kind of direction-variable power device realizing the vertical landing of existing unmanned aerial vehicle |
Country Status (1)
| Country | Link |
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| CN (1) | CN204173159U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106275424A (en) * | 2015-05-18 | 2017-01-04 | 王泽民 | A kind of inclining rotary mechanism and a kind of sealing mechanism |
-
2014
- 2014-06-24 CN CN201420339903.8U patent/CN204173159U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106275424A (en) * | 2015-05-18 | 2017-01-04 | 王泽民 | A kind of inclining rotary mechanism and a kind of sealing mechanism |
| CN106275424B (en) * | 2015-05-18 | 2020-01-21 | 王泽民 | Rotor wing tilting mechanism and belt type sealing mechanism for rotor wing tilting mechanism |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150225 Termination date: 20190624 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |