CN206307262U - A kind of VUAV undercarriage - Google Patents
A kind of VUAV undercarriage Download PDFInfo
- Publication number
- CN206307262U CN206307262U CN201621409821.1U CN201621409821U CN206307262U CN 206307262 U CN206307262 U CN 206307262U CN 201621409821 U CN201621409821 U CN 201621409821U CN 206307262 U CN206307262 U CN 206307262U
- Authority
- CN
- China
- Prior art keywords
- undercarriage
- vuav
- high rigidity
- support
- utility
- 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
Links
Landscapes
- Buffer Packaging (AREA)
Abstract
The utility model discloses a kind of VUAV undercarriage, the unmanned plane undercarriage includes former and later two single undercarriages, and a single undercarriage includes：Support；Two hassock pieces；Lower link；Two high rigidity springs；Upper link.VUAV is during VTOL, the undercarriage constitutes 4 points of supports and is used for balancing VTOL stage undercarriage with ground or ship deck in the presence of longitudinal pitching moment when contacting, horizontal lateral tilting moment is buffered by the spring between undercarriage, rollover is prevented.Landing gear structure of the present utility model is simple, and convenient disassembly, quality is small, meets that unmanned plane undercarriage weight is small, and intensity is high, stationarity requirement high, has ensured the safety of unmanned plane.The VUAV undercarriage solve well VUAV take off landing security and undercarriage preserve permanent sex chromosome mosaicism.
Description
Technical field
The utility model is related to unmanned air vehicle technique field, particularly a kind of undercarriage of VUAV.
Background technology
Mostly by the way of the bar of both sides two, this common structure disclosure satisfy that small domestic rotor wing unmanned aerial vehicle undercarriage substantially
The takeoff and landing performance requirement of type multi-rotor unmanned aerial vehicle, but have that structure is single, support strength is poor, the problem of stability difference, easily sends out
Incline before death and turn on one's side.
Fixed-wing VUAV, take-off weight is big, and the carrying of undercarriage and holding aircraft are stablized during landing
Performance requirement is higher.Particularly in landing bad environments（Such as naval vessel landing）In the case of, the possibility that unmanned plane is turned on one's side
Property greatly increase, urgent need want a kind of simple structure unmanned plane undercarriage ensure unmanned plane landing stationarity（Refer mainly to rise and fall
The stage aircraft of the contact such as frame and ground or deck receives the stability after horizontal side interference）And security.
Utility model content
For above mentioned problem of the prior art, the utility model provides a kind of rising suitable for VUAV
Fall frame, for solving the problems, such as existing unmanned plane VTOL stationarity and security.
To achieve the above object, the utility model provides a kind of VUAV undercarriage, the VTOL
Unmanned plane undercarriage includes former and later two single undercarriages, and two undercarriages are along distribution before and after VUAV fuselage longitudinal direction.
One single undercarriage includes：Support；Hassock piece, the hassock piece is two；Lower link；High rigidity spring, the high rigidity
Spring is two；Upper link.
During VTOL, the undercarriage constitutes 4 points of supports and is used for providing aircraft the VUAV
The support reaction and torque when on the ground are parked, by the way that the high rigidity spring between undercarriage is come the buffering vertical landing stage or stops
Tilting moment when body is by horizontal side interference when putting ground, prevents rollover.
Preferably, the support is π shape supports, and former and later two supports constitute double π shapes.
Preferably, the support and lower link are fastened by bolt and hassock piece, and upper link and fuselage are connected, convenient
Quick Release.
Preferably, the lower link and upper link are connected by bearing pin and two high rigidity springs.
Preferably, the high rigidity spring is placed on rotating shaft both sides and symmetrically locates, undercarriage not load when, high rigidity spring is equal
It is convenient to install in free state.
Preferably, the frame body that rises and falls is using full carbon fiber composite structure.
The beneficial effect of the utility model VUAV：The VUAV landing gear structure is simple, side
Just dismount, it is ensured that flat when VUAV is parked under the adverse circumstances such as certain uneven face or naval vessel
Stability and security.Full carbon fiber structural, anticorrosion Defend salt fog is used to be suitable as small-sized carrier-borne VUAV simultaneously
Undercarriage.Preferably solve the stationarity that take off landing of the fixed-wing VUAV under complicated landing environment is parked
And safety issue.
Brief description of the drawings
Fig. 1 is the structural representation of the VUAV undercarriage according to the utility model first embodiment.
Fig. 2 is the front view of the VUAV undercarriage according to the utility model first embodiment.
Figure acceptance of the bid note is respectively：1st, support；2nd, hassock piece；3rd, lower link；4th, high rigidity spring；5th, upper link.
Specific embodiment
For the purpose, technical scheme and advantage for implementing the utility model are clearer, below in conjunction with the utility model
Accompanying drawing in embodiment, is further described in more detail to the technical scheme in the utility model embodiment.Described implementation
Example is a part of embodiment of the utility model, rather than whole embodiments.Embodiment below with reference to Description of Drawings is
Exemplary, it is intended to for explaining the utility model, and it is not intended that to limitation of the present utility model.Based on the utility model
In embodiment, the every other implementation that those of ordinary skill in the art are obtained under the premise of creative work is not made
Example, belongs to the scope of the utility model protection.Embodiment of the present utility model is described in detail below in conjunction with the accompanying drawings.
As shown in Fig. 1 Fig. 2, the unmanned plane undercarriage that the present embodiment is provided includes former and later two single undercarriages, and two are risen and fallen
Frame is symmetrical before and after VUAV fuselage direction.One single undercarriage includes：Support 1；Hassock piece 2, hassock piece 2
It is two；Lower link 3；High rigidity spring 4, high rigidity spring 4 is two；Upper link 5.
During VTOL, the undercarriage constitutes 4 points of supports and is used for balancing vertically the VUAV
Landing stage longitudinal direction pitching moment, tilting moment is buffered by the high rigidity spring between undercarriage, prevents rollover.
In the present embodiment, support is π shape supports, and former and later two supports constitute double π shapes.
In the present embodiment, support and lower link are fastened by bolt and hassock piece, and upper link and fuselage are connected, side
Just Quick Release.
In the present embodiment, lower link and upper link are connected by bearing pin and two high rigidity springs.
In the present embodiment, high rigidity spring is placed on rotating shaft both sides and symmetrically locates, undercarriage not load when, high rigidity spring
It is in free state.High rigidity spring is in regime of elastic deformation, and compression or stroke are linear with stand under load, no matter high
The original state of rigid spring is compression, freedom or elongation state, aircraft three kinds of state high rigidity bullets in the case of microvariations
The righting moment that spring is provided is the same, and free state is convenient to be installed.
In the present embodiment, undercarriage uses full carbon fiber structural.It is understood that above-mentioned is only one embodiment
In situation, the material of the unmanned plane undercarriage of the application can sets itself as needed.For example, using titanium alloy or
Aircraft aluminum.
Using the beneficial effect of above scheme：Because undercarriage constitutes 4 points of supports, support strength is high, and stationarity is good, can be with
There is provided support reaction and equalising torque VTOL stage undercarriage contact with ground and fly to control regulating power it is limited when longitudinal direction pitching
Torque, and tilting moment is buffered by the high rigidity spring in undercarriage, prevent rollover.Undercarriage uses anticorrosion Defend salt fog
Carbon fiber structural, especially solve Shipborne UAV take off landing security and undercarriage preserve permanent sex chromosome mosaicism.
Landing gear structure is simple, and convenient disassembly, quality is small, meets that unmanned plane undercarriage weight is small, and intensity is high, stationarity it is high will
Ask, ensured the safety of unmanned plane.
Above example is only used to further describe the technical solution of the utility model, it is impossible to assert the utility model
Specific embodiment be confined to these explanations.For the utility model person of an ordinary skill in the technical field,
The other embodiment drawn in the case where the technical solution of the utility model is not departed from, should be included in protection model of the present utility model
In enclosing.
Claims (6)
1. a kind of VUAV undercarriage, it is characterised in that the VUAV undercarriage include before and after two
Individual single undercarriage, two undercarriages are distributed along before and after the y direction of VUAV；
Single undercarriage includes：Support（1）；Hassock piece（2）, the hassock piece（2）It is two；Lower link（3）；High rigidity bullet
Spring（4）, the high rigidity spring（4）It is two；Upper link（5）；
During VTOL, the undercarriage constitutes 4 points of supports and is parked for providing aircraft the VUAV
Support reaction and torque when on the ground, by the way that the high rigidity spring between undercarriage is come the buffering vertical landing stage or parks ground
Tilting moment when body is by horizontal side interference during face, prevents rollover.
2. VUAV undercarriage according to claim 1, it is characterised in that the support（1）It is π shape branch
Frame, former and later two supports constitute double π shapes.
3. VUAV undercarriage according to claim 2, it is characterised in that the support（1）With lower connection
Frame（3）By screw and hassock piece（2）Connection, upper link（5）With fuselage connection, facilitate Quick Release.
4. VUAV undercarriage according to claim 3, it is characterised in that lower link（3）With upper connection
Frame（5）By bearing pin and two high rigidity springs（4）Connection.
5. VUAV undercarriage according to claim 4, it is characterised in that high rigidity spring（4）It is placed on
Rotating shaft both sides are symmetrically located, undercarriage not load when, high rigidity spring is in drift.
6. VUAV undercarriage according to claim 5, it is characterised in that the frame body that rises and falls is fine using full carbon
Dimension composite structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621409821.1U CN206307262U (en) | 2016-12-21 | 2016-12-21 | A kind of VUAV undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621409821.1U CN206307262U (en) | 2016-12-21 | 2016-12-21 | A kind of VUAV undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206307262U true CN206307262U (en) | 2017-07-07 |
Family
ID=59252074
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621409821.1U Expired - Fee Related CN206307262U (en) | 2016-12-21 | 2016-12-21 | A kind of VUAV undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206307262U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108516079A (en) * | 2018-04-18 | 2018-09-11 | 佛山论剑科技有限公司 | A kind of unmanned plane buffering undercarriage |
-
2016
- 2016-12-21 CN CN201621409821.1U patent/CN206307262U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108516079A (en) * | 2018-04-18 | 2018-09-11 | 佛山论剑科技有限公司 | A kind of unmanned plane buffering undercarriage |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109178301A (en) | A kind of fixed-wing rotor mixing unmanned plane | |
| CN207809790U (en) | A kind of unmanned logistics transportation machine of binary | |
| CN107891973A (en) | A kind of unmanned plane support foot rest | |
| CN206307262U (en) | A kind of VUAV undercarriage | |
| CN110803280A (en) | Pure electric manned vehicle | |
| CN101774429A (en) | Small UAV aerodynamic layout for vertical rope-type recovery | |
| CN103803070B (en) | Engineering-type rotary wind type unmanned vehicle | |
| CN205256671U (en) | Screw power balance mechanism for unmanned aerial vehicle | |
| CN205801499U (en) | Flying wing type solar powered aircraft | |
| CN204279926U (en) | A kind of Brattice type multi-rotor aerocraft alighting gear with guide functions | |
| CN204750551U (en) | Transportation class aircraft of all -wing aircraft overall arrangement | |
| CN210284611U (en) | Flying wing layout solar unmanned aerial vehicle | |
| CN112644686B (en) | Tandem wing overall arrangement solar energy unmanned aerial vehicle | |
| CN211055359U (en) | Tail structure suitable for multi-rotor unmanned aerial vehicle and multi-rotor unmanned aerial vehicle | |
| CN108058830A (en) | A kind of unmanned logistics transportation machine of binary | |
| CN204895841U (en) | Be provided with an arm -type main landing gear of buffer | |
| CN202624645U (en) | X-axis structure of aerial photography cloud deck on spacecraft | |
| CN210191820U (en) | Vertical take-off and landing fixed wing unmanned aerial vehicle | |
| CN203593159U (en) | Multi-purpose unmanned aerial vehicle | |
| CN111071463A (en) | Whole layout of full-external hanging type fuel oil storage airplane | |
| CN108791813A (en) | Rear single vortex-spraying type composite wing cargo aircraft with solar energy additional fin | |
| CN203528806U (en) | Fixed wing type unmanned aerial vehicle | |
| CN205872432U (en) | Many rotors of combined material airframe | |
| CN216660278U (en) | Solar sensor unmanned aerial vehicle | |
| CN108791864A (en) | Rear single vortex-spraying type composite wing formula aircraft with solar energy additional fin |
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: 20170707 Termination date: 20191221 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |